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首页> 外文期刊>International journal of aerospace engineering >Flight Control Design for a Tailless Aircraft Using Eigenstructure Assignment
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Flight Control Design for a Tailless Aircraft Using Eigenstructure Assignment

机译：基于特征结构分配的无尾飞机飞行控制设计

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We apply eigenstructure assignment to the design of a flight control system for a wind tunnel model of a tailless aircraft. The aircraft, known as the innovative control effectors (ICEs) aircraft, has unconventional control surfaces plus pitch and yaw thrust vectoring. We linearize the aircraft in straight and level flight at an altitude of 15,000 feet and Mach number 0.4. Then, we separately design flight control systems for the longitudinal and lateral dynamics. We use a control allocation scheme with weights so that the lateral pseudoinputs are yaw and roll moment, and the longitudinal pseudoinput is pitching moment. In contrast to previous eigenstructure assignment designs for the ICE aircraft, we consider the phugoid mode, thrust vectoring, and stability margins. We show how to simultaneously stabilize the phugoid mode, satisfy MIL-F-8785C mode specifications, and satisfy MIL-F-9490D phase and gain margin specifications. We also use a cstar command system that is preferable to earlier pitch-rate command systems. Finally, we present simulation results of the combined longitudinal/lateral flight control system using a full 6DOF nonlinear simulation with approximately 20,000 values for the aerodynamic coefficients. Our simulation includes limiters on actuator deflections, deflection rates, and control system integrators.
机译：我们将本征结构分配应用于无尾飞机风洞模型的飞行控制系统的设计中。该飞机被称为创新控制效应器（ICE）飞机，具有非常规的控制面以及俯仰和偏航推力矢量。我们在15,000英尺的高度和0.4马赫数的直线和水平飞行中线性化飞机。然后，我们分别为纵向和横向动力学设计飞行控制系统。我们使用具有权重的控制分配方案，以使横向伪输入为偏航和侧倾力矩，而纵向伪输入为俯仰力矩。与以前的ICE飞机本征结构分配设计相反，我们考虑了phugoid模式，推力矢量和稳定性裕度。我们展示了如何同时稳定倒相模式，满足MIL-F-8785C模式规范以及满足MIL-F-9490D相位和增益裕度规范。我们还使用了cstar命令系统，它比早期的变桨率命令系统更好。最后，我们使用完整的6DOF非线性仿真（具有大约20,000的空气动力学系数值）来提供组合的纵向/横向飞行控制系统的仿真结果。我们的仿真包括对执行器偏转，偏转率和控制系统积分器的限制器。

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