1.1目的: 1.1.1本规程的主要目的是为航天器和组件进行充分的热平衡测试提供指导，其中太阳模拟被确定为适用方法。认真遵守本文件应确保充分模拟空间辐射环境，以进行航天器热测试。 1.1.2必然的目的是为航天器的系统集成测试提供适当的测试环境。热平衡的精确空间模拟测试通常将为在各种任务模式下操作所有电气和机械系统提供良好的环境，以确定整个系统内的干扰。尽管遵守本规程将为此类测试提供正确的热环境，但没有讨论支持系统所需的大量电子设备和程序- 集成测试。 1.2不适用性-本规程不适用于以下类型的测试，也不提供不完整的覆盖范围: 1.2.1航天器的发射阶段或大气再入， 1.2.2行星表面着陆器， 1.2.3热涂层的降解， 1.2.4机械装置空间摩擦增加，有时称为“冷焊” 1.2.5太阳传感器， 1.2.6太空人， 1.2.7能量转换装置，以及 1.2.8部件泄漏、放气、辐射损伤或整体热性能测试。 1.3适用范围: 1.3.1航天器、设计理念和分析工作的极端多样化使得编写一份简短、简洁的文件变得不可能。因此，在7.6中的图表中对各种航天器参数进行了分类，并与空间模拟器的重要特性相关。 1.3.2热平衡测试的最终结果是证明热设计符合热设计师的要求。 必须为他们提供灵活性，以权衡模拟器不足带来的额外分析工作。综合热分析模型、现代计算机和称职的分析员团队的结合大大降低了对空间模拟精度的要求。 1.4实用性-本推荐规程将在从开发到飞行验收测试的航天器测试阶段有用。它应在子系统和航天器热控制模型设计阶段的早期为空间模拟测试提供指导。飞行航天器经常在发射前进行测试。有时，在姐妹航天器发射后，会在太空舱中进行测试，以帮助分析太空中发生的异常情况。 1.5本标准无意解决与其使用相关的所有安全问题（如有）。本标准的用户有责任在使用前制定适当的安全和健康实践，并确定监管限制的适用性。

1.1 Purpose: 1.1.1 The primary purpose of this practice is to provide guidance for making adequate thermal balance tests of spacecraft and components where solar simulation has been determined to be the applicable method. Careful adherence to this document should ensure the adequate simulation of the radiation environment of space for thermal tests of space vehicles. 1.1.2 A corollary purpose is to provide the proper test environment for systems-integration tests of space vehicles. An accurate space-simulation test for thermal balance generally will provide a good environment for operating all electrical and mechanical systems in their various mission modes to determine interferences within the complete system. Although adherence to this practice will provide the correct thermal environment for this type of test, there is no discussion of the extensive electronic equipment and procedures required to support systems-integration testing. 1.2 Nonapplicability -This practice does not apply to or provide incomplete coverage of the following types of tests: 1.2.1 Launch phase or atmospheric reentry of space vehicles, 1.2.2 Landers on planet surfaces, 1.2.3 Degradation of thermal coatings, 1.2.4 Increased friction in space of mechanical devices, sometimes called "cold welding," 1.2.5 Sun sensors, 1.2.6 Man in space, 1.2.7 Energy conversion devices, and 1.2.8 Tests of components for leaks, outgassing, radiation damage, or bulk thermal properties. 1.3 Range of Application: 1.3.1 The extreme diversification of space-craft, design philosophies, and analytical effort makes the preparation of a brief, concise document impossible. Because of this, various spacecraft parameters are classified and related to the important characteristic of space simulators in a chart in 7.6. 1.3.2 The ultimate result of the thermal balance test is to prove the thermal design to the satisfaction of the thermal designers. Flexibility must be provided to them to trade off additional analytical effort for simulator short-comings. The combination of a comprehensive thermal-analytical model, modern computers, and a competent team of analysts greatly reduces the requirements for accuracy of space simulation. 1.4 Utility -This recommended practice will be useful during space vehicle test phases from the development through flight acceptance test. It should provide guidance for space simulation testing early in the design phase of thermal control models of subsystems and spacecraft. Flight spacecraft frequently are tested before launch. Occasionally, tests are made in a space chamber after a sister spacecraft is launched as an aid in analyzing anomalies that occur in space. 1.5 This standard does not purport to address all of the safety problems, if any, associated with its use. It is the responsibility of the user of this standard to establish appropriate safety and health practices and determine the applicability of regulatory limitations prior to use.