RU2714037C2 - Device for holding and releasing transformable mechanical systems of spacecraft - Google Patents

Abstract

FIELD: astronautics.

SUBSTANCE: invention relates to the field of space engineering, and more specifically to mechanisms for retention of the transformable mechanical systems in the folded position. Device for holding and releasing transformable mechanical systems of spacecraft comprises stationary and detachable parts tightened by pin. Device is additionally equipped with a strain-gage sensor, a sensor with microswitches and a retainer. Pin is retained by lever mechanism.

EFFECT: simplified assembly.

1 cl, 5 dwg

Description

The present invention relates to rocket and space technology, in particular to the field of mechanisms for holding transformable mechanical systems of a spacecraft (SC) in a folded position.

The prior art device is known as a pyrozam lock with pyrogas shock absorption (patent RU 2354923, C1 F42B 15/36, 05/10/2009), comprising a housing, a bolt with a groove inserted in the groove of crackers, a sleeve that locks the crackers, a working piston, an intermediate piston.

A device for separating structural elements is also known (patent RU 2441823 CI, B64G 1/64 F42B 15/36, 01/01/2010), comprising a housing mounted in one part of the housing, a chamber with pyrocartridges and a membrane with a shank, and in another part of the housing, a rod , the protrusions of which are in contact with the protrusions of the liners, the grooves of which interact with the grooves of the parts of the housing, combining them.

A disadvantage of the known devices is the high complexity of the assembly in view of the large number of parts, the need for special treatment with them in view of the use of pyrotechnic elements in their composition and, as a result, large dimensions and weight.

Closest to the claimed technical solution according to the technical essence and the technical result achieved is a device for holding and releasing a transformable mechanical system (patent EP 2298648 F1, B64G 1/64, 03/23/2011) based on a bolted connection containing a pin initiating the device releasing the pin and pin catcher.

This device is taken as a prototype of the claimed invention.

The prototype has several disadvantages, namely:

1

- high complexity of assembly and operation of the device associated with a large number of parts;

- the need for the use of special equipment for locking the pin of the device, in connection with its location in a deep glass.

The problem to which the invention is directed is to implement a device for holding and releasing transformable mechanical systems of a spacecraft, providing:

- a more technologically simple device diagram, in comparison with the prototype;

- ease of assembly and operation of the device;

- implementation of control suitability, confirmation of the fact of operation of the device.

The problem is solved due to the fact that the device for holding and releasing transformed mechanical systems of the spacecraft contains a lock consisting of a housing, a lever mechanism that provides a small number of parts, compactness and does not require additional special equipment to perform operations with it, which provides a more technologically simple device circuit, a detachable part consisting of two washers providing an interface with a detachable or transformable structural element mounted on a power funnel through a spherical bearing, which provides isolation for compensating mounting stress between the device and held them element. Also, the device structurally provides easy access to the lock pin, which ensures ease of assembly and operation of the device. In addition, the device is additionally equipped with a sensor with micro switches and a latch, which ensures the suitability of the device.

The invention is illustrated by drawings:

- in FIG. 1 shows a general view of the device before operation;

- in FIG. 2 shows a general view of the device after operation;

- in FIG. 3 shows a section through a center line of a lock;

- in FIG. 4 shows a general view of the device;

- in FIG. 5 shows the pumping angle a of the washers 30.

The retention device consists of a stationary part 1 and a detachable part 2.

The stationary part 1 consists of a lever 3, a housing 4, a lever 5, an arm 6, a sensor 7, a roller 8, a roller 9, an axis 10, an axis 11, an axis 12, an axis 13, an axis 14, springs 15, a spring 16, a spring 17, the connector 18, the bracket 19, the spring 20, the screws 21, the spring 22, the retaining element 23, the spring 24, the bracket 25, the rod 26, the screws 27, the axis 28, the screws 29.

The detachable part 2 consists of washers 30, a bearing 31, a spring 32, washers 33, a nut 34, a pin 35, a funnel 36, a nut 37, a strain gauge sensor 38.

The stationary part is designed to fix the retention device on the spacecraft body and place the lever mechanism in it consisting of levers 3 and 5, interconnected via roller 9, and the detachable part is intended to be fixed on the spacecraft's detachable or transformable part, as well as to compensate for mounting voltages due to the possibility of pumping the washers 30 in the bearing 31 to an angle α (see Fig. 5) and controlling the tightening force in the connecting surface using a strain gauge sensor 38.

Angle α provides isolation to compensate for mounting voltages between the device and the element held by it. The angle is determined by the geometric parameters of the washers 30 and bearing 31.

The strain gauge sensor 38 is a sensitive strain gauge element mounted in the pin of the device in the zone of its maximum tension, which allows you to control the actual value of the load in the docking surface of the device.

The stationary and detachable parts of the device are tightened together along the connecting surface by a nut 34 through the pin 35.

The operation of the holding device is as follows: after the lever mechanism has been unlocked by the holding element 23, the bracket 6 is rotated in the direction of actuation under the action of the springs 15 and 16. The roller 8 is rolled along the bracket 6, releasing the lever 5. The lever 5 under the action of the spring 17 and the buoyant force passing to it through the roller 9, from the lever 3 rotates and releases the lever 3. The lever 3 turning, releases the lock, consisting of a spring 24 and an arm 25. At this moment, the rod 26 of the sensor 7 raises, previously fixed the bracket 25 which synchronized it, due to which the sensor 7 is triggered, confirming the fact of the operation of the lock. After the lever 3 is released, it releases the pin 35. The pin 35 is pulled from the funnel 36 by force from the spring 32, after which the separation of the detachable part from the stationary part occurs along the connecting surface.

The sensor 7 is a device consisting of a spring-loaded rod 26, when clamped or released, the contacts of its microswitches are closed or opened.

The charging and loading of the holding device after operation is performed in the following sequence:

- the tip of the pin 35 should go into the throat of the housing 4 along its longitudinal axis to the stop, while the protrusion 39 on the pin should be oriented towards the bracket 6;

- in the cocked state, the pin 35 should be engaged with the lever 3, the lever 3 with the lever 5 through the roller 9, the bracket 6 with the lever 5 through the roller 8, while for cocking use holes 40 and 41;

- install the remaining parts of the detachable part and tighten the nut 34 with the necessary torque.

The technical result consists in the application of:

- lever mechanism, providing a small number of parts, compactness and not requiring additional special equipment to perform operations with it, which provides a more technologically simple device circuit;

- a structural diagram of the device, providing free access to the lock pin, which, in turn, provides ease of assembly and operation of the device.

Claims (1)

A device for holding and releasing transformable mechanical systems of a spacecraft containing stationary and detachable parts pulled together by a pin, characterized in that the device is additionally equipped with a strain gauge sensor, a sensor with micro switches and a latch, and the pin is held by a lever mechanism.

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