CN111879409A - Device and method for measuring earth outward radiation energy based on lunar-based platform - Google Patents

Abstract

The invention discloses a moon-based platform-based earth external radiation energy measuring device and method. The device includes a detector cavity system, a temperature control system, a support system and a filter system. The double-layer shell combined with the cross-supporting plate is adopted, and the wall surface is coated with a specific emissivity material, which can effectively reduce the heat conduction loss and radiation heat loss of the detector barrel, thereby improving the temperature control accuracy of the detector barrel and Reduce energy consumption. Secondly, the four-channel detector barrel, together with the eight-hole filter wheel and the three-hole light baffle, can realize high-precision detection of different bands of radiated energy from the earth. Placing the temperature control baffle between the detector barrel and the filter wheel can reduce the influence of temperature fluctuations of the filter wheel and the light baffle on the detector barrel. Reduce the influence of the external lunar surface temperature environment on the working performance of the detector.

Description

A moon-based platform-based device and method for measuring external radiation energy from the earth

technical field

The invention belongs to the technical field of the earth's outward radiation energy detection by a moon-based detection platform, and particularly relates to a moon-based platform-based earth's outward radiation energy measurement device and method.

Background technique

Since industrialization, the global climate has shown a warming trend, which has aroused concerns from all walks of life about changes in the environment for human survival and development. Fundamentally speaking, the change of the earth's climate depends on the change of the radiation energy budget in the earth-atmosphere system, and the current observation and research on the change of the earth-atmosphere radiation energy budget mainly rely on surface meteorological observation stations and spaceborne earth observation sensors. The data. For ground observation stations, the detection data is not only affected by the atmosphere and the surrounding environment of the station, but also is insufficient and unevenly distributed. Since the late 1970s, many countries in the world have successively launched dozens of artificial earth satellites specially designed to measure the radiation of the sun and the earth. However, there are still many shortcomings in the measurement of artificial earth satellites. The measurement results of different satellites sometimes even contradict each other. The main reason is that the observation angle of artificial earth satellites is limited, and it is not a long-term stable observation platform. Short operating life, limited instantaneous field of view spatial coverage, orbital drift, sensor aging degradation and other factors are not conducive to long-term continuous observation of the earth's global scale. Therefore, it is very necessary to observe the Earth's climate energy balance from a new angle and approach, and to explore the mechanism of global climate change. As the earth's eternal natural satellite, in contrast, it can provide a new earth observation platform to make up for the lack of satellite observations, and provide more accurate and comprehensive data for humans to conduct more in-depth research on the energy balance process of the earth's climate system support.

At the top of the atmosphere, radiation is the only way of energy exchange. The energy changes in the climate system are the result of a balance between the absorption of shortwave radiation from the sun and the emission of longwave radiation into space. Earth's radiation budget detection mainly measures three parts of radiation: the sun's radiation to the climate system (receive), the climate system's long-wave radiation to outer space (branch), and the climate system's reflection of solar radiation (branch). The first part of the radiation (receive) is relatively stable, and the annual rate of change is small, and the change of total solar radiation can be monitored for a long time by a solar radiation monitor. Earth radiation detectors usually use two channels of 0.2-5μm short-wave and 0.2-100μm full-band broadband observations. The short-wave channel mainly observes the solar radiation reflected by the climate system, and the full-wave channel observes the sum of the reflected solar radiation and the outgoing long-wave infrared radiation. On the surface, the surface radiation balance determines the amount of radiation absorbed by the land surface, and the radiation distribution causes natural phenomena on the surface to vary over time and space. Net surface radiation is generally the sum of short-wave and long-wave radiation energies. Surface albedo is the most important parameter in short-wave radiation balance estimation, and surface temperature and emissivity are very important surface variables in long-wave radiation balance estimation. Range: 8μm-12μm), the setting of this band mainly considers the two factors that the detected target has the strongest signal characteristics in this band and the detected remote sensing information can reach the sensor through the atmosphere to the greatest extent.

The moon is the closest natural celestial body to the earth, and it is also the only extraterrestrial body that human beings can reach and have already reached. It has the advantages of long-term consistency, integrity and stability of earth observation. At the same time, the distance between the moon and the earth is more than 300,000 kilometers. , a small telescope can obtain the observation of the entire disk of the earth, and a variety of sensors can be arranged in the vast space of the moon, which is convenient for the coordinated observation of the earth by a variety of detectors. These features can provide support for the integrated research of global-scale multi-layers, and it is possible to realize the mutual coupling of global multi-layers from the perspective of earth system science, including global air-sea interaction, land-air interaction and boundary layer atmospheric processes, and sea-land correlation changes. and scientific explanations of phenomena such as coastal processes, global energy balance, etc. In recent years, with the rise of lunar exploration, the construction planning of lunar bases has also been put on the agenda by the world's aerospace powers, thus laying a solid foundation for exploring the moon and conducting lunar-based observations of the earth and space. When the detector on the moon-based platform observes the radiated energy from the earth, the lunar surface does not have the influence of the complexity of various circles such as the atmosphere. At the same time, due to the tidal locking effect, the lunar near-Earth hemisphere can always face the earth. Therefore, placing the radiated energy from the earth on the lunar surface near the earth can give full play to the integrity, long-term, consistent and continuous earth observation of the lunar-based platform. sexual characteristics. In order to give full play to the advantages of the moon-based platform in detecting the earth's outward radiation energy, the present invention provides a moon-based platform-based earth's outward radiation energy measuring device and method based on the special ambient temperature of the lunar surface.

SUMMARY OF THE INVENTION

The invention provides a moon-based platform-based earth radiation energy measuring device and method, which realizes the detection of the earth's radiation in different bands based on the moon-based platform, and can obtain large-scale and dynamic energy balance for studying the entire earth system. Continuous observational data to meet the needs of global-scale observational capabilities for scientific issues of global change.

In order to achieve the above-mentioned purpose, the present invention is a moon-based platform-based earth external radiation energy measurement device, comprising an outer cylinder, an inner cylinder, a detector cylinder, a filter wheel, a top cover, an outer field of view cylinder and a power device, and an outer cylinder. An inner tube is arranged in the tube, a top cover is arranged on the top of the outer tube, and M through holes for passing light are opened on the top cover. There is a filter wheel, and a group of working filters is installed on the filter wheel; a plurality of detector barrels are arranged in the inner barrel; the power device is used to drive the filter wheel to rotate; the detector barrel includes a temperature-controlled field of view barrel and a set of In the detector cavity below the temperature control field of view cylinder, the upper part of the detector cavity is installed with a detection main cavity, and the lower part is installed with a detection auxiliary cavity. The detection main cavity and the detection auxiliary cavity are exactly the same, and they are arranged back to back; A first temperature control heating wire and a first temperature sensor are installed in the detection main cavity; a second temperature control heating wire and a second temperature sensor are installed in the detection auxiliary cavity.

Further, the upper end of the detection main cavity is provided with a precision field of view hole, and the precision field of view hole is used to control the area of the detection main cavity to receive radiation.

Further, a temperature control baffle is arranged between the inner cylinder and the filter wheel.

Further, an annular support frame is installed at the bottom of the outer cylinder, the inner cylinder is installed on the annular support frame, a support plate is arranged in the inner cylinder, and the detector cylinder is suspended on the support plate.

Further, two sets of filters are installed on the filter wheel: a working filter set and a verification filter set. The working filter set includes filters with an efficient pass band of 0.2 μm-100 μm, and an efficient pass band of 8μm-12μm filter, high-efficiency pass filter with wavelength range of 5μm-100μm, verify that the filter set includes at least the same set of filters as the working filter set; a light baffle is provided above the filter wheel , the light baffle is provided with at least three light passing holes.

Further, two layers of filters are installed at the same position of the filter wheel, and the filters installed at the same position are identical.

Further, the inner side of the outer cylinder, the inner and outer sides of the inner cylinder, and the outer side of the detector cylinder are all coated with a thermal control coating with an emissivity of less than 0.05.

Further, the inner wall and bottom of the detector cavity are provided with heat sinks.

A method for radiating energy outward from the earth based on the moon-based platform of the above-mentioned measuring device of claim, comprising the steps of:

Step 1: Keep the set working temperature of the detector cylinder unchanged, so that the working temperature difference between the detection main cavity and the detection auxiliary cavity is always maintained at 0.5 °C;

Step 2: Rotate the filter wheel so that the centerlines of the different detector cylinders are collinear with the centerlines of the filters in the working filter set in the filter wheel. At this time, other holes on the filter wheel filter The light sheet is in a non-working state;

Step 3: Enter the deep space observation mode: Aim the center line of sight of the detector to the deep space, and maintain the thermal environment state in step 1 according to the set temperature requirements; monitor the electric heating power PE of the detection main cavity in each detector cylinder ₁ ;

Step 4: Enter the earth observation mode: Aim the detector's center line of sight to the earth, and maintain the thermal environment state in step 1 according to the set temperature requirements; monitor the electric heating power PE ₂ of the detection main cavity in each detector cylinder ;

Step 5: Calculate the earth's outward radiation energy PE, PE=PE ₁ -PE ₂ ; the earth's outward radiation energy PE calculated by each detector barrel is the passing band of the filter facing the detector barrel. The earth radiates energy outward.

Further, after the device runs for a set time, the filter performance is verified, and the specific process is: driving the filter wheel to rotate, so that the detector cylinder and the verification filter set filter on the filter wheel are in the right direction, Repeat steps 3 to 5 to obtain another set of earth radiated energy PE. If the obtained earth radiated energy at this time and the data measured by using the working filter set are within the error range, it means that the working mode is used. The filtering performance of the filter has not deteriorated; otherwise, it indicates that the filtering performance of the optical filter used in the working mode has deteriorated. At this time, the data detected in the working mode needs to be corrected.

Compared with the prior art, the present invention has at least the following beneficial technical effects:

The invention adopts a plurality of detector cylinders with the same design in the structure, processing and assembling process to form a multi-channel detection structure, and combined with the filter wheel and the light baffle can realize the high-precision detection of different wavelength bands of the earth's outward radiated energy. Some of these channels are used for routine detection, and the remaining channels are used for periodic verification of filter performance. During the working mode, the first detection channel corresponds to the ultraviolet to far-infrared channel (the detection band range is 0.2μm ~ 100μm), which is used to measure the total radiation energy that leaves the earth system and reaches outer space; the second channel is the far-infrared band channel ( The wavelength range is 5μm-100μm), which is used to measure the radiation energy emitted by the Earth's climate system to outer space; the fourth channel is the earth's infrared radiation channel (wavelength range is 8μm-12μm), which is used to measure the long-wave infrared energy emitted by the earth. Radiated energy in multiple bands can be measured simultaneously.

Further, the present invention adopts a double-layer shell structure composed of the inner cylinder and the outer cylinder, the detector cylinder is fixed on the support plate through the connecting piece, and the support plate is fastened with the inner cylinder through the connecting piece.

The contact area between the detector barrel and the support plate is small, and the thermal insulation material can effectively reduce the heat conduction loss of the detector barrel. The emissivity material can effectively reduce the dissipation of heat along the radial direction, improve the temperature control accuracy of the detector cylinder and reduce energy consumption.

Further, the temperature control baffle is placed between the detector cylinder and the filter wheel, which reduces the influence of temperature fluctuations of the filter wheel and the light baffle on the detector cylinder. The transmission gears are all built into the outer cylinder, which also keeps a relatively closed and stable environment inside the outer cylinder, reducing the influence of the external lunar surface temperature environment on the working performance of the detector.

Further, the wires of all electrical equipment in the whole system are drawn out from the wire lead-out holes on the edge of the top cover; except for the openings of the connecting pieces, no other openings are set in the entire outer and inner cylinders to ensure the sealing of the entire system and reduce heat loss.

Further, a heat sink is arranged on the inner wall and bottom of the detector cavity, and the temperature of the heat sink is controlled to a constant temperature by a thermostat and a heater, so as to ensure a constant temperature difference between the detection main cavity and the heat sink, thereby realizing the detection of weak detection. Effective and accurate detection of radiant energy.

The measurement method of the present invention can verify the stability of the thermal environment of the detector by alternately performing deep space observation and earth observation, and can effectively eliminate the deep space background when observing the earth. effects of radiation.

Further, after working for a period of time, the performance change of the filter is verified. If the verification fails, the measured data is corrected to improve the accuracy of the measurement.

Description of drawings

Figure 1 is a structural diagram of the detector system;

Figure 2 is a schematic diagram of a four-channel cylinder of the detector;

3 is a schematic diagram of a filter wheel;

4 is a schematic diagram of a light baffle;

FIG. 5 is a schematic diagram of the cooperation relationship between the detector channel, the filter wheel and the light baffle.

In the attached drawings: 1-outer cylinder, 2-inner cylinder, 3-annular support frame, 4-cross support plate, 5-detector cylinder, 6-temperature-controlled field of view cylinder, 7-temperature-controlled baffle plate, 8- Filter wheel, 9-light baffle, 10-top cover, 11-stepper motor, 12-outer field tube, 13-connector, 14-filter, 15-filter holder, 16-transmission gear , 17-detector cavity, 18-detection main cavity, 19-detection auxiliary cavity, 20-heat sink, 21-precision field of view hole.

Detailed ways

In order to make the purpose and technical solutions of the present invention clearer and easier to understand. The present invention will be further described in detail below with reference to the accompanying drawings and embodiments. The specific embodiments described herein are only used to explain the present invention, but not to limit the present invention.

In the description of the present invention, it should be understood that the terms "center", "portrait", "horizontal", "top", "bottom", "front", "rear", "left", "right", " The orientation or positional relationship indicated by vertical, horizontal, top, bottom, inner, outer, etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present invention and The description is simplified rather than indicating or implying that the device or element referred to must have a particular orientation, be constructed and operate in a particular orientation, and therefore should not be construed as limiting the invention. In addition, the terms "first" and "second" are only used for descriptive purposes, and should not be construed as indicating or implying relative importance or implying the number of indicated technical features. Thus, a feature defined as "first" or "second" may expressly or implicitly include one or more of that feature. In the description of the present invention, unless otherwise specified, "plurality" means two or more. In the description of the present invention, it should be noted that the terms "installed", "connected" and "connected" should be understood in a broad sense, unless otherwise expressly specified and limited, for example, it may be a fixed connection or a detachable connection Connection, or integral connection; it can be mechanical connection or electrical connection; it can be directly connected, or indirectly connected through an intermediate medium, and it can be internal communication between two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood in specific situations.

Referring to FIG. 1 , a moon-based platform-based earth radiated energy measuring device consists of an outer cylinder 1, an inner cylinder 2, an annular support frame 3, a cross support plate 4, a detector cylinder 5, a temperature control baffle 7, The filter wheel 8 , the light baffle 9 , the top cover 10 , the stepping motor 11 , the outer field of view tube 12 , the connecting piece 13 , the transmission gear 16 , the heat sink 20 and the precise field of view hole 21 are formed. These components together form the detector cavity system, temperature control system, support system and filter system.

1) The main body of the detector cavity system is four detector barrels 5 and four external field barrels 12 . The detector barrel 5 is composed of a temperature-controlled field of view barrel 6 and a detector cavity 17 disposed below the temperature-controlled field of view barrel 6 . The function of the temperature-controlled field of view tube 6 is to maintain the detected ambient temperature as a set temperature value by means of electric heating. The function of the detector cavity 17 is to receive the radiation energy after passing through the external field tube 12 , the filter 14 , the temperature control baffle 7 and the precise field of view hole 21 in sequence, so as to measure the radiation energy by means of electrical substitution.

The upper end of the detector cavity 17 is provided with a precise field of view hole 21, the inner wall and bottom of the detector cavity 17 are provided with a heat sink 20, the upper part of the detector cavity 17 is installed with a detection main cavity 18, and the lower part is installed with a detection auxiliary cavity 19 , the detection main cavity 18 and the detection auxiliary cavity 19 are exactly the same, and they are arranged back to back; the detection main cavity 18 is installed with a first temperature control heating wire and a first temperature sensor; the detection auxiliary cavity 19 is installed with a second The temperature control heating wire and the second temperature sensor; the heat sink 20 of the detector cavity 17 is provided with a third temperature control heating wire and a third temperature sensor, and the outer wall of the temperature control field of view cylinder 6 is provided with a fourth temperature control heating wire and a third temperature sensor. Fourth temperature sensor. The first to fourth temperature-controlled heating wires are used to heat the part where they are located, and the temperature-controlled heating wires and temperature sensors set on the outer wall of the temperature-controlled field of view barrel 6 and the heat sink 20 are used to ensure the required special thermal environment for work. . The first to fourth temperature sensors are used to measure the temperature at the location to realize the measurement of radiation. The heat sink 20 is composed of a copper heat sink and an aluminum heat sink, and a third temperature control heating wire and a third temperature sensor are installed between the copper heat sink and the aluminum heat sink and outside the aluminum heat sink. The precise field of view hole 21 is arranged at the upper end of the detection main cavity 18 to control the amount of radiation energy entering the detection main cavity and to limit the input radiation.

2) The temperature control system is mainly composed of heat insulation gasket, temperature control baffle 7, low emissivity material, first to fourth temperature control heating wires and first to fourth temperature sensors.

The thermal insulation gasket is arranged at the place where the detector cylinder 5 is connected and fastened with the cross support plate 4 through the connecting piece 13 and the bolt, the inner side of the outer cylinder 1, the inner and outer sides of the inner cylinder 2, the upper and lower sides of the temperature control baffle 7, The outside of the detector barrel 5 is coated with a specific low emissivity material (such as sprayed with black paint with an emissivity less than 0.05).

The temperature control baffle 7 is placed between the detector barrel 5 and the filter wheel 8 to reduce the influence of the temperature fluctuation of the filter wheel 8 and the light baffle 9 on the detector barrel 5 .

3) The support system is mainly composed of an outer cylinder 1, an inner cylinder 2, an annular support frame 3 and a cross support plate 4. An annular support frame 3 is installed at the bottom of the outer cylinder 1, an inner cylinder 2 is arranged on the annular support frame 3, the upper end of the inner cylinder 2 is connected with one end of a plurality of connecting pieces 13 through bolts, and the other end of the plurality of connecting pieces 13 is connected with the outer cylinder 1 through bolts. Fixed connection. The inner cylinder 2 is connected with the outer cylinder 1 in a center-aligned manner; the cross support plate 4 is fixed in the inner cylinder 2 through the connecting piece 13 and the bolts, and the four detector cylinders 5 are fixed with the cross support plate 4 through the connecting piece 13 and the bolts Connection; the bottom of the four detector cylinders 5 and the bottom of the inner cylinder 2 are not in contact. The temperature control baffle 7 is fixed on the upper end of the inner cylinder 2 by bolts, and the temperature control baffle 7 is provided with a through hole for passing radiant energy; The top cover 10 is connected and fixed; the top cover 10 and the outer cylinder 1 are connected and fixed by connecting pieces 13 and fasteners. The top cover 10 is provided with a motor shaft hole, a wire lead-out hole, a bolt connection hole and a radiation through hole.

The inner cylinder 2 and the outer cylinder 1 together form a double-layered shell structure, which can effectively reduce the heat dissipation along the radial direction after coating the wall with a specific emissivity material.

The contact area between the detector cylinder 5 and the cross support plate 4 is small, and the thermal insulation material is arranged at the contact point and the specific emissivity material is coated on the wall surface, which can effectively reduce the heat conduction loss and radiation heat loss, and improve the detector cylinder 5. Temperature control accuracy and reduced energy consumption.

4) The filter system is mainly composed of a stepping motor 11 , a filter wheel 8 , a light baffle 9 and a transmission gear 16 . The filter wheel 8 is disposed directly above the temperature control baffle 7 , and a light baffle 9 is disposed directly above the filter wheel 8 , and both the filter wheel 8 and the light baffle 9 are located under the top cover 10 . The light baffle 9 and the filter wheel 8 form a coaxial system and are driven by a group of stepper motors 11 and transmission gears 16 ; The group of stepping motors 11 includes two motors, one for driving the light baffle 9 and the other for driving the filter wheel 8 .

3, wherein the filter wheel 8 is composed of a filter 14 and a filter holder 15; An optical filter 14 is installed in the hole, and the double-layer arrangement can reduce the influence of the thermal effect of the optical filter on the detector. Specifically, filter A, filter B, filter C, filter D, filter E, filter F, filter G and filter H are adjacent in sequence. The high efficiency band of filter A is 0.2μm-100μm, the high efficiency band of filter B is 8μm-12μm, the high efficiency band of filter C is 5μm-100μm, and the high efficiency band of filter D is 8μm -12μm, the high efficiency band of filter E is 5μm-100μm, the high efficiency band of filter F is 0.2μm-100μm, the high efficiency band of filter G is 8μm-12μm, the high efficiency band of filter H is The wavelength range is 5μm-100μm.

The channel where the filter with the high-efficiency passing band is 0.2μm-100μm is the ultraviolet to far-infrared channel, which is used to measure the total radiant energy leaving the earth system and reaching outer space; the channel where the filter with the high-efficiency passing band is 5μm-100μm is the far-infrared channel. The infrared channel is used to measure the radiant energy emitted by the earth's climate system to outer space; the channel where the 8μm-12μm filter with high efficiency pass band is located is the earth infrared radiation channel, which is used to measure the long-wave infrared energy emitted by the earth.

4, the light baffle 9 is provided with three light passing holes, the light passing hole X, the light passing hole Y and the light passing hole Z, and the line segment obtained by connecting the centers of the light passing hole Y and the light passing hole Z is L, and the light passing through The hole X is located at the midpoint of the line segment L and is on a straight line perpendicular to the line segment L, and the centers of the light passing hole X, the light passing hole Y and the light passing hole Z are located on the same circumference.

1 and 2 , four identical detector cylinders 5 are used to form a 4-channel detection structure, and the four detector cylinders 5 are evenly distributed on the same circumference. With different combinations of the 8-hole filter wheel 8 and the 3-hole light baffle 9, high-precision detection of different wavelength bands of the earth's outward radiated energy is realized. The detectors are provided with four detector cylinders 5, each of which is a channel, wherein the first, second and fourth cylinders 5 perform daily detection, and the third channel is used to periodically check the filter 14 The performances of the first, second and fourth cylinders are calibrated and verified, and the four detector cylinders 5 are identical in structure, processing and assembly to reduce the introduction of errors.

The detector barrel 5 , the filter 8 , the light baffle 9 and the outer field of view barrel 12 must be kept coaxial, and the coaxial detector barrel 5 , the filter 8 , the light barrier 9 and the outer field of view barrel 12 A channel is formed, and the present invention has four channels in total. The temperature-controlled field of view tube 6, the outer field of view tube 12 and the precise field of view hole 21 must strictly control the aperture size accuracy, and ensure that the central axes of the three are collinear after installation; The diameter of the sheet 14 and the light baffle 9 is 5 mm larger than the diameter of the outer field of view barrel 12 to ensure the efficient and complete passage of radiant energy.

The filter wheel 8, the light baffle 9 and the transmission gear 16 are all built into the outer cylinder 1, the filter wheel 8 is located directly above the inner cylinder 2, and the light baffle 9 is located directly above the filter wheel 8, keeping the inside of the detector as A relatively closed and stable environment reduces the influence of the external lunar surface temperature environment on the working performance of the detector.

The wires of all electrical equipment of the entire energy measuring device are drawn out from the wire lead-out holes on the edge of the top cover 10; the entire outer cylinder 1 and inner cylinder 2 are not provided with other openings except for the holes where the bolts need to be installed to ensure the entire The closedness of the system reduces heat loss.

The measurement principle of the earth's outward radiation measurement device based on the moon-based platform and the steps of its use are as follows:

working principle:

The working principle of the earth's outward radiation energy measurement based on the moon-based platform is: it is realized by the method of using the electric heating power to replace the received earth's outward radiation energy, and it can be expressed by the following formula:

Among them, PE represents the electric heating power of the detection main cavity 18; _{PR represents} the radiation power incident to the detection main cavity 18; K _C is the detection main cavity 18, the heat sink 20 and the detector auxiliary cavity 19. The sum of thermal conductivity and thermal resistance; ΔT _C represents the sum of the heat exchange temperature differences between the detection main cavity 18 and the heat sink 20 and the detector auxiliary cavity 19; C _C represents the heat capacity of the detection main cavity 18; T _C represents the detection main cavity 18. The temperature in the cavity 18; ∑P _r represents the sum of the radiation heat exchange between the detection main cavity 18 and other parts inside the detector cylinder 5, ∑Q _i is the sum of the heat transferred by the detector cavity through various leads and.

The working temperature of the detector cylinder 5 is set to be 30°C, and the working temperature difference maintained between the detection main cavity 18 and the detection auxiliary cavity 19 is 0.5°C. When the incident radiation power P _R =0, it means that the system maintains the working temperature difference between the detection main cavity 18 and the detection auxiliary cavity 19 to be ΔT=0.5°C completely under the condition of electric heating power. When the incident radiation power P _R ≠0, it means that the measuring device maintains the working temperature difference between the detection main cavity and the detection auxiliary cavity under the condition of electric heating power and incident radiation power as ΔT=0.5°C, so The incident radiant power is equal to the change of the electric heating power, so the incident radiant energy can be calculated from the power change of the electric heater.

After the detector works stably, the items on the right side of Equation 1 are constant terms and will not change. At this time, the electric heating power _{PE of the detection main cavity 18 and the sum P R of} the incident radiation power is a constant, which can be The target radiation heating power P _R is obtained by measuring the electric heating power _PE of the detection main cavity, as shown in Equation 2:

After the detector is assembled on the ground, the value on the right side of the equal sign in equation (1) can be obtained by calibration according to the thermal environment required by the setting.

Due to the harshness of the lunar surface space environment, the performance of the optical filter may decline and decline. Therefore, in order to verify the performance and change of the optical filter, after the detector works for a period of time, the stepping motor 11 drives the filter wheel 8 Enter the filter performance detection mode, verify its performance, and re-calibrate the thermal environment data and store it. If the measurement data of the front and rear detectors are within the error range, it means that the filter performance in operation has not deteriorated; otherwise, the detection data needs to be corrected. The matching method of the detector channel, the filter and the light passing hole adopts the matching method from bottom to top in sequence, as shown in Figure 5, such as the combination method of 1AX: where 1 represents the first channel, A represents filter A, X stands for via X.

Instructions:

Step 1: Set the working temperature of the detector cylinder to 30°C through the temperature-controlled heating wire, and the working temperature difference between the detection main cavity 18 and the detection auxiliary cavity 19 maintained by the temperature-controlled heating wire and the main cavity heating wire is 0.5 °C.

Step 2: The stepping motor 11 drives the filter wheel 8 and the field of view baffle 9, so that the centerlines of the first channel, the second channel and the fourth channel of the detector are The centers of filter C and filter G are collinear with the center lines of light passing hole X, light passing hole Y, and light passing hole Z. At this time, the matching method of detector channel, filter and light passing hole is: the first channel , filter A and light passing hole X are coaxial, the second channel, filter C and light passing hole Y are coaxial, and the fourth channel, filter G and light passing hole Z are coaxial; at this time, the detector The cavity is in the working mode, and the other aperture filters on the filter wheel 8 are in a non-working state at this time. The working modes are respectively the deep space observation mode and the earth observation mode.

Step 3: Deep space observation mode. Aim the center line of sight of the detector to the deep space, and maintain the thermal environment state in step 1 according to the set temperature requirements; each detector barrel is provided with 4 sets of copper-nickel heating wires, and whether the heating wires are heated through the SMUL4 series thermostat Control; the position of each group of heating wires is set with high-precision NTC thermistor to measure the temperature, and it is connected to the SMUL4 series temperature controller to complete the real-time temperature acquisition; each detector cylinder uses a SMUL4 series temperature controller, Finally, the voltage and current signals corresponding to the electric heating power PE ₁ of the detection main cavity 18 are output to the data centralization system of the platform on which the detector is mounted.

Step 4: The Earth Observation Mode. Aim the detector's center line of sight to the earth, and maintain the thermal environment state in step 1 according to the set temperature requirements; each detector barrel is provided with 4 sets of copper-nickel heating wires, and whether the heating wires are heated is controlled by the SMUL4 series thermostat ;The position of each group of heating wires is also set with a high-precision NTC thermistor to measure the temperature, and it is connected to the SMUL4 series temperature controller to complete the real-time temperature acquisition; each detector cylinder uses a SMUL4 series temperature controller, and finally The voltage and current signals corresponding to the electric heating power PE ₂ of the detection main cavity 18 are output to the data centralization system of the platform on which the detector is mounted.

Step 5: Calculate the radiation energy PE=PE ₁ -PE ₂ in different wavebands from the earth, wherein the calculation and storage of the radiation energy value are completed by the data centralized system of the platform on which the detector is mounted.

Specifically, the first channel measures the radiant energy in the 0.2μm-100μm band, that is, the earth’s outward radiation energy; the second channel measures the radiant energy in the 5μm-100μm band, and the fourth channel measures the 8μm-12μm band. radiant energy.

Step 6: Filter performance degradation verification mode. The stepper motor drives the filter wheel 8 or the light baffle 9, so that the detector channel, the filter wheel and the light baffle are matched in the following ways: 1HX, 2BY and 4FZ, or 1BX, 2DY and 4HZ, or 1CX, 2EY and 4AZ, Repeat data measurement and output storage for the deep space observation mode and the earth observation mode. If the radiant energy data measured by the Earth observation mode and the filter performance degradation verification method are the same, it means that the filter performance of the filter used in the working mode has not deteriorated; if not, it means that the filter used in the working mode has not deteriorated. The filter performance declines, and at this time, the data detected in the working mode needs to be corrected. When different channels need to be verified, other parameters are kept different, and the third channel is used to verify any one of the first, second and third channels. The operation method is similar to step six. Rotate the same filter as the filter on this verification channel to the fourth channel to measure the data. If the two sets of data are within the error range, it means that the verified channel can work normally; if it is not within the error range, It means that there is a problem with this channel, and the third channel can be used as a working channel to replace this channel later. The above content is only to illustrate the technical idea of the present invention, and cannot limit the protection scope of the present invention. Any modification made on the basis of the technical solution proposed in accordance with the technical idea of the present invention falls within the scope of the claims of the present invention. within the scope of protection.

Claims (10)

1. The device for measuring the energy radiated outwards by the earth based on the lunar-based platform is characterized by comprising an outer barrel (1), an inner barrel (2), a detector barrel (5), a filter wheel (8), a top cover (10), an outer field of view barrel (12) and a power device, wherein the inner barrel (2) is arranged in the outer barrel (1), the top cover (10) is arranged at the top of the outer barrel (1), M through holes for light to pass through are formed in the top cover (10), the outer field of view barrel (12) is arranged right above the through holes, the filter wheel (8) is arranged between the upper part of the inner barrel (2) and the top cover (10), and a group of working light filters are arranged on the filter wheel (8); a plurality of detector cylinders (5) are arranged in the inner cylinder (2); the power device is used for driving the filter wheel (8) to rotate;

the detector barrel (5) comprises a temperature control view field barrel (6) and a detector cavity (17) arranged below the temperature control view field barrel (6), a detection main cavity (18) is arranged at the upper part of the detector cavity (17), a detection auxiliary cavity (19) is arranged at the lower part of the detector cavity, the detection main cavity (18) and the detection auxiliary cavity (19) are completely the same, and the detection main cavity and the detection auxiliary cavity are arranged back to back; a first temperature control heating wire and a first temperature sensor are arranged in the detection main cavity (18); a second temperature control heating wire and a second temperature sensor are arranged in the detection auxiliary cavity (19).

2. The earth-based outward radiant energy measuring device of claim 1, characterized in that the upper end of the main detecting cavity (18) is provided with a precise field-of-view hole (21), and the precise field-of-view hole (21) is used for controlling the area of the main detecting cavity (18) for receiving the radiation.

3. The device for measuring the energy radiated outwards by the earth based on the lunar platform as claimed in claim 1, wherein a temperature control baffle (7) is arranged between the inner cylinder (2) and the filter wheel (8).

4. The device for measuring the energy radiated outwards by the earth based on the lunar platform is characterized in that an annular supporting frame (3) is installed at the bottom of the outer cylinder (1), an inner cylinder (2) is installed on the annular supporting frame (3), a supporting plate is arranged in the inner cylinder, and the detector cylinder (5) is hung on the supporting plate.

5. The device for measuring the energy radiated outwards by the earth based on a lunar platform as claimed in claim 1, wherein said filter wheel (8) is mounted with two sets of filters: the device comprises a working filter set and a verification filter set, wherein the working filter set comprises a filter with a high-efficiency passing waveband of 0.2-100 mu m, a filter with a high-efficiency passing waveband of 8-12 mu m and a filter with a high-efficiency passing waveband of 5-100 mu m, and the verification filter set at least comprises a group of filters which are the same as the working filter set; light baffle (9) is arranged above the filter wheel (8), and at least three light passing holes are formed in the light baffle (9).

6. The device for measuring the energy radiated outwards by the earth based on the lunar platform as claimed in claim 1, wherein the filter wheel (8) is installed with two layers of filters (14) at the same position, and the filters (14) installed at the same position are identical.

7. The earth-based outward radiant energy measuring device of claim 1, characterized in that the inner side of the outer cylinder (1), the inner side and the outer side of the inner cylinder (2) and the outer side of the detector cylinder (5) are coated with thermal control coating with emissivity less than 0.05.

8. The earth-based outward radiant energy measuring device of claim 1 characterized in that the inner wall and bottom of the probe cavity (17) is provided with heat sink (20).

9. A method for radiating energy outwards from the earth based on a lunar-based platform of a surveying device according to claim 1, comprising the steps of:

step 1: keeping the set working temperature of the detector cylinder (5) unchanged, and keeping the working temperature difference between the detection main cavity (18) and the detection auxiliary cavity (19) to be 0.5 ℃;

step 2: rotating the filter wheel (8) to enable the central lines of different detector cylinders (5) to be collinear with the central lines of the optical filters (14) in the working optical filter group in the filter wheel (8), and enabling other hole optical filters on the filter wheel (8) to be in a non-working state;

and step 3: entering a deep space observation mode: aligning the central sight of the detector to the deep space, and maintaining the thermal environment state in the step 1 according to the set temperature requirement; monitoring the electrical heating power PE of the main cavity (18) in each detector cylinder (5)₁；

And 4, step 4: entering an earth observation mode: aligning the central sight of the detector to the earth, and maintaining the thermal environment state in the step 1 according to the set temperature requirement; monitoring the electrical heating power PE of the main cavity (18) in each detector cylinder (5)₂；

And 5: calculating the external radiation energy PE of the earth, wherein PE is PE₁-PE₂(ii) a The earth outward radiation energy PE obtained by calculation of each detector cylinder (5) is the earth outward radiation energy of the filter (14) opposite to the detector cylinder (5) and passing through the wave band.

10. The earth-based outward radiant energy measuring method based on the lunar-based platform as claimed in claim 9, wherein the filter performance is verified after the device is operated for a set time by the following specific processes: the filter wheel (8) is driven to rotate, so that the optical filters of the verification optical filter group on the detector cylinder (5) and the filter wheel (8) are opposite, the steps from 3 to 5 are repeated, another group of energy PE radiated outwards by the earth is obtained through measurement, and if the obtained energy radiated outwards by the earth and the data measured by the working optical filter group are within an error range, the optical filter performance of the optical filter used in the working mode is not degraded; otherwise, it indicates that the filtering performance of the optical filter used in the working mode is degraded, and at this time, the data detected in the working mode needs to be corrected.

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