CN107856886B - Thermal control device of cold air propulsion module outside satellite cabin - Google Patents
Thermal control device of cold air propulsion module outside satellite cabin Download PDFInfo
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- CN107856886B CN107856886B CN201711138911.0A CN201711138911A CN107856886B CN 107856886 B CN107856886 B CN 107856886B CN 201711138911 A CN201711138911 A CN 201711138911A CN 107856886 B CN107856886 B CN 107856886B
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- cold air
- propulsion module
- air propulsion
- thermal control
- control device
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- 238000009413 insulation Methods 0.000 claims abstract description 36
- 239000011888 foil Substances 0.000 claims description 16
- 229910052782 aluminium Inorganic materials 0.000 claims description 12
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 12
- 229920000728 polyester Polymers 0.000 claims description 6
- 229920006267 polyester film Polymers 0.000 claims description 6
- 239000000463 material Substances 0.000 claims description 4
- 239000004642 Polyimide Substances 0.000 claims description 3
- 239000011152 fibreglass Substances 0.000 claims description 3
- 239000004033 plastic Substances 0.000 claims description 3
- 229920003023 plastic Polymers 0.000 claims description 3
- 229920001721 polyimide Polymers 0.000 claims description 3
- 239000004677 Nylon Substances 0.000 claims description 2
- 229920001778 nylon Polymers 0.000 claims description 2
- 238000010248 power generation Methods 0.000 abstract 1
- 230000005855 radiation Effects 0.000 description 7
- 238000010521 absorption reaction Methods 0.000 description 5
- 238000001816 cooling Methods 0.000 description 4
- 229910052751 metal Inorganic materials 0.000 description 4
- 239000002184 metal Substances 0.000 description 4
- 238000005485 electric heating Methods 0.000 description 3
- 238000010438 heat treatment Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000003292 glue Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000003647 oxidation Effects 0.000 description 1
- 238000007254 oxidation reaction Methods 0.000 description 1
- 125000006850 spacer group Chemical group 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/40—Arrangements or adaptations of propulsion systems
- B64G1/409—Unconventional spacecraft propulsion systems
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Control Of Resistance Heating (AREA)
- Mattresses And Other Support Structures For Chairs And Beds (AREA)
Abstract
The invention relates to the technical field of aerospace thermal control, and discloses a thermal control device of a cold air propulsion module outside a satellite cabin, wherein the cold air propulsion module is arranged on a satellite cabin board through a fastener, and the thermal control device comprises: the solar energy power generation system comprises a positive temperature coefficient thermistor heater, a heat insulation pad and a multi-layer heat insulation assembly, wherein the positive temperature coefficient thermistor heater covers the outer surface of the cold air propulsion module, the multi-layer heat insulation assembly wraps the positive temperature coefficient thermistor heater and the outer side of the cold air propulsion module, and the heat insulation pad is arranged between a fastener and a satellite cabin plate and between the satellite cabin plate and the cold air propulsion module. The invention adopts the positive temperature coefficient thermistor heater with self-adaptive temperature control capability to heat before the cold air propulsion module works, does not need a thermal control controller and a temperature sensor, has simple system, reduces the cost and increases the reliability of the thermal control device.
Description
Technical Field
The invention relates to the technical field of aviation thermal control, in particular to a thermal control device of a satellite off-cabin cold air propulsion module.
Background
The cold air propulsion module outside the satellite cabin is directly influenced by the background of the cold and black space, the direct solar radiation heat flow, the earth albedo heat flow, the earth infrared radiation heat flow and the star infrared radiation heat flow, a thermal control device is needed to ensure that the temperature of the cold air propulsion module is controlled within a required range during in-orbit storage, and the temperature is raised to a required value before the cold air propulsion module works.
The thermal control device of the traditional satellite off-cabin cold air propulsion module consists of a passive thermal control component and an active thermal control component. The passive thermal control assembly comprises a multi-layer heat insulation assembly and a heat insulation pad; the active thermal control component comprises a negative temperature coefficient thermistor temperature sensor, a metal foil type resistance heater and a thermal control controller. The multi-layer heat insulation assembly and the heat insulation pad are used for reducing heat exchange between the external environment and the cold air propulsion module. The thermal control controller collects the temperature of the cold air propulsion module measured by the negative temperature coefficient thermistor temperature sensor, and compared with a set temperature control threshold, when the temperature of the cold air propulsion module is lower than a lower limit of the temperature control threshold, the metal foil type resistance heater is electrified, and when the temperature of the cold air propulsion module is higher than an upper limit of the temperature control threshold, the metal foil type resistance heater is powered off, so that the temperature of the cold air propulsion module is controlled within a required range. The active thermal control component adopts feedback electric heating control and comprises a negative temperature coefficient thermistor temperature sensor, a metal foil type resistance heater and a thermal control controller, and the system is complex, so that the cost is increased and the reliability of the system is affected.
Disclosure of Invention
First, the technical problem to be solved
The invention aims to provide a thermal control device of a satellite cabin outer cold air propulsion module, which solves the defects that the thermal control device in the prior art adopts feedback electric heating control, so that the system is complex, the cost is increased and the reliability of the system is affected.
(II) technical scheme
In order to solve the above technical problems, the present invention provides a thermal control device of a cold air propulsion module outside a satellite cabin, which is characterized in that the cold air propulsion module is mounted on a satellite cabin board through a fastener, and the thermal control device comprises: the solar energy cooling system comprises a positive temperature coefficient thermistor heater, a heat insulation pad and a multi-layer heat insulation assembly, wherein the positive temperature coefficient thermistor heater covers the outer surface of a cooling air propulsion module, the multi-layer heat insulation assembly wraps the positive temperature coefficient thermistor heater and the outer side of the cooling air propulsion module, and the heat insulation pad is arranged between a fastening piece and a satellite cabin plate and between the satellite cabin plate and the cooling air propulsion module.
Wherein the positive temperature coefficient thermistor heater covers more than 70% of the outer surface area of the cold air propulsion module.
Wherein, the multilayer heat insulation component comprises a bright anodic aluminum foil and a multilayer core, wherein the bright anodic aluminum foil is positioned on the outer side of the multilayer core.
Wherein the multilayer core comprises a multilayer double-sided aluminized polyester film and a multilayer polyester net spacing layer.
The multi-layer double-sided aluminized polyester film is nine-layer, and the multi-layer polyester net spacing layer is eight-layer.
The multi-layer core is arranged on the outer sides of the positive temperature coefficient thermistor heater and the cold air propulsion module through nylon buckles.
Wherein, the heat insulation pad is glass fiber reinforced plastic or polyimide plastic.
The positive temperature coefficient thermistor heater is made of a positive temperature coefficient thermistor material with the Curie temperature being 3-5 ℃ higher than the lower limit of the working temperature requirement of the cold air propulsion module.
(III) beneficial effects
The thermal control device of the cold air propulsion module outside the satellite cabin provided by the invention adopts the positive temperature coefficient thermistor heater with self-adaptive temperature control capability to heat before the cold air propulsion module works, a thermal control controller and a temperature sensor are not needed, the system is simple, the cost is reduced, and the reliability of the thermal control device is increased.
Drawings
FIG. 1 is a schematic diagram of a thermal control device of an off-board cool air propulsion module of the present invention;
FIG. 2 is a schematic view of a multi-layer insulation assembly of the present invention.
In the figure, 1, a multi-layer heat insulation assembly; 2. a heat insulating mat; 3. a positive temperature coefficient thermistor heater; 4. a cold air propulsion module; 5. a spout; 6. a satellite cabin board; 7. a fastener; 8. bright anodic oxidation aluminum foil; 9. a multi-layer core.
Detailed Description
The following describes in further detail the embodiments of the present invention with reference to the drawings and examples. The following examples are illustrative of the invention and are not intended to limit the scope of the invention.
In the description of the present invention, it should be noted that, unless explicitly specified and limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be either fixedly connected, detachably connected, or integrally connected, for example; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the present invention will be understood in specific cases by those of ordinary skill in the art.
As shown in fig. 1, the present invention discloses a thermal control device of a cold air propulsion module outside a satellite cabin, the cold air propulsion module is mounted on a satellite cabin board 6 through a fastener 7, and the thermal control device comprises: the thermal insulation system comprises a positive temperature coefficient thermistor heater 3, a thermal insulation pad 2 and a multi-layer thermal insulation assembly 1, wherein the positive temperature coefficient thermistor heater 3 covers the outer surface of a cold air propulsion module 4, the multi-layer thermal insulation assembly 1 wraps the positive temperature coefficient thermistor heater 3 and the outer side of the cold air propulsion module 4, and the thermal insulation pad 2 is arranged between a fastening piece 7 and a satellite cabin board 6 and between the satellite cabin board 6 and the cold air propulsion module 4.
Specifically, the PTC thermistor heater 3 is an active heat control assembly, and is energized before the cold air propulsion module 4 works, so as to realize an electric heating temperature control function. The insulation pad 2 is used to reduce conductive heat exchange between the satellite deck 6 and the cold air propulsion module 4. The multi-layer insulation assembly 1 is used for reducing radiation heat exchange of the cold air propulsion module 4 and the external environment. The heat insulation blanket 2 and the multi-layered heat insulation assembly 1 are used together to reduce heat loss during heating. The positive temperature coefficient thermistor heater 3 is made of a positive temperature coefficient thermistor material with the Curie temperature being 3-5 ℃ higher than the lower limit of the working temperature requirement of the cold air propulsion module 4. By utilizing the characteristics that the resistance value is increased in a nonlinear way along with the temperature and is increased in a step way when the Curie temperature is exceeded, the self-adaptive temperature control is realized, and the temperature of the cold air propulsion module 4 is controlled above the lower limit of the working temperature requirement. The positive temperature coefficient thermistor heater 3 is glued on the outer surface of the cold air propulsion module 4 by adopting heat conduction glue.
The invention discloses a thermal control device of a cold air propulsion module outside a satellite cabin, which adopts a positive temperature coefficient thermistor heater with self-adaptive temperature control capability to heat before the cold air propulsion module works, does not need a thermal control controller and a temperature sensor, has simple system, reduces the cost and increases the reliability of the thermal control device.
Wherein, positive temperature coefficient thermistor heater 3 covers the outer surface area of cold air propulsion module 4 more than 70%, under the circumstances of guaranteeing the heating effect, save material as far as possible, select the coverage area according to actual conditions.
Wherein, as shown in fig. 2, the multi-layer heat insulation assembly 1 comprises a bright anodized aluminum foil 8 and a multi-layer core 9, wherein the bright anodized aluminum foil 8 is positioned outside the multi-layer core 9. Specifically, the solar absorption ratio and the infrared hemispherical emissivity of the bright anodized aluminum foil 8 are selected according to the following formula with reference to the thermal environment of the space in which the cool air propulsion module is located, for adjusting the temperature of the cool air propulsion module 4 during in-orbit storage. The solar absorption ratio and the infrared hemispherical emissivity of the bright anodized aluminum foil 8 are calculated according to the following formula:
Wherein alpha s is solar absorption ratio, epsilon is infrared hemispherical emissivity, sigma is Stefan-Boltzmann constant, T is on-orbit storage temperature requirement of the cold air propulsion module, The angular coefficients of the surface to direct solar radiation, earth albedo, earth infrared radiation, S, R, E are the solar constant, earth albedo intensity, earth average infrared radiation intensity, respectively.
The solar absorption ratio is selected to be 0.2, the emissivity of the infrared hemisphere is 0.2, and the temperature of the cold air propulsion module 4 during in-orbit storage can be ensured to meet the requirement. A bright anodized aluminum foil 8 is mounted on the outer surface of the multi-layered core 9 by means of double-sided tape.
Preferably, the multilayer core 9 comprises a multilayer double-sided aluminized polyester film and a multilayer polyester mesh spacer layer. Preferably, the multi-layer double-sided aluminized polyester film is nine layers, and the multi-layer polyester net spacing layer is eight layers.
Preferably, the multi-layered core 9 is mounted to the outside of the ptc thermistor heater 3 and the cold air propulsion module 4 by velcro. According to the actual need, the positions of the nozzle 5 and the fastening piece 7 are not covered by the multi-layer core 9, and the bright anodized aluminum foil 8 is not arranged on the installation bottom surface of the cold air propulsion module 4.
Wherein, the heat insulation pad 2 is glass fiber reinforced plastic or polyimide plastic. For reducing conductive heat exchange between the satellite deck 6 and the cold air propulsion module 4.
The invention discloses a thermal control device of a satellite off-cabin cold air propulsion module, which consists of a multi-layer heat insulation assembly, a heat insulation pad and a positive temperature coefficient thermistor heater. The outermost layer of the multi-layer heat insulation component adopts a bright anodic aluminum foil, the solar absorption ratio and the infrared hemispherical emissivity can be selected according to the needs, the temperature of the cold air propulsion module can be ensured to meet the requirements during in-orbit storage, and the satellite power consumption is not required to be consumed. Before the cold air propulsion module works, the positive temperature coefficient thermistor heater with self-adaptive temperature control capability is adopted for heating, a thermal control controller and a temperature sensor are not needed, the system is simple, the cost is reduced, and the reliability of a thermal control device is improved.
The foregoing description of the preferred embodiments of the invention is not intended to be limiting, but rather is intended to cover all modifications, equivalents, alternatives, and improvements that fall within the spirit and scope of the invention.
Claims (5)
1. A thermal control device for a cold air propulsion module outside a satellite cabin, characterized in that the cold air propulsion module is mounted to a satellite cabin board (6) by a fastener (7), the thermal control device comprising: a positive temperature coefficient thermistor heater (3), a heat insulation pad (2) and a multi-layer heat insulation assembly (1), wherein the positive temperature coefficient thermistor heater (3) covers the outer surface of a cold air propulsion module (4), the multi-layer heat insulation assembly (1) is wrapped on the outer sides of the positive temperature coefficient thermistor heater (3) and the cold air propulsion module (4), and the heat insulation pad (2) is installed between a fastener (7) and a satellite cabin board (6) and between the satellite cabin board (6) and the cold air propulsion module (4);
the multi-layer heat insulation assembly (1) comprises a bright anodic aluminum foil (8) and a multi-layer core (9), wherein the bright anodic aluminum foil (8) is positioned on the outer side of the multi-layer core (9);
the multilayer core (9) comprises a plurality of layers of double-sided aluminized polyester films and a plurality of layers of polyester mesh spacing layers;
The multi-layer core (9) is arranged outside the positive temperature coefficient thermistor heater (3) and the cold air propulsion module (4) through nylon buckles;
the positive temperature coefficient thermistor heater (3) is energized before the cold air propulsion module (4) is operated.
2. The thermal control device of a satellite off-board cold air propulsion module according to claim 1, wherein the ptc thermistor heater (3) covers more than 70% of the outer surface area of the cold air propulsion module (4).
3. The thermal control device of the satellite off-board cool air propulsion module according to claim 1, wherein the multi-layer double-sided aluminized polyester film is nine layers, and the multi-layer polyester mesh spacing layer is eight layers.
4. The thermal control device of a satellite off-board cold air propulsion module according to claim 1, wherein the heat insulation pad (2) is glass fiber reinforced plastic or polyimide plastic.
5. The thermal control device of the satellite off-cabin cold air propulsion module according to claim 1, wherein the positive temperature coefficient thermistor heater (3) is made of a positive temperature coefficient thermistor material with the Curie temperature higher than the lower limit of the working temperature requirement of the cold air propulsion module (4) by 3-5 ℃.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711138911.0A CN107856886B (en) | 2017-11-16 | 2017-11-16 | Thermal control device of cold air propulsion module outside satellite cabin |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711138911.0A CN107856886B (en) | 2017-11-16 | 2017-11-16 | Thermal control device of cold air propulsion module outside satellite cabin |
Publications (2)
| Publication Number | Publication Date |
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| CN107856886A CN107856886A (en) | 2018-03-30 |
| CN107856886B true CN107856886B (en) | 2024-04-26 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711138911.0A Active CN107856886B (en) | 2017-11-16 | 2017-11-16 | Thermal control device of cold air propulsion module outside satellite cabin |
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| Country | Link |
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| CN (1) | CN107856886B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111498146A (en) * | 2020-06-03 | 2020-08-07 | 中国科学院微小卫星创新研究院 | Thermal control system and method for detecting and verifying satellite by near-earth orbit gravitational wave |
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| CN107856886A (en) | 2018-03-30 |
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