In this paper, an adaptive-estimate-incremental nonlinear dynamic inverse (AE-INDI) flight control method is proposed to address the issue of inaccurate angular acceleration signals in the thrust vector control of vertical/short takeoff and landing (V/STOL) aircraft. First, considering the change of center of gravity (CG) caused by aircraft structure transformation, a model for the deflection of a three-bearing swivel duct nozzle is established. This model corrects the equations for the aircraft's moment of inertia and angular rate under CG changes. Second, to account for modeling uncertainty and sensor noise, the angular acceleration is estimated by using the aircraft's actuator information and known states. The uncertainty is then compensated for using adaptive techniques. Finally, a stability analysis is performed based on Lyapunov theory to prove the robustness of the control method. Simulation results show that the proposed controller effectively mitigates interference from model uncertainty, stabilizes affected states within 2 s, weakens the effect of unfavorable sensor noise, and reduces the angular rate noise variance by 77.63%, thus verifying the effectiveness and robustness of the control method.

中文翻译：

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基于角加速度估计的推力矢量V/STOL飞机控制


针对垂直/短距起降（V/STOL）飞机推力矢量控制中角加速度信号不准确的问题，提出了一种自适应估计增量非线性动态逆（AE-INDI）飞行控制方法。 。首先，考虑飞机结构改造引起的重心变化，建立了三轴承旋转导管喷管偏转模型。该模型修正了重心变化下飞机转动惯量和角速率的方程。其次，为了考虑建模不确定性和传感器噪声，通过使用飞机的致动器信息和已知状态来估计角加速度。然后使用自适应技术来补偿不确定性。最后，基于Lyapunov理论进行稳定性分析，证明控制方法的鲁棒性。仿真结果表明，该控制器有效减轻了模型不确定性的干扰，在2 s内稳定了受影响的状态，减弱了不利传感器噪声的影响，角速率噪声方差降低了77.63%，验证了控制方法的有效性和鲁棒性。