RU2362713C2 - Space vehicle layout design method - Google Patents

Abstract

FIELD: transportation.

SUBSTANCE: said utility invention relates mainly to telecommunication satellites with long service life. The method involves designing a space vehicle of two modules, a support system module and a payload module. The module radiators are made of triple-layer honeycomb panels with heat tubes integrated into them. These radiators are located in planes normal to the +Z and -Z axes of the vehicle (at its "northern" and "southern" sides). Module instruments are installed on the outer surfaces of the inner shells of the radiator panels and on the surfaces of the triple-layer honeycomb instrument panels located between the said radiator panels. The latter are equipped with manifolds for the heat medium circulation, which are connected to the similar manifolds integrated in the instrument panels so that both manifolds form closed circulation circuits. The manifolds of the said radiators are installed on the outer surfaces of the inner shells of the honeycomb radiator panels, opposite to the evaporation zones of the heat tube integrated in these panels. The condensation zones of these heat tubes are located parallel to the +Y or -Y axes of the vehicle (the "eastern" and "western" directions). The evaporation zones of the heat tubes are located in parallel to the longitudinal axis +X of the vehicle. A safety shield is installed above each manifold of the said radiators.

EFFECT: decreased radiator weight (by 3 % minimum) with these types of heat tubes, manifolds, and honeycomb panel structure.

10 dwg

Description

The invention created by the authors in the order of performance of an assignment relates to space technology, in particular to telecommunication satellites.

Known methods of linking telecommunication satellites according to the patents of the Russian Federation No. 2151722 [1], No. 2237600 [2], according to which the devices of the payload module (MPN) and the module of the service systems (MSS) of the satellite are installed on three-layer cellular panels (hereinafter: honeycomb panels) ) with collectors built-in under the devices for coolant circulation, and cellular panels + Z, -Z of MPN and MCC radiators with collectors built-in for the circulation of coolant in the panels, respectively, are placed in perpendicular planes to the + Z, -Z axes of the satellite.

An advantage of the above known layout methods is the provision of ground tests for the operability of the assembled satellite in both the vertical and horizontal thermal pressure chambers as a result of removal of excess heat from the instruments, and then from the radiators at any position in space during testing.

However, a significant drawback of the known methods [1], [2] is the increased mass of the cell radiator panels, because:

1) the total length of the duplicated collectors of the radiator panels is several tens of meters, for example, about 50 m;

2) the collectors have a relatively large internal diameter, for example 16 mm;

3) the total volume (and mass) of the coolant in the liquid paths of the collectors due to their relatively large lengths and internal diameters is also large;

4) the increased thickness of the honeycomb panels of radiators due to the use of the above collectors built into the honeycomb panels with a relatively large inner diameter.

There is a known method of arranging a spacecraft according to the patent of the Russian Federation No. 2092398 C1 [3], according to which the honeycomb panels of radiators with heat pipes built into them are placed in planes perpendicular to the axes + Z, -Z, + Y, -Y of the device, and devices of service system modules and payloads are installed on the outer surfaces of the inner linings of the radiator panels perpendicular to the axes + Z, -Z, and on the surfaces located between these radiator panels with integrated heat pipes.

For the equatorial (geostationary) satellite, the surfaces perpendicular to the + Z and -Z axes correspond to its “northern” and “southern” sides. The + Y, -Y axes of the satellite are oriented in the “east” and “west” directions. The longitudinal axis X is directed along the radius vector of the orbit.

An advantage of the known layout method [3] is to ensure the compactness of the satellite. However, the aforementioned known method of spacecraft arrangement has a significant drawback - honeycomb radiator panels placed in perpendicular planes to the + Y, -Y axes of the device have an increased mass, because:

1) these honeycomb panels have an increased thickness due to the incorporation of two different types of heat pipes into them (see Figs. 8 and 9 in the application materials) in such a way that one of the shelves of one heat pipe is in contact with one of the shelves of the other heat pipe and , for example, when using heat pipes with a diameter of the steam channel 6.3 mm (technologically smallest possible diameter), the thickness of the honeycomb panel is ≈26 mm;

2) from the outside (from the side facing outer space), each of the aforementioned panels contains (see FIG. 6 in the application materials) curtains with spring drives and an electromechanical system for notching and stripping;

3) the above panels have an increased total area for emitting the same amount of excess heat compared to panels placed in perpendicular planes to the + Z, -Z axes of the satellite, because radiator panels placed in perpendicular planes to the + Y, -Y axes of the device emit excess heat to outer space periodically (i.e. the panel that is facing in the shadow direction works).

In addition, the disadvantage is that it is not possible to test the assembled satellite for operability in ground conditions, which is now mandatory, even in a horizontal thermal chamber (since for this method of spacecraft arrangement, the placement of heat pipes is such that in ground tests it is impossible to ensure a horizontal position (to ensure operability) of all heat pipes installed on the apparatus even in a horizontal pressure chamber (see the last two sentences in ednem paragraph in the description of the invention [3])).

It should also be noted that at present the technological processes of embedding heat pipes of a U-shaped (and L-shaped) configuration in U-shaped (and L-shaped) honeycomb panels are not mastered by the industry, and if such heat pipes are attached to the surfaces of honeycomb panels and devices installed on honeycomb panels, total weight (for the same area of honeycomb panels with the same lengths of the same type of heat pipes): honeycomb panels of a U-shaped (and L-shaped) configuration plus heat pipes of a U-shaped (and L-shaped) configuration , it turns out more (by 4-7%) than the mass of honeycomb panels with heat pipes embedded in them, and, thus, at present it is not possible to use U-shaped (and L-shaped) honeycomb panels with heat embedded in them P-shaped (and L-shaped) pipes.

Thus, a common significant drawback of the above known methods of satellite arrangement is the increase in satellite mass due to the use of high mass radiators in the arrangement.

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 method of layout of the spacecraft according to [3].

According to the known method (see Fig.6-10) the layout of the spacecraft is performed as follows:

- provide for the manufacture, assembly, testing and ground tests separately:

- payload dashboard 3 with radiators + Z, -Z (see Fig. 6 and 7, where: 2 - devices; 3 - payload dashboard; 25, 26 - U-shaped U-shaped configurations in the honeycomb panel and L-shaped heat pipes; 6 - information-logical instrument unit (ILB); 7 - energy-motor instrument unit (EDB); 32 - curtain radiators + Y, -Y and payload module (MPN) as a whole;

- information-logical instrument unit 6 (ILB) with radiators + Y, -Y (see Fig. 8 and 9, where 6 - ILB; 4 - devices; 16 and 17 - radiators + Y, -Y, which are part of H- shaped honeycomb panel with built-in direct heat pipes 28 and U-shaped heat pipes 27; 31 - dashboard center panel; ILB is part of the service systems module (MSS));

- energy-driven instrument unit 7 (EDB) with radiators + Z, -Z (see Fig. 10, where: 5 - devices; 7 - EDB; 28, 29, 30 - U (P) configurations embedded in the honeycomb panel -shaped heat pipes; EDB is part of the service systems module (MSS);

they provide for satellite assembly: they are combined into a single unit along the mechanical, electrical interfaces of MPN and MSS (including: payload dashboard 3 plus ILB 6 with EDB 7) and they believe that the satellite has been completed (assembled) and is ready for launch orbit.

As shown above, a significant drawback of the known technical solution is the increase in the mass of the spacecraft due to the use in its design of radiator panels of an insufficiently perfect design having a relatively large mass.

The aim of the proposed technical solution is to eliminate the above significant drawback.

This goal is achieved by arranging the spacecraft in such a way that the collectors for the heat carrier circulated for the radiators, connected to the collectors integrated in the instrument panels for circulating the heat carrier and together with them forming closed circulation circuits, are installed on the outer surfaces of the inner skin of their cell panels opposite to the evaporation zones heat pipes embedded in the radiator honeycomb panels with the placement of their condensation zones parallel to the + Y (-Y) axis And evaporation zones - in relation to the areas of condensation, in a direction parallel to the axis X + apparatus, wherein each of the aforesaid collector radiators mounted protective shield, which is, according to the authors, the essential distinctive features of the proposed technical solutions authors.

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 Fig.1-5) the layout of the spacecraft is performed as follows:

- provide for the manufacture of:

- honeycomb radiator panels 1.1, 1.2, 2.1, 2.2 with heat pipes 1.1.5, 1.1.6 embedded in them (see Figs. 2, 3, 4; similarly for the other radiator panels mentioned above) with an inner diameter of, for example, 6, 3 mm, with the placement of the condensation zones 1.1.5.1, 1.1.6.1 (see figure 4) parallel to the axis + Y (-Y) of the spacecraft, and the evaporation zones 1.1.5.2, 1.1.6.2 (see figure 3) - in relation to condensation zones - in a direction parallel to the + X axis of the apparatus;

- collectors 1.1.7, 1.1.8 for circulation of the coolant intended for installation (see Fig. 3) on the outer surfaces 1.1.2.1 of the inner skin 1.1.2 of the honeycomb panels 1.1 of the radiators (in Fig. 3: 1.1 - honeycomb panel; 1.1 .1 - honeycomb; 1.1.2 - inner lining; 1.1.2.1 and 1.1.2.2 - outer and inner surfaces respectively of inner lining 1.1.2; 1.1.3 - outer lining; 1.1.3.1 and 1.1.3.2 - outer and inner surface, respectively, of the outer skin 1.1.3; 1.1.10 - optical solar reflector);

- protective shields 1.1.9 (see FIG. 3) intended for installation above collectors 1.1.7 (1.1.8) for the circulation of coolant placed on the outer surfaces 1.1.2.1 of the inner skin 1.1.2 of the honeycomb panels 1.1 of the radiators;

- individually MPN 1 and MSS 2, combined into a single unit by mechanical, electrical and hydraulic interfaces at the final stage of manufacture before testing the assembled spacecraft;

- three-layer honeycomb (instrument) panels 1.3, 1.4, 1.5, 2.3, 2.4, 2.5 with integrated duplicated (functionally identical and independent) collectors in them for circulation of the coolant - see Fig. 5 (similarly for the other above-mentioned panels): 1.3 - three-layer honeycomb dashboard; 1.3.3, 1.3.4 - devices; 1.3.1, 1.3.2 - collectors for coolant circulation; 1.3.11 - EVTI - screen-vacuum thermal insulation (to exclude unregulated heat transfer and minimize the external solar heat flux on the edge of the satellite in the direction of the axes + X, -X, + Y, -Y);

- install three-layer honeycomb panels of MPN and MCC radiators 1.1, 1.2, 2.1, 2.2 with heat pipes 1.1.5, 1.1.6 built into them (see figure 2; similarly for other radiator panels) in planes perpendicular to the + Z axes , -Z apparatus (north and south sides of the satellite; the radiating surfaces of the radiator panels facing north and south are covered with optical solar reflectors 1.1.10 - see Figs. 3, 4));

- between the radiator panels 1.1, 1.2, 2.1, 2.2, three-layer honeycomb panels 1.3, 1.4, 1.5, 2.3, 2.4, 2.5 are installed with the duplicated collectors 1.3.1, 1.3.2 built into them (see figure 5; similarly for the other above panels) and on them opposite the location of the collectors place most of the satellite devices 1.3.3, 1.3.4 (see figure 5) (the other part of the devices 1.1.4 (see figure 4) of the satellite with relatively small heat and with wide allowable changes in operating temperatures are placed on the surfaces of the radiator panels 1.1, 1.2, 2.1, 2.2, placing them opposite the radiation guide surfaces 1.1.10);

- install (attach) - see figure 3 - radiator collectors 1.1.7 and 1.1.8 for circulation of the coolant on the outer surfaces 1.1.2.1 of the inner skin 1.1.2 of their honeycomb panels 1.1 opposite the evaporation zones 1.1.6.2 (1.1.5.2) heat pipes 1.1.6, 1.1.5, embedded in the honeycomb panels 1.1 of radiators with the placement (see Fig. 4) of condensation zones 1.1.6.1 (1.1.5.1) parallel to the + Y (-Y) axis, and evaporation zones (see figure 3) 1.1.6.2, 1.1.5.2 - in relation to the condensation zones - in the direction parallel to the axis + X of the apparatus;

- connect by pipelines the collectors and collectors installed in the honeycomb panels installed on the radiator panels, forming two closed duplicated, functionally identical and independent hydraulic circuits for circulating the coolant (circulation of the coolant through each closed circuit is carried out by an electric pump unit provided in each circuit);

- over each of the above collectors 1.1.7, 1.1.8 radiators install a protective screen 1.9 (see figure 3) (for example, a screen of brass tape with a thickness of 0.1 mm in two layers).

The collectors and collectors installed on the honeycomb panels of radiators built into the honeycomb dashboards are connected by pipelines in such a way that two closed hydraulic circuits are formed, combining the corresponding collectors of all panels, including radiator collectors located in planes perpendicular to the + Z axes, - Z.

Thus, the external heat flux from the radiator panel illuminated by the Sun is transferred by the liquid coolant to the unlit panel, thereby reducing the total area (and weight) of the radiators, ensuring the same level of maximum temperatures.

It should be additionally noted that as a result of such a spacecraft arrangement, the operability of heat pipes is ensured during ground tests of the device in both vertical and horizontal pressure chamber.

To increase reliability, the collectors of the radiator panels are protected from the effects of micrometeorites and technogenic particles by protective shields.

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

The excess heat generated during the operation of satellite devices 1.3.3, 1.3.4 is transferred through heat transfer to the coolant circulating through the collectors 1.3.1, 1.3.2, built into the honeycomb panels 1.3, 1.4, 1.5, 2.3, 2.4, 2.5 and laid under devices, and then the heated coolant enters the radiator collectors 1.1.7, 1.1.8, and the excess heat is transferred through the heat transfer from the circulating coolant to the radiator sheaths and evaporative zones 1.1.5.2, 1.1.6.2 of the heat pipes 1.1.5, 1.1.6, built-in into the honeycomb panels of radiators. Heat pipes evenly distribute the heat flux along the outer skin of the radiators, after which it is radiated into outer space.

In this way:

- heat pipes embedded in the honeycomb panels + Z, -Z radiators, perform the following functions:

- removal of excess heat from devices installed on the panels + Z, -Z radiators;

- heat removal from heat exchange sections of collectors attached to panels + Z, -Z radiators;

- uniform distribution of heat on the panels + Z, -Z radiators;

- liquid collectors built into the honeycomb dashboards and attached to the panels + Z, -Z radiators, perform the following functions:

- removal of excess heat from devices installed on the mobile instrument panels MPN and MSS, and partially from devices installed on the panels + Z, -Z radiators;

- transfer of excess heat flux between the panels + Z, -Z radiators;

- alignment of temperature fields on cellular dashboards and in separate ("hot") temperature zones on panels + Z, -Z radiators;

- performing the functions of vertically oriented (in the sense - with respect to ground tests) heat pipes, which contributes to conducting ground tests of the assembled satellite for operability both in its horizontal and vertical position; and, as analysis has shown, as a result of the integrated operation of heat pipes and collectors to provide the required heat sink to outer space, a relatively reduced total required area of panels + Z, -Z radiators will be required.

The analysis showed:

- as a result of the use of radiators built-in and originally arranged according to the proposed technical solution in the + Z, -Z honeycomb panels and the placement of collectors for circulating the coolant on the outer surfaces of the inner casing of the above radiator panels and at the same time eliminating relatively heavy (and complex) panels from the satellite + Y, -Y radiators is provided, for example, for a satellite with a heat load of 4000 W; the total reduction in the mass of the satellite radiators is not less than 3%;

- in addition, a relative decrease in the mass of the satellite as a whole is ensured as a result of the increased compactness of the satellite as a result of the installation of devices on cellular dashboards with collectors built in them for circulating coolant located between the + Z, -Z panels of both MPN and MCC radiators, and transfer of excess heat generated during their operation, circulating through the collectors with coolant on the panel + Z, -Z radiators with heat pipes originally built into them according to the proposed technical solution uw, ie thereby achieving the objectives of the invention.

Currently, the technical solution proposed by the authors is reflected in the technical documentation for the development of a telecommunication satellite.

Claims (1)

The spacecraft layout method, including the implementation of the device consisting of two modules: a service system module and a payload module, the radiators of which are made of three-layer honeycomb panels with heat pipes built into them, are placed in planes perpendicular to the + Z and -Z axes of the device, and the devices of these modules are installed on the outer surfaces of the inner casing of these panels of radiators of these modules and on the surfaces of three-layer honeycomb dashboards placed between these panels radiators, characterized in that the collectors for the coolant provided for the said radiators are connected to the collectors for the coolant circulation integrated in the dashboards, forming closed circulation circuits from both collectors, and the collectors of these radiators are installed on the outer surfaces of the inner skin of the cell radiator panels opposite zones of evaporation of heat pipes embedded in these honeycomb panels of radiators, with the placement of condensation zones of these heat pipes in parallel flax axis + Y or -Y apparatus and vaporization zone - with respect to the condensation zone - in a direction parallel to the axis X + apparatus, wherein the collector of each of said set of radiators shield.

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