可重复使用航天器IMU动态精度评估方法  

IMU Dynamic Accuracy Evaluation Method for Reusable Spacecraft

作　　者：任焜[1] 龚宇莲[1] 蔺玥 颜军[1] REN Kun;GONG Yulian;LIN Yue;YAN Jun(Beijing Institute of Control Engineering,Beijing 100094,China)

机构地区：[1]北京控制工程研究所,北京100094

出　　处：《空间控制技术与应用》2023年第5期38-46,共9页Aerospace Control and Application

基　　金：国家高技术发展计划(863)(H8634003AA0231-2-01)。

摘　　要：可重复使用航天器使用的惯性测量单元(IMU)既需要满足空间段长期在轨使用需求,又需要满足再入大气过程较严酷的力学振动环境及高动态下的高精度导航需求.针对可重复使用航天器对IMU的需求,本文对研制过程中动态精度设计和验证方法进行了总结,并介绍了一种六自由度振动IMU精度试验方法,该方法能够更真实模拟再入力学环境,可从系统需求出发,对IMU动态精度进行综合评估,为其他天地往返类型航天器提供参考.The inertial measurement unit(IMU)deployed on the reusable spacecraft not only meets the needs of long-term space segment,but also needs to have high dynamic performance to meet the needs of high-precision nav-igation during re-entry.According to the needs of IMU deployed on the reusable spacecraft,the methods of dynam-ic accuracy design and verification in the development of reusable spacecraft IMU are summarized,and a six-de-gree-of-freedom vibration IMU accuracy test method is introduced.The method can simulate the re-entry mechani-cal environment more realistically,and can be triggered by system requirements to comprehensively evaluate the dy-namic accuracy of IMU.It can also provide reference for other types of reusable spacecraft.

关 键 词：惯性测量单元 频率特性 六自由度振动 可重复使用航天器 评估 

分 类 号：V412.4[航空宇航科学与技术—航空宇航推进理论与工程]