Annular combustion increasing structure on charging outer end surface of missile engine

An engine and outer end face technology, applied in rocket engine installations, machines/engines, mechanical equipment, etc., can solve the problems of reduced engine mass ratio, increased engine risk, and reduced performance, increased initial thrust, and eliminated grain stress concentration. With cracks, the effect of avoiding the reduction of the mass ratio

Inactive Publication Date: 2016-07-06
SHANGHAI XINLI POWER EQUIP RES INST
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  • Abstract
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AI Technical Summary

Problems solved by technology

[0004] The problem with drilling the end face of the grain is that once there is a crack in the deep hole, it cannot be detected by conventional means, which increases the risk of the engine
At the same time, drilling will reduce the amount of medicine, reduce the mass ratio of the engine, and reduce the performance

Method used

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  • Annular combustion increasing structure on charging outer end surface of missile engine

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Embodiment Construction

[0014] The invention will be described in more detail hereinafter with reference to the accompanying drawings showing embodiments of the invention. However, this invention may be embodied in many different forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art.

[0015] Such as figure 1 Shown is a schematic diagram of the circumferential combustion-increasing structure on the outer end face of the missile engine charge of the present invention.

[0016] The combustion-increasing structure includes 1: powder column, 2: coating sleeve, and 3: liner. The powder column and the covering sleeve are firmly bonded through the lining layer.

[0017] The powder column 1 adopts hydroxybutylated propellant, and the powder column 1 is in the shape of a solid column charged with powder. The ou...

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Abstract

The invention discloses a circumferential combustion-increasing structure on the outer end surface of the charge of a missile solid motor, including a charge column, a cladding sleeve and a liner. The grain is bonded to the covering sleeve through the lining layer, and the initial combustion surface of the grain can be changed by adjusting the length of the covering sleeve, so that the engine can meet the overall engine initial thrust index requirements. Compared with the prior art, the present invention adopts the hoop-increasing structure, and its advantages and beneficial effects are: the hoop-increasing structure is easy to measure and detect, and at the same time, it eliminates the stress concentration and cracks of the grain caused by the complex profile , so that the risk of engine operation is reduced; the initial burning surface of the grain can be effectively adjusted without losing the amount of medicine, so that the initial thrust of the engine can be increased, thereby ensuring the mass ratio of the engine.

Description

technical field [0001] The invention relates to an internal charging structure of a solid rocket motor, in particular to a ring direction combustion-increasing structure on the outer end surface of a missile motor charging. Background technique [0002] The charge in the combustion chamber is one of the important parts of the engine structure, which provides power for the engine to push the missile body. In order to meet the ballistic requirements of the missile, sometimes in the engine development task book, there will be requirements for the initial thrust of the engine. Therefore, in the charge design of the engine combustion chamber, consideration should be given to increasing the burning surface of the charge column at the initial stage of combustion, so as to ensure that the thrust of the engine at the initial stage of operation meets the requirements of use, so that the missile can be launched reliably. [0003] The existing combustion chamber charge in the form of...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/24F02K9/10
Inventor 王一奇阳洁潘惠泉刘爱琴刘乡芸娄永春俞鑫乐浩
Owner SHANGHAI XINLI POWER EQUIP RES INST
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