RU2391264C1 - Spacecraft light protection device - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: invention relates to safety device of spacecraft. Proposed device comprises frame (1), cover made up of two flaps (2) coupled with their rotation drives, two locking mechanisms, electric drive, turn angle transducer, flap emergent open mechanism and limiters of flaps extreme positions (17). Turn angle transducer is arranged with clearance in shielded casing and represents a rotor (9). One end of rotor shaft interacts with electric drive shaft and another end interacts with bell crank (12) of articulated lever mechanism (ALM). The latter comprises also tie rods (13), spring compensators (14) and control levers (15). Rotor (9) is furnished with magnets interacting with tight contacts on shielded casing. Compensator spring (14) is arranged between two conical tips with their conical surfaces interacting with casing of compensator (14), jointing element and mating conical surfaces on fastening elements. Shafts of mechanisms of flaps emergent opening have their end coupled with ALM output shafts and another end interacting with active levers of flaps (2) for coupling with flaps rotation drives. Said levers interact, in their turn, with stops (17) incorporated with said rotation drives. Flaps passive levers interact with said stops (17) arranged on the other side of flaps.

EFFECT: higher reliability.

6 dwg

Description

The invention relates to space technology and is used to protect the optoelectronic equipment of spacecraft from the effects of external thermal and light factors.

A light-protective device (SZU) of a spacecraft (KA) is known according to patent RU No. 2128134 C1, comprising a frame, a cover, a mechanism for opening the cover, an electric drive (EP) made of two autonomous sections, on a common output shaft of which a cam interacts with command contact cover position sensors.

The disadvantage of this RAM is the low reliability due to the fact that when the common output shaft is jammed and there is no emergency cover opening in the structure, the RAM failure occurs. In addition, command contact sensors installed outside the EF contain a pair of sliding friction, which with a large number of “Open-Close” cycles of the cover (n≥1 × 105) significantly reduces the reliability of the RAM.

It is also known SZU KA 17F12 1310-0, developed by TsSKB, Kuibyshev, 1981 (see figure 1-4), which includes:

- frame 1, rigidly fixed to the spacecraft;

- cover 2, consisting of two flaps connected with rotation nodes mounted on frame 1;

- two locking mechanisms 3, ensuring the pressure of the flaps of the lid 2 to the frame 1 through a spring-loaded opening shield 4;

- a fixed shield 5, forming together with the shield 4 and the flaps of the cover 2 (after opening) a hood;

- electric drive 6 (ET) with a rotation angle sensor 7 installed in it, which ensures the issuance of signals: to the control system (SU) - to turn off the actuator after turning the actuator shaft to a given angle and to the telemetric measuring system (SI) - about the fact of opening (closing) ) leaf flaps 2;

- articulated lever mechanism (SHRM), which provides a kinematic connection of the leaflets 2 with the EP 6 and consisting of a central two shoulders lever 8 connected through the emergency opening mechanism of the leafs (MAO) 9 with the shaft of the EP 6, two rods 10 with spring compensators 11 and control levers 12 interacting with stops-limiters 13 of their extreme positions;

- MAO 9, consisting of a shaft 14 connected at one end to the shaft of the ЭП 6, and the other with a two-arm lever 8 ШРМ, the driving element of the MAO is a cocked torsion spring 15, which is connected at one end to the shaft 14, and rests on the two-armed lever 8 at the other and during normal operation, the SZU rotates together with them, and when the EP 6 shaft (shaft 14) is jammed, the pyrochek 16, when triggered, breaks the connection of the two shoulders of the lever 8 with the shaft 14, under the action of the released spring 15, the sash of the cover 2 is moved to the “Open” position, the control MAO provides a teleme nonstoichiometric sensor 17;

- two spring compensators 11, providing compensation for errors associated with inaccuracies in working out EP 6 of a given value for the angle of rotation of the flaps of the lid 2 and with temperature deformations of the ShRM elements, each of which consists of a housing 18, springs 19, 20 and connecting elements, one of which 21 fixed in the housing 18 and provided with a hinge for connection with the control lever 12, and the other 22 with one end connected to the rod 10, and the second to the sleeve 23, moving in the housing 18 and interacting with the spring washers 24.

The disadvantages of the known RAM are low reliability due to:

- ES complexity due to the presence of a rotation angle sensor in its design;

- the complexity of the process of preparing the spacecraft for operation due to the impossibility of tuning the SZU without installing the electronic drive;

- the possibility of failure of the SZU due to jamming of the hinged components of the SHRM, since in this case the MAO cannot make an emergency opening of the lid flaps;

- the presence in the spring compensators of sliding friction pairs, the possibility of jamming of which in the SZU of the spacecraft with a long active life (T≥5 years) and a large number of “Open-Close” cycles of the leaf flaps (n≥1 × 105) is very real;

- the interaction of the SHRM control levers with stops-limiters, which does not provide for large cover sizes (diameter ≥ 2 m) the necessary accuracy of the positioning of the shutters in extreme positions due to the influence of stiffness of the structure on it.

The objective of the proposed technical solution is to increase the reliability of the spacecraft.

The problem is solved in that in the SZU of the spacecraft containing the frame, a cover consisting of two wings associated with rotation nodes, two locking mechanisms, an electric drive, a rotation angle sensor, a linkage mechanism with spring compensators, an emergency opening mechanism for the wings and stops - limiters of the extreme positions of the flaps of the lid, the rotation angle sensor is made in the form of a hinge mounted in a shielded housing mounted on the frame, a rotor, the shaft of which is coupled at one end to the drive shaft and the other with a two-armed growl ohm of the articulated lever mechanism, while the rotor contains magnets and is installed with a gap with respect to the shielded case, containing sealed contacts interacting remotely with the magnets, the spring of the spring compensator is located between two conical tips, while the conical surfaces of one of them interact on one side with the case of the compensator, and on the other with the connecting element, the conical surfaces of the other tip interact with the mating cones made in the fixing elements entents, one of which is installed in the compensator housing, and the other on the connecting element, in addition, each leaf of the lid is equipped with its emergency opening mechanism, made integral with the leaf rotation unit, the shafts of the emergency opening mechanisms of the flaps are joined at one end to the output shafts of the articulated lever mechanism, and others interact with active levers, which are equipped with lid flaps for communication with rotation nodes, interacting, in turn, with stop stops, which are part of these nodes rotation, and with the stops-limiters, which are part of other nodes of rotation, passive levers interact with which the leafs of the lid are used to connect the leafs with these nodes of rotation.

The inventive design is illustrated by drawings:

- figure 1, 2 is a General view of the spacecraft;

- figure 3 - angle sensor;

- figure 4 - spring compensator;

- figure 5, 6 - emergency opening mechanism of the lid flaps.

The light-protective device of the spacecraft contains a frame (base) 1 mounted on the hood of the spacecraft, a cover 2, consisting of two wings associated with rotation nodes 3 and 4, two locking mechanisms 5, which ensure that the leaves of the cover 2 are pressed against the frame 1 during transportation and launch it into orbit, an electric drive (EP) 6, a rotation angle sensor (DUP) 7, which provides the delivery of signals to the control system and the spacecraft and is made in the form of a hinge mounted in a shielded housing 8, mounted on the frame 1, the rotor 9, the shaft 10 of which one end interacts with the shaft 11 EP 6, and the other with a two-arm lever 12 of the articulated lever mechanism (SHRM), which provides a kinematic connection of the flaps of the lid 2 with the EP 6, which also contains rods 13, spring compensators 14, control levers 15, output shafts 16, eight stops - limiters 17, four of which are mounted on the frame 1, and four are part of the nodes of rotation 3 and 4. The rotor 9 contains magnets 18 and is installed with a gap 19 relative to the shielded housing 8, containing sealed contacts 20, interacting remotely with the magnets 18. Spring 21 spring comp nsatora 14 is arranged between two conical tips 22 and 23, wherein the conical tip surface 22 interact on one side with the housing 24 of the compensator spring 14, and on the other - a connecting element 25.

The conical surfaces of the tip 23 interact with mating conical surfaces made in fasteners, for example, nuts 26 and 27, with the nut 26 installed in the housing 24 and the nut 27 on the connecting element 25. Each leaf of the lid 2 has its own emergency opening mechanism ( MAO) 28, which ensures the shutter is in the “OPEN” position when the shaft 11 of EP 8 is jammed, as well as any of the SHR hinge assemblies and is made integral with the rotation unit 5. The shafts 29 of the MAO 28 are joined at one end to the output shafts 16 by a lever th mechanism, and others interact with the active levers 30, which are provided with the leafs of the cover 2 for communication with the nodes of rotation 3, interacting, in turn, with the stop-stops 17 that are part of these nodes of rotation, and with the stop-stops 17 that are included in the composition of the rotation nodes 4, passive levers 31 interact with which the leaf flaps are provided for connecting the flaps with these rotation nodes. MAO 28 is equipped with torsion springs 32, pyroches 33 and telemetry sensors 34 SI KA.

The work of the RAM is as follows:

after launching the spacecraft into orbit at the command of the spacecraft SU, the locking mechanisms 5 are activated, while the flaps of the lid 2 are released from communication with the frame 1;

further, to ensure the operation of the optoelectronic equipment, the SU KA gives a command to turn on the ET 6, which transfers the shutter of the lid 2 from the “Closed” position to the “Open” position, while the output of the DUP 7 signal to the SU KA to turn off the ET 6 is made only after how the active levers 30 and passive 31 reach the stop-stops 17, and the springs 21 of the spring compensators 14 will be compressed to a force sufficient to eliminate the "bounce" of the wings when exposed to regular overloads;

at the end of the working route, determined by the program of work of optoelectronic equipment, the ACS of the AC, by applying reverse polarity voltage, turns on ET 6 to move the shutters from the “Open” position to the “Closed” position, while the shutter closes in the same way as the open process - DUP 7 gives a signal in the control system of the spacecraft to turn off the electric actuator 6 after the contact of the active levers 30 and passive 31 with the stops-stops 17 and compression of the springs 21 of the spring compensators 14;

in case of failure of the standard system of opening the shutters due to jamming of the shaft 11 of the ЭП 6, as well as any of the hinge assemblies ШРМ СУ КА gives a command to operate pirochki 33, providing a break in the connections between the output shafts 16 ШРМ and the active levers 30 of the shutter leaves 2, and under torsion springs 32 MAO 28 the flaps of the lid 2 are moved to the "Open" position, while the telemetry sensor 34 gives a signal to the spacecraft about the fact of the emergency opening mechanism 28.

Using the proposed technical solution allows to increase the reliability of the spacecraft SZU due to:

- the implementation of the rotation angle sensor in the form of a separate unit that is not part of the EF, in which there are no friction-slip pairs, which simplifies the design of the EF and reduces the probability of failure of the sensor itself,

- settings of the SZU without installing the electronic drive, which simplifies the process of preparing the spacecraft for operation;

- installation of two emergency opening mechanisms, made at the same time with the rotation of the leaflets, which allows the emergency opening of the lid flaps, not only in the case of jamming of the EA shaft, but also when jamming in any of the hinge assemblies SHRM;

- execution of spring compensators without pairs of sliding friction, which reduces the likelihood of failure of spring compensators;

- Interactions with stop-limiters of active and passive levers of the valves, which allows for high-precision positioning of the valves in extreme positions when setting up the SZU and, as a result, to improve the quality of the spacecraft.

Claims (1)

A light-protective device of a spacecraft containing a frame, a cover consisting of two wings connected by levers with rotation units, two locking mechanisms, an electric drive, a rotation angle sensor, a pivot-lever mechanism with spring compensators, an emergency opening mechanism for the wings, and stop-limiters for the extreme positions of the wings a cover, characterized in that the rotation angle sensor is made in the form of a rotor pivotally mounted in a shielded housing mounted on the frame, the shaft of which is coupled at one end to the electric shaft the drive, and the other with a two-arm lever of the linkage mechanism, the rotor contains magnets and is mounted with a gap in relation to a shielded housing containing sealed contacts interacting remotely with magnets, the spring of the spring compensator is located between two conical tips, while the conical surfaces one of them interacts on the one hand with the housing of the compensator, and on the other hand with the connecting element, the conical surfaces of the other tip interact with the mating cones made in fasteners, one of which is installed in the compensator housing and the other on the connecting element, in addition, each leaf of the lid is equipped with its emergency opening mechanism, made integral with the leaf rotation unit, the shafts of the emergency opening mechanisms of the leaves are docked at one end with the output shafts of the articulated linkage mechanism, and others interact with the active levers, which are equipped with cover flaps for communication with the rotation nodes, interacting, in turn, with the stop-limiter The passive levers interact with passive levers, which are equipped with cover flaps for connecting the flaps with these rotation units, with the constituents of these rotation nodes, and with the stop-limiters that are part of other rotation nodes.

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