CN113998158B - Radiating system of focal plane electric box of space remote sensing camera and design method - Google Patents
Radiating system of focal plane electric box of space remote sensing camera and design method Download PDFInfo
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- CN113998158B CN113998158B CN202111425368.9A CN202111425368A CN113998158B CN 113998158 B CN113998158 B CN 113998158B CN 202111425368 A CN202111425368 A CN 202111425368A CN 113998158 B CN113998158 B CN 113998158B
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- 230000017525 heat dissipation Effects 0.000 claims abstract description 48
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- 230000005457 Black-body radiation Effects 0.000 claims description 7
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- QVRYCILXIXLVCU-UHFFFAOYSA-N N.[AlH3] Chemical compound N.[AlH3] QVRYCILXIXLVCU-UHFFFAOYSA-N 0.000 claims description 6
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Classifications
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- 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
- B64G1/66—Arrangements or adaptations of apparatus or instruments, not otherwise provided for
-
- G—PHYSICS
- G03—PHOTOGRAPHY; CINEMATOGRAPHY; ANALOGOUS TECHNIQUES USING WAVES OTHER THAN OPTICAL WAVES; ELECTROGRAPHY; HOLOGRAPHY
- G03B—APPARATUS OR ARRANGEMENTS FOR TAKING PHOTOGRAPHS OR FOR PROJECTING OR VIEWING THEM; APPARATUS OR ARRANGEMENTS EMPLOYING ANALOGOUS TECHNIQUES USING WAVES OTHER THAN OPTICAL WAVES; ACCESSORIES THEREFOR
- G03B17/00—Details of cameras or camera bodies; Accessories therefor
- G03B17/55—Details of cameras or camera bodies; Accessories therefor with provision for heating or cooling, e.g. in aircraft
Abstract
The invention discloses a radiation type heat dissipation system of a focal plane electric box of a space remote sensing camera and a design method thereof, and relates to the technical field of spacecraft thermal control. The radiation type heat radiation system of the space remote sensing camera focal plane electric box comprises a radiation plate, a heat pipe, a satellite heat radiation surface and a camera focal plane electric box, wherein the radiation plate and the camera focal plane electric box are arranged on a satellite cabin plate, the radiation plate and the camera focal plane electric box are arranged in a relative gap, and the radiation plate is connected with the satellite heat radiation surface through the heat pipe; the satellite provided by the invention is provided with the radiation type heat radiation system of the focal plane electric box of the space remote sensing camera. The invention utilizes the coupled radiating surface to realize heat radiation, ensures the temperature indexes of the camera focal plane electric box and the satellite platform, can obviously reduce the temperature of the focal plane electric box, simultaneously reduces the power consumption of thermal compensation, balances the temperature of the whole satellite, and reduces the power consumption requirement of the camera load on the whole satellite.
Description
Technical Field
The invention relates to the field of spacecraft thermal control research, in particular to a radiation type heat dissipation system of a focal plane electric box of a space remote sensing camera and a design method.
Background
With the development of the fast response space technology, the function and performance requirements of the space flight on the fast response satellite are higher and higher. Features such as high functional density, high payload ratio, multi-task and multi-mode have become a trend for fast response satellites. Due to the limitations of size, weight and the like, the effective load (remote sensing camera) of the optical remote sensing satellite and the satellite platform are not obviously divided in layout, and the integrated design of the load and the platform has become the trend of the satellite development. In addition, the task requirement of high performance requires that the satellite remote sensing camera be powered on almost every orbit and have long duration. On the one hand, the camera boundary is seriously coupled with the satellite platform; on the other hand, the camera has large short-time power consumption and difficult heat dissipation, and brings serious challenges to the thermal design of the camera and the satellite platform. The traditional camera heat dissipation design directly arranges a heat dissipation surface and an active temperature control loop, or adopts a radiation plate and a temperature control loop, so as to achieve the purpose of heat dissipation of a focal plane electric box of the camera. In a high-temperature working condition, the temperature of the camera focal plane electric box is higher; and under the low-temperature working condition, the heating loop needs to be started, so that the waste of the whole satellite power consumption is caused.
Disclosure of Invention
The invention provides a radiation type heat radiation system and a design method of a focal plane electric box of a space remote sensing camera aiming at the problems existing in the prior art.
In order to solve the technical problems, the invention adopts the following technical scheme:
a radiation type heat radiation system of a focal plane electric box of a space remote sensing camera is characterized by comprising a radiation plate, a heat pipe, a satellite heat radiation surface and the focal plane electric box of the camera; the camera focal plane electric box is a movable component positioned below the camera lens cone; the radiation plate is arranged on the satellite cabin plate, and the radiation plate and the camera focal plane electric box are arranged in a relative gap; the radiation plate is also connected with the satellite radiating surface through the heat pipe;
the heat pipe is fixedly connected with the radiation plate, or the heat pipe is movably connected with the radiation plate, and a heat conducting filler is arranged between the heat pipe and the radiation plate when the heat pipe is movably connected with the radiation plate;
the heat pipe is fixedly connected with the satellite radiating surface, or the heat pipe is movably connected with the satellite radiating surface, and a heat conducting filler is arranged between the heat pipe and the radiating plate when the heat pipe is movably connected with the satellite radiating surface.
Optionally, a black anodic oxidation layer or a black paint layer is arranged on one side of the radiation plate facing the camera focal plane electric box.
Optionally, one or more first heat insulation material layers are arranged on the installation surface of the radiation plate close to the satellite cabin plate side; one or more second heat insulation material layers are arranged on the installation surface of the camera focal plane electric box close to the satellite cabin plate side.
Optionally, the heat pipe is an aluminum-ammonia aerospace heat pipe, the aluminum-ammonia aerospace heat pipe comprises a closed pipeline made of an aluminum alloy shell, and a heat conduction working medium in the closed pipeline is ammonia.
Optionally, the camera lens barrel is fixedly installed on the installation surface of the other satellite cabin boards except the satellite cabin board.
Further, the radiation type heat dissipation system of the focal plane electric box of the space remote sensing camera further comprises a temperature compensation subsystem, wherein the temperature compensation subsystem comprises a thermistor, a heater and a control unit, the thermistor is arranged on the satellite heat dissipation surface to detect the temperature of the satellite heat dissipation surface, the heater is arranged on the satellite heat dissipation surface to heat the satellite heat dissipation surface, and the thermistor and the heater are respectively connected with the control unit.
Optionally, the heater is a polyimide film type heating plate, is adhered to the back surface of the satellite cooling surface, and is arranged adjacent to the part of the heat pipe mounted on the satellite cooling surface.
In addition, the invention also provides a design method of the radiation type heat dissipation system of the focal plane electric box of the space remote sensing camera, which comprises the following steps:
s1, collecting basic parameters of a camera focal plane electronic box and a satellite cooling surface, wherein the basic parameters comprise: maximum temperature T in ambient temperature e Maximum allowable temperature T of camera focal plane electric box max Heating power q of camera focal plane electric box in Blackbody radiation coefficient epsilon of camera focal plane electric box, mass m of camera focal plane electric box, heat capacity c of camera focal plane electric box and temperature T of satellite radiating surface r ；
S2, configuring the area A of the radiation plate p ；
S3, selecting the cross section type of the heat pipe, and setting parameters of the heat pipe, wherein the steps include: the length l of the heat pipe and the heat transfer coefficient lambda of the heat pipe;
s4, respectively calculating the temperatures of the radiation plate and the camera focal plane electric box by adopting the following heat balance equation:
wherein T is p T is the temperature of the radiation plate, T is the temperature of the camera focal plane electric box e T is the highest temperature in the ambient temperature r Is the temperature of the satellite radiating surface, m p For radiating plate mass c p For radiant panel heat capacity, σ is the Stefin-Boltzmann constant, A p For radiating plate area A e Is the effective heat radiation area between the camera focal plane electric box and the radiation plate, l is the length of the heat pipe, lambda is the heat transfer coefficient of the heat pipe, m, c, epsilon and q in The quality, heat capacity, blackbody radiation coefficient and heating power of the camera focal plane electric box are respectively represented byRepresenting time differentiation;
s5, judging whether the temperature T of the camera focal plane electric box is not more than the maximum allowable temperature T max Is required by the following steps: if so, ending the design; if not, adjusting parameters of the radiation plate and the heat pipe, including the area A of the radiation plate p And repeating the steps S2-S4 until the temperature T of the focal plane electric box meets the requirement.
Compared with the prior art, the technical scheme of the invention has the beneficial effects that: the invention comprises a radiation plate, a heat pipe, a satellite cooling surface and a camera focal surface electric box, wherein the radiation plate and the camera focal surface electric box are arranged on a satellite cabin plate, the radiation plate and the camera focal surface electric box are arranged in a relative gap, and the radiation plate is connected with the satellite cooling surface through the heat pipe.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are required in the embodiments or the description of the prior art will be briefly described, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and other drawings may be obtained according to the structures shown in these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic diagram of a heat dissipation system according to an embodiment of the present invention;
FIG. 2 is a schematic diagram of a radiation plate, a heat dissipating surface and a focusing mechanism according to an embodiment of the present invention;
FIG. 3 is a schematic diagram of a heat dissipation channel and a heat dissipation mode of a camera focal plane electronic box in a conventional method;
FIG. 4 is a schematic diagram of a heat dissipation channel and a heat dissipation mode of a camera focal plane electronic box according to the present invention;
FIG. 5 is a thermal balance test temperature measurement data (low temperature conditions) in an embodiment of the present invention;
FIG. 6 is a graph showing the thermal equilibrium test temperature measurement data (high temperature conditions) in an embodiment of the present invention.
Reference numerals:
1-a radiation plate; 2-a heat pipe; 3-satellite cooling surface; 4-thermistor; 5-a heater; 6-a control unit; 7, a focusing mechanism; 8—a first layer of insulating material; 9, a camera focal plane electric box; 10-satellite deck; 11—a camera barrel; 91—cmos imaging device; 92-PCB board; 93—a mounting frame; 94-a housing; 95-heat conductive grease.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and fully with reference to the accompanying drawings, in which it is evident that the embodiments described are only some, but not all embodiments of the invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
The camera focal plane electric box 9 is a movable component on the space remote sensing camera, as shown in fig. 1, and is located below the camera lens barrel 11, and the camera focal plane electric box 9 can move in a certain range according to the task requirement, so that the camera focal plane electric box 9 and the satellite cooling surface 3 cannot be directly connected through the heat pipe 2.
The camera focal plane electric box 9 mainly comprises a focal plane circuit board, a video processing circuit board, a power supply circuit board and the like, wherein a plurality of large-power chips with small sizes exist on the circuit boards, the peak value of heat consumption is large, and the requirements on heat dissipation and temperature uniformity are high. It can be said that the camera focal plane electric box 9 has high requirements on temperature, but the heat dissipation of the movable parts is greatly affected by the structure. Normally, the environment where the camera focal plane electric box 9 is located is set to be a low-temperature environment, so that the temperature index requirement can be met when the camera focal plane electric box works.
Referring to the schematic diagram of the heat dissipation channel and mode of the camera focal plane electric box in the conventional method shown in fig. 3, in order to implement heat dissipation of the camera focal plane electric box 9, the conventional method generally connects the camera focal plane electric box 9 with the satellite heat dissipation surface 3 through the flexible heat pipe 2 or the heat conducting cable, but since the heat pipe 2 or the heat conducting cable still has a certain rigidity, it will have a certain influence on the motion of the high precision mechanism.
The invention provides a design idea of a heat dissipation system different from a conventional method, and a schematic diagram of a heat dissipation channel and a mode of a camera focal plane electric box in the invention is shown in fig. 4. The heat dissipation channel is as follows: the CMOS imaging device 91 of the camera generates a lot of heat during operation, transferring the heat to the PCB board 92 by heat conduction; a heat conduction silicone grease 95 is coated between the PCB 92 and the mounting frame 93, and the PCB 92 conducts heat to the mounting frame 93 and the casing 94; the cabinet 94 transfers heat to the radiation plate 1 by heat radiation; the radiation plate 1 transfers heat to the satellite radiating surface 3 through the heat pipe 2, and the satellite radiating surface 3 radiates heat to the space. The invention provides a design idea of independently arranging the radiation plate cold source for the camera focal plane electric box 9, the design does not generate any interference on a moving mechanism part of the camera focal plane electric box 9, and the radiation indirect heat dissipation method can ensure the short-term start-up heat dissipation requirement, and simultaneously, when the camera does not work, the temperature of a heat dissipation surface can be controlled to be lower so as to reduce the temperature control power and save the whole satellite energy of a satellite.
Referring to fig. 1 again to illustrate a schematic structure diagram of a heat dissipation system of a focal plane electric box of a camera provided by the invention, the radiation type heat dissipation system of a focal plane electric box of a space remote sensing camera of the invention comprises a radiation plate 1, a heat pipe 2, a satellite heat dissipation surface 3 and a focal plane electric box 9 of the camera, wherein the focal plane electric box 9 of the camera is positioned below a camera lens barrel 11, and the camera lens barrel 11 is mounted on a satellite cabin plate; the radiation plate 1 is also mounted on the satellite cabin plate 10 and is arranged in a gap opposite to the camera focal plane electronic box 9; the radiation plate 1 is connected with the satellite radiating surface 3 through a heat pipe 2. The embodiment utilizes the coupled radiating surface to realize heat radiation, ensures the temperature indexes of the camera focal plane electric box 9 and the satellite platform, can obviously reduce the temperature of the focal plane electric box, reduces the power consumption of thermal compensation, balances the temperature of the whole satellite, and reduces the power consumption requirement of the camera load on the whole satellite. When the camera focal plane electric box 9 works, heat generated by the camera focal plane electric box 9 is radiated to the radiation plate 1 and is conducted to the satellite radiating surface 3 through the heat pipe 2, so that heat dissipation of the camera focal plane electric box 9 is realized.
In order to reduce the interface thermal resistance between the heat pipe 2 and the radiation plate 1 and reduce the temperature difference, the heat pipe 2 is welded with the radiation plate 1, or the heat pipe 2 is movably connected with the radiation plate 1, and a heat conducting filler (such as silicone grease and the like) is arranged between the heat pipe 2 and the radiation plate 1.
In order to reduce the interface thermal resistance between the heat pipe 2 and the satellite heat dissipation surface 3 and reduce the temperature difference, the heat pipe 2 is welded with the satellite heat dissipation surface 3, or the heat pipe 2 is movably connected with the satellite heat dissipation surface 3, and a heat conducting filler (such as silicone grease, etc.) is arranged between the heat pipe 2 and the radiation plate 1.
In order to increase the infrared emissivity of the camera focal plane box 9, the side (front) of the radiation plate 1 facing the camera focal plane box 9 is provided with a black anodized layer or a black paint layer (e.g. E51-M black paint).
As shown in fig. 1, in order to reduce the radiant heat exchange with the satellite cabin, the radiation plate 1 is provided with one or more first heat insulating material layers 8 on the installation surface on the side of the satellite cabin plate 10. The first heat insulation material layer 8 can be made of glass fiber reinforced plastic, polyimide or titanium alloy gaskets according to requirements, and has the characteristic of low heat conductivity coefficient. The shape and size of the first insulating material layer 8 are designed according to the thermal conductivity and mechanical strength.
The heat pipe 2 achieves the purpose of reducing the temperature difference between the radiating plate 1 and the satellite radiating surface 3. As an optional implementation manner, the heat pipe 2 in this embodiment is an aerospace heat pipe such as aluminum-ammonia, and the aerospace heat pipe such as aluminum-ammonia includes a closed pipeline made of an aluminum alloy shell, and a heat conducting working medium in the closed pipeline is ammonia.
In order to improve the heat dissipation performance of the satellite heat dissipation surface 3, the front surface (heat dissipation surface) of the satellite heat dissipation surface 3 may be heat dissipation white paint, F46 or cerium glass silver plating secondary surface mirror (OSR), etc., the heat dissipation surface radiates heat toward the cosmic cool black space, the heat dissipation surface is simultaneously the heat dissipation surface of the satellite, and the high heat consumption equipment of the satellite is also arranged on the heat dissipation surface.
As shown in fig. 1, in order to reduce the radiant heat exchange with the satellite cabin, the camera focal plane electric box 9 is provided with one or more layers of a second heat insulating material on the installation surface on the side of the satellite cabin board 10. The second heat insulation material layer can be made of glass fiber reinforced plastic, polyimide or titanium alloy gaskets according to the requirements, and has the characteristic of low heat conductivity coefficient. The shape and size of the second insulating material layer are designed according to the heat conductivity coefficient and the mechanical strength.
In addition, the embodiment further comprises a temperature compensation subsystem, the temperature compensation subsystem comprises a thermistor 4, a heater 5 and a control unit 6, the thermistor 4 is installed on the satellite cooling surface 3 to detect the temperature of the satellite cooling surface 3, the heater 5 is installed on the satellite cooling surface 3 to heat the satellite cooling surface 3, and the thermistor 4 and the heater 5 are respectively connected with the control unit 6. The thermistor 4 collects the temperature of the satellite radiating surface, and transmits a temperature signal to the control unit 6, and the control unit 6 controls the on-off of the heater 5 according to the control logic. The control unit 6 may be provided separately or may be integrated on a control host of the satellite, for example, the control unit 6 is integrated in a thermal control lower computer of the whole satellite in this embodiment.
In this embodiment, the thermistor 4 is an NTC type MF501 thermistor, the temperature measurement range is-40 to +70 ℃, the temperature measurement accuracy is ±0.3 ℃, and the thermistor is adhered to the back surface (on the in-satellite side) of the cooling surface for measuring the temperature of the satellite cooling surface and feeding back to the control unit 6; the heater 5 is a polyimide film type heating sheet, is adhered to the back surface of the satellite heat radiation surface 3, and is arranged adjacent to the heat pipe 2. The power of the heater 5 can be designed according to the size of the radiating surface.
In order to ensure reliability, the thermistor 4 and the heater 5 need to be arranged in a redundant manner, and in this embodiment, the number of the thermistor 4 and the heater 5 is two or more. The number of temperature measuring channels and temperature control channels of the control unit 6 should meet the requirements of the number of thermistors and heaters.
Finally, an application example of the invention is used for explaining the effect of the radiation type heat dissipation system of the focal plane electric box 9 of the space remote sensing camera. The power of the camera focal plane electric box 9 is about 20w, and the working time of each rail is 6.5min. The radiation plate 1 is an aluminum alloy sheet, E51-M black paint is sprayed on the front surface of the radiation plate, and a plurality of first heat insulation material layers 8 are arranged on the installation surface close to the satellite cabin plate 10 side. The satellite cooling surface 3 is a coupling cooling surface of the satellite equipment and the camera focal plane electric box 9, and a cerium glass silver-plated secondary surface mirror (OSR) is stuck on the outer side of the satellite cooling surface 3. The heater 5 comprises a main part and a backup two channels, the power of each channel is 4W, and 2 thermistors 4 are arranged on the back of the satellite radiating surface 3 and used as temperature control inputs. The control unit 6 is integrated in a whole star thermal control controller, adopts a minimum value interval temperature control principle, controls the temperature interval to be [ -10, -5 ]. DEG C, and can change the upper limit and the lower limit of the interval on track. The radiation plate 1 and the satellite, and the camera focal plane electric box 9 and the satellite are installed in a heat insulation way through a polyimide heat insulation pad (a first heat insulation material layer 8). Fig. 2 shows temperature curves of the radiation plate 1 and the satellite radiating surface 3 under the low-temperature working condition of the satellite heat balance experiment. The temperature range of the radiation plate 1 is 3.0-4.1 ℃, the temperature range of the satellite radiating surface 3 is 2.2-3.7 ℃, and the heat conduction condition of the heat pipe 2 is good. Meanwhile, the temperature range of the camera focal plane electric box 9 under the low-temperature working condition is 16.0-16.5 ℃. Fig. 3 shows temperature curves of the radiation plate 1, the satellite heat radiation surface 3 and the camera focal plane electric box 9 under the high temperature working condition of the satellite heat balance experiment. The temperature range of the radiation plate 1 is 7.7-10.5 ℃, the temperature range of the satellite radiating surface 3 is 7.0-11.2 ℃, and the temperature range of the camera focal plane electric box 9 is 19.2-20.8 ℃. The temperatures of the camera focal plane electric box 9 and the satellite cooling surface 3 at the initial stage of satellite in-orbit flight are as follows: the camera focal plane electric box 9 is kept in the range of 15.1-15.7 ℃, the temperature range of the satellite radiating surface 3 is 1-3 ℃, and the heater 5 is kept in a normally-off state according to the interval temperature control logic of [ -10, -5] DEG C, and accords with the condition of low-temperature working conditions.
In addition, the embodiment also provides a design method of the radiation type heat dissipation system of the focal plane electric box of the space remote sensing camera, which comprises the following steps:
s1, collecting basic parameters of a camera focal plane electronic box 9 and a satellite cooling surface 3, wherein the basic parameters comprise: maximum temperature T in ambient temperature e Maximum allowable temperature T of camera focal plane electric box max Heating power q of camera focal plane electric box in Blackbody radiation coefficient epsilon of camera focal plane electric box, mass m of camera focal plane electric box, heat capacity c of camera focal plane electric box and temperature T of satellite radiating surface r 。
S2, designing and configuring the area A of the radiation plate 1 p ；
S3, selecting the cross section type of the heat pipe 2 and setting parameters of the heat pipe 2, wherein the steps comprise: parameters such as the length l of the heat pipe 2, the heat transfer coefficient lambda of the heat pipe 2 and the like;
s4, calculating the temperatures of the radiation plate 1 and the camera focal plane electric box 9 by adopting a heat balance equation;
wherein T is p For radiating plate temperature, m p For radiating plate mass c p The heat capacity of the radiation plate is T is the temperature of the focal plane electric box, sigma is the Stefan-Boltzmann constant, A is the heat radiation effective area between the focal plane electric box and the radiation plate, and the sign is thatRepresenting the time derivative.
S5, judging whether the temperature T of the focal plane electric box meets the requirement of not more than the highest allowable temperature. If yes, the design is finished; if not, the parameters of the radiation plate 1 and the heat pipe 2 are adjusted, and the parameters mainly comprise the area A of the radiation plate 1 p And the length l of the heat pipe 2, the heat transfer coefficient lambda of the heat pipe and the like, repeating the steps S2 to S4 until the temperature T of the focal plane electric box meets the requirement, namely T is less than or equal to T max 。
The foregoing description is only of the preferred embodiments of the present invention and is not intended to limit the scope of the invention, and all equivalent structural changes made by the description of the present invention and the accompanying drawings or direct/indirect application in other related technical fields are included in the scope of the invention.
Claims (8)
1. The radiation type heat radiation system of the focal plane electric box of the space remote sensing camera is characterized by comprising a radiation plate (1), a heat pipe (2), a satellite heat radiation surface (3) and a camera focal plane electric box (9); the camera focal plane electric box (9) is a movable component positioned below the camera lens cone (11); the radiation plate (1) is arranged on the satellite cabin plate (10), and the radiation plate (1) and the camera focal plane electric box (9) are arranged in a relative gap; the radiating plate (1) is also connected with the satellite radiating surface (3) through the heat pipe (2);
the heat pipe (2) is fixedly connected with the radiation plate (1), or the heat pipe (2) is movably connected with the radiation plate (1), and a heat conduction filler is arranged between the heat pipe (2) and the radiation plate (1) when the heat pipe (2) is movably connected with the radiation plate;
the heat pipe (2) is fixedly connected with the satellite radiating surface (3), or the heat pipe (2) is movably connected with the satellite radiating surface (3), and a heat conducting filler is arranged between the heat pipe (2) and the radiating plate (1) when the heat pipe is movably connected with the satellite radiating surface;
the heat dissipation system is obtained according to the following design method:
s1, collecting basic parameters of a camera focal plane electric box (9) and a satellite cooling surface (3), wherein the basic parameters comprise: maximum temperature T in ambient temperature e Maximum allowable temperature T of camera focal plane electric box max Heating power q of camera focal plane electric box in Blackbody radiation coefficient epsilon of camera focal plane electric box, mass m of camera focal plane electric box, heat capacity c of camera focal plane electric box and temperature T of satellite radiating surface r ；
S2, the area A of the radiation plate (1) is configured p ；
S3, selecting the cross section type of the heat pipe (2) and setting parameters of the heat pipe (2), wherein the method comprises the following steps: the length l of the heat pipe (2) and the heat transfer coefficient lambda of the heat pipe (2);
s4, respectively calculating the temperature of the radiation plate (1) and the temperature of the camera focal plane electric box (9) by adopting the following heat balance equation:
wherein T is p T is the temperature of the radiation plate, T is the temperature of the camera focal plane electric box e T is the highest temperature in the ambient temperature r Is the temperature of the satellite radiating surface, m p For radiating plate mass c p For radiant panel heat capacity, σ is the Stefin-Boltzmann constant, A p For radiating plate area A e Is the effective heat radiation area between the camera focal plane electric box and the radiation plate, l is the length of the heat pipe, lambda is the heat transfer coefficient of the heat pipe, m, c, epsilon and q in The quality, heat capacity, blackbody radiation coefficient and heating power of the camera focal plane electric box are respectively represented byRepresenting time differentiation;
s5, judging whether the temperature T of the camera focal plane electric box is not more than the maximum allowable temperature T max Is required by the following steps: if so, ending the design; if not, the parameters of the radiant panel (1) and the heat pipe (2) are adjusted, including the radiant panel area A p And repeating the steps S2-S4 until the temperature T of the focal plane electric box meets the requirement.
2. The radiation type heat radiation system of the focal plane electric box of the space remote sensing camera according to claim 1, wherein a black anodic oxide layer or a black paint layer is arranged on one side of the radiation plate (1) facing the focal plane electric box (9) of the camera.
3. The radiation type heat radiation system of the focal plane electric box of the space remote sensing camera according to claim 1, wherein one or more layers of first heat insulation material layers (8) are arranged on a mounting surface of the radiation plate (1) close to the satellite cabin plate (10); one or more second heat insulation material layers are arranged on the installation surface of the camera focal plane electric box (9) close to the satellite cabin board (10).
4. The radiation type heat radiation system of the focal plane electric box of the space remote sensing camera according to claim 1, wherein the heat pipe (2) is an aluminum-ammonia heat pipe for space, the aluminum-ammonia heat pipe comprises a closed pipeline made of an aluminum alloy shell, and a heat conduction working medium in the closed pipeline is ammonia.
5. The radiation type heat radiation system of the focal plane electric box of the space remote sensing camera according to claim 1, wherein the camera lens barrel (11) is fixedly arranged on the installation surface of other cabins of the satellite except the satellite cabin board (10).
6. The radiation type heat radiation system of the focal plane electric box of the space remote sensing camera according to claim 1, further comprising a temperature compensation subsystem, wherein the temperature compensation subsystem comprises a thermistor (4), a heater (5) and a control unit (6), the thermistor (4) is installed on the satellite heat radiation surface (3) to detect the temperature of the satellite heat radiation surface (3), the heater (5) is installed on the satellite heat radiation surface (3) to heat the satellite heat radiation surface (3), and the thermistor (4) and the heater (5) are respectively connected with the control unit (6).
7. The radiation type heat radiation system of the focal plane electric box of the space remote sensing camera according to claim 6, wherein the heater (5) is a polyimide film type heating plate, is stuck on the back surface of the satellite heat radiation surface (3), and is arranged adjacent to the part of the heat pipe (2) mounted on the satellite heat radiation surface (3).
8. A design method of a radiation type heat dissipation system of a focal plane electric box of a space remote sensing camera comprises the following steps:
s1, collecting basic parameters of a camera focal plane electric box (9) and a satellite cooling surface (3), wherein the basic parameters comprise: maximum temperature T in ambient temperature e Maximum allowable temperature T of camera focal plane electric box max Heating power q of camera focal plane electric box in Blackbody radiation coefficient epsilon of camera focal plane electric box, mass m of camera focal plane electric box, heat capacity c of camera focal plane electric box and temperature T of satellite radiating surface r ；
S2, the area A of the radiation plate (1) is configured p ；
S3, selecting the cross section type of the heat pipe (2) and setting parameters of the heat pipe (2), wherein the method comprises the following steps: the length l of the heat pipe (2) and the heat transfer coefficient lambda of the heat pipe (2);
s4, respectively calculating the temperature of the radiation plate (1) and the temperature of the camera focal plane electric box (9) by adopting the following heat balance equation:
wherein T is p T is the temperature of the radiation plate, T is the temperature of the camera focal plane electric box e T is the highest temperature in the ambient temperature r Is the temperature of the satellite radiating surface, m p For radiating plate mass c p For radiant panel heat capacity, σ is the Stefin-Boltzmann constant, A p For radiating plate area A e Is the effective heat radiation area between the camera focal plane electric box and the radiation plate, l is the length of the heat pipe, lambda is the heat transfer coefficient of the heat pipe, m, c, epsilon and q in The quality, heat capacity, blackbody radiation coefficient and heating power of the camera focal plane electric box are respectively represented byRepresenting time differentiation;
s5, judging the focal plane electricity of the cameraWhether the tank temperature T satisfies not more than the maximum allowable temperature T max Is required by the following steps: if so, ending the design; if not, the parameters of the radiant panel (1) and the heat pipe (2) are adjusted, including the radiant panel area A p And repeating the steps S2-S4 until the temperature T of the focal plane electric box meets the requirement.
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105629629A (en) * | 2015-12-23 | 2016-06-01 | 中国科学院长春光学精密机械与物理研究所 | Adaptive focusing system and focusing method for fast imaging of spatial optical camera |
| CN108106726A (en) * | 2017-12-14 | 2018-06-01 | 中国科学院长春光学精密机械与物理研究所 | A kind of spectrometer ambient noise suppression system |
| CN112257191A (en) * | 2020-12-23 | 2021-01-22 | 中国人民解放军国防科技大学 | Load platform integrated microsatellite thermal control subsystem optimization method and system |
| CN112484541A (en) * | 2020-10-30 | 2021-03-12 | 西安空间无线电技术研究所 | Rotary space radiation heat exchanger |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20090272888A1 (en) * | 2008-01-25 | 2009-11-05 | Nugent Paul W | Thermal infrared imaging system and associated methods for radiometric calibration |
-
2021
- 2021-11-26 CN CN202111425368.9A patent/CN113998158B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105629629A (en) * | 2015-12-23 | 2016-06-01 | 中国科学院长春光学精密机械与物理研究所 | Adaptive focusing system and focusing method for fast imaging of spatial optical camera |
| CN108106726A (en) * | 2017-12-14 | 2018-06-01 | 中国科学院长春光学精密机械与物理研究所 | A kind of spectrometer ambient noise suppression system |
| CN112484541A (en) * | 2020-10-30 | 2021-03-12 | 西安空间无线电技术研究所 | Rotary space radiation heat exchanger |
| CN112257191A (en) * | 2020-12-23 | 2021-01-22 | 中国人民解放军国防科技大学 | Load platform integrated microsatellite thermal control subsystem optimization method and system |
Non-Patent Citations (3)
| Title |
|---|
| 多姿态变化相机中CCD焦面组件的热设计;韩冬;吴清文;卢锷;陈立恒;杨成禹;;光学精密工程(第11期);全文 * |
| 空间光学相机焦面拼接基座高温度稳定性控制;郭楠;于波;夏晨晖;于志;常君磊;;航天返回与遥感(第04期);全文 * |
| 空间光学遥感器环境适应性设计与试验研究;卢锷;颜昌翔;吴清文;董得义;郭亮;罗志涛;;中国光学与应用光学(第05期);全文 * |
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