RU2367895C1 - Method to realise missile connection - Google Patents

Abstract

FIELD: weapons.

SUBSTANCE: invention relates to missiles, particularly to guided missile connections. Proposed method comprises connecting separate missile modules mechanically and by wiring. Missile modules wiring is effected with the help of integrated detachable cable bundles made from tape-type wires and assembly p.c.b. soldered thereto. One of the said printed-circuit boards accommodates missile electronic hardware, the other ones support missile radio electronic starting circuits and male-female connectors. Mating parts of detachable connectors are fitted on appropriate missile units, while integrated detachable bundle is fixed on and along missile outer surface after connecting detachable connectors together, aforesaid bundle being protected by a protective cover plate. Integrated detachable bundle can, partially or completely, represent parallel isolated conductors. One or several printed circuit boards can have additional boards with electro radio hardware components.

EFFECT: higher reliability.

3 dwg, 3 cl

Description

The invention relates to the field of weapons, namely to rocket technology and, in particular, to guided missiles, and can be used in their development and installation.

A known method of mounting a rocket, which is implemented in a guided missile in a transport and launch container [Prospect LOCKHEED MARTIN. Copyright 1997 Lockheed Martin Corporation. All rights reserved. S097-0113 OA 12, 127 10/97], which is an analogue in which the electrical installation of the rocket blocks is carried out using separate harnesses rigidly fixed to the rocket blocks.

A known method of mounting a rocket, which is implemented in a guided missile in a transport and launch container [RF patent No. 2288423, 04/13/05, IPC ⁷ F41F 3/055, IPC ⁷ F41F 3/042], selected as a prototype. In this method, the installation of the rocket involves connecting the individual blocks of the onboard equipment of the rocket mechanically and using electrical wiring, which is done using separate harnesses, rigidly fixed and soldered to the rocket blocks. Moreover, on-board equipment (devices) is understood as starting and accelerating propulsion systems, electronic control equipment, steering gear, warhead, which can be made in the form of two: leading and main charges, etc.

The disadvantages of this method of installation are:

1. The decrease in the reliability of the rocket due to the possibility of violating the integrity of the wiring during Assembly and equipment of the rocket, because electrical installation is performed using separate harnesses, rigidly fixed and soldered to the blocks, which causes inconvenience during installation. For example, during the installation of the steering gear unit, equipment and the installation of starting and accelerating engines, the installation of the leading and main warhead charges and the installation of electronic equipment, the harnesses of these units are located in the installation area and are subject to numerous bends and other mechanical influences, as well as damage mounting tool.

2. The increase in the time of installation of the rocket (the complexity) due to the need for multiple connections of individual harnesses and the complexity of their placement on the rocket.

The objective of the present invention is to increase the reliability of the rocket and reduce its complexity in manufacturing by performing electrical installation in the rocket using a single detachable harness.

The problem is solved due to the fact that in the method of mounting the rocket, which includes connecting the individual rocket blocks mechanically and using electrical installation, the electrical installation of the rocket blocks is carried out using a single detachable harness, which is made of tape wires and mounting boards soldered to them, on one of of these boards, the electronic equipment of the rocket is installed, and on the other, the electric radio products of the rocket launch circuits and detachable connections in the form of pins and sockets, while the mating parts of the detachable mounted on the union of the respective blocks missile, and a single detachable harness after docking detachable connections disposed and secured along the outer surface of the missile body, which is formed by interconnected blocks, the wiring harness to protect the top plate.

The mounting method of the rocket is illustrated by the following graphic materials shown in figures 1, 2 and 3, where

figure 1 shows the layout of the components of the rocket;

figure 2 and 3 shows a design drawing of a single detachable harness, respectively, a bottom and side view.

The layout diagram of the rocket components and the design drawing of a single detachable harness depict:

1, 6, 7 and 14 - rocket blocks - B1, B2, B3, ... Bn, respectively;

2, 5, 8 and 12 - detachable connections of rocket blocks - P1, P2, P3, ... Pn, respectively;

3, 4, 9 and 13 - circuit boards of a single detachable harness with detachable connections - MP1, MP2, MP3, ... MPn, respectively;

10 - circuit board of a single detachable harness with MPA electronic equipment;

11 - electronic equipment - EA;

15 - a single detachable harness;

16 - rocket body;

17 - pins of detachable connections;

18 - socket connectors;

19 - electric radio products ERI (resistors);

20 - tape wires;

21-screen;

22 - ERI (filters).

As the tape wires 20 are used, for example, the wire LMF. As a material for circuit boards 3, 4, 9, 10 and 13, for example, foil-coated glass fiber laminate SONF-2-35-1 is used. On circuit boards perform the corresponding printed conductors. Electronic equipment 11 can be performed in microelectronic performance, on a printed circuit board, etc.

The claimed method of mounting a rocket (figure 1) is implemented as follows. The design of the rocket is carried out in the form of separate blocks 1, 6, 7 and 14. The electrical installation of these blocks is carried out using a single detachable harness 15, which is made (figure 2 and 3) from tape wires 20 and circuit boards 3, 4 soldered to these wires, 9, 10 and 13. On one of these boards (in this case 10) electronic equipment 11 is installed, for example, in microelectronic design.

On the other (remaining) circuit boards 3, 4, 9, and 13, the ERI of the rocket launch circuits and detachable joints in the form of pins and sockets are installed. The counterparts of detachable connections 2, 5, 8 and 12 (Fig. 1) are installed on the respective blocks 1, 6, 7, 14 and placed, for example, on the end or side surfaces of the respective blocks. A single detachable harness 15 after joining the detachable joints is placed and fastened along the outer surface of the rocket body 16, which is formed by mechanically connected blocks, while the harness is protected from above by an overlay.

The installation of the rocket of figure 1 is carried out in the following order. Install blocks 1, 6, 7 and 14 in a device that protects them from mechanical damage during installation. The detachable connections of the circuit boards 3 and 4 of a single detachable harness 15 are joined, respectively, with the detachable connections 2 and 5 of blocks 1 and 6. Mechanically connect block 6 with block 1 and block 7 with block 6.

A detachable connection of the circuit board 9 of the single detachable harness 15, respectively, with the detachable connection 8 of the block 7. Fasten the circuit board 10 with electronic equipment 11 and a screen 21 at the end of the block 7. Mechanically connect the block 14 to the block 7. Connect the detachable connection of the circuit board 13 of the single detachable harness 15, respectively, with a detachable connection 12 of the block 14.

When carrying out the installation of the rocket, a common ribbon wire connecting the circuit boards 3, 4, 9 and 13 of a single detachable harness 15 is placed on the outside of the rocket housing 16 and, upon completion of installation, is protected from above with a metal plate.

Such a docking of rocket blocks (electrical and mechanical) allows certification of a single detachable harness and rocket blocks both individually (in the process of their docking), and all together. This increases the reliability of the rocket and at the same time reduces the time of its manufacture (assembly).

In the method of mounting the rockets of FIGS. 2 and 3, electrical circuit connections are specified (a specific example of a single detachable harness is provided). In this case, the ribbon wires 20 are soldered on the circuit boards 3, 4, 9 and 13. On the circuit board 10, the electronic equipment is soldered 11. On the remaining circuit boards 3, 4, 9 and 13, the ERI of the rocket launch circuits 19, 22, pins 17 and are soldered sockets 18 detachable joints that are mated with mating detachable parts installed, for example, respectively, on the block of the steering drive, the accelerating engine, the warhead and the starting engine.

ERI, for example filters, 22 protect the rocket launch circuits from electromagnetic fields, and resistors 19 limit the current in the electric igniter circuits of the rocket launch circuits. The screen 21 protects, for example, the safety-actuating mechanism (s) of the warhead from the effects of powerful external electromagnetic fields.

As noted above, a single detachable harness is made from tape wires. However, in some cases, a single detachable harness can be made in whole or in part in the form of ordinary insulated wires arranged in parallel, for example, according to GOST 23586-79.

In addition, on one or more circuit boards, in some cases, an ERI is installed or additional printed circuit boards with an ERI are installed. For example, on these printed circuit boards perform electronic equipment or its individual functional parts on discrete ERE. The printed circuit boards themselves with ERI can be interconnected using strings, forming a structure in the form of whatnot. Or, this design can be distributed (scattered) across several circuit boards.

The proposed method of mounting a rocket increases the reliability of the rocket, because eliminates the possibility of wiring damage during tuning, checking, assembling, equipping rocket blocks and mounting the rocket, while reducing the complexity of manufacturing (assembling) the rocket by reducing the number of harnesses docked in the rocket and simplifying their placement.

Claims (3)

1. A method of mounting a rocket, including connecting the individual rocket blocks mechanically and using electrical installation, characterized in that the electrical installation of the rocket blocks is carried out using a single detachable harness, which is made from tape wires and circuit boards soldered to them, on one of which an electronic rocket equipment, and on others - radio products of the rocket launch circuits and detachable connections in the form of pins and sockets, while the mating parts of the detachable connections are installed on the corresponding x missile blocks, and a single detachable tourniquet after docking detachable joints is placed and fastened along the outer surface of the rocket body, formed by interconnected blocks, and protected from above by an overlay. 2. The method according to claim 1, characterized in that a single detachable harness is performed in whole or in part from parallel insulated wires. 3. The method according to claim 1, characterized in that on one or more circuit boards install additional boards with electrical products.

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