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Constant-thrust rocket engine or engine thrust chamber performance testing device

A rocket engine and test device technology, which is applied to rocket engine devices, jet propulsion devices, machines/engines, etc., can solve problems such as the inability to perform fluid flow performance tests with back pressure, and achieve stable pressure and convenient disassembly and assembly.

Active Publication Date: 2019-10-08
XIAN AEROSPACE PROPULSION INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] In order to solve the technical problem that the existing rocket engine thrust chamber performance test device cannot perform the liquid flow performance test with back pressure, the present invention provides a constant thrust rocket engine or engine thrust chamber performance test device

Method used

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  • Constant-thrust rocket engine or engine thrust chamber performance testing device
  • Constant-thrust rocket engine or engine thrust chamber performance testing device
  • Constant-thrust rocket engine or engine thrust chamber performance testing device

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Embodiment Construction

[0044] The present invention will be further described below in conjunction with the accompanying drawings and specific embodiments.

[0045] refer to figure 2 , a fixed-thrust rocket engine or engine thrust chamber performance testing device, comprising an anti-top assembly 2, a throat support assembly 3, a bottom support assembly 4 and a stand 5.

[0046] The thrust chamber 1 of the engine under test is fixedly connected in the stand 5 through the anti-top assembly 2 . Throat 107 and expansion section 108 of engine thrust chamber 1 support throat support assembly 3 , the bottom of throat support assembly 3 is provided with bottom support assembly 4 , and bottom support assembly 4 is fixedly connected to the bottom surface of stand 5 .

[0047] refer to image 3 and Figure 4 , The throat support assembly 3 includes a rubber head cover 301 , a rubber protective cover 302 and a core 303 . Considering the weight of the engine thrust chamber 1 and the pressure during the test...

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Abstract

The invention relates to a performance testing device of a rocket engine, in particular to a constant-thrust rocket engine or engine thrust chamber performance testing device. The technical problem that an existing rocket engine thrust chamber performance testing device cannot be used for performing a liquid flow performance test with back pressure is solved. The constant-thrust rocket engine or engine thrust chamber performance testing device is characterized by comprising an anti-jacking assembly, a throat supporting assembly, a bottom supporting assembly and a rack; the anti-jacking assembly is used for fixedly connecting a tested engine or an engine thrust chamber in the rack; the throat supporting assembly is supported in a throat part and an expanding section of the engine or the engine thrust chamber; a bottom supporting assembly is arranged at the bottom of the throat supporting assembly; the bottom supporting assembly is fixedly connected to the bottom surface of the rack; thethroat supporting assembly comprises a rubber head sleeve, a rubber protective sleeve and a core body; the core body comprises a cylindrical head and a circular-truncated-cone-shaped body; the cylindrical head is sleeved with the rubber sleeve; and the circular-truncated-cone-shaped body is sleeved with the rubber protective sleeve.

Description

technical field [0001] The invention relates to a performance testing device of a rocket engine, in particular to a performance testing device of a fixed-thrust rocket engine or a thrust chamber of the engine. Background technique [0002] During the development process of the engine, a number of liquid tests are required to obtain its performance parameters and verify whether the product design meets the technical requirements. Among them, the hydraulic test of the engine thrust chamber needs to carry out pressure drop matching debugging and stability test. [0003] refer to figure 1 , the engine thrust chamber 1 includes an injector 101 and a body 102 connected in series from top to bottom. The lower part of the injector 101 is provided with a connecting flange 105 . [0004] The body 102 includes a body cylindrical section 103, a convergent section 106 (above the throat), a throat 107 (where the diameter of the body is smallest), and a divergent section 108 (below the ...

Claims

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Application Information

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IPC IPC(8): F02K9/96
CPCF02K9/96
Inventor 徐亚丽教传军
Owner XIAN AEROSPACE PROPULSION INST
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