RU2771868C1 - System for separating rocket stages - Google Patents

Abstract

FIELD: rocket engineering.

SUBSTANCE: invention relates to the field of rocket engineering, more specifically, to systems for releasing or separating objects of an aerial vehicle. System for separating rocket stages includes attachment fittings for frames of the separated structures, mounting surfaces made in the end planes of the frames, explosive units for releasing the attachment fittings, and a compartment pusher. The attachment fittings for the frames comprise thrust flanges made on the frame of one of the separated structures and locking levers made on the frame of the other one of the separated structures, installed on the axes of rotation. Also provided is a movable frame installed on guides through the windows made in the movable frame, configured to be moved along the guides, locks for the final position of the movable frame, rods connecting the movable frame with opposing parts of the locking levers. The locks for the final position of the movable frame are made on the guides in the form of deformable locking cones blocking the movable frame when the frame is moved to the end position. The thrust flanges and thrust ends of the locking levers are made at an angle to the mounting plane of the frames.

EFFECT: structural simplification.

1 cl, 6 dwg

Description

The invention relates to systems for dropping or separating objects, mainly rocket stages, compartments, fairings, protective screens and payloads, from the supporting structures of an aircraft in any part of the flight path and can be used in the field of aviation and rocketry.

The closest technical solution, chosen as a prototype, is a system for separating structural elements - patent RU 2724337, containing power attachment points for frames of separable structures, mating surfaces made in the end planes of frames, pyrounits for releasing power attachment points and a separation pusher, power attachment points for frames contain thrust shelves made on the frame of one of the separable structures, distributed along the periphery of the frame, and locking levers made on the frame of another of the separable structures, mounted on the axes of rotation, with the possibility of a stop during rotation on the axes of rotation of one of the ends of the locking lever on the thrust shelves of the frame of the opposite detachable part of the structure, as well as a movable frame equipped with floating spherical plain bearings, mounted on guides through the holes of the inner rings of the floating spherical plain bearings, with the possibility of movement along the guides, in the direction perpendicular to the mating plane of the frames, spring-loaded end position locks located on the movable frame, made in the form of rocking chairs mounted on the axes of rotation, with the possibility of stopping during rotation on the axes of rotation of the edge of the rocking chair into a ledge on the frame, when moving the movable frame to the extreme position, rods connecting the movable frame with the opposite parts of the locking levers, made with the possibility of adjusting their length, a nut with a tightening bolt, with the head of the tightening bolt resting against the movable frame, and pressing the frames along the mating surfaces when the movable frame moves in the process of tightening the bolt, with In this case, an annular groove is made in the bolt body with a conical side wall located on the side opposite to the bolt tightening direction; between the groove of the draw bolt body and the cylindrical shiftable spring-loaded piston located above the individual crackers, and the pyro-assembly for releasing the power fasteners is made in the form of a pneumatic cylinder with a body shifted relative to the draw bolt body, fixed on the movable frame and enclosing the shifted spring-loaded piston.

The common essential features of the prototype - a system for separating structural elements, coinciding with the essential features of the proposed device are the following: the joint contains power attachment points for frames of separated structures, mating surfaces made in the end planes of the frames, pyrounits for releasing power attachment points and a detachment pusher, while power nodes frame fastenings contain thrust shelves made on the frame of one of the separable structures, distributed along the periphery of the frame, and locking levers made on the frame of the other of the separable structures, mounted on the axes of rotation, with the possibility of stopping during rotation on the axes of rotation of one of the ends of the locking lever on the thrust shelves of the frame of the opposite detachable part of the structure, as well as a movable frame mounted on guides through windows made in the movable frame, with the possibility of moving along the guides, in the direction perpendicular to the mating th plane of the frames, locks of the end position of the movable frame, rods connecting the movable frame with the opposite parts of the locking levers.

A feature of the known prototype joint is the complexity of the design and assembly of the end position of the movable frame, the details of which occupy the internal space of the product and increase its mass, and the emphasis of the locking levers on the thrust shelves in a plane parallel to the mating plane of the frames does not provide reliable fixation of one frame relative to the other in the direction parallel to the mating plane of the frames, under vibration loading conditions.

The proposed invention - a rocket stage separation system - solves the problems of simplifying the design and assembly, increasing the reliability of the product as a whole, and reducing the weight and dimensions.

To achieve the above technical result in the rocket stage separation system, there are: power attachment points for frames of separated structures, mating surfaces made in the end planes of the frames, pyrounits for releasing power attachment points and a separation pusher, while the power attachment points of the frames contain one of the divided structures made on the frame structures, thrust flanges distributed along the periphery of the frame, and made on the frame of another of the separable structures, locking levers mounted on the axes of rotation, with the possibility of a stop during rotation on the axes of rotation of one of the ends of the locking lever on the thrust flanges of the frame of the opposite detachable part of the structure, as well as a movable a frame mounted on guides through windows made in the movable frame, with the possibility of moving along the guides, in the direction perpendicular to the mating plane of the frames, locks for the final position of the movable frame, rods connecting a movable frame with opposite parts of the locking levers, while the end position locks of the movable frame are made on the guides in the form of deformable locking cones that jam the movable frame when it moves to the final position, and the thrust shelves and the thrust ends of the locking levers are made at an angle to the mating plane of the frames.

A distinctive feature of the proposed rocket stage separation system is that the end position locks of the movable frame are made on guides in the form of deformable locking cones that jam the movable frame when it moves to the final position, and the thrust shelves and thrust ends of the locking levers are made at an angle to the mating plane of the frames .

Due to the presence of these distinguishing features in combination with the known ones, the following is achieved: the design and assembly are simplified, the reliability of the product as a whole is increased, and the weight and dimensions are reduced.

This technical solution can be used as a docking unit for rocket stages, compartments, fairings, protective screens and payloads that need to be separated during the flight.

The invention is illustrated in FIG. 1…6.

In FIG. 1 is a rear view of the rocket stage separation system.

In FIG. 2, section A-A (Fig. 1), the rocket stage separation system is shown in the hold position.

In FIG. 3, section A-A (Fig. 1), the rocket stage separation system is shown in the unlocked position.

In FIG. 4, section B-B (Fig. 1), shows the stop of the locking lever on the thrust shelf of the frame at an angle α°.

In FIG. 5, remote element B (Fig. 2), shows the lock of the end position of the movable frame.

In FIG. Fig. 6, remote element B (Fig. 3), shows the end position lock of the movable frame in the deformed state.

The rocket stage separation system shown in Fig. 1 ... 6 contains power attachment points of frames 1 (Fig. 2, 3, 4) and 2 (Fig. 2, 3, 4, 5, 6) of separable structures, mating surfaces 3 (Fig. 2, 3, 4), made in the end planes of the frames 1 and 2, the pyrounits of the release 4 (Fig. 1, 2, 3) of the power attachment points and the compartment pusher 5 (Fig. 1), while the power attachment points of the frames 1 and 2 contain one of the separable ones made on the frame 1 structures, thrust shelves 6 (Fig. 4) distributed along the periphery of the frame 1, and made on the frame 2 of another of the separable structures, locking levers 7 (Fig. 4) mounted on the axes of rotation 8 (Fig. 4), with the possibility of a stop during rotation on the axes of rotation 8 of one of the ends of the locking lever 7 on the thrust shelf 6 of the frame 1 of the opposite detachable part of the structure, as well as the movable frame 9 (Fig. 1, 2, 3, 4, 5, 6) mounted on the guides 10 (Fig. 1 , 2, 3, 5, 6) through the windows 11 made in the movable frame 9 (Fig. 5, 6), with the possibility of moving along the guides 10, in the direction perpendicular to the mating plane 3 of frames 1 and 2, end position locks 12 (Fig. 5, 6) of the movable frame 9, rods 13 (Fig. 4), connecting the movable frame 9 with the opposite parts of the locking levers 7, while the end position locks 12 of the movable frame 9 are made on the guides 10 in the form of deformable locking cones that jam the movable frame 9 when it is moved to the final position, and the thrust shelves 6 and thrust ends 14 (Fig. 4) of the locking levers 7 are made at an angle α° (Fig. 4) to the mating plane 3 of the frames 1 and 2.

The rocket stage separation system works as follows: when an electrical signal is applied to the release pyrounits 4, excess pressure occurs, which ensures the movement of the movable frame 9 along the guides 10, while the movable frame 9 rotates the locking levers 7 through the rods 13, thereby releasing the frames 1 and 2 out of engagement. In the final position, the windows 11, made in the movable frame 9, are combined with the end position latches 12, made on the guides 10 in the form of deformable locking cones, which leads to jamming of the movable frame 9, after which the separation pusher 5 is triggered, which takes away the frames 1 and 2 from each other.

Claims (1)

Rocket stage separation system, including power attachment points of frames of separable structures, mating surfaces made in the end planes of the frames, pyrounits for unlocking power attachment points and a detachment pusher, while the power attachment points of the frames contain thrust shelves made on the frame of one of the structures to be separated, distributed along the periphery of the frame, and made on the frame of another of the separable structures, the locking levers mounted on the axes of rotation, with the possibility of stopping during rotation on the axes of rotation of one of the ends of the locking lever on the thrust flanges of the frame of the opposite detachable part of the structure, as well as a movable frame mounted on guides through made in the movable frame of the window with the ability to move along the guides in the direction perpendicular to the mating plane of the frames, the latches of the end position of the movable frame, the rods connecting the movable frame with the opposite parts of the fixing movable frame end position locks, characterized in that the end position locks of the movable frame are made on the guides in the form of deformable locking cones that jam the movable frame when it moves to the end position, and the stop shelves and the stop ends of the fixing levers are made at an angle to the mating plane of the frames.

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