1.1 本指南的目的是为当前和发展中的太空飞行运营商提供指导，他们打算让人类乘坐航天器。乘客包括轨道飞行器中的机组人员和太空飞行参与者。本指南主要针对地面发射的近地轨道（LEO）航天器，这些航天器提供从地面到轨道的运输，然后与轨道复合体进行后续交会或短时间的自由飞行轨道操作，并安全返回地球表面。正如指南中所使用的，LEO是一个距离地球表面约2000公里的近似圆形轨道。轨道空间站上持续时间较长（>约两周）的太空飞行带来了独特的设计和医疗限制，本指南未具体说明。 1.2 本指南中的方法是最佳实践。拥有先前的积极执行系统可能是遵守本指南的基础。 1.2.1 这是一个非全面的最佳安全实践子集，用于机组人员在灾难性危险中的生存能力，所有的容错能力都已耗尽。这一点在 1.5 和 4.2 。 1.3 单位-- 以国际单位制或英寸磅单位表示的数值应单独视为标准。每个系统中规定的值可能不是完全相等的；因此，每个系统应独立使用。将两个系统的值结合起来可能会导致不符合标准。 1.4 每个航天器都将提出自己的一组安全隐患，本标准的用户应在可行的情况下分析并实施生存能力选项。 此外，请注意，安全是系统的固有特征，而不是几个关键的灾后缓解功能的产物。历史表明，一个安全成功的航天系统是按照设计稳健性、制造质量、检查、测试和运行（包括维护和维持工程）的最高标准建造和运行的。本指南中建议添加的设计特征和功能不能也不是为了弥补这些基础知识的不足。本标准的用户有责任在使用前制定适当的安全、生存能力、健康和环境实践，并确定监管限制的适用性。例如，在生存能力方面，某些运营商可能需要在允许其航天器搭载机组人员之前提供额外的机组人员生存能力。 1.5 本标准并不旨在解决与其使用相关的所有安全或生存性设计问题（如有）。本标准的用户有责任在使用前制定适当的安全、生存能力、健康和环境实践，并确定监管限制的适用性。 1.6 本国际标准是根据世界贸易组织技术性贸易壁垒委员会发布的《关于制定国际标准、指南和建议的原则的决定》中确立的国际公认的标准化原则制定的。 ===意义和用途====== 4.1 机组人员安全是载人航天的一个复杂而全面的目标。 整个航天器的设计目的是让机组人员安全地往返于近地轨道（LEO）目的地。本着规范精神 F3479 ，亚轨道车辆乘员安全的故障容限，故障容限或故障容限不切实际的等效控制手段，是预防设计中无法消除的灾难性危险的主要控制手段。这适用于所有可能导致灾难性事件的危险。航天器的设计也可以提高故障容忍度，以提高任务成功的可能性。 4.2 本指南侧重于在故障容限耗尽时支持机组生存能力所需的设计和操作能力。 例如，一个航天器可能有三台执行相同功能的任务计算机。管理飞行操作的典型规则可能允许在第一次失败后继续执行任务。第二次失败后，任务中止可能会使用剩下的一台任务计算机将航天器返回安全地带。如果第三台计算机出现故障，应急系统可在可能的情况下帮助机组人员返回安全地带，而这些系统正是本指南的重点。请注意，对于本文所述的每种紧急情况，都将提供一套应急程序和执行这些程序的设备，以便船员生存。 4.3 LEO任务分为发射前、上升、轨道、再入和着陆。 请注意，对于在低地球轨道以外的载人运输和在低地球地球轨道上载人持续时间超过约30天的任务，有单独的额外考虑因素，这些都不在本指南的范围内。

1.1 The purpose of this guide is to provide guidance for current and developing space flight operators who intend to fly humans on spacecraft. The occupants include the crew and spaceflight participants in the orbital vehicles. This guide is targeted primarily toward ground launched, Low Earth Orbit (LEO) spacecraft which provide transportation from the surface to orbit followed by subsequent rendezvous with an orbital complex or short-duration free flight orbit operations, and safe return to Earth’s surface. As used in the guide, LEO is an approximate circular orbit within ~2000 km of Earth’s surface. Longer duration spaceflight (>approximately two weeks) aboard an orbital space station poses unique design and medical constraints which are not specifically addressed in this guide. 1.2 The methods in this guide are best practices. Having prior positive performing systems may be a basis for compliance to this guide. 1.2.1 This is a non-comprehensive subset of best safety practices for crew survivability of catastrophic hazards for which all failure tolerance has been exhausted. This is further elaborated upon in 1.5 and 4.2 . 1.3 Units— The values stated in either SI units or inch-pound units are to be regarded separately as standard. The values stated in each system may not be exact equivalents; therefore, each system shall be used independently of the other. Combining values from the two systems may result in nonconformance with the standard. 1.4 Each spacecraft will present its own set of safety hazards that the user of this standard is expected to analyze and implement survivability options where practical. Also, note that safety is an inherent characteristic of a system, not the product of a few key post-hazard mitigation features. History has shown that a safe and successful spaceflight system is built and operated to the highest possible standards of design robustness, manufacturing quality, inspection, test, and operation, including maintenance and sustaining engineering. The addition of the design features and capabilities as recommended in this guide cannot and is not intended to make up for deficiencies in these basics. It is the responsibility of the user of this standard to establish appropriate safety, survivability, health, and environmental practices and determine the applicability of regulatory limitations prior to use. For example, with regard to survivability, certain operators will likely require additional crew survivability capabilities be provided prior to permitting their space vehicle to fly a crew. 1.5 This standard does not purport to address all of the safety or survivability design concerns, if any, associated with its use. It is the responsibility of the user of this standard to establish appropriate safety, survivability, health, and environmental practices and determine the applicability of regulatory limitations prior to use. 1.6 This international standard was developed in accordance with internationally recognized principles on standardization established in the Decision on Principles for the Development of International Standards, Guides and Recommendations issued by the World Trade Organization Technical Barriers to Trade (TBT) Committee. ====== Significance And Use ====== 4.1 Flight crew safety is a complex and all-encompassing goal of human spaceflight. The entire spacecraft is designed to get the flight crew safely to and from their Low Earth Orbit (LEO) destination. In the spirit of Specification F3479 , Failure Tolerance for Occupant Safety of Suborbital Vehicles, failure tolerance, or an equivalent means of control where failure tolerance is impractical, is the primary control for prevention of catastrophic hazards that cannot be eliminated from the design. This is true for all hazards which may result in a catastrophic event. The spacecraft can be also be designed with increased levels of failure tolerance to enhance the likelihood of mission success. 4.2 This guide is focused upon the design and operational capabilities necessary to support flight crew survivability when failure tolerance has been exhausted. For example, a spacecraft may have three mission computers that perform identical functions. Typical rules that govern the flight operations might allow continuation of the mission after the first failure. Following the second failure, a mission abort is likely using the single remaining mission computer to return the spacecraft to safety. Should this third computer fail, emergency systems are available to assist the return of the flight crew to safety when possible, and it is those systems that are the focus of this guide. Note that for each emergency situation described herein, a set of emergency procedures and the equipment to implement them will be available in order for the crew to survive. 4.3 LEO missions are divided into pre-launch, ascent, orbit, reentry, and landing. Note that there are separate, additional considerations for transport of humans beyond LEO and for missions having crewed durations in LEO of greater than approximately 30 days which are not within the scope of this guide.