RU130299U1 - HEATING REGIME SYSTEM FOR PRECISION SPACE VEHICLES - Google Patents

Abstract

1. A system for ensuring the thermal regime of precision instruments of a spacecraft, comprising a thermostabilized platform with seats for installing devices, made in the form of a flat honeycomb panel with integrated heat pipes connected to each other by a common collector heat pipe, and a radiator heat pipe based on a contour heat pipe, the evaporator of which in contact with the collector heat conductor, and the condenser is integrated into the radiator, which dissipates heat into outer space, while the seats for installation of devices in contact with the heat-generating bases of the devices are located on both sides of the honeycomb panel, characterized in that the system is equipped with flat contact heat exchangers with heat pipes built into them installed inside precision devices and additional heat pipes of radiators based on contour heat pipes, while the pipes of each contact heat exchanger are in contact with the evaporator of the corresponding additional heat sink of the radiator. 2. The thermal management system according to claim 1, characterized in that the system is equipped with an additional collector heat conduit connecting the heat pipes of contact heat exchangers with the possibility of providing thermal contact between them. The thermal management system according to claim 1, characterized in that the contact heat exchangers are made monolithic and have lodgements for accommodating built-in heat pipes. The thermal management system according to claim 1, characterized in that the contact heat exchangers are based on axial heat pipes filled with a�

Description

The proposed technical solution relates to space technology, in particular, to the systems of thermal regulation of the payload of spacecraft (SC) and can be used to ensure the thermal regime of precision instruments and other equipment of the SC, which requires accurate temperature maintenance.

There are known systems for ensuring the thermal regime of office equipment and the payload of spacecraft in which the temperature control of devices is carried out by installing devices on a thermostatically controlled platform and maintaining the temperature of the instrument seats in a given range [RF Patent No. 2092398, C1 B64G 1/10]. Such platforms can be made of lightweight heat-conducting metal by milling or casting, or glued in the form of honeycomb panels, while in most cases, regardless of the manufacturing method, they are equipped with heat pipes, mainly heat pipes, with which heat from the equipment seats assigned to radiators or to radiating zones (sections) of thermostatically controlled platforms (panels) themselves.

There is a known system for providing thermal conditions in which heat from a platform with installed devices is removed to radiators using loop heat pipes (KNTT) [KAGoncharov, E. Yu. Kotlyarov and GPSerov, Computer Model of Satellite Thermal Control System Using a Controlled Capillary Pumped Loop, Proceeding of the 23th International Conference on Environmental Systems, Colorado Springs, USA, 1993, # 932306 SAE Technical Paper Series]. In this case, KNTT evaporators are connected to all heat pipes mounted on the platform and removing heat from the equipment using collector heat pipes, and KNTT condensers are built into radiation heat exchangers. The indicated solution has found wide application in practice, since with the help of KnTT it is possible to provide effective and accurate temperature control, as well as transfer significant heat fluxes.

The well-known "System for ensuring the thermal regime of the thermal honeycomb service systems" (SOTR TSP SS) KA "Electro", developed in NPO them. S.A. Lavochkina and, currently, performing the task in orbit of the satellite [Altov V.V., Gulya V.M., Kopyatkevich PM, Mishin G.S., Goncharov K.A., Kochetkov A.Yu., Tulin D.V., Shabarchin A.F., Thermal design and fragment-wise ground testing of a system for providing thermal conditions for an unpressurized spacecraft based on honeycomb panels with heat pipes, Cosmonautics and Rocket Engineering, TsNIIMASH, Korolev, Russia, issue 3 (60 ), 2010, pp. 34-41]. To maintain a given thermal regime, the bulk of the service equipment of the Electro spacecraft is installed on a thermal honeycomb panel (TSP). This panel has the shape of a flat octahedron and is a three-layer glued honeycomb panel with integrated axial heat pipes. The heat power generated by the equipment installed on the TSP is removed from the seats by axial heat pipes to the collector heat pipe and, further, by the contour heat pipes to the working surface of the radiators, from where it is radiated into the surrounding space. The composition of the SOTR TSP SS includes two radiators based on contour heat pipes, the radiating surfaces of which are oriented, respectively, in the “-Z” direction and in the “+ Z” direction. Figure 1 shows the spacecraft "Electro", carrying several honeycomb panels and several radiators, in particular radiators and honeycomb panel SOTR TSP SS.

The main elements of COTR TSP SS type systems are KNTT based radiators, which are commonly called radiator heat pipes (TPR), since KNTT and radiator in this case represent a single structural element. Each TST based on KnTT contains the following components:

- an evaporator with a capillary pump and an attached compensation cavity;

- transport channels for steam and liquid, (steam pipe and condensate pipe), through which the evaporator is connected to the condenser;

- a radiation heat exchanger in which the KnTT condenser is structurally integrated.

In the design of КНТТ, on the basis of which the TPR is built, as a rule, the necessary elements are provided that provide temperature control, for example, a pressure regulator.

The closest analogue to the claimed system for providing thermal conditions for precision instruments of a spacecraft, selected as a prototype, is a system for providing thermal conditions (MOT) for precision instruments for a spacecraft [Tulin D.V., Tulin I.D., Goncharov K.A., Kochetkov A.Yu. Termal control system of the precision instrument board integrated into meteorological satellite. Proceedings of the VII Minsk International Seminar "Heat Pipes, Heat Pumps, Refrigerators, Power Sources", VII Minsk International Seminar, Minsk, Belarus, 2008, p.445-455] ^ which is part of the Electro spacecraft and contains a thermostable platform with seats for installation of devices, made in the form of a flat honeycomb panel with built-in heat pipes connected to each other by a common collector heat pipe, and a heat sink of a radiator based on a loop heat pipe, the evaporator of which contacts the collector heat pipe, and the condenser is integrated into the radiator, which dissipates heat into cosmic skoe space, wherein the planting space for installation of devices that come into contact with heat bases devices are arranged on both sides of honeycomb panels.

Figure 2 shows the thermostabilized platform of precision devices of the spacecraft "Electro", which is made in the form of a honeycomb. It also shows the main elements of the thermal control system.

As can be seen from Figure 2, three astro sensors are located on the honeycomb panel, below, on the brackets, and on top is the GIVUS device (which is shown in the form of a cylinder) and two identical multi-zone scanning devices (MSU), which are subject to the most stringent requirements regarding the accuracy of maintenance temperature. Further, first of all, these devices will be referred to as precision.

Schematically SOTR precision instruments (SOTR PP) is shown in Figure 3. This COTR consists of:

- thermal honeycomb panels (1), designed for two-sided installation of devices and having built-in heat pipes (2);

- collector heat conduit (3), which is in contact (through the shell of the TSP) with each of the heat pipes built into the TSP and with the evaporator (4) of the КНТТ;

- heat sink of the radiator (5), based on KNTT, which structurally combines the radiator (6) and the loop heat pipe, and the KNTT condenser is uniformly integrated into the radiator (6).

The thermal connection of all heat pipes to each other and, simultaneously, to the KNTT evaporator is carried out using a collector heat pipe, which in this example is made in the form of three axial heat pipes installed in parallel. Thus, heat is removed from the seats of devices placed on the TSP to a radiation heat exchanger.

The solution described above is currently being used to ensure the thermal regime of precision instruments of the KA Electro electro-technical complex named after S.A. Lavochkina. However, with an increase in the power of the units installed on the ТСП, the developed СТР has significant limitations associated with the increase of temperature gradients on the ТТС, with the increase in temperature differences at the joints of heat transfer units, as well as with the increase of internal temperature gradients in the equipment blocks themselves.

The proposed technical solution was developed in connection with a significant increase in thermal power allocated from ISU units, modified for use in the new version of the Electro spacecraft. Maintaining a given temperature here cannot be achieved by simply increasing the number of heat pipes and / or by increasing the area of the existing radiator. The technical problem solved by the proposed utility model is to maintain a given level of operating temperature of precision instruments while avoiding elevated temperature gradients, both between seats and inside the instruments themselves.

This task is ensured by the fact that, in contrast to the known system for ensuring the thermal regime of precision instruments of a spacecraft, containing a thermostabilized platform with seats for installing devices, made in the form of a flat honeycomb panel with integrated heat pipes connected to each other by a common collector heat pipe, and a heat sink radiator based on a contour heat pipe, the evaporator of which is in contact with the collector heat conductor, and the condenser is integrated into the radiator, diffuse heat in outer space, while the seats for installing devices in contact with the heat-generating bases of the devices are located on both sides of the honeycomb panel, the new one is that the system is equipped with flat contact heat exchangers with heat pipes built into them installed inside precision instruments, and additional heat pipes of radiators based on contour heat pipes, while the heat pipes of each contact heat exchanger are in contact with the evaporator of the corresponding heat sink radiator

In addition, the system is equipped with an additional collector heat conduit connecting the heat pipes of contact heat exchangers with the possibility of providing thermal contact between them.

In addition, contact heat exchangers are made monolithic and have lodgements for accommodating built-in heat pipes.

In addition, contact heat exchangers are made on the basis of axial heat pipes filled with ammonia.

In addition, contact heat exchangers are made in the form of honeycomb panels with integrated heat pipes.

In addition, the main and additional radiators are located in parallel planes without combining their projections.

In addition, an additional collector heat pipe is made on the basis of at least one axial heat pipe charged with ammonia.

The installation inside precision instruments of flat contact heat exchangers with heat pipes built into them, placed inside the precision instruments, and supplying the system with additional heat pipes of radiators based on the loop heat pipes, as well as contacting the heat pipes of each contact heat exchanger with the evaporator of the corresponding additional heat sink of the radiator, can more effectively remove unnecessary heat heat from precision instruments to radiating surfaces and reduce temperature gradients.

The presence of an additional collector heat conduit connecting the heat pipes of contact heat exchangers with the possibility of providing thermal contact between them provides additional temperature equalization (reduction of gradients), and, in addition, allows the duplication function to be implemented on the basis of two additional heat pipes of radiators (if the MCUs operate alternately) , due to which the reliability of the system is increased.

The implementation of contact heat exchangers in monolithic, with lodgements for the placement of built-in heat pipes increases their strength and reliability and provides effective heat transfer from devices.

The implementation of contact heat exchangers based on axial heat pipes charged with ammonia simplifies their integration into the thermal control system.

The implementation of contact heat exchangers in the form of honeycomb panels with integrated heat pipes reduces their mass.

The placement of the main and additional radiator are located in parallel planes without combining their projections.

The invention is illustrated by drawings, where:

Figure 1 - General view of the panel of service systems and radiators SOTRTSSS;

Figure 2 - General view of the existing thermostabilized platform of precision instruments of the spacecraft "Electro" (prototype);

Figure 3 is a schematic diagram of the existing COTP precision instruments (prototype);

Figure 4 and Figure 5 is a General view of the inventive thermostabilized platform of precision instruments KA "Electro";

6 is a schematic diagram of the inventive SOTR precision instruments (SOTR GSH) (part of the circuit with elements known from the prototype);

7 is a schematic diagram of the inventive COTP precision instruments (COTP PP) (part of the circuit with additionally introduced elements of COTP);

The inventive system for ensuring the thermal regime of precision instruments of the spacecraft shown in Figs. 4-7 includes a thermostabilized platform (1) with seats for installing devices made in the form of a flat honeycomb panel with integrated heat pipes (2) connected to each other by a common collector heat conduit ( 3), and the heat sink of the radiator (5) based on a contour heat pipe, the evaporator (4) of which is in contact with the collector heat pipe (3), and the condenser is integrated into the radiator (6), which dissipates heat in the space th space. Seats for installing devices in contact with the heat-generating bases of the devices are located on both sides of the honeycomb panel. In particular, the MSU blocks are in contact with the TSP (1), on the one hand, within the contact zones “A”. Inside precision instruments, flat contact heat exchangers (7) are installed with heat pipes built into them (8). The heat pipes of each contact heat exchanger are in contact with the evaporator (9) of the corresponding additional heat sink of the radiator (10). The internal elements of the MCU that generate heat are in contact with heat exchangers (7) within the contact zones “B”, on both sides. The thermal regime support system can be equipped with an additional collector heat conductor (11) connecting the heat pipes (8) of the contact heat exchangers with the possibility of providing thermal contact between them. Contact heat exchangers (7) can be made monolithic with lodges to accommodate built-in heat pipes or in the form of honeycomb panels with built-in heat pipes. As heat pipes, axial heat pipes filled with ammonia can be used. These pipes can be used in an additional collector heat conduit (11). The main (6) and additional (12) radiators are located in parallel planes without combining their projections.

The design of flat contact heat exchangers can, in many respects, inherit the experience gained in the development of thermostatically controlled platforms and contact heat exchangers into which heat pipes are built.

The system works as follows. The heat generated by the equipment installed on the TSP (1) is transferred through the TSP shell to the heat pipes integrated into the TSP (2). Further, the heat taken from the equipment through heat pipes enters the colder collector heat pipe (3), which also consists of heat pipes. Heat is transferred from the collector heat pipe to the cooler evaporator (4) of the heat pipe of the radiator (5) and further to the radiator (6) where it is dissipated into outer space. At the same time, the heat that is generated by powerful ISU units is partially taken away by contact heat exchangers built into them (7). Each contact heat exchanger through the evaporator (9) КНТТ gives heat directly to its additional heat pipe of the radiator (10). In this case, additional radiators (12) belonging to the corresponding additional TPR (10) also dissipate heat into the surrounding space. This allows you to unload the TSP and reduce temperature gradients in the powerful MSU blocks.

Since contact heat exchangers are interconnected by an additional collector heat conductor (11), both additional TPR can (simultaneously) remove heat from each ISU. This is especially important in the case of alternate use of the ISU or in case of asymmetric power consumption (heat generation).

Thus, in the solution presented in Fig. 4 and Fig. 5, the heat generated from high-power precision instruments (ISU) has two parallel paths for dissipation into open space

- through the main thermostabilized platform and the main heat sink of the radiator;

- through contact heat exchangers that are connected to additional heat pipes of radiators.

The developed technical solution allows more efficiently remove heat from precision instruments to radiating surfaces and reduce temperature gradients. At the same time, the installation of an additional collector heat conduit provides additional temperature equalization (reduction of gradients), and, in addition, allows the duplication function to be implemented on the basis of two additional TPR (if the MSU units will work alternately), thereby increasing the reliability of the system.

Claims (7)

1. A system for ensuring the thermal regime of precision instruments of a spacecraft, comprising a thermostabilized platform with seats for installing devices, made in the form of a flat honeycomb panel with integrated heat pipes connected to each other by a common collector heat pipe, and a radiator heat pipe based on a contour heat pipe, the evaporator of which in contact with the collector heat conductor, and the condenser is integrated into the radiator, which dissipates heat into outer space, while the seats for the installation of devices in contact with the heat-generating bases of the devices are located on both sides of the honeycomb panel, characterized in that the system is equipped with flat contact heat exchangers with heat pipes built into them installed inside precision devices, and additional heat pipes of radiators based on contour heat pipes, while the pipes of each contact heat exchanger are in contact with the evaporator of the corresponding additional heat sink of the radiator. 2. The thermal management system according to claim 1, characterized in that the system is equipped with an additional collector heat conduit connecting the heat pipes of contact heat exchangers with the possibility of providing thermal contact between them. 3. The system of providing thermal conditions according to claim 1, characterized in that the contact heat exchangers are made monolithic and have lodgements for accommodating built-in heat pipes. 4. The thermal management system according to claim 1, characterized in that the contact heat exchangers are made on the basis of axial heat pipes charged with ammonia. 5. The system of providing thermal conditions according to claim 1, characterized in that the contact heat exchangers are made in the form of honeycomb panels with integrated heat pipes. 6. The thermal management system according to claim 1, characterized in that the primary and secondary radiators are located in parallel planes without combining their projections. 7. The thermal management system according to claim 1, characterized in that the additional collector heat pipe is made on the basis of at least one axial heat pipe filled with ammonia.

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