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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。
In order to study the working performance of liquefied gas propulsion system for small spacecraft, a numerical model of one-dimensional and one-component liquefied gas self-evaporation process was established based on the mass and energy conservation equations. The model was used to simulate the main parameters such as temperature, pressure and mass flow, and a test platform was set up for testing and verification. N2O self-evaporation experiments show that the model simulation is in good agreement with the corresponding test results, which proves the validity of the model under the assumption. The numerical model is suitable for all real gas liquefied gas propulsion, air-conditioning propulsion, and extra-space vacuum, liquefied gas propulsion under zero-gravity conditions. The results of the study can be used to evaluate the liquefied gas engines of small spacecraft.