| 摘要: |
| 考虑末制导阶段的攻击时间和攻击角度约束，提出了一种最大视场角约束下攻击时间和攻击角度可控的三维矢量制导律。首先，基于三维矢量制导模型，将二维平面最优制导律扩展至三维空间，通过李雅普诺夫稳定性分析证明了其在三维空间中能够满足攻击角度约束。其次，在三维矢量攻击角度约束制导律中引入估计剩余飞行时间偏置项，通过最优误差动力学设计出三维矢量攻击角度和攻击时间约束制导律，随后加入视场角约束函数，并通过理论分析证明了所提制导律的正确性。最后，通过数值仿真验证了所设计制导律在三维空间中可以同时满足视场角约束、攻击角度约束和攻击时间约束。 |
| 关键词: 导弹 三维非线性制导 视场角约束 攻击角度约束 攻击时间约束 |
| DOI： |
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| 基金项目:国家自然科学基金（62273178） |
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| Three-dimensional vector guidance law with impact time and angle control under FOV constraint |
| ZOU Haowen,ZHANG Min,CHEN Tao |
| (College of Automation, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China) |
| Abstract: |
| Considering the impact time and angle constraint in the terminal guidance stage, a three-dimensional (3D) vector guidance law with impact time and angle control under the maximum field of view (FOV) constraint is proposed. Firstly, the two-dimensional (2D) planar optimal guidance law is extended to 3D space based on the 3D vector guidance model, and Lyapunov theory is used to prove that it satisfies the impact angle constraint in 3D space. Secondly, the estimated time-to-go bias term is introduced into the 3D vector guidance law with impact angle constraint, and the optimal error dynamics is used to design the 3D vector guidance law with impact angle and time constraints, then the FOV constraint function is added. The correctness of the guidance law is proved by theoretical analysis. Finally, the numerical simulation verifies that the guidance law can satisfy the FOV constraint, the impact angle constraint, and the impact time constraint in 3D space. |
| Key words: Missile Three-dimensional nonlinear guidance Field of view(FOV) constraint Impact angle constraint Impact time constraint |
