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面向多约束下高超声速飞行器末制导过程中的通道耦合、参数扰动、模型失配等突出问题,设计一种适于高超声速飞行器的三维非线性自适应末制导律。为了模型描述的完整性和简洁性,引入视线旋量和旋量速度的概念,并基于此建立三维制导参考模型和实际系统的表达式;为了保证制导律的鲁棒性和自适应性,基于自适应控制理论,设计一种三维非线性自适应制导律;通过数学推导证明了该制导律的稳定性。该制导律能够从理论上克服高超声速飞行器末制导面临的通道耦合、参数扰动、模型失配等突出问题,满足多约束制导要求。仿真结果验证了所设计制导律的有效性。
To overcome the prominent problems of channel coupling, parameter perturbation and model mismatch in hypereutectic hypersonic vehicles under multiple constraints, a three-dimensional nonlinear adaptive final guidance law for hypersonic vehicles is designed. In order to describe the completeness and conciseness of the model, the concept of line of sight spin and spin speed is introduced, and based on which the three-dimensional Guidance Reference Model and the expression of the actual system are established. In order to ensure the robustness and self-adaptability of Guidance Law, Adaptive control theory, a three-dimensional nonlinear adaptive guidance law is designed. The stability of the guidance law is proved by mathematical derivation. The guidance law can theoretically overcome the salient issues of channel guidance, parameter perturbation and model mismatch faced by the hypersonic vehicle final guidance and meet the requirements of multi-constraint guidance. The simulation results verify the effectiveness of the designed guidance law.