RU2299840C1 - Device for simulation of weightlessness of sectional collapsible panels of spacecraft solar batteries - Google Patents

Abstract

FIELD: testing low-stiffness multi-member mechanical systems of spacecraft equipment for opening.

SUBSTANCE: proposed device includes sectional collapsible rods secured on horizontal transportation ring mounted in upper part of spacecraft. Rods are located above sectional collapsible panels of solar batteries and are connected with them by means of adjustable weightlessness springs mounted vertically. Secured on ceiling of room (or on separate support) are load-bearing pylons with horizontal shelves; bearing rollers are mounted on rods on side of solar battery panels. Rollers may be engageable with horizontal shelves of pylons when the rods are in the open position. These shelves are provided with inclined receivers for rollers; spring-loaded permanent magnets are secured on pylons. Magnets may be engageable with plates made from magnetic material. These plates are secured on sectional collapsible rods.

EFFECT: improved service characteristics of device due to reduced loads on panel opening drives in testing them for functioning.

4 dwg

Description

The present invention relates to devices for testing the functioning of multi-link low-rigid mechanical systems of space technology products, and more particularly, to devices for weightless sectional folding solar panels of a spacecraft.

A device for weighting sectional folding solar panels of a spacecraft is made in the form of a stationary support with pivoting arms connected by springs to the solar panels of a spacecraft located on a technological stand (see Product 11F654. Assembly (disassembly), 11F654. IE14, edition 1, 2001, Design Bureau "Flight", l. 53).

Also known is a device for weightless sectional folding solar panels of a spacecraft, comprising mounted on a transportation ring horizontally mounted in the upper part of the spacecraft, sectional folding rods located in plan above the corresponding sections of folding solar panels and associated with them through vertically mounted detachable latches and adjustable weightless springs. When the sections of the folding solar panels of the spacecraft are opened, the sectional folding rods of the transportation ring are opened synchronously with them, taking the load from the weight of the sectional folding solar panels of the spacecraft. Thus, the unloading (reduction of the existing efforts) of the drives for opening the sectional folding solar panel panels occurs (see UDC. 355.02. "Development of the military-industrial complex at the present stage", materials of the scientific and technical conference (Omsk, June 4-6, 2003 .), part 2. Omsk, publishing house of Omsk State University, 2003, pp. 135-140).

The disadvantage of this device for weightless sectional folding solar panels of the spacecraft is that with a sequential console layout of the disclosure of the sections of folding solar panels of the spacecraft (which is used in most designs of existing and planned spacecraft), when they are tested for functioning under laboratory conditions, deflections ( deformations of the elements of the disclosed system) “accumulate” from the root (the least distant from the spacecraft’s body a) to the end (farthest from the spacecraft body) sections of the folding solar panels of the spacecraft. Therefore, to exclude unacceptable deflections of sectional folding rods in the open position, the latter should have great rigidity. An increase in the rigidity of sectional folding rods leads to a significant increase in their mass. And since the sectional folding rods are part of the transport ring fixed directly to the spacecraft, the “pressing” load acting on the spacecraft increases accordingly. This leads to the need to strengthen the power structure of the spacecraft, to increase the mass of the spacecraft structure and, ultimately, to losses in the energy sector when the spacecraft is put into orbit and the launch cost increases. Failure to take measures to increase the stiffness of sectional folding rods leads to an increase in the acting loads on the drives during the opening of the sections of the folding solar panels, to an unjustified increase in the power of the opening drives of the sections of the folding solar panels of the spacecraft, and in some cases (with insufficient power of the drives for opening the sections folding solar panels) even to mechanical damage to elements of the spacecraft (opening drives, locking locks, hinges, panels th solar, etc.).

The objective (goal) of the present invention is to increase operational characteristics (reducing the load on the disclosure drives of the sectional folding solar panels of the spacecraft) devices for weighting the sectional folding solar panels of the spacecraft.

The task (goal) is achieved by the fact that in the proposed device for weightless sectional folding solar panels of the spacecraft, comprising mounted on a transportation ring horizontally mounted in the upper part of the spacecraft, sectional folding rods located in plan above the sectional folding solar panels and associated with them by means of vertically mounted detachable latches and adjustable weightless springs, it is proposed on the ceiling of the room fasten the supporting pylons with horizontal shelves, and install support rollers on the sectional folding bars from the side of the sections of the folding solar panels with the possibility of their interaction with the open position of the sectional folding bars with horizontal shelves of the supporting pylons, while the horizontal shelves are equipped with inclined receivers, and on the supporting pylons spring-loaded permanent magnets are fixed, installed with the possibility of their interaction with the strips made of magnetic material and fixed emymi at sectional folding bars.

The interaction of the support rollers of the sectional folding rods with the horizontal shelves of the bearing pylons and the sections of the sectional folding rods with spring-loaded permanent magnets mounted on the bearing pylons allows you to create a system with intermediate supports. The disclosure of each of the subsequent sections of the sectional folding rods with weightless solar panels is carried out on the fixed (from the deflection) previous sections of the sectional folding rods, which significantly reduces the load on the opening and deflection drives in the process of opening (distortions, deformation, movement) of the subsequent sections of the sectional folding rods and associated by means of adjustable springs of weightlessness of subsequent sections of sectional folding solar panels. The loads on the disclosure drives and deflections in the proposed weightless device will be significantly less than the loads on the disclosure drives and deflections arising in the weightless device with a cantilever disclosure scheme adopted as a prototype.

At the same time, the smoothness and impactlessness of the interaction of the support rollers of the sectional folding rods with the horizontal shelves of the supporting pylons (at the end of the opening of each section of the sectional folding solar panels) is ensured by securing the inclined (profiled) receivers to the horizontal shelves of the supporting pylons and the spring-loaded permanent magnets holding the sectional folding rods from reverse bounce.

The proposed device is illustrated in figures 1-4.

Figure 1 presents a General view of the device in the operating position.

Figure 2 shows a section aa according to figure 1.

Figure 3 shows the relative position of the elements of the device when finding the support rollers on the inclined receivers of the bearing pylons.

Figure 4 presents the position of the elements of the device when retracting the slats of the sectional folding rods from the spring-loaded permanent magnets of the bearing pylons.

The proposed device contains sectional folding rods 1 (1), mounted on a transport ring 2, horizontally mounted in the upper part of the spacecraft 3. Sections 4 of the sectional folding rods 1 are located in plan above the corresponding sections 5 of the sectional folding solar panels 6 of the spacecraft 3 and are connected with them by means of vertically mounted detachable latches (not shown conventionally in Fig.) and adjustable weightless springs 7. At the same time, supporting saws are fixed on the ceiling 8 of the room 9 us with horizontal flanges 10 (Figure 2). The mounting of the supporting pylons 9 can be carried out to the wall of the room or to a specially installed support on the floor of the room. On the collapsible folding rods 1 from the side of the collapsible folding solar panels 6 of the spacecraft 3, support rollers 11 are installed (FIG. 2) with the possibility of their interaction (FIG. 2) when the folding collapsible rods 1 with the horizontal shelves 10 of the bearing pylons are open 9. Horizontal shelves 10 are equipped with inclined receivers 12 (figure 2). On the supporting pylons 9 are fixed spring-loaded permanent magnets 13 (figure 2), installed with the possibility of their interaction with the strips 14 made of magnetic material and mounted on sectional folding rods 1 from the side of the spring-loaded permanent magnets 13.

The proposed device operates as follows.

The spacecraft 3 by a crane (not shown conventionally in Fig.) Is installed on a technological stand 15 (Fig. 1), pre-installed (by marking) on the floor of the room. Dismantle clamps (not shown conditionally in FIG.) Of adjustable weightless springs are dismantled 7. Clamps are dismantled (not shown conventionally in FIG.) Of the position of the sections 5 of the sectional folding solar panels 6 of the spacecraft 3 and the latches (not shown conventionally in FIG.) Of the position of sections of 4 sectional folding bars 1 of the transport ring 2. After actuation of the opening drives (not shown conventionally in FIG.) of the spacecraft 3, the sections 5 of sectional folding panels are sequentially opened (rotated) solar panels 6 of the spacecraft 3, together with the opening (rotation) of the sections 4 of the sectional folding rods 1 of the transport ring 2, interconnected by adjustable weightless springs 7. In this case, the support rollers 11 (at the final section of the opening of section 4) interact first (Fig. 3 ) with inclined receivers 12, and then (figure 2) and with horizontal shelves 10 of the bearing pylons 9, mounted on the ceiling 8 of the room. The cantilever deflection of the sections 4 of the sectional folding rods 1 with 7 sections 5 of the folding solar panels 6 suspended on them on adjustable weighting springs, which is formed after the sections 4 are unlocked from the transportation ring 2 of the spacecraft 3, is compensated by their corresponding rise (sections 4), which occurs when the movement of the support rollers 11 sections 4 along the inclined receivers 12 horizontal shelves 10 of the bearing pylons 9. (The lifting height of the sections 4 along the inclined receivers 12 horizontal shelves 10 of the bearing pylons 9 is set equal to the amount of deflection determined (calculated) on the cantilever sections Scheme 5 disclosure sectional foldable solar panels of a spacecraft 6, 3). Thus, the next disclosed section 4, associated with the corresponding section 5, will have less deflection (the "pressing" load from the previous sections 4 and 5 will be "turned off" by supporting the support rollers 11 of the previous sections 4 on the horizontal shelves 10 of the bearing pylons 9). With further movement of the sections 4 (supporting rollers 11 along the horizontal shelves 10), the planks 14 made of magnetic material and fixed on the sections 4 of the sectional folding rods 1 will come into contact (Fig. 2) with spring-loaded permanent magnets 13, mounted on bearing pylons 9 s using springs 16 (figure 2). In this case, the springs 16 during their compression quench the collision speed and reduce shock loads during the interaction of sections 4 with spring-loaded permanent magnets 13, thereby eliminating the possibility of "rebound" of sections 4 from bearing pylons 9 and contributing to the "sticking" of the straps 14 (sections 4) to the spring-loaded permanent magnets 13 (bearing pylons 9).

It should be noted that the required number of bearing pylons 9, depending on the rigidity of the disclosed structure, can be different - not each section 4 can be “supported” on the supporting pylons 9, but only some (for example, every second, etc.).

After the tests, sections 4 and 5 are folded (in the reverse order) in manual mode. Moreover, to "detach" the strips 14 (sections 4) from the spring-loaded permanent magnets 13 (carrier pylons 9), use the adjustable stops 17 (Fig. 4), mounted on sections 4, screwing them all the way into the carrier pylons 9 allows the strips 14 to be separated from spring-loaded permanent magnets 13 with the fixed springs 16 (spring retainers 16 are not shown conventionally in FIG.) and thereby take sections 4 away from the carrier pylons 9. After folding sections 4, the adjustable stops 17 are returned to their original position (or dismantled).

Thus, the proposed device has significant differences from previously known devices for weightless sectional folding solar panels of the spacecraft and can improve their performance (reduce the load on the opening drives of the sectional folding solar panels of the spacecraft when they are checked for operation).

Claims (1)

A device for weighting sectional folding solar panels of a spacecraft, comprising mounted on a transportation ring horizontally mounted in the upper part of the spacecraft, sectional folding rods arranged in plan above the corresponding sections of folding solar panels and connected by vertically mounted detachable latches and adjustable weightless springs, characterized in that on the ceiling of the room are fixed bearing pylons with horizontally support shelves, and on the sectional folding rods from the side of the sectional folding solar panels, support rollers are installed with the possibility of their interaction with the open position of the sectional folding rods with horizontal shelves of the bearing pylons, while the horizontal shelves are equipped with inclined receivers of the supporting rollers, and spring-loaded on the supporting pylons permanent magnets installed with the possibility of their interaction with strips made of magnetic material and mounted on sectional folding x bars.

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