RU2514015C1 - Spacecraft light protection device cover assembly - Google Patents

Abstract

FIELD: aircraft engineering.

SUBSTANCE: proposed cover assembly comprises base with drive motor and mechanism of emergent cover opening with pyro cotter-pin. Besides, this assembly comprises spring-loaded cylindrical barrel mounted at drive motor housing to displace vertically thereabout. Spring-loaded barrel interacts with mechanism of emergent cover opening pyro cotter-pin rod Bracket with yoke for coupling between cover and drive motor output shaft is fitted on said shaft. Rotary spring-loaded latch is fitted in bracket yoke and has lever interacting with spring-loaded barrel on one side. On opposite side, cylindrical contact surface aligned with the latch rotational axis interacts with flat contact surface of the retainer spring-loaded rod. Force developed by latch spring is directed towards latch closing direction.

EFFECT: expanded operating performances.

8 dwg

Description

The invention relates to space technology and is used to open and close openings in a hood that protects the optoelectronic equipment of spacecraft (SC) from the effects of external thermal and light factors.

Known light-protective device (SZU) of a spacecraft (KA) according to patent RU No. 2128134, containing a frame, a cover, a mechanism for opening the cover, an electric drive (EP), made of two autonomous sections.

The disadvantage of the opening-closing lid assembly described in the known SZU is its low reliability, due to the fact that when the common output shaft of the drive is jammed and there is no emergency lid opening mechanism in the design, the SZU fails.

A light-protective device of the spacecraft according to the patent RU No. 2391264 is known, in which the SZU cover assembly containing an electric drive base, a cover consisting of two wings, emergency shutter opening mechanisms made integrally with their rotation nodes, pyrochecks.

A disadvantage of the known SZU cover assembly is its limited operational capabilities, since it is designed for double-leaf covers, and due to the design features of the spacecraft and the limited space in the installation area of the SZU cover, where it becomes necessary to use a single-leaf cover, the axis of rotation of which should be in a different plane (in cutting plane of the hood), and since the installation of such a cover is provided directly on the output shaft of the electric drive, therefore, the use of the known cover assembly Memory is unacceptable.

The objective of the proposed technical solution is to expand the operational capabilities of the lid assembly of the light-protective device of the spacecraft (CC SZU KA.)

The problem is solved in that the UK SZU KA, containing a base with an electric drive, the emergency opening mechanism of the cover with pyrochee, characterized in that it is equipped with a spring-loaded cylindrical cup that is mounted on the electric housing with the possibility of vertical movement and interacts with the pyrochemical rod of the emergency opening mechanism of the cover mounted motionlessly on the base, moreover, a bracket with a plug is installed on the output shaft of the electric drive for coupling the cover with the output shaft of the electric drive, and in the fork of the bracket, a rotating spring-loaded latch is mounted, having a lever that, on the one hand, interacts with the spring-loaded cup, and on the other hand, with its cylindrical contact surface, located coaxial with the axis of rotation of the spring-loaded latch, with the flat contact surface of the spring-loaded latch rod mounted on the lid, with this force, developed by the spring of the latch, is directed towards the locking of the spring-loaded latch.

The inventive design is illustrated by drawings:

- figure 1 is a General view of the Criminal Code SZU KA;

- figure 2 is a view A in figure 1 (cover in the "Closed" position);

- figure 3 is a view A in figure 1 (cover in the "Open" position);

- figure 4 - remote element B in figure 1;

- figure 5 - remote element In figure 4 (latch to the emergency opening mechanism);

- 6 - remote element In figure 4 (latch after the operation of the emergency opening mechanism);

- Fig.7 is a section GG in Fig 4;

- Fig.8 is a section DD in Fig.4.

The lid assembly of the light-protective device of the spacecraft contains:

- base 1 with electric drive 2 mounted on the spacecraft;

- a cover 3 mounted on the output shaft of the electric drive 2;

- emergency opening mechanism 4, connecting the cover 3 with the output shaft of the electric drive 2 by means of a moving spring-loaded rod 5, the latch 6, which interacts with the cover 3 and with the fork of the bracket 7;

- pyrochelic 8, mounted on the base 1 and having a fixed electric cable loop 9, the rod 10 of which interacts with a spring-loaded cylindrical glass 11 mounted on the housing of the electric drive 2 with the possibility of vertical movement;

bracket 7, in the plug of which a rotating spring-loaded latch 12 is mounted, having a lever 13, which on the one hand interacts with the spring-loaded cup 11, and on the other hand, with its cylindrical surface 14, located coaxial with the axis of rotation of the spring-loaded latch 12, with a flat contact surface 15 of the spring-loaded rod 5 of the latch 6 mounted on the cover 3. In this case, the force exerted by the spring 16 of the spring-loaded latch 12 is directed towards the locking of the spring-loaded latch 12.

In the initial position, the output shaft of the electric drive 2 through the bracket 7 is rigidly connected with the spring-loaded rod 5 of the latch 6 mounted on the cover 3. The spring-loaded rod 5 is held in the extended position by the spring-loaded latch 12, which due to its spring 16 is constantly pressed against the spring-loaded rod 5 of the latch 6. The rigid connection of the output shaft of the electric drive 2 through the bracket 7 and the spring-loaded rod 5 of the retainer 6 with the cover 3 transfers to the last torque, and through the control system of the spacecraft is "Opening" or “Closing” of the cover 3. The spring-loaded cylindrical cup 11 is held by a pyroece 8.

In case of failure of the electric drive 2 and the impossibility of the regular opening of the cover 3, the spacecraft control system issues a command for the operation of the pyrochelic 8, while the rod 10 of the pyrochee releases the spring-loaded cylindrical cup 11, which moves due to its spring. As a result of the contact of the end surface of the cylindrical spring-loaded cup 11 with the lever 13 of the spring-loaded latch 12, the latter rotates around its axis of rotation, overcoming the force of the spring 16. The contact surface 14 of the spring-loaded latch 12, located coaxially with the axis of rotation, slides along the flat contact surface 15 of the spring-loaded clamp rod 5 6, without creating additional axial forces on the spring-loaded rod 5 of the latch 6. At the end of the rotation of the spring-loaded latch 12, the spring-loaded rod 5 of the latch 6 breaks from the contact surface 15, out of interaction with the fork of the bracket 7 and releases the cover 3. The cover 3, under the action of the spring of the emergency opening mechanism 4, unfolds at a predetermined angle and is fixed in the open position by a special latch (not shown in FIG. 2).

Using the proposed technical solution allows to expand the possibility of using the cover unit of the SZU KA with the emergency opening mechanism for use in the cover of the SZU, which is installed directly on the output shaft of the electric drive.

Claims (1)

A cover assembly for a light-protective device of a spacecraft containing an electric base, an emergency opening mechanism for a cover with pyrocheck, characterized in that it is equipped with a spring-loaded cylindrical cup that is mounted on the electric housing with the possibility of vertical movement and interacts with the pyrocheck rod of the emergency opening mechanism for a cover mounted motionless on the base, moreover, a bracket with a plug is installed on the output shaft of the electric drive for coupling the cover with the output shaft of the electric of the actuator, and in the fork of the bracket a rotating spring-loaded latch is mounted having a lever that, on the one hand, interacts with the spring-loaded cup, and, on the other hand, with its cylindrical contact surface, located coaxial with the axis of rotation of the latch, with the flat contact surface of the spring-loaded latch rod mounted on the cover while the force developed by the spring of the latch is directed toward locking the latch.

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