ISO 16694:2015
航天系统.液体火箭发动机发射台和飞行试验的测量参数

Space systems - The measured parameters at firing bench and flight tests of liquid rocket engines

标准号

ISO 16694:2015

发布

2015年

发布单位

国际标准化组织

当前最新

ISO 16694:2015

 

 

引用标准

ISO 15864:2004 ISO 15865:2005 ISO 24917:2010

适用范围

This International Standard applies to all types of liquid rocket engines for expendable launch systems and satellites: a) Combustible fuel (including cryogenic); c) Low-thrust engines, one component (mono-propellant) and two-component (bi-propellant). b) Large-thrust, multiple component engines, with and without afterburning; This International Standard establishes a list of parameters to be measured and registered with the firing stand and flight tests of serial LRE. The order of preparation and carrying out of stand and flight tests, methods of processing, and analysis of tests results of liquid rocket engines, also measurement accuracy requirements are not regulated by this International Standard. Measurement accuracy requirements are established by engine designer. Parameters listed in this International Standard characterize performance attributes of liquid rocket engines and are used for evaluating of technical state of engines (operative, inoperative), if they correspond 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 items taking into account their design and diagrammatical features. The meaning “optional parameter” denotes (in cases when a proper unit or a component can be the part of 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 means of the same sensors if possible.

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