头尾交替对日连续偏航姿态控制策略
Attitude control schemes of yaw steering with front and back pointing to the sun alternately
王曦 1陈长青 2徐小平 1黄震1
作者信息
- 1. 北京空间飞行器总体设计部,北京 100094
- 2. 北京控制工程研究所,北京 100094
- 折叠
摘要
航天器在传统连续偏航模式下,绕偏航轴在一定角度范围内来回摆动,使航天器头部或尾部始终受到阳光直射,导致舱外设备的热设计需要花费额外的重量功耗代价.提出了头尾交替对日连续偏航的姿态控制策略,为航天器提供了受晒均匀的热环境,不仅简化了舱外设备的热设计,还有利于提高对温度范围波动敏感的设备在轨工作的可靠性.从发电量与推进剂消耗量两方面,比较了3种头尾交替对日连续偏航的姿态控制策略,将综合指标最优的余角偏航控制策略成功应用在了天舟一号货运飞船上.
Abstract
In the traditional yaw-steering mode,spacecraft swings back and forth around the yaw axis within a certain angle range,causing the spacecraft's front or back to be always exposed to direct sunlight,resulting in additional weight and power consumption costs for the thermal design of extravehicular equipment.A yaw-steering attitude con-trol strategy with front and back pointing to the sun alternately is proposed,providing spacecraft with a uniformly ex-posed thermal environment.This not only simplifies the thermal design of extravehicular equipment,but also improves the reliability of the in-orbit equipment sensitive to temperature range fluctuations.Three attitude control strategies for yaw-steering with front and back pointing to the sun alternately are compared in terms of power generation and propel-lant consumption.The complementary-angle control strategy with the optimal comprehensive index is successfully ap-plied to the Tianzhou-1 cargo spacecraft.
关键词
连续偏航/姿态控制/头尾交替对日/货运飞船/天舟一号Key words
yaw steering/attitude control/pointing to the sun alternately/cargo spaceship/Tianzhou-1引用本文复制引用
出版年
2025
国家科技期刊平台
NSTL
万方数据