CN113503965B - Method for realizing synchronous imaging of satellite-borne imaging spectrometer by using satellite platform second pulse - Google Patents
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- G—PHYSICS
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- G01J—MEASUREMENT OF INTENSITY, VELOCITY, SPECTRAL CONTENT, POLARISATION, PHASE OR PULSE CHARACTERISTICS OF INFRARED, VISIBLE OR ULTRAVIOLET LIGHT; COLORIMETRY; RADIATION PYROMETRY
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- G—PHYSICS
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- G01J—MEASUREMENT OF INTENSITY, VELOCITY, SPECTRAL CONTENT, POLARISATION, PHASE OR PULSE CHARACTERISTICS OF INFRARED, VISIBLE OR ULTRAVIOLET LIGHT; COLORIMETRY; RADIATION PYROMETRY
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Abstract
The invention discloses a method for realizing synchronous imaging of a satellite-borne imaging spectrometer by using satellite platform second pulses, which comprises the steps of simultaneously detecting second pulse signals from a satellite platform by using FPGA (field programmable gate array) of two imaging spectrometers, extracting the leading edge of the second pulse and generating an internal second synchronous signal; resetting the internal sequential logic of the FPGA by using the existing second pulse, setting the frame transfer CCD exposure time as the imaging period, completing one or a plurality of complete imaging at the arrival time of each second pulse by two CCDs with different exposure times, and starting the next round of shooting at the same time; the imaging spectrometer is made to use a frame transfer CCD whose pixel readout time and exposure time are overlapping, i.e. during each exposure, the readout of the last image is completed. The invention uses the on-board second pulse, and can realize synchronous imaging of a plurality of imaging spectrometers with different exposure time by designing the exposure time sequence and the CCD readout time sequence under the condition of not adding hardware, and the synchronous precision is better than 100ns.
Description
Technical Field
The invention relates to the technical field of satellite-borne imaging spectrometers, in particular to a method for realizing synchronous imaging of a satellite-borne imaging spectrometer by using satellite platform second pulse.
Background
The atmosphere observation satellite-borne imaging spectrometer performs spectral imaging on the ground (an area array CCD camera performs push-broom under multiple spectral lines). And simultaneously acquiring the space and spectrum dimension information of the target area. The distribution of the atmospheric components is obtained by the spectral curves of the spatial dimension points. To obtain a wider spectrum detection range for more gas component distribution, for example, two imaging spectrometers in ultraviolet and visible bands are placed on the same low orbit satellite platform. Because of the low geographical resolution requirements of atmospheric observations, each imaging spectrometer has previously operated independently, marking the geographical coordinates of each line of images with an image time scale (on-board broadcast time, accurate to seconds). The imaging beats of the two spectrometers depend on the respective crystal oscillator, so that the image dyssynchrony causes the data time marks to be staggered, thereby causing the data products, namely the ultraviolet band atmospheric distribution diagram and the visible band atmospheric distribution diagram, to be staggered by 1 row of images at most, and corresponding to the deviation of 14 km in geographic position (the flight distance of two seconds of a low orbit satellite).
Currently, multiple CCD synchronous controls are required, typically in several forms:
1) Homology to plate: the multichannel CCD shares a crystal oscillator and the same controller. The design is limited to a small spectrometer, and for a spectrometer with a complex light path and a large caliber, the focal planes of the two spectrometers are arranged in a short distance, so that the light path and the mechanical design of the spectrometer are limited, and the spectrometer is not suitable for a spectrometer with a complex light path.
2) Using a synchronous controller: the external trigger signal is provided for each camera, and the external trigger signals of different exposure time are synchronized on a long period. Thus, extra hardware circuits are added outside the two current satellite-borne spectrometers.
3) Synchronizing by an upper computer control command: the invention relates to a space multichannel TDICCD camera synchronization method, which does not increase hardware, and only needs a load control computer to send a starting command through an RS-422 serial port. The two cameras work after receiving the command. However, as the mode is soft part operation, the on-board main control CPU simultaneously serves a plurality of tasks, and the time delay is uncontrollable; the invention only carries out imaging synchronization when the system is started, is easy to cause error accumulation and is not suitable for synchronization of continuous photographing type multichannel imaging spectrometers.
4) Clock phase locked loop synchronization: the imaging plate time adding system circuit uses a high-stability crystal oscillator and a voltage-adding control circuit to construct a phase-locked loop, and uses a disciplinary clock algorithm to obtain a real-time clock. The two spectrometers operate in a timed photographing mode. This solution also requires additional hardware circuitry.
Along with the improvement of the measurement precision requirement, the gas distribution diagram detected by the ultraviolet band and the gas distribution diagram detected by the visible band have higher coincidence degree, so that the requirement of synchronous shooting of two imaging spectrometers is provided.
Disclosure of Invention
According to the method for realizing synchronous imaging of the satellite-borne imaging spectrometer by using the satellite platform second pulse, the satellite-borne second pulse signal is used, the two spectrometers synchronously shoot by setting the exposure time of which the second is a period and designing the corresponding CCD chip reading time sequence, so that the overlapping error of the obtained images is not more than 100 nanoseconds, and meanwhile, more hardware expenditure is not increased.
In order to achieve the above purpose, the present invention adopts the following technical scheme:
a method for realizing synchronous imaging of a satellite-borne imaging spectrometer by using satellite platform second pulse is based on two imaging spectrometers and a satellite platform, an imaging circuit of the imaging spectrometers comprises an FPGA, a crystal oscillator and a CCD, and comprises the following steps,
the FPGA of the two imaging spectrometers simultaneously detects a second pulse signal from a satellite platform, and extracts the leading edge of the second pulse to generate an internal second synchronous signal; setting a satellite-borne imaging spectrometer to continuously shoot, and adopting a frame transfer CCD, wherein the two imaging spectrometers are respectively ultraviolet and visible channels;
the method comprises the steps that the existing second pulse is utilized to reset the internal sequential logic of an FPGA, the operation period of a CCD is fixed, and an exposure and pixel reading module resets the value of an exposure time period register by using a second synchronous signal;
defining the exposure time gear of the imaging spectrometer as an integer frequency division value of seconds, fixing a CCD reading period as an exposure period shorter than the highest frame frequency, and selecting a crystal oscillator frequency according to the total beat number of a reading logic, so that the difference value between the reading time and the exposure time meets the redundancy of crystal oscillator errors and system time errors, and ensuring that the last image per second is read earlier than the second pulse arrival time;
designing the whole reading time of the CCD to be smaller than the exposure time of the highest frame frequency, meeting the redundancy of crystal oscillator errors, resetting and recounting if the exposure control counter is not the last frame of a one-second period when the exposure control counter reaches a set value, and starting the next exposure;
if the time is the last time, stopping counting, waiting for second pulse reset, wherein the second pulse preferably resets the exposure time counter and other corresponding control registers under any state, ending the current time sequence and starting a new time sequence generation period.
Further, it also includes integer division defining the exposure time as one second, i.e., 1/16S,1/12S,1/8S,1/6S,1/4S,1/3S,1/2S,1S for a total of 8 steps.
According to the technical scheme, the method for realizing synchronous imaging of the satellite-borne imaging spectrometers by using the satellite platform pulse per second provided by the invention uses the existing pulse per second signals provided by the satellite platform to realize synchronous imaging of 2 imaging spectrometers and a plurality of imaging spectrometers, and is simple and reliable without increasing extra hardware cost.
In general, the invention uses satellite second pulse, and can realize synchronous imaging of a plurality of imaging spectrometers with different exposure time by designing the exposure time sequence and the CCD readout time sequence under the condition of not adding hardware, and the synchronous precision is better than 100ns.
Drawings
FIG. 1 is a schematic diagram of an imaging spectrometer imaging system;
FIG. 2 is a push-broom imaging of an imaging spectrometer and results;
FIG. 3 is a schematic diagram of the deviation between the time scale and the actual exposure under the condition of independent photographing by two spectrometers;
FIG. 4 is a system block diagram of the present invention;
FIG. 5 is a logic design of the FPGA of the camera imaging circuit of the present invention (other exposure times are similar for 1/4S exposure time).
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the embodiments of the present invention more apparent, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is apparent that the described embodiments are some embodiments of the present invention, but not all embodiments of the present invention.
The imaging spectrometer is composed of a telescope, a slit, a grating and an area array detector (CCD or CMOS), wherein light passing through the slit is divided into spectrums through the grating, the spectrums are scattered and projected along one direction of the area array CCD, and the other direction of the CCD corresponds to the position of a geometric pixel. Thus, the image obtained by each shot of the CCD is a distribution of different spectra of a narrowband target (as shown in FIG. 1).
Along with the movement of the target or the movement of the imaging spectrometer, scanning imaging is carried out on the target, as shown in fig. 2, an imaging spectrometer of an area array CCD loaded with 1024×1024 pixels is carried on a satellite platform, and when photographing the ground, namely, the imaging spectrometer is equivalent to 1024 linear array CCDs which sweep the map on different spectral lines at the same time, and each image is 1024 spectral lines of a geographically long and narrow strip (1024 pixels).
The satellite-borne atmosphere observation imaging spectrometer images the ground, and according to the characteristic absorption spectrum lines of different gases, the distribution of different gas components can be obtained, and environmental protection and meteorological data are provided.
In order to observe more gas, imaging spectrometers with different spectral ranges can be used and are mounted on the same satellite platform, for example, the application case of the invention is to use two imaging spectrometers with ultraviolet and visible spectral ranges to be mounted on the same satellite platform.
In the past, because the atmospheric observation is not high to the geographical resolution requirement, two spectrometers independently take photos. Map matching is respectively carried out according to the data time marks of the two spectrometers. The time scale is the broadcasting time provided by the satellite platform, and the precision is 1S. The atmospheric profiles of the two spectrometers are maximally likely to be displaced 7 km (the flight distance of the low orbit satellite 1S). As shown in fig. 3, for example, the exposure time of one second is taken as an example, two spectrometers work with respective crystal oscillators, and the imaging time stamp (precision 1S) where each exposure starting time is recorded; if the crystal oscillator error of the imaging spectrometer 1 is assumed to be +30%, and the error of the spectrometer 2 is assumed to be-16.7%, when the time scale of the spectrometer for photographing the 4 th image is 4, the time scale of the spectrometer 2 for photographing the 6 th and 7 th images is 4, that is, one image with the same time scale in the two spectrometer data is inconsistent due to the real exposure starting time, at most, the deviation of a row of images in the geographic position (one image is obtained as a result of each imaging in time) may be caused. Note that here in one image there corresponds to 1024 spectral lines, which are in fact one row in the geographic direction, i.e. a single row image of 1024 pixels. Thus, the spectrometer geographical coordinates of the two channels are staggered by at most 7 km.
Moreover, this phase difference is not fixed but changes gradually periodically, due to the differences of the respective crystal oscillators. In addition, it should be noted that in the application of imaging spectrometers, the improvement of the timing accuracy cannot change the synchronization bias of two imaging spectrometers, because unlike a frame-type imaging device, the geographic imaging corresponding to one image of the spectrometer is actually one row of pixels, and each pixel is integrated for one second (7 km) in the flight direction and cannot be subdivided.
With the recent increase in the demands of users for accuracy of observation, the requirements for the coincidence ratio of the ultraviolet and visible spectrum atmospheric component profiles are higher. For this purpose, two imaging spectrometers are required to record simultaneously.
As shown in fig. 4, the method for realizing synchronous imaging of satellite-borne imaging spectrometers by using satellite platform pulse per second according to the embodiment of the invention uses the existing pulse per second signal provided by the satellite platform to realize synchronous imaging of 2 imaging spectrometers and a plurality of imaging spectrometers, and the invention does not increase extra hardware cost, and is simple and reliable.
The method comprises the following steps:
the method is concretely realized by a camera imaging circuit, and a plurality of cameras use the imaging circuit; the imaging circuit comprises core elements such as FPGA, crystal oscillator and the like; as shown in fig. 4.
The FPGA of the two imaging spectrometers simultaneously detects the second pulse signals from the satellite platform, the front edge of the second pulse is extracted to generate an internal second synchronous signal, and then synchronous imaging of the two cameras is realized through the FPGA logic design.
The FPGA logic design comprises an imaging time sequence and a combined logic circuit, wherein the CCD imaging time sequence of the spectrometer is generated by an imaging circuit board, and the clock reference of the logic circuit is from an on-board crystal oscillator. It is not possible to use the same crystal oscillator for both spectrometers. To synchronize the two spectrometers, an external homologous trigger signal is required. Designing a trigger signal generator alone requires the addition of additional circuitry. The invention uses the existing second pulse signal of the satellite platform as a synchronous signal source, and completes the photographing synchronization of two spectrometers on the basis of not increasing hardware.
The second pulse is generated by satellite time system equipment and transmitted to each single machine on the satellite, and a single machine timing information source is provided by matching with a broadcasting time packet. The photographing time sequence of the CCD is controlled by an FPGA (field programmable logic array) of a CCD imaging circuit, and the time sequence logic of the FPGA is designed as follows by using second pulses as synchronous signals:
the exposure time is defined as an integer division of one second, i.e., 1/16S,1/12S,1/8S,1/6S,1/4S,1/3S,1/2S,1S for a total of 8 steps. So that different spectrometers can complete the whole exposure at the whole second time by using different exposure time.
Then, the logic design method of the FPGA is as follows:
resetting the internal sequential logic of the FPGA by using the existing second pulse on the satellite, fixing the exposure time period register value by taking each second as one CCD operation period, and resetting the exposure time period register value by using a second synchronous signal by an exposure and pixel reading module;
defining the exposure time gear of the imaging spectrometer as an integer frequency division value of seconds, fixing a CCD reading period to be slightly shorter than the exposure period (1/16S) of the highest frame frequency, and selecting the crystal oscillator frequency according to the total beat number of the reading logic, so that the difference value between the reading time and the exposure time is enabled to meet the redundancy of crystal oscillator errors and system time errors, and the last graph per second can be read out earlier than the second pulse arrival time;
the whole reading time of the CCD is designed to be slightly smaller than the exposure time of the highest frame frequency, crystal oscillator error redundancy is met, when the exposure control counter counts to a set value, if the exposure control counter is not the last one of the one second period, the exposure control counter resets and recounts, and the next exposure is started. If the time is the last time, stopping counting, waiting for second pulse reset, wherein the second pulse preferably resets the exposure time counter and other corresponding control registers in any state, ending the current time sequence and starting a new time sequence generation period.
The specific explanation is as follows:
1) In order to ensure the detection efficiency, the satellite-borne imaging spectrometer continuously shoots and adopts a frame transfer CCD. The two imaging spectrometers are respectively ultraviolet and visible channels, and the exposure time of the two channels may be set differently for different background brightnesses of the ground. To achieve second synchronization, the exposure gear needs to be set to an integer fraction of seconds. The invention uses 8 exposure time steps of 1/16 second, 1/12 second, 1/8 second, 1/6 second, 1/4 second, 1/3 second, 1/2 second and 1 second, namely 16 frames, 12 frames and 8 frames … frames are continuously shot every second. The frame transfer CCD exposure time is the imaging period thereof,
2) The imaging spectrometer uses a frame transfer CCD whose pixel readout time and exposure time overlap, i.e. during each exposure, the readout of the last image is completed, as shown in fig. 5. When there is no synchronization requirement, the CCD operation usually designs the exposure time to be the readout time, so that the exposure period can be utilized to the maximum extent, and the readout rate can be reduced, so as to obtain greater transfer efficiency and smaller readout noise. However, with pulse-per-second synchronization, 1S of the crystal oscillator timing may not coincide with one second of the pulse-per-second due to an accuracy error for the crystal oscillator of the imaging circuit itself. The satellite second pulse is the standard second that GPS signal or time service signal is tamed by the clock source with high stability. The crystal oscillator used by the imaging circuit is a space-flight crystal oscillator with common precision, the precision error is 50ppm, and the temperature drift and long-term drift also reach 50ppm, that is, the 1 second of the crystal oscillator timing of the circuit can be +/-100 microseconds from the standard second. The read operation of the CCD chip requires 2950000 beats, and if this beat is taken as the number of crystal oscillator clocks, the required crystal oscillator frequency is 2950000clocks×16 per second, i.e., 47.2MHz. On the premise of no need of synchronization, a crystal oscillator of 47.2MHz can be adopted. However, the second pulse synchronization method needs a slightly higher frequency, otherwise, due to crystal oscillation error, when the second pulse arrives, the readout of the last image is not completed (the crystal oscillation is slightly slower than the nominal value), and a new period starts, so that pixel data can be lost. For this reason, using a 48MHz crystal oscillator, slightly larger than the readout period, a margin of about 1mS can be obtained, and errors of the crystal oscillator and the second pulse can be completely eliminated. That is, under the shortest exposure condition of 1/16 second (62.5 mS), the operating frequency of the 48MHz crystal oscillator was 3000000 clocks by the exposure period meter, and 2950000clocks (61.5 mS) for reading. The end of reading is 1mS before the end of exposure. After the last pattern read out per second is completed, there are theoretically 50000clocks (1 mS) to complete the exposure while the second pulse arrives. Due to crystal oscillator errors, the pulse per second may be earlier or later than this clock number, but the error is not greater than 1mS. Meanwhile, after the exposure period of the last image is counted up to 3000000 clocks, the reset is not actively performed, but the reset is waited for by the second pulse, and the image of the exposure period starts to be read out after the reset. If 3000000 clock pulses have not been counted, the reset is forced and the next cycle is started, as shown in fig. 5. Thus, the exposure time of the last image contains the cumulative crystal oscillation error in one second (+/-100 microseconds), but is also allowed by the measurement accuracy.
Based on the design, different imaging spectrometers of the same satellite platform can achieve 20 nS-100 nS synchronous precision, and the synchronous precision depends on the difference of the distance between the two spectrometers and the transmission time delay of the pulse per second signals.
In summary, the invention uses the on-satellite second pulse, and can realize synchronous imaging of a plurality of imaging spectrometers with different exposure time by designing the exposure time sequence and the CCD readout time sequence under the condition of not adding hardware, and the synchronous precision is better than 100ns.
The above embodiments are only for illustrating the technical solution of the present invention, and are not limiting; although the invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical scheme described in the foregoing embodiments can be modified or some technical features thereof can be replaced by equivalents; such modifications and substitutions do not depart from the spirit and scope of the technical solutions of the embodiments of the present invention.
Claims (2)
1. The method for realizing synchronous imaging of the satellite-borne imaging spectrometer by using the satellite platform second pulse is based on two imaging spectrometers and a satellite platform, and an imaging circuit of the imaging spectrometer comprises an FPGA, a crystal oscillator and a CCD, and is characterized in that: comprises the steps of,
the FPGA of the two imaging spectrometers simultaneously detects a second pulse signal from a satellite platform, and extracts the leading edge of the second pulse to generate an internal second synchronous signal; the method comprises the steps of setting a satellite-borne imaging spectrometer to continuously shoot, adopting a frame transfer CCD, and respectively arranging an ultraviolet channel and a visible channel on the two imaging spectrometers;
the method comprises the steps that the existing second pulse is utilized to reset the internal sequential logic of an FPGA, the operation period of a CCD is fixed, and an exposure and pixel reading module resets the value of an exposure time period register by using a second synchronous signal;
defining the exposure time gear of the imaging spectrometer as an integer frequency division value of seconds, fixing the CCD reading period as an exposure period shorter than the highest frame frequency, and selecting the crystal oscillator frequency according to the total beat number of the reading logic, so that the difference value between the reading time and the exposure time meets the redundancy of crystal oscillator errors and system time errors, and ensuring that the last image per second is read earlier than the second pulse arrival time;
designing the whole reading time of the CCD to be smaller than the exposure time of the highest frame frequency, meeting the redundancy of crystal oscillator errors, resetting and recounting if the exposure control counter is not the last frame of a one-second period when the exposure control counter reaches a set value, and starting the next exposure;
if the time is the last time, stopping counting, waiting for second pulse reset, and enabling the second pulse to reset the exposure time counter and other corresponding control registers in any state preferentially, ending the current time sequence, and starting a new time sequence generation period.
2. The method for realizing synchronous imaging of the satellite-borne imaging spectrometer by using the satellite platform second pulse according to claim 1, wherein the method comprises the following steps of: also included are integer divisions defining exposure times of one second, i.e., 1/16S,1/12S,1/8S,1/6S,1/4S,1/3S,1/2S,1S for a total of 8 steps.
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