RU211841U1 - MECHANICAL DEVICE OF A SOLAR SPACE VEHICLE BATTERY - Google Patents

Abstract

The utility model relates to space technology, namely to solar battery designs, and can be used in spacecraft (SC) energy-saving systems. The technical problem to be solved by the claimed utility model is: reduced controllability of the spacecraft, insufficient reliability and complexity of opening the mechanical devices of the solar battery. The technical problem posed is solved by the fact that the mechanical device of the solar spacecraft battery contains two harmonically folded panels connected to each other by means of swivel joints equipped with drive springs that open them. The first panel is connected to the spacecraft by means of swivel joints provided with drive springs. The beginning of the opening of the second panel is determined by the device releasing it at the moment of opening the first panel. The device that determines the opening order of the panel can be made in the form of a hook engaged with this panel. The technical result of the utility model is to increase the compactness of the design of the mechanical device of the solar battery, due to the closest center of mass to the body of the spacecraft.

Description

The utility model relates to space technology, namely to the construction of solar batteries and can be used in the creation of a spacecraft (SC).

From the existing prior art, a mechanical device of a solar battery is known, described in the invention "Device for containment and determining the deployment order" (patent US 6010096A, B64G 1/44), containing a harmonically folded frame and three panels connected to each other and through the frame with the spacecraft by means of swivel joints equipped with drive springs that open them. The articulated joints are connected in series by a cable transmission with pulleys installed in these articulated joints, which ensures the synchronous opening of the frame and panels into the operating position relative to the spacecraft. At the same time, side panels are attached to the side edges of the second panel by means of hinged joints provided with drive springs that open them. The opening of the side panels is determined by the device that releases them at the moment the second panel is opened.

The disadvantage of the device described above is that, provided that the first panel is not shaded by the elements of the spacecraft, the distance between the center of mass of the mechanical devices of the solar battery and the center of mass of the spacecraft is determined by the location of the second panel, with side panels installed on it, relative to the spacecraft at a distance of a minimum, but sufficient for their non-shadowing. Thus, everything that is located after the second panel leads to an increase in the distance between the center of mass of the mechanical device and the center of mass of the spacecraft. As a result, by increasing the distance between the center of mass of the mechanical device of the solar array and the center of mass of the spacecraft, the value of the necessary control moments of the spacecraft increases, which leads to a decrease in the efficiency of its control.

From the existing level of technology known mechanical battery of a solar spacecraft, described in the invention "Solar battery spacecraft" (patent RU No. 2619158C1, B64G 1/44). The solar battery contains panels and a frame. The spacecraft, frame and panels are interconnected by means of articulated joints. All swivel joints are connected in series by a cable transmission with pulleys. For reusable transfer of the solar battery to the open and folded position, an engine is installed in one of the swivel joints. Each swivel includes drive springs to fully open or fold the solar array.

From the existing level of technology known mechanical device battery solar spacecraft described in the invention "Solar Battery" (patent RU No. 2258640 C1, B64G 1/44). The solar battery contains a harmonically folded triangular frame and panels connected to each other and through the frame with the spacecraft by means of hinged joints installed along the edges of the panels. All articulated joints are connected in series by a cable transmission with pulleys installed in the articulated joints, which ensures synchronous opening of the frame and panels into the working position relative to the spacecraft. The opening occurs due to the drive springs installed in all swivel joints, and the engine. The engine is installed in a swivel joint between the spacecraft and the frame and determines the deployment speed.

From the existing state of the art, the closest to the claimed solution (prototype) is the invention "Mechanical solar battery device" (patent RU No. 196176 U1, B64G 1/44), containing a harmonically folded frame and panels connected to each other and through the frame with the spacecraft by means of swivel joints equipped with drive springs that open them. Articulations between the spacecraft and the frame, as well as between the frame and the first panel, are connected by a cable transmission with pulleys installed in these articulated joints, which ensures synchronous opening of the frame and the first panel, at a speed determined by the engine installed in the articulated connection between the frame and the first panel. In this case, the order of opening each next panel is determined by the device that releases it at the moment of opening each previous panel. The device that determines the opening order of the panel can be made in the form of a hook engaged with this panel.

The disadvantage of the arrangement of the device described above is that, provided that the first panel is located relative to the spacecraft at a minimum distance, but sufficient for it not to be shaded by the elements of the spacecraft, the distance between the center of mass of the mechanical device of the solar battery and the center of mass of the spacecraft is determined by the number of successively arranged panels. Thus, with an increase in the number of panels to provide a given power of a solar battery, the distance between the center of mass of the mechanical device and the center of mass of the spacecraft will increase. As a result, by increasing the distance between the center of mass of the mechanical device of the solar battery and the center of mass of the spacecraft, the value of the necessary control moments of the spacecraft increases, which leads to a decrease in the efficiency of its control.

For the claimed utility model, the following common essential features have been identified: a mechanical device for a solar spacecraft battery, containing harmonically folded panels connected to each other by means of swivel joints, equipped with drive springs that open them.

The technical problem to be solved by the claimed utility model is the irrational layout of the mechanical device of the solar battery, leading to a decrease in the functionality of the spacecraft.

The technical problem posed is solved by the fact that the mechanical device of the solar spacecraft battery contains two harmonically folded panels connected to each other by means of swivel joints equipped with drive springs that open them. The first panel is connected to the spacecraft by means of swivel joints provided with drive springs. The beginning of the opening of the second panel is determined by the device releasing it at the moment of opening the first panel. The device that determines the opening order of the panel can be made in the form of a hook engaged with this panel.

In FIG. 1 shows the mechanical device of the solar battery in the folded position.

In FIG. 2 shows the mechanical device of the solar battery in the open position.

In FIG. 3 view A of Fig. 2.

In FIG. 4 shows a device that determines the beginning of the opening of the panels of the mechanical device of the solar battery.

In FIG. 5 shows the process of opening the mechanical device of a solar battery.

The mechanical device of the solar battery (MU BS) 1 of the spacecraft 2 contains harmonically folded panels 3 and 4, interconnected by means of a swivel 5, equipped with drive springs 9 (for example, clock-type springs) that open them. The panel 3 is connected to the spacecraft 2 by means of swivel joints 6 provided with drive springs 9 that open them. The beginning of the opening of the panel 4 is determined by the device (for example, a hook 12 hooked onto the panel 4) installed in the swivel joint 6. The joint ball contains a bracket 7 on which the hook 10 is installed and the bracket 11 with the axle 11 installed. drive springs 9, the hook 10 goes beyond the axis 11 and fixes the swivel in the open position.

The described mechanical device is able to provide the most efficient control of the spacecraft, due to the displacement of the panels close to the device, thereby providing a minimum but sufficient distance Z between the center of mass of the mechanical device of the solar battery C.M.1 and the center of mass of the spacecraft C.M.

The mechanical device of a solar battery works as follows:

First stage of disclosure. After the release of the panels 3, 4 folded on the body of the spacecraft 2, the panel 3 opens. The panel 4 is held by the hook 12, hooked to this panel and installed in the swivel joint 6.

The second stage of disclosure. After the panel 3 is opened (from position I to position II), the bracket 13 (in the swivel joint 6), with the stop 14 installed on it, abuts against the protrusion 15 of the hook 12 and rotates it around the axis 16, releasing the axis 17 of the panel 4. The panel 4 opens under action of drive springs 6 in direction B.

The technical result of the utility model is to increase the compactness of the design of the mechanical device of the solar battery, which, in turn, increases the functionality, due to the closest center of mass to the body of the spacecraft.
Fig. 9

Claims (2)

1. The mechanical device of the battery of a solar spacecraft, containing two harmonically folded panels connected to each other by means of swivel joints equipped with drive springs that open them, characterized in that the first panel is connected directly to the spacecraft by means of swivel joints equipped with drive springs, the beginning of disclosure of the second panel is determined by the device that releases it at the moment of opening the first panel. 2. The mechanical device of the solar spacecraft battery according to claim 1, characterized in that the device that determines the opening order of the panel can be made in the form of a hook engaged with this panel.

Images