RU2686804C1 - Spacecraft movable structural elements retention device - Google Patents

Abstract

FIELD: space equipment.SUBSTANCE: invention relates to the spacecrafts (SC) transformable mechanical systems or separable structural elements retention and remote separation mechanisms. Proposed SC movable structural elements retention device comprises connected together by the separation plane housing and funnel. In the housing the retention and releasing mechanism and the activating device are installed, and the detachable part is fixed on the SC structure retained element. Retention and release mechanism is made in the form of installed on the thrust bearing nut, and a rod with a thread on one end, which ensures the nut from the rod screwing out under the axial load action. Housing and funnel have the rod under the axial load action rotation limiters. Into the stationary part providing the device actuation confirmation mechanism can be additionally installed.EFFECT: technical result of the invention is reduction of impact actions with the device actuation.1 cl, 5 dwg

Description

The present invention relates to the field of mechanisms for retaining and remotely separating transformable mechanical systems or detachable (moving) elements of a spacecraft (SC) structure.

From the current level of technology known holder (patent RU 2558960 C2, B64G 1/64, F16B 21/20, 07/09/2015) on the basis of the bolted connection, which contains a housing, a pin held by a lever reducing mechanism, which is released by a swivel base.

The disadvantages of this invention are the large dimensions, weight and high complexity due to the large number of parts.

Also known pyrozamok with pirogas depreciation (patent RU 2354923 C1, F42B 15/36, 20.09.2007), comprising a housing, with a chambers with pyropatrons installed in one part and a shank membrane, and in another part of the housing with a stem, the protrusions of which are in contact with lugs inserts, grooves which interact with grooves of body parts, combining them.

The disadvantages of this invention include the high mass and the presence of pyrotechnic means, which leads to the presentation of additional requirements for electrical safety and the creation of shock pulses when triggered pyrozamka.

In addition, a device for the separation of structural elements (RU 2455205 C1, B64G 1/64, F42B 15/36, 01.11.2010) is known, based on a bolted connection and containing a housing, in one part of which there is a chamber with pyro cartridges installed in a glass with a membrane bottom on which the rod with grooves is rigidly fixed, and the detachable element is fixed on the other part. The two parts of the body are interconnected by segments through a thread made on their outer surface.

The disadvantages of this invention include the high mass and the presence of pyrotechnic means, which leads to the presentation of additional requirements for electrical safety and the creation of shock pulses when triggered pyrozamka.

The closest of the existing prior art is a device for the separation of structural elements (patent RU 2455205 C1), containing a composite case, installed in one part of the chamber of the chamber with squibs and a membrane with a rigidly fixed stem, one end of which is installed in the second part of the case in the form of a sleeve by liners. On the outer side of the liners, as well as on the inner side of the second part of the body, there are grooves. On the inner side of the liners and on the rod there are supporting shoulder, interacting with each other. One part of the housing is in contact with the second part of the housing in the form of a sleeve along the separation line. The second end of the rod, connected to the membrane, is installed in the housing through the grooves. This device is taken as a prototype. The prototype has several disadvantages, namely:

- the absence of a mechanism for triggering the sensor, confirming the fact of the device actuation;

- elements of the retention mechanism, when triggered, instantaneously relieve the load from the docking surface and move with great speed, followed by stopping due to collision with other elements of the structure, which leads to the creation of shock effects;

The task for which the claimed invention is directed is to implement a device for holding moving parts of a spacecraft structure providing:

- the possibility of testability (confirmation of the fact of actuation);

- the use of a containment mechanism, the elements of which do not create high values of shock effects.

The problem is solved due to the fact that in the holding device of movable structural elements of the spacecraft, comprising a housing, including a holding and releasing mechanism, a trigger device, as well as a funnel attached to the retaining structural member, contractible along the separation plane, according to the claimed invention, the retention and release mechanism is made in the form of a nut mounted on a thrust bearing and a pin with a thread made at one end thereof, which ensures fastening a nut with the pin under axial load. The housing and the funnel have in their design elements that limit the rotation of the pin under the action of axial load, and the axial load on the pin is created by a nut that is screwed on the second end of the pin. In addition, a bracket, a spring-loaded rod and a plate are installed in the body, which allows the sensor to operate when the pin disengages from the nut. The invention is illustrated by drawings:

- in fig. 1 shows a general view of the device;

- in fig. 2 shows a general view of the device;

- in fig. 3 shows a general view of the device;

- in fig. 4 shows a general view of the device before operation;

- in fig. 5 shows a general view of the device after operation.

The holding device consists of a housing 1, a funnel 2, a sensor 3 and a trigger device 4.

Case 1 includes a nut 6, thrust bearing 7, bracket 8, bracket 9, rod 10, plate 11, stops 12.

The funnel 2 includes, stops 13, the sleeve 14, the spring 15, the spherical washer 16, the pin 17, the washer 18, the screw 19, the nut 20.

Case 1 is designed to fix the mechanism for holding pin 17 on the body of the spacecraft, placing the sensor 3 and the trigger device 4, and funnel 2 is designed to fix to the detachable or transformable part of the spacecraft and accommodating elements to ensure the pin 17 is pulled out and fixed to the elements (stop 12 and stop 13), ensuring the restriction of rotation of the pin 17 under the action of axial load. The housing 1 and the funnel 2 of the device are pushed together with each other along the separation plane by the nut 20 through the pin 17.

The funnel 2 is intended for fixing on the detachable element of the KA and pulling the pin 17 out of the housing 1.

The holding device is a nut 6, with multi-threading made therein, mounted on a thrust bearing 7 in the housing 5.

The operation of the device is as follows, after the control signal is applied to the trigger device 4, the nut 6 is released, which, under the action of the load in the separation plane of the body 1 and the funnel 2, as well as the spring 15, rotates, screwing with the pin 17 and thereby freeing the pin 17. Self-unscrewing of the nut 6 under the action of axial load is possible due to the fact that the angle of elevation of the thread profile is greater than the angle of friction. After the pin 17 is completely out of the nut 6, there is a separation along the separation plane of the body and the funnel 1 and 2 of the device. At the same time, the rod 10, previously limited in movement by the pin 17, under the action of a force from the spring 21 bends the plate 11, catching the rod of the sensor 3, thereby releasing the rod of the sensor 3 and its actuation. The technical result consists in applying:

- the mechanism that provides the sensor triggering when the pin 19 is released from the engagement with the nut 6;

- the retention mechanism, made in the form of a nut and a threaded pin, which secures the nut from the pin under the action of an axial load, the elements of which do not collide with other structural elements while moving at high speed after they are triggered. This effect is achieved due to the gradual screwing of the nut from the pin, which smoothly removes the load from the connecting surface and reduces the speed of movement of the colliding elements of the holding mechanism;

Claims (2)

1. A device for holding movable structural elements of a spacecraft, comprising a housing including a holding and releasing mechanism, a launching device, as well as a funnel attached to the structure being retained, clamped together along a separation plane, characterized in that the holding and releasing mechanism made in the form of a nut mounted on a thrust bearing, and a pin with a thread made at one end, which secures the nut from the pin under the action of an axial load; the housing and the funnel have in their design elements that limit the rotation of the pin under the action of axial load, and the axial load on the pin is created by a nut that is screwed on the second end of the pin. 2. The device according to claim 1, characterized in that a bracket, a spring-loaded rod and a plate are additionally installed in the case, which allows for the sensor to be triggered when the pin disengages from the nut.

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