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

An ambient temperature and control device technology, applied in rocket engine devices, machines/engines, jet propulsion devices, etc., can solve the problems of long vacuuming time, poor cooling and cooling effect, and non-directional heat radiation, so as to avoid the power supply system. Short circuit problem, uniform cooling, and the effect of improving heat exchange efficiency

Active Publication Date: 2022-03-11
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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  • Ambient temperature control device and method for thermal environment test of attitude control engine
  • Ambient temperature control device and method for thermal environment test of attitude control engine
  • Ambient temperature control device and method for thermal environment test of attitude control engine

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Embodiment Construction

[0055] The following Examples and drawings of the present invention, the technical solutions of the present invention are clearly and completely described, obviously, not to limit the described embodiment of the present invention.

[0056] Attitude control engine thermal environment test in the present embodiment the temperature control apparatus comprises a vacuum chamber 1, a low temperature vacuum chamber assembly 2, the exhaust assembly 3, the engine support frame 4 is fixed, the lamp array assembly 5, 6 water-cooled components, vacuum 7 system and a nitrogen blowing assembly 8;

[0057] Such as figure 1 , figure 2 and image 3 , The engine support frame 4 is fixed in the vacuum chamber 1 is provided, for fixing the attitude control test engine 9;

[0058] The lamp assembly array 5 through the stationary platen 4 is fixed to the engine stationary support frame 10;

[0059] The lamp assembly 5 comprises a matrix array of light frame 51 is provided on the frame 51 of the lamp arr...

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Abstract

The present invention relates to the environment temperature control technology of liquid rocket engine, in particular to an environment temperature control device and method for attitude control engine thermal environment test, in order to solve the problem of vacuuming in the vacuum chamber when the attitude control engine conducts the vacuum thermal environment ignition test. Long time consumption, high ambient humidity inside the cabin, poor cooling effect, and non-directional heat radiation. The technical solution adopted in the present invention is: an ambient temperature control device for attitude control engine thermal environment test including a vacuum chamber, a vacuum chamber low-temperature assembly, an exhaust assembly, a fixed support frame for the engine, a lamp array assembly, a water cooling assembly, and a vacuum pumping system and nitrogen blowing components; the engine fixed support frame is set in the vacuum chamber; the lamp array assembly is fixed on the engine fixed support frame through a fixed pressure plate; the lamp array assembly includes a lamp array frame and a lamp array in a high heat flux area arranged on the lamp array frame and a lamp array in a low heat flow area; the present invention also provides an ambient temperature control method for an attitude control engine thermal environment test.

Description

Technical field [0001] The present invention relates to liquid rocket engine temperature control technology, particularly relates to apparatus and method for engine thermal environment of a test temperature control of attitude control. Background technique [0002] Present during the order of 2000N liquid attitude control ignition engine vacuum thermal environment test, the need for engine thrust chamber up to 340kW / m at the lowest degree of vacuum environment 2Pa 2 Load heat flux, the heat flux in the engine ambient temperature Maximum CPC exceeds 1000 ℃. However, the liquid attitude control engine thermal environment during the vacuum firing test, the following technical problems: [0003] 1, the conventional attitude control engine mounted in a vacuum chamber, inlet communicating with the nozzle penetrates the vacuum chamber tail diffuser attitude control of the engine, the outlet diffuser attached to further steam ejector system; due diffuser and its large water vapor eject...

Claims

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Application Information

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Patent Type & Authority Patents(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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