RU168688U1 - DEVICE FOR PLACING AN ELECTRICAL CONNECTOR IN THE HOUSING OF THE AIRCRAFT - Google Patents

Abstract

The claimed technical solution relates to the field of rocket technology, in particular to devices for undocking electrical communications between a rocket and an aircraft, with a launcher or with a transport and launch container. The device for locating an electrical connector in the aircraft body contains a terminal block of the onboard electrical connector fixed in place the outlet of the electrical connector block has a hatch, which is equipped with a rotary cover. The rotary cover is fixed on the axis of rotation installed in the hole of the aircraft body parallel to the axis of the hole for placement of the electrical connector, and is equipped with a spring mechanism installed in the aircraft body and comprising a body pivotally connected to the aircraft body, a spring-loaded rod mounted in the spring mechanism body with the possibility of longitudinal movement and pivotally connected to a rocking chair installed in the aircraft body with the possibility of rotation and rigidly with Unification with the cover rotation axis. The rotary cover follows the theoretical contour of the aircraft.

Description

The claimed technical solution relates to the field of rocket technology, in particular to devices for undocking electrical communications between a rocket and an airplane, with a launcher or with a transport and launch container (TPK).

Various devices are known for accommodating an electrical connector in a rocket housing, followed by closing the electrical connector. The closest in the set of essential features is the technical solution according to patent RU No. 2247920, which was accepted by the authors as an analogue.

This technical solution consists in the fact that a hatch with lowered supporting edges is made on the rocket body at the exit point of the electrical connector block. The missile is equipped with a rotary shield, consisting of a cover and one end of the lever rigidly connected to it, pivotally attached to the other end on the outer surface of the rocket body in front of the hatch. The outer surface of the lid is conical with an extension towards the aft of the rocket.

The disadvantages of this technical solution include the fact that the lever pivotally attached at one end to the rocket body and the conical shape of the outer surface of the lid lead to a decrease in the flow of the rocket and lower aerodynamic characteristics of the rocket, especially when using this technical solution in the design of high-speed rockets. Also, the absence of fixing elements of the cover in the working position can lead to its opening during rocket maneuvers and, as a result, to the effect of high temperatures on the connector and carbonization of the electrical insulation between the contacts of the connector block, while it becomes electrically conductive, which causes the contacts to close, which may result in become a failure on-board equipment.

The technical result of the utility model is the elimination of the above disadvantages.

The specified technical result is achieved in that the device for locating the electrical connector in the aircraft body comprises a board of the electrical connector fixed in the opening of the housing, and a hatch is provided at the exit of the electrical connector block, which is provided with a rotatable cover. The rotary cover is fixed on the axis of rotation installed in the hole of the aircraft body parallel to the axis of the hole for placement of the electrical connector, and is equipped with a spring mechanism installed in the aircraft body and comprising a body pivotally connected to the aircraft body, a spring-loaded rod mounted in the spring mechanism body with the possibility of longitudinal movement and pivotally connected to a rocking chair installed in the aircraft body with the possibility of rotation and rigidly with Unification with the cover rotation axis. The outer surface of the rotary cover repeats the theoretical contour of the aircraft.

The proposed technical solution is illustrated by drawings - in FIG. 1-4, which presents a general view and section on structural elements.

In FIG. 1-4, the positions are indicated in the following order:

1 - aircraft body;

2 - electrical connector;

3 - block;

4 - hatch;

5 - a rotary cover;

6 - axis of rotation;

7 - spring mechanism;

8 - case;

9 - stock;

10 - spring;

11 - rocking chair.

A device for placing an electrical connector in an aircraft body, comprising an on-board electrical connector (2) secured to a hole (3) in an aircraft body hole (1), and a sunroof (4) is provided at the outlet of the electrical connector (3) pad (2), which is provided with a pivoting cover ( 5). The rotary cover (5) is fixed on the axis of rotation (6) installed in the hole of the aircraft body (1), parallel to the axis of the hole for placement of the electrical connector (2) and is equipped with a spring mechanism (7) installed in the aircraft body and containing the body (8), pivotally connected to the aircraft body (1), a spring-loaded rod (9) using a spring (10) mounted in the housing (8) of the spring mechanism (7) with the possibility of longitudinal movement and pivotally connected to a rocking chair (11) installed in the aircraft body ( 1) with the possibility of rotation and rigidly connected to the axis of rotation (6) of the roof pulleys (5). The outer surface of the rotary cover (5) follows the theoretical contour of the aircraft.

The device operates as follows. In the prelaunch position, the rocket is electrically connected to the launcher (with the aircraft, with the TPK) through an electrical connector (2) consisting of a block (3) docked with the launch pad of the launcher (aircraft, TPK) with a harness. The rotary cover (5) is then retracted to its original position. After the launch of the rocket, there is an electrical undocking of the pads. After electrical disconnection under the action of the spring mechanism (7), the rotary cover (5) is moved to the working position and held in this position throughout the flight. In this case, the outer surface of the rotary cover (5) repeats the theoretical contour of the aircraft body (1).

The proposed technical solution allows to implement a simple design of the device for placing an electrical connector in the aircraft body, comprising a rotatable cover that closes the electrical connector after electrical disconnection.

Claims (1)

A device for locating an electrical connector in an aircraft’s hull, comprising an onboard electrical connector block, a hatch is provided at the exit of the electric connector block, which is provided with a hinged lid, characterized in that the hinged lid is mounted on a rotation axis mounted in the aperture of the aircraft’s hull, in parallel the axis of the hole to accommodate the electrical connector and is equipped with a spring mechanism mounted in the aircraft body and comprising a body articulated with United with the aircraft body, a spring-loaded rod installed in the body of the spring mechanism with the possibility of longitudinal movement and pivotally connected to a rocker mounted in the aircraft body with the possibility of rotation and rigidly connected to the axis of rotation of the cover, while the outer surface of the rotary cover repeats the theoretical contour of the aircraft apparatus.

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