快速响应空间固体运载火箭轨道转移级以最大限度利用能量而非消耗能量为目的进行耗尽关机制导,基于椭圆轨道理论和牛顿迭代法,提出了一种适用于具有轨道、制导多种约束的耗尽关机闭路制导方法,通过实时寻找需要推力方向,充分利用轨道转移级能量,导引上面级进入具有给定轨道倾角和最大高度约束的转移轨道,同时实现耗尽关机。理论推导和数学仿真表明,本文提出的制导方法能在耗尽关机条件下实现对转移轨道的高精度控制。 Based on elliptic orbit theory and Newton iterative method, a fast response space solid-propellant rocket orbit transfer stage is proposed to use depletion shutdown to maximize the energy instead of the energy consumption. To make full use of the orbital transfer level energy by guiding the upper stage into the transfer orbit with the given orbital inclination and the maximum height constraint by finding the direction of thrust needed in real time and implementing the exhausted shutdown. The theoretical derivation and mathematical simulation show that the guidance method proposed in this paper can realize the high-precision control of the transfer orbit under the conditions of exhausted shutdown.