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Working Remotely From North BC – Examples
After publishing my first Facebook post on Tumbler Ridge and the opportunities to run an online business, I was asked by a few people to provide examples of companies that I was able to serve or work with at a distance. Below is a partial list of clients that I worked with OUTSIDE of my immediate area. I used phone, fax, email, Skype, Webinars, and remote demos.
- Michael Penner Consulting – A web development company in Visalia, California. Provided a variety of web consulting, design services for close to 20 years.
- CARS Engines – A custom Engine builder in Prince George, BC. Developed and worked on Website as well as marketing race car parts.
- Castaway Boarts – website development to Fort St John based company plus marketing plan and business planning.
- The Heli Farm / Dennis Pedersen – Assisted marketing of business and web site design and management for Spirit River, Alberta based company.
- Haltech Testing – Web site design and development services to Baytree, Alberta company.
- Evocative Inc – Berkeley, California based e-commerce company. Offered a variety of marketing and computer services.
- Regional District of Nanaimo – Business consulting services to Nanaimo based regional Government.
- North Peace Community Resources – Custom design and graphics work + prepress work.
- CarSpots.ca – Provided consulting services to Nanaimo based Audio advertising company.
- Hammer Korp Vending – Logo Design as well as web development, marketing and consulting, Fort St John, BC based business.
- City of Fort St. John – Logo development, web site development and consulting, training and graphic design services in Fort St. John, BC.
- Naughty Biscotti – San Jose, California based company selling Biscotto baking. Worked remotely managing e-commerce store, web consulting, e-commerce services.
- John Lovett – Artist – Australia based Watercolour Artist – Assisted in developing web site development and web site marketing services.
- America Flyers – San Francisco / Honeymoon Bay, California based company requiring web development, e-commerce, marketing of commercial lighting and hanging suspended lamps.
- DreamCatcher Interactive – Toronto, Ontario based Gaming Company. Provided marketing advice, graphic design, web programming, analytics consulting, business advice, budgeting and business planning.
- Mattel Interactive – San Franciso / Novato, California based office providing Marketing Advice, Community building, promotions, online marketing development and planning.
- UbiSoft – San Francisco, California based gaming company. Product development and promotions, community building, fan development and general online marketing services + E-Commerce.
- Asset Protection Corporation – Newport Beach, California – Graphic design, logo development, web site conselting, music / audio consulting. Worked remotely for over 10 years.
- Achex Inc. – Based in Palo Alto / Cupertino, California, provided consulting and web design / coding services for 1 year.
- Andrews Keys Associates – Based in Fairfax, California, provided remote programming services, graphic design, project planning, brainstorming services.
- Pacific Bell – San Diego, California – worked on design advice and web consulting to large telephone company (partnered with AKA firm out of Fairfax, CA.
- CYAN Inc. – Consulting, Community development, adventure gaming to Spokane, Washington based gaming consultantcy / developer.
- Colteran Developments – Fort St John, BC based real estate marketing / development company. Offered design services, online marketing and web development services.
- Ethix Consulting Inc – Fort St John, BC based company offering executive services to small to medium government projects. Logo development to the Oil and Gas Industry as well as consulting on annual report design and publications.
- Back Flow Testing – Worked with Prince Goerge, BC based plumbing startup. Offered design services for graphic design and print media. Also offered business startup advice, web development services and marketing services.
- Threewave Software – This Vancouver, BC based computer game company hired me to build logos, design a website and provide consulting services to CEO and management team.
- Fort St John Child Development Centre – Fort St John, BC, social agency – provided graphic design, consulting on marketing and web development. Also provided training / presentations and ongoing technical support for online projects.
- Timberline Transport – Calgary based trucking company – provided business consulting, marketing advice and graphic design as needed.
- Trustmakers Inc. – Los Angeles, California based financial services company and education leader in asset protection and US based trust work. Provided consulting services, graphic design, computer programming, e-commerce sales consulting and coding.
- Rogers Trucking – Fort St John, BC based trucking company. Provided web site development while partnered with Nortech Data Servcies.
- Nortech Data Services – Fort St John, BC based computer company. Worked on web site development and web consulting.
- Light Harbor Managed Servers – Berkeley, California based computer server / data facility manager. Provided e-commerce consulting, marketing for services and products, and logo development and branding services.
- PaleWriter Publishing – a Michigan based publishing company (Adventure gaming) – provided graphic design and web development services. Business consulting and marketing advice.
- Transferable Skills – Burnaby, BC based training company / website. Provided web development advice, computer graphics and more.
- Springloaded Inc – San Francisco, California based start up company offering email tools. Porvided computer programming, web development services and consulting, marketing services.
- Sentius Corporation – California based technology design firm, developer of RickLink technology. Partnered with AKA, provided graphic design and web development.
- ShadowMan Entertainment – Dana Point, California based entertainement company focusing on country music and the film industry. Provided a variety of services ranging from e-comemrce to online marketing and graphic design.
- Presto Studios – San Diego, California based game company developing products for Mattel / The Learning Company. Porvided web site development, marketing and community development, Flash programming, web site testing, usability consulting.
- Vocal Stream – Los Angeles, California based music programmer – worked on logo development, branding and graphic design with partner AKA from San Francisco, California.
- Latino Info Inc. / El Click – New York, NY based Hispanic web portal – provided consulting services / business advice as well as web development, logo development and more.
- Claremont Strategic Advisors – Newport Beach, California based consulting company in financial services sector. Provided consulting for web development, marketing and other misc services.
- Boris Kleyman Inc. – New York City, NY consulting company specialising in Russian based website for financial services. Web development, community management, branding consulting.
- StockWorm Inc. – Huntsville, Alabama based software development company serving the financial services sector. Web site development, logo development and general marketing consulting.
- British Columbia Fire Chiefs Association – Piers Island, BC based association that managed all Fire Chiefs in the province of BC. Provided consulting services, technology solutions, graphic design, web site design and more.
- Virgin Records – New York City, NY based office for record promotions and marketing. Worked on music project and marketing of album (game sountrack) to fan community.
In over 25+ years I have sold books online, soccer jerseys, advice, trusts, food, chocolate, wine, flowers and at least another 300 products. Now you don't have to keep these products on hand, the majority were dropped shipped or shipped from worldwide locations. There are many opportunities for people wanting to work remotely but not keep stock in their own town or location.
Its also worth noting that many US based firm have no idea where Dawson Creek, Tumbler Ridge, Groundbirch or Chetwynd is. To them, its a subburb of Vancouver, BC.
In a future post, I will provide more details on how business can be run in the north from small towns. And provide services / products to others around teh globe.


text:
21 Olander Drive
Northampton, MA 01060
|Salary Range:
|Job Type:
|Part Time
|Human Services
|Education Level:
|Work Experience:
|Associate Degree
Preference: Required
Preference: Nice to have
|CNAs needed for our Intensive Clinical Group Living Environment
Part-time Positions
We're expanding the services of our 24-hour team at a lovely neighborhood residence for four adults who are in mental health recovery. And we are looking for someone who is eager to apply his or her skills and training to help the people in our program meet their unique health and wellness goals. Compassionate and creative, you are someone who attends to details that can make all the difference in someone's care
• Must be a certified CNA
• Previous experience working with people in mental health recovery is desired.
• Teach and assist program participants with managing activities of daily living, including bathing and other self-care;
• Administer medication, monitor vital signs and visible medical concerns
• Accompany people to their medical appointments.
• Educate and assist with nutritional needs, cooking and shopping
• Provide social interaction
• Collaborate with the team to support participants in achieving their individual goals
• Excellent computer skills and are familiar with electronic medical record-keeping
• Valid Driver's License
We believe in a healthy balance between work and the rest of your life. So in addition to our starting wage of $14/hr and we offer:
• a generous time-off package;
• comprehensive health and dental insurance plans;
• a 403(B) retirement plan, with employer matching;
• Long-term disability benefits; paid life insurance; tuition assistance; and several more benefit options.
Please email your resume and cover letter, and schedule you are interested in, noting Search #340 in the subject line, to firstname.lastname@example.com. We look forward to hearing from you!

subset: commoncrawl


text:
Richard M. Westfall
Galactic Mining Industries, Inc.
Castle Rock, Colorado 80104-7578
ABSTRACT: This paper will describe future spacecraft propulsion systems through the examination of the types of thrusters, sources of energy, energy to electricity conversion, systems configurations and appropriate comparative modeling.
Types of thrusters:
(1.1) Liquid thrusters.
(1.2) Solid thrusters.
(1.3) Solar thermal thrusters.
(1.4) Electric Arcjet thrusters.
(1.5) Electric Single Beam Ion thrusters.
(1.6) Electric Dual Beam Ion thrusters.
(1.7) Warp Drive thrusters.
Sources of energy:
(2.1) Chemical energy.
(2.2) Solar energy.
(2.3) Nuclear fission.
(2.4) Nuclear fusion.
(2.5) Matter-antimatter annihilation.
Energy to electricity conversion:
(3.1) Photovoltaics.
(3.2) Faraday monopolar generators.
(3.3) Fusion plasma direct electrical conversion.
Systems configurations:
(4.1) Solar Thermal Propulsion system description.
(4.2) Photovoltaics powering Arcjet thrusters.
(4.3) Photovoltaics powering Single Beam Ion thrusters
(4.4) Photovoltaics powering Dual Beam Ion thrusters.
(4.5) SP-100 nuclear reactor - Turbine – Generator powering Dual Beam Ion thrusters.
(4.6) Fusion Reactor - Turbine - Generator powering Dual Beam Ion thrusters.
(4.7) Fusion Reactor - Direct Electrical Conversion powering Dual Beam Ion thrusters.
(4.8) Matter-Antimatter Annihilation - Turbine - Generator powering Dual Bean Ion thrusters.
(4.9) Matter-Antimatter Annihilation Warp Drive.
Comparative modeling:
(5.1) Space Shuttle -vs- Dual Beam Ion Craft
Types of thrusters:
(1.1) Liquid thrusters.
Liquid propellant systems such as the Space Shuttle Main Engines (SSME) utilize separate liquid oxidizers and fuels. Liquid propellant systems have the capability to be started, throttled (vary thrust), shut-down, and restarted.
Liquid propulsion systems suffer from inherent constraints imposed by fluid dynamics and propulsion system materials limitations providing limited maximum achievable exhaust velocities on the order of 1500 meters/second.
(1.2) Solid thrusters.
Solid propellants have evolved into composite materials made up of metal powders (fuels), oxidizers, catalysts, binders, curing agents, etc. These composite mixtures are processed into various shapes (pellets, star-core-structures, etc . ) and then cured. Solid propellant systems can be started, but are not able to be throttled, shut-down, or restarted.
Solid propellant thrusters have limited maximum achievable exhaust velocities on the order of 6000 meters/second.
(1.3) Solar thermal thrusters.
Solar Thermal Propulsion (STP) systems are capable of superior performance compared to liquid and solid fuel propulsion systems. An STP system exhaust velocity can be as high as 20,000 meters/second, significantly higher than conventional solid or liquid thruster systems. A higher exhaust velocity allows the use of a proportionately lower exhausted mass flux rate for a given thrust value. The lower the exhausted mass flux rate the lower the fuel mass fraction for the accomplishment of a given mission (impulse). STP systems providing long duration and long distance are suitable for interorbital transfer and maneuvering missions.
STP systems consist of two off-axis elliptical solar reflectors focused to an appropriate solar energy absorber apparatus where a gas such as hydrogen is superheated and expelled at high velocity providing thrust. The reflectors are mounted on reflector mounting rings which can rotate 360 degrees, The reflector mounting rings are mounted to a receiver assembly which can rotate 180 degrees. The solar energy absorber is within the receiver assembly. Through the rotation of the reflectors about the receiver assembly, and the rotation of the receiver assembly, solar radiation is continuously focused on the solar energy absorber. In order to specify the components of the STP system, each concern will be addressed individually.
1. Reflector and reflective surface:
Seamless, goveless, accurately-contoured plastic reflectors made of polyimide under development by SRS Technologies of Huntsville, Alabama promise to be suitable for service as reflectors in the STP system. SRS is using polyimide with glass transition temperatures between 220 degrees C and 263 degrees C, compatible with the temperatures encountered in Chemical Vapor Deposition (CVD) coating techniques for aluminum and other metals used in producing the reflective surface.
The reflective surface of the mirror can be applied to the reflector in space through the use of Chemical Vapor Deposition (CVD). Aluminum and alloys of aluminum are deposited through the thermal pyrolysis of aluminum alkyls and other gases which come in contact with the solar-heated reflector surface. Deposition of aluminum at 220 degrees C yields aluminum of 111 crystal structure, grain size near 1 micron,. and >50% reflectance. Improvements in the reflective surface can be achieved through control of deposition rate and conditions, application of optical reflection coatings, deposition of silver onto the aluminum, or other method. A metal reflective surface provides superior reflector performance and rigidizes the inflated mirror surface, alleviating the need for make-up inflatant over time. Special composition materials can be deposited through incorporation of other metal containing species in
the gas stream of the CVD system.
2. Torus and support structure:
The reflector is mounted on the torus and support structure such that the mirror focuses solar radiation into the receiver to the solar energy absorber. An inflatable torus and support structure can be fabricated with kevlar-weave teflon laminate materials. Upon deployment, the torus and support structure would have nickel carbonyl introduce. Solar radiation exposure heats the inflatable, causing pyrolitic deposition of nickel metal on the inside of the inflatable, rigidizing it to produce load-heaving capacity, high-rigidity and high-pointing-accuracy.
3. Gimbaling receiver assembly:
The gimbaling receiver-assembly is made up of the receiver housing, the reflector mounting ring rotation systems, and the rotation system that mates from the receiver housing to the spacecraft. The receiver mechanically points the reflectors to maintain solar energy focus on the solar energy absorber.
4. Solar energy absorber:
The solar energy absorber produces superheated hydrogen with the heat from the absorption of
focused solar energy. Small capillary metal-matrix heat transfer elements may be useful in the construction of solar energy absorbers. To produce these metal-matrix elements entails the following steps: Impregnate and saturate a bundle of organic-fibers with nickel metal, or an alloy to produce a metal-matrix / organic-fibers structure. This structure is heated and the organic fibers are melted or burned out to produce a solar absorber with open micropore tubules. Frit assemblies with capillary micropores fabricated in this manner could be useful in the construction of a suitable solar energy absorber.
5. Pointing and navigation system: In order for the reflectors to remain focused on the solar energy absorber at all times, the navigation and sun sensing and pointing systems must be integrated in real-time. Upon change in attitude to the sun the receiver mechanism will make suitable adjustments to maintain solar radiation pointing accuracy.
(1.4) Electric Arcjet thrusters.
Arcjet thrusters involve the superheating of gases passing through an electrical arc and can be started, throttled, shut-down, and restarted. These thrusters have maximum achievable exhaust velocities on the order of 20,000 meters/second. Arcjet thrusters have recently been chosen for orbital maintenance service on communications satellites.
(1.5) Electric Single Beam Ion thrusters.
Single beam ion propulsion systems accelerate a flux of positive-ions through negatively charged electrical grids and can be started, throttled, shut-down, and restarted. Ion propulsion systems based on single beam ion thruster configurations have to date only been capable of providing satisfactory performance in low thrust missions, generally with exhaust velocities less than 10,000 meters/second. Maximum achievable exhaust velocities are limited by the emission velocities achievable with hollow cathode emitted electron velocities. Exhaust velocity is proportional to the square root of the accelerating voltage, and so the required electrical power levels increase as the square of the exhaust velocity. Ion propulsion has been unable to provide the levels of thrust required to be considered for the role as primary propulsion systems, due to the lack of suitable ultra-high power/mass ratio power supplies. Ion propulsion has been examined both theoretically and experimentally since the 1950's. Past experimental thrusters have been of the metallic ion class, mercury (Hg), or cesium (Cs), or the noble gas variety xenon (Xe). These thrusters have been of the single beam configuration, as opposed to the Dual Beam Ion (DBI) configuration described herein. Single beam thrusters, of the metallic class, exhaust poisonous metal vapors. Single beam thrusters, of the noble gas variety, exhaust rare gases with limited availabilities.
Passive Neutralization Systems:
Passive Neutralization Systems (PNS) encountered on single beam ion propulsion systems are used to neutralize the positively-charged ion beam exhaust through contribution of electrons, producing a neutral-charge exhaust of high velocity vapor. Passive neutralization is achieved through various mechanisms such as: thermionic emission (hollow cathode), or through positive-ion collisions with an electron contributing Cathodic-Neutralizing-Screen (CNS). Thermionic emission neutralization systems maintain spacecraft charge neutrality through the thermal emission of electrons into the positively-charged ion stream to produce neutral ion species. Ultimate Exhaust velocity is limited to the thermionic emission velocity of the electrons. Cathodic-Neutralizing Screen (CNS) neutralizing systems maintain spacecraft charge neutrality through the collision of positive-ions with a negatively charged grid. Exhausted mass flux rates are limited by the constricting neutralizing grid's presence in the exhaust stream. CNS lifetime is limited by damage caused through the collision of positive-ion flux with the neutralizing grid.
(l.6) Electric Dual Beam Ion thrusters.
Ion propulsion systems of the Dual Beam Ion (DBI) configuration, powered by ultra-high power/mass ratio power supplies, can theoretically provide service as primary propulsion systems for vehicles launched from
Earth into space. DBI propulsion systems exhaust environmentally safe water.
Primary propulsion systems are capable of launching spacecraft into orbit from the surface of the Earth.
Ultra-high power/mass ratio power supplies are possible with the advent of superconductivity, and more
specifically the advent of high temperature superconductivity. Superconducting Dual Beam Ion Thrust
systems will be described herein, in comparison to liquid propulsion, solid propulsion, and classical
single beam ion propulsion systems.
Active Neutralization Systems:
Active neutralization distinguishes the Dual Beam Ion thrusters from the single beam ion thruster passive neutralization systems. Active neutralization involves side-by-side oppositely charged ion beams with equivalent exhaust velocities and stoichiometrically balanced charge fluxes. The Dual Beam Ion (DBI)
proton (+) - oxygen (-2) thruster configurations examined produce environmentally safe water as the exhaust. DBI propulsion systems are theoretically able to deliver the large thrust levels required for service as primary propulsion systems.
High power/mass ratio power supplies:
Ion propulsion systems have historically been unable to perform as primary propulsion systems for spacecraft due to the lack of sufficiently high power/mass ratio power supplies with dedicated ion primary propulsion programs of theoretical modeling and experimental development considered unfruitful.
Fortunately, with the advent of superconducting and other technologies theoretical models of machines with remarkable new levels of power/mass ratio are conceivable. Energy sources such as fusion and matter-antimatter annihilation may be realized within the foreseeable future due to the level of technical advancement in the various technologies. Described within are theoretical models and calculations which
indicate that quite favorable results can be achieved through utilization of ultra-high power/mass ratio power supplies and Dual Beam Ion (DBI) thrusters.
Dual Beam Ion (DBI) propulsion systems consist of a positively charged proton (H+) beam and a negatively charged oxygen (O-2) beam, dual accelerator configuration. Dual Beam configuration promotes charge neutrality for the craft and specifically, proton (H+) – oxygen (O-2) beams are chosen due to environmental concern for a non-toxic exhaust. Spacecraft charge neutrality is maintained when beam currents are equivalent, resulting in stoichiometric water (H2O) exhaust. Recombination of oppositely charged beams, yields water under normal operations. For asteroid mining operations, or for military weapons use, individual beams with different exhaust vectors, which do not collide and recombine can be used as beam mining tools in outer space, or as formidable beam weapons able to dissect all materials.
Accelerators of both varieties are similar in design and operation. Operation is that of linear electrical acceleration of ions, which are axially focused into a coherent pencil beam by use of an axially applied magnetic focusing field. Lengths of the respective accelerator beams are designed such that the beams can be operated in the earth's atmosphere, and if operated correctly even started in atmosphere.
Paschen's rule for dielectric breakdown in gaseous media yields for the earth's atmosphere about 300,000 volts/meter as the minimum expected Breakdown Voltage Separation Product (BVSP). For a proton (H+) accelerator voltage of 3*105 volts, an accelerator produced exhaust velocity of 7.57*10+6 meters/second results. This type of dramatic increase in exhaust velocity is the main advantage of ION PROPULSION - ACTIVE NEUTRALIZATION SWEETENS THE RESULTS BY REMOVING LIMITATIONS OF EXHAUSTED MASS FLUX RATES. Additionally, for an oxygen (O-2) accelerator voltage of 4.15*106 volts, an accelerator minimum length of 13.8 meters is required.
Atmospheric Startup Sequencing
The desire for use of DBI propulsion systems as primary propulsion orbit achieving systems, leads to the requirement for atmospheric startup, throttling, shutdown and restart capabilities.
Sequencing for atmospheric startup involves the steps:
1. Begin by flushing the individual accelerator tubes with high molecular weight molecules, such as carbon
halides (mostly fluorides), which have markedly higher molecular weights, and so markedly higher dielectric breakdown values when compared to normal atmospheric constituents.
2. Initiate low current axially magnetically focused ion flow in both accelerators. High molecular weight
species provide catastrophic breakdown protection during low current initial flow of ions. Such low current initial ion flow creates an evacuation effect, due to the extremely high 7*106 meters/second, (in the case of the CORRECTION UNDERWAYnewtons thrust specification) exhaust velocity of the ion flow. Under proper operating conditions, the ion flow flushes out the breakdown protection gas and ambient atmosphere. The thrusters once started hinder the re-entry into the tube of ambient atmospheric gas species.
3. Current density for the ion beam may be increased in unison with the axial magnetic focusing field to their maximum values after the high molecular weight dielectric protection gas and any other unwanted initial gaseous constituents have been evacuated by the low current initial ion beam flux. Catastrophic dielectric breakdown phenomena can of course be extremely destructive, and must be avoided by careful design and operation. Startup in atmosphere must be approached with great care and diligence in the correct sequencing of startup events.
Breakdown Voltages for Various Gases
Utilizing the following equations;
Paschen's Law U(br) = p*h = 5.67*(mm Hg)*mm,
U(br) = breakdown minimum product,
p = pressure (mm Hg),
h = separation of electrodes (mm),
U(br) = d*U(bro) = 0.386*(p/K)*U(bro),
U(bro) = minimum breakdown voltage at STP (standard temperature and pressure, 20 degrees celsius, and 760 mm Hg),
d = density (g/cc),
K = temperature (degrees kelvin),
Utilizing Paschen's law, the following examples of
Minimum breakdown voltages are provided;
p * h
air 70%N2 - l4%O2 - etc. 326 volts
hydrogen H2 195 volts
helium He 19 volts
carbon dioxide C02 293 volts
420 volts
neon Ne 85 volts
argon Ar 137 volts
elegas SF6 146 amu 815 volts
freon 12 CCl2F2 120 amu 847 volts
perfluoromethylcyclohexane C7F14 350 amu 1956 volts
perfluorodibutylether C8F180 54 amu 2445 volts
perfluorodimethylcyclohexane C8F16 400 amu 2771 volts
perfluorophenatrene C14F24 624 amu 3260 volts
Dual Beam Ion propulsion systems calculations:
Calculations of relative performance and specification are presented which are usable in the comparison of STS class craft and DBI class craft. Calculations involving impulse, thrust, energy density, etc., are developed with STS class craft used as the baseline in order to develop understandable performance
Dual Beam Ion propulsion systems developing thrust levels equivalent of STS class craft initial pad lift off thrust are examined. In such modeling the initial pad mass of the DBI class craft is set to be equivalent to the initial pad mass of the STS class craft.
Dual Beam Ion propulsion systems developing thrust levels equivalent to lesser thrust values which are comparable with the various types of thrusters encountered on STS class craft are also set forth.
In order to compare Dual Beam Ion (DBI) craft primary propulsion system performance with that of Space
Shuttle (STS) craft primary propulsion system performance, we shall begin by using the initial lift off thrust level developed by the 3-Space Shuttle Main Engines and 2-Solid Rocket Boosters in unison, 2.84*107newtons, as the initial lift-off thrust level developed by the Dual Beam Ion propulsion system.
In order to examine other thrust levels, comparison with the other types of thrusters encountered on STS class craft, as well as levels of thrust applicable to future large interplanetary craft is provided.
DBI Calculations
The following derivation is provided, which is of interest in understanding the DBI propulsion system.
T = (dx/dt)*(dm/dt) = thrust,
t = duration of thrust,
dx/dt = exhaust velocity,
dm/dt = exhausted mass flux rate,
I = T*t = impulse,
I(H+) = proton beam current,
I(O-2) = oxygen Seam current,
I(H+) = I(O-2) criteria for craft neutrality,
U(H+) = proton beam acceleration voltage,
U (O-2) = oxygen beam acceleration,
voltage, U(total) = U(H+) + U(O-2) = total acceleration voltage
Classical calculations of acceleration voltages;
U*q = 1/2(m)*(v)2,
U = acceleration voltage,
q = charge,
q(unit) = 1.6021892(46)*10-19 coulombs,
faraday constant 96,484.56(.27) coulombs/mole electrons,
avogadro's number = 6.022045(31)*1023 particles/mole,
m = mass of ion,
v = resultant velocity of ion,
Relativistic calculations of accelerations voltages;
U*q = (m0 )*(c)2* [(((v 2)*(c-2 ))-0.5)-1 ],
mO = rest mass of ion,
m0(H+) = 1.6737503*10-27kilograms,
m0(0-2) = 2.6568051*10-26kilograms,
c = speed of light = 2.99792458*108 meters/second = 9.835690893*108 feet/second = 3.540848721*1012 feet/hour = 6.703613634*108 miles/hour = 1.862114898*105 miles/second,
dm/dt (H+) = [I(H+)(coulombs/second)] * [1.0446644*10-8(Kg/coulomb)],
dm/dt (O-2) = [I(O-2) (coulombs/second)] * [8.2911706*10-8(kg./coulomb)],
dm/dt (total) = I*9.335835*10-8(Kg/coulomb),
1Kilogram is exhausted with the passage of 1.071141467*107(ampere-seconds),
(1.7) Warp Drive thrusters.
Warp-Drive thrusters are likely to involve some form of warping of the space-time around a vessel. This would involve the expansion of space in front of a ship and the contraction of space behind a ship. Unified Field Theory must develop further to be able to theoretically understand how this can be accomplished. In all likelihood, it will involve energy on the order of what you can achieve by matter-antimatter annihilation reactions. In the future, we may be able to "fall" forward and experience "warp-drive" propulsive capabilities. I certainly hope this is true.
In light of the need to at least model the current ultimate in propulsion technology, I would like to suggest a psuedo-warp-drive capability by using a photon push drive. A Gamma Radiation Push type drive will have an exhaust velocity of the speed of light (c), 300,000,000 meters/second. This type of thruster has the ultimate in exhaust velocity and is able to provide the ultimate in performance with the (4.54*12) 4,540,000,000,000 watt-hours/kilogram matter+antimatter annihilation energy density.
Matter+antimatter (proton and anti-proton) annihilation produces gamma rays which are focused by a superconductive reflecting contour into a collimated beam, whereby thrust is derived. Reflection can be optimized by utilization of glancing incidence configurations with multiple glancing reflections resulting in minor losses and an organized common exhaust vector beam of gamma rays.
Sources of energy:
(2. 1) Chemical energy.
Chemical reactions as sources of energy are listed below. Energy densities are too low for consideration as energy sources for primary propulsion systems using electric thrusters such as the Dual Beam Ion thrusters described herein.
Chemical Energy Source Energy Density
1. Ni-Cd batteries 7.7
2. Ag-Zn batteries 36.3
3. H202 decomposition 231.5
4. Gasoline-air 571.5
5. H2 + Cl2 = 2HC1 698.8
6. Hydrazine airbreathing systems 1,127
7. 2Li + F2 = 2LiF 1,343
9. 2H2 + 02 = 2H20 internal oxidizer 3,660
11. Si + 2F2=SiF4 4,027
13. 4Al + 3O2 = 2Al2O3 4,543
15. 2H = H2 nacent hydrogen recombination 12,247
16. H2 airbreathing systems 32,700
17. Nacent H recombination & airbreathing oxidation 45,000
Conventional oxidation is able to provide up to near 3.66*103 watt-hours/Kg for hydrogen and self-contained oxidizer, 3.27*104 watt-hours/kg for airbreathing hydrogen systems, with the possible future development of nacent hydrogen storage and recombination providing an additional 1.2*104 watt-hours/kg. The storage of nacent hydrogen is done in a magnetic containment vessel. Hybrid utilization of the energy released by the airbreathing oxidation of hydrogen and the energy released by the recombination of nacent hydrogen summed together, produces the highest energy density achievable with conventional systems, near 4.5*104 watt-hours/kg .
(2.2) Solar energy.
Solar radiation is useful in Solar Thermal Propulsion systems and photovoltaic to electricity conversion. Solar radiation intensity at the average distance from the sun to the earth (150,000,000
kilometers) is on the order of 1,400 watts/meter2. Relative distances closer and farther away from the sun have higher or lower solar radiation intensities, respectively.
(2.3) Nuclear fission.
Nuclear fission may be useful in space, with continuing investment in the SP-100 nuclear reactor of the DOD, DOE, and NASA. There may be environmental impact risks which will forever make this option just a dream. These energy-densities are included as food for thought.
Energy Source Energy Density
1. Pu plutonium fission cycle 13,600,000
2. U uranium fission cycle 4,500,000,000
(2.4) Nuclear fusion.
Nuclear fusion is potentially clean, with sufficient energy density to be useful as a source of energy for electric thruster primary propulsion systems.
Fusion Energy Source Energy Density
1. D + D = 3He + neutron fusion cycle 21,600,000,000
2. Fusion published estimate 22,700,000,000
3. D + D = T + H fusion cycle 26,590,000,000
4. 6D = 2(4He) + 2H + 2neutrons 31,800,000,000
5. D + T = 4He + neutron 93,580,000,000
Fusion reactor research has centered on magnetic confinement and laser confinement techniques in the past. Examination of various experimental results are illustrative of a new potential approach involving inertial confinement.
In research involving fusion of super-heavy nuclei, it has been found that to form a nucleus of 110 amu, two nuclei of 55 amu can be made to collide. The two 55 amu nuclei must possess the correct momentums, in other words , not too hot and not too cold. Collision at the correct momentum allows the two 55 amu nuclei to overcome the coulomb repulsion so that the strong nuclear force can bind them, forming a 110 amu nucleus. The 110 amu nucleus is very unstable and can only be formed through collision of two 55 amu nuclei at the correct momentums for the 110 amu nucleus to be formed, yet be cool enough to be stable, with fissile decay retarded. Light nuclei with less than 26 protons (iron) inherently are more stable than nuclei with more than 26 protons, and so fusion of light elements is expected to be easier than the fusion of unstable nuclei of greater mass.
Examination of typical particle velocities in magnetic confinement plasma fusion systems reveals a bell or gaussian distribution, with many nuclei too cool and a few nuclei too hot. Ideal conditions would involve nuclei with all the correct momentums, where cool nuclei don't quench the fusion reactions, and where hot nuclei don't cause fissile instabilities. Neutral Beam Injection (NBI) has achieved same success as a technique for modifying the velocity distribution in magnetically confined-plasma fusion experiments. Neutral Beam Injection into magnetic confinement systems has been shown to increase the number of hot nuclei, shifting the velocity distributions, producing plasmas where we are closer to fulfillment of the fusion breakeven point (Lawson criteria).
Conventional magnetic confinement plasma fusion systems suffer from a lack of particle energy and motion uniformity, with particles moving in all of the conceivable 4pi steradians of vectors. Colliding beam configurations can provide inertial confinement at a focus with vectoral cohesion of motion of particles.
Potential colliding beam configurations include:
2-beams - head-on collision at a focus (one-dimensional confinement),
3-beams - 120 degrees apart in a plane with collision at a focus (two-dimensional confinement),
4-beams - three-dimensional tetrahedrally oriented collision at a focus (three-dimensional confinement),
6-beams - three pairs of two head-on colliding beams (three-dimensional confinement).
Only the last two options involving 4-beams or 6-beams provide three-dimensional inertial confinement.
The tetrahedral 4-beam orientation requires significantly greater beam currents than the 6-beam
configuration, due to the desirable head-on collision nature of the 6-beam configuration, For purposes of
specifying a system only the 6-beam, lower beam current, configuration will be considered here. Whether
6-neutral beams or 6-positively charged ion beams and 4-negatively charged electron beams are used must depend upon a more in-depth theoretical analysis of the two configurations. (see illustrations of the two types of 6-beam configurations) The collision of beams at a focus, due to the effect of space charge, reduces the effective coulomb repulsion of nuclei to be fused, and so promotes fusion reactions.
In conventional plasma fusion systems of the deuterium + deuterium = helium4 variety, a detrimental
neutron flux is generated. This is due to the unstable nature of a helium4 with 24MeV, which undergoes fissile decay to he!ium3, a neutron, and 3.25MeV of residual energy. In order to control this detrimental neutron flux, the use of neutron-deficient mixed deuterium/hydrogen beam currents will promote the
formation of helium3, and minimize the formation of the unstable helium4 species.
Continuous operation of inertial confinement systems such as the 6-beam configurations, is desirable
to minimize excessive thermal and pressure cycling as is found in pulsed operation systems. The continuous energy production of the inertial confinement systems is compatible with the two, energy to electricity conversion systems, described in sections 3.2 and 3.3.
Poly-well magnetic confinement and electrostatic well confinement (Dr. Robert W. Bussard, EMC2) are also research areas deserving of consideration.
(2.5) Matter-antimatter annihilation.
Matter+antimatter annihilation has the highest energy density of all known energy production systems. The production and storage of antimatter is at the present time very expensive, and difficult to perform,
however technical understanding is improving and it can be expected that technical barriers will be overcame as research continues. Production of antimatter by collision of accelerated beams with metal foils is currently underway, with advanced techniques involving impingement of gamma-rays on certain metal crystals expected to be a practical antimatter production method in the future. The listed energy density is intended to provide an idea of the magnitude of achievable energy densities.
Matter+Antimatter Annihilation Energy Source
Energy Density
1. Matter+Antimatter annihilation 4,540,000,000,000 (4.54*1012)
Matter-antimatter annihilation energy production can either power energy to electricity conversion systems such as described in section. 3.2, or can be used in warp drive propulsion systems as described in section (1.7).
Energy to electricity conversion:
(3.1) Photovoltaics.
Photovoltaics, also known as solar cells, are solid-state devices which convert solar radiation to D.C. electricity. Photovoltaics are made of materials such as silicon, gallium arsenide, and other semiconductors. Photovoltaics have no moving parts and can be expected to have useful lifetimes in space of from 5 years to 50 years, depending on the materials and methods of fabrication.
Photovoltaic radiant solar energy to D.C. power conversion efficiencies are in the range of 10% to 41% (theoretical), depending on the type of device. AM0 (air mass 0) insolation (solar radiation intensity in earth's orbit around the sun) is near 1400 watts/meter2, with the average distance to the earth from the sun being 149,476,000 kilometers. Relative distances closer or farther from the sun will have greater or lesser insolation values, and thus power generation densities. Assuming a location near earth's solar orbit distance, and an efficiency of 30%, yields a required collector area of near 2,380 meter2/megawatt generation capacity. Solar energy is incapable of providing suitable energy densities to be considered as a primary, earth orbit achieving, power supply. Importance in outer space operations, is significant, with electric thruster systems requiring DC power.
(3.2) Faraday monopolar generators,
Faraday monopolar generators are chosen to convert shaft torque into electricity in ultra-high power/mass ratio power supply configurations. Faraday monopolar generators have been used as pulse power generators in high-current applications such as thermal-pulse welding, and defense department research programs. The Center for Electromechanics at the University of Austin, Texas has been involved in these programs for many years.
Faraday monopolar generators consist of a disc armature rotor, which spins in an axially oriented magnetic field. For a disc armature rotor spinning clockwise (looking from above) in the horizontal plane and magnetic north oriented upwards, the outer edge of the spinning disc armature rotor will be negative (-),
with the rotational axis positive (+). Faraday monopolar generators operating in continuous-mode
provide D.C. current with no ripple in voltage, making them compatible with superconductors. Superconductors exhibit markedly lower critical current densities and critical magnetic field strengths in the presence of varying electrical and(or) magnetic fields. Conventional D.C. electrical generators exhibit ripple
in the D.C. wave form due to such things as magnetic field non-linearities and discontinuities in current
collection brush assemblies. In order to produce the ultimate in superconducting ultra-high power/mass ratio power supplies, variances in voltage waveform must be eliminated and faraday monopolar generators exhibit the purest D.C. waveforms conceivable from rotating machines. Another reason why Faraday monopolar generators are excellent candidates for service as ultra-high power/mass ratio power generators is due to the ability to build machines with a minimum of stray magnetic flux.
Considerations involved in the design of Faraday monopolar generators are dealt with in the following sections.
(3.2.1) Faraday disc armature rotor:
A Faraday disc armature rotor spins in an axial magnetic field and through the cross product of the
magnetic field and the Faraday disc armature rotor's velocity vector, voltage is generated between the edge
and the axis of the Faraday disc armature rotor.
The Faraday disc armature rotor is a normal conductor and not a superconductor as the Meissner
effect would exclude magnetic field and prevent voltage generation. Joule heating of the Faraday disc armature rotor due to the flow of current will require advanced active cooling methods in order to maintain acceptable Faraday disc armature rotor temperatures. The Faraday disc armature rotor is a metal/graphite-fiber matrix, in order to provide high-conductivity, high-strength, and controllable coefficient of thermal expansion.
(3.2.2) Current Collection Systems:
Conventional brush current collection systems have limited rubbing speeds (listed below) and so are not
useful in Faraday monopolar ultra-high power/mass ratio generators. For a 5 meter diameter Faraday disc
armature rotor spinning at 30,000 rpm, the effective rubbing speed would Se 7,854 meters/second,
significantly greater than the 100 meters/second rubbing speeds possible with conventional brush current
collection systems.
In order to circumvent this restriction, a non-rubbing current collection system where electrons
are emitted from the outer edge of the Faraday disc armature rotor and collected by an anodic electron counter electrode ring is described. With the configuration described above, the outer edge of the Faraday disc armature rotor is negative (-). Emission of electrons from the outer edge of the disc is achieved through a hybridized approach involving:
(22.214.171.124) Laser induced photoemmision from low work-function materials such as:
1. Cesiated (exposed to cesium) surfaces of semiconductors such as Gallium Arsenide.
2. Oxides of the low work function elements, such as those of IIA, IIIB, lanthanides, actinides.
(220.127.116.11) Electric field emission from low work function materials such as those listed in (126.96.36.199).
(22.214.171.124) Centripetal acceleration (inertial) forces.
(22.214.171.124) High-strength magnetic field at the Faraday disc armature rotors outer edge.
High-current operation will require advanced active cooling of the emitting surface at the outer edge of the
Faraday disc armature rotor and advanced active cooling of the anodic (electron collecting) counter electrode ring around the circumference of the Faraday disc armature rotor.
Current collection at the rotation axis (the positive (+) pole) can be accomplished through similar methods or through the use of liquid metal brush assemblies.
Conventional brush current collection systems performance limits:
300 KA/m2 @ 40 meters/second solid carbon-copper.
900 KA/m2 @ 100 meters/second carbon fiber.
? KA/m2 @ 220 to 250 meters/second for liquid brushes.
(3.2.3) Rare earth magnets:
Rare earth magnet discs are placed above and below the rotating Faraday disc armature rotor and provide the initial magnetic field for phase one of the start-up procedure of the Faraday generator. the magnetization
is axial in these rare earth magnets.
High energy product (BHmax, B in gauss, H in oersteds) rare earth magnets are becoming common in
everything from sound speakers, demonstration kits for superconductors, stepping motors, generators, almost any application conventional magnets find use.
The major categories of rare earth magnets are described below:
1. R(M)5, where R is an element or a mixture thereof, from the rare earths (for example, Pr, Y, Sm, La, Ce, etc.], IIIB, lanthanides.
M is an element or a mixture thereof, from the group of elements known as ferro elements(Fe, Co, Ni, sometimes Mn).
R(M)5 – SmCo5 is the most common of the rare earth magnets commercially produced presently.
2. (R)2(M)14(IIIA)1, where R is an element or mixture thereof from the lanthanides.
M is an element or a mixture thereof, from the group of elements known as the ferro elements (Fe, Co, Ni, sometimes Mn).
IIIA is in most cases Boron, however, Aluminum is a possible component of a mixture.
(R)2(M)14(IIIA)1 - Nd2Fe14B1 is the best known example of these magnets, with energy products of up to between 56 and 80 (rumor) million gauss-oersteds.
Research in Japan indicates replacement for Nd by partial fractions of Dy, and Tb results in increased energy products. It can be noted, Dy and Tb have much greater susceptibilities in the elemental state than Nd. This can be explained through the examination of field pinning mechanisms in these materials, seeming to imply the ultimate density of magnetic flux quanta which can be stored is related to the magnetic susceptibility of the rare earth component. Pinning is also assisted by the mixing of elements on a specific site, in other words, a certain fraction of Co and (or) Ni in the Fe vacancy may be added to the ternary in order to achieve higher retained magnetic field intensities.
(3.2.4) Superconducting magnet coils:
Superconducting magnet coils provide the high-strength magnetic fields for full-power (phase 2 power-up) operation of the Faraday monopolar generators. The superconducting coils are made of high-temperature superconducting materials such as yttrium barium copper oxide or bismuth strontium calcium copper oxide. The superconductors are refrigerated with solid-state thermoelectric cryo-sheathing (see section 3.2.7) to below the superconductor's critical temperature during phase-1 of the power-up sequence and during continuous operation of the Faraday monopolar generator.
Hoop stresses during phase-2 of the power-up sequence and during continuous operation can be alleviated through the use of coils made up of segmented multiple axially oriented superconducting sections attached end-to-end with flexible superconducting connections (see section 3.2.5). Segmented coil windings lend themselves to maintenance activities, repair activities and overall machine reliability.
(3.2.5) Superconductive flexible connections:
High-temperature superconductors suffer from brittle fracture limitations and must be connected by superconductive flexible connections in order to alleviate hoop stresses developed during power-up and
during continuous operation of Faraday monopolar generators. Superconductive flexible connections are
composed of dendrites or fibers of high-temperature superconductor embedded in a matrix of conductive polymer and provide means for accommodation of hoop-stresses produced by mechanical, thermal,
electrical and magnetic loads and variations.
Fabrication of flexible superconductive connections is done by embedding longitudinally oriented superconductive dendrites or fibers in a matrix of conductive polymer (such as polyacetylene). For example, the superconductive dendrites or fibers have an aspect ratio of 10:1, with 1 micron diameter and 10 microns length. The dimensional variances of the superconductive coils are tolerated through the relative
movement of the superconductive dendrites or fibers within the flexible polymer conductive matrix.
The refrigeration (and resultant dimensional contraction of the polymer matrix) of the flexible superconductive/polymer matrix to below the critical temperature of the superconductive fibers results in intimate contact along the superconducting fiber's outer longitudinal surfaces, providing conductive paths.
The conductive polymer matrix has a greater coefficient of thermal expansion than the superconductive fibers.
Thermal excursions above the critical temperature of the superconductive fibers cause the expansion of the
conductive polymer matrix, protecting the superconductive magnet coil through discontinuation of intimate contact between the superconductive fibers.
In the normal conducting state the superconductive fibers have poorer bulk conductivity than the conductive polymer matrix, so during cool down but above the critical temperature of the superconductive fibers, the current is shunted through the conductive polymer matrix. Upon reaching, and below the critical temperature of the superconductive fibers, the current is shunted through the superconductive fibers held in intimate contact. Conversely, as a thermal excursion occurs from below to above the critical temperature, the conductive polymer matrix expands, the superconductive fibers discontinue intimate contact, and the current is shunted through the conductive polymer matrix. The ability to shunt current through the conductive polymer matrix reduces the damage caused by joule heating of the flexible superconductive connection above the critical temperature of the superconductive fibers.
(3.2.6) Superconductive magnetic shaft bearings:
Superconductive magnetic shaft bearings are used in the construction of rotating machines such as Faraday
monopolar generators and turbines. Superconductive magnetic shaft bearings allow rotation of a shaft without frictional wear or losses associated with conventional bearing assemblies.
(3.2.7) Thermoelectric cryo-sheathing
Thermoelectric solid-state refrigeration is chosen to cool the superconductors in ultra-high power/mass
ratio power supplies. Thermoelectric cryo-sheathing of superconductors may be an ideal method of providing reliable service, supplementing conventional liquid and gaseous refrigeration systems.
Thermoelectric solid-state devices are made up of multiple stage alternating p-type/n-type semiconductor
junctions . With current flow in one direction heating occurs and with current flow in the opposite direction
cooling occurs.
Thermoelectric devices have been able to provide cooling to 140 degrees Kelvin, and with further research, temperatures below the critical temperatures of high temperature superconductors is expected.
(3.2.8) Housing, shielding and internal supports:
The housing assembly of the Faraday Monopolar Generator provides mechanical support for mounting in the vessel or spacecraft, acts as the magnetic field containment shielding, and provides mechanical support
for internal assemblies such as rare earth magnets, superconducting magnet coils, superconducting bearings,
and current collection assemblies.
Magnetic Field Containment is achieved by means of diamagnetic materials such as bismuth (Bi) metal for
rare earth magnetic field containment, and superconducting materials for superconducting coil
high-strength magnetic field containment. During periods of inoperation, and during phase-1 of the start-up sequencing, the diamagnetic bismuth lining of the housing acts to contain the magnetic field of the rare earth magnets. During phase-2 of start-up sequencing and during full-power operation of the Faraday monopolar generator the superconductive lining of the housing supplements the diamagnetic bismuth layer, containing the combined rare earth magnet and superconductive coil magnetic fields. The superconductive lining of the housing is cooled to below the critical temperature during phase-1 of the start-up sequencing, and is maintained at temperatures below the critical temperature during full power operations.
Toroidal-contour housing curvature provides optimal magnetic flux-line/housinq-surface incidence, such that magnetic field containment is optimized. Superconductors, such as the superconductive lining of
the housing, exhibit two critical magnetic fields, Hc2 the critical magnetic field intensity for normal (into
the surface) flux-line/surface incidence, and Hc3. the critical magnetic field intensity for glancing (parallel
to surface) flux-line/surface incidence.
Flux-line/surface glancing incidence critical field intensity Hc3 (Hc3=Hc2*1.69) is near 1.69 times the
flux-line/surface normal incidence critical field intensity, Hc2.
(3.2.9) Start-up sequencing and operational description:
Faraday monopolar generator start-up sequencing involves two phases. Phase-1 begins with rotation of
the Faraday disc armature rotor in the permanent magnetic field of the rare earth magnets, generating sufficient electricity to power the thermoelectric cryo-sheathing which cools the superconductive electromagnet coils and the superconductive magnetic field containment lining of the housing. When the superconductive materials are cooled to below the critical temperature, phase-2 begins with the power-up of the superconductive electromagnet coils, and the resultant increase in output voltage to full-power levels.
Full-power operation involves the rotation of the Faraday disc armature rotor(s) in the cumulative magnetic field of the rare earth magnets and the superconductive magnet coils, with the resultant current flow through the current collection assemblies, and the full power output of ultra-high power levels of D.C. current and voltage.
(3.3) Fusion plasma direct electrical conversion:
Fusion Reactor Direct Conversion (FRDC) technology capable of harnessing the energy produced in fusion
plasmas involves the utilization of magnetic separation techniques. Magnetic separation in this system involves deflection of the negatively charged (-) electron cloud and the positively charged (+) ionic cloud, such that each impinge on separate electrodes. Deflection is accomplished by slowly decreasing the focusing axial magnetic flux intensity the exhausting fusion plasma experiences on the way cut of the Vacuum Exhaust Port (VEP) of the fusion reactor. Deflection of the exhausted electrons is more severe and the electron cloud is seen to lie in a large diameter ring distribution where the Cathodic Electron Collecting Electrode (CECE) is positioned. Positively charged ions maintain a straighter trajectory, being deflected to a much lesser degree than the ring like electron cloud, because of a positive ions inherently larger inertial mass than an electron. The central positive ion cloud impinges upon the Anodic Ion Neutralization Electrode (AINE), are neutralized, and continue out of the Vacuum Exhaust Port (VEP) into space. The spatially differentiated ring cloud of negatively charged electrons and the central cloud of positively charged ions impinge on their respective electrodes, developing a potential difference which drives current through the load circuitry.
The negatively charged electrons impinge on the Cathodic Electron Collection Electrode (CECE) and are absorbed into a high work function surface, whose static potential is thus driven negative. These electrons then move through the desired load circuit system(s) and emerge at the surface of the Anodic ion Neutralization Electrodes surface, where the negatively charged electrons recombine with and neutralize the positively charged flux of ions which continue on out of the crafts Vacuum Exhaust Port as neutral species. Designation of cathode and anode is done from the viewpoint of craft electrical systems, such that the cathode provides electrons to the load circuitry, analogous to a battery or other source of DC power. To avoid Anodic Ion Neutralizing Electrode corrosion, the AINE surface is covered with a low work function material with preferably; high melting point, low vapor pressure, high ion milling resistance (low ion milling rates), chemical compatibility with the fusion plasma positive ion exhaust stream, and other properties favoring long Anodic Ion Neutralizing Electrode lifetimes.
The Vacuum Exhaust Port (VEP) exhausted mass flux from such a Fusion Reactor Direct Conversion (FRDC) system does not significantly contribute to the thrust of the DBI craft. This is due to significantly lower exhaust velocity and plasma mass flux rate of the fusion reactors VEP exhaust stream, when compared to the much greater exhaust velocity of the Dual Beam Ion Thrusters themselves.
Direct Conversion technology can theoretically achieve up to near 90% thermal to D.C. (direct current) power conversion efficiencies. High power density rotating machines are not required using such Fusion Reactor Direct Conversion (FRDC) technology, with the resultant improvement in simplicity, reliability, and overall power/mass performance ratios.
Systems configurations:
(4.1) Solar Thermal Propulsion system.
Solar Thermal Propulsion (STP) systems involve the apparatus described in section 1.3, powered by solar radiation described in section 2.2. Solar radiation impinges on the reflector surfaces of the STP system and are focused onto the solar absorber within the receiver assembly, causing super-heating of a gas such as hydrogen, with expulsion at high-velocity to produce thrust.
(4.2) Photovoltaics powering Arcjet thrusters.
Photovoltaics, described in section 3.1, generate electricity from solar radiation, described in section 2.2, and power Arcjet thrusters, described in section 1.4.
(4.3) Photovoltaics powering Single Beam ion thrusters.
Photovoltaics, described in section 3.1, generate electricity from solar radiation, described in section 2.2, and power Single Beam Ion thrusters, described in section 1.5.
(4.4) Photovoltaics powering Dual Beam Ion thrusters.
Photovoltaics, described in section 3.1, generate electricity from solar radiation, described in section 2.2, and power Dual Beam Ion thrusters, described in section 1.5.
(4.5) SP-100 nuclear reactor - turbine - generator powering Dual Beam Ion thrusters.
Nuclear fission reactors, described in section 2.3, produce heat which is converted to shaft torque by turbines and converted to electricity by Faraday monopolar generators, described in section 3.2, producing electricity which powers Dual Beam Ion thrusters, described in section 1.6.
(4.6) Fusion reactor - turbine - generator powering Dual Beam Ion thrusters.
Nuclear fusion reactors, described in section 2.4, produce heat which is converted to shaft torque by turbines and converted to electricity by Faraday monopolar generators, described in section 3.2, producing electricity which powers Dual Beam Ion thrusters, described in section 1.6.
(4.7) Fusion reactor - direct electrical conversion powering Dual Beam Ion thrusters.
Nuclear fusion reactors, described in section 2.4, produce heat which is converted to electricity by fusion Reactor Direct Conversion systems, described in section 3.3, producing electricity which powers Dual Beam Ion thrusters, described in section 1.6.
(4.8) Matter-antimatter annihilation - turbine - generator powering Dual Beam Ion thrusters.
Matter-antimatter annihilation, described in section 2.5, produces heat which is converted to shaft torque by turbines and converted to electricity by Faraday monopolar generators, described in section 3.2, producing electricity which powers Dual Beam Ion thrusters, described in section 1.6.
(4.9) Matter-antimatter annihilation Warp-Drive.
Matter-antimatter annihilation, described in section 2.5, produces gamma-rays which are focused into a collimated beam by Warp-Drive thruster systems, described in section 1.7, producing the ultimate in propulsion performance.
Comparative modeling:
(5.1) Space Shuttle -vs- Dual Beam Ion craft.
In order to establish a baseline readily comparable to present space shuttle (STS) class craft, an equivalent pad mass Dual Beam ion (DBI) class craft will be examined. To do this the following STS performance and specifications are provided, and a theoretical model for an equivalent initial pad mass DBI class craft is provided.
STS shuttle class craft performance and specifications:
Space Transportation System (STS), space shuttle class craft exhibit near the following values of performance and specification.
STS class craft are able to attain a maximum orbital height of 1,100km (690miles) (gravitational acceleration .85g = 8.33m/sec2), and putting this in perspective, geosynchronous orbit is 35,900km (22,300miles) above sea level (gravitational acceleration .15g = 1.47m/sec2).
STS class craft are composed of four principle units, an Orbiter, an External Tank (ET), and two Solid Rocket Boosters (SRB). The Orbiter craft carries the crew and payload, and is attached to the large External Tank. The External Tank (ET) contains the liquid oxygen tank in the nose and the liquid hydrogen tank in the rear, used by the three Space Shuttle Main Engines (SSME) in the rear of the Orbiter. The two Solid Rocket Boosters (SRB), are attached to opposing sides of the External Tank.
The orbiter itself has the following dimensions, 37m (121.4ft) long, 17m (55.8ft high), with a wing span of 24m (78.7ft). The fuselage has dimensions of near 5.6m*5.6m*37m (1,190 m3) (1.19*109cc).
The cargo bay in the Orbiter of an STS class craft measures 4.5m (15ft) in diameter, and 18m (60ft) in length, representing a cargo bay volume of 286m3 (2.86*108cc), implying a gravimetric average density of
0.103grams/cc for the cargo bay contents (low-density cargo, or not much cargo).
The External Tank has the following dimensions, 47m (154ft) total length, and 8.4m (27,5ft) in diameter representing an approximate internal volume of 2,600m3 (2.6*109cc).
Solid Rocket Boosters (SRB) have the following dimensions, 45.5m (l49ft) in length, and 3.6m (12ft) in diameter representing internal volumes of 46.3 m3 (4.63*108cc) each.
NOTE: estimating the volumetric density utilizing the above dimensions yields that the 2,046,000 kg of mass inside of the estimated volume of 4,724 m3 (4.724*109cc), results in an average gravimetric craft density of near .43g/cc.
The total impulse (I = T*t, thrust(T), duration(t)), for STS class craft is near 5,300,000,000 newton-seconds.
The STS class craft develops 28,400,000 newtons initial lift off thrust.
Space Shuttle Main Engines (SSME) thrusters together produce 2,500,000,000 newton-seconds impulse, consisting of 4,800,000 newtons thrust for a duration of 510 seconds.
The two Solid Rocket Boosters (SRB) together produce 2,800,000,000 newton-seconds impulse, consisting of 23,400,000 newtons thrust for a duration of 120 seconds.
Propellants for the STS SSME system consist of 102,000 kg (1,500,000 liters) of liquid hydrogen and 616,500 kg (540,000 liters) of liquid oxygen, with a gravimetric mixing ratio of 1:6, or a volumetric mixing ratio of 5:18, respectively.
Propellants for the STS SRB system consist of 176,000 kg Al (aluminum metal powder), 768,130 kg
NH4C104 (ammonium perchlorate), 1,870 kg Fe203 (ferric oxide catalyst), 154,000 kg binder and curing agent.
From consideration of the exhausted mass and the resultant impulse produced, it can be shown that the
average exhaust velocity of the exhausted fuel is near 2,900 m/sec.
The Orbiter itself has a mass of 75,000 kg.
The combined mass of the Orbiter and the payload carried on board can be up to 104,500 kg.
The empty SRB casings have a mass of 84,100 kg.
The large empty outer SSME fuel tank (ET) has a mass of 35,400 kg.
The maximum payload capacity is 29,500 kg.
Total fueled pre-launch STS pad mass is on the order of 2,045,000 kg.
NOTE: It can be seen that the maximum payload an STS class craft can deliver to an orbital height of 1,100km is only 1.44% of the initial fueled pre-launch STS pad mass.
STS class craft of 2,045,000 kg pad mass, are found to consist of 1,820,000 kg fuel (89% of pad mass) and only 225,000 kg of actual craft and payload (11% of pad mass). This configuration with 89% of pad mass being fuel and only 9.6% of pad mass being craft, with the remaining 1.4% of pad mass being payload, necessitates significant sacrifices in many ways.
Structural integrity of the STS class craft is compromised in order to carry such a large fuel fraction. This compromise between fuel and craft can lead to increased catastrophic failure probability. This questionable craft integrity factor and the associated low payload capacity leave much to be desired. In order to seriously improve spacecraft performance a new type of propulsion system needs to be examined and developed.
Orbital Maneuvering System thrusters:
Two Orbital Maneuvering System (OMS) thrusters are used by the Shuttle Orbiter craft to adjust orbital
trajectories. Each OMS thruster weighs 118kg, is 1.96m (6.43ft) long and can deliver 26,700 newtons of thrust. The exothermic hypergolic (spontaneous reaction upon mixing) reaction of the monomethylhydrazine (fuel) and nitrogen-tetroxide (oxidizer) mixture assures reliable starting of the OMS thrusters. Together the two OMS thrusters can deliver up to 53,400 newtons of thrust for orbital adjustments, which is near 0.51 newtons/kg of orbiter+payload combined craft mass for orbiter
Reaction Control System thrusters:
Reaction Control System (RCS) thrusters are composed of clusters of thrusters in the nose and tail
of the orbiter which serve to control the attitude (yaw,roll,pitch) of the STS class craft. RCS thrusters
of two kinds are encountered, the 38-primary RCS thrusters which are collectively capable of delivering 3,870 newtons of thrust, and the 6-vernier ACS thrusters which are individually capable of delivering 110 newtons of thrust.
Auxiliary Power Units:
Auxiliary Power Units (APU) generate power for the STS class craft hydraulic systems during ascent and descent. Individually, each APU generates near 135 horsepower (100,000 watts), each APU has a mass of 40
kg, resulting in airbreathing APU power generation densities of near 2.5 watts/(gram of APU mass).
Hydrazine is the fuel for these airbreathing turbines, with 134 kg allotted to each of the 3-APUs, resulting in
90 minutes of service for each one. These performance levels represent an extractable energy density of near
1,127 w-h/kg for hydrazine airbreathing oxidation.
STS SSME class fuels:
STS SSME derive thrust by utilization of the energy released during the oxidation of fuels and the resultant
expansion of gases. The energy density obtainable is near 3,660 watt-hours(w-h)/kilogram(kg) of
hydrogen(H2) and oxygen(O2). Exhaust velocity is limited as a function of factors such as the inherent energy density of available fuel-oxidizer mixtures, the fluid dynamics of expanding heated gases, the inherent materials limitations of nozzles and other propulsion system components.
In order to achieve greater mission capabilities the impulse (Thrust*duration) must be increased, with a simultaneous decrease in the required fuel fraction of pad mass, and increase in the permitted craft+payload
fraction of pad mass. Thrust (T) is defined as the multiplication product of the exhausted mass flux rate
(dm/dt), and the exhaust velocity (dx/dt = v) of the exhausted mass flux. In order to maintain a constant
level of thrust and achieve a decrease in the required exhausted mass flux, the exhaust velocity produced by
the propulsion system must be increased. Thermal expansion propulsion systems are all limited by fluid
dynamics and materials constraints, thus electrical acceleration is chosen for development as exhaust
velocities can be dramatically increased.
STS class craft performance -vs- equivalent mass DBI class craft.
DBI class craft of near 2,046,000 kg initial pad mass, equivalent to STS class craft initial pad mass,
with only a 10% fuel fraction, as compared to the 89% fuel fraction of the STS class craft, are theoretically
capable of providing near 30 to 200 times the deliverable impulse (5,300,000,000 newton-seconds) of comparable STS class craft.
DBI class craft producing 28,500,000 newtons of thrust, for a duration of !86 seconds, deliver the equivalent impulse of STS class craft (5,300,000,000 newton-seconds).
This is achieved with an exhaust velocity of 20,000,000 meters/second, and an exhausted mass flux rate of near 1.42 kg/second, for the proton(H+) - oxygen(O-2) DBI system.
With 186 seconds duration, it can be shown that the total exhausted mass from the DBI thrusters is of the order of 264.1 kg of H20.
Acceleration of this H20 is accomplished by use of near 1.37*1013 watt-hours of electricity, which for a fusion reactor direct thermal to D.C. power conversion rate of near 10%, yields a total of 6,336 kg of deuterium fuel.
Summing the mass of the exhausted H2O and the mass of the deuterium, yields on the order of 6,600 kg fuel used by a DBI class craft to produce 5,300,000,000 newton-seconds impulse, which when compared to the initial 200,000 kg fuel fraction (10% initial DBI pad mass), yields on the order of 30.3 times the deliverable impulse of comparable pad mass STS class craft (1.606*1011 newton-seconds).
Similarly, a fusion reactor thermal energy to DC power conversion rate of near 90%, yields a total of 704 kg deuterium used by a DBI class craft to produce the energy for the 5,300,000,000 newton-seconds impulse. Summation of the deuterium (704 kg), and H2O (264.1 kg), yields 968 kg required fuel fraction, when considered in context of the initial 10% pad mass fuel fraction yields on the order of 206 times the deliverable impulse of comparable pad mass STS class craft (1.092*1012 newton-seconds).


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Difference between revisions of "Sofia"
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Revision as of 14:11, 1 January 2016
Spoiler Warning:
This article reveals important elements of a work yet unpublished.
(This notice may only be removed by a Lead Editor.)
| unknown, probably early 1990s
|Leader of the Remnant
|Jacob and Alya
|Rise of the Tomb Raider
Sofia it a member of the Remnant, a seclusive people living in a Geothermal Valley near the lost city of Kitezh. She is one of the main characters in Rise of the Tomb Raider and daughter of the Prophet Jacob.
Before Rise of the Tomb Raider
Before Lara coming to the valley Sofia seems to have been the leader of a small group of hunters that provides meat for the inhabitants of the valley. She seems to be a very good archer and well respected within the community, although she seems to be fearful or even hostile towards outsiders, adopting a kind of "shoot first, ask questions later" approach.
Little is known about her childhood. Her mother, Alya, seems to have died when she was very young. She seems to have been raised mostly by her father, Jacob, who's devotedness to his people seems to let him at times have neglected her a bit, which in turn let her grow up to be an independent adult. The relation towards her father seems cold sometimes, but not without respect for one another.
During Rise of the Tomb Raider
Lara first encounters Sophia in the Siberian Wilderness where she and two other Remnant are being chased by Trinity mercenaries. They meet again later and she tells Lara with an arrow pointing at her to leave the Remnant alone and stop her quest for the Divine Source or else she would sooner or later have to face the consequences.
After travelling through the Abandoned Mines and getting separated from Jacob, Lara emerges in the Valley to again find Sofia blocking her way. She accuses her of having betrayed her father and is about to shoot at her. Only the timely arrival of Jacob via another path saves Lara.
Later on the relation between Lara and Sofia gets steadily better as Lara does everything in her power to ally herself with the Remnant.
After Rise of the Tomb Raider
After Jacob dies along with the other Deathless when Lara destroys the Divine Source Sofia takes up the part of the leader of the village, trying to follow in her dead fathers footsteps. It seems that most of the inhabitants are willing to stay even after the Source has been destroyed and there is no real reason to continue living as outcasts, although there is also talk of leaving, especially among the younger people.
Family and Friends
- Her father, the Prophet
- Her mother
Further Information
- Real Name: Sofia
- Age: Mid 20s (no exact date of birth is given)
- Nationality: Remnant (technically Russian, as she was born in Siberia)
- Occupation: Huntress, leader of the Remnant
See Also
- Jacob's people
- ↑ Pages of the Ledger document set


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KATZ STRAWBERRY PRESERVES 16 oz. $17.00
"For my money, KATZ makes the best jams in the country." Corby Kummer, The Atlantic
KATZ Strawberry Preserves
The sun has come out in Northern California so we quickly turned to our local trusted strawberry farmers for some of their amazing Albion Strawberries - our variety of choice. For the first few months of spring they will use only the groundwater gathered from the winter and spring rains and no added irrigation to grow these berries. This allows the berries to be extra firm and sweet!
When we prepare and cook these for preserves, the results are incredibly full-flavored and intensely rich preserves. Their deep, abundant taste defines our KATZ Strawberry Preserves, and as always they are made with only a small amount of sugar and fresh lemon juice and never any added pectin.
SERVING SUGGESTIONS: KATZ Strawberry Preserves are ready to adorn your morning whole wheat toast, yogurt or how about breaking out a jar for a special brunch of blintzes, KATZ Farm French Toast or KATZ Buckwheat & Honey Pancakes.
Our preserves are made the old-fashioned way...we do not use any preservatives, period! Please enjoy every spoonful of our fresh fruit preserves, and refrigerate after opening.
Making our fresh fruit preserves in the artisanal manner for the past 25+ years has been a true labor of love. Each new season brings the anticipation of visiting our farmer friends to see them once again and share in the bounty of their well-tended orchards and fields.
In our Napa kitchen, each batch of fruit is skillfully cut or sorted by hand, simmered in small, open kettles, using the smallest amount of sugar and fresh lemon juice needed to set (no pectin, no preservatives). Each "pot of jam" brings you 16 delectable ounces. . .a pound of preserved fruit in each jar hand wrapped in our proprietary Branches paper!
Articles in The Atlantic, Saveur, Gourmet, Fine Cooking, and The New York Times have inspired us to increase our production. Yet, with the small window Mother Nature provides for many of the varieties we use, we like to say around here, "when theyre gone...theyre gone!"
Shipping Notice
To Our KATZ Farm Friends:
While we remain humble and focused on keeping your 'proverbial' pantry stocked, we also take to heart the safety and well-being of our hard-working staff. We are processing orders as quickly and safely as we can so there may be delays in getting your orders fulfilled.
We thank you for your patience.
Stay safe, The KATZ Family and Team
Note: Our Napa Kitchen/Office facility is closed during this time.
You may call to set-up an order for pickup.
Sign up for our E-Newsletter
Exclusive Discount Offers!


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I was discussing JavaScript code with a friend and he noticed that I had declared all the variables at the top.
He likes to declare the variable where they are used to be sure that the variable being used is declared with var otherwise that variable will become global variable. This fear of accidentally creating a global variables wants him to see variable declaration next to where it is being used.
Use the right tool
In the above case user has declared payment variable in the middle so that he is sure that payment is declared. However if there is a typo as given below then he has accidentally created a global variable "payment".
Having variable declaration next to where variable is being used is not a safe way of guaranteeing that variable is declared. Use the right tool and that would be jslint validation. I use MacVim and I use Javascript Lint. So every time I save a JavaScript file validation is done and I get warning if I am accidentally creating a global variable.
You can configure such that JSLint validation runs when you check your code into git or when you push to github. Or you can have a custom rake task. Many solutions are available choose the one that fits you. But do not rely on manual inspection.
Variable declaration are being moved to the top by the browser
Take a look at following code. One might expect that console.log will print "Neeraj" but the output will be "undefined" . That is because even though you have declaration variables next to where they are being used, browsers lift those declarations to the very top.
Browser converts above code into one shown below.
In order to avoid this kind of mistakes it is preferred to declared variables at the top like this.
Looking at the first set of code a person might think that
Also remember that scope of variable in JavaScript at the function level.
Implications on how functions are declared
There are two ways of declaring a function.
In the first case only the variable declaration
myfunc is getting hoisted up. The definition of myfunc is NOT getting hoisted. In the second case both variable declaration and function definition is getting hoisted up. For more information on this refer to my previous blog on the same topic.


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Slingback shoe in Suede leather Black/Navy blue
250,00 €
Warning: Last items in stock!
Availability date:
The Slingback shoe comes back. Comfortable, easy to wear and modernized, it adapts itself perfectly to our current looks.
Product description :
Size & Fit information:
Fits true to size, take your normal size.
Handcrafted in our own workshops in Portugal.


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This quarter inch thick glass tray features gently sloping sides and functions as a decorative tray or generous serving platter. Featuring an original whitetail deer image by Rosemary Millette, this Whitetail Deer Glass Platter is ready to serve. This is a great addition to your cabin decor and a wonderful gift idea for the deer hunter in your life!
- Dimensions: 13"L x 11-1/2"W x 1"T
- Antler stand not included
- Made of sturdy glass
- Features gentle sloped sides
- Great for parties
- Beautiful artwork
Glass Platter - Deer [X]


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Quinoa is a high-nutrition crop that could be profitable
Special to the Nevada Appeal
A high-nutrition crop called quinoa shows promise for surviving the low water and high winds of Northern Nevada. The hope is that quinoa, a gluten-free, high-protein grain, can be a profitable crop for small-scale farmers and could help strengthen the local food system. Healthy Communities Coalition of Lyon and Storey, a regional nonprofit, envisions a day when the region will have expanded quinoa and gluten-free grain-processing capabilities, and has been helping local farmers find spots to test out the viability of quinoa and other specialty crops.
For instance, early in the growing season this summer, farmers from Dirt Merchant Farms of Stagecoach cultivated test plots of amaranth, quinoa and quinoa's "cousin crop," lamb's quarters, at the Dayton community garden on River Road. They also put in some quinoa test plants at the Silver Stage Community Garden near the local schools in Silver Springs. Next spring, they plan to try cultivating quinoa in Hawthorne, Fallon, Stagecoach and Yerington.
Jesse Alexander of Dirt Merchant Farms described the results of the quinoa test plots, saying, "all in all, I would call the Dayton patch successful. I can recommend it for large-crop rotation here in spring and fall and in Southern Nevada during the winter months."
Quinoa and Nutrition
Quinoa has become more and more popular in recent years because it is a gluten-free, cholesterol-free grain with high iron, protein and fiber. One cup of cooked quinoa contains more than 8 grams of protein and about 15 percent of the recommended daily intake of iron. Due to its nutrient value, the Food and Agricultural Organization of the United Nations has declared 2013 "The International Year of the Quinoa."
You can find quinoa grain at the farmers markets at Community Roots in Dayton and at Penny Park in Silver Springs and at the Silver Stage Food Co-Op store on Spruce Avenue in Silver Springs. Seeds can be found through the Silver Stage Co-Op and Great Basin Community Food Co-Op in Reno.
The Healthy Communities Coalition is a regional nonprofit coalition composed of local, state, federal and tribal groups and community volunteers. For more information, call director Christy McGill at 775-246-7550.


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Apart from kids parties, we also serve corporate clients including:
Great Eastern
NTUC Income
Standard Chartered
JP Morgan
Fullerton Heritage
Tommy Hilfiger
Star Cruises
Wala Wala
Amber Nectar Bar
Screening Room
Dom Lounge
British Council
Asia PR Werkz
Boston Consulting Group
What our happier customers say:
Dear Alicia, thank you so much for your time and effort for our event. Your work is by far some of the best I have seen. I will put a note of fb to help you promote your work. I must though send you this note from the another Artist at the event; "The atmostphere, the crowd and the activities were exciting and I enjoyed myself just as much. In fact, you had the best face painter who painted so well compared to many I have seen". – Udeshika, RSP
Dear Alicia, thank u very much for ur team's service. I'm so happy with them both and they r most professional. Christopher was a big hit in the party. Engaging u guys is the best decision Ive made, definitely looking fwd to hiring u guys again:) – Pauline, Mummy
Dear Alicia, thanks for the services rendered on 16 Nov 13 at my son's baby dedication. The balloon artist (Kelvin) was excellent– he was professional and accommodating and he was a blast with the kids. He really went the extra mile and made the evening extra special for us. I am also really pleased he took the notes that we sent earlier very seriously and made an effort to make my elder son feel special. Please send our thanks and compliments to him. I am really pleased with the service provided by you and your team; we're certainly made happier by engaging you guys. – Grace, Mummy
Doris is a joy to work with and her presence spreads laughter and joy to my client's guests. We are very happy to have worked with her and wish that we are able to do so again in future. – Zaid, Freelance events
So far, we are very pleased with the Balloon Sculptor and Decorations that Happier Singapore has provided. Chris had been awesome and very engaging. Our clients LOVE him! Will definitely engage his for future shows! – Fiona, Roadshow organizer
Warmest thanks to Chris from happier Singapore u really did a great job by entertaining the kids in our son's birthday bash..We really appreciate your hard work..Thank you so much.. – Louislucnikhil, Mummy
Oh everyone loved Amanda's painting! Even my daughter who always insists on being a dinosaur was happy being a pretty butterfly yesterday! Job well done! Thank you! Will recommend u guys to my friends as well! Many pple were asking already – Almeta, Mummy
Thank you! Damian was a very nice guy and did nice butterfly paintings. – Madlene, Mummy
Both (SP & Mel) were lovely they did an excellent job. Mel especially. Everyone loved her work. Infact they've taken your number from me and will get in touch with you for their events. I'm so glad we got your team to work on our baby's birthday. We're definitely going to be coming back for next time. Mel was a super duper hit. – Naima, Mommy
What's the face painter's name? Please help me thank him (Damian) for his good work I like to thank you too for your service – Justin, Magician
The face painter (Damian) so meticulous and patience. Balloonist (Doris) same passionate and patience. Magic show seen her before so no comment. Everyone enjoyed the show though. But to me the face painter and balloonist *big applause*. Fiona recommended your team and she was always right la. Thank u. – Heppy, Mummy
Hi Alicia! Thank you for the adorable balloon decor and stunning face painting! The kids loved it!! Will def contact you for future birthdays!! Love Simrit!!
Thank you very much.. Damian did amazing work… Kids were very happy and so were the adults. Great work. Thank you again. – Jamillah Elvehoey, Mummy
Hi Alicia, the adults and the kids had a lovely time! We love your artowrk! Keep the good work going and thank you for painting at our event! – Xin Xiu, Gunvor
Dear Alicia, just dropping to let you know that our client was very happy with the face and hand painting service rendered by Xue Li. They thought she was great and the kids were very delighted too! Will be in touch again for other events. Thank you. – Emily, Asia PR Werkz
Hi Alicia, thanks for coming down the past two events last weekend! The response was really great and a lot of teachers, parents and kids seemed to be really enjoying themselves. – Christina, British Council
Hi Alicia, just a note to thank u and yr colleagues for the job well done on sat. The guests, regardless of age, all enjoyed it. – Caroline, Mummy
Hi Alicia, I would like to say a big thank you for making today's carnival amazing with your services. We are very pleased and we look forward to working with you guys again. Thank you once again – Deb, Amazonia
Hi Alicia! Thank u so much for yesterday! My guests had so much fun coz face painting is new to them! i'll definitely recco u to my friends and colleagues and let u know when our next party's up! Hihi..Do u have a facebook page that i can like?;) – Christi, Mummy
Alicia thanks a lot for the great experience…. my children and the other kids definitely had a great time and you are truly a great artist… some of my guests are amazed with your work and asked for your contact…. I have forwarded them to contact you directly for your services. Your friend who does balloon twisting is great too. Hope you had great time with us too! – Sharifah, Mummy
Hi thank you for your wonderful service. We are very very pleased with your professionalism! May god bless your team. Will definitely recommend your service to my friends. – Agnes, Mummy
Thank you so much for all the balloons all the mummies say the kids say they had alot of fun – Pemme, Mummy
Thanks Alicia. All my little guests were so happy. Lots of compliments from their parents too. Will definitely recommend your services to my parents too. – Karen, Mummy
Hi Alicia. Thank u so much for sharing Dan's bday celebration today. We love u and what u do! I'm sure we'll call u again some time. In the meantime, take care. – Daryl, Daddy
thank u alicia, the kids had a fabulous time yesterday.. yr works of art were amazing – Dani, Daddy
Thanks for your lovely works at the party today. Our guests were full of praise for you. – Cindy, Mummy
Hi Alicia- it was wonderful! Butterfly facepaints were esp popular among the girls, balloon swords & bows for boys, surprise! Great services with a smile & such a hit with the kids, thank you & will be sure to employ yr services again if I have a similar event. – Ruo Ting, JP Morgan


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Ron Alexenburg – Past President of Epic Records
This week's episode talks about Ron's meeting with Elvis in Las Vegas. Col. Parker turned down the request for the meeting, so Ron tipped a head waiter to get him backstage to the King's dressing room. The upshot of the story is – promo guys never give up. The Insane Darrell Wayne hosts.Read More


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TOLEDO, OH (WTVG) — A 51-year-old Toledo man fell head first off of a train overpass. Police call the fall accidental saying he was drunk. It happened around 7:30 Friday night at Detroit and Dura.
Police say Joseph Nurkiewicz, 51, was breathing when they found him in the street, but it appears he has severe head injuries. Sgt. Mark Evanoff of the Toledo Police Department says, "He didn't know where he was going ."
Toledo police say they were first called to Detroit and Dura Friday night because of a report of a kid throwing rocks. It turns out it was a 51-year-old man who just got kicked out of the Insane Clown Posse concert at Headliners. Sgt. Evanoff says, "He brought some beer with him and they don't allow any beer here."
Sgt. Evanoff says officers told Joseph Nurkiewicz to leave and shortly after he fell 25 feet head-first off the bridge over Detroit. "He fell twice, from one level to another, hit his head both times and wound up in the street on Detroit," says Sgt. Evanoff.
Police say the victim's son witnessed the fall. "His son was supposedly trying to catch up with him and seen him go over," Sgt. Evanoff.
There is no word on Nurkiewicz's condition at this time.


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|Attestation committee
Accreditation committee
Expert committee
Dispositions, instructions
Normative acts
Scientific councils
|Scientific advisers
Doctoral students
Postdoctoral students
StatusThe thesis was presented on the 15 July, 2011
Approved by NCAA on the 5 October, 2011
Abstract– 1.23 Mb / in romanian
The PhD thesis in biology consists of introduction, four chapters, conclusions and recommendations, a bibliography of 192 titles, nine appendices, and 127 pages of basic text, 22 tables, and 39 figures. The results are published in 20 scientific papers.
Purpose: highlighting the current status and role of Orthoptera insects in natural and agriculture ecosystems from the Republic of Moldova.
Objectives: species identification and determination of Orthoptera insects from the Republic of Moldova and analysis of their zoogeographical distribution, trophy spectrum and their habitats; investigation of Orthoptera insects from different scientific and landscapes reserves from the Republic of Moldova; the significance of Orthoptera insects in the biocoenoses; elaboration of recommendations for monitoring, estimation and improvement of harmful grasshoppers species group.
Scientific originality of work. For the first time where done an amply review of Orthoptera species from the Republic of Moldova which is listing 113 species. The subfamily Gryllomorphinae, 10 genera and 35 species are new for the fauna of the Republic of Moldova. There are also done dates belonging biogeographically distributions on the types of habitat, vital form and food spectrum. Three species have been identified rare and endangered grasshoppers in the Republic of Moldova and in other European countries. These species (Saga pedo, Onconotus servillei and Gampsocleis glabra) are proposed to be included in the Third edition of the Red Book of Moldova.
Theoretical significance. The research has made a significant contribution to the study of insect from Orthoptera order in the Republic of Moldova. The obtained dates about place and role of grasshoppers in ecosystems of each species present the base of the Animal Cadastre of the Republic of Moldova and contribute to solving problems related to integrate environmental monitoring.
The practical value. The main results of the thesis are part of the theme of academic and applied scientific study of the Institute of Zoology of the ASM. Research results will contribute to increasing theoretical and empirical heritage, the diversity of fauna, seasonal dynamics, trophy spectrum, spatial structure in bio interference geographical zone of populations of Orthoptera insects.
Implementation of scientific results. The obtained results are used in preparing of the Animal
Cadastre of the Republic of Moldova and the third edition of the Red Book of Moldova. Also, the dates of
pest and invasive species are utilised especial courses in Agriculture State University of Moldova at the
speciality "Plant Protection" and in elaborating of measures of fight in forests tree nursery and green
Under consideration [1] :
Theses Archive:


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The Akhil Bharat Hindu Mahasabha, one of the main litigants in the Ayodhya title suits, on Saturday said it will move the Supreme Court against the verdict of the Allahabad High Court by November 10.
"The mahasabha would file its appeal in the apex court against the High Court verdict by November 10 and has authorised its national leader Dinesh Chandra Tyagi to pursue the case," state unit president of the mahasabha Kamlesh Tewari said here.
He said that at a recent meeting of all factions of the party it was decided that since Tyagi has been looking after the case in the High Court he should continue to do so in the Supreme Court.
"Counsel Hari Shankar Jain, who had represented the mahasabha in the High Court, would continue to look after it," Tewari said.
On the ongoing dispute within the party over the post of the national president, he said that some of its leaders had tried to "hog the limelight" by making different claims to the media.
While the state unit was preparing to move the apex court, Swami Chakrapani filed a caveat in the SC to lay claim over the post of the national president, Tewari said, adding, agents of the BJP and RSS would be "thrown out" by the mahasabha.


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| 8.5°C Belfast
Arsenal gave their Barclays Premier League title hopes a shot in the arm with a 2-1 victory over Manchester City at the Emirates Stadium.
Here, Press Association Sport examines the performance of Arsenal forward Theo Walcott and City striker Sergio Aguero.
There was only one winner here with Walcott's sublime finish from the edge of the area putting Arsenal in control after a half an hour in which City had dominated. The Gunners remained in the driving seat until late in the match.
Aguero was well contained by Arsenal centre-back Laurent Koscielny, who tackled him three times and was alive to his threat all night. Walcott's influence waned but in the first half his movement off the wing was lethal.
Aguero could muster only two shots at goal, both of which were directed straight at Arsenal goalkeeper Petr Cech. Walcott's goal came when he collected Mesut Ozil's pass and curled a shot into the corner. It was an outstanding finish.
Aguero may be the £35million striker but Walcott was more valuable this evening.


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On one hand, crowdfunding is as old an idea as rattling a tin in the marketplace. Today, however, the word has assumed a new meaning. The term is now more usually associated with the activity of raising funds online.
We define crowdfunding more precisely as raising a specific sum for a specific project within a specific timeframe.
Sounds simple. In essence, it is simple. And it can deliver astounding results. A GlobalGiving crowdfunding project raises on average £3974! But to be successful you will need to acquire a variety of new skills. Join a workshop or webinar.
We are currently planning our workshop schedule for the rest of 2016. If you are interested in attending a workshop, please check back on this page soon. In the meantime, we have just launched a new online guide with tips for running a successful crowdfunding campaign: Crowdfundamentals: 11 steps to online fundraising success.
Liverpool: 10th March 2016
Manchester: 11th March 2016
Southampton: 14th March 2016
Norwich: 16th March 2016
Swindon: 6th April 2016
Sheffield: 21st April 2016
Doncaster: 22nd April 2016
Newcastle: 4th May 2016
Leeds: 5th May 2016
Birmingham: 12th May 2016
Leicester: 18th May 2016
London: 24th May 2016
Exeter: 25th May 2016
London: 17th June 2016
Bristol: 29th June 2016
We are very grateful to the Cabinet Office for supporting our programme by generously underwriting most of the costs. This enables us to offer places valued at £175, for only £25 per person for smaller charities – those with an income under £1 million – and £95 per person for larger charities. Prices exclusive of booking fee but inclusive of refreshments and lunch!
Webinars are an excellent way to gain knowledge and skills without leaving your seat! For a quick and easy introduction to Crowdfunding & Online Fundraising sign up below. They give you the basics on what it is and how to start thinking about this type of fundraising for your charity. You can join a webinar from anywhere as long as you have a computer and the internet. All webinars start at 10am GMT and last approximately 1.5 hours.
Sign up for one of our upcoming webinars:
Webinar: 3rd March 2016
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Webinar: 11th May 2016
Can't see a date or location that works for you? Leave your details with us and we will be in touch when we have new dates - complete form here.
We helped Tim from Salem Union raise £5,666 from 102 people in 40 days through our training. "We were fundraising novices so this training enabled us to go from nothing to executing a successful campaign."
GlobalGiving is the world's first and largest Global crowdfunding community for non-profits and social entrepreneurs. We have helped 508,000 donors raised £150 million+ for 13,900 community projects in 164 countries since 2002.