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无尾飞翼通常利用开裂式阻力方向舵(SDR)对称偏转方式控制其偏航,该方式简单有效,但约束了SDR上下舵面只做对称偏转,限制了舵面的分配与控制模式,降低了飞机在俯仰轴和滚转轴上的最大可用力矩,影响了飞机低速飞行时的操纵性能。针对此问题,利用CFD方法分析了某无尾飞翼SDR对称/非对称偏转方式的舵面操纵特性,提出了一种基于包络体坐标变换的优化控制分配方法,研究了其分配效率。仿真结果表明,该方法分配效率较高,可以拓展SDR非对称偏转时的可达转矩集,增强对俯仰轴和滚转轴的控制能力,改善飞机的机动性。
The tailless flying wing usually controls its yaw by means of the symmetrical deflexion of deflective resistance rudder (SDR), which is simple and effective. However, constraining only the symmetrical deflections of the upper and lower control surfaces of the SDR restricts the distribution and control modes of the control surface and reduces The maximum torque available on the pitch and roll axes affects the handling of the aircraft at low speed. In order to solve this problem, CFD method was used to analyze the control surface of SDR symmetrical / asymmetrical deflection of a tailless flying wing. An optimized control allocation method based on envelope coordinate transformation was proposed and its distribution efficiency was studied. The simulation results show that this method has a high distribution efficiency, which can expand the reachable torque set of SDR asymmetric deflection, enhance the control ability of pitch axis and roll axis, and improve the maneuverability of aircraft.