RU2518137C2 - Pulse-free device for unlocking of spacecraft moving elements - Google Patents

Abstract

FIELD: aircraft engineering.

SUBSTANCE: invention relates to space engineering. Proposed device comprises case with the main and auxiliary actuators composed of reciprocating cylinders and spring-loaded pawl with its pin. Discs of isolation material are fitted on said reciprocating cylinders and have cut-outs for winding of wire made of material with shape memory for voltage to be fed to wire ends locked at extreme discs of every cylinder. Note here that one of extreme discs is fixed relative to reciprocating cylinder while another one is fixed relative to the case. Return spring is fitted inside every reciprocating cylinder, its one end being secured to the case and opposite end interacting with reciprocating cylinder. Coaxial bores to accommodate balls are made in the case and yokes covering the case on both sides. Cut-outs are made in said cylinders and shifted relative to coaxial bores. Note here that rocker slides on spring-loaded pawl interacting by its ends with ledges made at said yokes. Spring is arranged between the case and yokes, on both sides.

EFFECT: ruled out impact pulse at operation of pyro-means.

10 dwg

Description

The invention relates to space technology and can be used for fixing and fixing movable structural elements (PEC), in which the impact of shock pulses is not allowed.

Previously and currently used devices for fastening (PEC) in the spacecraft launch and fixation section in the orbital section are developed on the basis of pyrotechnic means. Depending on the application it may be explosive bolts, pirozamki, pirorezaki, pirocheki etc., in which the actuating element are squib and to increase ^- reliability put two cutter. With proper operation, they showed high reliability and in future developments (SC) they will be the main means for fastening and unlocking (PEC), separation of rocket stages and separation of satellites. But all of them have a significant drawback - a large impulse when triggered by pyro media. Moreover, disturbances to the structure arise not at the moment of pyrolysis explosion, but as a result of displacement and instantaneous stop of the piston or folding clamping elements, obligatory parts of all pyrotechnic means.

In the process of spacecraft development, ways to reduce disturbances by means of gaskets, installing shock absorbers, or putting pyrodevices at the maximum distance from sensitive equipment were constantly searched for. But it was not possible to exclude the shock pulse. In addition, the modern spacecraft (SC) being developed are subject to additional requirements for the transport of spacecraft in which the presence of pyrotechnic equipment is not allowed.

A device is known for connecting flight components shared in flight (patent RU No. 2096275), comprising a housing rigidly connected to a carrier in which a bolt, a lever, a piston with a seal, a squib are placed, and a nut is screwed onto the coupling bolt, and the sleeve mounted on detachable element, interacts with a coupling bolt, while the piston is connected with a lever.

There is also known a device for unlocking a moving element of a spacecraft (patent RU No. 2207307 - prototype), which contains a housing of the main and backup pyroelements located in the device case, a spring-loaded dog having its own axis installed in the body and pressing the moving element of the spacecraft, while the device is equipped with side axes and a lever that interacts with a spring-loaded pusher installed in the device.

The disadvantages of the known device, as well as the aforementioned, are significant shock pulses when the pyro charges are triggered, and also are a source of fire or explosion during transportation.

The objectives of the claimed technical solution is the exclusion of a shock pulse when triggered fire and fire hazards during transportation due to the exclusion of fire.

The problem is achieved in that in a pulseless device for decoding the moving structural elements of the spacecraft (BUR PE KA), consisting of a housing, main and backup actuating elements located in the housing, a spring-loaded dog having its own axis, which is installed in the lock housing, while actuating elements are made in the form of movable cylinders with the possibility of reciprocating rotation, on which are mounted discs of insulating material, in which are made on both sides cuts for winding wires of material with a shape memory effect, to which voltage is periodically applied and the ends of which are fixed on the extreme disks of each cylinder, while one of the extreme disks is fixed motionless relative to the movable cylinder and the other motionless relative to the body, with a returnable cylinder installed inside each cylinder a spring fixed at one end to the housing, and at the other interacts with the movable cylinder, while in the housing and in the clamps covering the housing from two sides, coaxial holes for the balls, and in the cylinders cuts are made with an offset relative to the coaxial holes, while the rocker is pivotally mounted on a spring-loaded dog, which at its ends interacts with protrusions made on the clamps, and a spring is installed between the body and the clamps on both sides.

Figure 1 shows the main view of the BUR PE KA and the position of the parts in the initial position before operation.

Figure 2 shows the BUR PE KA from above and shows the position of the rocking chair before it is triggered.

Figure 3 shows the BUR PE KA on the left and visible electrical connectors.

Figure 4 shows a General view of BUR PE KA with a cut of parts.

Figure 5, 6, 7 shows the process of turning cylinders with disks, moving (indenting) the balls into the channels and the rotated position of the clamps.

On Fig shows one of the movable disks and the placement of electrical connectors.

Figure 9 shows the device after triggering with the dog turned down.

Figure 10 shows a method of securing the ends of the wire from the EPF.

The pulseless device for decoding mobile elements of a spacecraft (BUR PE KA) consists of a housing 1 with a main and backup actuating elements, in the form of movable cylinders 2, on which disks 3 made of insulating material are mounted. A spring-loaded dog 4 is fixed on the housing 1, the axis 5 of which is fixed in the housing 1. In the disks 3, slots 6 are made on both sides for winding the wires 7 from a material with a shape memory effect (EPF), to which voltage is periodically applied, while the ends of the wires 7 mounted on the extreme disks of each movable cylinder 2, and one of the extreme disks 3 is fixed motionless relative to the movable cylinder 2, and the other motionless relative to the housing 1. Inside each movable cylinder 2 are installed return springs 8, the ends of which are connected Ans with a housing 1 and a movable cylinder 2. In the clamps 9, covering the housing 1, as well as in the housing 1 itself, there are coaxial holes 10 for balls 11, which are kept from falling out by plugs 12. In the movable cylinders 2, cutouts 13 are made with an offset relative to the coaxial holes 10 A rocker 14 is pivotally mounted on the spring-loaded dog 4, the ends of which abut against the protrusions 15 of the clamps 9. A spring 16 is installed between the housing 1 and the clamps 9. The ends of the wires 7 are fixed on the extreme disks of the movable cylinders 2 and connected to the electrical connectors 17.

To unlock and open, for example, a BS, on command from the spacecraft control system, power is supplied to all wires 7 of the EPF metal, which begin to heat up and contract, turning the movable cylinder 2, overcoming the resistance of the return springs 8, the friction resistance between the balls 11 and the movable cylinder 2 , (FIGS. 5, 6 and 7). In the process of rotation of the movable cylinder 2, all the balls 11 are constantly squeezed by the clamp 9 by the forces of the spring 16 (Fig. 4) until they are aligned with the cutouts 13 (sockets) in the movable cylinder 2, and the movement of the balls 11 is slow due to the heating of the wire 7 of EPF for a time greater than 5 s, and, therefore, eliminates the instantaneous folding of the spring-loaded dog 4 and its impact at the end of rotation. If a failure occurs during the rotation of one of the movable cylinders 2, its jamming or failure of the command to heat the wire 7, then in this case the second movable cylinder may work, because the swivel rocker 14 provides free folding of the spring-loaded dog 4.

Thus, when shortening the heated wire, each disk rotates by a certain angle Δα, and the final movable disk rotates by the angle α = ΣΔα. The value of the final angle can be set and depends on the length of the wire.

In this design, two wires are laid in order to eliminate friction losses during rotation of the disks, i.e. the force of squeezing the disk from the tension of the wire and the counteraction of the return spring are located on opposite sides of the disk and are perceived by the disk itself.

The proposed design of a pulseless device for decoding the moving elements of the spacecraft will eliminate the shock pulse that affects the operation of sensitive spacecraft equipment and fire hazard during transportation of the product due to the exclusion of pyromedicines from the design, and will also allow for verification tests during complex pre-launch tests of the spacecraft.

Claims (1)

A pulseless device for the fixation of moving structural elements of a spacecraft (SC), consisting of a housing, main and backup actuating elements located in the housing, a spring-loaded dog having its own axis, which is installed in the housing, characterized in that the actuating elements are made in the form of movable cylinders with the possibility of reciprocating rotation, on which disks of insulating material are mounted, in which slots for winding material wires are made on both sides with a shape memory effect, to which voltage is periodically applied and the ends of which are fixed on the extreme disks of each cylinder, while one of the extreme disks is fixed motionless relative to the movable cylinder, and the other motionless relative to the housing, with a return spring installed inside each movable cylinder, fixed at one end on the housing, and the other interacts with the movable cylinder, while in the housing and in the clamps covering the housing on both sides, coaxial holes are made for the balls, and in rah cutouts offset with respect to the coaxial bores, wherein the rocker is hinged to a spring-loaded pawl which engages at its ends with projections formed on the collars, and between the housing and the clamps on both sides of a spring.

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