Abstract
A new semi-empirical thruster plume model is presented based on recent experimental and numerical (Direct Simulation Monte Carlo) studies. The results are unique in that they pertain to unprecedentedly low flow rates (nozzle Reynolds numbers below 200). The model is used in computing the impingement forces acting on a spacecraft solar panel emersed in a thruster plume. The time-varying impingement effects due to changes in surface temperature were found not to be a serious limitation on the thruster calibration accuracies for the GP-B and STEP spacecraft. This suggests that both spacecraft could yield useful aeronomic data through monitoring of the thruster activity of the drag-free control systems.
Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a call
