【摘要】 考虑末制导阶段捷联导引头视场角限制及攻击角度约束，提出一种基于三维比例导引攻击角度控制的导引律。首先，利用三维矢量制导模型和四元数理论实现三维比例导引的攻击角度预测，进而基于空间几何原理设计一种能够满足视场角约束的三维比例导引攻击角度控制方法。对闭环制导动力学进行分析，并采用李雅普诺夫原理证明视场角受限情况下的制导误差收敛性。分析该制导方法在导弹速度大小变化情况下的轨迹不变性，进而保证制导方法在速度大小变化情况下的有效性。理论分析和仿真校验结果说明了该方法的正确性和有效性。提出的方法可为视场角受限下的攻击角度控制导引律设计提供参考。更多还原

【Abstract】 Considering the limitation of field-of-view(FOV) and impact angle constraint of strapdown seeker in terminal guidance stage, a three-dimensional(3 D) impact angle control guidance law based on proportional navigation guidance(PNG) is proposed. Firstly, the 3 D vector guidance model and quaternion theory are used to predict the 3 D PNG impact angle. Then, an impact angle control law of 3 D PNG is designed based on spatial geometry principle. The closed-loop guidance dynamics is analyzed and the Lyapunov theory is used to prove the convergence of guidance error under limited FOV. The trajectory invariance of the guidance method is analyzed to ensure the effectiveness of the guidance method under the circumstance of velocity variation. Theoretical analysis and simulation results validate the effectiveness of the proposed method. The proposed method can provide a reference for the design of impact angle control guidance law with limited FOV.更多还原