CN213661478U - Passive continuous power supply device for on-orbit spacecraft - Google Patents
Passive continuous power supply device for on-orbit spacecraft Download PDFInfo
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- CN213661478U CN213661478U CN202022863944.5U CN202022863944U CN213661478U CN 213661478 U CN213661478 U CN 213661478U CN 202022863944 U CN202022863944 U CN 202022863944U CN 213661478 U CN213661478 U CN 213661478U
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Abstract
The utility model provides an on-orbit spacecraft lasts power supply unit with passive, include: the heat-conducting plate, the heat shield, the thermoelectric device and the energy-storing temperature control component absorb and release heat through the phase-change material; the heat conducting plate and the heat insulation cover form a temperature control space; the thermoelectric device and the energy storage temperature control assembly are arranged in a temperature control space; one side of the thermoelectric device is attached to the heat conducting plate, and the other corresponding side of the thermoelectric device is attached to the energy storage temperature control assembly. The utility model provides a passive power supply unit that lasts for in-orbit spacecraft has solved the problem that power supply unit can't realize the electric energy and keep the fail safe nature of power supply structure when lasting the supply.
Description
Technical Field
The utility model belongs to the technical field of the spacecraft technique of on orbit and specifically relates to an utilize continuous power supply unit in the cold and hot alternating environment of using of orbit spacecraft periodicity.
Background
During the long-time in-orbit operation of spacecrafts such as satellites and spacecrafts, a large amount of electric energy consumed by various electronic devices in the spacecrafts is mainly provided by solar batteries, and the power supply mode has more defects: for example, most spacecrafts periodically enter and exit a sunshine area and a shadow area during orbital flight, and cannot generate electricity when a solar panel in an outward-suspended and unfolded state is in the shadow area, so that full-load operation of part of airborne electronic equipment is limited; furthermore, during the on-orbit operation of the spacecraft, under the action of space heat radiation such as the sun, the earth and the like and the shadow of the earth, the solar panel is subjected to periodic high and low temperature changes with larger amplitude, and the space thermal environment with alternating heat and cold generates a time-varying temperature field and temperature gradient in the structure of the solar panel, so that the structure is bent and deformed, even thermally induced to vibrate, and the structure of the solar panel is damaged.
How to effectively utilize the service environment of the cold and hot alternation of the on-orbit spacecraft, the problem of keeping the safety and the reliability of a power supply structure while realizing the continuous supply of electric energy is a worth of research.
SUMMERY OF THE UTILITY MODEL
The utility model provides an on-orbit spacecraft is with passive power supply unit that lasts aims at solving the current power supply unit and can't realize keeping the fail safe nature's of power supply structure when the electric energy lasts the supply problem.
The utility model provides an on orbit spacecraft lasts power supply unit with passive, include: the heat-conducting plate, the heat shield, the thermoelectric device and the energy-storing temperature control component absorb and release heat through the phase-change material; the heat conducting plate and the heat insulation cover form a temperature control space; the thermoelectric device and the energy storage temperature control assembly are arranged in a temperature control space; one side of the thermoelectric device is attached to the heat conducting plate, and the other corresponding side of the thermoelectric device is attached to the energy storage temperature control assembly.
Furthermore, the energy storage temperature control assembly comprises a fixing frame, a radiator, a phase change material layer and a cover plate; the radiator and the phase change material layer are both arranged inside the fixed frame; the top of the fixed frame is covered with a cover plate; the heat radiator is provided with a plurality of fins which are uniformly distributed, the phase change material layer is provided with fin holes corresponding to the fins, and the heat radiator is tightly attached to the phase change material layer through the fins and the fin holes; the phase change material layer is filled with expanded graphite/paraffin composite materials.
Further, the heat conducting plate is attached to the heat insulation pad; the heat insulation pad is provided with a first square hole, the bottom surface of the fixing frame is provided with a second square hole, the thermoelectric device is arranged in the first square hole and the second square hole, the bottom surface of the thermoelectric device is attached to the top surface of the heat conduction plate, and the top surface of the thermoelectric device is attached to the bottom surface of the radiator; and heat-conducting silicone grease is smeared on the connecting part of the thermoelectric device and the heat-conducting plate, and heat-conducting silicone grease is also smeared on the connecting part of the thermoelectric device and the radiator.
Further, a voltage conversion space is formed between the heat insulation pad and the protective cover, and a voltage conversion device is arranged in the voltage conversion space and is connected with a thermoelectric device; the voltage conversion device comprises a storage battery, a voltage inverter, a voltage stabilizing charger and a circuit integrated board, wherein the storage battery, the voltage inverter and the voltage stabilizing charger are arranged on the circuit integrated board.
Further, the thermoelectric device is electrically connected with the voltage inverter, the voltage inverter is electrically connected with the voltage stabilizing charger, and the voltage stabilizing charger is electrically connected with the storage battery.
Furthermore, the protective cover is bonded on the heat insulation plate through cured rubber, and a circular hole for circuit heat dissipation is formed in the surface of the protective cover.
Furthermore, the storage battery, the voltage inverter and the voltage stabilizing charger are all fixed on the circuit integrated board through screw connection.
Further, the radiator and the fixing frame are bonded through cured rubber.
Further, the heat conducting plate and the heat insulation pad are bonded through cured rubber.
Furthermore, threaded holes are formed in the corners of the heat conducting plate and the heat insulation pad, and the heat conducting plate and the heat insulation pad are fixed with the inner wall surface of the cabin body through screws.
According to the passive continuous power supply device for the on-orbit spacecraft, one end of a thermoelectric device is connected with the inner wall surface of a cabin body through a heat conducting plate, and the other end of the thermoelectric device is connected with an energy storage temperature control assembly; when the cabin body is irradiated by sunlight, and the temperature of the inner wall surface of the cabin body is high, heat is transmitted sequentially through the heat conduction plate, the thermoelectric device and the energy storage temperature control assembly, and finally melting in the energy storage temperature control assembly absorbs a large amount of heat, so that the temperature difference is kept at the two ends of the thermoelectric device for power generation.
When the cabin body does not receive the irradiation of sunlight, the temperature of the inner wall surface of the cabin body is low, and the phase-change material in the energy storage temperature control assembly is solidified to release a large amount of heat, so that the temperature difference is kept between the two ends of the thermoelectric device for power generation, the in-orbit spacecraft can continuously generate and store power in the whole operation process, and the defect that the solar cell panel cannot generate power when being in a shadow area is overcome.
On the other hand the device of the utility model is small and install at internal face of cabin, and the external space environment direct action of having avoided cold and hot alternation makes the structure produce bucking, deformation and heat and induces the vibration in the electricity generation structure, and this can show increase power generation facility's the labour life-span.
Further, the utility model discloses there is not any transmission mechanical device, simple structure can select single device still to establish ties the use according to specific under-deck space and electric energy demand, and the installation is convenient with the change.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the embodiments or the technical solutions in the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
Fig. 1 is an assembly view of a power supply apparatus provided by the present invention;
fig. 2 is a schematic structural diagram of the power supply device provided by the present invention.
Description of reference numerals:
1 is a heat conducting plate; 2 is a heat insulation pad, 21 is a first square hole; 3 is a heat shield; 4 is a protective cover; 5 is a thermoelectric device;
6, an energy storage temperature control assembly, 61, a fixing frame, 62, a radiator, 63, a phase change material layer, 64, a cover plate, 65, a second square hole, 66 and 67 are fin holes;
the reference numeral 7 denotes a voltage conversion device, 71 denotes a battery, 72 denotes a voltage inverter, 73 denotes a voltage-stabilizing charger, and 74 denotes a circuit board.
Detailed Description
The technical solution of the present invention will be described clearly and completely with reference to the following embodiments, and it should be understood that the described embodiments are some, but not all embodiments of the present invention. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and to simplify the description, but do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore should not be construed as limiting the present invention.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, features defined as "first", "second", may explicitly or implicitly include one or more of the described features. In the description of the present invention, "a plurality" means two or more unless specifically limited otherwise. Furthermore, the terms "mounted," "connected," and "connected" are to be construed broadly and may, for example, be fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art.
The utility model provides an on-orbit spacecraft lasts power supply unit with passive, include: the heat-conducting plate comprises a heat-conducting plate 1, a heat-insulating cover 3, a thermoelectric device 5 and an energy-storing temperature control component 6 which absorbs and releases heat through a phase-change material; the heat conducting plate 1 and the heat insulation cover 3 form a temperature control space; the thermoelectric device 5 and the energy storage temperature control assembly 6 are arranged in a temperature control space; one side of the thermoelectric device 5 is attached to the heat conducting plate 1, and the other corresponding side is attached to the energy storage temperature control component 6.
Specifically, a temperature control space is formed between the heat conducting plate 1 and the heat insulating cover 3, a thermoelectric device 5 and an energy storage temperature control component 6 are installed in the temperature control space, and the heat conducting plate 1 is attached to the heat insulating pad 2; the heat insulating pad 2 is in order to be used for preventing heat entering energy storage temperature control assembly 6, causes the damage to energy storage temperature control assembly 6, thermoelectric device 5 sets up the inside of heat insulating pad, heat insulating pad 2 can choose arbitrary thermal-insulated material can, as long as can prevent the heat and pass through heat insulating pad 2 conduction and get into energy storage temperature control assembly 6 can.
Furthermore, a first square hole 21 is formed in the heat insulation pad 2, the thermoelectric device 5 penetrates through the heat insulation pad 2 through the first square hole 21 and is connected with the top surface of the heat conduction plate 1, and the size of the first square hole 21 is consistent with that of the thermoelectric device 5, so that the lower surface of the thermoelectric device 2 can be ensured to be in good contact with the upper surface of the heat conduction plate 1; the thermal conductive silicone grease is smeared on the connecting part of the thermoelectric device 5 and the heat conducting plate 1, the interface thermal resistance between the thermoelectric device 5 and the heat conducting plate 1 is reduced by arranging the thermal conductive silicone grease, and the heat loss during the transmission between the thermoelectric device 5 and the heat conducting plate 1 is prevented, so that the performance of the thermoelectric device 5 and the heat conducting plate 1 is changed due to the rise of the temperature.
Furthermore, the heat insulation material is a silicon dioxide aerogel/glass fiber composite material which has extremely low thermal conductivity and certain mechanical strength; through setting up heat insulating mattress 2, prevent that outside temperature shock from leading to spacecraft cabin internal temperature to fluctuate by a wide margin, can prevent simultaneously again that outside cold and hot environment direct action from influencing the establishment of the 5 both ends difference in temperature of thermoelectric device on phase change material layer 63, and then influence the electricity generation.
Furthermore, threaded holes are formed in the corners of the heat conducting plate 1 and the heat insulation pad 2, and the heat conducting plate 1 and the heat insulation pad 2 are fixed to the inner wall surface of the cabin body through screws. Through the screw connection, the firmness of the connection between the device and the inner wall surface of the cabin body can be ensured.
Further, the heat-conducting plate 1 with the heat insulating mattress 2 passes through the cured rubber bonding, through the heat-conducting plate 1 with the heat insulating mattress 2 coats cured rubber and bonds, and firm in connection can also avoid other connected modes to be right the heat-conducting plate with the damage of heat insulating mattress.
Furthermore, the heat conducting plate is made of copper, and the copper has good heat conducting performance.
Particularly, heat insulating mattress 2 with constitute the control by temperature change space in the middle of the heat exchanger 3, install thermoelectric device 5 and energy storage temperature control component 6 in the control by temperature change space, thermoelectric device 5 principle is through utilizing the difference in temperature at its both ends to generate electricity, reserve temperature control component 6 can set up to the part that can adjust the temperature wantonly, thermoelectric device 5 the bottom with heat-conducting plate 1's top is connected.
Further, energy storage temperature control assembly 6 includes fixed frame 61, radiator 62, phase change material layer 63 and apron 64, radiator 62 with phase change material layer 63 all sets up fixed frame 61's inside, fixed frame 61's top lid is equipped with apron 64, fixed frame 61's material is epoxy, and epoxy has good viscidity, and the solidification is convenient, connection radiator 62 that can be better, fixed frame 61 bonds through high temperature curing rubber with heat insulating mattress 2, thermoelectric device 5's top with radiator 62's bottom is connected, thermoelectric device 5 can take optional mode with the radiator 62 laminating.
Furthermore, a second square hole 65 is formed in the bottom of the fixing frame 61, the thermoelectric device 5 passes through the second square hole 65 and is attached to the bottom of the heat sink 62, and the size of the second square hole 65 is the same as that of the thermoelectric device 5, so that the top surface of the thermoelectric device 5 can be ensured to be in good contact with the bottom surface of the heat sink 62; in addition, heat-conducting silicone grease is coated between the top surface of the thermoelectric device 5 and the bottom surface of the heat sink 62, and the heat-conducting silicone grease is arranged to reduce the interface thermal resistance between the thermoelectric device 5 and the heat sink 62, so that heat loss during the heat transfer between the thermoelectric device 5 and the heat sink 62 is prevented.
Furthermore, the top of the heat sink 62 is provided with a plurality of uniformly distributed fins 66, and by arranging the fins 66, the heat dissipation or heat absorption rate of the heat sink 62 can be increased, so that the two ends of the thermoelectric device 5 can ensure a large enough temperature difference, and the thermoelectric device 5 can generate electricity; the phase change material layer 63 is provided with fin holes 67 corresponding to the fins 66, the fins 66 correspond to the fin holes 67 by forming the fin holes 67 corresponding to the fins 66 on the phase change material layer 63, so that the heat absorption or heat release rate of the phase change material layer 63 can be increased, the two ends of the thermoelectric device 5 can ensure a large enough temperature difference, and the thermoelectric device 5 can generate electricity; the inside material of filling of phase change material layer 63 is expanded graphite paraffin combined material, expanded graphite paraffin combined material has good phase transition latent heat and thermal conductivity, can absorb a large amount of heats, when 5 one end of thermoelectric device is overheated, the heat transmits the combined material layer of the 5 other ends of thermoelectric device, the combined material layer can be quick the heat absorption, make 5 both ends of thermoelectric device keep the difference in temperature, when 5 one end of thermoelectric device is supercooled, the heat transmits the combined material layer of the 5 other ends of thermoelectric device, the heat release that the combined material layer can be quick, make 5 both ends of thermoelectric device keep the difference in temperature.
Further, the heat shield 3 covers the energy storage temperature control assembly 6 and is bonded with the heat insulation pad 2 through high-temperature curing rubber, the heat shield 3 is made of silicon dioxide aerogel/glass fiber composite materials, the heat shield 3 and the heat insulation pad 2 have excellent heat insulation performance at the same time, internal and external heat exchange can be prevented, the internal temperature stability of the spacecraft cabin is maintained, the external space environment with cold and hot alternation is prevented from being directly acted on a power generation structure, the structure is enabled to generate buckling, deformation and heat induced vibration, and the service life of the power generation device can be remarkably prolonged.
Further, the cover plate 64 is bonded to the fixing frame 61 through high temperature cured rubber for encapsulating the phase change material layer, and the cover plate 64 is made of epoxy resin.
It is worth noting that thermoelectric device 5 mainly comprises many pairs of P type and N type semiconductor thermoelectric arm, electrode and ceramic protection shield of establishing ties etc. because thermoelectric device 5 generates electricity through the difference in temperature that utilizes both ends, has corresponding product on market, belongs to prior art, the utility model discloses do not make too much repeated description to thermoelectric device 5.
Specifically, a voltage conversion space is formed between the heat insulating mat 2 and the protective cover 4, a voltage conversion device 7 is disposed in the voltage conversion space, the voltage conversion device 7 is connected to the thermoelectric device 5, the thermoelectric device 5 converts the generated electricity into a stable voltage and stores the stable voltage after generating electricity, and the voltage conversion device 7 may be formed by any components as long as the effect can be achieved.
Further, the voltage conversion device 7 includes a storage battery 71, a voltage inverter 72, a regulator charger 73, and a circuit board 74. The storage battery 71, the voltage inverter 72 and the regulated charger 73 are arranged on the circuit integrated board 74; the voltage inverter 72 can enable the positive voltage output by the thermoelectric device 5 to be normally output, and the negative voltage is completely converted into the positive voltage; the voltage stabilization charger 73 can convert the output time-varying dc voltage into a constant output voltage to charge the battery 71.
Further, the thermoelectric device 5, the voltage inverter 72, the regulated charger 73 and the battery 71 are integrated on the circuit board 74, so as to realize the conduction and transmission of the currents of the respective components, wherein the thermoelectric device 5 is electrically connected with the voltage inverter 72, the voltage inverter 72 is electrically connected with the regulated charger 73, the regulated charger 73 is electrically connected with the battery 71, and the principle of the power generation is as follows: the thermoelectric device 5 generates power through two ends, the temperature difference between the two ends can be a positive value or a negative value, so the output voltage is also a positive voltage and a reverse voltage, the thermoelectric device 5 is electrically connected with the voltage inverter 72, when the output voltage of the thermoelectric device 5 is a positive voltage, the voltage is normally output, and when the output voltage of the thermoelectric device 5 is a negative voltage, the negative voltage is completely converted into the positive voltage through the voltage inverter 72; because the instantaneous value of the output voltage is different due to the difference of the temperature difference values at the two ends, if the voltage is directly stored in the secondary storage battery 71, the secondary storage battery 71 can be damaged, the voltage inverter 72 is electrically connected with the voltage stabilizing charger 73, and the output time-varying direct-current voltage can be converted into constant output voltage through the voltage stabilizing charger 73; the voltage stabilizing charger 73 is electrically connected with the storage battery 71, and the voltage stabilizing charger 73 converts the constant positive voltage and transmits the converted constant positive voltage to the storage battery 71 for storage.
Further, the protective cover 4 is used for protecting the voltage inverter 72, the voltage stabilizing charger 73 and the storage battery 71 device, and is bonded with the heat insulation plate through high-temperature curing rubber; the surface of the protective cover 4 is provided with a round hole for circuit heat dissipation, and the round hole on the surface is mainly used for heat dissipation of an electronic circuit.
Further, the storage battery 71, the voltage inverter 72 and the voltage stabilizing charger 73 are all fixed on the circuit integrated board 74 through screw connection, circuits are already arranged inside the circuit board, and the storage battery 71, the voltage inverter 72 and the voltage stabilizing charger 73 are all directly fixed on the circuit integrated board through screws, so that the installation is simple and convenient, the circuit board does not need to be connected through lines outside the circuit board, and the safety and the attractiveness are improved.
The utility model provides an on orbit spacecraft is with passive power supply unit that lasts's theory of operation does: the device is fixed on the inner wall surface of the cabin body through screws, when the spacecraft is in a sunshine area, the temperature of the inner wall surface of the cabin body is high, heat is transmitted sequentially through the heat conduction plate 1, the thermoelectric device 5 and the phase change material layer 63 due to the existence of the heat insulation pad 2, and after the phase change material layer 63 is heated, internal paraffin is melted and phase-changed to absorb a large amount of heat, so that the end surface of the thermoelectric device 5 is kept in a low-temperature state; when the spacecraft is in the shadow area, the temperature of the wall surface of the cabin body is very low, and at the moment, the phase-change material layer 63 is solidified and phase-changed in the paraffin after being cooled so as to release a large amount of heat, so that the end surface of the thermoelectric device 5 is kept in a high-temperature state. Therefore, the temperature difference between the two sides of the thermoelectric device can be kept large no matter in the sunshine area or the shadow area, and the continuous supply of electric energy is realized.
Therefore, the passive continuous power supply device for the on-orbit spacecraft, provided by the invention, has the advantages that one end of the thermoelectric device is connected with the inner wall surface of the cabin body through the heat conducting plate, and the other end of the thermoelectric device is connected with the energy storage temperature control assembly; when the cabin body is irradiated by sunlight, and the temperature of the inner wall surface of the cabin body is high, heat is transmitted sequentially through the heat conduction plate, the thermoelectric device and the energy storage temperature control assembly, and finally melting in the energy storage temperature control assembly absorbs a large amount of heat, so that the temperature difference is kept at the two ends of the thermoelectric device for power generation. When the cabin body does not receive the irradiation of sunlight, the temperature of the inner wall surface of the cabin body is low, and the phase-change material in the energy storage temperature control assembly is solidified to release a large amount of heat, so that the temperature difference is kept between the two ends of the thermoelectric device for power generation, the in-orbit spacecraft can continuously generate and store power in the whole operation process, and the defect that the solar cell panel cannot generate power when being in a shadow area is overcome.
Further, the utility model discloses small and install at internal face of cabin, the external space environment of having avoided cold and hot alternation directly acts on power generation structure and makes the structure produce bucking, deformation and heat and induce the vibration, and this can show increase power generation facility's the labour life-span.
Further, the utility model discloses there is not any transmission mechanical device, simple structure can select single device still to establish ties the use according to specific under-deck space and electric energy demand, and the installation is convenient with the change.
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; although the present invention has been described in detail with reference to the foregoing embodiments, it should be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; such modifications and substitutions do not depart from the spirit and scope of the present invention.
Claims (10)
1. A passive continuous power supply device for an on-orbit spacecraft is characterized by being installed on the inner wall surface of a cabin body and comprising: the heat-conducting plate, the heat shield, the thermoelectric device and the energy-storing temperature control component absorb and release heat through the phase-change material;
the heat conducting plate and the heat insulation cover form a temperature control space;
the thermoelectric device and the energy storage temperature control assembly are arranged in a temperature control space;
one side of the thermoelectric device is attached to the heat conducting plate, and the other corresponding side of the thermoelectric device is attached to the energy storage temperature control assembly.
2. The passive continuous power supply device for the in-orbit spacecraft of claim 1, wherein the energy storage temperature control assembly comprises a fixing frame, a radiator, a phase change material layer and a cover plate;
the radiator and the phase change material layer are both arranged inside the fixed frame;
the top of the fixed frame is covered with a cover plate;
the radiator is provided with a plurality of evenly distributed fins, the phase change material layer is provided with fin holes corresponding to the fins, and the radiator is tightly attached to the phase change material layer through the fins and the fin holes.
3. The passive continuous power supply device for the in-orbit spacecraft of claim 2, wherein the heat conducting plate is attached to a heat insulating pad;
the heat insulation pad is provided with a first square hole, the bottom surface of the fixing frame is provided with a second square hole, the thermoelectric device is arranged in the first square hole and the second square hole, the bottom surface of the thermoelectric device is attached to the top surface of the heat conduction plate, and the top surface of the thermoelectric device is attached to the bottom surface of the radiator;
and heat-conducting silicone grease is smeared on the connecting part of the thermoelectric device and the heat-conducting plate, and heat-conducting silicone grease is also smeared on the connecting part of the thermoelectric device and the radiator.
4. The passive continuous power supply device for the on-orbit spacecraft of claim 3, wherein a voltage transformation space is formed between the heat insulation pad and the protective cover, and a voltage transformation device is arranged in the voltage transformation space and is connected with a thermoelectric device;
the voltage conversion device comprises a storage battery, a voltage inverter, a voltage stabilizing charger and a circuit integrated board, wherein the storage battery, the voltage inverter and the voltage stabilizing charger are arranged on the circuit integrated board.
5. The passive continuous power supply device for the on-orbit spacecraft of claim 4, wherein the thermoelectric device is electrically connected with the voltage inverter, the voltage inverter is electrically connected with the voltage stabilizing charger, and the voltage stabilizing charger is electrically connected with the storage battery.
6. The passive continuous power supply device for the in-orbit spacecraft of claim 5, wherein the protective cover is bonded on the heat insulation pad through cured rubber, and a circular hole for heat dissipation of a circuit is formed in the surface of the protective cover.
7. The passive continuous power supply device for the on-orbit spacecraft of claim 6, wherein the storage battery, the voltage inverter and the regulated charger are fixed on the circuit integrated board through screw connection.
8. The passive continuous power supply device for the in-orbit spacecraft of claim 2, wherein the heat radiator is bonded with the fixing frame through cured rubber.
9. The passive continuous power supply apparatus for in-orbit spacecraft of claim 3, wherein the thermally conductive plate and the thermal insulation pad are bonded by cured rubber.
10. The passive continuous power supply device for the in-orbit spacecraft of claim 9, wherein the heat conducting plate and the heat insulating pad are provided with threaded holes at the corners, and are fixed with the inner wall surface of the cabin body through screws.
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112491300A (en) * | 2020-12-03 | 2021-03-12 | 中国航天空气动力技术研究院 | Passive continuous power supply device for on-orbit spacecraft |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112491300A (en) * | 2020-12-03 | 2021-03-12 | 中国航天空气动力技术研究院 | Passive continuous power supply device for on-orbit spacecraft |
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