本标准的目的是定义安全因素（FOS），设计因素和其他因素，用于空间硬件的尺寸和设计验证，包括鉴定和验收测试。 本标准不自主，并与ECSS-E-ST-32，ECSS-E-ST-32-02和ECSS-E-ST-33-01文件结合使用。 以下假设在文件中作了说明: •识别的方法用于确定应用于硬件和应力分析的极限载荷，包括其分散度; •结构和机械系统设计适用于目前最先进的方法的工程分析，符合航空航天工业标准。 定义了安全因素，以涵盖所选择的负荷水平概率，假设机械性能和制造的不确定性，但不是缺乏工程设计。 程序的安全因素的选择与程序中设计，尺寸和测试所保留的理由直接相关。因此，由于开发逻辑和相关的可靠性目标不同: 无人值守的科学或商业卫星， 消耗性运载火箭， •。 •任何

The purpose of this Standard is to define the Factors Of Safety (FOS), Design Factor and additional factors to be used for the dimensioning and design verification of spaceflight hardware including qualification and acceptance tests. This standard is not self standing and is used in conjunction with the ECSS-E-ST-32, ECSS-E-ST-32-02 and ECSS-E-ST-33-01 documents. Following assumptions are made in the document: • that recognized methodologies are used for the determination of the limit loads, including their scatter, that are applied to the hardware and for the stress analyses; • that the structural and mechanical system design is amenable to engineering analyses by current state-of-the-art methods and is conforming to standard aerospace industry practices. Factors of safety are defined to cover chosen load level probability, assumed uncertainty in mechanical properties and manufacturing but not a lack of engineering effort. The choice of a factor of safety for a program is directly linked to the rationale retained for designing, dimensioning and testing within the program. Therefore, as the development logic and the associated reliability objectives are different for: • unmanned scientific or commercial satellite, • expendable launch vehicles, • man-rated spacecraft, and • any other unmanned space vehicle (e.g. transfer vehicle, planetary probe) specific values are presented for each of them. Factors of safety for re-usable launch vehicles and man-rated commercial spacecraft are not addressed in this document. For all of these space products, factors of safety are defined hereafter in the document whatever the adopted qualification logic: proto-flight or prototype model. For pressurized hardware, factors of safety for all loads except internal pressure loads are defined in this standard. Concerning the internal pressure, the factors of safety for pressurised hardware can be found in ECSS-E-ST-32-02. For loads combination refer to ECSS-E-ST-32-02. For mechanisms, specific factors of safety associated with yield and ultimate of metallic materials, cable rupture factors of safety, stops/shaft shoulders/recess yield factors of safety and limits for peak Hertzian contact stress are specified in ECSS-E-ST-33-01. Alternate approach The factors of safety specified hereafter are applied using a deterministic approach i.e. as generally applied in the Space Industry to achieve the structures standard reliability objectives. Structural safety based on a probabilistic analysis could be an alternate approach but it has to be demonstrated this process achieves the reliability objective specified to the structure. The procedure is approved by the customer. This standard may be tailored for the specific characteristics and constraints of a space project in conformance with ECSS-S-ST-00.