建立了亚轨道火箭的六自由度运动数学模型,然后以设计出的亚轨道火箭为例,对箭体模型的线性化进行了详细推导,得出了线性化后的扰动方程;接着对动力系数进行定量分析,根据结果推导出简化的箭体传递函数;最后对亚轨道火箭箭体的动力学特性进行了仿真分析,仿真结果表明该火箭在1.676Ma和5.580Ma条件下分别处于静稳定和静不稳定的不同状态,与气动数据静稳定判定结果一致,为下一步控制系统设计打下基础。

Aiming at analyzing the dynamic characteristics for the suborbital launcher, the six-degree dynamics model for the suborbital launcher was established. Taking the designed rocket as an example, the linearization process for the dynamic model was clearly deduced. Subsequently, the linear equation of the pitching motion was obtained. Based on the quantitative analysis of dynamic coefficient, the transfer function was simplified. Finally, the simulation was carried out for the designed suborbital launcher. The results prove that the rocket are working at statically stable state on 1.676 Ma, but statically instability on 5.580 Ma, which is in accordance with the expected target of the experimental aerodynamic data. This paper lays the foundation for the flight control system.