高超声速飞行器脉冲风洞测力系统研究

吸气式高超声速飞行器具有各系统高度耦合的特点，现阶段的主要研究手段是在脉冲燃烧风洞中开展一体化飞行器带动力试验。针对脉冲燃烧风洞的特点，发展了一体化飞行器风洞试验快速测力方法。对试验模型和天平组成的测力系统进行了建模，获得了测力系统结构设计准则；采用数值仿真和锤击法获得了测力系统的模态，对试验过程中模型振动信号进行分析研究。结果表明:测力系统的振动频率满足测力要求，且其振动形式与锤击法测定模态一致。在脉冲燃烧风洞中开展的飞行器带动力试验结果表明:测力系统满足脉冲燃烧风洞测力要求，能够获得大尺度高超声速一体化飞行器气动力载荷，且满足精度要求，证明了在脉冲燃烧风洞中开展大尺度高超声速一体化飞行器技术研究的可行性。

Research on the force measuring system of hypersonic vehicle in the impulse wind tunnel

Strong coupling is the salient feature of the hypersonic airbreathing vehicle. Currently the most important research method is the powered experiment of the full system vehicle in impulse combustion wind-tunnel. Firstly, based on the characteristics of the impulse wind tunnel, a fast measurement method of an integrated vehicle wind-tunnel experiment was developed in this paper. The dynamic equation of the force measurement system consisting of the test model and the balance was derived and a structural designation rule was obtained by analyzing the equation. Then, the mode analysis of the force measurement system was conducted through the simulation and the hammering test, and also the vibration signal was monitored by the acceleration sensor. The results show that the frequency of the model system meets the request of the force measurement and the vibration shape is in consistent with hammering test mode. Finally, the impulse combustion wind-tunnel experiment of the powered vehicle was carried out and the result proves that the designed model could meet the request of the impulse combustion wind-tunnel and could acquire the accurate aerodynamic load of the large-scale hypersonic integrated vehicle. All the above investigation proves that it is practical to do the research of the large-scale hypersonic integrated vehicle in the impulse combustion wind-tunnel.