Electric control solid thruster

A thruster and solid propellant technology, which is used in machines/engines, jet propulsion devices, rocket engine devices, etc., can solve problems such as unstable thrust control, and achieve the effects of stable propellant combustion, optimized design, and improved current density.

Inactive Publication Date: 2022-04-05
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] Aiming at the problem of unstable thrust control in existing end-face combustion thrusters, the present invention provides an electronically controlled solid thruster, which adopts a unique electrode structure to keep the resistance of the propellant between the two electrodes unchanged, thereby improving the precision of thrust control

Method used

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  • Electric control solid thruster
  • Electric control solid thruster
  • Electric control solid thruster

Examples

Experimental program
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specific Embodiment approach 1

[0037] Specific implementation mode one: the following combination Figure 1~6 Describe this embodiment. An electronically controlled solid thruster described in this embodiment includes a housing 1, an adiabatic insulation sleeve 2, an electrode pressing piece 3, a combustion electrode fixing sleeve 4, a combustion electrode 5, a nozzle 6, and a square ring electrode. , electronically controlled solid propellant grain 9, propellant grain push plate 10, supply spring 11, front head baffle 13 and front head 14;

[0038] Described square annular electrode comprises four electrode sheets 7 and square fixed frame 8, and square fixed frame 8 is a conductive part, and four electrode sheets 7 are symmetrically arranged on the square fixed frame 8; All have arc-shaped contact surfaces, and the four electrode sheets 7 enclose an adjustable, axially transparent square area;

[0039] The casing 1 has an open structure at both ends, and the end of the inner cavity of the casing 1 is prov...

specific Embodiment approach 2

[0057] Specific implementation mode two: the following combination figure 2 This embodiment will be described. This embodiment will further describe Embodiment 1, and the combustion electrode 5 is a flat hole-shaped electrode. There are many exhaust holes on the combustion electrode 5, which is beneficial to the discharge of the high-temperature gas generated by the combustion of the electronically controlled solid propellant.

[0058] The combustion electrode is fixed by the electrode pressing piece 3 and the combustion electrode fixing sleeve 4. The previous combustion electrode structure is optimized, the diameter of the electrode hole is increased, the spacing between the holes is reduced, the contact area with the propellant is reduced, and the ignition power of the propellant is reduced.

[0059] As an example, the diameter of the electrode hole of the combustion electrode (5) is 2 mm, and the distance between the holes is 0.7 mm.

specific Embodiment approach 3

[0060] Specific implementation mode three: the following combination figure 2 The present embodiment will be described. This embodiment will further describe Embodiment 1. The heat-insulating insulating sleeve 2 is made of heat-insulating ceramic material.

[0061] The heat-insulating insulating sleeve 2 is used to isolate the high-temperature gas in the combustion chamber and the current of the terminal, and protect other parts of the thruster. The outermost layer of the thruster is the casing 1, and the nozzle 6 is at the other end, which is directly welded to the casing 1.

[0062] The integrated design of heat insulation and insulation is adopted, which simplifies the independent design structure of the heat insulation layer and the insulation layer in the past. There are grooves and through holes inside, which are used to fix the electrode piece fixing sleeve 4 and the protective electrode terminal. The use of heat-insulating ceramic materials, on the one hand, isolates...

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Abstract

The invention discloses an electric control solid thruster, belongs to the field of special solid propellant rocket engines, and aims to solve the problem of unstable thrust control of an existing end face combustion type thruster. According to the scheme, the square annular electrode comprises four electrode plates and a square fixing frame, and the four electrode plates define a square area which is adjustable in size and axially through; a heat insulation sleeve and a combustion electrode fixing sleeve are arranged in the shell side by side, the combustion electrode fixing sleeve clamps and fixes a combustion electrode, a square annular electrode is installed in a groove in the tail end of the heat insulation sleeve, the square annular electrode is of a structure with the two ends open, and the combustion electrode fixing sleeve is arranged at the tail end of an inner cavity of the shell and provided with an annular notch. The combustion electrode is clamped and fixed at the annular gap, and the annular gap is blocked, filled and leveled up by using the electrode pressing sheet; the tail end of the electric control solid propellant grain penetrates through a square area defined by the four electrode slices and abuts against the end face of the combustion electrode, and an axial working gap is formed between the square annular electrode and the combustion electrode.

Description

technical field [0001] The invention relates to a thrust-adjustable and multiple-start rocket engine using electronically controlled solid propellant, which belongs to the field of special solid propellant rocket engines. Background technique [0002] The electronically controlled solid thruster realizes the controllable start and stop of the rocket and the adjustable thrust, but there are many problems in the existing electronically controlled solid thruster. Existing electronically controlled solid thrusters mainly include thrusters with coaxial electrode structures and end face combustion electrode structures. [0003] The coaxial miniature thruster has small thrust, less charge and short working time. The thrust of the thruster can be increased by parallel connection, but at the same time, the weight of the thruster itself will be increased. [0004] The end-burning thruster applies an electric field between the two ends of the propellant to control the combustion of t...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/32F02K9/34F02K9/95
Inventor 丁永杰胡洪同徐薏深
Owner HARBIN INST OF TECH
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