Abstract: In order to obtain a calculation method which can solve the operating parameters of the vortex valve SRM thrust modulation fastly and study the influence law of vortex valve SRM thrust modulation affected by control flow parameters，a theoretical calculation model which provides evidence for further study of the vortex valve SRM thrust modulation’s design and theoretical analysis was improved. The results show that: (1)The model’s maximum relative error is 10.84%;(2)Improving the temperature of the control flow can promote the thrust modulation under a working condition with similar pressure，flow and molecular weight; (3)Comparing with the pressure of the control flow，flow has greater effect on thrust modulation; (4)Increasing the gas generator’s burning surface can not only increase the vortex valve SRM thrust modulation，but also decrease the engine’s specific impulse loss.

Key words: Solid rocket motor；Thrust modulation；Vortex valve；Control flow；Numerical calculation

摘要： 为快速求解涡流阀固体变推力发动机的工作参数、研究控制流参数对涡流阀固体变推力发动机的影响规律，改进了求解涡流阀固体变推力发动机工作参数的理论计算模型，并利用该模型研究了控制流参数对涡流阀固体变推力发动机推力调节性能的影响规律。结果表明:该模型最大相对误差为10.83%，可用于涡流阀固体变推力发动机的计算分析；在控制流压强与控制流流量相同及分子量相当的情况下，提高控制流温度可以提高推力调节比；控制流流量是决定涡流阀固体变推力发动机推力调节比最重要的参数；增加燃气发生器的燃面，不仅可以提高涡流阀固体变推力发动机的推力调节比，同时可以减小发动机的比冲损失。

关键词: 固体火箭发动机；推力调节；涡流阀；控制流；数值计算