小型航天器液化气推进系统的数值模拟

为研究小型航天器液化气推进系统的工作性能,依据质量、能量守恒方程建立了一维、单组元液化气自蒸发过程的数值模型。利用模型对温度、压力、质量流量等主要参数进行了理论仿真,并搭建试验平台进行测试验证。N2O自蒸发实验表明模型仿真与相应测试结果吻合良好,证明了该模型在假设条件下的有效性。该数值模型适用于所有真实气体的液化气推进、冷气推进,以及外太空真空、零重力条件下的液化气推进。研究结果可用于评估小型航天器的液化气发动机。

Numerical simulation of liquefied gas self-pressurization for small spacecraft propulsion systems

A one-dimensional, heterogeneous liquefied gas self-pressurization computer model was developed based on mass and energy conservation equations to study performance of liquefied gas propulsion systems for small spacecrafts. Parameters were simulated using the model including the temperatures, pressures and mass flow rates. The model's results for N2O liquefied gas agree well with experimental data. The model can be applied to other liquefied gases as well as non-liquefied gases for the conditions of zero gravity and zero ambient pressure in the outer space. The model can be used to assess liquefied gas propulsion systems for small space vehicles.