CN117382914A

CN117382914A - Satellite thermal control system and satellite

Info

Publication number: CN117382914A
Application number: CN202311482823.8A
Authority: CN
Inventors: 邱少杰; 杨鹏; 支佳运; 丁汀; 方杰; 杨巧龙; 常明
Original assignee: Galaxyspace Beijing Communication Technology Co ltd
Current assignee: Galaxyspace Beijing Communication Technology Co ltd
Priority date: 2023-11-08
Filing date: 2023-11-08
Publication date: 2024-01-12

Abstract

The application relates to a satellite thermal control system and a satellite. The satellite thermal control system comprises: the magnetic rod thermal control module is arranged on a magnetic rod of the satellite and is used for adjusting the temperature of the magnetic rod; the propulsion thermal control module is arranged on the propulsion system of the satellite and is used for adjusting the temperature of the propulsion system; the battery thermal control module is arranged on a battery of the satellite and is used for adjusting the temperature of the battery; the battery controller thermal control module is arranged on the battery controller of the satellite and is used for adjusting the temperature of the battery controller; the antenna thermal control module is arranged on an antenna of the satellite and is used for adjusting the temperature of the antenna. The satellite thermal control system can adjust the temperature of equipment on the satellite, so that the equipment on the satellite can be exposed in an external space environment, and normal operation of the satellite is ensured.

Description

Satellite thermal control system and satellite

Technical Field

The application relates to the field of aerospace, in particular to a satellite thermal control system and a satellite.

Background

The traditional satellite is provided with an equipment cabin, equipment with requirements on temperature is arranged in the equipment cabin, and the working requirements of all the equipment are met by controlling the temperature of the equipment cabin. The novel flat satellite cancels the equipment cabin, all the equipment is arranged on the base plate or the supporting frame, equipment with requirements on temperature can be exposed to the outer space, and the environment of the outer space can influence the operation of partial satellite equipment.

Disclosure of Invention

Based on the above problems, the application provides a satellite thermal control system and a satellite, wherein the satellite thermal control system can adjust the temperature of an exposure device on the satellite so as to enable the satellite to stably operate in an external space.

In order to achieve the above effects, the technical scheme adopted in the application is as follows:

in a first aspect, the present application provides a satellite thermal control system comprising:

the magnetic rod thermal control module is arranged on a magnetic rod of the satellite and is used for adjusting the temperature of the magnetic rod;

the propulsion thermal control module is arranged on a propulsion system of the satellite and is used for adjusting the temperature of the propulsion system;

the battery thermal control module is arranged on a battery of the satellite and is used for adjusting the temperature of the battery;

the battery controller thermal control module is arranged on a battery controller of the satellite and is used for adjusting the temperature of the battery controller;

the antenna thermal control module is arranged on an antenna of the satellite and is used for adjusting the temperature of the antenna;

and the master controller is respectively connected with the magnetic rod thermal control module, the propulsion thermal control module, the battery controller thermal control module and the antenna thermal control module.

According to some embodiments of the present application, the magnetic rod thermal control module includes:

the magnetic rod temperature sensor is arranged on the magnetic rod and used for detecting the temperature of the magnetic rod;

the magnetic rod heating piece is arranged on the magnetic rod and used for heating the magnetic rod;

the magnetic rod heat dissipation structure is arranged on the magnetic rod.

According to some embodiments of the present application, at least two heating plates of the magnetic rod are uniformly arranged in a heating plate group in a circumferential direction around an axis of the magnetic rod, and a plurality of heating plate groups are sequentially arranged along the axis of the magnetic rod.

According to some embodiments of the present application, the magnetic rod heating sheet includes:

the film body is arranged on the magnetic rod;

the resistance wire is arranged on the film body and comprises a straight line portion and a connecting portion, the straight line portions are arranged in parallel, the connecting portions are respectively connected with the adjacent straight line portions, and the straight line portions are parallel to the axis of the magnetic rod.

According to some embodiments of the present application, the bar magnet heat dissipation structure comprises a white paint applied to a surface of the bar magnet.

According to some embodiments of the present application, the propulsion thermal control module includes:

the gas cylinder temperature adjusting structure is arranged on a gas cylinder of the propulsion system and used for adjusting the temperature of the gas cylinder;

The flow regulator temperature regulating structure is arranged on the flow regulator of the propulsion system and used for regulating the temperature of the flow regulator;

the propulsion controller temperature adjusting structure is arranged on a propulsion controller of the propulsion system and used for adjusting the temperature of the propulsion controller;

the propulsion support temperature adjusting structure is arranged on a propulsion support of the propulsion system and used for adjusting the temperature of the propulsion support.

According to some embodiments of the present application, the gas cylinder includes a cylinder body and a spherical end portion connected to each other, and the gas cylinder temperature adjustment structure includes:

the first air bottle heating plate is arranged on the bottle body;

the second gas cylinder heating piece is arranged at the spherical end part;

the third gas cylinder heating plates are arranged at the spherical end parts, the length of each third gas cylinder heating plate is smaller than that of each second heating plate gas cylinder, and a plurality of second gas cylinder heating plates and a plurality of third gas cylinder heating plates are alternately arranged around the axis of each gas cylinder.

According to some embodiments of the present application, the gas cylinder attemperation structure further includes a first multi-layer insulation assembly that encases the gas cylinder.

According to some embodiments of the present application, the flow regulator attemperation structure includes:

The flow regulator heating plate is arranged on the bottom surface of the flow regulator;

and the flow regulator heat dissipation film is arranged on the top surface and the side surface of the flow regulator.

According to some embodiments of the present application, the propulsion controller attemperation structure includes a white paint applied to a surface of the propulsion controller.

According to some embodiments of the present application, the propulsion stent attemperation structure includes a second multi-layer insulation assembly that encases the top surface and sidewalls of the propulsion stent.

According to some embodiments of the present application, the surface of the battery includes a top surface, a bottom surface, two long sides, and two short sides; the battery thermal control module includes:

the battery temperature sensor is arranged on the surface of the battery and is used for detecting the temperature of the battery;

the battery heating structure is arranged on the long side face of the battery and is used for heating the battery;

the battery heat insulation structure is arranged on the surface of the battery;

and the battery heat dissipation structure is arranged on the surface of the battery.

According to some embodiments of the application, the battery heating structure comprises battery heating plates, and at least one battery heating plate is respectively arranged on two long sides of the battery.

According to some embodiments of the present application, the battery insulation structure includes a third multi-layer insulation assembly covering at least a bottom surface, a portion of the long side surface, and a portion of the short side surface of the battery.

According to some embodiments of the present application, the battery heat dissipation structure comprises a white paint applied to the top surface and at least one long side surface of the battery.

According to some embodiments of the present application, the battery comprises:

a housing provided with a cavity;

the electric core, set up in the cavity, the electric core includes:

a core;

the insulating film comprises a side insulating film and a bottom insulating film, wherein the side insulating film covers the side surface of the core body and is folded towards the bottom center of the core body, and the bottom insulating film is adhered to the folded part of the side insulating film.

According to some embodiments of the present application, the battery further comprises:

a bushing provided to the housing;

titanium alloy screws penetrate into the bushings.

According to some embodiments of the present application, the battery controller thermal control module includes:

white paint coated on the top surface of the battery controller;

a fourth multi-layered heat insulation assembly coating a side of the battery controller;

And the heat insulation pad is arranged on the bottom surface of the battery controller.

According to some embodiments of the present application, the antenna thermal control module includes:

an antenna heating plate, a motor arranged on the antenna;

an antenna heat dissipation film arranged on a reflecting cover of the antenna;

a fifth multi-layer assembly disposed on the locking cylinder of the antenna;

and white paint is coated on the surface of the rotating unit of the antenna.

According to some embodiments of the present application, the satellite thermal control system further comprises a shield for protection of the digital temperature sensor, the shield comprising:

a cover body;

the accommodating groove is arranged on the surface of the cover body;

and the threading groove is arranged on the side wall of the cover body and is communicated with the accommodating groove.

According to some embodiments of the application, the protective cover further comprises a protective cover insulating layer, and the protective cover insulating layer is arranged on the surface of the cover body.

According to some embodiments of the present application, the satellite thermal control system further comprises a fluid cooling system comprising:

the cold plate is used for bearing the load of the satellite and is provided with a cooling flow passage;

the circulating pump is arranged on the cold plate and is communicated with the cooling flow passage;

And the fluid controller is arranged on the cold plate and is electrically connected with the circulating pump so as to control the circulating pump.

According to some embodiments of the application, the cold plate comprises:

the circulating pump and the fluid controller are both arranged on the first cold plate, the first cold plate is provided with a first cooling flow passage, and the circulating pump is communicated with the first cooling flow passage;

the second cooling plate is arranged above the load of the satellite and is provided with a second cooling flow passage, and the second cooling flow passage is connected with the first cooling flow passage.

According to some embodiments of the application, at least one of the first cooling flow channels comprises:

a first flow passage part, one end of which is communicated with one port of the first cooling flow passage;

a first heat absorbing portion having the same shape as the bottom surface corresponding to the load and communicating with the other end of the first flow path portion;

the second heat absorption part is the same as the bottom surface corresponding to the load in shape and is communicated with the first heat absorption part;

and one end of the second flow part is communicated with the second heat absorbing part, and the other end of the second flow part is communicated with the other port of the first cooling flow passage.

A third heat absorbing part communicated with one port of the first cooling flow channel;

a fourth heat absorbing part which has the same shape as the bottom surface corresponding to the load and is communicated with the third heat absorbing part;

and one end of the third flow through part is communicated with the fourth heat absorbing part, and the other end of the third flow through part is communicated with the other port of the first cooling flow passage.

a fifth heat absorbing part communicated with the third heat absorbing part;

and the fourth heat absorption part is communicated with the fifth geothermal part and is communicated with the other port of the first cooling flow passage.

and two sixth heat absorbing parts which are mutually communicated, wherein one sixth heat absorbing part is communicated with one port of the first cooling flow channel, and the other sixth heat absorbing part is communicated with the other port of the first cooling flow channel.

According to some embodiments of the application, the cold plate comprises:

a base body provided with a cooling groove;

and the cover plate is arranged on the base body and seals the top end opening of the cooling groove so as to form the cooling flow passage.

According to some embodiments of the present application, the fluid cooling system further comprises:

the liquid storage device is communicated with the circulating pump;

the filter is communicated with the circulating pump and is used for filtering solid particles in the liquid working medium;

the filling and discharging valve is communicated with the circulating pump and is used for filling or discharging liquid working media;

the pressure sensor is arranged on a pipeline between the cooling flow channel and the circulating pump and is used for detecting the pressure of liquid working medium in the pipeline, and the pressure sensor is in communication connection with the fluid controller.

In a second aspect, the present application provides a satellite comprising a satellite thermal control system as described above.

The satellite thermal control system can adjust the temperature of equipment on the satellite, so that the equipment on the satellite can be exposed in an external space environment, and normal operation of the satellite is ensured.

Drawings

In order to more clearly illustrate the technical solutions of the present application, the drawings that are needed in the description of the embodiments will be briefly described below, it being obvious that the drawings in the following description are only some embodiments of the present application, and that other drawings may be obtained according to these drawings by a person skilled in the art without departing from the scope of protection of the present application.

FIG. 1 is a schematic diagram of a satellite thermal control system according to an embodiment of the present application;

FIG. 2 is a schematic view of a magnetic rod mounted to a star according to an embodiment of the present application;

FIG. 3 is a schematic diagram of a magnetic rod thermal control module according to an embodiment of the present application;

FIG. 4 is a schematic view of a heat patch assembly according to an embodiment of the present application;

FIG. 5 is a schematic diagram of a magnetic rod heating plate according to an embodiment of the present application;

FIG. 6 is a schematic view of a propulsion system of an embodiment of the present application mounted to a star;

FIG. 7 is a schematic diagram of a propulsion system thermal control module according to an embodiment of the present application;

FIG. 8 is a schematic view of a cylinder heater plate according to an embodiment of the present application;

FIG. 9 is a schematic view of a first multi-layer insulation assembly according to an embodiment of the present application;

FIG. 10 is a schematic view of a temperature regulating structure of a flow regulator according to an embodiment of the present application;

FIG. 11 is a schematic view of a second insulation blanket according to an embodiment of the present application;

fig. 12 is a schematic view of a third insulation blanket according to an embodiment of the present application.

FIG. 13 is a schematic view of a battery mounted to a star according to an embodiment of the present application;

FIG. 14 is a schematic diagram of a battery thermal control module according to an embodiment of the present application;

FIG. 15 is a schematic view of a part of the structure of a battery thermal control module according to an embodiment of the present application;

FIG. 16 is a schematic view of a battery thermal insulation structure according to an embodiment of the present application;

FIG. 17 is a schematic view of a battery heat dissipation structure according to an embodiment of the present application;

Fig. 18 is an exploded view of a battery according to an embodiment of the present application;

FIG. 19 is an exploded view of an embodiment of the present application;

FIG. 20 is a schematic view of a side insulating film wrapped core according to an embodiment of the present application;

fig. 21 is a schematic view showing folding of a side insulating film according to an embodiment of the present application;

FIG. 22 is a schematic view of a bushing and screw of an embodiment of the present application;

FIG. 23 is a schematic view of the thermal insulation structure of a plurality of cells according to an embodiment of the present application;

FIG. 24 is a schematic diagram of a battery controller thermal control module according to an embodiment of the present application;

FIG. 25 is a schematic diagram of an antenna thermal control module according to an embodiment of the present application;

FIG. 26 is a schematic diagram of a protective cover covering a digital temperature sensor according to an embodiment of the present application;

FIG. 27 is a schematic view of a protective cover and digital temperature sensor according to an embodiment of the present application;

FIG. 28 is a schematic view of a shield according to an embodiment of the present application;

FIG. 29 is a schematic view of a fluid cooling system according to an embodiment of the present application;

FIG. 30 is a schematic view of a cooling flow path according to an embodiment of the present application;

FIG. 31 is a schematic illustration of a first cold plate and a second cold plate according to an embodiment of the present application;

FIG. 32 is a schematic diagram II of a first cold plate and a second cold plate according to an embodiment of the present application;

FIG. 33 is a schematic view of a first cooling flow path and a second cooling flow path according to an embodiment of the present application;

FIG. 34 is a schematic view of a piping connection block according to an embodiment of the present application;

FIG. 35 is a schematic view of a first cooling flow path of a first cold plate A according to an embodiment of the present application;

FIG. 36 is a schematic view of a first cooling flow path of a first cold plate B according to an embodiment of the present application;

FIG. 37 is a schematic view of a first cooling flow path of a first cold plate C according to an embodiment of the present application;

FIG. 38 is a schematic view of a first cooling flow path of a first cold plate E according to an embodiment of the present application;

FIG. 39 is a schematic view of a base and cover plate of an embodiment of the present application;

FIG. 40 is a schematic diagram of a cooling trough according to an embodiment of the present application;

FIG. 41 is a schematic view of a fluid module according to an embodiment of the present application;

fig. 42 is a satellite schematic diagram of an embodiment of the present application.

Detailed Description

The following description of the embodiments of the present application, taken in conjunction with the accompanying drawings, will clearly and fully describe the technical aspects of the present application, and it will be apparent that the described embodiments are some, but not all, embodiments of the present application. All other embodiments, which can be made by those skilled in the art based on the embodiments herein without making any inventive effort, are intended to be within the scope of the present application.

As shown in fig. 1, the star 200 of the satellite is provided with various devices, wherein the magnetic rod, the propulsion system, the battery controller, the antenna and the like are sensitive to temperature, and the external space environment affects the operation of the temperature sensitive devices. One embodiment of the present application provides a satellite thermal control system 100. The satellite thermal control system 100 includes a magnetic rod thermal control module 1, a propulsion thermal control module 2, a battery thermal control module 3, a battery controller thermal control module 4, an antenna thermal control module 5, and a general controller (not shown).

The magnetic rod thermal control module 1 is arranged on a magnetic rod of a satellite, and the magnetic rod thermal control module 1 is used for adjusting the temperature of the magnetic rod so that the magnetic rod can stably run in an external space. The propulsion thermal control module 2 is arranged on a propulsion system of the satellite, and the propulsion thermal control module 2 is used for adjusting the temperature of the propulsion system so that the propulsion system can stably operate in an external space. The battery thermal control module 3 is arranged on a battery of the satellite, and the battery thermal control module 3 is used for adjusting the temperature of the battery so that the battery can stably run in an external space and supply electric energy for electronic equipment of the satellite. The battery controller thermal control module 4 is arranged on a battery controller of the satellite, and the battery controller thermal control module 4 is used for adjusting the temperature of the battery controller so that the battery controller can stably operate in an external space. The antenna thermal control module 5 is arranged on an antenna of the satellite, and the antenna thermal control module 5 is used for adjusting the temperature of the antenna so that the antenna can stably operate in an external space.

The master controller is respectively and electrically connected with the magnetic rod thermal control module 1, the propulsion thermal control module 2, the battery thermal control module 3, the battery controller thermal control module 4 and the antenna thermal control module to control the operation of each thermal control module.

The satellite thermal control system can adjust the temperature of equipment on the satellite, so that the equipment on the satellite can be kept in a proper temperature interval, and the equipment on the satellite can be exposed in an external space environment to ensure the normal operation of the satellite.

As shown in fig. 2 and 3, in some embodiments, the magnetic rod 20 is disposed at the edge of the star 200, the magnetic rod 20 is substantially cylindrical, the magnetic rod 20 may be an existing magnetic rod, and the magnetic rod 20 is used for assisting in attitude control of a satellite. The magnetic rod thermal control module 1 is arranged on the magnetic rod 20, and the magnetic rod thermal control module 1 comprises: a magnetic bar temperature sensor 11, a magnetic bar heating plate 12 and a magnetic bar heat dissipation structure 13.

The magnetic rod temperature sensor 11 is arranged on the magnetic rod 20 and is used for detecting the temperature of the magnetic rod 20, the magnetic rod temperature sensor 11 is electrically connected with a master controller of the satellite, and the magnetic rod temperature sensor 11 sends the detected magnetic rod temperature to the master controller.

The magnetic rod heating plate 12 is disposed on the magnetic rod 20, and the magnetic rod heating plate 12 is used for heating the magnetic rod 20. The magnetic rod heating plate 12 is electrically connected with a master controller, and the master controller judges whether to start the magnetic rod heating plate 12 according to the signal of the magnetic rod temperature sensor 11. If the temperature of the magnetic rod 20 is lower than the preset value, the magnetic rod heating plate 12 is activated. Alternatively, the preset temperature range of the magnetic rod 20 is-10 to 50 ℃.

The magnetic rod heat dissipation structure 13 is disposed on the magnetic rod 20, and the magnetic rod heat dissipation structure 13 is used for reducing the influence of external space heat radiation on the magnetic rod 20. The magnetic rod heat radiation structure 13 has the characteristics of low absorptivity and high emissivity to external space heat radiation, and when the magnetic rod 20 is subjected to external space heat radiation, the temperature of the magnetic rod heat radiation structure 13 is kept within a preset range.

In the embodiment, the temperature of the magnetic rod 20 is detected by using the magnetic rod temperature sensor 11, the magnetic rod 20 is heated by using the magnetic rod heating plate 12, and the influence of external space heat radiation on the magnetic rod 20 is reduced by using the magnetic rod heat radiation structure 13, so that the magnetic rod 20 can be exposed in the external space environment without affecting the operation of satellites.

As shown in fig. 4, in some embodiments, at least two magnetic rod heating fins 12 are arranged uniformly in a circumferential direction about the axis of the magnetic rod 20 as a heating fin group. For example, the magnetic rod heating plates 12 are arc-shaped, the magnetic rod heating plates 12 can be attached to the surface of the magnetic rod 20, and the two magnetic rod heating plates 12 are uniformly distributed around the circumference of the axis of the magnetic rod 20 to form a heating plate group. The plurality of heating fin groups are sequentially arranged along the axis of the magnetic rod 20. In this embodiment, the number of the magnetic rod heating sheets 12 is ten, and the number of the magnetic rod heating sheets 12 can be set according to the requirement. The distances between the adjacent heating plate groups are equal to uniformly heat the magnetic bars 20.

As shown in fig. 5, in some embodiments, the magnetic rod heating sheet 12 includes: a film body 121 and a resistance wire 122. Alternatively, the film body 121 is a polyimide film and is disposed on the magnetic rod 20. The resistance wire 122 is disposed on the film 121, and the resistance wire 122 releases heat after being energized. The resistance wire 122 is in an S-shaped arrangement, including a straight portion 1221 and a connecting portion 1222. The plurality of straight portions 1221 are disposed in parallel with each other, and one connecting portion 1222 is disposed between adjacent straight portions 1221, and both ends of the connecting portion 1222 are connected to the adjacent straight portions 1221, respectively. The length of the straight line portion 1221 is longer than the length of the connection portion 1222, for example, the length of the straight line portion 1221 is 60cm and the length of the connection portion 1222 is 1cm.

The straight line portion 1221 is parallel to the axis of the magnetic rod 20. The magnetic effect of the magnetic rod 20 is affected by the magnetic rod heating sheet 12 after being energized, and the influence of the magnetic rod heating sheet 12 on the magnetic effect of the magnetic rod 20 can be reduced by arranging the straight line portion 1221 parallel to the axis of the magnetic rod 20.

As shown in fig. 3, in some embodiments, the magnetic rod temperature sensor 11 includes a first temperature sensor 111 and a second temperature sensor 112, both of which are disposed on the magnetic rod 20. Two temperature measuring points are arranged on the magnetic rod 20, so that the stability of temperature detection of the magnetic rod 20 is improved. The first temperature sensor 111 serves as a main temperature sensor, and the second temperature sensor 112 serves as a standby temperature sensor.

Alternatively, the first temperature sensor 111 is a thermistor temperature sensor, and the second temperature sensor 112 is a digital temperature sensor. The second temperature sensor 112 is disposed in the protective cover, so as to reduce interference of the external space environment to the digital temperature sensor.

In some embodiments, the magnetic rod heat dissipation structure 13 includes a white paint coated on the surface of the magnetic rod 20, where the white paint has a low absorptivity and a high emissivity to external space heat radiation, so that the temperature of the magnetic rod 20 remains within a preset range after the magnetic rod is subjected to the external space heat radiation.

As shown in fig. 3, in some embodiments, the magnetic rod thermal control module 1 further includes cover films 14, and two cover films 14 cover both ends of the magnetic rod 20, respectively. Optionally, the coating film 14 is an aluminized film. The coating film 14 can reduce the influence of heat radiation of the outer space on the magnetic rod 20.

In some embodiments, the magnetic rod 20 is disposed on the clip 15, and the clip 15 locks the magnetic rod 20. For example, the number of clips 15 is two, and the two clips 15 lock the magnetic bars 20, respectively. The clip 15 is used to attach to the star 200 of a satellite.

In some embodiments, a thermally conductive layer is disposed between the magnetic rod 20 and the clip 15. For example, the heat conducting layer is made of heat conducting silicone grease, so that heat of the magnetic rod 20 can be conveniently transferred to the star 200 through the clamp 15, and heat dissipation of the magnetic rod 20 is facilitated.

As shown in fig. 6 and 7, propulsion system 30 is disposed on a star 200 of a satellite. Propulsion system 30 includes a propulsion support 301, a gas cylinder 302, a flow regulator 303, a thruster 304, and a propulsion controller 305.

The gas cylinder 302, the flow regulator 303, the thruster 304 and the propulsion controller 305 may be any available devices. The gas cylinder 302, the flow regulator 303 and the propulsion controller 305 are all arranged on the propulsion bracket 301, and the propulsion bracket 301 and the thruster 304 are arranged on the star 200. The gas cylinder 302 is used for storing gas, the flow regulator 303 is communicated with the gas cylinder 302, the thruster 304 is communicated with the flow regulator 303, and the flow regulator 303 is electrically connected with the propulsion controller 305. The gas in the gas cylinder 302 is delivered to the thruster 304 through the flow regulator 303, and the thruster 304 ejects the gas for adjusting the attitude of the satellite. The propulsion controller 305 controls the opening degree of the flow regulator 303 to control the flow rate of the gas ejected from the thruster 304. The propulsion controller 305 is communicatively coupled to the overall controller and controls the operation of the propulsion system 30 in accordance with the overall controller's control signals.

The propulsion thermal control module 2 comprises: a gas cylinder temperature regulating structure 21, a flow regulator temperature regulating structure 22, a propulsion controller temperature regulating structure 23 and a propulsion bracket temperature regulating structure 24. The propulsion thermal control module 2 exposes the propulsion system 30 to the outside space environment for proper operation without affecting satellite operation.

The gas cylinder temperature adjusting structure 21 is disposed on the gas cylinder 302, and is used for adjusting the temperature of the gas cylinder 302, so that the temperature of the gas cylinder 302 is kept within a preset range. The flow regulator temperature adjusting structure 22 is disposed on the flow regulator 303, and is used for adjusting the temperature of the flow regulator 303, so as to keep the temperature of the flow regulator 303 within a preset range. The propulsion controller temperature adjusting structure 23 is disposed on the propulsion controller 305, and is used for adjusting the temperature of the propulsion controller 305 to keep the temperature of the propulsion controller 305 within a preset range. The pushing bracket temperature adjusting structure 24 is disposed on the pushing bracket 301 and is used for adjusting the temperature of the pushing bracket 301. Excessive temperature changes in the propulsion bracket 301 can affect the operation of the gas cylinder 302, the flow regulator 303, and the propulsion controller 305, and the propulsion bracket attemperation structure 24 can reduce the range of temperature changes in the propulsion bracket 301 to maintain the proper temperature of the gas cylinder 302, the flow regulator 303, and the propulsion controller 305.

Optionally, temperature sensors are disposed on the propulsion bracket 301, the gas cylinder 302, the flow regulator 303, the thruster 304, the propulsion controller 305, the pipeline of the gas cylinder 302 connected to the flow regulator 303, and the pipeline of the flow regulator 303 connected to the thruster 304, so as to detect the temperatures of the components of the propulsion system 30 in real time. The temperature sensor is in communication with the overall controller to send a detected temperature signal to the overall controller.

As shown in fig. 8, in some embodiments, the gas cylinder 302 includes a cylinder 3021 and a spherical end 3022, the cylinder 3021 being generally cylindrical, and the ends of the cylinder 3021 being provided with the spherical end 3022, respectively. The cylinder temperature adjustment structure 21 includes a first cylinder heating plate 211 and a second cylinder heating plate 212. The plurality of first air bottle heating fins 211 are uniformly distributed on the outer wall of the bottle 3021. A plurality of second cylinder heating fins 62 are provided at the spherical end 3022. The first air bottle heating plate 211 and the second air bottle heating plate 212 are electrically connected with the propulsion controller 305, and when the temperature of the air bottle 302 is lower than the preset temperature, the first air bottle heating plate 211 and the second air bottle heating plate 222 are started to heat the air bottle 302.

The cylinder attemperation structure 21 further includes a third cylinder heating tab 213, the third cylinder heating tab 213 being disposed at the spherical end 3022. The second cylinder heating plates 212 and the third cylinder heating plates 213 are alternately arranged around the axis of the cylinder 302, the plurality of second cylinder heating plates 212 are uniformly distributed around the circumference of the axis of the cylinder 302, and the plurality of third cylinder heating plates 213 are uniformly distributed around the circumference of the axis of the cylinder 302, so that the uniformity of heating the cylinder 302 is improved. The length of the third cylinder heating fin 213 is smaller than the length of the second cylinder heating fin 212. The cross-sectional diameter of the spherical end 3022 decreases gradually in a direction away from the cylinder 3021, the gap between adjacent second cylinder heating sheets 212 cannot accommodate one second cylinder heating sheet 212 any more, and a third shorter cylinder heating sheet 213 is provided between adjacent second cylinder heating sheets 212, so as to facilitate heating of the cylinder 302.

The heating plates on the gas cylinder 302 are all electrically connected with a master controller, and the master controller controls the operation of the heating plates on the gas cylinder 302 according to the temperature of the gas cylinder.

As shown in fig. 9, in some embodiments, the cylinder attemperation structure 21 further includes a first multi-layer insulation assembly 214, the first multi-layer insulation assembly 214 encasing the cylinder 302 and the heater strip on the cylinder 302. The first multi-layered insulation assembly 214 is selected from existing multi-layered insulation assemblies to reduce heat exchange between the cylinder 302 and the exterior space.

In some embodiments, one end of the gas cylinder 302 is fixedly connected to the pushing support 301, and the other end of the gas cylinder 302 is slidably connected to the pushing support 301, and the sliding connection adopts an existing sliding structure. The end of the gas cylinder 302 that is securely connected to the propulsion bracket 301 is provided with a thermal insulation layer between the gas cylinder 302 and the propulsion bracket 301 to reduce heat exchange between the gas cylinder 302 and the propulsion bracket 301. Optionally, the heat insulating layer is made of polyimide.

As shown in fig. 10, in some embodiments, the flow regulator attemperation structure 22 includes: a flow regulator heating fin 221 and a flow regulator heat sink 222.

The flow regulator heating sheet 221 is provided on the bottom surface of the flow regulator 303. The flow regulator heating plate 221 is electrically connected to the overall controller, and the flow regulator heating plate 221 is activated when the temperature of the flow regulator 303 is below a preset value. Alternatively, the number of the flow regulator heating sheets 221 is plural.

The flow regulator heat dissipation film 222 is disposed on the top surface and the side wall of the flow regulator 303, for example, the flow regulator heat dissipation film 222 covers the top surface and the side wall of the flow regulator 303. Optionally, the heat dissipation film 222 of the flow regulator is an F46 film, which has a low absorptivity and a high emissivity to external space heat radiation, so that the influence of external space heat radiation on the temperature of the flow regulator 303 can be effectively reduced.

In some embodiments, propulsion controller attemperation structure 23 includes a white paint layer that is applied to a surface of propulsion controller 305, e.g., the white paint layer covers the top surface and sidewalls of propulsion controller 305. Optionally, the white paint layer is SR-2 white paint, so that the absorption rate of external space heat radiation is low, the emissivity is high, and the influence of the external space heat radiation on the temperature of the propulsion controller 305 can be effectively reduced.

Optionally, the bottom surface of propulsion controller 305 abuts star 200 to facilitate heat exchange between propulsion controller 305 and star 200.

In some embodiments, propulsion controller attemperation structure 23 further includes a thermally conductive layer disposed on a bottom surface of propulsion controller 305. A heat conducting layer is arranged between the bottom surface of the propulsion controller 305 and the star 200, so that the heat exchange efficiency between the propulsion controller 305 and the star 200 is improved.

In some embodiments, the pusher carriage temperature conditioning structure 24 includes a second multi-layered insulation assembly that encases the top surface and sidewalls of the pusher carriage 301 to reduce heat exchange of the pusher carriage 301 with the exterior space. Alternatively, the second multi-layer insulation assembly is an existing multi-layer insulation assembly.

As shown in fig. 10, 11, and 12, in some embodiments, the propulsion thermal control module 2 further includes a first thermal insulation pad 25, a second thermal insulation pad 26, and a third thermal insulation pad 27. The first insulation pad 25 is disposed between the flow regulator 303 and the pushing bracket 301 to reduce heat exchange between the regulator 303 and the pushing bracket 301. The second insulation blanket 26 is disposed between the propulsion controller 305 and the propulsion bracket 301 to reduce heat exchange between the propulsion controller 305 and the propulsion bracket 301. The third heat insulation pad 27 is disposed on the bottom surface of the pushing bracket 301 to reduce heat exchange between the pushing bracket 301 and the star 200. Optionally, the materials of the first heat insulation pad 25, the second heat insulation pad 26 and the third heat insulation pad 27 are polyimide.

As shown in fig. 13, the battery 40 is disposed on the star 200, and the battery 40 is used to supply power to the electronic device of the satellite. Alternatively, the number of the batteries 40 is plural, for example, the number of the batteries 40 is three.

As shown in fig. 14, the battery thermal control module 3 includes: a battery temperature sensor 31, a battery heating structure 32, a battery insulating structure 33, and a battery heat dissipating structure 34.

As shown in fig. 15, the surface of the battery 40 includes a top surface 40a, a bottom surface 40b, two long side surfaces 40c, and two short side surfaces 40d. The battery temperature sensor 31 is provided on the surface of the battery 40, for example, the battery temperature sensor 31 is provided on the long side 40c of the battery 40. The battery temperature sensor 31 is used for detecting the temperature of the battery 40, and the battery temperature sensor 31 is in communication connection with the overall controller. Optionally, the battery temperature sensor 31 is a digital temperature sensor, and the protective cover covers the battery temperature sensor 31 to avoid the external space environment from affecting the operation of the battery temperature sensor 31.

The battery heating structure 32 is disposed on the long side 40c of the battery, the battery heating structure 32 is used for heating the battery 40, and the battery heating structure 32 is electrically connected with the overall controller. The battery temperature sensor 31 sends a detection signal to the overall controller, the overall controller judges whether the temperature of the battery 40 is lower than a preset temperature, and if the temperature of the battery 40 is lower than the preset temperature, the overall controller starts the battery heating structure 32 to heat the battery 40.

The battery thermal insulation structure 33 is disposed on the surface of the battery 40, and the position of the battery thermal insulation structure 33 is set according to the requirement, for example, the battery thermal insulation structure 33 covers a part of the short side 40d of the battery 40. The battery heat insulation structure 33 can reduce heat exchange between the battery 40 and the external space, and is beneficial to maintaining the battery 40 in a preset temperature range.

The battery heat dissipation structure 34 is disposed on the surface of the battery 40. The battery heat dissipation structure 34 is made of a material with low absorption and high emission to external space heat radiation, so as to reduce the influence of the external space heat radiation on the temperature of the battery 40. The battery 40 can generate heat during operation, and the high emission characteristic of the battery heat dissipation structure 34 is beneficial to cooling the battery 40.

The battery thermal control module 3 keeps the temperature of the battery 40 within a preset range, for example, 20-40 ℃, and the battery 40 can be exposed to the external space environment to ensure the normal operation of the satellite.

In some embodiments, the battery heating structure 32 includes battery heating tabs, at least one of which is disposed on each of the two long sides 40c of the battery 40. Optionally, the battery heating plate is a resistance wire heating plate. The battery heating plate is arranged on the long side 40c of the battery, so that the battery cells in the battery 40 can be heated uniformly.

As shown in fig. 16, the battery insulating structure 33 includes a third multi-layered insulating assembly that covers at least the bottom surface 40b, a portion of the long side 40c, and a portion of the short side 40d of the battery. For example, the third multi-layered heat insulating assembly includes an i-th multi-layered heat insulating assembly 331 and a ii-th multi-layered heat insulating assembly 332, the i-th multi-layered heat insulating assembly 331 covering a portion of the long side 40c and a portion of the short side 40d of the battery, and the ii-th multi-layered heat insulating assembly 332 covering the bottom surface 40b of the battery. The third multi-layered insulation assembly can reduce heat exchange between the battery 40 and the outer space and the star.

As shown in fig. 17, in some embodiments, the battery heat dissipation structure 34 is white paint 341, the white paint 341 coating the top surface 40a and at least one long side 40c of the battery 40. The white paint 341 has the characteristics of low absorption and high emission of external space heat radiation, and when the battery 40 is subjected to the external space heat radiation, the white paint 341 is beneficial to reducing the temperature of the battery 40, so that the battery 40 can work normally within a proper temperature range. Whether the other surfaces of the battery 40 are coated with white paint 341 is set according to the need, for example, the white paint 341 may coat the top surface 40a and both long sides 40c of the battery 40, and may coat the top surface 40a, one long side 40c, and part of the short sides 40d of the battery 40.

As shown in fig. 15, in some embodiments, the battery heat dissipation structure 3 further includes a heat pipe 35, and the heat pipe 35 is disposed on the long side 40c of the battery 40. Optionally, the length of heat pipe 35 is slightly less than the length of long side 40c. The battery 40 is provided with a plurality of battery cells, and the heat pipe 35 is beneficial to improving the temperature uniformity of the battery 40.

As shown in fig. 18, in some embodiments, the battery 40 includes: a housing 401 and a battery cell 402. The inside of the housing 401 is provided with a cavity, and a plurality of battery cells 402 are sequentially arranged in the housing 401.

As shown in fig. 19 and 20, the battery cell 402 includes a core 403 and an insulating film 404. The core 403 has a rectangular parallelepiped shape, the surface including a top surface 403a, a bottom surface 403b, two opposite long sides 403c, and two opposite short sides 403d. When the battery cell 402 is disposed in the housing 401, the short side 403d of the core 403 is substantially parallel to the long side 40c of the battery 40.

The insulating film needs to be folded in order to cover the core 403.

In the embodiment of the present application, in order to improve the adaptability of the battery 40 to the external space environment, the short side 403d of the core 403 needs to radiate heat, and the short side 403d of the core 403 can only be covered with one insulating film.

The insulating film 404 includes a side insulating film 4041 and a bottom insulating film 4042. The side insulating films 4041 cover four sides of the core 403, and the side insulating films 4041 are bonded to the long side 403c of the core 403 so that the insulating films 404 are closed. The top surface of the side insulating film 4041 is substantially flush with the top surface 403a of the core 403, and the bottom end of the side insulating film 4041 extends out of the bottom surface 403b of the core 403, for example, the bottom end of the side insulating film 4041 extends out of the bottom surface 403b of the core 403 by about 3mm.

As shown in fig. 21, a portion of the bottom end of the side insulating film 4041 extending out of the bottom surface 403b of the core 403 is folded toward the center of the bottom surface 403 b. The bottom insulating film 4042 is bonded to the folded portion of the side insulating film 4041 to complete the cladding of the core 403. The special folding manner of this embodiment makes the insulating film 404 have only one layer on two short sides 403d of the core 403, so that the core 403 is convenient for heat dissipation, and the problem that in the conventional battery, the insulating film has a large number of layers somewhere after folding, which is unfavorable for heat dissipation is avoided.

As shown in fig. 22, in some embodiments, the four corners of the housing 401 are provided with vertically oriented through holes 4011. The battery 40 further includes: bushing 403 and titanium alloy screw 404. Bushing 403 is positioned in throughbore 4011, bushing 403 extending out of the two end openings of throughbore 4011. Titanium alloy screws 404 penetrate into bushings 403, and titanium alloy screws 404 attach star 200 to secure battery 40 to star 200. The bushing 403 may be made of polyimide, and the titanium alloy screw 404 has a low thermal conductivity to reduce heat exchange between the battery 40 and the star 200.

As shown in fig. 13, among the plurality of cells 40, some of the cells 40 are closer to the edge of the star 200. The cells 40 at the edges of the star 200 exchange more heat with the outer space than the other cells 40.

As shown in fig. 23, the third multi-layered heat insulating assembly at the edge of the star 200 includes a third multi-layered heat insulating assembly 333, and the third multi-layered heat insulating assembly 333 covers a portion of the top surface 40a, a portion of the long side surface 40c, and a portion of the short side surface 40d of the battery 40 to reduce heat exchange between the battery 40 at the edge of the star 200 and the external space. The second multi-layer insulation assembly 332 covers the bottom surface 40b of the cell to insulate the cell from radiant heat exchange with the star 200. The remaining cells 40 are covered with a first multilayer insulation 331 and a second multilayer insulation 332.

As shown in fig. 24, in some embodiments, a battery controller 50 is used to control the operation of the battery 40. The battery controller thermal control module 4 includes: white paint 41, fourth multi-layer insulation assembly 42, and insulation pad 43. The battery controller thermal control module 4 is used to adjust the temperature of the battery controller 50. The battery controller thermal control module 4 further includes a temperature sensor disposed on the battery controller 50 to detect the temperature of the battery controller 50. The temperature sensor is communicatively connected to the overall controller to send a temperature detection signal of the battery controller 50 to the overall controller.

The white paint 41 is coated on the top surface of the battery controller 50, has the characteristic of low absorption and high emission of external space heat radiation, and is beneficial to reducing the temperature of the battery controller 50 when the battery controller 50 is subjected to the external space heat radiation.

The fourth multi-layered heat insulation assembly 42 covers sides of the battery controller 50, for example, the fourth multi-layered heat insulation assembly 42 covers three sides of the battery controller 50 to reduce heat exchange of the battery controller 50 with an external space.

The heat insulation pad 43 is disposed on the bottom surface of the battery controller 50 to reduce heat exchange between the battery controller 50 and the star 200. Optionally, the heat insulation pad 43 is made of polyimide.

The heat generated by the electronic components inside the battery controller 50 is transferred to the top surface of the battery controller 50 through the housing of the battery controller 50, and the heat is radiated outward from the top surface of the battery controller 50.

As shown in fig. 25, the antenna 60 is a Q/V band antenna, and includes a motor 601, a rotation unit 602, a lock cylinder 603, and a reflecting cover 604. The motor 601 and the rotation unit 602 are both disposed on the antenna stand 605, and the antenna stand 605 is disposed on the star 200. The reflecting cover 604 is rotatably arranged on the locking cylinder 603, and the locking cylinder 603 is arranged on the star 200. The motor 601 drives the reflection housing 604 to rotate by the rotation unit 602. For example, the rotor 602 is a decelerator.

The antenna thermal control module 5 includes: an antenna heating sheet 51, an antenna heat dissipation film 52, a fifth multilayer assembly 53, and a white paint 54. The antenna thermal control module 5 is used for adjusting the temperature of the antenna 60 so that the antenna 60 operates within a reasonable temperature range.

The antenna heating plate 51 is provided to the motor 601 of the antenna 60, and the antenna heating plate 51 is electrically connected to the overall controller. The motor 601 is provided with a temperature sensor to detect the temperature of the motor 601, and the temperature sensor is in communication connection with the overall controller. When the motor 601 is lower than the preset temperature, the master controller starts the antenna heating plate 51, and the antenna heating plate 51 can be a resistance wire heating plate. The overall controller of the satellite controls the operation of the antenna patch 51.

The antenna heat dissipation film 52 is disposed on the reflective cover 604 of the antenna, and optionally, the antenna heat dissipation film 52 is disposed on the back surface of the reflective cover 604. The antenna heat dissipation film 52 can be an F46 film, so that the absorption rate of the external space heat radiation is low, the emissivity is high, and the influence of the external space heat radiation on the temperature of the reflecting cover 604 can be effectively reduced. The area of the antenna heat dissipation film 52 covering the reflection cover 604 is set according to the need.

The fifth multilayer assembly 53 is provided on the side wall of the locking cylinder 603 of the antenna. The fifth multi-layered assembly 53 is an existing multi-layered insulation assembly to reduce heat exchange between the locking cylinder 603 and the outside space.

The white paint 54 is applied to the surface of the rotating unit 602 of the antenna, and the white paint 54 is advantageous to reduce the temperature of the rotating unit 602 when the rotating unit 602 is subjected to external space heat radiation. Optionally, the surface of the motor 601 is also coated with white paint.

A thermistor temperature sensor can be used as a temperature sensor of a satellite, but the cost of the thermistor temperature sensor is high, and a digital temperature sensor with low cost cannot withstand a space radiation environment. As shown in fig. 26, in some embodiments, the satellite thermal control system 100 further includes a protective cover 6, and when the temperature sensor is the digital temperature sensor 10, the digital temperature sensor 10 is disposed in the protective cover 6, and the protective cover 6 protects the digital temperature sensor 10.

As shown in fig. 27, the shield 6 includes: the cover 61, the accommodating groove 62 and the threading groove 63, and the accommodating groove 62 and the threading groove 63 are provided on the cover 61. The accommodating groove 62 is provided on the surface of the cover 61, for example, the accommodating groove 62 is provided on the bottom surface of the cover 61, the accommodating groove 62 may be a circular arc groove, and the probe 102 of the digital temperature sensor 10 is located in the accommodating groove 62. The threading groove 63 is provided on the side wall of the cover 61, and the threading groove 63 communicates with the accommodating groove 62. The wire through groove 63 is adapted to the signal wire 101 of the digital temperature sensor 10, the signal wire 101 passes through the wire through groove 63, and the signal wire 101 is used for outputting a detection signal.

The protective cover 6 and the digital temperature sensor 10 are adhered to equipment to be detected. The protection cover 100 covers the digital temperature sensor 10, and after the satellite is lifted off, the digital temperature sensor 10 is prevented from being exposed to the space environment, so that the digital temperature sensor 10 can still stably work after being lifted off. The cost of the digital temperature sensor 10 is lower than that of a conventional thermistor temperature sensor, reducing the cost of the satellite.

As shown in fig. 28, in some embodiments, the receiving groove 62 includes: a first receiving groove 621 and a second receiving groove 622. The bottoms of the first accommodation groove 621 and the second accommodation groove 622 are each arc-shaped. The second accommodating groove 622 is located between the first accommodating groove 621 and the threading groove 63, one end of the second accommodating groove 622 is communicated with the first accommodating groove 621, and the other end of the second accommodating groove 622 is communicated with the threading groove 63. The width D2 of the second receiving groove 622 is greater than the width D1 of the first receiving groove 621. The probe 102 is positioned in the first receiving groove 621, and the signal wire 102 sequentially passes through the second receiving groove 622 and the threading groove 63.

In some embodiments, the shield 6 further comprises a thermal insulation layer disposed on the shield body 61, e.g., the thermal insulation layer is a multi-layer thermal insulation assembly disposed on a surface of the shield body 1. The heat insulating layer plays a role in heat insulation when the protective cover 6 is subjected to heat radiation.

Optionally, the cover 61 is made of aluminum alloy or tantalum alloy, and has good radiation resistance.

As shown in fig. 29, the satellite thermal control system 100 further includes a fluid cooling system 7, the fluid cooling system 7 including a cold plate 71, a circulation pump 72, and a fluid controller 73. The fluid cooling system 7 utilizes liquid working substance to cool the heavy work load of the satellite, and improves the temperature uniformity of the satellite. The heavy duty load of the satellite is communication load, overall controller, antenna, etc.

As shown in fig. 30, the load of the satellite is provided on the cold plate 71, and the cold plate 71 may serve as a base plate of the star 200 to support the respective loads of the satellite. The cooling plate 71 is provided therein with cooling flow paths 711 open at both ends, and the cooling flow paths 711 extend below the load. In fig. 30, the broken line indicates a cooling flow path 711. The cooling flow channel inlet and the cooling flow channel outlet are both located on the surface of the cold plate 71. The heat absorption capacity of the liquid working medium is large, for example, the liquid working medium is perfluoro cyclic ether. The liquid working medium absorbs heat emitted by the load when flowing in the cooling flow channel 711, the heat absorbed by the liquid working medium is transferred to the cold plate 71, and the cold plate 71 radiates heat to the outer space to cool the load. Optionally, the cold plate 71 is made of aluminum alloy.

The circulation pump 72 is disposed on the cold plate 71, and the circulation pump 72 is connected to the cooling flow path 711 through a pipe 74, for example, an outlet of the circulation pump 72 is connected to an inlet of the cooling flow path, and an inlet of the circulation pump 72 is connected to an outlet of the cooling flow path. The circulation pump 72 can drive the flow of the liquid working medium in the cooling flow passage 711. The cooling flow channels 711 extend in turn below the respective loads of the satellite, e.g., the cooling flow channels 711 extend in turn below the propulsion system 30, the battery 40, the battery controller 50, and the antenna 60. The flow of the liquid working medium can balance the temperature of each load of the satellite, improve the temperature uniformity of the satellite and avoid the occurrence of an excessive temperature point. The circulation pump 72 may be an existing circulation pump. Optionally, the tubing 74 is a metal bellows.

A fluid controller 73 is provided on the cold plate 71, and the fluid controller 73 is electrically connected to the circulation pump 72 to control the operation of the circulation pump 72. The fluid controller 73 is communicatively coupled to a general controller of the satellite, for example, the general controller of the satellite can signal the fluid controller 73 to activate the circulation pump 72.

The cold plate 71 of the fluid cooling system 7 integrates the functions of bearing load, cooling the load and radiating heat to the outside space, and the cooling flow channels sequentially extend to the lower part of each load, so that the temperature of each position of the satellite is uniform, the occurrence of an excessive temperature point is avoided, and the stability of the satellite is improved.

As shown in fig. 31 and 32, in some embodiments, the cold plate 71 includes: a first cold plate 712 and a second cold plate 713.

As shown in fig. 33, the first cooling plate 712 is provided on a support frame of the satellite, and functions as a satellite substrate, and the circulation pump 72, the fluid controller 73, and the respective loads of the satellite are provided on the first cooling plate 712. The first cold plate is provided with a first cooling flow passage 7121, and the circulation pump 72 communicates with the first cooling flow passage 7121.

The second cold plate 713 is disposed above the load of the satellite, and the second cold plate 713 is provided with a second cooling flow passage 7131, the second cooling flow passage 7131 being connected to the first cooling flow passage 7121. The first cold plate 712 cools the load from below the load, and the second cold plate 713 cools the load from above the load, improving the cooling capacity of the cold plate 71 to the load.

Optionally, the number of the first cold plates 712 and the second cold plates 713 is plural. For example, the number of the first cold plates 712 is five, and the number of the second cold plates 713 is two. The first cooling flow channels 7121 of the first plurality of cold plates 712 and the second cooling flow channels 7131 of the second plurality of cold plates 713 are connected in series by a pipe 74 to form a cooling flow channel 711. The number of the first cold plates 712 and the second cold plates 713 is set according to the need.

In some embodiments, the two ports of the first cooling flow channel 7121 are an inlet of the first cooling flow channel 7121 and an outlet of the first cooling flow channel 7121, and the two ports of the second cooling flow channel 7131 are an inlet of the second cooling flow channel 7131 and an outlet of the second cooling flow channel 7131, respectively, and the two ports of the first cooling flow channel 7121 and the two ports of the second cooling flow channel 7131 are each provided with a pipe connection block 714 so that the first cold plate 712 and the second cold plate 713 are connected with the pipe 74.

As shown in fig. 34, the pipe connection block 714 is provided with a through hole 7141 and a screw hole 7142. The through hole 7141 communicates with the first cooling flow path 7121 or the second cooling flow path 7131. The screw hole 7142 is used for fastening with the pipe 74 by bolts.

As shown in fig. 30 and 35, the first cooling flow passage of the first cold plate a includes: a first flow-through portion 1211, a first heat sink portion 1212, a second heat sink portion 1213, and a second flow-through portion 1214.

One end of the first flow-through portion 1211 communicates with one port 121a of the first cooling flow passage, and the first flow-through portion 1211 extends along an edge of the first cold plate a.

The first heat absorbing portion 1212 communicates with the other end of the first flow-through portion 1211. The first heat sink 1212 has the same shape as the bottom surface corresponding to the load. For example, the first heat absorbing portion 1212 is located below the communication load, and the shape of the first heat absorbing portion 1212 is the same as the shape of the bottom surface of the communication load, so that the liquid working medium flowing through the first heat absorbing portion 1212 absorbs the heat of the communication load.

The second heat sink 1213 communicates with the first heat sink 1212 through a connection. The second heat absorbing portion 1213 has the same shape as the bottom surface corresponding to the load. For example, the second heat absorbing part 1213 is located under the receiving phased array antenna, and the shape of the second heat absorbing part 1213 is the same as the shape of the bottom surface of the receiving phased array antenna, so that the liquid working medium flowing through the second heat absorbing part 1213 absorbs the heat of the receiving phased array antenna. The connection portion between the second heat sink 1213 and the first heat sink 1212 extends along the edge of the first cold plate a.

One end of the second flow passage 1214 communicates with the second heat absorbing portion 1213, and the other end of the second flow passage 1214 communicates with the other port 121b of the first cooling flow passage. The second flow-through portion 1214 extends along an edge of the first cold plate a.

The connection parts among the first flow-through part 1211, the second heat absorption part 1213 and the first heat absorption part 1212 and the second flow-through part 1214 extend along the edge of the first cold plate a, which is favorable for diffusing the heat absorbed by the liquid working medium to the whole first cold plate a and facilitating the heat dissipation of the first cold plate a.

As shown in fig. 30 and 36, the first cooling flow passage of the first cold plate B includes: a third heat sink 1215, a fourth heat sink 1216, and a third flow-through portion 1217.

The third heat absorbing portion 1215 communicates with one port 121a of the first cooling flow passage. The third heat absorbing part 1215 is located below the phased array antenna power supply, and the liquid working medium flowing through the third heat absorbing part 1215 is used for absorbing heat of the phased array antenna power supply.

The fourth heat sink 1216 communicates with the third heat sink 121. The shape of the bottom surface of the fourth heat absorption portion 1216 is the same as that of the bottom surface of the corresponding load, for example, the fourth heat absorption portion 1216 is located below the transmitting phased array antenna, the shape of the bottom surface of the fourth heat absorption portion 1216 is the same as that of the bottom surface of the transmitting phased array antenna, and the liquid working medium flowing through the fourth heat absorption portion 1216 can absorb heat of the transmitting phased array antenna conveniently.

One end of the third flow-through portion 1217 communicates with the fourth heat sink 1216, and the other end of the third flow-through portion 1217 communicates with the other port 121b of the first cooling flow passage. At least a portion of the third flow portion 1217 extends along an edge of the first cold plate B to facilitate diffusion of heat absorbed by the liquid working medium to the entire first cold plate B to facilitate heat dissipation by the first cold plate B.

As shown in fig. 30 and 37, the first cooling flow passage of the first cold plate C includes: third heat sink 1215, fifth heat sink 1218, and fourth heat sink 1216.

The third heat absorbing portion 1215 communicates with one port 121a of the first cooling flow passage. The third heat absorbing portion 1215 in the first cold plate C functions the same as the third heat absorbing portion 1215 in the first cold plate B.

The fifth heat absorbing portion 1218 communicates with the third heat absorbing portion 1215. The fifth heat absorbing portion 1218 is located below the satellite master controller, and the liquid working substance flowing through the fifth heat absorbing portion 1218 can absorb heat from the satellite master controller.

The fourth heat sink 1216 communicates with the fifth geothermal section 1218, and the fourth heat sink 1216 communicates with the other port 121b of the first cooling flow path. The fourth heat sink 1216 in the first cold plate C functions the same as the fourth heat sink 1216 in the first cold plate B.

The first cooling flow channels of the first cold plate D are symmetrically arranged with the first cooling flow channels of the first cold plate A.

As shown in fig. 30 and 38, the first cooling flow passage of the first cold plate E includes: two sixth heat absorbing portions 1219. The two sixth heat absorbing parts 1219 are located at both sides of the first cold plate E, respectively, and the two sixth heat absorbing parts 1219 communicate through the connection part. One sixth heat absorbing portion 1219 communicates with one port 121a of the first cooling flow passage, and the other sixth heat absorbing portion 1219 communicates with the other port 121b of the first cooling flow passage. The sixth heat absorbing part 1219 is located below the Q/V band antenna of the satellite, and is used for absorbing heat of the Q/V band antenna. The connection portion between the two sixth heat absorbing portions 1219 transfers the heat absorbed by the liquid working medium to the entire first cold plate E, facilitating heat dissipation by the first cold plate E.

Each heat absorption part and the circulation part can be provided with a plurality of sub-flow channels, and the quantity of the sub-flow channels is set according to the requirement, so that the liquid working medium in the cooling flow channel 711 can absorb the heat of the load more effectively.

As shown in fig. 39 and 40, in some embodiments, the cold plate 71 includes: a base 715 and a cover 716. The top surface of the base 715 is provided with a cooling groove 7151. A cover plate 716 is provided on the top surface of the base body 715, and the cover plate 716 closes the top end opening of the cooling groove 7151 to form a cooling flow channel 711 having both ends opened.

As shown in fig. 41, in some embodiments, the fluid cooling system 7 further includes a reservoir 75, the reservoir 75 being in communication with the circulation pump 72. The liquid working medium is stored in the liquid storage device 75, and when the fluid cooling system 7 works, if the pressure of the liquid working medium in the cooling flow channel 711 and the circulating pump 72 fluctuates, the liquid working medium can be compensated or stored in the liquid storage device 75, so that the pressure of the liquid working medium in the cooling flow channel 711 and the circulating pump 72 is ensured to be stable, and the stability of the fluid cooling system 7 is improved. The reservoir 75 may be an existing reservoir.

In some embodiments, the fluid cooling system 7 further includes a filter 76, where the filter 76 is in communication with the circulation pump 72, and the filter 72 is configured to filter solid particles in the liquid working medium, so as to avoid solid particle impurities generated in the fluid cooling system 7 from affecting the fluid cooling system 77. The filter 76 may be an existing filter.

In some embodiments, fluid cooling system 7 further includes a fill drain valve 77, fill drain valve 77 being in communication with circulation pump 72. A fill drain valve 77 is used to fill or drain the fluid cooling system 7 with liquid working medium. The fill drain valve 77 may also be used to evacuate the fluid cooling system 7.

In some embodiments, the fluid cooling system 7 further comprises a pressure sensor (not shown) disposed in the pipeline 74 between the cooling flow channel 711 and the circulation pump 72, the pressure sensor being configured to detect the pressure of the liquid working medium in the pipeline 74, the pressure sensor being in communication with the controller 73. The pressure data detected by the pressure sensor is sent to the fluid controller 73, and the fluid controller 73 adjusts the output pressure of the circulating pump 72 according to the detected pressure data, so that the pressure of the liquid working medium in the pipeline 4 is controlled within a preset range.

Alternatively, the circulation pump 72 includes a main circulation pump 721 and a backup circulation pump 722, and an outlet of the main circulation pump 721 and an outlet of the backup circulation pump 722 are both connected to the output module 79, and the output module 79 is connected to an inlet of the cooling flow path 711. Normally the main circulation pump 721 is active and the backup circulation pump 722 is inactive. If an abnormality in the operation of the main circulation pump 721 is detected, the backup circulation pump 722 is started, and the operation of the main circulation pump 721 is stopped. The outlet of the main circulation pump 721 and the outlet of the backup circulation pump 722 are both provided with a one-way valve 78, preventing local backflow of liquid working medium from forming between the main circulation pump 721 and the backup circulation pump 722.

Optionally, the circulation pump 72, the reservoir 75, the filter 76, the filling and draining valve 77, the one-way valve 78 and the output module 79 are integrated on the base to form a fluid module, which is arranged on the cold plate 71.

The embodiment of the application provides a satellite, and the satellite includes the satellite thermal control system 100, equipment on the satellite is exposed to the outer space, and the satellite thermal control system can carry out temperature adjustment to the equipment on the satellite, guarantees the normal operating of satellite.

As shown in fig. 42, the star 200 includes a support 201, a cold plate 71 is provided on the support 201, a load of a satellite is provided on the cold plate 71, and the cold plate 71 functions as a star substrate.

The embodiments of the present application are described in detail above. Specific examples are used herein to illustrate the principles and embodiments of the present application, and the description of the above examples is only used to help understand the technical solution and core ideas of the present application. Therefore, those skilled in the art will recognize that many modifications and adaptations of the present application are possible and can be accomplished with the aid of the teaching herein within the scope of the present application. In view of the foregoing, this description should not be construed as limiting the application.

Claims

1. A satellite thermal control system, comprising:

2. The satellite thermal control system of claim 1, wherein the magnetic bar thermal control module comprises:

White paint is coated on the surface of the magnetic rod; wherein,

the magnetic rod heating plate comprises:

the film body is arranged on the magnetic rod;

3. The satellite thermal control system of claim 1, wherein the propulsion thermal control module comprises:

the propulsion controller temperature adjusting structure comprises white paint, wherein the white paint is coated on the surface of the propulsion controller and is used for adjusting the temperature of the propulsion controller;

and the pushing support temperature adjusting structure is used for adjusting the temperature of the pushing support.

4. A satellite thermal control system according to claim 3, wherein the gas cylinder comprises a body and a spherical end connected to each other, the gas cylinder attemperation structure comprising:

The first air bottle heating plate is arranged on the bottle body;

the second gas cylinder heating piece is arranged at the spherical end part;

the third gas cylinder heating plates are arranged at the spherical end parts, the length of each third gas cylinder heating plate is smaller than that of each second gas cylinder heating plate, and a plurality of second gas cylinder heating plates and a plurality of third gas cylinder heating plates are alternately arranged around the axis of each gas cylinder;

a first multi-layer insulation assembly coating the cylinder;

the flow regulator attemperation structure includes:

the flow regulator heat dissipation film is arranged on the top surface and the side surface of the flow regulator;

the pushing support temperature adjusting structure comprises a second multi-layer heat insulation assembly, and the second multi-layer heat insulation assembly wraps the top surface and the side wall of the pushing support.

5. The satellite thermal control system of claim 1, wherein the surface of the battery comprises a top surface, a bottom surface, two long sides, and two short sides; the battery thermal control module includes:

The battery heating structure comprises battery heating plates, at least one battery heating plate is arranged on two long side surfaces of the battery respectively, and the battery heating plates are used for heating the battery;

a battery insulating structure comprising a third multi-layered insulating assembly covering at least a bottom surface, a portion of a long side surface, and a portion of a short side surface of the battery;

a battery heat dissipation structure comprising a white paint applied to a top surface and at least one long side surface of the battery;

the battery includes:

a housing provided with a cavity;

the electric core, set up in the cavity, the electric core includes:

a core;

an insulating film including a side insulating film and a bottom insulating film, the side insulating film covering a side surface of the core and being folded toward a bottom center of the core, the bottom insulating film being bonded to a folded portion of the side insulating film;

a bushing provided to the housing;

titanium alloy screws penetrate into the bushings.

6. The satellite thermal control system of claim 1, wherein the battery controller thermal control module comprises:

white paint coated on the top surface of the battery controller;

7. The satellite thermal control system of claim 1, wherein the antenna thermal control module comprises:

an antenna heating plate, a motor arranged on the antenna;

an antenna heat dissipation film arranged on a reflecting cover of the antenna;

a fifth multi-layer assembly disposed on the locking cylinder of the antenna;

and white paint is coated on the surface of the rotating unit of the antenna.

8. The satellite thermal control system of claim 1, further comprising a shield for protection of the digital temperature sensor, the shield comprising:

a cover body;

the accommodating groove is arranged on the surface of the cover body;

9. The satellite thermal control system of claim 1, further comprising a fluid cooling system comprising:

the fluid controller is arranged on the cold plate and is electrically connected with the circulating pump so as to control the circulating pump; wherein,

The cold plate includes:

the second cooling plate is arranged above the load of the satellite and is provided with a second cooling flow passage, and the second cooling flow passage is connected with the first cooling flow passage; wherein,

at least one of the first cooling flow passages includes:

one end of the second flow part is communicated with the second heat absorbing part, and the other end of the second flow part is communicated with the other port of the first cooling flow passage; or,

at least one of the first cooling flow passages includes:

One end of the third flow through part is communicated with the fourth heat absorbing part, and the other end of the third flow through part is communicated with the other port of the first cooling flow passage; or,

at least one of the first cooling flow passages includes:

a fifth heat absorbing part communicated with the third heat absorbing part;

a fourth heat absorbing part communicated with the fifth geothermal part, the fourth heat absorbing part being communicated with the other port of the first cooling flow passage; or,

at least one of the first cooling flow passages includes:

two sixth heat absorbing parts which are communicated with each other, wherein one sixth heat absorbing part is communicated with one port of the first cooling flow channel, and the other sixth heat absorbing part is communicated with the other port of the first cooling flow channel;

the fluid cooling system further comprises:

the liquid storage device is communicated with the circulating pump;

10. A satellite comprising a satellite thermal control system according to any one of claims 1 to 9.