RU125552U1 - ROTATION CENTRIFUGAL SOLAR BATTERY OF SPACE VEHICLE - Google Patents

Abstract

1. The rotation device of the centrifugal solar battery of the spacecraft, containing a solar battery, an electric motor and a thrust, characterized in that the thrust is located in the sleeve and is made sliding ball, has a flange housing with three flanges, in one of which an angular drive gear located on the ball bearing is located meshed with two angled follower gears and connected with an electric motor and overrunning clutch, while one of the angular follower gears is designed to allow split rotation ball bearings, and on the other angled driven gear rotating in the opposite direction, a flywheel mounted on the second flange is mounted, both angled driven gears are mounted on angular contact and thrust ball bearings preloaded by springs. 2. The device according to claim 1, characterized in that the third flange is configured to install a backup electric motor.

Description

The utility model (PM) relates to space technology, in particular, to space energy, namely, to solar panels (SB).

The advantage of ultralight thin-film SBs based on amorphous silicon is that they are structurally simple, cheap to manufacture, and have a low mass per unit of generated power.

The advantage of centrifugal SBs is that SBs are deployed from the stacked (transport) position, maintaining shape in working position and ensuring the surface tension state of the SBs is provided by centrifugal forces, which ensures good power generating properties and large current collection.

A known analogue of a spacecraft (KA) with SB-KA with a film SB based on amorphous silicon using an inflatable tube frame (patent RU No. 2309093, 2006). In this analogue of a spacecraft with a centrifugal SB, the SB is oriented to the sun both with the help of spacecraft orientation engines (i.e., due to fuel consumption), and regardless of the spacecraft’s position due to the operation of the electronic control units of the SB control automatics using two electric motors connected a shaft with a frame on which the SB are located (i.e., due to energy consumption).

In the proposed PM, fuel and electricity consumption for the compensation of the kinetic moment of the rotating structure of the centrifugal SB spacecraft is not required.

In outer space, the operating conditions of electronic products are becoming more complicated. With ionizing radiation from outer space, they work unstably. Irreversible changes in the electrophysical parameters of materials occur due to the destruction of their crystalline structure. In order not to spend fuel for compensating the kinetic moment of the spacecraft (eliminating the rotation of the spacecraft) created by the rotating structure of the centrifugal SB and not to use electronic automation to orient the SB, it is advisable to compensate for the kinetic moment of the rotating structure of the centrifugal SB on the spacecraft by installing on the spacecraft “Rotation devices of centrifugal SB rotation” having a flywheel weighing equal to the sum of the weight of the structural elements of the rotating centrifugal SB, which rotates on the axis of rotation of the center of mass of the SB in the opposite direction rotation of the SB from the same electric motor that rotates the SB.

The closest analogue in terms of the totality of existing features and the achieved result to a utility model is a spacecraft with a film centrifugal SB (patent RU No. 2200115, 2001), which is selected as the prototype for the claimed spacecraft with SB. The identity of the proposed PM with the analogue is that the analogue has a continuous circular structure, which ensures the stress state of the SB surface due to centrifugal forces, and, therefore, good power generating properties and large current collection will be realized. A drawback of a spacecraft with a SB prototype is the introduction of two identical circular SBs rotating in opposite directions to the spacecraft to compensate for the kinetic moment when both SBs are located on opposite sides of the spacecraft on rigid rods. This design, which is very complex and large in volume, may not fit in the spacecraft during transportation. The claimed PM is free from these shortcomings.

The main problem for centrifugal SBs, in addition to maintaining the shape and stress state of the SB surface, is the compensation of the kinetic moment created by the rotating structure of the centrifugal SB.

With a constant rotation of the centrifugal SB structure, in order to overcome the resistance in the elements of electromechanics (overrunning clutch, current collector, bearings, electric drive reducer, etc.), the control system consumes additional energy to stabilize the spacecraft (eliminating its rotation). So, when conducting a space experiment on an American spacecraft with a centrifugal SB for one month, it took about 30 kg of fuel to operate the spacecraft orientation engines. It is known that launching 1 kg of cargo into orbit costs about $ 10,000.

The essence of the utility model lies in the fact that in the rotation device of the SB KA containing SB, the electric motor and traction, the thrust is located in the sleeve, is made sliding ball and has a flange housing with three flanges. In one of the flanges on the ball bearing, an angular drive gear is installed, which is meshed with two angled follower gears and connected with an electric motor and an overrunning clutch. One of the gears of the angled followers is made with the possibility of rotation of the sliding ball rod. A flywheel mounted on the second flange is mounted on another gear driven angular driven in the opposite direction. Both angular driven gears are mounted on spring-loaded angular contact and thrust ball bearings. The third flange is configured to install a backup motor.

The technical result of using the "Rotation device centrifugal SB KA" is:

1. Fuel economy due to compensation of the kinetic moment resulting from the rotation of the SB, with a flywheel rotating in the direction opposite to the direction of rotation of the SB.

2. Reducing weight, energy consumption and simplifying the design of SB.

3. The increase in the active life of spacecraft with SB due to the use of a backup engine.

Figure 1 shows the design of the "Rotation device centrifugal SB SC".

Figure 2 presents the structural diagram of a spacecraft with SB in expanded form. The rotation device of a centrifugal solar SB contains:

1 - connection pipe SB

2 - stop screw

3 - upper brush

4 - sleeve sliding ball thrust

5 - ball screw

6 - balls

7 - bottom brush

8 - angular contact ball bearing

9 - thrust ball bearing

10 - gear angular leading

11 - electric motor

12 - freewheel

13 - an epiploon of a leading gear wheel

14 - a flange of installation of the electric motor

15 - a flywheel installation flange

16 - flywheel

17 - angular contact ball bearings

18 - gear wheel angled driven flywheel

19 - flange backup motor

20 - ball bearing

21 - reserve flange oil seal

22 - angular driven gear SB

23 - spring

24 - flange housing sliding ball thrust

25 - nut

26 - coupling collar

27 - nut-lift

28 - ball bearing drive gear

29 - solar battery in expanded form

30 - sliding ball thrust

31 - the container for the security system when folded

32 - flange housing sliding ball thrust

33 - freewheel

34 - drive gear electric motor

35 - flywheel

36 - spacecraft

37 - standby motor

"The device for rotation of the centrifugal SB KA" consists of a sliding ball rod 30 having a flange housing 24 with three flanges 14, 15 and 19 of figure 1. The rod 30 is located in the sleeve and is a screw mechanism with a rolling pair, which converts the rotation of the screw of the ball pair 5 into the translational movement of the lifting nut 27, which sharply (~ 7-8 times) reduces friction compared to a conventional sliding pair.

A feature of a screw pair (the combination of elements 5 and 27) is that the balls are placed between the nut 27 by the screw 5. This sharply increases the efficiency of the mechanism.

Screw 5 and nut 27 have a special profile thread. Balls 6 roll in grooves, make two turns, run onto the cut-off tooth in nut 27 and are directed into the bypass channel into the nut, and from the bypass channel they enter the working channel again. At the ends of the nut 27 there are upper and lower brushes 3 and 7, respectively, made of felt impregnated with grease for cleaning and lubricating the treadmill of the balls 6.

On the flange 14 of the housing of the sliding ball thrust on the ball bearing 28, an angular drive gear 10 is installed, which is meshed with two angled driven gears and connected to an electric motor 11 and an overrunning clutch 12.

The angled driven gear 18 is mounted on the flange 15 and is connected to the flywheel 16, which has a weight equal to the weight of all structural elements of the rotating SB.

The flange 19 is configured to install a backup motor.

The angular driven gear of the driven flywheel 18, and, consequently, the flywheel 16, will rotate on the axis of rotation of the SB center of mass in the direction opposite to the direction of rotation of the gear of the angular driven SB and, consequently, to the rotation of the SB, which achieves the compensation of the kinetic moment from the rotating structure of the centrifugal SB .

Ball bearings are installed on the angled driven gears 18 and 22, as they are more loaded: angular contact 8 and axial support 9. Flange 19 is used to install a backup electric motor (not shown in the figures), which will be used when the main one stops (malfunctions) electric motor 11, which is necessary to increase the active life of the spacecraft with SB.

When the spacecraft is put into orbit and the fairing is dropped, the sliding ball rod starts to rotate by the electric motor and lifts the SB from the container above the end of the spacecraft’s body, and when the screw ball mechanism is fully extended, it becomes a rod for spinning the SB. As is known from analogues, the role of ejecting and spinning centrifugal SB devices is performed by various structural elements, and in the proposed PM these functions are performed by one sliding ball rod.

Claims (2)

1. The rotation device of the centrifugal solar battery of the spacecraft, containing a solar battery, an electric motor and a thrust, characterized in that the thrust is located in the sleeve and is made sliding ball, has a flange housing with three flanges, in one of which an angular drive gear located on the ball bearing is located meshed with two angled follower gears and connected with an electric motor and overrunning clutch, while one of the angular follower gears is designed to allow split rotation ball thrust, and a flywheel mounted on the second flange is mounted on the other angled driven gear, rotating in the opposite direction, both angled driven gears are mounted on angular contact and thrust ball bearings preloaded by springs. 2. The device according to claim 1, characterized in that the third flange is configured to install a backup electric motor.

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