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Environment temperature control device and method for thermal environment test of attitude control engine

An ambient temperature and control device technology, which is applied in rocket engine devices, machines/engines, jet propulsion devices, etc., can solve the problems of long vacuuming time, non-directional heat radiation, poor cooling and cooling effect, etc.

Active Publication Date: 2021-04-20
XIAN AEROSPACE PROPULSION TESTING TECHN INST
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Problems solved by technology

[0008] The present invention aims to solve the problems of long vacuuming time in the vacuum cabin, high ambient humidity inside the cabin, poor cooling effect and non-directional heat radiation in the vacuum thermal environment ignition test of the attitude control engine, and provides an attitude control engine. Ambient temperature control device and method for engine thermal environment test

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  • Environment temperature control device and method for thermal environment test of attitude control engine
  • Environment temperature control device and method for thermal environment test of attitude control engine
  • Environment temperature control device and method for thermal environment test of attitude control engine

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Embodiment Construction

[0055] The technical solutions of the present invention will be clearly and completely described below in conjunction with the embodiments of the present invention and the accompanying drawings. Apparently, the described embodiments do not limit the present invention.

[0056] The ambient temperature control device of the attitude control engine thermal environment test in this embodiment includes a vacuum chamber 1, a vacuum chamber low temperature assembly 2, an exhaust assembly 3, an engine fixed support frame 4, a lamp array assembly 5, a water cooling assembly 6, a vacuum chamber System 7 and nitrogen purge assembly 8;

[0057] Such as figure 1 , figure 2 and image 3 As shown, the engine fixed support frame 4 is arranged in the vacuum chamber 1 for fixing the attitude control engine 9 to be measured;

[0058] The lamp array assembly 5 is fixed on the engine fixed support frame 4 through the fixed pressing plate 10;

[0059] The lamp array assembly 5 includes a lamp ...

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Abstract

The invention relates to an environment temperature control technology of a liquid rocket engine, in particular to an environment temperature control device and method for a thermal environment test of an attitude control engine, and aims to solve the problems that when the attitude control engine is subjected to a vacuum thermal environment ignition test at present, a vacuum cabin is long in vacuumizing time consumption, high in internal environment humidity, poor in cooling effect and non-directional in thermal radiation. According to the technical scheme, the environment temperature control device for the thermal environment test of the attitude control engine comprises the vacuum cabin, a vacuum cabin low-temperature assembly, an exhaust assembly, an engine fixing supporting frame, a lamp array assembly, a water cooling assembly, a vacuumizing system and a nitrogen blowing-down assembly; the engine fixing supporting frame is arranged in the vacuum cabin; the lamp array assembly is fixed on the engine fixing supporting frame through a fixing pressing plate; and the lamp array assembly comprises a lamp array frame, a high-heat flow area lamp array and a low-heat flow area lamp array, wherein the high-heat flow area lamp array and the low-heat flow area lamp array are arranged on the lamp array frame. The invention further provides the environment temperature control method for the thermal environment test of the attitude control engine.

Description

technical field [0001] The invention relates to an environment temperature control technology of a liquid rocket engine, in particular to an environment temperature control device and method for an attitude control engine thermal environment test. Background technique [0002] At present, when carrying out the ignition test of the vacuum thermal environment of the liquid attitude control engine of the order of 2000N, it is necessary to test the thrust chamber of the engine in a minimum vacuum environment of 2Pa to a maximum of 340kW / m 2 The heat flux is loaded, and the maximum ambient temperature of the engine exceeds 1000°C under this heat flux. However, the liquid attitude control engine has the following technical problems in the vacuum thermal environment ignition test: [0003] 1. When the existing attitude control engine is installed in the vacuum chamber, the tail of the nozzle of the attitude control engine is connected with the inlet of the diffuser penetrating int...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/96F02K9/64
Inventor 寇鑫王岳何小军令芸赵飞张建明刘宇丰刘丽宁刘阳李志勋张鹏李亮向红艳严岚卜学星
Owner XIAN AEROSPACE PROPULSION TESTING TECHN INST
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