CN110985233A

CN110985233A - Double-pulse solid rocket engine wiring board combination device

Info

Publication number: CN110985233A
Application number: CN201911084656.5A
Authority: CN
Inventors: 陈树茂; 沈铁华; 乐浩; 麦玲; 邹晓慧; 朱敏; 赵瑜; 薛牧遥; 沈俊新
Original assignee: Shanghai Xinli Power Equipment Research Institute
Current assignee: Shanghai Xinli Power Equipment Research Institute
Priority date: 2019-11-08
Filing date: 2019-11-08
Publication date: 2020-04-10
Anticipated expiration: 2039-11-08
Also published as: CN110985233B

Abstract

The invention provides a wiring board combination of a double-pulse solid rocket engine, which comprises: terminal block, terminal, spring, pin, and flat washer. The wiring terminal penetrates through the through hole in the side wall of the wiring board, and is fixed in the square hole of the wiring board together with the spring and the first and second pulse ignition device wiring sheets, and finally the small end of the wiring terminal is fixed on the wiring board by using a flat washer and a pin. The terminal plate assembly is fixed on an engine compartment through counterbores at two ends of the terminal plate by screws. Its advantages and beneficial effects are: the structure is simple, and the assembly is convenient; the first pulse ignition device lug and the second pulse ignition device lug are extruded to be tightly attached through the pretightening force of the spring, ignition circuits are reliably connected, and the electric appliance fault mode caused by connector connection is reduced; the wiring board assembly plays a role in fixing and protecting the cable; in addition, the marks among the ignition loops are clear, so that the correctness of the circuit is convenient to check, and the reliability of the operation of the ignition circuit of the solid rocket engine is ensured.

Description

Double-pulse solid rocket engine wiring board combination device

Technical Field

The invention relates to a double-pulse solid rocket engine technology, in particular to an electrical appliance connecting and fixing structure of a double-pulse engine ignition device.

Background

In order to improve the performance of tactical missiles, increase the range, reasonably distribute and use energy, the double-pulse engine technology is widely applied. The double-pulse engine achieves reasonable use of energy of the solid rocket engine by controlling ignition time sequences of the first pulse and the second pulse.

The double-pulse engine is generally composed of a double-pulse ignition device, a double-pulse combustion chamber, a compartment, a pulse ignition device, a pulse combustion chamber, a spray pipe and the like. In order to adapt to the structure of a double-pulse engine, the engine ignition system consists of a double-pulse ignition device, a pulse ignition device and a wire fixing plate assembly, wherein the wire fixing plate assembly is fixed on a compartment device at one side of the double pulses. The secondary pulse ignition device is positioned at the head of the engine, and two nine-core electric connectors are arranged at the outer part of the secondary pulse combustion chamber and connected with the missile-mounted cable network for acquiring a missile instruction; the two-pulse ignition device is characterized in that a lead wire extends out of the two-pulse combustion chamber of the engine to the end of a compartment, penetrates through the two-pulse combustion chamber, and is connected with a pulse ignition device through a wire fixing plate assembly at the compartment for providing missile instructions for the pulse ignition device.

The scheme is as follows: the two ignition devices of the double-pulse engine are not controlled uniformly on the bomb, one pulse ignition signal is provided by a ground ignition control system, and the ignition signal of the two pulse ignition devices is provided by a bomb control cabin, so that the ignition signals can be transmitted only on the ground, and the application range of the double-pulse engine is limited.

Disclosure of Invention

The invention aims to solve the problems and provide a terminal plate combination device of a double-pulse engine ignition device. The solid rocket engine wiring board composite set includes: terminal board, terminal, spring, round pin and flat washer. The wiring terminal penetrates through the through hole in the side wall of the wiring board, and is fixed in the rectangular through hole of the wiring board together with the spring and the first and second pulse ignition device wiring lugs, and the wiring lugs are tightly attached together through the extrusion of the spring; the other end of the terminal post is fixed to the terminal block with a flat washer and a pin. The terminal block assembly is secured to the engine compartment by two screws.

Furthermore, the wiring board is in a straight shape and is made of an insulating material, preferably a polytetrafluoroethylene material; counter bores are formed in the two ends of the connecting plate and used for mounting and fixing the connecting plate combination on the engine; the mounting surface is provided with a rectangular through hole for placing a spring and an ignition device lug plate, and the center of the upper surface and the center of the lower surface of the rectangular through hole is provided with a through hole; holes may be provided between the rectangular holes for weight reduction.

Furthermore, the binding post is of a T-shaped solid cylinder structure, the material is a conductor, and an aluminum material with good processability is preferred; the diameter of the large end is larger than that of the side wall through hole on the wiring board, and the diameter of the small end is slightly smaller than (smaller than 0-2 mm) that of the side wall through hole; the tail end of the small diameter is provided with a small through hole, and the through hole can penetrate through the pin and fix the end of the binding post together with the flat washer. Furthermore, the outer diameter of the spring is smaller than the width of the rectangular through hole of the wiring board and larger than the diameters of the through holes on the upper surface and the lower surface of the rectangular through hole; the inner diameter is slightly larger than (larger than 0.1-3 mm) the diameter of the small end of the wiring terminal, and the spring has certain pretightening force on the wiring terminal of the ignition device in an assembly state.

The invention adopts the fixing mode of the wiring board structure, and has the advantages and beneficial effects that:

1) the structure is simple, and the assembly is convenient;

2) the first pulse ignition device lug and the second pulse ignition device lug are extruded to be tightly attached through the pretightening force of the spring, ignition circuits are reliably connected, and the electric appliance fault mode caused by connector connection is reduced;

3) the wiring board assembly plays a role in fixing and protecting the cable;

4) the marks among the ignition loops are clear, so that the correctness of the circuit is convenient to check, and the reliability of the work of the ignition circuit of the solid rocket engine is ensured.

Drawings

FIG. 1 is a schematic view of a patch panel assembly of the present invention;

FIG. 2 is a schematic view of a patch panel of the present invention;

fig. 3 is a schematic view of the binding post of the present invention.

Detailed Description

The following describes embodiments of the present invention in further detail with reference to the accompanying drawings.

The invention provides a wiring board combination device of a double-pulse engine ignition device, as shown in figure 1, the wiring board combination is fixed on a double-pulse engine compartment through screws, and a first pulse ignition device and a second pulse ignition device can be reliably connected. The solid rocket engine terminal plate combination includes: terminal board 1, terminal 2, spring 3, pin 4 and flat washer 5. The wiring terminal 2 penetrates through a through hole in the side wall of the wiring board 1, and is fixed in a rectangular through hole of the wiring board 1 together with the spring 3 and the first and second pulse ignition device wiring lugs, and the wiring lugs are tightly attached together through the extrusion of the spring pretightening force; the other end of the terminal 2 is attached to the terminal block with a pin 4 and a flat washer 5.

Taking a certain type of patch panel combination as an example, as shown in fig. 2:

the wiring board 1 is made of polytetrafluoroethylene insulating material, is in a shape of a straight line, and has a total length of 75mm, a width of 10mm and a thickness of 7 mm. Counter bores 6 are arranged at the two ends and are used for mounting and fixing the wiring board combination on the engine; a rectangular through hole 7 for placing the spring 3 and an ignition device lug is arranged on the mounting surface, the section is 7.2mm multiplied by 5mm, and a central through hole (side wall through hole) 8 with phi 3mm is arranged on the upper surface and the lower surface of the rectangular through hole 7; through holes 9 with the diameter of phi 4mm are arranged between the rectangular through holes 7 for reducing weight.

The post 2 is preferably made of aluminum material with good processability and has a T-shaped structure, as shown in FIG. 3, the total length is 13.6mm, the diameter of the large end is 5mm, and the height is 1 mm; the diameter of the small end is 3mm, and a pin hole with phi 1.2mm is arranged at the position 11mm away from the large end.

The spring 3 is made by right-handed (or left-handed) rotation, the effective number of turns N is 5.5, the total number of turns N is 6, the pitch p is 1.4, the design rigidity k is 1N/mm, and the expansion length L is approximately equal to 82.7 mm.

The pin 4 and flat washer 5 preferably conform to the standard of GB/T91 and GB/T848.

When the wiring board is used, the spring 3 is firstly placed in the rectangular through hole 7 of the wiring board 1, and then the small end of the wiring board 2 penetrates through the central through hole 8 and penetrates through a part of the spring 3. And then, overlapping the lugs corresponding to the first pulse and the second pulse into the tail end of the spring 3, and adjusting the position of a lug hole to enable the wiring terminal 2 to penetrate through the spring 3 and the lugs together, so that a pin hole on the wiring terminal 2 is exposed out of the wiring board 1. Finally, the small end of the terminal is fixed on the wiring board 1 by a pin 4 and a flat washer 5.

And (4) sequentially completing the assembly of two ignition loops and four groups of wire harnesses.

The wiring board combination is applied to multiple models, the product manufacturability and the productivity are verified, multiple environmental tests, ground static tests and flight tests are passed, the structure is reliable, and the use requirement is met.

It should be noted that the foregoing is only illustrative and illustrative of the present invention, and that any modifications and alterations to the present invention are within the scope of the present invention as those skilled in the art will recognize.

Claims

1. A double-pulse solid rocket engine terminal block assembly, said terminal block assembly comprising: the wiring board penetrates through a through hole in the side wall of the wiring board and is fixed in a rectangular through hole of the wiring board together with the spring, and the small end of the wiring board is fixed on the wiring board through the flat washer and the pin.

2. A double pulse solid rocket engine terminal block assembly as recited in claim 1, wherein a pulse igniter terminal strip and a double pulse igniter terminal strip are pressed together by a spring and secured together with the terminal strip and the spring in a rectangular through hole in the terminal block.

3. A double pulse solid rocket engine terminal block assembly as recited in claim 2, wherein said terminal posts are spaced apart on said terminal block.

4. A double-pulse solid-rocket engine terminal block assembly as recited in claim 3, wherein said terminals are four in number and are grouped in pairs to form firing circuits.

5. A double pulse solid rocket engine terminal block assembly as recited in claim 2, wherein said terminal block is "in-line" with counterbores at both ends for mounting and securing the terminal block assembly.

6. A double-pulse solid rocket engine terminal block assembly as recited in claim 5, wherein said terminal block mounting surface has rectangular through holes for receiving springs and pulse igniter lugs, and the centers of the upper and lower surfaces of said rectangular through holes have sidewall through holes, and holes are provided between said rectangular through holes for weight reduction.

7. A double-pulse solid-rocket engine terminal block assembly as recited in claim 6, wherein said terminal block is a T-shaped solid cylinder structure, the diameter of the terminal block's large end is greater than the diameter of the side wall through hole on the terminal block, and the diameter of the terminal block's small end is less than the diameter of the side wall through hole; the tail end of the small diameter is provided with a tail end through hole, and the tail end through hole is used for fixing the small end of the wiring terminal through a pin.

8. A double-pulse solid rocket engine terminal block assembly as recited in claim 7, wherein said spring has an outer diameter less than the width of said rectangular through hole in said terminal block and an inner diameter greater than the diameter of said terminal post at its small end, said spring exerting pressure on said terminal block of said pulse initiator in said assembled state.

9. A double-pulse solid-rocket motor terminal block assembly as recited in claim 8, wherein said terminal block is formed of a conductive material.

10. A double pulse solid rocket motor terminal block assembly as recited in claim 9, wherein said conductive material comprises aluminum.