Composite vibration component test system of turbopump-feed liquid rocket engine structure

Abstract

The invention provides a composite vibration component test system of a turbopump-feed liquid rocket engine structure, and relates to the field of a structural composite vibration component test method. The system comprises three vibration exciters, an excitation support device, a computer, three control instrument and signal generators, a response acquisition system, three power amplifiers, threeexcitation rods, three force transducers and an acceleration sensor. According to the system, a vibration response which is difficult to realize by one single vibration excitation source is excited for the engine structure by employing excitation of multiple groups of vibration exciters, vibration response frequency spectrum components simultaneously comprise frequency spectrum characteristics ofa plurality of excitation sources including an engine combustion chamber, a turbine pump, and a combustion gas generating device etc., an amplification rule or an attenuation rule of each vibration excitation load spectrum can also be reflected, the sensitive degrees of the engine structural vibration response to different excitation sources are obtained through a relation analysis of the structural vibration response frequency spectrum synthesis components and the excitation sources, the cost is low, the technical difficulty is moderate, and the system is applicable to the turbopump-feed liquid rocket engine structure.

Description

technical field [0001] The invention relates to the field of a structural compound vibration component test method, in particular to a structural compound vibration component test system of a pump-pressed liquid rocket engine. Background technique [0002] For the pump-pressed liquid rocket engine, the loads received in the whole life cycle are manifested as external loads and self-loads: the former is the vibration load transmitted by the upper-stage engine when the base-stage engine is working, and the latter is its own combustion load. The vibration excitation generated by the main excitation sources such as chamber, turbo pump and gas generator. In recent years, as the launch density has become higher and higher, the phenomenon of pipeline breakage, support plate breakage, and boundary restraint device breakage has been increasing year by year during flight and ground heat tests, which has led to multiple launch failures and Ground test failure. Since 2007, there have ...

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Problems solved by technology

[0004] At present, there is no test system and method suitable for the structural characte

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