【摘要】 针对可重复使用火箭回收过程中的动力减速段推力调节能力有限且初始偏差大问题，提出了一种基于3通道解耦的多约束解析制导方法。首先，为减小推力调节需求，通过预测从当前状态运动至目标速度、位置所需的推力，建立自适应开机时间指令生成方案，优化推力使用效率。然后，参照传统迭代制导方法，推导满足三方向速度、两方向位置约束的程序角指令；在此基础上引入推力调节机制并实现通道解耦，从而达成对末端三方向速度与位置的精确约束，保障回收精度。仿真结果表明，该自适应制导方法不仅具备较高的制导精度，且对推力调节的需求显著降低；同时，其采用完全解析设计，计算量小，能够充分满足当前垂直回收火箭的箭载算力要求，无需额外升级硬件，具备良好的工程应用前景与推广价值。更多还原

【Abstract】 Constrained thrust modulation capability and substantial initial deviation exist in the powered deceleration phase during the recovery of reusable launch vehicles, which affect the recovery accuracy and safety. To address these issues, a multi-constraint analytical guidance approach based on three-channel decoupling is proposed. First, to reduce the demand for thrust adjustment, the thrust required to transition from the current state to the target velocity and position is predicted, and an adaptive ignition-timing command-generation scheme is established. Then, program-angle commands that satisfy velocity constraints in three directions and position constraints in two directions are derived by drawing on traditional iterative guidance methods. On this basis, thrust adjustment is introduced and the channels are decoupled to achieve precise terminal constraints on velocity and position in all three directions. Simulation results demonstrate that high guidance accuracy is achieved by the proposed adaptive guidance method, and the demand for thrust adjustment is minimal. In addition, it is fully analytical with low computational complexity, which fully meets the onboard computingpower requirements of current vertical-landing rockets and exhibits excellent prospects for engineering application.更多还原