Analysis and improvement of lateral instability of quasi-biconical lifting reentry spacecraft
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摘要:
类双锥型升力式返回器的横航向稳定性对其理想再入策略的实施构成严苛的约束，且在设计阶段需要进行专门分析。针对类双锥型升力式返回器的标称再入过程，使用数值仿真方法计算该飞行器在全速域、宽迎角范围内的横航向稳定性，结合流场特征分析亚/跨/超声速速域内的横航向稳定性突变规律；重点分析涡流发生器、航向增强型面、重心偏置对横航向稳定性的影响及其作用机理，最终确定了航向舵偏转与重心偏置相结合的方案就是最佳横航向增稳方案。
Abstract:The lateral stability of the quasi-biconical lifting reentry spacecraft is a strict constraint on the implementation of its ideal reentry strategy, which requires specialized analysis in the design stage. In this paper, for the nominal reentry process of the quasi-biconical lifting reentry spacecraft, the lateral stability of the spacecraft in the range of full speed and wide angle of attack was calculated by using the numerical simulation method. According to the flow field characteristics, the mutation regularity of the lateral stability in the sub-/trans-/supersonic domain was analyzed. Then, the effect of the eddy current generator, lateral stability enhancement surface, and center-of-gravity offset on the lateral stability was analyzed, as well as the corresponding mechanism. The results reveal that the combination of rudder deflection and center-of-gravity offset is the optimal solution to enhance lateral stability.
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图 4 返回器横航向特性随马赫数变化
Figure 4. Changes in the lateral features of reentry spacecraft with Mach number
图 6 横航向压心位置随迎角变化（Ma = 5）
Figure 6. Variation of lateral pressure center with angle of attack (Ma = 5)
图 11 涡流发生器不同安装位置及对应流场速度分布
Figure 11. Vortex generator locations and corresponding field velocity distribution
图 13 使用航向增强型面流场速度分布
Figure 13. Flow field velocity distribution with lateral stability enhancement surfaces
图 14 不同构型返回器与xy平面交线压力分布对比
Figure 14. Pressure distribution on intersection lines of xy plane and reentry spacecraft with different configurations
图 15 航向增强返回器横航向特性计算结果分析
Figure 15. Calculated lateral feature of reentry spacecraft lateral stability enhancement analysis
图 16 重心下偏6%返回器横航向特性计算结果
Figure 16. Calculated lateral features of reentry spacecraft center-of-gravity offset 6%
表 1 类神舟返回器计算值与实验值对比
Table 1. Comparison of calculated and experimental values of Shenzhou-like reentry spacecraft
参数项 CA CN CL CD Cm 预测值 1.315 0.1587 − 0.3006 1.290 0.0999 实验值 1.335 0.1590 − 0.3072 1.309 0.1025 
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