Minitype solid rocket engine structure based on 3D printing technology

Abstract

The invention discloses a minitype solid rocket engine structure based on a 3D (Three Dimensional) printing technology, which comprises a three-spray-head printer, wherein the printer prints different materials of a design entity in each cross section, and prints a housing, an explosive column and a metal igniter into an integrated structure; the housing consists of a combustion chamber, a spray pipe and a front end socket; the spray pipe is provided with a convergent section and an expansion section; the metal igniter is positioned on the inner surface of the combustion chamber; a lead wire of the metal igniter is led out from the front end socket, and connected with a control chip in an independently addressing manner; different quantities of metal igniters are triggered, and directly ignite the explosive columns in the combustion chambers; the metal igniters are made of copper materials; and the explosive columns are made of any one of solid propellant materials. The minitype solid rocket engine structure is easy to ignite, reliable in sealing, and simple; a total impulse is higher; a minitype engine array is formed by printing multiple minitype engines which are in the same size and are arranged and distributed at equal intervals; the operation is concise; and a technology cycle is short.

Description

technical field [0001] The invention belongs to the field of micro solid rocket motor structure design, in particular, relates to a micro solid rocket motor structure based on 3D printing technology. Background technique [0002] The miniature solid rocket motor attached to the miniature spacecraft needs to be able to perform high-precision site tracking, attitude control, gravity compensation, and orbit adjustment, and traditional miniature engines cannot meet the required thrust accuracy and space requirements. In the past few decades, micro-engine technology has been a hot research field, and among the numerous research projects, the feasibility of downsizing traditional micro-engines has been studied. Several micro-engine technologies have been developed, such as: micro-electric propulsion technology, micro-cooled air propulsion technology, micro-laser plasma propulsion technology, which can provide 10 -8 Thrust pulses of N·s~10N·s can provide precise control for spacec...

AI Technical Summary

Problems solved by technology

[0004] 1. Vapor tends to condense or solidify in the propellant lines or at the nozzle

[0005] 2. There is a more complicated micro-pipeline system, which reduces the reliability of the system

[0007] 1. The size of the nozzle is small, and it must be divided into 3 layers, the structure is complex, and the process requirements are high

[0008] 2. The igniter is installed in the throat, which is difficult to install; the lead wire of the ignition resistance wire is difficult to lead out

[0009] 3. The diameter of the throat of the micro engine is small, and the alignment and bonding of the top plate and the middle plate are difficult

[0011] 1. The nozzle manufactured by the MEMS process is square and has poor aerodynamic characteristics

[0012] 2. The igniter can only be installed on the front head

[0013] 3. When the nozzle layer and the combustion chamber layer are charged and bonded, the charge inside the combustion chamber layer may explode, which is poor in safety

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