基于准平衡滑翔的解析再入制导方法

针对高超声速滑翔飞行器再入制导问题，提出了一种基于准平衡滑翔的解析制导方法。在纵向基于准平衡滑翔条件建立再入航程与能量、倾侧角的解析关系，得到了倾侧角解析解，并通过高度变化率反馈使轨迹平滑；针对终端高度约束，在准平衡滑翔条件下得到常值航迹角假设，从而建立终端高度与再入航程、航迹角的解析关系，得到了航迹角指令，并通过设计反馈控制律得到攻角解析解。对于过程约束，提出了一种基于航迹角指令的在线约束控制方法。侧向制导采用航向角走廊确定倾侧角符号。仿真结果表明，该制导方法计算速度快、制导精度高、扰动条件下鲁棒性较强。

Analytical Reentry Guidance Method Based on Quasi-equilibrium Glide

An analytical reentry guidance method based on quasi-equilibrium glide is proposed for hypersonic glide vehicles. The analytical relationship among range, energy and bank angle is established based on the quasi-equilibrium glide condition, and the analytical solution of bank angle is obtained. The tra- jectory is smoothed by altitude rate feedback. For terminal altitude constraint, the analytical relationship among range, terminal altitude and flight path angle is established, and the solution of flight path angle is given based on the hypothesis of constant flight path angle deriving from quasi-equilibrium glide condition. Then the angle of attack command is obtained by designing feedback control law for flight path angle. For path constraints, an online constraint control method based on flight path angle command is proposed. The heading angle corridor is used to determine the sign of bank angle in lateral guidance. Simulated results show that the proposed algorithm is efficient in calculation with good accuracy and strong robustness.