高精度姿态跟踪非合作目标的控制方法研究

Small scale vehicle is becoming smarter, and its quest is becoming more complex. Once released by the carrier, its attitude control system must be autonomous in high precision attitude regulation and smooth attitude maneuvering. Searching, capturing and tracking of non-cooperative objects should be accomplished without external helping information. This project is to investigate into attitude control strategy and algorithm designed for attitude stabilization and attitude maneuver for extra-atmosphere small scale vehicle. Objective of attitude control system is to track non-cooperative target with high precision. Attitude precision is affected by the Minimum Pulse Effect of fixed-thrust propellers. Non-cooperative target may be lost and need a full scan to get recaptured. To eliminate Initial attitude pinpointing error, or iterate through the scan range of recapture procedure, big scale attitude maneuvering is required while angular speed must be constraint. So, three major research topics in this project are: Phase modulation technique of fixed-thrust propeller to improve attitude control precision; recovering and recapturing strategy when target is lost in the sight field; algorithm for big scale attitude maneuver under angular speed constraint. Based on theoretical analyze and mathematical modeling, a simulation system will be build to verify the proposed algorithms and methods. Research achievements will be constructive and supportive to further exploitation related to smart small extra-atmosphere vehicle.

随着空间小型飞行器智能化程度需求的提高，需要空间小型飞行器在分离母舱后，在没有外部合作信息的条件下，能够自主完成高精度的姿态稳定控制和姿态机动控制，以实现对非合作目标的搜索、捕获、跟踪等任务，本项目针对该需求，研究了常值推力发动机相位调制技术，以获得接近连续的发动机推力输出，解决常值推力发动机最小推力脉冲带来的姿态精度和稳定度限制的问题，研究了角速度受限的大姿态机动控制方法，以实现大姿态调整的平稳过渡，解决空间小型飞行器由于初始对准姿态误差过大和对目标跟踪过程中目标丢失后的再捕获需要大姿态机动问题，开展了目标再捕获策略研究，以完成对目标的再搜索、捕获和跟踪，解决飞行器目标跟踪过程中目标丢失后的再捕获策略问题。在理论分析和仿真建模的基础上，完成仿真软件编写。本项目研究结果将为空间小型智能飞行器设计和相关研究提供支持。

空间小型飞行器智能化程度需求的提高，需要空间小型飞行器在分离母舱后，在没有外部合作信息的条件下，能够自主完成高精度的姿态稳定控制和姿态机动控制，以实现对非合作目标的搜索、捕获、跟踪等任务，本项目针对该需求，研究了常值推力发动机相位调制技术，以获得接近连续的发动机推力输出，解决常值推力发动机最小推力脉冲带来的姿态精度和稳定度限制的问题。在理论分析和仿真建模的基础上，完成仿真软件编写。本项目研究结果将为空间小型智能飞行器设计和相关研究提供支持。