CN113998158A - Radiation type heat dissipation system of focal plane electric box of space remote sensing camera and design method - Google Patents
Radiation type heat dissipation system of focal plane electric box of space remote sensing camera and design method Download PDFInfo
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- B64G1/00—Cosmonautic vehicles
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- B64G1/66—Arrangements or adaptations of apparatus or instruments, not otherwise provided for
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- 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
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Abstract
The invention discloses a radiation type heat dissipation system of a focal plane electric box of an aerospace remote sensing camera and a design method, and relates to the technical field of thermal control of spacecrafts. The radiation type heat dissipation system of the focal plane electric box of the space remote sensing camera comprises a radiation plate, a heat pipe, a satellite heat dissipation 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 clearance mode, and the radiation plate is connected with the satellite heat dissipation surface through the heat pipe; the invention relates to a radiation type heat dissipation system of a satellite with the space remote sensing camera focal plane electric box. The invention realizes heat dissipation by utilizing the coupled heat dissipation surface, simultaneously 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 rapid response space technology, the aerospace has higher and higher requirements on the functions and the performances of the rapid response satellite. The characteristics of high function density, high effective load ratio, multi-task and multi-mode and the like become the development trend of the quick response satellite. Due to the limitations of size, weight and the like, there is no longer obvious cabin division on the layout between the effective load (remote sensing camera) of the optical remote sensing satellite and the satellite platform, and the integrated design of the load and the platform becomes the development trend of the satellite. In addition, the task requirement of high efficiency requires that the satellite remote sensing camera is started to work almost every orbit and has long continuous working time. On the one hand, the camera boundary is heavily coupled with the satellite platform; on the other hand, the camera has large short-time power consumption and difficult heat dissipation, and brings a serious challenge 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 to achieve the purpose of heat dissipation of a camera focal plane electronic box. Under the high-temperature working condition, the temperature of the camera focal plane electric box is higher; and under the low temperature operating mode, need open the heating circuit again, caused the waste of whole star consumption.
Disclosure of Invention
The invention provides a radiation type heat dissipation system of a focal plane electric box of an aerospace remote sensing camera and a design method thereof, aiming at the problems in the prior art, the invention realizes heat dissipation by utilizing a coupled heat dissipation surface, simultaneously ensures the temperature indexes of the focal plane electric box of the camera and a satellite platform, can obviously reduce the temperature of the focal plane electric box of the camera, 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.
In order to solve the technical problems, the technical scheme adopted by the invention is as follows:
a radiation type heat dissipation system of a focal plane electric box of an aerospace remote sensing camera is characterized by comprising a radiation plate, a heat pipe, a satellite heat dissipation 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 clearance manner; 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 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 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 anodized layer or a black paint layer is disposed 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 mounting surface of the radiation plate on the side close to the satellite cabin plate; one or more layers of second heat insulation material layers are arranged on the mounting 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 includes a closed pipeline made of an aluminum alloy shell, and the heat conducting working medium inside the closed pipeline is ammonia.
Optionally, the camera lens barrel is fixedly mounted on a mounting surface of another satellite deck except the satellite deck.
Furthermore, the radiation type heat dissipation system of the space remote sensing camera focal plane electronic box further comprises a temperature compensation subsystem, wherein the temperature compensation subsystem comprises a thermistor, a heater and a control unit, the thermistor is installed on the satellite cooling surface to detect the temperature of the satellite cooling surface, the heater is installed on the satellite cooling surface to heat the satellite cooling surface, and the thermistor and the heater are respectively connected with the control unit.
Optionally, the heater is a polyimide film-type heating sheet, is adhered to the back of the satellite cooling surface, and is arranged adjacent to the portion 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 electric box and a satellite cooling surface, comprising the following steps: maximum temperature T in ambient temperatureeMaximum allowable temperature T of camera focal plane electric boxmaxHeating power q of camera focal plane electric boxinThe black body radiation coefficient epsilon of the camera focal plane electric box, the mass m of the camera focal plane electric box, the heat capacity c of the camera focal plane electric box and the temperature T of the satellite radiating surfacer；
S2, area A of radiation platep；
S3, selecting the cross section type of the heat pipe, and setting the parameters of the heat pipe, including: length l of the heat pipe and heat transfer coefficient lambda of the heat pipe;
and S4, respectively calculating the temperatures of the radiation plate and the camera focal plane electric box by adopting the following heat balance equation:
in the formula, TpIs the radiation plate temperature, T is the camera focal plane cabinet temperature, TeThe highest temperature in the ambient temperature, TrIs the temperature of the radiating surface of the satellite, mpTo the quality of the radiation plate, cpσ is the Stefan-Boltzmann constant, A, for the heat capacity of the radiating platepIs the area of the radiation plate, AeIs the effective area of heat radiation 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 qinRespectively the mass, heat capacity, black body radiation coefficient and heating power of the camera focal plane electric box, and symbols
Represents a differential over time;
s5, judging whether the temperature T of the camera focal plane electric box meets the condition that the temperature T is not more than the maximum allowable temperature TmaxThe requirements of (1): if so, finishing the design; if not, adjusting the parameters of the radiation plate and the heat pipe, including the area A of the radiation platepRepeating the steps S2-S4 until the focal plane electric box is reachedThe temperature T meets the requirements.
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 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 clearance manner, 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 used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the structures shown in the drawings without creative efforts.
FIG. 1 is a schematic structural diagram of a heat dissipation system according to an embodiment of the present invention;
FIG. 2 is a schematic view of a radiation plate, a heat dissipation 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 method 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 method of a camera focal plane electronic box according to the present invention;
FIG. 5 is temperature measurement data (low temperature condition) of a thermal equilibrium test in an embodiment of the present invention;
FIG. 6 shows measured data of temperature (high temperature condition) in the thermal equilibrium test in the example of the present invention.
Reference numerals:
1-a radiation plate; 2-heat pipe; 3-satellite cooling surface; 4-a thermistor; 5-a heater; 6-control unit; 7-a focusing mechanism; 8-first layer of thermal insulation material; 9-camera focal plane electronic box; 10-satellite deck board; 11-camera lens barrel; 91-CMOS imaging device; 92-PCB board; 93-mounting frame; 94-the enclosure; 95-thermal grease.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The camera focal plane electric box 9 belongs to a movable component on the space remote sensing camera, as shown in figure 1, the camera focal plane electric box 9 is positioned below a 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 cannot be directly connected with the satellite cooling surface 3 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 high-power chips with small sizes exist on the circuit boards, the heat consumption peak value is large, and the requirements on heat dissipation performance and temperature uniformity are high. It can be said that the camera focal plane electronic box 9 has a high temperature requirement, but the heat dissipation of its moving parts is greatly affected by its structure. Normally, the environment of the camera focal plane electric box 9 is set to be a low-temperature environment, so that the requirement of temperature index can be still met during the operation.
Referring to fig. 3, a schematic diagram of a heat dissipation channel and a heat dissipation manner of a camera focal plane electrical box in the conventional method is shown, in order to realize heat dissipation of the camera focal plane electrical box 9, the conventional method generally connects the camera focal plane electrical box 9 with a satellite heat dissipation surface 3 through a flexible heat pipe 2 or a heat conduction cable, but the heat pipe 2 or the heat conduction cable still has certain rigidity, and will have certain influence on the motion of a high-precision mechanism.
The invention provides a design idea of a heat dissipation system different from that of the conventional method, and the heat dissipation channel and mode schematic diagram of the camera focal plane electric box in the invention are shown in fig. 4. The heat dissipation channel is as follows: the CMOS imaging device 91 of the camera generates a large amount of heat during operation, transferring the heat to the PCB 92 by thermal conduction; thermal conductive 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 chassis 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 cosmic deep cooling space. The invention provides a design idea of independently arranging a cold source of a radiation plate for a 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 radiation method can not only ensure the short-term startup heat radiation requirement, but also control the temperature of a heat radiation surface to be lower when a camera does not work so as to reduce the temperature control power and save the whole satellite energy of a satellite.
Referring to fig. 1 again, the radiation type heat dissipation system of the focal plane electric box of the 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, wherein the focal plane electric box 9 is positioned below a camera lens cone 11, and the camera lens cone 11 is mounted on a satellite cabin plate; the radiation plate 1 is also arranged on the satellite cabin plate 10 and is arranged opposite to the camera focal plane electric box 9 in a clearance way; the radiation plate 1 is connected to the satellite cooling surface 3 via a heat pipe 2. The embodiment utilizes the coupled radiating surface to realize heat dissipation, 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, 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. 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 conducted to the satellite cooling surface 3 through the heat pipe 2 so as to realize the cooling of the camera focal plane electric box 9.
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 and the radiation plate 1 are connected by welding, or the heat pipe 2 and the radiation plate 1 are movably connected 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 cooling surface 3 and reduce the temperature difference, the heat pipe 2 and the satellite cooling surface 3 are connected by welding, or the heat pipe 2 and the satellite cooling surface 3 are movably connected 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 increase the infrared emissivity of the camera focal plane electrical box 9, the side (front) of the radiation plate 1 facing the camera focal plane electrical box 9 is provided with a black anodized layer or a black lacquer layer (e.g. E51-M black lacquer).
As shown in fig. 1, in order to reduce the radiation heat exchange with the inside of the satellite compartment, the mounting surface of the radiation plate 1 on the satellite compartment plate 10 side is provided with one or more layers of a first thermal insulation material layer 8. The first heat insulation material layer 8 can be made of glass fiber reinforced plastic, polyimide or titanium alloy gaskets according to needs, and has the characteristic of low heat conductivity coefficient. The shape and size of the first thermal insulation material layer 8 are designed according to the thermal conductivity and the mechanical strength.
The heat pipe 2 achieves the purpose of reducing the temperature difference between the radiation plate 1 and the satellite radiating surface 3. As an optional implementation manner, in this embodiment, the heat pipe 2 is an aluminum-ammonia or other aerospace heat pipe, the aluminum-ammonia or other aerospace heat pipe includes a closed pipeline made of an aluminum alloy shell, and the heat conducting working medium inside 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-plated secondary surface mirror (OSR), etc., and the heat dissipation surface radiates heat to the space with cold black space, and is also the heat dissipation surface of the satellite, on which high heat dissipation equipment of the satellite is also arranged.
As shown in fig. 1, in order to reduce the radiation heat exchange with the inside of the satellite capsule, the camera focal plane electric box 9 is provided with one or more layers of a second thermal insulation material on the mounting surface on the satellite capsule plate 10 side. The second heat insulation material layer can adopt glass fiber reinforced plastic, polyimide or titanium alloy gaskets as required, and has the characteristic of low heat conductivity coefficient. The shape and size of the second thermal insulation material layer are designed according to the thermal conductivity and the mechanical strength.
In addition, the present embodiment further includes a temperature compensation subsystem, the temperature compensation subsystem includes 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 to the control unit 6. The thermistor 4 collects the temperature of the satellite cooling surface, 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 separately provided, or may be integrated with a control host of the satellite, for example, in this embodiment, the control unit 6 is integrated with a thermal control lower computer of the whole satellite.
In the embodiment, the thermistor 4 is an NTC type MF501 thermistor, the temperature measuring interval is-40 to +70 ℃, the temperature measuring precision is +/-0.3 ℃, and the thermistor is adhered to the back surface (one side in a satellite) of the radiating surface and used for measuring the temperature of the radiating surface of the satellite 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 radiating surface 3, and is arranged adjacent to the heat pipe 2. The power of the heater 5 can be designed accordingly according to the size of the radiating surface.
In order to ensure reliability, the thermistors 4 and the heaters 5 need to be arranged redundantly, and the number of the thermistors 4 and the heaters 5 is more than two in the embodiment. The number of temperature measuring channels and temperature controlling channels of the control unit 6 should meet the requirements of the number of thermistors and heaters.
Finally, the effect of the radiation type heat dissipation system of the focal plane electronic box 9 of the space remote sensing camera is explained through an application example of the invention. The power of a camera focal plane electric box 9 is about 20w, and the working time of each rail is 6.5 min. The radiation plate 1 is an aluminum alloy thin plate, E51-M black paint is sprayed on the front surface of the radiation plate, and a plurality of layers 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 plating secondary surface mirror (OSR) is pasted on the outer side of the satellite cooling surface 3. The heater 5 comprises a main channel and a backup channel, each channel has power of 4W, and 2 thermistors 4 are arranged on the back of the satellite radiating surface 3 as temperature control input. The control unit 6 is integrated in the whole satellite thermal control controller, the temperature control principle of the minimum value interval is adopted, the temperature control interval is between-10 and-5 ℃, and the upper limit and the lower limit of the interval can be changed on the 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 mode through polyimide heat insulation pads (first heat insulation material layers 8). Fig. 2 shows temperature curves of the radiation plate 1 and the satellite cooling surface 3 under a low-temperature working condition of a 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 better. 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 cooling surface 3 and the camera focal plane electronic box 9 under the high-temperature working condition of the satellite thermal balance experiment. The temperature range of the radiation plate 1 is 7.7-10.5 ℃, the temperature range of the satellite heat dissipation 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 temperature of the camera focal plane electric box 9 and the satellite cooling surface 3 at the initial stage of the satellite in-orbit flight is as follows: the camera focal plane electric box 9 is kept within the range of 15.1-15.7 ℃, the temperature range of the satellite cooling 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, so that the condition of low-temperature working condition is met.
In addition, the embodiment further provides a design method of a radiation type heat dissipation system of the focal plane electronic box of the space remote sensing camera, which includes the following steps:
s1, collecting basic parameters of the camera focal plane electric box 9 and the satellite cooling surface 3, including: maximum temperature T in ambient temperatureeMaximum allowable temperature T of camera focal plane electric boxmaxHeating power q of camera focal plane electric boxinBlack body 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 surfacer。
S2, designing and arranging area A of radiation plate 1p；
S3, selecting the type of the cross section of the heat pipe 2, and setting the parameters of the heat pipe 2, including: the length l of the heat pipe 2, the heat transfer coefficient lambda of the heat pipe 2 and other parameters;
s4, calculating the temperature of the radiation plate 1 and the camera focal plane electric box 9 by adopting a heat balance equation;
in the formula, TpIs radiant panel temperature, mpTo the quality of the radiation plate, cpIs the heat capacity of the radiation plate, T is the temperature of the focal plane electric box, sigma is the Stefan-Boltzmann constant, A is the effective area of the heat radiation between the focal plane electric box and the radiation plate, and the symbol
Representing the differential over time.
And S5, judging whether the temperature T of the coke surface electric box meets the requirement that the temperature T is not more than the maximum allowable temperature. If so, finishing the design; if not, adjusting the parameters of the radiation plate 1 and the heat pipe 2, mainly including the area A of the radiation plate 1pAnd the length l of the heat pipe 2, the heat transfer coefficient lambda of the heat pipe and the like, and repeating the steps S2-S4 until the temperature T of the focal plane electric box meets the requirement, namely T is less than or equal to Tmax。
The above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention, and all modifications and equivalents of the present invention, which are made by the contents of the present specification and the accompanying drawings, or directly/indirectly applied to other related technical fields, are included in the scope of the present invention.
Claims (8)
1. A radiation type heat dissipation system of a focal plane electric box of an aerospace remote sensing camera is characterized by comprising a radiation plate (1), a heat pipe (2), a satellite heat dissipation 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 a satellite cabin plate (10), and the radiation plate (1) and the camera focal plane electric box (9) are arranged in a relative clearance mode; the radiation 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 conducting filler is arranged between the heat pipe (2) and the radiation plate (1) when the heat pipe 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.
2. The radiation type heat dissipation system of the focal plane electric box of the space remote sensing camera according to claim 1, wherein one side of the radiation plate (1) facing the focal plane electric box (9) of the camera is provided with a black anodic oxidation layer or a black paint layer.
3. The radiation type heat dissipation system of the focal plane electric box of the space remote sensing camera according to claim 1, characterized in that one or more first heat insulation material layers (8) are arranged on the mounting surface of the radiation plate (1) close to the satellite cabin plate (10); one or more layers of second heat insulation material layers are arranged on the mounting surface of the camera focal plane electric box (9) close to the satellite cabin plate (10).
4. The radiation type heat dissipation 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 flight, the aluminum-ammonia heat pipe for space flight comprises a closed pipeline made of an aluminum alloy shell, and a heat conducting working medium in the closed pipeline is ammonia.
5. The radiant heat dissipation system of an electric focal plane box of an astronautic remote sensing camera according to claim 1, wherein said camera lens barrel (11) is fixedly mounted on a mounting surface of a satellite deck other than said satellite deck (10).
6. The radiation type heat dissipation 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 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).
7. The radiation type heat dissipation 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 sheet, is adhered to the back surface of the satellite heat dissipation surface (3), and is arranged adjacent to the part of the heat pipe (2) installed on the satellite heat dissipation surface (3).
8. A design method of a radiation type heat dissipation system of a focal plane electric box of an aerospace 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 temperatureeMaximum allowable temperature T of camera focal plane electric boxmaxHeating power q of camera focal plane electric boxinThe black body radiation coefficient epsilon of the camera focal plane electric box, the mass m of the camera focal plane electric box, the heat capacity c of the camera focal plane electric box and the temperature T of the satellite radiating surfacer；
S2, area A of the radiation plate (1) is arrangedp；
S3, selecting the cross section type of the heat pipe (2), and setting the parameters of the heat pipe (2), wherein the parameters comprise: the length l of the heat pipe (2) and the heat transfer coefficient lambda of the heat pipe (2);
s4, respectively calculating the temperatures of the radiation plate (1) and the camera focal plane electric box (9) by adopting the following heat balance equation:
in the formula, TpIs the radiation plate temperature, T is the camera focal plane cabinet temperature, TeThe highest temperature in the ambient temperature, TrIs the temperature of the radiating surface of the satellite, mpTo the quality of the radiation plate, cpσ is the Stefan-Boltzmann constant, A, for the heat capacity of the radiating platepIs the area of the radiation plate, AeIs the effective area of heat radiation 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 qinMass and heat capacity of camera focal plane electric boxBlack body radiation coefficient and heating power, sign
Represents a differential over time;
s5, judging whether the temperature T of the camera focal plane electric box meets the condition that the temperature T is not more than the maximum allowable temperature TmaxThe requirements of (1): if so, finishing the design; if not, adjusting the parameters of the radiation plate (1) and the heat pipe (2) including the area A of the radiation platepAnd repeating the steps S2-S4 until the temperature T of the focal plane electric box meets the requirement.
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