The invention discloses a solid carrier rocket injection correction method which comprises the following steps: when a three-stage engine is shut down, acquiring the speed position state quantity of the rocket body; determining a sliding attitude instruction and fourth-stage ignition time according to the speed position state quantity and the orbit parameter information; adjusting the attitude of the rocket according to the sliding attitude instruction in the sliding attitude adjusting section until the rocket is adjusted to the four-stage fixed-axis attitude; when the fourth-stage ignition time is up, sending out a fourth-stage ignition instruction so that the rocket enters a fourth-stage active section; calculating the number of predicted injection orbits in the whole process of the four-stage active section at intervals of delta t4 according to an inner ballistic curve of an engine and engine state parameters; calculating to obtain a compensation value of the four-stage attitude angle instruction by predicting the number of injection orbits and the number of target orbits; and updating the fourth-stage attitude angle instruction according to the compensation value until the fourth-stage engine is used up and shut down. According to the method, the solid rocket engine is accurately shut down, and the injection cost is reduced due to the fact that the thrust terminating device does not need to be arranged.
本申请公开了一种固体运载火箭入轨修正方法,包括:在三级发动机关机时,获取箭体的速度位置状态量;根据速度位置状态量及轨道参数信息确定滑行姿态指令和四级点火时间;在滑行调姿段根据滑行姿态指令对火箭进行姿态调整,直至调至四级定轴姿态;在四级点火时间到达时,发出四级点火指令,使得火箭进入四级主动段;根据发动机的内弹道曲线及发动机状态参数,计算四级主动段全程每间隔时间Δt4的预测入轨轨道根数;通过预测入轨轨道根数与目标轨道根数计算获得四级姿态角指令的补偿值;根据补偿值对四级姿态角指令进行更新,直到四级发动机耗尽关机。本申请使得固体火箭发动机实现精准关机,由于不需要设置推力终止装置,降低了入轨成本。
Solid carrier rocket injection correction method
一种固体运载火箭入轨修正方法
2021-11-05
Patent
Electronic Resource
Chinese
IPC: | B64G Raumfahrt , COSMONAUTICS |
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