RU2353553C2 - Space vehicle arrangement method - Google Patents

Abstract

FIELD: aircraft industry.

SUBSTANCE: invention refers namely to telecommunication satellites with energy consumption power of 1-2.5 kV. According to the invention, space vehicle (satellite) is made of two modules: payload and support systems. Instruments are installed on inner skins of their radiators - honeycomb panels. Evaporation zones of horizontal straight and uncontrolled L-shaped heat tubes are built into those panels opposite the instrument location area. Those zones are attached with their flanges to inner skin of panels in that area. Condensation zones of the above tubes are arranged in the panel areas free of instruments. Radiators are located in planes perpendicular to the axes corresponding to northern and southern sides of the vehicle. At that, opposite located radiator panels are arranged at a minimum possible distance from each other, which is determined beforehand based on instrument arrangement conditions. More heat-stressed instruments are located in the lower part of panels, in which there used are uncontrolled L-shaped heat tubes. Condensation zone flanges of the above heat tubes are made so that they face outer skins, and are attached thereto. The above zones are located in extreme zones of panels, which are free from instruments.

EFFECT: decreasing mass, and reaching the acceptable configuration of the above satellites.

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Description

The invention relates to space technology, in particular to telecommunication satellites, and was created by the authors in the order of performance of a job.

Currently, domestic telecommunication satellites intended for use in the geostationary orbit are launched into the indicated orbit from the Baikonur Cosmodrome.

In modern conditions, the task of further reducing the overall material and financial costs spent on each satellite operating in a geostationary orbit is very urgent, and it is preferable that they be launched into the indicated orbit from the Plesetsk cosmodrome.

To solve the above problem, it is necessary to improve the layout of newly developed satellites to ensure simultaneous launch from the Plesetsk cosmodrome to working orbits using a Soyuz-2 launch vehicle plus a Frigate booster, for example, two or three satellites with power consumption 1-2.5 kW.

The analysis showed that if such satellites are arranged on the basis of well-known technical solutions described in the patent of the Russian Federation No. 2092398 [1] and the source: Jean J. Dechezelles, Dietric E Koelle "Design and application of the AS / MBB Spacebus Family" - AJAA 11 Communication Sattelite Sistems, March 17-20, 1986, pp. 688 - 696. RJ 41, 1986, ref. 10.41.125-10.41.126 (SC platform S В - 44) [2], such a task is not feasible, because due to their complex configuration, the masses of satellites are unacceptably large.

Consequently, the newly developed satellite for solving the above problem should have such a layout that it would provide a significant simplification of the design and reduction of its mass while guaranteeing high quality workmanship and high reliability for a long period of orbital operation of the satellite.

An analysis of the sources of information on patent and scientific and technical literature showed that the closest in technical essence to the prototype of the proposed technical solution is the spacecraft layout method [1] made of payload modules and service systems in which spacecraft devices are installed on radiators - cell panels, in which unregulated heat pipes are installed on the northern (+ Z) and southern (-Z) sides of the spacecraft. The known prototype does not provide a solution that provides a compact design of the spacecraft with an acceptable, relatively low weight.

The purpose of the proposed technical solution is the elimination of the above significant disadvantages.

As a result of a comprehensive detailed analysis of this problem, the authors found that the minimum possible mass of a satellite with an acceptable required configuration is realized when the following complex technical solution is performed during the assembly process.

All devices should be placed on the inner casing installed on the north and south sides of the satellite and located as close as possible to each other radiators made of aluminum honeycomb panels with built-in aluminum straight and L-shaped unregulated heat pipes (with redundancy), each having one condensation and evaporation zone (based on experience, currently unregulated aluminum heat pipes are the most reliable and have a low relative mass compared to other types of heat pipes) b: if a direct unregulated heat pipe (or a U-shaped heat pipe) has two condensation zones located on opposite sides of the evaporation zone, then one of the condensation zones may overflow with the liquid phase and the effective operation of the heat pipe will be impaired (see Chi C “Heat pipes: theory and practice” - translation from English by V. Ya. M. Sidorov, “Mechanical Engineering”, 1981, p. 65).

In this case, the condensation zones of the heat pipes should be located in the zone of the location of the side margins, where heat-generating devices should not be installed.

Heat-stressed devices (for example, solid-state amplifiers) should be located in the lower region of the radiator panels and excess heat should be removed from them by L-shaped unregulated heat pipes (this will provide a favorable arrangement of condensation zones: they will be located in the marginal zones above the evaporation zones, which is important in ground tests).

To ensure the minimum possible distance between the radiator panels, in particular, the satellite must be made up of two modules: the payload module (MPN) and the service system module (MSS) - this will require the minimum possible distance between the panels to ensure replacement (or repair) of substandard devices, mainly detected during autonomous tests of MPN and MSS.

As a result of the close distance between the radiator panels, the mass costs for the design and the cables are reduced, and the mutual heat exchange between the devices and the surfaces of the radiator panels located on different sides is improved, as a result of which the degree of difference in the operating temperatures of the devices decreases, which favorably affects their work.

The thickness of the radiator panels should be as low as possible - this means that the thickness of the heat pipes should also be as low as possible and they should have a shelf in the evaporation zone facing the inner skin of the panel on which the heat-generating device is installed, and in the condensation zone the shelf should face outer skin.

In addition, the location of the shelves thus reduces the temperature difference between the evaporation and condensation zones and increases the average temperature of the radiator surface radiation, thereby reducing the required area of the radiators and further reducing their mass.

In addition, the outer surfaces of the heat pipes in the areas opposite the shelves are made with protrusions having a flat surface to ensure effective thermal communication with the skin surface and further with the radiation surface, which also contributes to an increase in the temperature of the radiating surface and to reduce the required area of radiators.

Thus, the goal set by the authors - to compose the spacecraft with the minimum possible mass and an acceptable required configuration - is achieved according to the technical solution of the authors using such a spacecraft layout method that oppositely located radiator panels are placed at a predetermined minimum possible distance from each other, while more heat-stressed devices are placed in the lower region of the panels, in which L-shaped unregulated heat pipes are used, and the shelves of condensation zones and heat pipes are made facing the outer casing and attached to them with the placement of these zones in the peripheral areas of the panels, free from devices, which is, according to the authors, the essential distinguishing features of the proposed technical solution.

As a result of the analysis conducted by the authors of the known patent and scientific and technical literature, the proposed combination of significant distinguishing features of the claimed technical solution in the known sources of information was not found and, therefore, the known technical solutions do not exhibit the same properties as in the claimed invention.

According to the proposed method (see figures 1, 2, 3, 4, where 1 is the antenna placement zone; 2 is the solar panels placement zone (shown in the folded position at the orbital site); 3 - MPN; 4 - MSS; 3.1 - MPN radiator; 4.1 - MCC radiator; 3.1.1, 4.1.1 - direct heat pipes; 3.1.2 - L-shaped heat pipes; 3.2, 4.2 - zone of non-heat-stressed devices; 3.3 - zone of heat-stressed devices; 3.4 ( 4.4) - instruments; 3.1.3 (4.1.3) - external (external) casing of the radiator panel; 3.1.4 (4.1.4) - internal casing of the radiator panel; 3.1.1.1 (4.1.1.1) (3.1.2.1) - evaporation zones; 3.1.1.2 (4.1 .1.2) (3.1.2.2) - condensation zones; 3.1.5 - optical solar reflector; 3.5 (4.5) -insulation) spacecraft layout, for example, a telecommunications satellite with a power consumption of 2 kW with a long lifetime in orbit (15 years or more ), perform as follows: SCs are made up of two modules: payload module 3 and service system module 4, and devices 3.4 (4.4) are installed on the inner skin 3.1.4 (4.1.4) of their radiators 3.1 (4.1) - cellular panels with built-in evaporator 3.1.1.1 (4.1.1.1) (3.1.2.1) horizontal straight lines 3.1.1 (4.1.1) and L-shaped 3.1.2 unregulated heat pipes connected in this area by shelves 3.1.1.3 (4.1.1.3) ( 3.1.2.3) to the inner casing 3.1.4 (4.1.4) of the panels, with the placement of condensation zones 3.1.1.2 (4.1.1.2) (3.1.2.2) of the pipes in the areas of the panels free from instruments, while the radiators are placed in planes, perpendicular to the axes + Z (north side of the spacecraft) and -Z (south side of the spacecraft) of the apparatus.

Opposite radiator panels are placed at a predetermined minimum possible distance from each other (see above), while more heat-stressed devices (in particular, MPN) are placed in the lower region of the panels, and L-shaped unregulated heat pipes are used in this area, the shelves 3.1.1.4 (4.1.1.4) (3.1.2.4) of the condensation zones of the heat pipes are made facing the outer casing 3.1.3 (4.1.3) and attached to them with the placement of these zones in the outlying areas of the panels, free from appliances.

The operation of a spacecraft arranged according to the proposed method is as follows.

In the areas of the spacecraft launch to the operating points of the geostationary orbit, substitute electric heaters are included, located on the inner skin near the installation of the devices, and their required temperature is provided by the corresponding compensating heat supply from the electric heaters.

After the devices are brought to operating points and their respective orientations, devices 3.4 (4.4) are put into operation according to the standard sequence diagram: the main amount of excess heat from the devices is transferred to the heat pipe evaporators 3.1.1.1 (4.1.1.1) (3.1.2.1), then to their condensers are then transferred to the outer skin of the radiator panel (in this case, part of the excess heat is transferred from the inner skin to the outer skin), and the total amount of heat is radiated into outer space.

The final layout of the newly developed telecommunications satellite is currently being developed.

In the process of compiling a satellite, various options for compiling a satellite were considered using well-known technical solutions to this issue and the method proposed by the authors, and it was found that in the case of using the proposed method, an acceptable satellite configuration and a decrease in its mass are achieved as a result of:

1) the maximum possible rapprochement of the MPN and MSS radiators with each other: this distance is determined by the height of the devices installed on the inner paneling and the minimum necessary additional distance to replace substandard devices;

2) the location of heat-stressed devices (in particular, MPN) in the lower part of the radiators and the absence of devices in the areas of the outskirts of the radiators;

3) the use of unregulated heat pipes and the location of their evaporation zones horizontally (relative to the Earth);

4) each heat pipe has one condensation zone;

5) heat pipes are used, in which the shelf in the evaporation zone is turned towards the inner casing on which the devices are installed, and in the condensation zone the pipe shelf is turned towards the outer casing (the transport zone of the pipes to ensure placement in the structure of the honeycomb panel is between two parallel claddings - accordingly bent by a small amount), which ensures, on the one hand, the minimum possible thickness of the honeycomb panel and the minimum possible mass of the heat pipe itself, while ensuring a decrease in mass ( area) of the radiator as a result of increasing the average radiation temperature of the outer surface of the outer skin.

Thus, as can be seen from the foregoing, as a result of the development of the layout of the newly created satellite according to the technical solution proposed by the authors, the required configuration and reduction of its mass to an acceptable value are provided, i.e. thereby achieving the objectives of the invention.

Claims (1)

The spacecraft layout method, including the implementation of the apparatus of two modules: payload and service systems, installation of devices on the inner casing of their radiators - honeycomb panels, into which, opposite the device placement area, evaporation zones of horizontally located straight and L-shaped unregulated heat pipes are connected in this area, with their shelves to the inner lining of the panels, and the condensation zones of these pipes are placed in the areas of the panels free from appliances, and the indicated the radiators are placed in planes perpendicular to the + Z and -Z axes corresponding to the north and south sides of the apparatus, characterized in that the opposite radiator panels are placed at a predetermined minimum possible distance from each other, while the more heat-stressed devices are placed in the lower region of the panels in which L-shaped unregulated heat pipes are used, and the shelves of the condensation zones of these heat pipes are facing the outer skin and are attached to them, placing these zones in innyh areas panels free devices.

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