RU2568965C1 - Device for separation and jettison of payload fairing of carrier missile - Google Patents

Abstract

FIELD: armaments and ammunition.

SUBSTANCE: invention can be used to separate and to jettison the payload fairing of the carrier missile. The device for separation and jettison of payload fairing of carrier missile with possibility of rotation, pushers supported by the carrier missile fittings, shank with spherical end edges, springs with opposite direction of winding, and installed one in another. The pusher contains telescopically connected with each other external cylinder with sleeve with rigidly connected bottom lid with small sleeve, and internal cylinder with rod with rigidly secured top lid with sleeve. The sleeves are telescopically connected with each other with cavity creation between the bottom and top lids.

EFFECT: invention improves reliability of separation and jettison of the payload fairing.

2 dwg

Description

The proposed invention relates to the field of rocket technology and can be used in the development of launch vehicles.

The closest set of essential features is the technical solution according to the patent of the Russian Federation No. 2406662, B64G 1/64, F42B 51/36, 2009, which was adopted by the authors as an analogue.

This technical solution is a device for separating and dumping the head fairing of the launch vehicle and comprises pivots mounted on it with the possibility of rotation, the pushers mounted on the outer surface of the wings, supported on the fittings of the launch vehicle, axially adjustable, connected with the shafts of the pushers, having spherical endings. The pusher is made in the form of a pneumatic cylinder, and a pressure accumulator is installed on each leaf on its inner side, connected through an opening valve and a pneumatic line with pneumatic cylinders installed on the same leaf.

The disadvantages of this device include the fact that this device has a complex pusher design, which leads to a decrease in the reliability of separation and dumping of the head fairing of the launch vehicle. The presence of pressure accumulators installed on the inner sides of the flaps leads to a decrease in the net volume under the cowl, as well as to the need for additional alarm elements to activate the system. Also in the process of long-term storage (10 years or more) in a state of constant readiness (duty), there is a need for routine maintenance and inspections.

The aim of the invention is to provide a device for the separation and discharge of the head fairing of the launch vehicle of a simple design and increasing the reliability of separation and dumping of the head fairing.

This goal is achieved by the fact that the device for separating and dumping the head fairing of the launch vehicle comprises flaps mounted on it with the possibility of rotation, pushers pivotally mounted on the outer surface of the flaps, supported by the launch vehicle fittings connected to the pusher rods by shanks having spherical tips. Each pusher contains external and internal cylinders telescopically connected to each other with the possibility of longitudinal movement relative to each other. The inner cylinder consists of a rod pivotally connected to one of the leaves, and a top cover rigidly fixed to the rod. The outer cylinder consists of a sleeve connected to the shank with the possibility of translational motion, and a lower cover rigidly fixed to the sleeve. A glass is installed on the top lid, and a small glass is installed on the lower lid, which are telescopically connected to form a cavity between the lower and upper lids. In the cavity, springs with the opposite direction of winding are installed in one another.

The invention is illustrated by drawings, where in FIG. 1 and 2 show a device for separation and discharge of the head fairing of the launch vehicle mounted on the launch vehicle.

In FIG. 1 and 2 indicate the positions in the following order:

1 - sash;

2 - hinge;

3 - booster;

4 - lock longitudinal joint;

5 - a pusher;

6 - fitting;

7 - shank;

8 - spherical ending;

9 - the inner cylinder;

10 - an external cylinder;

11 - stock;

12 - top cover;

13 - sleeve;

14 - bottom cover;

15 - a glass;

16 - a small glass;

17 - cavity;

18 - spring;

19 - spring;

20 - stopper.

The device for separating and dumping the head fairing of the launch vehicle consists of two flaps 1 mounted on hinges 2 on the launch vehicle 3 and interconnected by locks of the longitudinal joint 4. A pair of pushers 5, supported by fittings, are pivotally mounted on each of the wings 1 6 launch vehicles 3, adjustable shanks 7 having spherical tips 8. Each pusher 5 contains an outer 10 and an inner 9 cylinder, telescopically connected to each other with the possibility of longitudinal movement relative to each other a. The inner cylinder 9 consists of a rod 11, pivotally connected to one of the leaves 1, and the upper cover 12, rigidly mounted on the rod 11. The outer cylinder 10 consists of a sleeve 13 connected to the shank 7 with the possibility of translational movement, and the lower cover 14, rigidly mounted on the sleeve 13. A glass 15 is mounted on the upper cover 12, and a small glass 16 is mounted on the lower cover 14, which are telescopically connected to form a cavity 17 between the lower 14 and the upper 12 covers. In the cavity 17, springs 18 and 19 are installed in the other with the opposite direction of winding. To store the pusher 5 in a cocked state before installing it on the launch vehicle 3, it is equipped with a stopper 20.

The device operates as follows.

After the shutters 1 are joined together by the locks of the longitudinal joint 4 and pivoted on the shutters 1 of the pushers 5, the fairing is installed in the hinges 2 of the launch vehicle 3 and secured to the carrier rocket 3. Before installing the fairing, the shanks 7 of the pushers 5 are screwed into their sleeves 13 on the value that ensures docking with the fittings 6 of the launch vehicle 3. After installing the fairing on the launch vehicle 3, the shanks 7 are unscrewed from the sleeves 13, thereby combining the spherical tips 8 with the fittings 6 ra carrier chum. After adjusting the gap between the tips 8 of the shanks 7 and the fittings 6 to zero, the stopper 20 is removed, as a result of which the wings 1 are springed relative to the fittings 6 of the launch vehicle 3. During the flight, the locks of the longitudinal joint 4 are opened at the specified time, the joint of the wings 1 and carrier rockets 3, as a result of which from the pushers 5 a pushing force begins to act on the carrier rocket 3 and the shutter 1, under the influence of which the shutter 1 turns. Moreover, due to the proximity Ichin efforts pushers perturbed motion launcher 3 is minimal.

The proposed technical solution allows to implement a simple design of the separation device and dump the head fairing of the launch vehicle, to improve the reliability of separation and dump the head fairing.

Claims (1)

A device for separating and discharging the head fairing of the launch vehicle, comprising pushers mounted on it with a possibility of rotation, pivotally mounted on the outer surface of the wings, supported on the launch vehicle fittings, connected to the pusher rods by shanks having spherical tips, characterized in that each the pusher contains an outer and inner cylinder telescopically connected to each other with the possibility of longitudinal movement relative to each other, the inner cylinder consists of a rod pivotally connected to one of the leaves and the upper cover rigidly fixed to the stem, the outer cylinder consists of a sleeve connected to the shank with the possibility of translational movement, and the lower cover rigidly fixed to the sleeve, a glass is mounted on the upper cover and a lower cover is installed a small cup is installed, which are telescopically connected to each other with the formation of a cavity between the lower and upper covers, in which springs with the opposite direction of winding are installed in one another.

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