CN117382914B - Satellite thermal control system and satellite - Google Patents

Abstract

The present application relates to a satellite thermal control system and a satellite. The satellite thermal control system includes: a magnetic rod thermal control module, which is arranged on the magnetic rod of the satellite, and the magnetic rod thermal control module is used to adjust the temperature of the magnetic rod; a propulsion thermal control module, which is arranged on the propulsion system of the satellite, and the propulsion thermal control module is used to adjust the temperature of the propulsion system; a battery thermal control module, which is arranged on the battery of the satellite, and the battery thermal control module is used to adjust the temperature of the battery; a battery controller thermal control module, which is arranged on the battery controller of the satellite, and the battery controller thermal control module is used to adjust the temperature of the battery controller; an antenna thermal control module, which is arranged on the antenna of the satellite, and the antenna thermal control module is used to adjust the temperature of the antenna. The satellite thermal control system of the present application can adjust the temperature of the equipment on the satellite so that the equipment on the satellite can be exposed to the outer space environment to ensure the normal operation of the satellite.

Description

Satellite thermal control system and satellite

Technical Field

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

Background Art

Traditional satellites are equipped with equipment cabins, and all devices with temperature requirements are placed in the equipment cabins. The temperature of the equipment cabins is controlled to meet the working requirements of each device. New flat-panel satellites have eliminated the equipment cabins, and each device is placed on a substrate or support frame. Devices with temperature requirements will also be exposed to the outer space, and the environment in the outer space will affect the operation of some satellite equipment.

Summary of the invention

Based on the above problems, the present application provides a satellite thermal control system and a satellite. The satellite thermal control system can adjust the temperature of exposed equipment on the satellite so that the satellite can operate stably in outer space.

In order to achieve the above effects, the technical solutions adopted in this application are as follows:

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

A magnetic bar thermal control module is arranged on the magnetic bar of the satellite, and the magnetic bar thermal control module is used to adjust the temperature of the magnetic bar;

A propulsion thermal control module is provided in the propulsion system of the satellite, and the propulsion thermal control module is used to adjust the temperature of the propulsion system;

A battery thermal control module is provided in a battery of the satellite, and is used to adjust the temperature of the battery;

A battery controller thermal control module is provided in the battery controller of the satellite, and the battery controller thermal control module is used to adjust the temperature of the battery controller;

An antenna thermal control module, disposed at the antenna of the satellite, the antenna thermal control module being used to adjust the temperature of the antenna;

The main controller is respectively connected to the magnetic rod thermal control module, the propulsion thermal control module, the battery 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:

A magnetic bar temperature sensor, arranged on the magnetic bar, for detecting the temperature of the magnetic bar;

A magnetic rod heating plate, arranged on the magnetic rod, for heating the magnetic rod;

The magnetic bar heat dissipation structure is arranged on the magnetic bar.

According to some embodiments of the present application, at least two of the magnetic bar heating plates are evenly arranged in the circumferential direction around the axis of the magnetic bar to form a heating plate group, and a plurality of the heating plate groups are arranged in sequence along the axis of the magnetic bar.

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

A membrane body, arranged on the magnetic rod;

The resistance wire is arranged on the film body, and the resistance wire comprises a straight portion and a connecting portion. A plurality of the straight portions are arranged parallel to each other, and the connecting portions respectively connect adjacent straight portions. The straight portions are parallel to the axis of the magnetic rod.

According to some embodiments of the present application, the magnetic bar heat dissipation structure includes white paint, and the white paint is coated on the surface of the magnetic bar.

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

A gas cylinder temperature regulating structure, provided in the gas cylinder of the propulsion system, for adjusting the temperature of the gas cylinder;

A flow regulator temperature adjustment structure, provided in the flow regulator of the propulsion system, for adjusting the temperature of the flow regulator;

A propulsion controller temperature adjustment structure, provided in the propulsion controller of the propulsion system, for adjusting the temperature of the propulsion controller;

The propulsion support temperature adjustment structure is arranged on the propulsion support of the propulsion system and is used to adjust the temperature of the propulsion support.

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

A first gas cylinder heating plate, arranged on the cylinder body;

A second gas cylinder heating plate is arranged at the spherical end;

The third gas cylinder heating plate is arranged at the spherical end, the length of the third gas cylinder heating plate is less than the length of the second gas cylinder heating plate, and multiple second gas cylinder heating plates and multiple third gas cylinder heating plates are alternately arranged around the axis of the gas cylinder.

According to some embodiments of the present application, the gas cylinder temperature control structure further includes a first multi-layer thermal insulation component, and the first multi-layer thermal insulation component covers the gas cylinder.

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

A flow regulator heating plate, arranged on the bottom surface of the flow regulator;

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 temperature adjustment structure includes white paint, and the white paint is applied to the surface of the propulsion controller.

According to some embodiments of the present application, the propulsion support temperature control structure includes a second multi-layer thermal insulation component, and the second multi-layer thermal insulation component covers the top surface and side walls of the propulsion support.

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:

A battery temperature sensor is disposed on the surface of the battery and is used to detect the temperature of the battery;

A battery heating structure, disposed on a long side of the battery, and used to heat the battery;

A battery heat insulation structure, arranged on the surface of the battery;

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

According to some embodiments of the present application, the battery heating structure includes a battery heating sheet, and at least one of the battery heating sheets is respectively disposed 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 component, and the third multi-layer insulation component covers at least the bottom surface, part of the long side surface, and part of the short side surface of the battery.

According to some embodiments of the present application, the battery heat dissipation structure includes white paint, and the white paint is 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 includes:

A housing having a cavity;

A battery cell is disposed in the cavity, and the battery cell comprises:

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 toward the center of the bottom surface of the core body, and the bottom insulating film is bonded to the folded portion of the side insulating film.

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

A bushing, disposed on the housing;

A titanium alloy screw is inserted into the bushing.

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

White paint, applied to the top surface of the battery controller;

a fourth multi-layer heat insulation assembly, covering the side surfaces of the battery controller;

A thermal 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, arranged on the motor of the antenna;

An antenna heat dissipation film is arranged on the reflective cover of the antenna;

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

White paint is applied to the surface of the rotating unit of the antenna.

According to some embodiments of the present application, the satellite thermal control system further includes a protective cover for protecting the digital temperature sensor, and the protective cover includes:

Cover body;

A receiving groove is arranged on the surface of the cover body;

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

According to some embodiments of the present application, the protective cover further includes a protective cover heat insulation layer, and the protective cover heat insulation layer is arranged on the surface of the cover body.

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

A cold plate, used to carry the payload of the satellite, wherein the cold plate is provided with a cooling channel;

A circulation pump, disposed on the cold plate, the circulation pump being connected to the cooling channel;

A fluid controller is disposed on the cold plate, and the fluid controller is electrically connected to the circulation pump to control the circulation pump.

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

A first cold plate, 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 channel, and the circulating pump is connected to the first cooling channel;

The second cold plate is arranged above the payload of the satellite. The second cold plate is provided with a second cooling channel, and the second cooling channel is connected to the first cooling channel.

According to some embodiments of the present application, at least one of the first cooling channels includes:

a first circulation portion, one end of which is connected to a port of the first cooling channel;

A first heat absorbing portion having the same shape as the bottom surface of the corresponding load and connected to the other end of the first flow portion;

A second heat absorbing part, having the same shape as the bottom surface of the corresponding load and connected to the first heat absorbing part;

One end of the second circulation portion is connected to the second heat absorption portion, and the other end of the second circulation portion is connected to another port of the first cooling channel.

According to some embodiments of the present application, at least one of the first cooling channels includes:

a third heat absorbing portion, connected to a port of the first cooling channel;

A fourth heat absorbing portion, having the same shape as the bottom surface of the corresponding load and connected to the third heat absorbing portion;

One end of the third circulation portion is connected to the fourth heat absorption portion, and the other end of the third circulation portion is connected to another port of the first cooling channel.

According to some embodiments of the present application, at least one of the first cooling channels includes:

a third heat absorbing portion, connected to a port of the first cooling channel;

a fifth heat absorbing part, connected to the third heat absorbing part;

The fourth heat absorbing part is connected to the fifth geothermal part, and the fourth heat absorbing part is connected to another port of the first cooling channel.

According to some embodiments of the present application, at least one of the first cooling channels includes:

Two sixth heat absorbing parts are connected to each other, wherein one of the sixth heat absorbing parts is connected to one port of the first cooling channel, and the other sixth heat absorbing part is connected to the other port of the first cooling channel.

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

A base body provided with a cooling groove;

A cover plate is arranged on the base body, and the cover plate closes the top opening of the cooling groove to form the cooling channel.

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

A liquid reservoir connected to the circulation pump;

A filter, connected to the circulation pump, for filtering solid particles in the liquid working medium;

A filling and discharging valve connected to the circulation pump for filling or discharging liquid working medium;

A pressure sensor is arranged in the pipeline between the cooling channel and the circulating pump, and is used to detect the pressure of the liquid working medium in the pipeline. The pressure sensor is communicatively connected with the fluid controller.

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

The satellite thermal control system of the present application can adjust the temperature of the equipment on the satellite so that the equipment on the satellite can be exposed to the outer space environment to ensure the normal operation of the satellite.

BRIEF DESCRIPTION OF THE DRAWINGS

In order to more clearly illustrate the technical solution of the present application, the drawings required for use in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without exceeding the scope of protection required by the present application.

FIG1 is a schematic diagram of a satellite thermal control system according to an embodiment of the present application;

FIG2 is a schematic diagram of a magnetic bar installed on a star body according to an embodiment of the present application;

FIG3 is a schematic diagram of a magnetic rod thermal control module according to an embodiment of the present application;

FIG4 is a schematic diagram of a heating plate assembly according to an embodiment of the present application;

FIG5 is a schematic diagram of a magnetic rod heating sheet according to an embodiment of the present application;

FIG6 is a schematic diagram of a propulsion system according to an embodiment of the present application installed on a satellite;

FIG7 is a schematic diagram of a thermal control module of a propulsion system according to an embodiment of the present application;

FIG8 is a schematic diagram of a gas cylinder heating sheet according to an embodiment of the present application;

FIG9 is a schematic diagram of a first multi-layer thermal insulation assembly according to an embodiment of the present application;

FIG10 is a schematic diagram of a temperature regulating structure of a flow regulator according to an embodiment of the present application;

FIG11 is a schematic diagram of a second thermal insulation pad according to an embodiment of the present application;

Figure 12 is a schematic diagram of the third thermal insulation pad of the embodiment of the present application.

FIG13 is a schematic diagram of a battery installed on a star body according to an embodiment of the present application;

FIG14 is a schematic diagram of a battery thermal control module according to an embodiment of the present application;

FIG15 is a schematic diagram of a partial structure of a battery thermal control module according to an embodiment of the present application;

FIG16 is a schematic diagram of a battery heat insulation structure according to an embodiment of the present application;

FIG17 is a schematic diagram of a battery heat dissipation structure according to an embodiment of the present application;

FIG18 is an exploded view of a battery according to an embodiment of the present application;

FIG19 is an exploded view of a battery cell according to an embodiment of the present application;

FIG20 is a schematic diagram of a core body wrapped with a side insulating film according to an embodiment of the present application;

FIG21 is a schematic diagram of the folding of the side insulating film according to an embodiment of the present application;

FIG22 is a schematic diagram of a bushing and a screw according to an embodiment of the present application;

FIG23 is a schematic diagram of the heat insulation structure of multiple batteries according to an embodiment of the present application;

FIG24 is a schematic diagram of a thermal control module of a battery controller according to an embodiment of the present application;

FIG25 is a schematic diagram of an antenna thermal control module according to an embodiment of the present application;

FIG26 is a schematic diagram of a protective cover covering a digital temperature sensor according to an embodiment of the present application;

FIG27 is a schematic diagram of a protective cover and a digital temperature sensor according to an embodiment of the present application;

FIG28 is a schematic diagram of a protective cover according to an embodiment of the present application;

FIG29 is a schematic diagram of a fluid cooling system according to an embodiment of the present application;

FIG30 is a schematic diagram of a cooling channel according to an embodiment of the present application;

FIG31 is a schematic diagram 1 of a first cold plate and a second cold plate according to an embodiment of the present application;

FIG32 is a second schematic diagram of the first cold plate and the second cold plate according to an embodiment of the present application;

FIG33 is a schematic diagram of a first cooling channel and a second cooling channel according to an embodiment of the present application;

FIG34 is a schematic diagram of a pipeline connection block according to an embodiment of the present application;

FIG35 is a schematic diagram of a first cooling channel of a first cold plate A according to an embodiment of the present application;

FIG36 is a schematic diagram of a first cooling channel of a first cold plate B according to an embodiment of the present application;

FIG37 is a schematic diagram of a first cooling channel of a first cold plate C according to an embodiment of the present application;

FIG38 is a schematic diagram of a first cooling channel of a first cold plate E according to an embodiment of the present application;

FIG39 is a schematic diagram of a substrate and a cover plate according to an embodiment of the present application;

FIG40 is a schematic diagram of a cooling tank according to an embodiment of the present application;

FIG41 is a schematic diagram of a fluid module according to an embodiment of the present application;

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

DETAILED DESCRIPTION

The following is a clear and complete description of the technical solution of the present application in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative work are within the scope of protection of the present application.

As shown in Figure 1, a variety of devices are arranged on the satellite body 200, among which the magnetic rod, propulsion system, battery, battery controller, antenna, etc. are sensitive to temperature, and the outer space environment affects the operation of temperature-sensitive devices. An embodiment of the present application provides a satellite thermal control system 100, which 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 master controller (not shown in the figure).

The magnetic rod thermal control module 1 is arranged on the magnetic rod of the satellite, and the magnetic rod thermal control module 1 is used to adjust the temperature of the magnetic rod so that the magnetic rod can operate stably in outer space. The propulsion thermal control module 2 is arranged on the propulsion system of the satellite, and the propulsion thermal control module 2 is used to adjust the temperature of the propulsion system so that the propulsion system can operate stably in outer space. The battery thermal control module 3 is arranged on the battery of the satellite, and the battery thermal control module 3 is used to adjust the temperature of the battery so that the battery can operate stably in outer space and provide electrical energy for the satellite's electronic equipment. The battery controller thermal control module 4 is arranged on the battery controller of the satellite, and the battery controller thermal control module 4 is used to adjust the temperature of the battery controller so that the battery controller can operate stably in outer space. The antenna thermal control module 5 is arranged on the antenna of the satellite, and the antenna thermal control module 5 is used to adjust the temperature of the antenna so that the antenna can operate stably in outer space.

The master controller is electrically connected to 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 respectively to control the operation of each thermal control module.

The satellite thermal control system of the present application can adjust the temperature of the equipment on the satellite to keep the equipment on the satellite in a suitable temperature range. The equipment on the satellite can be exposed to the outer space environment to ensure the normal operation of the satellite.

As shown in FIG. 2 and FIG. 3 , in some embodiments, a magnetic bar 20 is disposed at the edge of a satellite 200. The magnetic bar 20 is substantially cylindrical. The magnetic bar 20 may be an existing magnetic bar. The magnetic bar 20 is used to assist the attitude control of the satellite. A magnetic bar thermal control module 1 is disposed on the magnetic bar 20. The magnetic bar thermal control module 1 includes: a magnetic bar temperature sensor 11, a magnetic bar heating sheet 12, and a magnetic bar heat dissipation structure 13.

The magnetic bar temperature sensor 11 is arranged on the magnetic bar 20 and is used to detect the temperature of the magnetic bar 20. The magnetic bar temperature sensor 11 is electrically connected to the main controller of the satellite, and the magnetic bar temperature sensor 11 sends the detected magnetic bar temperature to the main controller.

The magnetic rod heating plate 12 is arranged on the magnetic rod 20, and the magnetic rod heating plate 12 is used to heat the magnetic rod 20. The magnetic rod heating plate 12 is electrically connected to the main controller, and the main controller determines 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 started. Optionally, the preset temperature range of the magnetic rod 20 is -10 to 50°C.

The magnetic bar heat dissipation structure 13 is arranged on the magnetic bar 20, and the magnetic bar heat dissipation structure 13 is used to reduce the influence of heat radiation from the external space on the magnetic bar 20. The magnetic bar heat dissipation structure 13 has the characteristics of low absorptivity and high emissivity to heat radiation from the external space. When the magnetic bar 20 is subjected to heat radiation from the external space, the temperature of the magnetic bar heat dissipation structure 13 is maintained within a preset range.

In this embodiment, a magnetic bar temperature sensor 11 is used to detect the temperature of the magnetic bar 20, a magnetic bar heating plate 12 is used to heat the magnetic bar 20, and a magnetic bar heat dissipation structure 13 is used to reduce the influence of outer space thermal radiation on the magnetic bar 20, so that the magnetic bar 20 can be exposed to the outer space environment without affecting the operation of the satellite.

As shown in FIG4 , in some embodiments, at least two magnetic rod heating plates 12 are evenly arranged in the circumferential direction around the axis of the magnetic rod 20 to form a heating plate group. For example, the magnetic rod heating plate 12 is in the shape of an arc, and the magnetic rod heating plate 12 can be attached to the surface of the magnetic rod 20, and the two magnetic rod heating plates 12 are evenly distributed around the axis of the magnetic rod 20 to form a heating plate group. Multiple heating plate groups are arranged in sequence along the axis of the magnetic rod 20. In this embodiment, the number of magnetic rod heating plates 12 is ten, and the number of magnetic rod heating plates 12 can be set according to demand. The distance between adjacent heating plate groups is equal so that the magnetic rod 20 is evenly heated.

As shown in FIG5 , in some embodiments, the magnetic rod heating sheet 12 includes: a film body 121 and a resistance wire 122. Optionally, the film body 121 is a polyimide film, which is arranged on the magnetic rod 20. The resistance wire 122 is arranged on the film body 121, and releases heat after the resistance wire 122 is energized. The resistance wire 122 is arranged in an S shape, including a straight portion 1221 and a connecting portion 1222. A plurality of straight portions 1221 are arranged in parallel with each other, and a connecting portion 1222 is arranged between adjacent straight portions 1221, and the two ends of the connecting portion 1222 are respectively connected to the adjacent straight portions 1221. The length of the straight portion 1221 is greater than the length of the connecting portion 1222. For example, the length of the straight portion 1221 is 60 cm, and the length of the connecting portion 1222 is 1 cm.

The straight portion 1221 is parallel to the axis of the magnetic bar 20. When the magnetic bar heating plate 12 is powered on, it affects the magnetic effect of the magnetic bar 20. Setting the straight portion 1221 to be parallel to the axis of the magnetic bar 20 can reduce the influence of the magnetic effect of the magnetic bar heating plate 12 on the magnetic bar 20.

As shown in FIG3 , in some embodiments, the magnetic bar temperature sensor 11 includes a first temperature sensor 111 and a second temperature sensor 112, and the first temperature sensor 111 and the second temperature sensor 112 are both disposed on the magnetic bar 20. Providing two temperature measurement points on the magnetic bar 20 is conducive to improving the stability of temperature detection of the magnetic bar 20. The first temperature sensor 111 serves as a main temperature sensor, and the second temperature sensor 112 serves as a backup temperature sensor.

Optionally, 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 to reduce interference of the external space environment on the digital temperature sensor.

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

As shown in FIG3 , in some embodiments, the magnetic bar thermal control module 1 further includes a coating film 14, and two coating films 14 respectively cover the two ends of the magnetic bar 20. Optionally, the coating film 14 is an aluminum-plated film. The coating film 14 can reduce the influence of heat radiation from the external space on the magnetic bar 20.

In some embodiments, the magnetic bar 20 is disposed on the clamp 15, and the clamp 15 locks the magnetic bar 20. For example, there are two clamps 15, and the two clamps 15 respectively lock the magnetic bar 20. The clamp 15 is used to connect the satellite body 200.

In some embodiments, a heat-conducting layer is provided between the magnetic bar 20 and the clamp 15. For example, the heat-conducting layer is a heat-conducting silicone grease, which facilitates the heat of the magnetic bar 20 to be transferred to the star 200 through the clamp 15, which is beneficial to the heat dissipation of the magnetic bar 20.

As shown in FIG6 and FIG7 , the propulsion system 30 is disposed on the satellite body 200. The 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 can all be selected from existing 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 satellite 200. The gas cylinder 302 is used to store gas, the flow regulator 303 is connected to the gas cylinder 302, the thruster 304 is connected to the flow regulator 303, and the flow regulator 303 is electrically connected to the propulsion controller 305. The gas in the gas cylinder 302 is transported to the thruster 304 through the flow regulator 303, and the gas ejected by the thruster 304 is used to adjust the attitude of the satellite. The propulsion controller 305 controls the opening of the flow regulator 303 to control the flow rate of the gas ejected by the thruster 304. The propulsion controller 305 is connected to the master controller in communication, and controls the operation of the propulsion system 30 according to the control signal of the master controller.

The propulsion thermal control module 2 includes: a gas cylinder temperature control structure 21, a flow regulator temperature control structure 22, a propulsion controller temperature control structure 23 and a propulsion bracket temperature control structure 24. The propulsion thermal control module 2 enables the propulsion system 30 to work normally when exposed to the outer space environment without affecting the operation of the satellite.

The gas cylinder temperature adjustment structure 21 is arranged on the gas cylinder 302, and is used to adjust the temperature of the gas cylinder 302, so that the temperature of the gas cylinder 302 is maintained within a preset range. The flow regulator temperature adjustment structure 22 is arranged on the flow regulator 303, and is used to adjust the temperature of the flow regulator 303, so that the temperature of the flow regulator 303 is maintained within a preset range. The propulsion controller temperature adjustment structure 23 is arranged on the propulsion controller 305, and is used to adjust the temperature of the propulsion controller 305, so that the temperature of the propulsion controller 305 is maintained within a preset range. The propulsion bracket temperature adjustment structure 24 is arranged on the propulsion bracket 301, and is used to adjust the temperature of the propulsion bracket 301. If the temperature change of the propulsion bracket 301 is too large, it will affect the operation of the gas cylinder 302, the flow regulator 303 and the propulsion controller 305. The propulsion bracket temperature adjustment structure 24 can reduce the temperature change range of the propulsion bracket 301, so that the gas cylinder 302, the flow regulator 303 and the propulsion controller 305 maintain a suitable temperature.

Optionally, temperature sensors are provided on the propulsion support 301, the gas cylinder 302, the flow regulator 303, the thruster 304, the propulsion controller 305, the pipeline connecting the gas cylinder 302 to the flow regulator 303, and the pipeline connecting the flow regulator 303 to the thruster 304, so as to detect the temperature of each component of the propulsion system 30 in real time. The temperature sensor is communicatively connected to the master controller to send the detected temperature signal to the master controller.

As shown in FIG8 , in some embodiments, the gas cylinder 302 includes a cylinder body 3021 and a spherical end 3022, the cylinder body 3021 is roughly cylindrical, and the spherical ends 3022 are respectively provided at both ends of the cylinder body 3021. The gas cylinder temperature adjustment structure 21 includes a first gas cylinder heating plate 211 and a second gas cylinder heating plate 212. A plurality of first gas cylinder heating plates 211 are evenly distributed on the outer wall of the cylinder body 3021. A plurality of second gas cylinder heating plates 62 are provided at the spherical end 3022. The first gas cylinder heating plate 211 and the second gas cylinder heating plate 212 are both electrically connected to the propulsion controller 305. When the temperature of the gas cylinder 302 is lower than the preset temperature, the first gas cylinder heating plate 211 and the second gas cylinder heating plate 222 are activated to heat the gas cylinder 302.

The gas cylinder temperature regulating structure 21 also includes a third gas cylinder heating plate 213, which is arranged at the spherical end 3022. The second gas cylinder heating plate 212 and the third gas cylinder heating plate 213 are alternately arranged around the axis of the gas cylinder 302, and multiple second gas cylinder heating plates 212 are evenly distributed around the circumference of the axis of the gas cylinder 302, and multiple third gas cylinder heating plates 213 are evenly distributed around the circumference of the axis of the gas cylinder 302, so as to improve the uniformity of heating the gas cylinder 302. The length of the third gas cylinder heating plate 213 is less than the length of the second gas cylinder heating plate 212. The cross-sectional diameter of the spherical end 3022 gradually decreases in the direction away from the bottle body 3021, and the gap between adjacent second gas cylinder heating plates 212 cannot accommodate another second gas cylinder heating plate 212. A shorter third gas cylinder heating plate 213 is arranged between adjacent second gas cylinder heating plates 212 to facilitate heating of the gas cylinder 302.

The heating plates on the gas cylinder 302 are all electrically connected to the main controller, and the main 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 gas cylinder temperature regulating structure 21 further includes a first multi-layer heat insulation component 214, and the first multi-layer heat insulation component 214 covers the gas cylinder 302 and the heating plate on the gas cylinder 302. The first multi-layer heat insulation component 214 uses an existing multi-layer heat insulation component to reduce heat exchange between the gas cylinder 302 and the external space.

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

As shown in FIG. 10 , in some embodiments, the flow regulator temperature adjustment structure 22 includes: a flow regulator heating plate 221 and a flow regulator heat dissipation film 222 .

The flow regulator heating plate 221 is arranged on the bottom surface of the flow regulator 303. The flow regulator heating plate 221 is electrically connected to the main controller, and the flow regulator heating plate 221 is activated when the temperature of the flow regulator 303 is lower than a preset value. Optionally, there are multiple flow regulator heating plates 221.

The flow regulator heat dissipation film 222 is disposed on the top surface and side walls of the flow regulator 303. For example, the flow regulator heat dissipation film 222 covers the top surface and side walls of the flow regulator 303. Optionally, the flow regulator heat dissipation film 222 is an F46 film, which has a low absorption rate of external space thermal radiation and a high emissivity, and can effectively reduce the influence of external space thermal radiation on the temperature of the flow regulator 303.

In some embodiments, the propulsion controller temperature adjustment structure 23 includes a white paint layer, which is coated on the surface of the propulsion controller 305. For example, the white paint layer covers the top surface and side walls of the propulsion controller 305. Optionally, the white paint layer is SR-2 white paint, which has a low absorption rate of external space thermal radiation and a high emissivity, and can effectively reduce the impact of external space thermal radiation on the temperature of the propulsion controller 305.

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

In some embodiments, the propulsion controller temperature adjustment structure 23 further includes a heat conductive layer, which is disposed on the bottom surface of the propulsion controller 305. The heat conductive layer is disposed between the bottom surface of the propulsion controller 305 and the star body 200 to improve the heat exchange efficiency between the propulsion controller 305 and the star body 200.

In some embodiments, the propulsion support temperature regulating structure 24 includes a second multi-layer insulation component, which covers the top surface and side walls of the propulsion support 301 to reduce heat exchange between the propulsion support 301 and the external space. Optionally, the second multi-layer insulation component uses an existing multi-layer insulation component.

As shown in FIGS. 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 thermal insulation pad 25 is disposed between the flow regulator 303 and the propulsion bracket 301 to reduce the heat exchange between the regulator 303 and the propulsion bracket 301. The second thermal insulation pad 26 is disposed between the propulsion controller 305 and the propulsion bracket 301 to reduce the heat exchange between the propulsion controller 305 and the propulsion bracket 301. The third thermal insulation pad 27 is disposed on the bottom surface of the propulsion bracket 301 to reduce the heat exchange between the propulsion bracket 301 and the star body 200. Optionally, the first thermal insulation pad 25, the second thermal insulation pad 26 and the third thermal insulation pad 27 are all made of polyimide.

As shown in Fig. 13, a battery 40 is disposed on the satellite 200, and the battery 40 is used to power the electronic equipment of the satellite. Optionally, there are multiple batteries 40, for example, there are three batteries 40.

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

As shown in FIG15 , 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 disposed on the surface of the battery 40, for example, the battery temperature sensor 31 is disposed on the long side surface 40c of the battery 40. The battery temperature sensor 31 is used to detect the temperature of the battery 40, and the battery temperature sensor 31 is communicatively connected with the main controller. Optionally, the battery temperature sensor 31 is a digital temperature sensor, and the protective cover covers the battery temperature sensor 31 to prevent 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 surface 40c of the battery. The battery heating structure 32 is used to heat the battery 40. The battery heating structure 32 is electrically connected to the main controller. The battery temperature sensor 31 sends a detection signal to the main controller, and the main controller determines whether the temperature of the battery 40 is lower than a preset temperature. If the temperature of the battery 40 is lower than the preset temperature, the main controller starts the battery heating structure 32 to heat the battery 40.

The battery heat insulation structure 33 is disposed on the surface of the battery 40, and the position of the battery heat insulation structure 33 is set according to the requirements, for example, the battery heat insulation structure 33 covers part of the short side surface 40d of the battery 40. The battery heat insulation structure 33 can reduce the heat exchange between the battery 40 and the external space, which is conducive to keeping the battery 40 within 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 of external heat radiation to reduce the impact of external heat radiation on the temperature of the battery 40. The battery 40 itself will generate heat when working, and the high emission characteristics of the battery heat dissipation structure 34 are conducive to cooling the battery 40.

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

In some embodiments, the battery heating structure 32 includes a battery heating sheet, and at least one battery heating sheet is respectively disposed on the two long sides 40c of the battery 40. Optionally, the battery heating sheet is a resistance wire heating sheet. The battery heating sheet is disposed on the long side 40c of the battery to facilitate uniform heating of the battery cells inside the battery 40.

As shown in FIG16 , the battery insulation structure 33 includes a third multi-layer insulation component, which covers at least the bottom surface 40b, part of the long side surface 40c, and part of the short side surface 40d of the battery. For example, the third multi-layer insulation component includes a first multi-layer insulation component 331 and a second multi-layer insulation component 332, wherein the first multi-layer insulation component 331 covers part of the long side surface 40c and part of the short side surface 40d of the battery, and the second multi-layer insulation component 332 covers the bottom surface 40b of the battery. The third multi-layer insulation component can reduce the heat exchange between the battery 40 and the external space and the celestial body.

As shown in FIG. 17 , in some embodiments, the battery heat dissipation structure 34 is painted with white paint 341, and the white paint 341 is applied to the top surface 40a and at least one long side surface 40c of the battery 40. The white paint 341 has the characteristics of low absorption and high emission of heat radiation from the external space. When the battery 40 is subjected to heat radiation from the external space, the white paint 341 is helpful to reduce the temperature of the battery 40, so that the battery 40 can operate normally within a suitable temperature range. Whether other surfaces of the battery 40 are coated with white paint 341 is set according to demand. For example, the white paint 341 can be applied to the top surface 40a and two long side surfaces 40c of the battery 40, or the top surface 40a, one long side surface 40c and part of the short side surface 40d of the battery 40 can be applied.

As shown in FIG15 , 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 the heat pipe 35 is slightly less than the length of the long side 40c. The battery 40 is provided with a plurality of battery cells, and the heat pipe 35 is conducive to improving the temperature uniformity of the plurality of battery cells inside the battery 40.

As shown in FIG18 , in some embodiments, the battery 40 includes: a housing 401 and a battery cell 402. The housing 401 has a cavity therein, and a plurality of battery cells 402 are sequentially arranged in the housing 401.

As shown in Figures 19 and 20, the battery cell 402 includes a core body 403 and an insulating film 404. The core body 403 is in a rectangular parallelepiped shape, and the surface includes a top surface 403a, a bottom surface 403b, two opposite long side surfaces 403c and two opposite short side surfaces 403d. When the battery cell 402 is arranged in the housing 401, the short side surface 403d of the core body 403 is substantially parallel to the long side surface 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 surface 403d of the core 403 is required to dissipate heat, and the short side surface 403d of the core 403 can only be covered with a layer of insulating film.

The insulating film 404 includes a side insulating film 4041 and a bottom insulating film 4042. The side insulating film 4041 covers the four sides of the core 403, and the side insulating film 4041 is bonded to the long side 403c of the core 403 to close the insulating film 404. The top surface of the side insulating film 4041 is roughly 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 3 mm.

As shown in FIG. 21 , the bottom end of the side insulating film 4041 extends out of the bottom surface 403b of the core 403 and is folded toward the center of the bottom surface 403b. The bottom insulating film 4042 is bonded to the folded portion of the side insulating film 4041 to complete the coating of the core 403. The unique folding method of this embodiment allows the insulating film 404 to have only one layer on both short sides 403d of the core 403, which facilitates the heat dissipation of the core 403 and avoids the problem in traditional batteries that the insulating film has too many layers at a certain point after the insulating film is folded, which is not conducive to heat dissipation.

As shown in FIG. 22 , in some embodiments, the four corners of the housing 401 are provided with vertical through holes 4011. The battery 40 further includes: a bushing 403 and a titanium alloy screw 404. The bushing 403 is located in the through hole 4011, and the bushing 403 extends out of the two end openings of the through hole 4011. The titanium alloy screw 404 penetrates into the bushing 403, and the titanium alloy screw 404 is connected to the star body 200 to fasten the battery 40 to the star body 200. The bushing 403 can be made of polyimide, and the titanium alloy screw 404 has a low thermal conductivity to reduce the heat exchange between the battery 40 and the star body 200.

As shown in Fig. 13, among the plurality of batteries 40, some batteries 40 are closer to the edge of the star 200. Compared with other batteries 40, the batteries 40 at the edge of the star 200 have more heat exchange with the external space.

As shown in FIG23 , the third multi-layer heat insulation assembly at the edge of the star body 200 includes a third multi-layer heat insulation assembly 333, which 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 the heat exchange between the battery 40 at the edge of the star body 200 and the external space. The second multi-layer heat insulation assembly 332 covers the bottom surface 40b of the battery to isolate the battery from the radiation heat exchange with the star body 200. The remaining batteries 40 are covered by the first multi-layer heat insulation assembly 331 and the second multi-layer heat insulation assembly 332.

As shown in FIG. 24 , in some embodiments, the battery controller 50 is used to control the operation of the battery 40. The battery controller thermal control module 4 includes: white paint 41, a fourth multi-layer thermal insulation component 42 and a thermal 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 also includes a temperature sensor, which is disposed on the battery controller 50 to detect the temperature of the battery controller 50. The temperature sensor is connected to the main controller in communication to send a temperature detection signal of the battery controller 50 to the main controller.

The white paint 41 is coated on the top surface of the battery controller 50 and has the characteristics of low absorption and high emission to external space heat radiation. When the battery controller 50 is subjected to external space heat radiation, the white paint 41 helps to reduce the temperature of the battery controller 50.

The fourth multi-layer thermal insulation component 42 covers the side surfaces of the battery controller 50 . For example, the fourth multi-layer thermal insulation component 42 covers three side surfaces of the battery controller 50 to reduce heat exchange between the battery controller 50 and the 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 body 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 outer shell of the battery controller 50, and the heat is dissipated outward from the top surface of the battery controller 50.

As shown in FIG25 , the antenna 60 is a Q/V band antenna, comprising a motor 601, a rotating unit 602, a locking cylinder 603 and a reflector 604. The motor 601 and the rotating unit 602 are both disposed on an antenna bracket 605, and the antenna bracket 605 is disposed on the star body 200. The reflector 604 is rotatably disposed on the locking cylinder 603, and the locking cylinder 603 is disposed on the star body 200. The motor 601 drives the reflector 604 to rotate through the rotating unit 602. For example, the rotating unit 602 is a reducer.

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

The antenna heating plate 51 is arranged on the motor 601 of the antenna 60, and the antenna heating plate 51 is electrically connected to the main controller. A temperature sensor is arranged on the motor 601 to detect the temperature of the motor 601, and the temperature sensor is connected to the main controller for communication. When the motor 601 is lower than the preset temperature, the main controller starts the antenna heating plate 51, and the antenna heating plate 51 can be a resistance wire heating plate. The satellite's main controller controls the antenna heating plate 51 to work.

The antenna heat dissipation film 52 is arranged on the reflector 604 of the antenna. Optionally, the antenna heat dissipation film 52 is arranged on the back of the reflector 604. The antenna heat dissipation film 52 can be made of F46 film, which has a low absorption rate of external space heat radiation and a high emissivity, and can effectively reduce the influence of external space heat radiation on the temperature of the reflector 604. The area of the reflector 604 covered by the antenna heat dissipation film 52 is set according to demand.

The fifth multi-layer component 53 is disposed on the side wall of the locking tube 603 of the antenna. The fifth multi-layer component 53 uses an existing multi-layer heat insulation component to reduce the heat exchange between the locking tube 603 and the external space.

The white paint 54 is coated on the surface of the rotating unit 602 of the antenna. When the rotating unit 602 is subjected to heat radiation from the outer space, the white paint 54 helps to reduce the temperature of the rotating unit 602. Optionally, the surface of the motor 601 is also coated with white paint.

The temperature sensor of the satellite may use a thermistor temperature sensor, but the thermistor temperature sensor is relatively expensive, and the low-cost digital temperature sensor cannot withstand the space radiation environment. As shown in FIG26 , in some embodiments, the satellite thermal control system 100 further includes a protective cover 6 , and when the temperature sensor is a 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 FIG27 , the protective cover 6 includes: a cover body 61, a receiving groove 62 and a threading groove 63, and the receiving groove 62 and the threading groove 63 are both arranged on the cover body 61. The receiving groove 62 is arranged on the surface of the cover body 61, for example, the receiving groove 62 is arranged on the bottom surface of the cover body 61, and the receiving groove 62 can be an arc groove, and the probe 102 of the digital temperature sensor 10 is located in the receiving groove 62. The threading groove 63 is arranged on the side wall of the cover body 61, and the threading groove 63 is connected with the receiving groove 62. The threading groove 63 is adapted to the signal line 101 of the digital temperature sensor 10, and the signal line 101 passes through the threading groove 63, and the signal line 101 is used to output the detection signal.

The protective cover 6 and the digital temperature sensor 10 are both bonded to the equipment to be detected. The protective cover 100 covers the digital temperature sensor 10, and after the satellite is launched, the digital temperature sensor 10 is prevented from being exposed to the space environment, so that the digital temperature sensor 10 can still work stably after launch. The cost of the digital temperature sensor 10 is lower than that of a traditional thermistor temperature sensor, which reduces 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 receiving groove 621 and the second receiving groove 622 are both arc-shaped. The second receiving groove 622 is located between the first receiving groove 621 and the threading groove 63, one end of the second receiving groove 622 is connected to the first receiving groove 621, and the other end of the second receiving groove 622 is connected to 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 located in the first receiving groove 621, and the signal line 102 passes through the second receiving groove 622 and the threading groove 63 in sequence.

In some embodiments, the protective cover 6 further includes a heat insulation layer, which is disposed on the cover body 61. For example, the heat insulation layer is a multi-layer heat insulation component, which is disposed on the surface of the cover body 1. When the protective cover 6 is subjected to heat radiation, the heat insulation layer plays a role of heat insulation.

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

As shown in FIG29 , the satellite thermal control system 100 further includes a fluid cooling system 7, which includes a cold plate 71, a circulating pump 72, and a fluid controller 73. The fluid cooling system 7 uses liquid working fluid to cool the satellite's large loads to improve the temperature uniformity of the satellite. The satellite's large loads include communication loads, a master controller, and antennas.

As shown in Figure 30, the satellite's payload is set on the cold plate 71, and the cold plate 71 can serve as the substrate of the satellite 200 to support the various payloads of the satellite. A cooling channel 711 with openings at both ends is arranged inside the cold plate 71, and the cooling channel 711 extends to the bottom of the payload. The dotted line in Figure 30 is the cooling channel 711. The cooling channel inlet and the cooling channel outlet are both located on the surface of the cold plate 71. The liquid working fluid has a large heat absorption capacity. For example, the liquid working fluid is perfluorocyclic ether. When the liquid working fluid flows in the cooling channel 711, it absorbs the heat emitted by the load. The heat absorbed by the liquid working fluid is transferred to the cold plate 71, and the cold plate 71 radiates heat to the external space to cool the load. Optionally, the cold plate 71 is made of aluminum alloy.

The circulating pump 72 is arranged on the cold plate 71, and the circulating pump 72 is connected to the cooling channel 711 through the pipeline 74. For example, the outlet of the circulating pump 72 is connected to the inlet of the cooling channel, and the inlet of the circulating pump 72 is connected to the outlet of the cooling channel. The circulating pump 72 can drive the liquid working medium in the cooling channel 711 to flow. The cooling channel 711 extends to the bottom of each payload of the satellite in sequence. For example, the cooling channel 711 extends to the bottom of the propulsion system 30, the battery 40, the battery controller 50 and the antenna 60 in sequence. The flow of liquid working medium can balance the temperature of each payload of the satellite, improve the temperature uniformity of the satellite, and avoid the occurrence of excessively high temperature points. The circulating pump 72 can use an existing circulating pump. Optionally, the pipeline 74 is a metal bellows.

The fluid controller 73 is disposed on the cold plate 71 and is electrically connected to the circulation pump 72 to control the circulation pump 72. The fluid controller 73 is communicatively connected to the satellite's master controller. For example, the satellite's master controller can send a signal to the fluid controller 73 to start the circulation pump 72.

The cold plate 71 of the fluid cooling system 7 integrates the functions of bearing the load, cooling the load and dissipating heat to the external space. The cooling flow channel extends to the bottom of each load in turn to make the temperature of each position of the satellite more uniform, avoid the occurrence of excessively high temperature points, and improve the stability of the satellite.

As shown in FIGS. 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 FIG33 , the first cold plate 712 is disposed on the support frame of the satellite and serves as a satellite substrate. The circulation pump 72, the fluid controller 73 and various loads of the satellite are all disposed on the first cold plate 712. The first cold plate is provided with a first cooling channel 7121, and the circulation pump 72 is connected to the first cooling channel 7121.

The second cold plate 713 is disposed above the payload of the satellite, and is provided with a second cooling channel 7131, which is connected to the first cooling channel 7121. The first cold plate 712 cools the payload from below, and the second cold plate 713 cools the payload from above, thereby improving the cooling capacity of the cold plate 71 for the payload.

Optionally, the number of the first cold plate 712 and the number of the second cold plate 713 are both multiple. For example, the number of the first cold plate 712 is five, and the number of the second cold plate 713 is two. The first cooling channels 7121 of the multiple first cold plates 712 and the second cooling channels 7131 of the multiple second cold plates 713 are connected in series through the pipeline 74 to form the cooling channel 711. The number of the first cold plate 712 and the second cold plate 713 is set according to demand.

In some embodiments, the two ports of the first cooling channel 7121 are respectively the inlet of the first cooling channel 7121 and the outlet of the first cooling channel 7121, and the two ports of the second cooling channel 7131 are respectively the inlet of the second cooling channel 7131 and the outlet of the second cooling channel 7131, and both ports of the first cooling channel 7121 and the two ports of the second cooling channel 7131 are provided with pipeline connecting blocks 714 to facilitate the connection of the first cold plate 712 and the second cold plate 713 with the pipeline 74.

As shown in Fig. 34, the pipeline connection block 714 is provided with a through hole 7141 and a threaded hole 7142. The through hole 7141 is connected to the first cooling channel 7121 or the second cooling channel 7131. The threaded hole 7142 is used for fastening and connecting with the pipeline 74 by bolts.

As shown in FIGS. 30 and 35 , the first cooling channel of the first cold plate A includes a first circulation portion 1211 , a first heat absorbing portion 1212 , a second heat absorbing portion 1213 and a second circulation portion 1214 .

One end of the first circulation portion 1211 is connected to a port 121 a of the first cooling channel, and the first circulation portion 1211 extends along an edge of the first cold plate A.

The first heat absorbing portion 1212 is connected to the other end of the first circulation portion 1211. The first heat absorbing portion 1212 has the same shape as the bottom surface of the corresponding 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 bottom surface shape 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 absorbing part 1213 is connected to the first heat absorbing part 1212 through a connecting part. The second heat absorbing part 1213 has the same shape as the bottom surface of the corresponding load. For example, the second heat absorbing part 1213 is located below the receiving phased array antenna, and the shape of the second heat absorbing part 1213 is the same as the bottom surface shape of the receiving phased array antenna, so that the liquid working fluid flowing through the second heat absorbing part 1213 absorbs the heat of the receiving phased array antenna. The connecting part between the second heat absorbing part 1213 and the first heat absorbing part 1212 extends along the edge of the first cold plate A.

One end of the second circulation portion 1214 is connected to the second heat absorbing portion 1213 , and the other end of the second circulation portion 1214 is connected to the other port 121 b of the first cooling channel.

The first circulation portion 1211 , the second heat absorbing portion 1213 , the connecting portion between the first heat absorbing portion 1212 , and the second circulation portion 1214 all extend along the edge of the first cold plate A, which is beneficial for diffusing the heat absorbed by the liquid working medium to the entire first cold plate A, thereby facilitating heat dissipation of the first cold plate A.

As shown in FIGS. 30 and 36 , the first cooling channel of the first cold plate B includes a third heat absorbing portion 1215 , a fourth heat absorbing portion 1216 and a third circulation portion 1217 .

The third heat absorbing portion 1215 is connected to a port 121a of the first cooling channel. The third heat absorbing portion 1215 is located below the phased array antenna power supply, and the liquid working medium flowing through the third heat absorbing portion 1215 is used to absorb the heat of the phased array antenna power supply.

The fourth heat absorbing portion 1216 is connected to the third heat absorbing portion 121. The fourth heat absorbing portion 1216 has the same shape as the bottom surface of the corresponding load. For example, the fourth heat absorbing portion 1216 is located below the transmitting phased array antenna. The fourth heat absorbing portion 1216 has the same shape as the bottom surface of the transmitting phased array antenna, so that the liquid working fluid flowing through the fourth heat absorbing portion 1216 can absorb the heat of the transmitting phased array antenna.

One end of the third circulation part 1217 is connected to the fourth heat absorbing part 1216, and the other end of the third circulation part 1217 is connected to another port 121b of the first cooling channel. At least part of the third circulation part 1217 extends from the edge of the first cold plate B, which is conducive to diffusing the heat absorbed by the liquid working medium to the entire first cold plate B, so as to facilitate heat dissipation of the first cold plate B.

As shown in FIGS. 30 and 37 , the first cooling channel of the first cold plate C includes a third heat absorbing portion 1215 , a fifth heat absorbing portion 1218 and a fourth heat absorbing portion 1216 .

The third heat absorbing part 1215 is connected to a port 121a of the first cooling channel. The function of the third heat absorbing part 1215 in the first cold plate C is the same as that of the third heat absorbing part 1215 in the first cold plate B.

The fifth heat absorbing part 1218 is connected to the third heat absorbing part 1215. The fifth heat absorbing part 1218 is located below the satellite master controller, and the liquid working medium flowing through the fifth heat absorbing part 1218 can absorb the heat of the satellite master controller.

The fourth heat absorbing part 1216 is connected to the fifth geothermal part 1218 and is connected to the other port 121b of the first cooling channel. The function of the fourth heat absorbing part 1216 in the first cold plate C is the same as that of the fourth heat absorbing part 1216 in the first cold plate B.

The first cooling channel of the first cold plate D and the first cooling channel of the first cold plate A are symmetrically arranged.

As shown in Figures 30 and 38, the first cooling channel of the first cold plate E includes: two sixth heat absorbing parts 1219. The two sixth heat absorbing parts 1219 are respectively located on both sides of the first cold plate E, and the two sixth heat absorbing parts 1219 are connected through a connecting part. One sixth heat absorbing part 1219 is connected to a port 121a of the first cooling channel, and the other sixth heat absorbing part 1219 is connected to another port 121b of the first cooling channel. The sixth heat absorbing part 1219 is located below the Q/V band antenna of the satellite and is used to absorb the heat of the Q/V band antenna. The connecting part between the two sixth heat absorbing parts 1219 transfers the heat absorbed by the liquid working fluid to the entire first cold plate E, so as to facilitate the heat dissipation of the first cold plate E.

Each heat absorption part and the circulation part may be provided with a plurality of sub-channels, and the number of sub-channels is set according to demand, which is conducive to the liquid working medium in the cooling channel 711 to absorb the heat of the load more effectively.

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

As shown in FIG. 41 , in some embodiments, the fluid cooling system 7 further includes a liquid reservoir 75, and the liquid reservoir 75 is connected to the circulation pump 72. The liquid reservoir 75 stores liquid working medium. When the fluid cooling system 7 is working, if the pressure of the liquid working medium in the cooling channel 711 and the circulation pump 72 fluctuates, the liquid reservoir 75 can compensate or contain the liquid working medium to ensure that the pressure of the liquid working medium in the cooling channel 711 and the circulation pump 72 is stable, thereby improving the stability of the fluid cooling system 7. The liquid reservoir 75 can use an existing liquid reservoir.

In some embodiments, the fluid cooling system 7 further includes a filter 76, which is connected to the circulation pump 72 and is used to filter solid particles in the liquid working medium to prevent the solid particle impurities generated in the cooling system 7 from affecting the fluid cooling system 77. The filter 76 can be an existing filter.

In some embodiments, the fluid cooling system 7 further includes a filling and discharging valve 77, which is connected to the circulation pump 72. The filling and discharging valve 77 is used to fill or discharge the liquid working medium in the fluid cooling system 7. The filling and discharging valve 77 can also be used to evacuate the fluid cooling system 7.

In some embodiments, the fluid cooling system 7 further includes a pressure sensor (not shown in the figure), which is disposed in the pipeline 74 between the cooling channel 711 and the circulating pump 72, and is used to detect the pressure of the liquid working medium in the pipeline 74, and the pressure sensor is communicatively connected 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, which is conducive to controlling the pressure of the liquid working medium in the pipeline 4 within a preset range.

Optionally, the circulation pump 72 includes a main circulation pump 721 and a standby circulation pump 722, and the outlets of the main circulation pump 721 and the standby circulation pump 722 are both connected to the output module 79, and the output module 79 is connected to the inlet of the cooling channel 711. Under normal circumstances, the main circulation pump 721 works and the standby circulation pump 722 does not work. If it is detected that the main circulation pump 721 works abnormally, the standby circulation pump 722 is started and the main circulation pump 721 is stopped. The outlets of the main circulation pump 721 and the standby circulation pump 722 are both provided with a one-way valve 78 to prevent the local reflux of the liquid working medium between the main circulation pump 721 and the standby circulation pump 722.

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

An embodiment of the present application provides a satellite, which includes the satellite thermal control system 100 as described above. The equipment on the satellite is exposed to outer space, and the satellite thermal control system can adjust the temperature of the equipment on the satellite to ensure the normal operation of the satellite.

As shown in FIG. 42 , the satellite body 200 includes a support frame 201 , a cold plate 71 is disposed on the support frame 201 , a payload of the satellite is disposed on the cold plate 71 , and the cold plate 71 serves as a substrate of the satellite body.

The embodiments of the present application are described in detail above. Specific examples are used herein to illustrate the principles and implementation methods of the present application. The description of the above embodiments is only used to help understand the technical solution and core ideas of the present application. Therefore, changes or deformations made by those skilled in the art based on the ideas of the present application, the specific implementation methods and the scope of application of the present application, all belong to the scope of protection of the present application. In summary, the contents of this specification should not be construed as limiting the present application.

Claims (10)

1. A satellite thermal control system for a satellite, wherein a magnetic rod, a propulsion system, a battery controller, and an antenna of the satellite are all exposed to an external space, the 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.

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

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;

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;

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.

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

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 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 the gas cylinder;

a first multi-layer insulation assembly coating the cylinder;

the flow regulator attemperation structure includes:

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

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

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;

The insulation film comprises a side insulation film and a bottom insulation film, wherein the side insulation film covers the side surface of the core body and is folded towards the center of the bottom surface of the core body, the bottom insulation film is adhered to the folded part of the side insulation film, and the insulation film is formed in one layer on two short side surfaces of the core body;

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;

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.

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;

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

9. The satellite thermal control system of claim 1, further comprising 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;

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 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; wherein,

At least one of the first cooling flow passages includes:

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;

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 alternatively

At least one of the first cooling flow passages includes:

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;

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 alternatively

At least one of the first cooling flow passages includes:

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

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

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

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;

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.

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