一种应用于静不稳定飞行器的级间分离稳定控制方法
By selecting the three-axis attitude angular velocity as the state variable in a multi-stage aircraft, establishing state equations and filters, and combining the attitude controllable boundary model to determine the start-up time in real time, the problem of attitude instability in multi-stage aircraft during inter-stage separation is solved, and stable control is achieved.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- SHANGHAI AEROSPACE CONTROL TECH INST
- Filing Date
- 2023-12-26
- Publication Date
- 2026-07-17
AI Technical Summary
During the separation process between stages of a multi-stage spacecraft, the spacecraft is affected by a large number of elastic vibrations. Existing technologies cannot accurately determine the start-up time, which can lead to attitude instability and possible interference and collision between the spacecraft and the boosters.
By selecting the three-axis attitude angular velocity as the state variable, state equations and measurement equations are established. An attitude angular velocity filter is used to filter out elastic vibration signals. The start-up time is determined in real time by combining the attitude controllable boundary model and integrated navigation data. A control strategy for the stability control system is designed.
It enables accurate determination of launch time under conditions of large-scale elastic vibration, avoids interference and collision between the spacecraft and the booster, and ensures stable attitude control of the spacecraft.
Smart Images
Figure CN117826834B_ABST