Spacecraft 490n engine solenoid heat sink

Abstract

The application provides a spacecraft 490N engine electromagnetic valve heat dissipation device related to the field of aerospace thermal control technology, which comprises an electromagnetic valve, a heat dissipation piece and a star body support flange, the 490N engine is installed and assembled through an engine flange and a satellite support flange screw, the heat dissipation piece is connected with the electromagnetic valve and the star body support flange through contact heat conduction filler, and the electromagnetic valve increases the heat dissipation area through the heat dissipation piece, so that the electromagnetic valve directly exchanges heat with the star body support flange. The 490N engine electromagnetic valve heat dissipation device is used to make the electromagnetic valve directly exchange heat with the star body support flange, so that the electromagnetic valve has stronger heat dissipation capacity, and has the characteristics of long service life, small weight, strong temperature control capacity, adaptability to extreme high and low temperature working conditions and high reliability.

Description

Technical Field

[0001] This invention relates to the field of aerospace thermal control technology, specifically to a heat dissipation device for a solenoid valve of a 490N engine in a spacecraft. Background Technology

[0002] Previously, the 490N engines in geosynchronous orbit spacecraft only operated for short periods in transfer orbits, resulting in a short lifespan. Therefore, the condition of the 490N engines when not igniting was less of a concern. In recent years, however, spacecraft have longer lifespans, more complex operating conditions and attitudes, and require frequent orbital changes. Furthermore, the tail-mounted 490N engines maintain a prolonged sun-oriented orientation, leading to high nozzle temperatures. This results in high ambient temperatures near the solenoid valves of the long-life 490N engines. The configuration of the solenoid valves, along with the engine's mounting method and location, makes heat dissipation difficult. Consequently, it is necessary to monitor the long-term on-orbit storage temperature of the 490N engine solenoid valves, and the temperature control requirements for these valves are more stringent. Therefore, spacecraft need to provide strong heat dissipation capabilities for the long-life 490N engine solenoid valves during normal on-orbit operation.

[0003] Patent CN110949696A discloses a satellite engine thermal protection performance verification system in the field of satellite engine thermal protection technology, including an infrared lamp array, a reflective heat shield, a thermal protection component sample, a high-temperature measuring device, and a power supply. The reflective heat shield is made of polished stainless steel. In actual on-orbit use, there is no adequate heat dissipation for the solenoid valves, making it impossible to guarantee that the ambient temperature of the solenoid valves can remain within their specified range during long-term solar orientation.

[0004] Patent CN109823575A discloses a thermal protection device for a 490N satellite engine, comprising a lightweight high-temperature multilayer assembly (50μm stainless steel foil, 15μm nickel foil, and high-silica cloth), a medium-temperature multilayer assembly (20μm aluminum foil, 25μm double-sided aluminized polyimide, and high-silica cloth), and a low-temperature multilayer assembly (6μm double-sided aluminized polyester film and fiberglass cloth). Similarly, during long-term, sun-oriented, and frequently maneuvering operations in orbit, it is impossible to strictly guarantee that the temperature of the engine solenoid valve remains within the specified range. Furthermore, the performance of the protection device degrades over time, potentially leading to solenoid valve failure at the end of the orbital period.

[0005] Patent CN112177798A discloses a heat insulation mechanism suitable for spacecraft engines, including an engine bracket, a heat insulation gasket assembly, an adapter plate, and a multi-layer heat insulation assembly. The rear end of the engine is mounted on the injector, and the front end is connected to the adapter plate via the heat insulation gasket assembly. The adapter plate is connected to the manifold of the engine and is multi-layered on the manifold. The engine bracket is a rigid frame structure; the addition of non-metallic gaskets and the multi-layered design increases the thermal resistance from the injector to the manifold by more than five times. While this method significantly improves heat insulation, it is too heavy, has complex installation steps, and is too costly, making it unsuitable for various spacecraft configurations and environments. Summary of the Invention

[0006] To address the shortcomings of existing technologies, the purpose of this invention is to provide a heat dissipation device for the electromagnetic valve of a spacecraft 490N engine.

[0007] According to the present invention, a heat dissipation device for a 490N engine solenoid valve of a spacecraft includes a solenoid valve, a heat sink, and a satellite support flange. The 490N engine is installed and assembled with the satellite support flange via engine flange and satellite support flange bolts. The heat sink is connected to the solenoid valve and the satellite support flange respectively via heat-conducting filler. The solenoid valve increases the heat dissipation area through the heat sink, so that the solenoid valve can directly exchange heat with the satellite support flange.

[0008] In some embodiments, each heat sink includes a first heat sink and a second heat sink. Multiple first heat sinks are connected to the column section of the solenoid valve by clamps. The first heat sinks and the second heat sinks are connected in a one-to-one correspondence. The second heat sink is located on the flange of the star support.

[0009] In some embodiments, thermally conductive filler is used to fill the space between the first heat sink and the second heat sink, and between the second heat sink and the star support flange. The thermally conductive filler is an indium foil with a thickness of 0.1-0.2 mm.

[0010] In some embodiments, the first heat sink and the solenoid valve, and the second heat sink and the star support flange are adjustable via a perforation.

[0011] In some embodiments, the waist holes are evenly distributed on the second heat sink, and the length of the waist holes is 2-3mm.

[0012] In some embodiments, the perpendicularity between the first heat sink and the horizontal and vertical surfaces inside the solenoid valve is better than 0.1 mm, and the coaxiality between the first heat sink and the solenoid valve column segment is ≤ +0.05 mm.

[0013] In some embodiments, the perpendicularity of the second heat sink to the horizontal and vertical surfaces inside the star support flange is better than 0.1 mm.

[0014] In some embodiments, the heat sink and the satellite support flange are made of 2A14 aluminum alloy, and the surfaces of the heat sink and the satellite support flange are treated with black anodizing, requiring an emissivity ≥0.85.

[0015] In some embodiments, a polyimide film heating element is attached to a portion of the heat sink surface. When the solenoid valve temperature is too low, the solenoid valve is energized and kept warm through the polyimide film heating element.

[0016] In some embodiments, based on the heat transfer path analysis of the 490N engine tail when oriented to the sun, and considering the high temperature of the flange during engine operation and hot backwashing, the flange of the solenoid valve and the flange of the celestial support are heat-insulated by two layers of 3mm thick titanium alloy gaskets.

[0017] Compared with the prior art, the present invention has the following beneficial effects:

[0018] This invention utilizes the heat dissipation device of the 490N engine solenoid valve, enabling the solenoid valve to directly exchange heat with the planetary support flange, thereby giving the solenoid valve a stronger heat dissipation capacity. It features long service life, light weight, strong temperature control capability, adaptability to extreme high and low temperature conditions, and high reliability. Attached Figure Description

[0019] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0020] Figure 1 This is a schematic diagram of the heat dissipation device installation;

[0021] Figure 2 It shows the temperature curves of the solenoid valve before and after the installation of the heat dissipation device.

[0022] Numbering on the map:

[0023] Solenoid valve 1; Heat sink 2; First heat sink 21; Second heat sink 22; Star support flange 3; 490N engine nozzle 4; Star support 5; Clamp 6. Detailed Implementation

[0024] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0025] Example

[0026] A heat dissipation device for a 490N engine solenoid valve of a spacecraft, as provided by the present invention, such as Figure 1 As shown, the system includes a solenoid valve 1, a heat sink 2, a satellite support flange 3, a 490N engine nozzle, a satellite support 5, and a clamp 6. Four satellite supports 5 are evenly mounted on the satellite support flange 3, and the 490N engine nozzle passes through the satellite support flange 3 and is fixed to the satellite support 5. The heat sink 2 is connected to both the solenoid valve 1 and the satellite support flange 3. Preferably, the flange of the 490N solenoid valve 1 is insulated from the satellite support flange 3 using two layers of 3mm titanium alloy gaskets to reduce the impact of external heat flow on the satellite support flange 3. The solenoid valve 1 has an increased heat dissipation area through the heat sink 2, allowing for direct heat exchange between the solenoid valve 1 and the satellite support flange 3. This results in a more powerful heat dissipation capacity, longer lifespan, lighter weight, stronger temperature control, adaptability to extreme high and low temperature conditions, and higher reliability.

[0027] Heat sink 2 increases the heat dissipation area of ​​the 490N engine solenoid valve, thereby giving solenoid valve 1 a stronger heat dissipation capacity, avoiding localized overheating caused by prolonged exposure to direct sunlight, and maintaining the temperature of solenoid valve 1 within the normal temperature range for on-orbit storage. The planetary support flange 3 serves as both the mounting surface of heat sink 2 and the heat dissipation surface of solenoid valve 1. Given the difficult heat dissipation conditions caused by the configuration and mounting position of solenoid valve 1, this design increases the heat dissipation area and capacity of the solenoid valve. Both heat sink 2 and planetary support flange 3 are made of 2A14 aluminum alloy with a black anodized surface treatment (emissivity ≥0.85). This serves two purposes: firstly, it allows the planetary support flange 3 to dissipate heat effectively into the surrounding cold space; secondly, it ensures a uniform surface temperature of the planetary support flange 3.

[0028] This invention includes two sets of heat sinks 2, each set comprising a first heat sink 21 and a second heat sink 22. The two first heat sinks 21 are pressed onto the column section of the solenoid valve 1 by clamps 6, which are secured with screws. The screw holes on the first heat sinks 21 are evenly distributed and are oblong holes with a length of 3mm. Preferably, the portion of the first heat sink 21 in contact with the solenoid valve 1 is divided into two parts, allowing for heat conduction between the first heat sink 21 and the solenoid valve 1 in two separate parts. The perpendicularity of the horizontal and vertical planes within these two parts is better than 0.1mm; the coaxiality of the first heat sink 21 and the column section of the solenoid valve 1 is ≤+0.05mm; thus establishing a good thermal conductivity relationship between the first heat sink 21 and the solenoid valve. The first heat sink 21 and the second heat sink 22 are connected in a one-to-one correspondence. The second heat sink 22 is mounted on the star support flange 3 by screws. The two second heat sinks 22 have evenly distributed oblong holes with a length of 2mm, allowing for positional adjustability of the components within the heat dissipation device. The thermally conductive filler at the contact surfaces between the first heat sink 21 and the solenoid valve 1, and between the second heat sink 22 and the star support flange 3, is indium foil with a thickness of 0.1-0.2 mm, creating a good thermal conductivity path between the solenoid valve 1 and the star support flange 3. The contact portion between the second heat sink 22 and the star support flange 3 is divided into two parts, allowing the second heat sink 22 and the star support flange 3, which serves as the heat dissipation surface, to have two separate thermal conductions. The perpendicularity of the horizontal and vertical surfaces within these two parts is better than 0.1 mm.

[0029] More specifically, the part of the first heat sink 21 that contacts the solenoid valve 1 and the part of the second heat sink 22 that contacts the star support flange 3 are both divided into two parts because the four star supports 5 need to be installed on the star support flange 3, which isolates the heat dissipation surface into four independent parts. In addition, the solenoid valve 1 has connectors installed on its surface, which occupy the cylindrical space of the valve body. Therefore, to enhance the heat dissipation effect and make full use of the heat dissipation surface, the installation form of dividing it into two parts and pairing them with each other is adopted.

[0030] In addition, based on the heat transfer path analysis of the 490N engine tail when orienting to the sun, in order to reduce the direct heat transfer from the engine to the satellite support flange, the engine flange and the satellite support flange need to be thermally insulated. Considering the high temperature of the flange during engine operation and hot backwashing, the flange of the solenoid valve and the satellite support flange are thermally insulated by two layers of 3mm thick titanium alloy gaskets.

[0031] Among them, a polyimide film heating element is attached to a portion of the surface of the heat sink 2. When the temperature of the solenoid valve 1 is too low, the polyimide film heating element provides electrical insulation. If the temperature of the star support flange 3 continues to decrease with the ambient temperature, the heat dissipation effect of the 490N solenoid valve heat dissipation device will be even more significant.

[0032] like Figure 2As shown, the on-orbit operating temperature of the 490N solenoid valve without a heat dissipation device has reached 70℃, while the on-orbit operating temperature of the 490N solenoid valve with a heat dissipation device has dropped to 47℃.

[0033] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0034] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A heat dissipating device for a spacecraft 490N engine solenoid, characterized by, It includes electromagnetic valve (1), heat sink (2) and star bracket flange (3), the 490N engine is installed and assembled on the star bracket flange (3) through engine flange with screw, the heat sink (2) is connected with the electromagnetic valve (1) and the star bracket flange (3) through contact heat conduction filler respectively, the electromagnetic valve (1) increases the heat dissipation area through the heat sink (2), so that the electromagnetic valve (1) directly exchanges heat with the star bracket flange (3); Each heat sink (2) includes first heat sink (21) and second heat sink (22), a plurality of first heat sink (21) is connected to the column segment of the electromagnetic valve (1) through the clamp (6), the first heat sink (21) is connected with the second heat sink (22) one by one, and the second heat sink (22) is located on the star bracket flange (3); The first heat sink (21) and the second heat sink (22) are filled with the contact heat conduction filler, and the contact heat conduction filler is made of indium foil with a thickness of 0.1-0.2mm; The perpendicularity of the first heat sink (21) and the horizontal vertical surface inside the electromagnetic valve (1) is better than 0.1mm, and the coaxiality of the first heat sink (21) and the column segment of the electromagnetic valve (1) is less than or equal to +0.05mm; The perpendicularity of the second heat sink (22) and the horizontal vertical surface inside the star bracket flange (3) is better than 0.1mm.

2. The heat sink for a spacecraft 490N engine solenoid valve according to claim 1, characterized in that, The first heat sink (21) and the electromagnetic valve (1), the second heat sink (22) and the star bracket flange (3) are adjusted through the waist hole.

3. The heat sink for a spacecraft 490N engine solenoid valve according to claim 2, wherein The waist holes are uniformly distributed on the second heat sink (22), and the length of the waist hole is 2-3mm.

4. The heat sink for a spacecraft 490N engine solenoid valve according to claim 1, wherein The heat sink (2) and the star bracket flange (3) are made of 2A14 aluminum alloy, and the surface of the heat sink (2) and the star bracket flange (3) is black anodized, and the emissivity is greater than or equal to 0.

85.

5. The heat sink for a spacecraft 490N engine solenoid valve according to claim 4, wherein The local surface of the heat sink (2) is pasted with polyimide film type heating sheet, when the temperature of the electromagnetic valve (1) is too low, the electromagnetic valve (1) is heated and kept warm through the polyimide film type heating sheet.

6. The heat sink for a spacecraft 490N engine solenoid valve according to claim 1, wherein The flange of the electromagnetic valve (1) and the star bracket flange (3) are installed through two layers of 3mm thick titanium alloy gaskets.

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