RU2376212C1 - Space platform - Google Patents

Abstract

FIELD: aerospace engineering.

SUBSTANCE: proposed platform comprises parallelepiped-shaped carcass with top (3) and bottom panels mounted thereon. Said carcass supports solar batteries hinged thereto and comprising root (7) and end (8) sections. Top panel (3) accommodates gravitation device bar (9). Intermediate panel divides in-carcass space into service system and useful load (UL) compartments. Orientation and stabilisation system electromagnetic components are attached to aforesaid bottom panel on carcass side. Magnetometer (15) is fastened onto top panel (3). Side panels are hinged to carcass and furnished with UL attachments arranged inside UL compartment. Solar battery hinges are arranged on the side of lateral panels. Root (7) and end (8) sections incorporate limiters of their mutual turn through angle not exceeding 270°. Total length of two pairs of root and end sections exceeds total length of carcass face ribs arranged on the side of lateral panels. Thin-film photo devices are glued to lateral panel that incorporates attachments for carcass to be jointed to separation system. Height of root (7) and end (8) sections does not exceed that of service system compartment. Lateral panels comprise rotary fragments (21) arranged in UL compartment zone and furnished with opening drives.

EFFECT: continuous onboard chemical battery recharging, reduced weight and higher accuracy of measurements.

4 cl, 6 dwg

Description

The invention relates to products of space technology, and more particularly to space platforms, and can be used to create spacecraft for various purposes.

The development of space technology at the present stage is characterized by the creation of spacecraft for various purposes on the basis of unified space platforms, which allows to reduce the cost of the development and manufacture of spacecraft and to reduce the time for their creation.

The space platform is a supporting structure equipped with utility systems and equipped with devices for placing on it a payload for various purposes. Service systems are systems common to spacecraft for various purposes, namely: power supply system, orientation and stabilization system, on-board control system, propulsion system, etc. The payload is instruments and devices that provide the solution of the target tasks of a particular spacecraft, namely: optical, radar, telecommunication equipment, etc. The bearing capacity of a space platform refers to the mass and volume of the payload that can be installed on the space platform. In practice, the bearing capacity of modern space platforms reaches 100%, i.e. the mass and volume of the space platform are approximately equal to the mass and volume of the payload placed on the space platform.

A space-free platform platform is known, comprising a flat (supporting) panel, on one side of which separate service system modules are installed, including an instrument module, an electric power supply system module and a propulsion system module, and on the other hand, fasteners for the target payload module and individual target instruments (see, for example, “Cosmonautics News” No. 4, April 2007, p. 38).

The disadvantages of this space platform are

- the difficulty of fixing and damping the space platform and the spacecraft created on its basis during ground operation (transportation in a shipping container, installation on technological supports, tilters, rigging operations) and in flight as part of a launch vehicle (increased weight of the adapter (transition devices between the space platform and the launch vehicle) associated with the need to place support and lifting elements exclusively on a flat (carrier) panel, on both sides of which swarm installed separate modules;

- difficult access for maintenance personnel to the service system modules during ground training, due to the installation of the space platform with a flat (carrier) panel on the support racks of the ground equipment units;

- oversize (increase) of the mass of the actual design of the space platform due to the placement of service systems in separate modules attached to a common flat (carrier) panel.

There is also known a space platform containing a frame made in the form of a parallelepiped, with side, top and bottom panels mounted on the frame, solar panels pivotally mounted on the frame, containing root and end sections, service systems devices mounted on the frame and placed inside the frame, with a bar a gravity device installed outside the frame on the top panel, fasteners of the module of the payload of the frame structure, nodes connecting the frame to the separation system, eplennymi on the bottom and one of the side boards (see., eg, "News of Cosmonautics» №7, July 2005, p.48). This space platform is actually a supporting service module designed to install a payload module on it.

At the same time, the disadvantages of this space platform are

- oversize (increase in mass) of the spacecraft created on the basis of this space platform, in view of the execution of its supporting structure according to the principle of individual modules;

- the influence of the magnetic field generated by the electromagnetic devices of the orientation and stabilization system on the readings of the magnetometer (due to the fact that these devices are part of the service systems and are located in the service module), leading to a distortion of the measurement results;

- recharge of onboard chemical batteries in the utility power system from solar panels is not constant and depends on the orientation of the solar panels to the Sun;

- an increase in the mass of the space platform due to the need to install radiation and thermal protection devices for service system devices on it;

- placement of the payload devices in the payload module of the frame structure does not protect them from radiation exposure (passage of the Earth’s radiation belts, solar flares), and in some cases the required temperature mode of operation.

The objective (goal) of the present invention is to expand the functionality (recharging on-board chemical batteries from solar panels when the space platform is oriented to the Sun by any side panel, thermal and radiation protection of payload devices) and improving operational characteristics (reducing the mass of the space platform structure, reducing the influence of magnetic the field created by the electromagnetic devices of the orientation and stabilization system, to the readings of the magnetometer) of the space platform we.

The goal in the proposed device is achieved by the fact that the frame space is divided by an intermediate panel placed between the lower and upper panels and fixed on the frame, respectively, to the service system compartment and the payload compartment, and the electromagnetic devices of the orientation and stabilization system installed in the service system compartment are fixed to bottom panel on the side of the frame. The magnetometer is mounted on the top panel outside the frame. The side panels are connected to the frame by means of hinges and are provided with fastening elements of the payload fastened to them from the frame inside the payload compartment. The hinges of rotation of the root sections of solar panels are placed on the frame from the side of the side panels that do not contain nodes connecting the frame with the separation system. The root and end sections of solar cells are equipped with limiters for their mutual rotation by an angle not exceeding 270 °, and the total length of two pairs of root and end sections of solar cells in the projection on a horizontal plane exceeds the total length of the end edges of the frame located on the side of the side panels that do not contain nodes connecting the frame with the separation system. Thin-film photoconverters are glued to the side panel containing the connection nodes of the frame with the separation system. The height of the root and end sections of solar panels does not exceed the height of the compartment service systems. Side panels contain rotary fragments installed in the area of the payload compartment and equipped with opening drives. Side panels are detachable and consisting of two sections, while the connector lines pass through the intermediate panel.

The proposed device is illustrated in figures 1-6.

Figure 1 shows a General view of the proposed space platform in the inoperative (transport) position.

Figure 2 presents a view And according to figure 1.

Figure 3 shows a view B according to figure 1 (when the solar panels are in the working position).

Figure 4 shows a three-dimensional model of the proposed space platform before installing a payload on it.

Figure 5 presents a three-dimensional model of the proposed space platform after installing a payload on it.

Figure 6 shows a three-dimensional model of a spacecraft based on the proposed space platform in the working position (in orbit of the Earth).

The proposed device (space platform) contains the frame 1 (figure 1), made in the form of a parallelepiped, with side panels 2 installed on the frame 1, top 3 and bottom 4 panels. On the frame 1 by means of hinges 5 installed solar panels 6 containing the root 7 (figure 3, 6) and the end 8 sections. Outside the frame 1, on the upper panel 3, a rod of a gravity device 9 is installed (Fig. 1). On the frame 1 from the side of the lower 4 and one of the side panels 2 are fixed (fasteners not shown conventionally) nodes 10 (frame 1) with the separation system (not shown conventionally). The intraframe space is divided by an intermediate panel 11 (Figs. 4, 5), located between the lower 4 and upper 3 panels and fixed (fasteners are not shown conventionally) on the frame 1, respectively, to the service system compartment 12 (Fig. 2) and the payload compartment 13 (Figs. 4, 5). The volume of the compartment of the service systems 12 is taken to be approximately equal to the volume of the compartment of the payload 13. The electromagnetic devices of the orientation and stabilization system 14 installed in the compartment of the service systems 12 (Fig. 2) are fixed (fasteners are not shown conventionally) on the bottom panel 4 from the side of the frame 1 The magnetometer 15 (Figs. 1, 4) is fixed (fasteners are not shown conditionally) on the upper panel 3 outside the frame 1. The side panels 2 are connected to the frame 1 by means of hinges 16 (Fig. 1) and are provided with frames mounted on them from the frame 1 side inside from ESA payload 13 of the payload of fastening elements 17 (Figure 4). The hinges 5 of the rotation of the root sections 7 of the solar panels 6 are placed on the frame 1 from the side of the side panels 2 that do not contain connection nodes 10 of the frame 1 with the separation system (not shown conditionally). The root 7 and end 8 sections of the solar panels 6 are equipped with limiters for their mutual rotation 18 (Fig.3) at an angle not exceeding 270 °. The total length of two pairs of root 7 and end 8 sections of solar cells 6 in the projection on a horizontal plane exceeds the total length of the end ribs 19 (Fig. 2) of the frame 1, placed on the side of the side panels 2, not containing nodes 10 of the frame 1 with the separation system ( conditionally not shown). Thin-film photoconverters 20 are glued to the side panel 2 containing the connection nodes 10 of the frame 1 with the separation system (not shown conventionally), (FIGS. 1, 4). The height of the root 7 and end 8 sections of the solar panels 6 does not exceed the height of the compartment of the service systems 12. The side panels 2 contain rotary fragments 21 (FIGS. 1, 6) installed in the area of the payload compartment 13 and equipped with disclosure drives 22 (FIG. 4, 5). The side panels 2 are made detachable, consisting of two sections 23 (Fig. 1) and 24, while the connector lines pass through the intermediate panel 11.

The assembly of the space platform at the factory is carried out with the vertical position of the frame 1 in the following technological sequence.

The side panels 2 are detached (fasteners not shown conventionally) from the frame 1 and rotated on hinges 16. Elements of service systems (not shown conventionally) are installed in the compartment of the service systems 12 and are attached to the frame 1. At the same time, the electromagnetic devices of the orientation and stabilization system 14 are fixed (fasteners are not conventionally shown) on the lower panel 4 from the side of the frame 1, and the magnetometer 15 is fixed (fasteners are not conventionally shown) on the upper panel 3 outside the frame 1. Then the side panels 2 are closed and fastened (Retention components are not shown) to the frame 1. Thereafter installed solar battery 6. Thus, the prepared space platform (1, 2) in an equipment payload.

The payload equipment of the spacecraft created on the basis of the proposed space platform is carried out either at the manufacturer of the space platform or at the manufacturer of the payload.

In this case, the latches 25 (Fig. 1) and sections 23 of the side panels 2, covering the payload compartment 13, are dismantled, rotated (Fig. 4) on hinges 16. Then, devices 26 (Figs. 5, 6) are installed on the rotary fragments 21 the payload of the spacecraft and are attached to them by means of fastening elements of the payload 17. After this, the sections 23 are translated into the initial position and fastened (fasteners are not shown conventionally) to the frame 1. It is also possible to install individual elements (not shown) of the payload on the side exit panels 2 outside the pivoting fragments 21 or outside the frame 1 on the top panel 3, or inside the frame 1 with a fastener (fasteners not shown conventionally) directly to the frame 1. In some cases, when ground preparation, it is advisable to simultaneously open sections 23 and 24 of the side panels 2 (performed with latches 25 installed).

After putting into operation the functioning of the spacecraft, created on the basis of the proposed space platform, the space platform is oriented in space and the root 7 and end 8 sections of the solar panels 6 are opened.

Orientation is provided by extending (6) the rod of the gravity device 9.

Unfixing (fixing elements not conventionally shown) of two pairs of root 7 and end 8 sections of solar panels 6 and their disclosure using electric drives (not conventionally shown) are performed. Mutual disclosure of the root 7 and end 8 sections of the solar panels 6 is carried out at an angle not exceeding 270 °, which is ensured by the installation of rotation limiters 18 on the root 7 and end 8 sections. In this case, two pairs of root 7 and 8 end sections cover (Fig. 3, 6) “box” side panels 2 (space platform) that do not contain connection nodes 10 (frame 1 with the separation system). This coverage is ensured by the fact that the total length of two pairs of root 7 and end 8 sections of solar panels 6 in the projection on a horizontal plane exceeds the total length of the end ribs 19 of the frame 1 located on the side of the side panels 2 that do not contain connection nodes 10 (frame 1 with the system separation), and the choice of an appropriate angle of rotation of the root 7 sections relative to the frame 1. Given the installation on the side panel 2 containing the connection nodes 10 (frame 1 with the separation system), thin-film photoconverters 20 provide full coverage of the space platform (in the area of the service systems compartment 12) from the side of the side panels 2 by solar panels 6 and thin-film photoconverters 20. Thus, at any angular position (regardless of orientation to the Sun) of the space platform relative to its longitudinal axis, a constant charge will be provided on-board chemical batteries (not shown conditionally) of the utility system for powering the space platform from solar panels 6 and thin-film photoconverters 20.

Then, the payload is prepared for work and transferred to its working position. To do this, using the drives of the opening 22, the rotary fragments 21 mounted on the side panels 2 (in the area of the payload compartment 13) are deployed on hinges 27 (Fig. 6) by the devices 26 that are part of the payload outward (frame 1). During the passage of radiation belts, or in the presence of flares on the Sun, or an unacceptable thermal effect with the help of disclosure drives 22, the rotary fragments 21 mounted on the side panels 2 (in the area of the payload compartment 13) are deployed (on hinges 27) with the instruments 26 included payload, into the carcass 1. When these factors cease to exist, the payload is again transferred to the working position.

Using the proposed device due to the installation of thin-film photoconverters 20 on one of the side panels 2 and the disclosure of the root 7 and end 8 sections of solar panels 6 with coverage of the remaining side panels 2 allows for constant recharging of on-board chemical batteries (not shown conditionally) of the power supply system of the space platform from solar panels 6 and thin-film photoconverters 20, regardless of the orientation of the space platform 6 on the Sun. This provides the possibility of uniform energy consumption of the payload, which extends the resource of its work and increases the amount of information taken. In addition, the disclosure of the root 7 and end 8 sections of solar panels 6 of the proposed space platform “box”, in some cases, is a measure of radiation and thermal protection (primarily the compartment service systems 12).

The calculations showed that the placement of the payload in one frame with service systems can reduce the mass of the supporting structure of the spacecraft created on the basis of the proposed space platform by 15-20%.

Installing a magnetometer on the upper panel outside the frame allows, by placing the magnetometer at the maximum possible distance from the electromagnetic devices of the orientation and stabilization system, to reduce the influence of the magnetic field created by the electromagnetic devices of the orientation and stabilization system on the magnetometer readings. Moreover, given that the magnetic field level is inversely proportional to the cube of the distance between interacting objects, at the same height of the payload compartment and the service system compartment, the influence of the magnetic field generated by the electromagnetic devices of the orientation and stabilization system on the magnetometer readings will decrease by eight times. This will increase the reliability of the information taken from the magnetometer, and will allow for a more accurate orientation of the space platform to the Earth.

The installation of the payload on the rotary fragments, pivotally mounted on the side panels and equipped with disclosure drives, provides protection of the entire payload from radiation exposure when passing by a spacecraft created on the basis of the proposed space platform, radiation belts of the Earth or during solar flares, and in some cases and the required temperature mode of operation.

Moreover, as the calculations showed, the proposed technical solution allows to reduce by 20-30%, compared with the prototype, the mass of radiation and thermal protection devices of the payload.

It should also be noted that the placement of the payload of the spacecraft created on the basis of the proposed space platform in one structural array (frame) with service systems while actually maintaining the principle of modularity of the compartments allows for compact placement of the payload in its idle position (during ground operation, launch into orbit of functioning). This significantly reduces the required dimensions of the cargo spaces of vehicles used in transportation, and the amount of runoff space of the launch vehicle used as a means of launching into orbit. In addition, the placement of the payload in its idle position inside the frame with the closed position of the side panels eliminates mechanical damage to the payload during the ground operation of the spacecraft created on the basis of the proposed space platform.

Thus, the proposed device has significant differences and allows you to expand the functionality and improve the operational characteristics of known space platforms.

Claims (4)

1. A space platform containing a frame made in the form of a parallelepiped, with side, top and bottom panels mounted on it, solar panels pivotally mounted on the frame, containing root and end sections, service system devices mounted on the frame and placed inside the frame, a bar a gravity device installed outside the frame on the upper panel, payload fastening elements, frame connection nodes with the separation system, mounted on the bottom and one of the side panels it, characterized in that the internal frame space is divided by an intermediate panel located between the lower and upper panels and mounted on the frame, respectively, to the service system compartment and the payload compartment, and the electromagnetic devices of the orientation and stabilization system installed in the service system compartment are mounted on the lower panel with side of the frame, while the magnetometer is mounted on the upper panel outside the frame, and the side panels are connected to the frame by means of hinges and are provided with the carcass torons inside the payload compartment by the payload fastening elements, and the hinges of rotation of the root sections of the solar panels are placed on the frame from the side of the side panels that do not contain the connection nodes of the frame with the separation system, while the root and end sections of the solar panels are equipped with limiters for their mutual rotation not exceeding 270 °, and the total length of two pairs of root and end sections of solar cells in the projection on a horizontal plane exceeds the total length of the end edges of the frame placed on the side of the side panels that do not contain nodes connecting the frame with the separation system. 2. The space platform according to claim 1, characterized in that thin-film photoconverters are glued to the side panel containing the connection nodes of the frame with the separation system. 3. The space platform according to claim 1 or 2, characterized in that the height of the root and end sections of the solar panels does not exceed the height of the compartment of service systems, and the side panels contain rotary fragments installed in the area of the payload compartment and equipped with disclosure drives. 4. The space platform according to claim 1, characterized in that the side panels are made detachable, while the connector lines pass through the intermediate panel.

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