ISO/TR 6832:2023 宇宙システム ― 熱真空チャンバーの開発技術 | ページ 2

Foreword

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This document was prepared by Technical Committee ISO/TC 20, Aircraft and space vehicles, Subcommittee SC 14, Space systems and operations.

Introduction

Since the first artificial satellite was launched into space successfully in 1957, space activities have been developed over the decades. The large amount of experience collected during that period demonstrates that a significant number of failures or defects appearing during spacecraft in-orbit operation were induced by space environment factors. These factors include space vacuum, cold black background, solar radiation, and also albedo and eigenradiation of the Earth. Therefore, thermal balance tests and thermal vacuum tests for spacecraft are performed in a simulated environment generated by ground simulation facilities in order to evaluate spacecraft performance, to verify thermal analysis models, and to discover early failures and defects in the spacecraft design and manufacturing process.

Countries engaged in spacecraft development have established several thermal test facilities, known as thermal vacuum chambers. They also have standardized requirements for thermal vacuum tests and thermal balance tests. These efforts greatly improved spacecraft reliability and played an important role in space activities.

A thermal vacuum chamber is designed to simulate vacuum, cold black and heat flux environment that a spacecraft experiences during its mission in space. It is composed of vacuum vessel, shroud, nitrogen system, vacuum system, heat flux simulation system, specimen support mechanism, measurement and control system, etc. Based on the state-of-the-art simulation technology, the relevant test standards and experiences accumulated from facilities development, this document provides development technology of a thermal vacuum chamber.

1 Scope

This document describes the technology for simulating space environments such as vacuum, cold black, and heat flux, as well as the compositions and functions of a thermal vacuum chamber (TVC). This kind of facility defined in this document is suitable for thermal vacuum tests (TVT) and thermal balance tests (TBT) on spacecraft-system level as well as on large-spacecraft-component level.

2 Normative references

There are no normative references in this document.

3 Terms and definitions

For the purposes of this document, the following terms and definitions apply.

ISO and IEC maintain terminology databases for use in standardization at the following addresses:

Bibliography