Air inflow adjusting structure of solid propellant rocket engine

A solid impulse engine and air intake adjustment technology, which is applied in the direction of machines/engines, mechanical equipment, jet propulsion devices, etc., can solve the problem of small adjustment range, achieve wide adjustment range, improve thrust and maneuverability, and flexibly adjust Effect

Inactive Publication Date: 2016-01-06
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The program structure is relatively simple, and the adjustment range is not large

Method used

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  • Air inflow adjusting structure of solid propellant rocket engine
  • Air inflow adjusting structure of solid propellant rocket engine
  • Air inflow adjusting structure of solid propellant rocket engine

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0021] This embodiment is an air intake regulating structure of a solid impulse engine.

[0022] refer to Figure 1 to Figure 8 , the air intake adjustment structure of the solid impulse engine is composed of the solid impulse engine and the intake adjustment structure. The gas generator 1 of the solid impulse engine is fixed in the engine casing 16 and installed at the front of the engine combustion chamber 14. The solid charge Placed in the engine combustion chamber 14, the igniter 13 is installed in the engine combustion chamber 14 and fixed in the round hole at the end of the solid charge, near one end of the tail nozzle 12, the gas generator nozzle 15 and the igniter 13 are coaxially installed.

[0023] The air intake adjustment structure includes an air inlet fixed section 2, an air inlet adjustable section 4, a flexible connecting section 3, a first connecting rod 5, a second connecting rod 9, an outlet reversing ball 8, an actuating connecting rod 7, a second connectin...

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PUM

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Abstract

The invention discloses an air inflow adjusting structure of a solid propellant rocket engine. Mixing of fuel gas of a combustion chamber can be adjusted and supplemented by adjusting the air inflow angle and changing the rotational air inflow mode or the irrotational air inflow mode, so that the thrust of the engine is adjusted. An air inflow duct fixed section is installed on an engine shell and is connected with an air inflow duct adjustable section through a flexible connection section, and the air inflow duct adjustable section is communicated with the engine combustion chamber through an outlet reversing ball. A first drive motor and a second drive motor are connected with an actuation connection rod of the air inflow duct adjustable section, and the second drive motor is connected to the outer shell wall of the engine combustion chamber through a reversing guide groove. The air inflow duct adjustable section rotates for reversing at any angle with the outlet reversing ball as the circle center within the rotating range of a cone with the vertex angle of 120 degrees under the common effect of the first drive motor and the second drive motor, so that the thrust and maneuverability of the solid propellant rocket engine are improved greatly. The air inflow adjusting structure is simple and easy to achieve.

Description

technical field [0001] The invention relates to the technical field of sub-combustion rate ramjet engines, in particular to a sub-combustion rate ramjet intake structure with a variable intake mode. Background technique [0002] Thrust adjustment technology is an important field of solid-state engines. Compared with single-chamber dual-thrust engines and pulse engines with predetermined thrust, the former can distribute propellant energy more reasonably and adjust its thrust according to the needs of aircraft. development trend. [0003] At present, relevant research institutions at home and abroad are all committed to the research of thrust control. The typical structures of several adjustable thrust solid rocket motors include: the engine that adjusts the throat area of ​​the nozzle, the control of the propellant mass burning rate and the flameout engine. , mass-added engines, these engines have been better applied to solid rockets, but there will also bring some new prob...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02C7/057
Inventor 冯喜平纪海龙李进贤唐金兰朱国强王恒
Owner NORTHWESTERN POLYTECHNICAL UNIV
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