CN110658147B - Satellite-borne terahertz atmosphere limb detector - Google Patents
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Abstract
The invention discloses a satellite-borne terahertz atmosphere edge detector, which comprises: the device comprises an antenna feed system, a scanning driving mechanism, a calibration body, a receiver, a rear-end spectrometer and a numerical control unit; the antenna feeder system is used for receiving the atmospheric edge radiation signal and the radiation signal of the calibration body and sending the signals to the receiver; the antenna feed system comprises an offset parabolic reflector antenna and four independent frequency feed sources; the scanning driving mechanism is used for driving the antenna feed system to realize one-dimensional reciprocating swing and complete the in-line scanning of the atmosphere parallel to the satellite travelling direction; the receiver comprises four detection channels, and each detection channel performs down-conversion, amplification and filtering on a radiation signal of one feed source; the back end spectrometer is used for carrying out spectrum analysis on signals output by each detection channel of the receiver so as to subsequently invert various atmospheric component contents and vertical distribution conditions; and the numerical control unit is used for controlling the working state of the whole detector.
Description
Technical Field
The invention relates to an atmosphere edge detector in the technical field of microwave remote sensing, in particular to a satellite-borne terahertz atmosphere edge detector.
Background
The terahertz atmosphere limb detection technology can be used for monitoring ozone, detecting atmospheric ozone layer, greenhouse effect tracer gas, global distribution and aerosol concentration distribution of trace gas having important influence in troposphere and stratospheric ozone chemistry, and the like. The composition change of various atmospheric trace gases and the influence on radiation balance and atmospheric state parameters can be researched, which is helpful for scientists to know the long-distance transportation and complexity of pollutants, better know how ozone holes react to the future stratospheric cooling, provide new knowledge ways for scientists to the physical and chemical processes influencing the stratospheric ozone layer and the climate, and help scientists monitor the generation of global pollution and know how climate change influences the recovery of the stratospheric ozone layer. Meanwhile, the research on the terahertz detector fills the gap of China in the aspect of global atmospheric composition observation, improves the overall development level of the terahertz remote sensing detection system of China, forms the monitoring capability of global atmospheric pollution and climate change, improves the influence on weather forecast and climate forecast, and has profound influence on urgent requirements of national defense construction and economic construction of China.
The existing atmospheric edge detectors divide frequency by adopting a quasi-optical frequency separation surface mode, so that the insertion loss is large, and more space is occupied. Atmospheric edge detectors have only used digital spectrometers in a few cases.
Disclosure of Invention
The invention aims to overcome the defects of large frequency division insertion loss, high error, lagging spectrum analysis technology and the like of the conventional atmosphere edge detector, and provides a brand-new design of the atmosphere edge detector.
In order to achieve the purpose, the invention provides a satellite-borne terahertz atmosphere edge detector, which comprises: the device comprises an antenna feed system, a scanning driving mechanism, a calibration body, a receiver, a plurality of rear end spectrometers and a numerical control unit;
the antenna feeder system is used for receiving the atmospheric edge radiation signal and the radiation signal of the calibration body and sending the signals to the receiver unit; the antenna feed system comprises an offset parabolic reflector antenna and four independent feeds with four frequencies;
the scanning driving mechanism is used for driving the antenna feed system to realize one-dimensional reciprocating swing and complete the in-line scanning of the atmosphere parallel to the satellite travelling direction;
the calibration body is used for providing brightness temperature calibration of the satellite in an in-orbit operation environment;
the receiver comprises four detection channels, and each detection channel performs down-conversion, amplification and filtering on a radiation signal of one feed source;
the back end spectrometer is used for carrying out spectrum analysis on signals output by each detection channel of the receiver so as to subsequently invert various atmospheric component contents and vertical distribution conditions;
and the numerical control unit is used for controlling the working state of the whole detecting instrument, sending data to the satellite tube counting computer, communicating, receiving, interpreting and executing a control instruction of the satellite tube counting computer.
As an improvement of the above device, the detecting instrument further includes a power supply for completing DC/DC conversion between the primary bus voltage and the secondary voltage of the satellite, and providing required voltage outputs for each component.
As an improvement of the above device, the offset parabolic reflector antenna is a standard offset parabolic antenna, and the four independent frequency feeds comprise: 640GHz feed horn antenna, 240GHz feed horn antenna, 190GHz feed horn antenna and 118GHz feed horn antenna.
As an improvement of the above device, the four detection channels of the receiver each include a radio frequency component and an intermediate frequency component; the four radio frequency components are respectively: 118GHz radio frequency components, 190GHz radio frequency components, 240GHz radio frequency components, 640GHz radio frequency components; the four intermediate frequency components are respectively: 118GHz intermediate frequency components, 190GHz intermediate frequency components, 240GHz intermediate frequency components and 640GHz intermediate frequency components; wherein the 1118GHz radio frequency part adopts a front LNA.
As an improvement of the device, the independent feed sources of the four frequencies, the four radio frequency components and the four intermediate frequency components are integrally designed.
As an improvement of the above apparatus, the calibration body includes: the calibration body is arranged between the offset parabolic reflector antenna and the four feed sources when the antenna feed system rotates to a specific position in an observation period under the action of the scanning driving mechanism, and the four feed sources receive radiation signals of the calibration body.
The invention has the advantages that:
1. the terahertz atmosphere limb detector antenna is formed by combining a single reflecting surface with four independent feed sources with four frequencies; the front-end quasi-optical frequency division is realized by using a reflecting surface and a discrete feed source, and compared with a frequency selection surface frequency division mode, the realization mode has the characteristics of small insertion loss, low error and the like;
2. the rear ends of the four working frequency bands are all in butt joint with a digital spectrometer, so that the spectrum analysis precision is higher;
3. the feed source and the receiver in the invention adopt an integrated design to optimize the available space to the maximum extent and improve the system index as much as possible;
4. the calibration scheme provided by the invention has a normal temperature source, a heating source and a cold air, and has one more temperature point compared with the traditional calibration mode, so that the calibration precision and accuracy can be improved.
Drawings
FIG. 1 is a system block diagram of a satellite-borne terahertz atmosphere near-edge detector disclosed by the invention;
FIG. 2 is a schematic diagram of the antenna feed system of the present invention;
fig. 3 is a schematic structural diagram of an antenna feed system of the present invention;
FIG. 4 is a diagram illustrating the relationship of four feed source positions;
FIG. 5 shows the spatial position relationship and the spacing between the elevation tangent planes of four feed sources;
FIG. 6 is a schematic side view projection of four feeds;
FIG. 7 is a schematic diagram of a layout of a calibration body;
FIG. 8 is a schematic view of the arrangement of the detectors of the present invention on a satellite;
FIG. 9 is a schematic diagram of a receiver module of the present invention;
FIG. 10 is an exploded view of the quad band integrated configuration of the present invention;
FIG. 11 is a layout diagram of a quad-band integrated configuration of the present invention;
FIG. 12 is a block diagram of a 2GHz bandwidth digital spectrometer system.
Detailed Description
The technical scheme of the invention is explained in detail in the following with reference to the attached drawings.
The invention discloses a satellite-borne terahertz atmosphere edge detector, which comprises: the device comprises an antenna feed system, a scanning driving mechanism, a calibration body, a receiver, a rear end spectrometer, a numerical control unit and a power supply unit; the antenna feeder system comprises: a projection caliber D is 1.6m of a standard offset parabolic antenna, the offset angle of a reflecting surface is 41.4039 degrees, the included angle of a feed source is 45 degrees, and multiple frequency points adopt a mode of a discrete feed source. The scanning mechanism adopts an integral scanning mode, the reflecting surface, the feed source and the receiver are integrated and are arranged on the satellite cabin plate through the rotary supporting mechanism, and the integral structure is controlled by a push-pull supporting rod to form the change of the observation direction through the front and back stretching, so that the scanning in the height direction is formed. The observation direction of the edge detector is parallel to the traveling direction of the satellite, and along with the scanning of the antenna in the height direction, the radiation signals in the received atmosphere edge direction enter each discrete feed source and are received by the corresponding receiver.
A, system constitution
Fig. 1 shows a functional block diagram of a terahertz edge detector system. The system comprises an antenna and scanning driving mechanism, a calibration body, a receiver (a radio frequency component and an intermediate frequency component), a digital spectrometer, a numerical control unit (comprising a spectrum analysis subunit and a data processing and communication subunit) and a power supply. Atmospheric radiation signals from the antenna are reflected by the primary mirror to the receiver system. The first path is the radiation coming from the antenna, the second path is the radiation from the cold air background, and the third path is the radiation of the calibration black body. The latter two paths of radiation are used to scale the receiver.
The radiation signals collected by the main reflecting surface respectively enter the front ends of the receivers at 118GHz, 190GHz, 240GHz and 640 GHz. The feed sources with different frequency points are connected into the receiver to complete low-noise amplification and frequency mixing of the front-end signal of the radiometer, and the intermediate-frequency signal is amplified and then further down-converted by 5 discrete components. The second-stage intermediate frequency down converter module uses different local oscillation frequencies to convert the frequencies into frequency bands suitable for the back-end spectrometer to work, and the converted intermediate frequency signals are fed into the back-end spectrum analysis component. And finally, the numerical control unit completes the functions of bus control and scientific data transmission.
1) Antenna form: the antenna adopts a form of a reflecting surface and a discrete feed source. Because the frequency of the system reaches 640GHz, the antenna shape and surface precision, the installation precision of the feed source, the availability of the focal plane and the layout thereof are key technologies, technical attack is needed, the influence of the integrated layout of the feed source and the receiver on the beam efficiency needs to be determined, and the realizability analysis and demonstration of the technology is also needed.
2) Front-end radio frequency network: the form of a reflecting surface and a discrete feed source is adopted, and the integrated design of the feed source and the front end of the receiver needs to be considered so as to optimize the available space to the maximum extent and improve the system index as much as possible.
3) The calibration mode comprises the following steps: the calibration adopting the discrete feed source system only needs to adopt the traditional two-point calibration technology, and is realized by shielding the feed source aperture, so that the requirement on the alignment precision is low.
Second, antenna feeder system
The antenna is composed of a single reflecting surface and four independent feed sources of frequencies, and the schematic diagrams of the antenna are shown in figures 2 and 3. The actual layout of the discrete feeds and their distribution characteristics in space are shown in fig. 4. The distance corresponding to a difference of 0.39 deg. in the height direction is about 17 km. The footprint size of the four frequency observations is 5.5, 3.84, 3.3, 0.96km in the plane perpendicular to the line of sight direction at the tangent point (calculated as 2500km (6378+600) × cos69 °), as shown in fig. 5. A schematic side view projection of the four feeds is shown in fig. 6.
The defect of adopting the separate feed source is that the observed regions have differences, but the system has simple design, low complexity and high measurement precision. With respect to quasi-optical separation schemes (overlapping observation regions, like concentric circles), the observation range here is about 22km x 38km range. But since the observations were made independently, the 5 radiometers operated independently. 118GHz provides pressure and temperature and the pressure data for the barometric cell is derived from the 118GHz inversion, so that for other cells there is a positional difference in pressure altitude of about 20km (considered here to be approximately constant within this range), since the atmospheric path is hundreds of kilometers long and the measured radiation is an integral quantity of such long path and therefore statistically reasonable.
Three, scanning strategy and sampling time design
The sweep range of the calibration source is from-7.8 to 4.9. The direction of the tangent to the earth's surface is set at 0 deg., below which is a negative angle, and above which is a positive angle. Two of the calibration sources were located at-5.18 ° (heating source) and-7.8 ° (normal temperature source), respectively. The observation range of the earth atmosphere adjacent edge is 0-2.6 degrees, and the cold air observation angle is 4.9 degrees.
Sampling at constant speed @0.26 °/s in a 0-2.6-degree edge range, wherein the sampling interval is about 1km, namely 100 sampling points are collected within 10s @100ms integration time. Stopping the black body and the cold air at the normal temperature for 2s respectively, and sampling 20 samples respectively; and staring at the normal temperature source for 2s, and oversampling without stopping by the heating source. The return stroke is also sampled from 2.6 to 0 degrees; the total number of samples in one cycle, 100 × 2+20 × 2+5 (heating source) ═ 245 points;
the initial position of the scan is-7.8 deg., and is aligned with the calibration source. The time allocation is as follows:
1) the time from-7.8 ° to 0 ° was set at 3 s.
2) From 0 DEG to 2.5022 DEG, the ascending motion is sampled for 0-100km, and the time is about 10 s;
3) going to a cold air calibration point for 3s from 100-200 km;
4) and sampling cold air at fixed points for 2 s.
5) The convolution process is designed to be the same as the forward process.
6) And reaching-7.8 degrees, and sampling the thermal calibration source at a fixed point for 2 s.
The total time of one cycle is about 36 s.
Four, scaling overall scheme
Scaling is a key to system application. Power scaling is achieved by means of external two-point scaling: a heat source and a cold air. The specific design is that a constant temperature source is placed at the starting point of scanning, then a heating source is arranged on the path, and cold air is directly observed at the end point (200km) of scanning. As shown in fig. 7 and 8.
This scaling method does not require additional aids. But due to the observation of two heat sources and cold air, the scanning range needs to be enlarged, and the scanning speed needs to be increased.
Fifth, the overall structure scheme
Fig. 9 gives a schematic view of the overall structure. The reflecting surface, the feed source and the receiver are integrated and are arranged on the cabin plate through the rotary supporting mechanism, and the integral structure is controlled through a push-pull supporting rod to stretch back and forth to form the change of the observation direction so as to form the scanning in the height direction.
And a calibration system is fixedly arranged on the satellite deck. When the radiometer system is retracted to the initial position, the feed source is shielded by the calibration source to form a calibration. And when the system is pushed to the highest point, the antenna integrally observes the cold air, and the cold air calibration is carried out.
In order to increase the on-track calibration capability in the ground test process, the design of the calibration source is divided into the combination of two black bodies, one black body is a normal-temperature black body and is not subjected to heat preservation and heat insulation installation, the other black body is heated on the ground, and the temperature is controlled to be about 60 ℃. The temperature of the normally warm blackbody is 20-30 ℃ lower than that of the satellite due to the fact that the normally warm blackbody is in the outside air environment, and the blackbody installed in a heat insulation mode is not heated at this time, only is passively insulated, and the temperature is close to that of the satellite. Thus, two-point calibration can be realized by two temperatures. Meanwhile, the cold air and air integrated observation is combined, a three-point calibration system can be realized, and the identification and correction of calibration errors are effectively enhanced, so that the calibration precision is improved.
Six, integrated receiver technical scheme
The schematic block diagram of the front end of the receiver of the atmospheric edge detector is shown in fig. 9, wherein the dashed frame part is an integrated part, and comprises: 640GHz, 240GHz, 190GHz and 118GHz feed horn antennas, 640GHz mixers, 320GHz multipliers, 160GHz multipliers, 240GHz mixers, 190GHz mixers, 118GHz orthogonal polarization splitters (OMT) and the like; the outside of the dotted line frame is: 118GHz low noise amplifier, 118GHz-H mixer, 118GHz-V mixer, 118GHz local oscillator link, 190GHz local oscillator link, 240GHz local oscillator link, 640GHz local oscillator link and the like. A four-band integrated part structure layout diagram is shown in fig. 10 and fig. 11.
Seven, 2GHz bandwidth digital spectrometer design scheme
The main indexes of the 2GHz bandwidth spectrometer are as follows:
sampling rate: not less than 4 Gsps;
quantization bit number: not less than 6 bits;
number of resolution channels in spectral analysis: not less than 1000.
The overall design system block diagram of the 2GHz bandwidth digital spectrometer is shown in FIG. 12. In signal acquisition, the ADC-EV8AQ160 completes the sampling of one path of signals. And the ADC output adopts an on-chip multiplexing parallel output mode. And the FPGA receives the ADC output data and performs related operation processing. In the design of the scheme, a high-speed clock chip AD9520 is adopted to generate a high-speed clock, and extremely low jitter of a sampling clock signal reaching an ADC is ensured. The FPGA configures the AD9520 and ADC by three-wire programming. The FPGA output data interface is provided with an LVDS interface, a serial port and a network port.
Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and are not limited. Although the present invention has been described in detail with reference to the embodiments, it should be understood by those skilled in the art that the technical solutions of the present invention may be modified or substituted with equivalents without departing from the spirit and scope of the technical solutions of the present invention, and all of them should be covered by the scope of the claims of the present invention.
Claims (2)
1. The utility model provides a satellite-borne terahertz atmosphere faces limit detection instrument which characterized in that, the detection instrument includes: the device comprises an antenna feed system, a scanning driving mechanism, a calibration body, a receiver, a plurality of rear-end spectrometers and a numerical control unit;
the antenna feeder system is used for receiving the atmospheric edge radiation signal and the radiation signal of the calibration body and sending the signals to the receiver unit; the antenna feed system comprises an offset parabolic reflector antenna and four independent feeds with four frequencies;
specifically, the offset parabolic reflector antenna is a standard offset parabolic antenna, and the independent four-frequency feed comprises: 640GHz feed horn antenna, 240GHz feed horn antenna, 190GHz feed horn antenna and 118GHz feed horn antenna;
four detection channels of the receiver respectively comprise a radio frequency component and an intermediate frequency component; the four radio frequency components are respectively: 118GHz radio frequency components, 190GHz radio frequency components, 240GHz radio frequency components, 640GHz radio frequency components; the four intermediate frequency components are respectively: 118GHz intermediate frequency components, 190GHz intermediate frequency components, 240GHz intermediate frequency components and 640GHz intermediate frequency components; the 118GHz radio frequency component adopts a front LNA;
the independent feed sources of the four frequencies, the four radio frequency components and the four intermediate frequency components adopt an integrated design;
the scanning driving mechanism is used for driving the antenna feeder system to realize one-dimensional reciprocating swing and complete the in-situ scanning of the atmosphere parallel to the satellite traveling direction;
the calibration body is used for providing brightness temperature calibration of the satellite in an in-orbit operation environment;
the calibration body includes: the system comprises a heating source and a normal temperature source which are fixed on a bracket, wherein the bracket is fixed on a satellite cabin plate, and in an observation period, under the action of a scanning driving mechanism, when a feed system rotates to a specific position, a calibration body is arranged between an offset paraboloid reflecting antenna and four feed sources which receive radiation signals of the calibration body;
the receiver comprises four detection channels, and each detection channel performs down-conversion, amplification and filtering on a radiation signal of one feed source;
the back end spectrometer is used for carrying out spectrum analysis on signals output by each detection channel of the receiver so as to subsequently invert various atmospheric component contents and vertical distribution conditions;
the numerical control unit is used for controlling the working state of the whole detecting instrument, sending data to the satellite tube counting computer, carrying out communication, receiving, interpreting and executing a control instruction of the satellite tube counting computer;
the scanning driving mechanism adopts an integral scanning mode, the reflecting surface, the feed source and the receiver are integrated and are arranged on the satellite cabin plate through the rotary supporting mechanism, and the integral structure is controlled by a push-pull supporting rod to form the change of an observation direction through front and back stretching, so that the scanning in the height direction is formed; the observation direction of the edge detector is parallel to the satellite travelling direction, and as the antenna scans in the height direction, the radiation signals in the received atmosphere edge direction enter each discrete feed source and are received by the corresponding receiver.
2. The spaceborne terahertz atmosphere limb detector according to claim 1, further comprising a power supply for completing DC/DC conversion of a primary bus voltage and a secondary voltage of a satellite and providing required voltage outputs for each component.
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| CN102375161A (en) * | 2010-08-10 | 2012-03-14 | 中国科学院空间科学与应用研究中心 | Spaceborne microwave atmospheric temperature and moisture detecting instrument |
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