Rocket engine inner trajectory parameter tester

A rocket engine and tester technology, which is applied in the field of parameter testers, can solve problems such as single function and poor adaptability, and achieve the effect of being convenient to carry

Inactive Publication Date: 2021-06-22
陕西四海测控技术有限公司
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The purpose of the invention is to solve the problem that the ballistic parameter tester in the rocket engine has a single function and poor adaptability in the prior art, and the ballistic parameter tester in the rocket engine proposed

Method used

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Embodiment Construction

[0019] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only some, not all, embodiments of the present invention.

[0020] In describing the present invention, it should be understood that the terms "upper", "lower", "front", "rear", "left", "right", "top", "bottom", "inner", " The orientation or positional relationship indicated by "outside", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the referred device or element must have a specific orientation, so as to Specific orientation configurations and operations, therefore, are not to be construed as limitations on the invention.

[0021] refer to Figure ...

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Abstract

The invention relates to the technical field of parameter testers, and discloses a rocket engine inner trajectory parameter tester which comprises a tester body and a U-shaped frame. Sleeves are symmetrically and fixedly embedded in the bottom end of the U-shaped frame, the sleeve opening end of each sleeve is rotationally connected with the side wall of the tester body through a first bearing, and the outer sleeve wall of each sleeve is slidably in cup joint with a matched positioning ring, a pressure regulation and control mechanism is mounted between each positioning ring and the corresponding sleeve and comprises a moving block slidably connected in the corresponding sleeve, L-shaped rods are fixedly connected to the top end and the bottom end of each moving block, through grooves matched with the L-shaped rods are formed in the side walls of the top ends and the bottom ends of the sleeves, the ends, away from the moving blocks, of the L-shaped rods are fixedly connected with the positioning rings, and the L-shaped rods are slidably connected with the through grooves. The parameter tester is convenient to carry, and the inclination angle and height of the parameter tester can be partially adjusted and controlled according to needs so that the parameter tester can conveniently adapt to different testing environments.

Description

technical field [0001] The invention relates to the technical field of parameter testers, in particular to a tester for internal ballistic parameters of a rocket engine. Background technique [0002] Rockets and space vehicles need the support of the power propulsion system during orbit change and attitude adjustment, and the rocket engine is the most critical component of the space propulsion power system. The internal ballistic parameters of the rocket motor usually need to be tested by a parameter tester, so as to ensure the stability of the rocket motor operation. [0003] In the prior art, the rocket engine internal ballistic parameter tester only has a simple parameter test function, and its structure is relatively simple, most of which are rectangular appearance structures. The parameter tester will encounter different test environments during the test process, and it does not itself It has the function of angle tilt control and height adjustment, which affects the a...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/96
CPCF02K9/96
Inventor 张文琪
Owner 陕西四海测控技术有限公司
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