RU2558960C2 - Holder - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: invention relates to means for the temporary fixation of different devices on a space vehicle (SV), namely solar-cell panels. A holder has a housing out of which a tightening pin (2) retaining elements (4.1-4.n) projects. For locking-unlocking of the head part of the pin there used are levers (14), a cylinder (17) with rollers (13), a spring (16) and a rotary base (12). After the pin is unlocked, a pressure element (18) presses a sensor rod (19) for actuation of the holder. Upon a command from a SV control system, the base (12) is turned. Limit stops (20) of the base slide off from bearings (28) of the cylinder (17). The latter goes down under the action of springs (16). The second arms of the levers (14) are rolled on the rollers (13), become free from rotation limitation, turned and make the head part of the pin (2) free. Under the action of the springs (6) the pin (2) goes up and makes a set of the retained elements (4.1-4.n) free. An element (18) moves together with the cylinder (17) by pressing the sensor rod (19).

EFFECT: technical result of the invention is the improvement of reliability and maintainability of the item, as well as the quality of diagnostics of the SV state on the orbit.

6 cl, 6 dwg

Description

The present invention relates to mechanical engineering, mainly to holders of various devices on a spacecraft (SC), in particular solar panels.

From the existing level of technology, there is a holder (lock) for caulking BS panels, which contains pyrotechnic charges (usually two) as a drive element, for example a squib that is triggered when an electric current is applied to it. The squibs have high reliability of operation. In this case, the actuating element holding the tightening bolt of the BS panels is a split pie-nut. As an example, consider patent EP 2298684 A1, dated 03/23/2011, M Cl. B64G 1/22, B64G / 64, F16B 21/12.

The advantages of this type of lock include high reliability of operation, due to the use of pyrotechnics.

The disadvantages of this technical solution are:

- firstly, a large shock pulse when triggered pyromedics;

- secondly, the crushing of the thread of the pie and the bolt, tightened with great effort, when the lock is triggered. In order to increase reliability, it becomes necessary to replace the split nut and the coupling bolt before use in normal conditions, which is not technologically advanced.

In this case, you can only check the integrity of the electrical circuits of pirochka or other drive elements. Checking the operation of the mechanism of the split lock nut is not carried out, so the use of unverified elements reduces the overall reliability of the lock and requires a large amount of testing to ensure the operation.

- Thirdly, the lack of telemetric information about the fact of the operation of the castle reduces the quality of diagnosing the state of the castle in orbit after operation.

According to patent EP 1191271 A2, class F16L 35/00 of 07/17/2001, the element holding the split nut is a twisted spring, the end of which is prevented from being untwisted by a metal element with shape memory.

The advantages of this type of lock include the exclusion of pyroshock when the lock is triggered, due to the use of metal elements with shape memory.

The disadvantages of this system are:

firstly, the crushing of the thread of the pie and the bolt, tightened with great effort. When the lock is triggered, additional low-tech features appear - removing the split nut to restore the unit in terms of replacing the elements of the split nut, cocking the untwisted spring, fixing the spring ends with metal elements with shape memory;

secondly, the lack of telemetric information about the fact of the operation of the lock reduces the quality of diagnosis of the lock in orbit after operation.

Closest to the claimed technical solution is the design of the castle according to the patent U.S. No. 5,098,042 dated March 24, 1992, MKl. E04H 12/18, E05D 15/26.

The known design is intended for multiple technological triggering during the manufacturing process of the castle and a single operation in the composition of the spacecraft in operating conditions.

A system for maintaining in a folded position a plurality of elements that are pivotally connected to each other and to a structure (for example, solar panels on a spaceship), the elements of which are able to occupy a folded position in which these elements form a packet, or another unfolded position in which these elements are in open end-to-end alignment, wherein said system comprises:

- a holder (locking lock) containing a locking element passing through the indicated sets of elements in the folded position, connected by the first of its ends to the specified structure and connected by the second end to the external element (BS panel) for locking by the fixing element in the folded position of these elements, and also controls for unlocking-locking the elements and releasing the locking element, thereby allowing the set of elements to pass from the folded position to the deployed position. In this case, the control means include a plurality of balls distributed around the first end, and screws forming the spacer force of the balls on the fixing element, and a second position of the balls releasing the end of the locking element.

Castle lock according to this patent operates as follows.

The first end of the locking element has an annular selection. This sample includes holding the given position of the end of the fixing element, pressing two balls on each side of the end, located in the horizontal channel, and one ball located in the vertical channel. The main force is created by two balls located in a horizontal channel. They are tightened by two screws located at the ends of the channels. To enable the mechanism to operate, the second horizontal ball is shifted downward, therefore, the tightening force is distributed both on the horizontal ball (tightening the end of the locking element) and on the lower ball resting on the controls for locking-unlocking and releasing the locking element - a rotary washer.

The rotary washer is connected to the spring drive, and the rod is connected to the pyroelectric unit and has a lowering side on the contact with the balls.

Thus, when the pyrocheck is triggered, a flexible connection connected to the lever of the rotary washer removes the holding force from turning the washer, and the washer rotates under the action of the spring, overcoming the force from tightening the upper ball. The third ball falls into the abatement of the puck, making room for the second ball. The end of the locking element, under the action of a tightening force, shifts the first balls to the sides and is released.

The advantages of this type of lock include the exclusion of a pyroshock when the lock is triggered, due to the use of the option of holding the pin with a ball lock.

The disadvantages of this technical solution are:

- firstly, the use of balls as retaining elements that increase contact stresses in the contact zone with the annular recess of the locking element (contact along the line);

- secondly, the complication of the manufacturing and adjustment technology of the lock (there must be a high purity of the processing of the channels, the presence of lubricant working in a vacuum, the accuracy of setting the value of the tightening of the adjustment screws) due to the use of multi-way movement of the balls when triggered. At the same time, the force of tightening the balls with screws (difficult to control) leads to an increase in the contact loading of the rotary washer, and the force on the rotation drive (spring) depends on it;

- thirdly, the lack of telemetric information about the fact of the operation of the castle, which reduces the quality of diagnosing the state of the castle in orbit after the operation of the castle.

The tasks to be solved by the claimed invention is directed, are to implement products that meet modern requirements for reliability and manufacturability, namely:

- improving the reliability of the operation of the holder by introducing a mechanism for disconnecting the held elements from a fixed position on the holder;

- the introduction of a safety element against unauthorized disclosure of the retention pin retention mechanism during technological work;

- simplification of manufacturing technology, adjusting the holder and reducing loads in the holding mechanism of the tightening pin of the holder;

- improving the quality of the diagnostics of the state of the spacecraft in orbit after the operation of the holder.

The tasks are solved due to the fact that the holder containing the housing, the tightening pin passing through the set of retained elements in the folded position, connected by the first of its ends to the holder body and connected by the second end to the external held element to lock the held elements, as well as the retention mechanism the clamping pin of the holder, connected with the spacecraft control system and providing the release of the set of held elements, contains a contact sensor mounted on the fixed part of the holder I, and a pressure element mounted on the surface of the larva and interacting with the sensor rod at the end of the stroke when moving the larva, a safety element against unauthorized operation of the retention pin retention mechanism by rotating the movable base of the mechanism, and a mechanism is introduced in conjunction with the set of retained elements and the holder body disconnecting the held elements from a fixed position on the holder after releasing, consisting of a spring, while the tightening pin has a spherical protrusion in the zone of contact with the levers, and the retention pin retention mechanism includes a clip with unequal arms, each of which rests with the smaller shoulder against the spherical protrusions of the retractor pin head, and rests against the retention mechanism larva with the larger shoulder, while the inability to move the larva along the axis of the retraction pin before the actuation of the retention mechanism, it is ensured by the presence of stops on the rotary base, against which the larva bearings abut, and the movable base together with the stops rotates under Corollary springs on command to turn on the satellite control system, wherein movement of larvae occurs, the release lever holder, releasing the tightening pin for opening and operation of the sensor.

The mechanism of separation of the held spacecraft elements from a fixed position on the holder can be made in the form of an annular spring.

The larva of the retention mechanism may include rollers in which the arms of the holder abut, and the rollers, when the larva moves, roll between the supporting surfaces of the levers and the larva.

Larvae can incorporate spring elements that return the rollers to their original position after the retention pin retention mechanism is activated.

The safety element against unauthorized rotation of the base can be made in the form of a rod passing through the rotary base and the holder body, with the fixation of the position of the rod on the end holding element, for example, with a union nut.

The pressure element interacting with the sensor rod at the end of the stroke when moving the larva can be spring loaded.

Thus, the claimed design of the holder will improve the reliability of operation of the holder by introducing an additional mechanism for disconnecting the held elements from a fixed position on the holder after the triggering mechanism for holding the tightening pin. The presence of a safety element against rotation of the movable base of the retention pin holding mechanism will simplify the technology of working with the holder, as protects against unauthorized opening of the holder during technological work associated, for example, with the connection of the holder rod with the opening elements on the spacecraft. The presence of a contact sensor improves the quality of diagnosing the state of the mechanism for holding the tightening pin in orbit after operation.

The presence of levers with unequal levers, rollers between the bearing surfaces of the levers and the larva, which allow replacing sliding friction with rolling friction when the larva is triggered, reduces the loads in the elements of the retention pin holding mechanism of the holder.

At the same time, the larvae can incorporate spring elements that return and hold the rollers in the initial position after the retention pin retention mechanism has been triggered, which simplifies the installation of the retraction pin when cocking the holder after inspections.

The presence of spherical protrusions of the head of the tightening pin also simplifies the technology for adjusting the holder when tightening the held elements.

The invention is illustrated by drawings, which do not cover and, moreover, do not limit the entire scope of the claims of this technical solution, but are only illustrative materials of a particular case of execution:

Figure 1 is a General view of the proposed holder with retained elements and a safety element from unauthorized disclosure of the pin holding mechanism during technological work, made in the form of a rod;

Figure 2 - section aa in figure 1;

Figure 3 is a General view of the proposed holder in the actuated position of the tightening pin and the holding mechanism;

Figure 4 is a General view of the spring mechanism of separation of the held elements (panel BS) KA;

5 is a General view of the larva with rollers of the movable part of the retention mechanism;

Fig.6 is a section bB in Fig.5.

The holder, in accordance with figure 1, includes a housing 1, a tightening pin 2, which with the help of a nut 5 holds the elements 4.1-4.n (panel BS) in the transport position. The nut 5 is installed in the funnel 7, fixed in the external element 4.n (end panel). In the same funnel, a spring 6 of the tightening pin is installed.

The set of retained elements 4.1-4.n is installed on the supporting surface of the holder 10. In this case, the root panel 4.1 compresses the spring 11 of the separation mechanism of the retained elements 4.1-4.n of the spacecraft from a fixed position on the holder.

For convenience, the rod 9 (Fig. 1) of the safety element against unauthorized opening of the holder mechanism during technological work passes from the rotary base 12 (Fig. 2) located in the holder body through the set of retained elements 4.1-4.n and the funnel 7 ( figure 1) outward, where with the help of a nut 8 is fixed on the end element 4.n from falling out. The holder through the rod 3 connected to the rotary base 12 (figure 2) is connected to the actuating element of the spacecraft control system (not shown).

In the housing 1 (Fig. 1) of the holder, there are controls for locking-unlocking the head of the tightening pin 2 (Fig. 2), consisting of levers 14, larva 17 with rollers 13, springs 16 and a rotary base 12, providing holding and releasing the set of held 4 elements associated with the spacecraft control system. On the surface of the larva 17, a pressing element 18 is fixed, which, after unlocking the head of the tightening pin, presses on the rod of the sensor 19 (Fig. 3). The pressing element 18 has a spring in its composition, which ensures a guaranteed force on the sensor rod during operation.

The procedure for preparing the holder for work.

Prior to the installation of the BS panels pos.4.1-4.n (Fig.2), the pin 2 is installed in the holding mechanism of the clamping pin of the holder, consisting of a fixed part - a holder 26 with unequal arms 14 and a moving part - a larva 17 with rollers 13 and a rotary base 12 holding a larva.

In this case, the tip of the pin pos.2 is inserted into the clip pos.26 along its longitudinal axis in the direction “E” until it stops. By turning the levers 14 in the direction "G" until it touches the spherical surface of the head of the pin 2, in this position the pin is clamped. Holding the tightening pin 2 and the levers 14 and overcoming the force of the springs 16, the larva 17 for the pins 25 (figure 1) moves in the direction of "And" (figure 2). In this case, the second shoulders of the levers 14 abut against the rollers 13 of the larva 17, ensuring that the levers capture the tightening pin 2 by the tip. The rollers 13 of the larva 17 with springs 24 (Fig.6) are held in the lower position of the groove 27.

Holding the larva 17 (figure 2) in this position, the base 12 is rotated until the stops 20 touch the bearings pos.28. This position of the base is fixed by the safety element 9 (figure 1). Next, a set of held elements 4.1-4.n is set (BS panels in the folded position). The funnel 7 (Fig. 1), mounted on the end panel of the BS is a power element of the holder that provides the connection of the pin 2 and the end panel of the BS. When installing the BS panels on the holder, the spring 11 (Fig. 1), located at the junction between the holder body 1 and the root panel, is brought into a compressed position. The spring is made in the form of an annular spring having protrusions 23 (Fig. 4), providing a certain amount of deformation of the spring and the hole 22 for attaching the spring to the holder body. Nut 5 (figure 2) provides fastening of the BS panels in the folded (transport) position.

The order of operation of the holder.

Starting position - rod 9 (figure 1) is removed.

On command from the spacecraft control system (not shown), the flexible rod 3 is released (Fig. 1). Under the action of the springs 29 (Fig. 2), the base 12 is rotated, while the stops 20 of the base 12 slide off the bearings 28 of the larva 17 and, under the action of the springs 16 (Fig. 3), the larva 17 is released downward. In this case, the second shoulders of the levers 14 are rolled along the rollers 13 of the larva 17 within the grooves 27 (Fig.6) and are freed from the restriction of rotation.

Under the action of efforts to tighten the nut 5 and the efforts of the springs 6, the levers 14 of the cage 26 rotate and release the head of the pin 2. The pin 2, under the action of the springs 6, rises upward (Fig. 3) until it contacts the funnel 7 and releases the set of retained elements 4.1-4.n (BS panels) for disclosure.

Together with the larva 17, the spring-loaded element 18 moves, which, at the end of its stroke, presses on the rod of the sensor 19, the actuation of which shows the fact of the actuation of the holder.

The mechanism of separation of the retained spacecraft elements from a fixed position on the holder, consisting of a spring in the form of an annular spring 11 (Fig. 1), brings the BS 4.1 root panel out of contact with the holder body by a value B (Fig. 3) equal to the size of the protrusions 23 (Fig. 4) springs, thereby increasing the reliability of the disclosure of the BS panels.

The claimed device passed the full amount of ground testing and flight tests to hold the solar panels in real conditions of transporting the spacecraft to the range, putting the spacecraft into orbit, separating the solar panels from the holder’s body on command from the spacecraft control unit with subsequent disclosure. The claimed device provides reliable transmission of information about the operation of the holder pin retaining mechanism, improves the structural design of the device due to the presence of a safety element from unauthorized opening of the holder pin retaining mechanism during technological work, contact stresses in the elements of the holder pin retaining mechanism are reduced. The tip of the pin with spherical protrusions eliminates the loading of the pin by the moment of forces while compensating for the movement of the pin from technological errors in the manufacture of BS panels.

Claims (6)

1. A holder comprising a housing, a tightening pin passing through a set of retained elements in a folded position, connected by the first of its ends to the holder body and connected by a second end to an external held element to lock the held elements, and a retention mechanism for holding the clamping pin of the holder associated with the spacecraft control system and providing release of the set of held elements, characterized in that the holder contains a contact sensor mounted on the fixed part of the holder, and a pressure an element mounted on the surface of the larva and interacting with the sensor rod at the end of the stroke when moving the larva, a safety element against unauthorized actuation of the retention pin retention mechanism by rotating the movable base of the mechanism, and a separation mechanism of the retention elements from fixed position on the holder after releasing, consisting of a spring, while the tightening pin has spherical protrusions in the contact zone the one with levers, and the retention pin retention mechanism includes a clip with unequal levers, each of which rests against the spherical protrusions of the retracting pin head with a smaller shoulder, and rests against the roller, which is part of the retention mechanism larva, with the larger shoulder, while the larva cannot be moved along the axis of the tightening pin before the retention mechanism is activated, is provided by the presence of stops on the rotary base, in which the larva bearings abut, and the movable base together with the stops rotate tsya under the action of the springs on a command to turn from the spacecraft control system. 2. The holder according to claim 1, characterized in that the mechanism for disconnecting the retained spacecraft elements from a fixed position on the holder is made in the form of an annular spring. 3. The holder according to claim 1, characterized in that the rollers that make up the larva, when moving the larva, roll between the supporting surfaces of the lever and larva. 4. The holder according to claim 3, characterized in that the larva incorporates spring elements that return the rollers to their original position after the retention pin retention mechanism has been actuated. 5. The holder according to claim 1, characterized in that the safety element against unauthorized rotation of the base is made in the form of a rod passing through the rotary base and the holder body with fixing the position of the rod on the end holding element, for example, with a union nut. 6. The holder according to claim 1, characterized in that the pressure element interacting with the sensor rod at the end of the stroke when moving the larva is spring loaded.

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