low Earth orbit (LEO) or from LEO to an escape orbit. This is a worst case calculation - in practice, gravity loss during launch and ascent is less than the maximum value of gt because the launch trajectory does not remain vertical and the vehicle's mass is not constant, due to consumption of propellant and staging. Vector considerations Thrust is a vector quantity, and the direction of the thrust has a large impact on the size of gravity losses. For instance, gravity loss on a rocket of mass m would reduce a 3mg thrust directed upward to an acceleration of 2g. However, the same 3mg thrust could be directed at such an angle that it had a 1mg upward component, completely canceled by gravity, and a horizontal component of mg× = 2.8mg (by Pythagoras' theorem), achieving a 2.8g horizontal acceleration. As orbital speeds are approached, vertical thrust can be reduced as centrifugal force (in the rotating frame of reference around the center of the Earth) counteracts a large proportion of the gravitation force on the rocket, and more of the thrust can be used to accelerate. Gravity losses can therefore also be described as the integral of gravity (irrespective of the vector of the rocket) minus the centrifugal force. Using this perspective, when a spacecraft reaches orbit, the gravity losses continue but are counteracted perfectly by the centrifugal force. Since a rocket has very little centrifugal force at launch, the net gravity losses per unit time are large at liftoff. It is important to note that minimising gravity losses is not the only objective of a launching spacecraft. Rather, the objective is to achieve the position/velocity combination for the desired orbit. For instance, the way to maximize acceleration is to thrust straight downward; however, thrusting downward is clearly not a viable course of action for a rocket intending to reach orbit. See also Delta-v budget Oberth effect References . External links General Theory of Optimal Trajectory for Rocket Flight in a Resisting Medium Astrodynamics