Barometric altimeter data during high vertical g-forces?
In the formula $dP = -\rho gdz$, $g$ is the local gravitational field that is pulling on the fluid (the atmosphere).  The apparent value of $g$ within the airplane is not relevant.

So other than making sure the sensor itself isn't affected by changes in apparent weight, there's no need to correct for accelerations of the barometer.


  And yes I am intending to ask whether the sensors are designed such that their “apparent weight” (or more generally their mass acted on by any directed force) is not an appreciable factor in their reported measurements?


My understanding is that no, it's not.  Altimeters already have a measurement error at level flight, and they have a lag when altitude is changing.  Additional errors due to apparent weight would have to exceed those to be worrisome.  

"vertical acceleration" is rather small for almost everything that's not a military fighter.  But a plane could easily pull 3g's in a level turn, and you would want your altimeter to remain accurate.

Obviously it's possible to design an instrument that is more susceptible to such inaccuracy (such as have the pressure vessel balance against a weight to indicate the altitude), but that shouldn't be a problem for a normal instrument.

The aneroids in a diaphragm barometer can be oriented so that downward forces have no effect on the reading.  Also, the smaller and lighter the disks, the less that any acceleration will affect the reading.  

I found lots of articles on various corrections for barometric altimeter readings based on temperature and different atmospheric profiles, but none on g-load corrections.  That suggests to me that no correction is necessary for standard instruments.  Perhaps someone can find published performance data for an installed instrument that calls it out explicitly.  The lack of information I found appears reasonable, but not completely satisfying.