大型航天器结构热稳定性试验系统设计与实现

Design and Implementation of Thermal Stability Testing System for Large Spacecraft Structures

摘要:

结构形面热稳定性是航天器结构设计的重要指标之一，对航天器在轨真空低温环境下功能与性能的实现具有重要作用，为确保航天器结构热稳性设计的正确性，需在地面开展空间环境热稳定性测试试验；针对大尺寸结构高精度、高频率热变形测量需求开展研究，采用光学摄影原位变形测量技术，设计了多相机融合测量系统架构及测量方法，有效保证了大型结构最优变形测量场的构建，并通过系统机电、图像采集装置的智能化同步控制设计，实现了图像数据的空间位置属性的自动匹配；通过试验验证，结果表明该系统可满足真空低温环境下尺寸不小于4米的瞬态、高精度结构变形测量，最小测量周期可达90s，单向测量精度优于28μm，测试过程运行稳定可靠。

Abstract:

The thermal stability of structural surfaces is one of the important indicators for spacecraft structural design, which plays an important role in achieving the functionality and performance of spacecraft in the vacuum and low temperature environment of orbit. To ensure the correctness of structural thermal stability design, it is necessary to conduct thermal stability testing tests in space environmental on the ground surface of spacecraft structures. The research on the high-precision and high-frequency thermal stability deformation testing requirements of large-scale structures was conducted. Using optical photography in-situ deformation measurement technology, a multi camera fusion measurement system architecture and measurement method were designed, effectively ensuring the construction of the optimal deformation measurement field for large structures. Through the intelligent synchronous control design of the system electromechanical and image acquisition devices, automatic matching of spatial position attributes of image data was achieved. Through verification of the experimental system, the results showed that the system can meet the transient and high-precision structural deformation measurement of no less than 4 meters in vacuum and low-temperature environments. The minimum measurement period can reach 90 seconds, and the unidirectional measurement accuracy is better than 28μm. The testing process runs stably and reliably.