CN100364857C - An Earth Simulator Suitable for Ground Detection of Dual Cone Scanning Infrared Horizon - Google Patents

Abstract

An earth simulator suitable for ground detection of a double-cone scanning infrared horizon, comprising a cold and hot plate assembly, a hot basin assembly, a cold and hot plate support, a hot basin support, a base, a temperature control system and a two-dimensional precision turntable. The hot basin and the hot plate constitute the earth simulation surface, the cold plate and the system background are used to simulate the cold background of space, and the temperature control system controls and heats the hot plate and the hot basin, which is equivalent to simulating the temperature obtained by the infrared horizon relative to the cold background of space. 14-16μm earth infrared radiation intensity and gradient, to realize the simulation of infrared horizon circle target on the boundary of cold and hot plates and the outer boundary of hot basin. The multi-dimensional adjustment mechanism in each component precisely adjusts the position of the boundary of the cold and hot plates and the outer boundary of the hot basin through optical calibration, so as to realize the geometric positional relationship between the satellite at a specific orbital height and the earth's infrared horizon circle. The infrared horizon is installed on a two-dimensional precision turntable, and the two-dimensional rotation simulates the roll and pitch attitude angle deviation of the satellite when it is in orbit, and realizes the measurement of the attitude angle and the ground performance detection of the double-cone scanning infrared horizon.

Description

An Earth Simulator Suitable for Ground Detection of Dual Cone Scanning Infrared Horizon

Technical field:

The invention relates to a ground detection device for a space science instrument, in particular to a ground detection device for an attitude sensor infrared horizon suitable for satellite platforms.

Background technique:

The infrared horizon using the earth's infrared radiation as a reference target has the advantages of high precision and good reliability, so it is widely used. Early infrared horizons were used to control missile engine ignition and loading tests. It has been used on satellites since February 1959 and has successfully measured the attitude of satellites flying around the earth. Compared with other attitude-sensitive technologies, the infrared horizon is simple, reliable and has high attitude measurement accuracy (generally within 0.1°- 0.5°), so it develops rapidly. It will be widely used in future manned spaceships, especially on man-made satellites such as ground-directed reconnaissance, meteorology, communication, and ground information. At present, most space vehicles launched use infrared horizons to achieve attitude Therefore, the development of infrared horizon has also become an independent branch of science in satellite attitude measurement.

Since the average brightness temperature of the earth is 247K, and the average brightness temperature of space is about 4.2K, the infrared image of the earth seen by the satellite when it is in orbit is a "hot" disk in the background of deep and cold space, and its boundary is usually The so-called infrared horizon is flat and circular. As the attitude sensor of the satellite attitude control system, the infrared horizon is based on the sensitivity to the earth's infrared radiation, and realizes the measurement of the satellite's rolling and pitching attitude signals relative to the local vertical line in orbit, which is the capture of the earth when the satellite is initially incident. And the attitude control of the satellite during steady-state operation provides a measurement reference. The measurement accuracy and reliability of the infrared horizon are directly related to the accuracy and stability of the satellite flight attitude.

At present, the infrared horizons used on Chinese satellite platforms are mainly conical scanning infrared horizons. The working principle of the double-cone scanning infrared horizons is based on being sensitive to the difference in infrared radiation between the earth and the cold background of space. Using optical scanning The motor and the specially designed optical system (composed of fixed mirrors, rotating mirrors and infrared thermal detectors) perform biconical optical scanning of the earth based on the instantaneous field of view of the infrared thermal detectors, and the equivalent biconical scanning optical path of the optical system And the scanning trajectory of the earth and space is shown in Figure 1. The horizon radiation signal is imaged on the thermal element, and after being processed by the electronic system, four infrared horizons relative to the sensor reference signal 0 can be obtained in one scan cycle. Circle crossing points: space/earth crossing points (S/E) 1, 3, earth/space crossing points (E/S) 2, 4, the measurement of the satellite attitude angle is realized through the information processing circuit.

As a special ground performance testing equipment for infrared horizon products, the earth simulator is a necessary means to realize ground detection, calibration and full physical simulation of infrared horizon performance indicators.

Invention content:

The purpose of the present invention is to provide an earth simulator suitable for ground performance detection, calibration and full physical simulation of a bicone scanning infrared horizon in consideration of the characteristics of bicone optical scanning products. Provide ground test equipment for the evaluation of the performance index of the dual-cone scanning infrared horizon, so that the dual-cone scanning infrared horizon can provide higher-precision satellite attitude measurement.

The object of the present invention is achieved like this: a kind of earth simulator of the present invention carries out detection etc. to bicone scanning type infrared horizon instrument on the ground, comprises following seven parts at least: four cold and hot plate assemblies, a thermal Basin assembly, a hot and cold plate support, a hot basin support, a base, a temperature control system and a two-dimensional precision turntable.

The earth simulator uses the hot basin and the hot and cold plate components to form the earth simulation surface, statically simulates the earth/space cold and hot crossing the boundary, and accurately adjusts and locates the position of the hot and cold boundary of the earth simulator through the optical correction structure adjustment system , to reach the ideal boundary position, and control the position accuracy within a certain range; the heat basin of the ground model and the hot plate of the four cold and hot plate components are coated with organic black paint (the specific emissivity is 0.9), and they are heated to simulate the heat of the earth. Radiation; sandblasting and anodizing the thermal simulation surface of the cold plate assembly to simulate the space cooling background; the heater is designed to heat the sheet and paste it on the inside of the heated body, while heating the sheet and the simulation Spaces are isolated with insulating materials to prevent the temperature rise of the simulated space body caused by heat exchange.

The temperature control system, that is, the temperature control system of the horizon instrument, is mainly composed of 5 independent temperature difference control units, a temperature difference display instrument and a multi-channel temperature inspection unit, which are arranged in a special control cabinet. Each control unit is composed of a digital temperature regulator, a thyristor AC power controller and a temperature measuring thermocouple, forming a closed-loop temperature control loop; the working principle of the temperature control system is to use 5 independent temperature difference control units through digital The temperature regulator realizes PID temperature regulation, controls the temperature difference between the 4 hot plates and the hot basin relative to the cold plate respectively, and the display instrument and the multi-channel temperature cycle detection unit can display the current temperature difference between the hot plate and the hot basin.

The earth simulator controls the precision two-dimensional turntable through the two-dimensional turntable controller to realize the attitude angle deviation of the horizon, that is, the pitch angle and the roll angle, and the horizon installed on the precision two-dimensional turntable optically scans the earth simulator, thereby Realize the measurement of different attitude angles. The key technical index to measure the measurement accuracy of the infrared horizon is the random noise equivalent angle: under the normal working mode of the ground test system, the measured random noise equivalent angle (3σ) of the infrared horizon is less than 0.07 ^* .

The advantages of the present invention are:

1. Based on the working principle of dual-cone scanning infrared horizontal circular optical scanning, the earth simulator is designed as a compound structure relative to the vertical plane formed by the outer frame shaft and the U-shaped frame shaft that are orthogonal to the zero position of the two-dimensional precision turntable. : The hot tub assembly is installed on the base parallel to the front and rear through the hot tub bracket, and the four cold and hot plate assemblies are front and rear parallel. A simulated infrared horizon circle formed by the boundary relative to the ambient background. In addition to providing a completely equivalent earth infrared radiation observation target for infrared horizon products, this structure greatly reduces the earth infrared radiation heat simulation surface compared to the single plane structure that simulates the infrared horizon circle On the one hand, the heating power of the earth simulator is reduced, and on the other hand, it is easy to ensure the temperature uniformity requirements of the thermal simulation surface, especially the hot plate.

2. In view of the large size of the earth simulator and the large number of assembly parts, the machining accuracy and assembly accuracy are difficult to meet the positional accuracy requirements of the parts. Multi-dimensional adjustment mechanism, using two-dimensional rectangular guide rail moving pair, cylindrical moving pair, adjustable pads and thread adjustment, etc., to make the cold and hot plate assembly and hot basin assembly have multi-degree-of-freedom adjustment functions, ensuring the system’s stability during optical assembly and adjustment. Adjustability and precision requirements. In addition, due to the selection of the multi-dimensional adjustment mechanism, by adjusting the positional relationship between the cold and hot plate assembly and the hot basin assembly relative to the two-dimensional precision turntable, the earth simulator can simulate the attitude detection of satellites at different orbital heights within a certain range of satellite orbits.

3. The heating of the hot plate and hot basin of the earth simulator uses a thin-film heater, which is arranged on the back of the radiating surface of the hot plate and hot basin. It has the characteristics of uniform heat flux density on the heating surface, high thermal efficiency and long heater life. The heat insulation and heat insulation design is adopted for the hot plate and the hot basin, including between the hot plate and the cold plate, the supporting structure, and between the hot basin and the supporting structure and the shell. Therefore, the heating power of the earth simulator is small, the temperature rise speed is fast, the temperature rise range is large, the control range of the temperature difference between the cold and the hot boundary is wide, and the temperature control accuracy is high.

Description of drawings

Figure 1-1 and Figure 1-2 are schematic diagrams of the scanning optical path and the earth and space scanning trajectories of the known dual-cone scanning infrared horizon optical system;

Fig. 2 is the composition block diagram of the earth simulator among the present invention;

Fig. 3 is the earth simulation structure schematic diagram among the present invention;

Fig. 4 is the structural installation diagram of the cold and hot plate assembly in the present invention;

Figures 5-1, 5-2, and 5-3 are assembly diagrams of the cold and hot plate assembly in the present invention;

Fig. 6 is the structural installation drawing of hot tub assembly among the present invention;

Figures 7-1 and 7-2 are assembly diagrams of the hot tub assembly in the present invention;

Fig. 8 is a structural diagram of a two-dimensional precision turntable in the present invention;

Fig. 9 is a functional block diagram of the temperature control system in the present invention.

Detailed ways

Provide a preferred embodiment of the present invention below according to Fig. 2-Fig. It is intended to illustrate the present invention, but not to limit the scope of the present invention.

Fig. 2 has provided the system composition and its function of the earth simulator of the present invention. The cold and hot plate assembly 1 and the hot basin assembly 2 constitute the earth's infrared horizon 9 of the earth simulator; The temperature difference of the cold plate in component 1 realizes the simulation of the infrared radiation intensity of the earth relative to the cold background of space; the infrared horizon product 10 is installed on the two-dimensional precision turntable 3, and the two-dimensional precision turntable 3 is realized through the turntable control system 8. The three-dimensional rotation is used to simulate the deviation of the roll and pitch attitude of the satellite when it is in orbit.

As shown in FIG. 3 , the structural and functional modules of the earth simulator include a cold and hot plate assembly 1 , a hot basin assembly 2 , a two-dimensional precision turntable 3 , a cold and hot plate assembly support 4 , a base 5 and a hot basin assembly support 6 . Referring to the definition of the coordinate system when the satellite is in orbit, the orthogonal coordinate system OXYZ given in the figure is: the X axis is the roll axis, the Y axis is the pitch axis, and the Z axis is the yaw axis, where the X axis and the Y axis are respectively Two rotating shafts of the two-dimensional precision turntable 3. The positional relationship of the four cold and hot plate assemblies 1 and the hot basin assembly 2 with respect to the coordinate system OXYZ depends on the specific orbital altitude of the satellite. The position accuracy is controlled within ±0.01mm by optical calibration.

As shown in FIG. 4 , the cold and hot plate assembly 1 includes four independent cold and hot plate assemblies 11 , 12 , 13 , 14 , which are symmetrically installed on the cold and hot plate support 4 based on the Z axis through bolts. The hot and cold plate assemblies 11 and 13 have the same structure, and the hot and cold plate assemblies 12 and 14 have the same structure and are mirror images of each other. Boundaries L1-L4 are designed to simulate the earth's infrared horizon circle 9, and are used for accurate detection of the performance of the rolling attitude angle R of the infrared horizon product 10 when -7°≤R≤+7°. The hot and cold plate assembly bracket 4 is threadedly connected to the base 5 through the inclined support rod 41 and the bracket mounting base 42. Relative to the verticality of the horizontal plane, at the same time use the bracket installation base 42 to adjust the cold and hot plate assembly bracket 4 backwards and forwards relative to the front of the OXY.

Figures 5-1, 5-2, and 5-3 show the detailed structure of the hot and cold plate assembly 1 . The thermal plate 17 is embedded in the combined thermal plate seat 18 by means of a heat-insulating limit block, and the thermal simulation surface is coated with organic black paint with high specific emissivity. The thin film heater 120 is pasted on the back of the hot plate 17 . An organic foam heat insulating material 110 is designed between the heat plate 17 and the combined heat plate seat 18 . The cold plate 16 is installed on the cylindrical moving pair 130, and the thermal simulation surface is sandblasted and anodized. Through thread adjustment, it can move forward and backward relative to the hot plate 17 along the OZ axis. Rotate in the OXY plane. Utilize the rectangular guide rail moving pair 150 and the cylindrical moving pair 140 to realize the up-and-down translation and left-right translation of the hot and cold plates 16, 17 in parallel to the OXY plane.

The assembly relationship between the hot tub assembly 2, the hot tub assembly bracket 6 and the base 5 is shown in Figure 6, and the hot tub assembly 2 is fixed on the hot tub assembly through the mounting flange (27 in Figure 7), the mandrel and the lock nut. On the support seat of the assembly bracket 6, loosen the lock nut to rotate the heat tub assembly 2 around the axis of the heat tub to meet the requirements of optical alignment. The hot tub assembly bracket 6 is bolted to the base 5 through the mounting base 64, and the axis of the hot tub assembly 2 is coaxial with the OZ axis. Boundaries L5-L10 are used to simulate the earth's infrared horizon circle 9, and are used to measure the attitude of the infrared horizon product 10 when the rolling attitude angle R is 7°<|R|≤36°. The two-dimensional movement adjustment mechanism 62 and the threaded lifting mechanism 63 realize the translation of the hot tub assembly 2 in the OXZ plane and the vertical lifting along the OY axis.

Figures 7-1 and 7-2 show the assembly structure of the heat basin assembly 2. The heat basin consists of a boundary simulation surface 21, a circular platform concave cavity simulation surface 22 and an end cover simulation surface 23. The heat radiation simulation surface is coated with high specific radiation High rate organic black paint, film heaters 26, 29, 211, 212 and 214 are respectively configured on the back side of the hot basin. Between the shells 24, 210, 215 and the mounting flange 27 and the heat basin, heat insulating bolts are used to connect and organic foam heat insulating materials are used for filling 25, 28, 210 and 213.

As shown in FIG. 8 , the two-dimensional precision turntable 3 includes an outer frame 31 , a U-shaped frame 32 , a base 33 and a threaded adjustment leg 34 which are mechanically connected. The detected infrared horizon product 10 is installed on the mounting plate of the U-shaped frame 32 . The outer frame 31 simulates the rolling attitude angle, the U-shaped frame 32 simulates the pitching attitude angle, and the positioning accuracy of the rotation angle is better than 5″. The threaded adjustment leg 34 is used to adjust the horizontal position of the two-dimensional precision turntable 3 .

As mentioned above, the temperature control system 17 in the present invention is composed of 5 independent temperature difference control units, a temperature difference display instrument and a multi-channel temperature inspection unit, and is arranged in a dedicated control cabinet. As shown in Figure 9, each control unit is composed of a digital temperature regulator 74, a thyristor AC power controller 71, a temperature control thermocouple 73 and a thin film heater 120, and the temperature measurement terminal of the temperature control thermocouple 73 and the reference The ends are respectively embedded in the hot plate 17 (or hot basin) and the cold plate 16 to form a closed-loop temperature control loop. The PID temperature adjustment is realized through the digital temperature regulator 74, and the four hot plates 17 and the The temperature difference between the hot tub in the hot tub assembly 2 relative to the cold plate 16. The temperature difference control range is from 20°C to 40°C, and the temperature control accuracy is better than ±0.5°C.

In a nutshell, this embodiment provides an earth simulator suitable for the ground performance detection and calibration of the double-cone scanning infrared horizon and the full physical simulation, which belongs to the special ground test system designed for the satellite platform attitude sensor infrared horizon. , including a hot and cold plate assembly 1, a hot basin assembly 2, a hot and cold plate support 4, a hot basin support 6, a base 5, a temperature control system 7, and a two-dimensional precision turntable 3, characterized in that the heat of the hot basin assembly 1 The basin and the hot plate 17 of the four independent cold and hot plate assemblies 11, 12, 13, 14 constitute the earth infrared radiation simulation surface, the cold plate 16 and the system environment background of the four independent cold and hot plate assemblies 11, 12, 13, 14 Simulate the cold background of space, and the temperature-controlled heating of the hot plate 17 and the hot basin by the temperature control system 7, which is equivalent to simulating the 14-16 μm earth infrared radiation intensity and Gradient, to realize the infrared horizon circle target of the simulation of the boundary of the cold and hot plate and the outer boundary of the hot basin relative to the height of the satellite orbit; using the multi-dimensional adjustment mechanism in each component, the relative relationship between the boundary of the cold and hot plate and the outer boundary of the hot basin can be precisely adjusted through the optical calibration method At the position of the two-dimensional precision turntable 3, the geometric positional relationship between the specific orbital height satellite and the earth's infrared horizon circle is realized; the two-dimensional precision turntable 3 includes a turntable base 33, an outer frame 31, a U-shaped frame 32 and a control system ( Adjusting feet) 34, wherein the outer frame 31 and the U-shaped frame 32 can independently rotate around the orthogonal axis, and the measured infrared horizon product 10 is installed on the U-shaped frame 32 mounting plate of the two-dimensional precision turntable 3, and the two-dimensional rotating To simulate the roll and pitch attitude angle deviation of the satellite when it is in orbit, to realize the measurement of the attitude angle, and then to realize the ground performance detection of the dual-cone scanning infrared horizon.

With respect to the vertical plane formed by the rotating shaft of the outer frame 31 and the rotating shaft of the U-shaped frame 32 that are orthogonal to the zero position of the two-dimensional precision turntable 3, the hot tub assembly passes through the hot tub bracket 6, four independent cold and hot plate assemblies 11, 12, 13 and 14 are installed on the base 5 in parallel front and rear through the cold and hot plate bracket 4 to form a composite structure, wherein the cold plate 16 and the hot plate 17 composed of four independent cold and hot plate assemblies 11, 12, 13, 14 The simulated infrared horizon circle 9 is used for accurate detection of the performance of the infrared horizon product 10 when the rolling attitude angle R is -7°≤R≤+7°, such as the accuracy, linearity and ground calibration of the product attitude angle measurement; and by The simulated infrared horizon circle 9 formed by the heat basin outer boundary L5-L10 of the heat basin assembly 2 relative to the environmental background is used for the attitude of the infrared horizon product 10 when the rolling attitude angle R is R≤-7° and R≥+7° The detection of the angle is used for the measurement of the working field of view of the product 10; the heat basin is designed as a concave cavity structure, which ensures the space requirement for the outer frame of the two-dimensional precision turntable 3 when simulating the deviation of the attitude angle;

The multi-dimensional adjustment mechanism used for optical calibration in each of the components includes a two-dimensional rectangular guide rail moving pair 50, a cylindrical moving pair 130, 140, an adjustable pad and a threaded adjustment mechanism, so as to ensure the accuracy of the infrared ground circle simulation boundary. The optical correction accuracy is in the range of ±0.01mm;

The temperature control system 7 is mainly composed of 5 independent temperature difference control units, a temperature difference display instrument and a multi-channel temperature inspection unit, which are arranged in a dedicated control cabinet. Each control unit is mainly composed of a digital temperature regulator 74, a thyristor The AC power controller 71 and the temperature measuring thermocouple 73 form a closed-loop temperature control loop. The temperature control system uses 7 independent temperature difference control units of 7 channels to realize PID temperature adjustment through a digital temperature regulator, and controls 4 hot plates respectively. 17 and the temperature difference between the hot plate and the cold plate 16, the display instrument and the multi-channel temperature inspection unit can display the current temperature difference between the hot plate and the hot plate;

The surface of the hot plate 17 of the cold and hot plate assembly 1 and the hot basin of the hot basin assembly 2 simulating the earth’s infrared radiation are coated with organic black paint, and the surface of the cold plate 16 of the cold and hot plate assembly 1 simulates the cold background of space for sandblasting and anodization In order to meet the design requirements for the radiation characteristics of the infrared radiation surface, the heating of the hot plate 17 and the hot basin adopts a thin film heater 120, which is arranged on the back of the hot plate 17 and the radiant surface of the hot basin; the hot plate 17 and the hot basin adopt Heat insulation and heat insulation design, including between the hot plate 17 and the cold plate 16, the supporting structure, between the hot basin and the supporting structure, and the shell; the maximum heating power of the temperature control system is less than 2Kw, and the slowest heating time is 45min , The temperature difference control range is 20-40°C, the temperature control accuracy is between ±0.5°C, and the temperature unevenness is less than ±1.5°C.

Claims (5)

1. a suitable double cone scanning type infrared horizon instrument ground performance detects the earth simulator for earth of usefulness, belong to and be the supporting design-calculated dedicated ground of satellite platform attitude sensor infrared horizon instrument test macro, comprise cold-hot plate component, hot basin component, cold-hot plate bracket, hot basin bracket, pedestal, temperature control system and two-dimensional precision rotating platform, it is characterized in that, constitute earth infrared radiation falseface by the hot basin of hot basin component and the hot plate of four cold-hot plate components, cold drawing and system environments background simulation space cold-scarce scape by cold-hot plate component, and by the temperature control heating of temperature control system to hot plate and hot basin, equivalent simulation satellite infrared horizon instrument is obtained when rail 14-16 μ m earth infrared intensity and gradient with respect to space cold-scarce scape realize the infrared horizon circle target of cold and hot edges of boards circle and hot basin exterior boundary simulation with respect to satellite orbital altitude; Have the multidimensional regulating mechanism in each assembly, accurately adjust cold and hot edges of boards circle and hot basin exterior boundary position, realize the geometry site of certain tracks height satellite and earth infrared horizon circle with respect to two-dimensional precision rotating platform by optical correction; Two-dimensional precision rotating platform comprises turret base, housing, U type frame and the control system with mechanical connection, wherein housing and U type frame can independently rotate around quadrature-axis, tested infrared horizon instrument is installed on the two-dimensional precision rotating platform U type frame adapter plate, utilize its two dimension to rotate rolling and the pitch attitude angular deviation of analog satellite when rail, thereby realize the measurement of attitude angle, and then realize that the ground performance of double cone scanned infrared horizon instrument detects.

2. suitable double cone scanning type infrared horizon instrument ground performance according to claim 1 detects the earth simulator for earth of usefulness, it is characterized in that, the vertical guide that the housing rotating shaft of quadrature and the rotating shaft of U type frame are constituted during with respect to the two-dimensional precision rotating platform zero-bit, hot basin component passes through hot basin bracket, four cold-hot plate components are installed on the pedestal by before and after the cold-hot plate bracket abreast, constitute duplex, wherein, by the simulation infrared horizon circle that the cold drawing and the hot plate of four cold-hot plate components constitutes, be used for the infrared horizon instrument product and accurately examine the precision of this product attitude angle during in-7 °≤R≤+ 7 ° as roll attitude angle R, the linearity and ground are demarcated; And by the hot basin exterior boundary of hot basin component with respect to the simulation infrared horizon circle that environmental background constitutes, be used for of the detection of infrared horizon instrument product when roll attitude angle R attitude angle in R≤-7 ° and during R 〉=+7 °, be used for the measurement of the product work ken; Hot basin is designed to curved cavity, guarantees the housing rotary space requirement of two-dimensional precision rotating platform when simulation attitude angle deviation.

3. the earth simulator for earth that suitable double cone scanning type infrared horizon instrument Performance Detection according to claim 1 is used, it is characterized in that, the multidimensional regulating mechanism that is used for optical correction in described each assembly, comprise two-dimensional rectangle guide rail moving sets, cylindrical moving sets, scalable cushion block and threaded adjusting mechanism, with the optical correction precision that guarantees infrared horizon circle simulating boundary in ± 0.01mm scope.

4. suitable double cone scanning type infrared horizon instrument ground performance according to claim 1 detects the earth simulator for earth of usefulness, it is characterized in that, temperature control system is mainly by 5 tunnel separate temperature difference control units, temperature difference display instrument and multi way temperature follow the inspection unit and form, be configured in the special-purpose control housing, every road control unit is mainly by the digital temperature regulating control, SCR AC electric power controller and temperature thermocouple constitute, form the closed loop thermal control loop, temperature control system utilizes 5 tunnel separate temperature difference control units to realize the PID adjustment by the digital temperature regulating control, control 4 blocks of hot plates and the hot basin temperature difference with respect to cold drawing respectively, display instrument and multi way temperature follow the inspection unit can show the hot plate and the current temperature difference of hot basin.

5. suitable double cone scanning type infrared horizon instrument ground performance according to claim 1 detects the earth simulator for earth of usefulness, it is characterized in that, the surface coating of the simulation earth infrared radiation of the hot plate of cold-hot plate component and the hot basin of hot basin component is organic pitch-dark, anodizing sandblasts on the surface of the cold drawing simulation space cold-scarce scape of cold-hot plate component, design the requirement of going up to satisfy to infrared radiation surface emissivity characteristic, thin film heater has been selected in the heating of hot plate and hot basin for use, is configured in the back side of hot plate and hot basin radiating surface; Hot plate and hot basin have adopted heat insulation and insulated design, between hot plate and cold drawing, supporting structure, between hot basin and supporting structure, the shell; The maximum heating power of temperature control system is less than 2Kw, and the temperature rise time is 45min the most slowly, and temperature difference range of control is at 20～40 ℃, and accuracy of temperature control is between ± 0.5 ℃, and the non-uniform temperature degree is less than ± 1.5 ℃.

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