CN111879409A - Device and method for measuring earth outward radiation energy based on lunar-based platform - Google Patents
Device and method for measuring earth outward radiation energy based on lunar-based platform Download PDFInfo
- Publication number
- CN111879409A CN111879409A CN202010561766.2A CN202010561766A CN111879409A CN 111879409 A CN111879409 A CN 111879409A CN 202010561766 A CN202010561766 A CN 202010561766A CN 111879409 A CN111879409 A CN 111879409A
- Authority
- CN
- China
- Prior art keywords
- detector
- earth
- filter
- cylinder
- cavity
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 230000005855 radiation Effects 0.000 title claims abstract description 76
- 238000000034 method Methods 0.000 title claims abstract description 23
- 238000001514 detection method Methods 0.000 claims abstract description 60
- 230000003287 optical effect Effects 0.000 claims description 56
- 238000010438 heat treatment Methods 0.000 claims description 30
- 238000005259 measurement Methods 0.000 claims description 14
- 238000012795 verification Methods 0.000 claims description 10
- 238000001914 filtration Methods 0.000 claims description 7
- 230000008569 process Effects 0.000 claims description 7
- 238000012544 monitoring process Methods 0.000 claims description 4
- 239000000523 sample Substances 0.000 claims description 4
- 238000000576 coating method Methods 0.000 claims description 3
- 239000011248 coating agent Substances 0.000 claims description 2
- 239000000463 material Substances 0.000 abstract description 6
- 238000005265 energy consumption Methods 0.000 abstract description 3
- 230000008859 change Effects 0.000 description 15
- PEDCQBHIVMGVHV-UHFFFAOYSA-N Glycerine Chemical compound OCC(O)CO PEDCQBHIVMGVHV-UHFFFAOYSA-N 0.000 description 12
- 238000005485 electric heating Methods 0.000 description 8
- 230000005540 biological transmission Effects 0.000 description 5
- 230000015556 catabolic process Effects 0.000 description 4
- 238000006731 degradation reaction Methods 0.000 description 4
- 230000007774 longterm Effects 0.000 description 4
- 241000282414 Homo sapiens Species 0.000 description 3
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 3
- 229910052782 aluminium Inorganic materials 0.000 description 3
- 238000011160 research Methods 0.000 description 3
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 2
- 229910000570 Cupronickel Inorganic materials 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 2
- 229910052802 copper Inorganic materials 0.000 description 2
- 239000010949 copper Substances 0.000 description 2
- YOCUPQPZWBBYIX-UHFFFAOYSA-N copper nickel Chemical compound [Ni].[Cu] YOCUPQPZWBBYIX-UHFFFAOYSA-N 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000009413 insulation Methods 0.000 description 2
- 239000012774 insulation material Substances 0.000 description 2
- 230000003993 interaction Effects 0.000 description 2
- 238000012545 processing Methods 0.000 description 2
- 230000032683 aging Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000008094 contradictory effect Effects 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000010259 detection of temperature stimulus Effects 0.000 description 1
- 230000006866 deterioration Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000018109 developmental process Effects 0.000 description 1
- 238000005562 fading Methods 0.000 description 1
- 230000017525 heat dissipation Effects 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000003973 paint Substances 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
- 230000000007 visual effect Effects 0.000 description 1
- 238000010792 warming Methods 0.000 description 1
Images
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01J—MEASUREMENT OF INTENSITY, VELOCITY, SPECTRAL CONTENT, POLARISATION, PHASE OR PULSE CHARACTERISTICS OF INFRARED, VISIBLE OR ULTRAVIOLET LIGHT; COLORIMETRY; RADIATION PYROMETRY
- G01J5/00—Radiation pyrometry, e.g. infrared or optical thermometry
- G01J5/007—Radiation pyrometry, e.g. infrared or optical thermometry for earth observation
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01J—MEASUREMENT OF INTENSITY, VELOCITY, SPECTRAL CONTENT, POLARISATION, PHASE OR PULSE CHARACTERISTICS OF INFRARED, VISIBLE OR ULTRAVIOLET LIGHT; COLORIMETRY; RADIATION PYROMETRY
- G01J5/00—Radiation pyrometry, e.g. infrared or optical thermometry
- G01J5/02—Constructional details
- G01J5/0205—Mechanical elements; Supports for optical elements
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01J—MEASUREMENT OF INTENSITY, VELOCITY, SPECTRAL CONTENT, POLARISATION, PHASE OR PULSE CHARACTERISTICS OF INFRARED, VISIBLE OR ULTRAVIOLET LIGHT; COLORIMETRY; RADIATION PYROMETRY
- G01J5/00—Radiation pyrometry, e.g. infrared or optical thermometry
- G01J5/02—Constructional details
- G01J5/0225—Shape of the cavity itself or of elements contained in or suspended over the cavity
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01J—MEASUREMENT OF INTENSITY, VELOCITY, SPECTRAL CONTENT, POLARISATION, PHASE OR PULSE CHARACTERISTICS OF INFRARED, VISIBLE OR ULTRAVIOLET LIGHT; COLORIMETRY; RADIATION PYROMETRY
- G01J5/00—Radiation pyrometry, e.g. infrared or optical thermometry
- G01J5/02—Constructional details
- G01J5/06—Arrangements for eliminating effects of disturbing radiation; Arrangements for compensating changes in sensitivity
- G01J5/068—Arrangements for eliminating effects of disturbing radiation; Arrangements for compensating changes in sensitivity by controlling parameters other than temperature
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01J—MEASUREMENT OF INTENSITY, VELOCITY, SPECTRAL CONTENT, POLARISATION, PHASE OR PULSE CHARACTERISTICS OF INFRARED, VISIBLE OR ULTRAVIOLET LIGHT; COLORIMETRY; RADIATION PYROMETRY
- G01J5/00—Radiation pyrometry, e.g. infrared or optical thermometry
- G01J5/02—Constructional details
- G01J5/08—Optical arrangements
- G01J5/0803—Arrangements for time-dependent attenuation of radiation signals
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01J—MEASUREMENT OF INTENSITY, VELOCITY, SPECTRAL CONTENT, POLARISATION, PHASE OR PULSE CHARACTERISTICS OF INFRARED, VISIBLE OR ULTRAVIOLET LIGHT; COLORIMETRY; RADIATION PYROMETRY
- G01J5/00—Radiation pyrometry, e.g. infrared or optical thermometry
- G01J5/80—Calibration
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Spectroscopy & Molecular Physics (AREA)
- Life Sciences & Earth Sciences (AREA)
- Environmental & Geological Engineering (AREA)
- General Life Sciences & Earth Sciences (AREA)
- Geology (AREA)
- Radiation Pyrometers (AREA)
Abstract
The invention discloses an earth outward radiation energy measuring device and method based on a lunar base platform. The structural arrangement mode that the double-layer shell is combined with the cross supporting plate is adopted, and meanwhile, the wall surface is coated with the specific emissivity material, so that the heat conduction loss and the radiation heat loss of the detector cylinder can be effectively reduced, the temperature control precision of the detector cylinder is improved, and the energy consumption is reduced. Secondly, the detector cylinder body of four passageways cooperates eight hole filter wheels and three hole light baffle plates can realize the high accuracy detection to the different wave bands of the outside radiant energy of earth. The temperature control baffle is arranged between the detector barrel and the filter wheel, so that the influence of temperature fluctuation of the filter wheel and the light baffle on the detector barrel can be reduced, and meanwhile, the filter wheel and the light baffle are arranged in the outer barrel, so that the influence of the external lunar surface temperature environment on the working performance of the detector can be reduced.
Description
Technical Field
The invention belongs to the technical field of detection of earth outward radiant energy by a lunar-based detection platform, and particularly relates to an earth outward radiant energy measuring device and method based on a lunar-based platform.
Background
Since the industrialization, the global climate shows the warming trend, and causes the worries of various social circles about the change of human living and developing environment. Fundamentally, the change of the earth climate depends on the change of the radiation energy balance in the earth-gas system, and the current observation and research on the change of the earth-gas radiation energy balance mainly depends on the data of the earth-surface meteorological observation station and the satellite-borne earth-surface observation sensor. For a ground observation station, the detection data is not only influenced by the atmosphere and the surrounding environment of the station, but also insufficient in quantity and uneven in distribution. Since the end of the seventies of the last century, several countries of the world have launched in succession tens of artificial earth satellites dedicated to the measurement of solar and earth radiation. However, there are still many disadvantages in artificial earth satellite measurement, and the measurement results of different satellites are sometimes even contradictory, mainly because the artificial earth satellite has a limited view angle to the earth and is not a long-term stable observation platform. Short operation life, limited instantaneous field space coverage, orbit drift, sensor aging degradation and other factors are not beneficial to long-term continuous observation of the global scale of the earth. Therefore, it is necessary to observe the energy balance of the earth climate from a completely new angle and way to explore the global climate change mechanism. Compared with the natural satellite with the earth being perpetual, the earth-based energy balance system can provide a new earth observation platform to make up for the defects of artificial satellite observation, and provides more accurate and comprehensive data support for the research of the earth climate system energy balance process which is carried out more deeply by human beings.
At the top of the atmosphere, radiation is the only way of energy exchange. The energy changes of the climatic system are the result of a balance between the absorbed solar short-wave radiation and the emitted long-wave radiation into space. The earth radiation balance detection mainly measures three parts of radiation: the radiation (reception) of the sun to the climate system, the long-wave radiation (branch) of the climate system to the outer space and the reflection (branch) of the climate system to the solar radiation. The first part of the radiation (receiving) is stable, the annual change rate is low, and the solar radiation monitor can monitor the solar total radiation change for a long time. The earth radiation detector is generally observed by two channels of 0.2-5 mu m short wave and 0.2-100 mu m full wave band. The short wave channel is mainly used for observing solar radiation reflected by the climate system, the full wave channel is used for observing the sum of the reflected solar radiation and emitted long-wave infrared radiation, and the reflected radiation is deducted to obtain long-wave radiation (the wavelength range is 5-100 mu m) emitted by the climate system. At the surface, the surface radiation balance determines the amount of radiation absorbed by the land surface, and the distribution of radiation causes the natural phenomena of the surface to vary in time and space. The net surface radiation dose is typically the sum of the short and long wavelength radiant energies. The earth surface albedo is the most important parameter in the short wave radiation balance estimation, the earth surface temperature and the emissivity are very important earth surface variables in the long wave radiation balance estimation, the common wave band for detecting the earth surface temperature by the current satellite-borne platform is a thermal infrared wave band (the wavelength range is 8-12 mu m), and the wave band is mainly set by considering two factors that a detected target has the strongest signal characteristic in the wave band and detected remote sensing information can reach a sensor through the atmosphere to the maximum extent.
The moon is a natural celestial body closest to the earth and is the only extraterrestrial celestial body which can be reached and has been reached by human beings at present, the lunar observation device has the advantages of long-term consistency, integrity and stability of earth observation, meanwhile, the distance between the moon and the earth is more than thirty thousand kilometers, a small telescope can obtain the observation of the whole disk surface of the earth, and a wide space of the moon can be provided with a plurality of sensors, so that the cooperative observation of the earth by a plurality of detectors is facilitated. The characteristics can provide support for global-scale multi-circle-layer integrated research, and scientific explanation of phenomena of global multi-circle-layer mutual coupling including global sea-air interaction, land-air interaction and boundary layer atmospheric process, sea-land related change and coastal zone process, global energy balance and the like can be realized from the viewpoint of earth system science. With the rise of moon exploration in recent years, the construction and planning of moon bases are also promoted by the world's astronauts, and a solid foundation is laid for exploration of the moon and development of observation of the earth and space based on the moon. When the detector on the lunar-based platform observes the energy radiated outwards from the earth, the lunar surface has no influence of complexity of each circle layer such as an atmospheric space. Meanwhile, due to the tidal locking function, the moon near-earth hemisphere can always face the earth, so that the characteristics of integrity, long-term property, consistency and continuity of earth observation of the moon-based platform can be fully exerted by placing outward radiant energy to the earth on the near-earth measurement of the moon surface. In order to fully exert the advantages of the lunar-based platform in detecting the earth outward radiation energy, the invention provides the device and the method for measuring the earth outward radiation energy based on the lunar-based platform based on the special environment temperature of the lunar surface.
Disclosure of Invention
The invention provides an earth outward radiation energy measuring device and method based on a moon-based platform, which can be used for detecting earth outward radiation energy of different wave bands based on the moon-based platform, and obtaining large-scale and dynamic energy balance continuous observation data for researching the whole system of the earth so as to meet the requirement of global scale observation capability of global change scientific problems.
In order to achieve the purpose, the invention relates to an earth outward radiation energy measuring device based on a lunar-based platform, which comprises an outer cylinder, an inner cylinder, a detector cylinder, a filter wheel, a top cover, an outward field cylinder and a power device, wherein the inner cylinder is arranged in the outer cylinder; a plurality of detector cylinders are arranged in the inner cylinder; the power device is used for driving the filter wheel to rotate; the detector barrel comprises a temperature control view field barrel and a detector cavity arranged below the temperature control view field barrel, the upper part of the detector cavity is provided with a detection main cavity, the lower part of the detector cavity is provided with a detection auxiliary cavity, the detection main cavity and the detection auxiliary cavity 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; and a second temperature control heating wire and a second temperature sensor are arranged in the detection auxiliary cavity.
Furthermore, the upper end of the detection main cavity body is provided with a precise view field hole, and the precise view field hole is used for controlling the area of the detection main cavity body for receiving radiation.
Furthermore, a temperature control baffle is arranged between the inner cylinder and the filter wheel.
Furthermore, an annular support frame is installed at the bottom of the outer barrel, the inner barrel is installed on the annular support frame, a support plate is arranged in the inner barrel, and the detector barrel is hung on the support plate.
Further, two groups of optical filters are installed on the optical filter wheel: 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; a light baffle is arranged above the light filtering wheel, and at least three light passing holes are formed in the light baffle.
Furthermore, two layers of optical filters are arranged at the same position of the filter wheel, and the optical filters arranged at the same position are completely the same.
Furthermore, the inner side of the outer cylinder, the inner side and the outer side of the inner cylinder and the outer side of the detector cylinder are coated with thermal control coatings with emissivity less than 0.05.
Further, heat sinks are arranged on the inner wall and the bottom of the cavity of the detector.
A method for radiating energy outwards from the earth based on a lunar-based platform of the surveying device of claim, comprising the steps of:
step 1: keeping the set working temperature of the detector barrel unchanged, and keeping the working temperature difference between the detection main cavity and the detection auxiliary cavity to be 0.5 ℃;
step 2: rotating the filter wheel to make the central lines of the different detector cylinders respectively collinear with the central lines of the optical filters in the working optical filter group in the filter wheel, and at the moment, the other hole optical filters on the filter wheel are 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 detection main cavity in each detector cylinderElectric heating power PE1；
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 electrical heating power PE of detecting main cavity in each detector cylinder2；
And 5: calculating the external radiation energy PE of the earth, wherein PE is PE1-PE2(ii) a The earth outward radiation energy PE calculated by each detector cylinder is the earth outward radiation energy of the filter opposite to the detector cylinder in the passing wave band.
Furthermore, after the device runs for a set time, the performance of the optical filter is verified, and the specific process is as follows: driving the filter wheel to rotate, enabling the detector barrel to be opposite to the optical filter of the verification optical filter group on the filter wheel, repeating the step 3 to the step 5, measuring to obtain another group of energy PE radiated outwards by the earth, and if the obtained energy radiated outwards by the earth and the data measured by using the working optical filter group are within an error range, indicating that the optical filter used in the working mode has no decline in the optical filtering performance; 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.
Compared with the prior art, the invention has at least the following beneficial technical effects:
the invention adopts a plurality of detector cylinders which are designed completely the same in the structure, processing and assembling processes to form a multi-channel detection structure, and can realize high-precision detection of different wave bands of the earth outward radiation energy by combining the filter wheel and the light ray baffle. Some of the channels perform routine probing, and the remaining channels are used to periodically verify the performance of the filter. During the working mode, the first detection channel is corresponding to an ultraviolet to far infrared channel (the detection wave band ranges from 0.2 mu m to 100 mu m) and is used for measuring the total radiation energy which leaves the earth system and reaches the outer space; the second channel is a far infrared wave band channel (the wavelength range is 5-100 mu m) and is used for measuring the radiation energy emitted to the outer space by the earth climate system; the fourth channel is an earth infrared radiation channel (the wavelength range is 8-12 mu m) and is used for measuring the long-wave infrared energy emitted by the earth. The radiant energy in multiple bands can be measured simultaneously.
Furthermore, the invention adopts a double-layer shell structure consisting of an inner cylinder and an outer cylinder, the detector cylinder is fixed on a support plate through a connecting piece, and the support plate is fixedly connected with the inner cylinder through the connecting piece.
The area of the contact part of the detector cylinder body and the support plate is small, heat conduction loss of the detector cylinder body can be effectively reduced by arranging heat insulation materials, and meanwhile, heat loss along the radius direction can be effectively reduced by coating specific emissivity materials on the inner side of the outer cylinder, the inner side of the inner cylinder, the outer side of the inner cylinder and the outer side of the detector cylinder body, so that the temperature control precision of the detector cylinder body is improved, and energy consumption is reduced.
Furthermore, the temperature control baffle is arranged between the detector cylinder and the filter wheel, so that the influence of temperature fluctuation of the filter wheel and the light baffle on the detector cylinder is reduced, meanwhile, the filter wheel, the light baffle and the transmission gear are arranged in the outer cylinder, so that a relatively closed and stable environment is kept inside the outer cylinder, and the influence of the external lunar surface temperature environment on the working performance of the detector is reduced.
Furthermore, wires of all electric equipment in the whole system are led out through lead-out holes at the edge of the top cover; except for the connecting piece opening, other openings are not arranged in the whole outer cylinder and the inner cylinder, so that the closure of the whole system is ensured, and the heat dissipation loss is reduced.
Furthermore, the inner wall and the bottom of the detector cavity are provided with heat sinks, the temperature of the heat sinks is controlled to be constant through the temperature controller and the heater, constant temperature difference between the main cavity and the heat sinks is guaranteed to be detected, and therefore effective and accurate detection of weak radiant energy is achieved.
The measuring method provided by the invention can verify the stability of the thermal environment of the detector and effectively eliminate the influence of deep space background radiation during earth observation by alternately performing the deep space observation and the earth observation.
Furthermore, after working for a period of time, the performance change of the optical filter is verified, and if the verification is unqualified, the measured data is corrected, so that the measurement accuracy is improved.
Drawings
FIG. 1 is a diagram of a detector system architecture;
FIG. 2 is a schematic view of a detector four-channel cartridge;
FIG. 3 is a schematic view of a filter wheel;
FIG. 4 is a schematic view of a light baffle;
FIG. 5 is a schematic diagram of the relationship between the detector channel, the filter wheel, and the light baffle.
In the drawings: 1-outer cylinder, 2-inner cylinder, 3-annular support frame, 4-cross support plate, 5-detector cylinder, 6-temperature control view field cylinder, 7-temperature control baffle, 8-filter wheel, 9-light baffle, 10-top cover, 11-stepping motor, 12-outer view field cylinder, 13-connecting piece, 14-optical filter, 15-optical filter support, 16-transmission gear, 17-detector cavity, 18-detection main cavity, 19-detection auxiliary cavity, 20-heat sink, and 21-precision view field hole.
Detailed Description
In order to make the objects and technical solutions of the present invention clearer and easier to understand. The present invention will be described in further detail with reference to the following drawings and examples, wherein the specific examples are provided for illustrative purposes only and are not intended to limit the present invention.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on those shown in the drawings, and are used only for convenience in describing the present invention and for simplicity in description, and do not indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and thus, are not to be construed as limiting the present invention. Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless otherwise specified. In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
Referring to fig. 1, the device for measuring the energy radiated outwards from the earth based on a lunar base platform comprises 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, a filter wheel 8, a light baffle 9, a top cover 10, a stepping motor 11, an outer field of view cylinder 12, a connecting piece 13, a transmission gear 16, a heat sink 20 and a precise field of view hole 21. The components jointly form a detector cavity system, a temperature control system, a supporting system and a filter system.
1) The main body of the detector cavity system is four detector cylinders 5 and four outer field-of-view cylinders 12. The detector barrel 5 consists of a temperature control view field barrel 6 and a detector cavity 17 arranged below the temperature control view field barrel 6. The temperature-controlled view field barrel 6 is used for keeping the detected environment temperature at a set temperature value in an electric heating mode. The detector cavity 17 is used for receiving the radiation energy after sequentially passing through the outer view field barrel 12, the optical filter 14, the temperature control baffle 7 and the precise view field hole 21, so that the radiation energy can be measured in an electric replacement mode.
The upper end of the detector cavity 17 is provided with a precise view field hole 21, the inner wall and the bottom of the detector cavity 17 are provided with heat sinks 20, the upper part of the detector cavity 17 is provided with a detection main cavity 18, the lower part of the detector cavity 17 is provided with a detection auxiliary cavity 19, the detection main cavity 18 and the detection auxiliary cavity 19 are completely the same, and the detection main cavity 18 and the detection auxiliary cavity 19 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; a third temperature control heating wire and a third temperature sensor are arranged on the heat sink 20 of the detector cavity 17, and a fourth temperature control heating wire and a fourth temperature sensor are arranged on the outer wall of the temperature control view field cylinder 6. The first to fourth temperature control heating wires are used for heating the positions where the temperature control heating wires are located, and the temperature control heating wires and the temperature sensors are arranged on the outer wall of the temperature control view field barrel 6 and the heat sink 20 and used for ensuring the required working special thermal environment. The first to fourth temperature sensors are used for measuring the temperature of the position where the first to fourth temperature sensors are located so as to achieve measurement of radiation. The heat sink 20 is composed of a copper heat sink and an aluminum heat sink, and the third temperature control heating wires and the third temperature sensors are arranged between the copper heat sink and the aluminum heat sink and outside the aluminum heat sink. The precise view field hole 21 is arranged at the upper end of the detection main cavity body 18 to control the radiation energy entering the detection main cavity body and limit the input radiation.
2) The temperature control system mainly comprises a heat insulation gasket, a temperature control baffle 7, a low emissivity material, first to fourth temperature control heating wires and first to fourth temperature sensors.
The heat insulation gasket is arranged at the fastening position where the detector cylinder 5 is connected with the cross support plate 4 through the connecting piece 13 and the bolt, and the inner side of the outer cylinder 1, the inner side and the outer side of the inner cylinder 2, the upper side and the lower side of the temperature control baffle 7 and the outer side of the detector cylinder 5 are coated with specific low-emissivity materials (for example, black paint with spraying emissivity less than 0.05).
The temperature control baffle 7 is arranged between the detector cylinder 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 cylinder 5.
3) The supporting system mainly comprises an outer cylinder 1, an inner cylinder 2, an annular supporting frame 3 and a cross supporting plate 4. Annular support frame 3 is installed to 1 bottom of urceolus, is provided with inner tube 2 on the annular support frame 3, and 2 upper ends of inner tube are connected through bolt and 13 one end of a plurality of connecting pieces, and the 13 other ends of a plurality of connecting pieces pass through bolt and 1 fixed connection of urceolus. The inner cylinder 2 is connected with the outer cylinder 1 in a center alignment way; the cross support plate 4 is fixed in the inner cylinder 2 through a connecting piece 13 and a bolt, and the four detector cylinders 5 are fixedly connected with the cross support plate 4 through the connecting piece 13 and the bolt; the bottoms of the four detector cylinders 5 are not contacted with the bottom of the inner cylinder 2. The temperature control baffle 7 is fixed at the upper end of the inner barrel 2 through a bolt, and a through hole for passing through radiant energy is formed in the temperature control baffle 7; a top cover 10 is fixed at the upper end of the outer cylinder 1, and an outer view field cylinder 12 is connected and fixed with the top cover 10 through a connecting piece 13; the top cover 10 is connected and fixed with the outer cylinder 1 through a connecting piece 13 and a fastening piece. The top cover 10 is provided with a motor shaft hole, an electric wire leading-out hole, a bolt connecting hole and a radiation through hole.
The inner cylinder 2 and the outer cylinder 1 jointly form a double-layer shell structure, and the loss of heat along the radius direction can be effectively reduced after the wall surface is coated with a specific emissivity material.
The contact area between the detector cylinder 5 and the cross support plate 4 is small, heat conduction loss and radiation heat loss can be effectively reduced after heat insulation materials are arranged at the contact position and specific emissivity materials are coated on the wall surface, the temperature control precision of the detector cylinder 5 is improved, and energy consumption is reduced.
4) The light filtering system mainly comprises a stepping motor 11, a light filtering wheel 8, a light baffle plate 9 and a transmission gear 16. Filter wheel 8 sets up directly over control by temperature change baffle 7, is provided with light baffle 9 directly over filter wheel 8, and filter wheel 8 and light baffle 9 all are located top cap 10 below. The light ray baffle 9 and the filter wheel 8 form a coaxial system which is driven by a stepping motor 11 group and a transmission gear 16; the shell of the stepping motor 11 is fixedly connected with the top cover 10 through a connecting piece 13. The set of stepper motors 11 includes two motors, one for driving the light shutter 9 and the other for driving the filter wheel 8.
Referring to FIG. 3, wherein filter wheel 8 is comprised of filters 14 and filter holders 15; the optical filter support 15 is provided with 8 upper and lower double-layer mounting holes which are uniformly arranged along the circumferential direction of the optical filter support 15, the optical filters 14 are mounted in the mounting holes, and the double-layer arrangement can reduce the influence of the thermal effect of the optical filters on the detectors, and the optical filters in different wave band ranges are mounted at different holes. The method specifically comprises the following steps: the filter A, the filter B, the filter C, the filter D, the filter E, the filter F, the filter G and the filter H are adjacent in sequence. The high-efficiency passing waveband of the optical filter A is 0.2-100 mu m, the high-efficiency passing waveband of the optical filter B is 8-12 mu m, the high-efficiency passing waveband of the optical filter C is 5-100 mu m, the high-efficiency passing waveband of the optical filter D is 8-12 mu m, the high-efficiency passing waveband of the optical filter E is 5-100 mu m, the high-efficiency passing waveband of the optical filter F is 0.2-100 mu m, the high-efficiency passing waveband of the optical filter G is 8-12 mu m, and the high-efficiency passing waveband of the optical filter H is 5-100 mu m.
The channel where the optical filter with the high-efficiency passing wave band of 0.2-100 microns is located is an ultraviolet to far infrared channel and is used for measuring the total radiation energy leaving the earth system and reaching the outer space; the channel where the optical filter with the high-efficiency passing wave band of 5-100 mu m is located is a far infrared channel and is used for measuring the radiation energy emitted to the outer space of the earth climate system; the channel where the high-efficiency passing wave band is the 8-12 μm optical filter is an earth infrared radiation channel and is used for measuring the long-wave infrared energy emitted by the earth.
Referring to fig. 4, the light baffle 9 is provided with three light passing holes, a light passing hole X, a light passing hole Y and a light passing hole Z, a line segment obtained by connecting the centers of the light passing hole Y and the light passing hole Z is set to be L, the light passing 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.
Referring to fig. 1 and 2, a 4-channel detection structure is formed by four identical detector cylinders 5, and the four detector cylinders 5 are uniformly distributed on the same circumference. The high-precision detection of different wave bands of the earth outward radiation energy is realized by matching with different combinations of the 8-hole filter wheel 8 and the 3-hole light baffle plate 9. The detector is provided with four detector cylinders 5, each cylinder is a channel, the first, second and fourth cylinders 5 perform daily detection, the third channel is used for periodically calibrating and verifying the performance of the optical filter 14 and the first, second and fourth cylinders, and the 4 detector cylinders 5 are completely the same in the structure, processing and assembling processes so as to reduce the introduction of errors.
The detector cylinder 5, the optical filter 8, the light baffle plate 9 and the outer view field cylinder 12 must keep coaxial, and the coaxial detector cylinder 5, the optical filter 8, the light baffle plate 9 and the outer view field cylinder 12 form a channel; meanwhile, the diameters of the optical filter 14 and the light baffle plate 9 are 5mm larger than the diameter of the outer view field cylinder 12, so that the high efficiency and the integrity of the passing of the radiation energy are ensured.
The filter wheel 8, the light baffle plate 9 and the transmission gear 16 are all arranged in the outer barrel 1, the filter wheel 8 is positioned right above the inner barrel 2, the light baffle plate 9 is positioned right above the filter wheel 8, the interior of the detector is kept to be a relatively closed and stable environment, and the influence of the external lunar surface temperature environment on the working performance of the detector is reduced.
The wires of all the electric equipment of the whole energy measuring device are led out from the wire leading-out holes at the edge of the top cover 10; except for the holes at the positions where the bolts need to be installed, other holes are not arranged in the whole outer cylinder 1 and the inner cylinder 2, so that the closure of the whole system is ensured, and the heat loss is reduced.
The measurement principle and the use method of the earth outward radiation measurement device based on the lunar base platform comprise the following steps:
the working principle is as follows:
the working principle of the earth outward radiation energy measurement based on the lunar-based platform is as follows: the method is realized by equivalently replacing the method of receiving the energy radiated outside the earth by using electric heating power, and can be represented by the following formula:
wherein, PEIndicating the electrical heating power to probe the main chamber 18; pRRepresents the radiation power incident to the main detection cavity 18; kCIs the sum of heat conduction resistances and resistances between the main detection cavity 18 and the heat sink 20 and the auxiliary detector cavity 19; delta TCRepresents the sum of the heat exchange temperature differences between the main detection cavity 18 and the heat sink 20 and the auxiliary detector cavity 19; cCIndicating the heat capacity of the probe main chamber 18; t isCIndicating the detection of temperature within the main chamber 18; sigma PrRepresents the sum of the radiation heat exchange between the main detection cavity 18 and other parts in the detector cylinder 5, sigma QiWhich is the sum of the heat transferred by the probe cavity through the various leads.
Setting the working temperature of the detector cylinder 5 to be 30 ℃, and detecting the main cavity 18 and the detectorThe working temperature difference maintained between the measurement auxiliary cavities 19 is 0.5 ℃. When incident radiation power PRWhen the temperature is equal to 0, it means that the system completely maintains the working temperature difference Δ T between the main detection cavity 18 and the auxiliary detection cavity 19 under the condition of the electric heating power to be equal to 0.5 ℃. When incident radiation power PRWhen the temperature is not equal to 0, the measurement device maintains the working temperature difference Δ T between the main detection cavity and the auxiliary detection cavity to be 0.5 ℃ under the conditions of the electric heating power and the incident radiation power, so that the incident radiation power is equal to the change of the electric heating power, and the incident radiation energy can be calculated through the power change of the electric heater.
When the detector works stably, the items on the right side in the formula 1 are constant items and do not change any more, and at the moment, the electric heating power P of the main cavity 18 is detectedEAnd the sum of the incident radiation power PRIs constant, i.e. the electrical heating power P of the main chamber can be detected by measurementECalculating a target radiant heating power PRAs shown in formula 2:
after the detector is assembled on the ground, the right value of the equal sign in the equation (1) in stable working can be obtained by calibration according to the thermal environment required by setting.
Due to the deterioration of the lunar surface space environment, the performance of the optical filter may be degraded and lowered, so 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 to enter the optical filter performance detection mode, verifies the performance of the optical filter, and recalibrates and stores thermal environment data. If the measured data of the front detector and the rear detector are within the error range, the performance of the optical filter in work is not degraded; otherwise, if the fading occurs, the detection data needs to be corrected. The detector channels, filters and light passing holes are fitted in a sequential bottom-up manner, as shown in fig. 5, for example a combination of 1 AX: wherein 1 represents a first channel, a represents a filter a, and X represents a via hole X.
The using method comprises the following steps:
the method comprises the following steps: the working temperature of the detector barrel is set to be 30 ℃ through the temperature control heating wire, and the working temperature difference between the detection main cavity 18 and the detection auxiliary cavity 19 through the temperature control heating wire and the main cavity heating wire is set to be 0.5 ℃.
Step two: step motor 11 drives filter wheel 8 and visual field baffle 9, makes the center line of the first passageway, second passageway and fourth passageway of detector respectively with filter A, filter C, the center of filter G and light through hole X, light through hole Y, the collineation of light through hole Z center line in filter wheel 8, the cooperation mode of detector passageway, filter and light through hole this moment is: the first channel, the filter A and the light passing hole X are coaxial, the second channel, the filter C and the light passing hole Y are coaxial, and the fourth channel, the filter G and the light passing hole Z are coaxial; at this time, the detector cavity is in a working mode, and at this time, the other hole filters on the filter wheel 8 are in a non-working state. The working modes are a deep space observation mode and an earth observation mode respectively.
Step three: deep space observation mode. Aligning the central sight of the detector to the deep space, and maintaining the thermal environment state in the first step according to the set temperature requirement; wherein each detector cylinder is provided with 4 groups of copper-nickel heating wires, and whether the heating wires are heated or not is controlled by an SMUL4 series temperature controller; the position of each group of heating wires is simultaneously provided with a high-precision NTC thermistor for measuring the temperature, and the NTC thermistor is connected to an SMUL4 series temperature controller to finish the real-time temperature acquisition; each detector cylinder uses an SMUL4 series temperature controller, and finally the electric heating power PE of the main cavity 18 is detected1The corresponding voltage and current signals are output to a data concentration system of the platform on which the detector is mounted.
Step four: and observing the earth. Aligning the central sight of the detector to the earth, and maintaining the thermal environment state in the first step according to the set temperature requirement; wherein each detector cylinder is provided with 4 groups of copper-nickel heating wires, and whether the heating wires are heated or not is controlled by an SMUL4 series temperature controller; the position of each group of heating wires is simultaneously provided with a high-precision NTC thermistor for measuring the temperature, and the NTC thermistor is connected to an SMUL4 series temperature controller to finish the real-time temperature acquisition; each probeThe detector cylinder uses an SMUL4 series temperature controller, and finally detects the electric heating power PE of the main cavity 182The corresponding voltage and current signals are output to a data concentration system of the platform on which the detector is mounted.
Step five: calculating the radiation energy PE (provider edge) of different outwards wave bands of the earth1-PE2Wherein the calculation and storage of the radiant energy value is performed by a data concentration system of the platform carried by the detector.
Specifically, the first channel measures the radiation energy in a wave band of 0.2-100 μm, namely the radiation energy outwards from the earth; the second channel measures radiation energy in the 5 μm-100 μm band and the fourth channel measures radiation energy in the 8 μm-12 μm band.
Step six: and (3) a filter performance degradation verification mode. Step motor drive filter wheel 8 or light baffle 9 for detector passageway, filter wheel, light baffle cooperation mode are: and the data measurement and output storage are repeatedly carried out on the deep space observation mode and the earth observation mode BY 1HX, 2BY and 4FZ, or 1BX, 2DY and 4HZ, or 1CX, 2EY and 4 AZ. If the radiation energy data measured in the earth observation mode and the optical filter performance degradation verification mode are the same, it is indicated that the optical filter used in the working mode has no degradation in optical filter performance; if the difference is not the same, 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. And when different channels need to be verified, keeping other parameters different, and verifying any one of the first channel, the second channel and the third channel by using the third channel in a similar operation mode as the sixth step. Rotating the optical filter which is the same as the optical filter on the verification channel to a fourth channel, and measuring data, wherein if the two groups of data are within an error range, the verified channel can normally work; if the error is not in the error range, the channel is indicated to have a problem, and a third channel can be used as a working channel to replace the channel in the later period. The above-mentioned contents are only for illustrating the technical idea of the present invention, and the protection scope of the present invention is not limited thereby, and any modification made on the basis of the technical idea of the present invention falls within the protection scope of the claims of the present invention.
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.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010561766.2A CN111879409B (en) | 2020-06-18 | 2020-06-18 | Device and method for measuring earth outward radiation energy based on lunar-based platform |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010561766.2A CN111879409B (en) | 2020-06-18 | 2020-06-18 | Device and method for measuring earth outward radiation energy based on lunar-based platform |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111879409A true CN111879409A (en) | 2020-11-03 |
| CN111879409B CN111879409B (en) | 2021-12-28 |
Family
ID=73157661
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010561766.2A Active CN111879409B (en) | 2020-06-18 | 2020-06-18 | Device and method for measuring earth outward radiation energy based on lunar-based platform |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111879409B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113689752A (en) * | 2021-07-06 | 2021-11-23 | 哈尔滨工业大学 | Moon multi-factor comprehensive environment simulation device |
| CN113763844A (en) * | 2021-08-31 | 2021-12-07 | 上海卫星工程研究所 | Red flag mark for Mars detection and mounting method |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4910409A (en) * | 1988-11-07 | 1990-03-20 | James W. Hoffman | Earth radiation array sensing system |
| CN105092046A (en) * | 2015-05-15 | 2015-11-25 | 中国计量科学研究院 | Self-calibrated surface infrared radiation temperature measuring system |
| CN106248203A (en) * | 2016-08-16 | 2016-12-21 | 中国科学院长春光学精密机械与物理研究所 | Absolute radiometer and the internal heat structure of radiometer for solar irradiance calibration |
| CN208366465U (en) * | 2018-08-01 | 2019-01-11 | 合肥中科九衡科技有限公司 | Multi-channel filter radiator for the detection system that filters |
| CN111272276A (en) * | 2020-02-17 | 2020-06-12 | 北京理工大学 | Lunar radiation calibration system and method by earth stationary orbit optical remote sensor |
-
2020
- 2020-06-18 CN CN202010561766.2A patent/CN111879409B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4910409A (en) * | 1988-11-07 | 1990-03-20 | James W. Hoffman | Earth radiation array sensing system |
| CN105092046A (en) * | 2015-05-15 | 2015-11-25 | 中国计量科学研究院 | Self-calibrated surface infrared radiation temperature measuring system |
| CN106248203A (en) * | 2016-08-16 | 2016-12-21 | 中国科学院长春光学精密机械与物理研究所 | Absolute radiometer and the internal heat structure of radiometer for solar irradiance calibration |
| CN208366465U (en) * | 2018-08-01 | 2019-01-11 | 合肥中科九衡科技有限公司 | Multi-channel filter radiator for the detection system that filters |
| CN111272276A (en) * | 2020-02-17 | 2020-06-12 | 北京理工大学 | Lunar radiation calibration system and method by earth stationary orbit optical remote sensor |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113689752A (en) * | 2021-07-06 | 2021-11-23 | 哈尔滨工业大学 | Moon multi-factor comprehensive environment simulation device |
| CN113689752B (en) * | 2021-07-06 | 2024-01-19 | 哈尔滨工业大学 | Moon multifactor comprehensive environment simulation device |
| CN113763844A (en) * | 2021-08-31 | 2021-12-07 | 上海卫星工程研究所 | Red flag mark for Mars detection and mounting method |
Also Published As
| Publication number | Publication date |
|---|---|
| CN111879409B (en) | 2021-12-28 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN111879409B (en) | Device and method for measuring earth outward radiation energy based on lunar-based platform | |
| Bernard et al. | PRONAOS observations of MCLD 123.5+ 24.9: cold dust in the Polaris cirrus cloud | |
| Glaccum et al. | The polar ozone and aerosol measurement instrument | |
| CN108120613B (en) | Carrier rocket upper-stage transient thermal balance test device and method | |
| Lee III et al. | The Clouds and the Earth's Radiant Energy System (CERES) sensors and preflight calibration plans | |
| CN112985607B (en) | Method for correcting heat radiation directivity of geostationary satellite earth surface uplink long-wave radiation product | |
| CN105157827A (en) | Integrating sphere transmission radiometer for ontrack spectrum radiation absolute calibration for remote sensor | |
| Fruck et al. | Instrumentation for comparing night sky quality and atmospheric conditions of CTA site candidates | |
| Vane et al. | Spectral and radiometric calibration of the airborne visible/infrared imaging spectrometer | |
| CN106768314A (en) | A kind of apparatus and method for determining positive the south sun direct projection scattering irradiation in real time | |
| EP3839452B1 (en) | System for simultaneously calibrating two or more solar radiation measuring pyranometers | |
| CN106872030A (en) | Can be used for the visible short infrared excess spectral irradiance instrument of long-term automatic Observation | |
| Halyo et al. | Modeling and characterization of the Earth Radiation Budget Experiment (ERBE) nonscanner and scanner sensors | |
| Driesse et al. | Investigation of pyranometer and photodiode calibrations under different conditions | |
| CN205246215U (en) | Harmless survey device of light high spectrum earth's surface emissivity | |
| Folkman et al. | Enhancements to the radiometric calibration facility for the Clouds and the Earth's Radiant Energy System instruments | |
| CN211347107U (en) | Device for measuring solar short wave radiation energy | |
| CN107483013B (en) | Double-sided solar irradiation simulation test system and test method | |
| CN207573311U (en) | Double-sided solar irradiation simulation test system | |
| Liu | Multi-channel Photometric Survey Telescope—Mephisto | |
| Kasten | Field instruments for solar radiation measurements | |
| Zerlaut | The calibration of pyrheliometers and pyranometers for testing photovoltaic devices | |
| Ganguly et al. | Diurnal and seasonal variation of columnar ozone at Rajkot | |
| Lian et al. | Development and calibration of an automated precision ground-solar-sky radiometer | |
| Scheiman et al. | Measurement and characterization of concentrator solar cells |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |