氨电弧喷射推力器实验和数值研究

Experimental and Numerical Study on Ammonia Arcjet Thrusters

为了证实氨电弧喷射推力器良好的工作性能,对其进行了系统的实验和数值研究。在实验研究中建立了高真空实验系统、先进的小推力测量系统和恒定电流控制系统,在数值研究中采用二阶精度无波动、无自由参数的耗散差分格式(NND格式)数值求解耦合电磁源项的扩展N S方程组。通过实验获得了不同结构尺寸的推力器不同工作条件下的工作性能,通过数值模拟给出了推力器的流场结构,预计了其推力、比冲和推进效率。研究结果表明,氨电弧喷射推力器工作性能良好,能够担负一定的空间应用任务。

To attest finer operating performance of ammonia Arcjet Thrusters, comprehensive experimental and numerical study was performed on them. High vacuum experiment system, advanced small thrust measurement system and invariable electric current control system were set up in experimental study. Non-oscillatory and Non-free-parameters Dissipative finite difference scheme with second order accuracy was adopted to solve Navier-Stokes equations coupled with electromagnetic source terms in numerical study. Operating performance of thrusters with various structure and size under various working conditions is obtained in experimental study, and flow distributions within some thruster are presented and its thrust, specific impulse and thrust efficiency are predicted in numerical study. The outcomes show that ammonia Arcjet Thrusters are of finer operating performance and can be operated for some space missions.