ISO 16694:2015 空间系统 点火平台的测量参数和液体火箭发动机的飞行测试

标准编号：ISO 16694:2015

中文名称：空间系统 点火平台的测量参数和液体火箭发动机的飞行测试

英文名称：Space systems — The measured parameters at firing bench and flight tests of liquid rocket engines

发布日期：2015-03

标准范围

This International Standard applies to all types of liquid rocket engines for expendable launch systemsand satellites:a) Combustible fuel (including cryogenic);b) Large-thrust, multiple component engines, with and without afterburning;c) Low-thrust engines, one component (mono-propellant) and two-component (bi-propellant).This International Standard establishes a list of parameters to be measured and registered with thefiring stand and flight tests of serial LRE.The order of preparation and carrying out of stand and flight tests, methods of processing, and analysisof tests results of liquid rocket engines, also measurement accuracy requirements are not regulated bythis International Standard. Measurement accuracy requirements are established by engine designer.Parameters listed in this International Standard characterize performance attributes of liquid rocketengines and are used for evaluating of technical state of engines (operative, inoperative), if theycorrespond to the requirements specified and possibilities of putting them into operation.There are parameters specified in this International Standard, obligatory for registration and optional ones.The manufacturer of liquid rocket engines can determine additional list of parameters for specific itemstaking into account their design and diagrammatical features.The meaning “optional parameter” denotes (in cases when a proper unit or a component can be the partof an engine) that according to the manufacturer’s decision, measurements are allowed not to be made.Measurement of parameters at firing stand and flight tests of liquid rocket engines is be made by meansof the same sensors if possible.

标准预览图