14 results about "Satellite laser ranging" patented technology

The invention discloses an automatic target tracking method and system based on satellite laser ranging echo signals, and the method comprises the steps: S1, carrying out the space scanning of an uncertain domain of a ranging target through employing a regular hexagon dense scanning strategy, and completing the searching and capturing of the target; s2, after the target is captured, correcting the direction of the telescope by dynamically switching a global optimization mode and a local optimization mode by adopting a miss distance optimization method combining a Bayesian optimization algorithm and a local optimization algorithm, so as to complete the optimization of the miss distance; s3, target tracking is carried out based on the optimized miss distance, and echo signal intensity is monitored in real time; and S4, judging whether the signal is attenuated or not, re-triggering the miss distance optimization process when detecting that the signal is attenuated, and otherwise, maintaining the current tracking state.

The application provides a method and system for determining the formation orbit of a lunar satellite, comprising the following steps: S1, establishing a high-precision dynamics model of the lunar satellite; S2, establishing a laser ranging and inter-satellite ranging mathematical model of the lunar satellite; S3, measuring the distance of a satellite of type A relative to a ground station, i.e. the absolute position, by laser ranging, and measuring the relative position of a satellite of type B relative to the satellite of type A by inter-satellite ranging; S4, preprocessing the absolute position and relative position data of the satellites measured by laser ranging and inter-satellite ranging to generate a data file in a format required for orbit calculation; and S5, calculating the position coordinates of each satellite in the lunar satellite formation by using the data file. The application uses laser ranging and inter-satellite ranging to jointly determine the orbit, realizes precise orbit determination of the lunar satellite formation, and compared with the traditional orbit determination mode, the precision can be improved from the hundred-meter level to the meter level, and the requirements for the number and distribution of the ground stations are reduced, and the pressure of the existing ground stations is reduced.

The invention discloses a GNSS (Global Navigation Satellite System) multi-source precision satellite orbit product synthesis method and equipment, and belongs to the technical field of satellite navigation and geodetic survey. Precise orbit data of multiple analysis centers are obtained, and orbit pre-alignment is carried out; the satellites are grouped; calculating radial, tangential and normal residual error sequences of each central orbit relative to the reference orbit, and performing abnormal value detection and elimination based on a corrected Z-fraction method; defining a core satellite in each satellite group; the core satellite residual error is used as an observation value, the weight of each analysis center is determined by using a least square variance component estimation method, and satellite laser ranging prior information is introduced to enhance the estimation stability; carrying out weighted average on the track according to the weight to obtain a comprehensive track; and carrying out iterative updating until convergence. According to the method, the precision difference of data of different sources is fully considered, and a comprehensive orbit product with the precision and reliability superior to those of a single analysis center can be automatically and objectively generated.

The application discloses a lunar-orbit satellite laser ranging data error correction and precision analysis method, and belongs to the technical field of deep space measurement, and comprises the following steps: setting inner coincidence error and outer coincidence error of the whole laser ranging process; calibrating and modeling the system error and random error in the inner coincidence error, correcting the system delay by using the calibration target in real time, and synthesizing the standard deviation of random error to evaluate the data precision; establishing a physical model for the relativistic effect, atmospheric refraction, earth tide, station offset and corner reflector offset in the outer coincidence error to correct the outer coincidence error; and finally comparing with external reference values, calculating the root mean square error of residual error to evaluate the data accuracy. The application realizes systematic correction and precision quantitative analysis of the whole link error of the lunar-orbit satellite laser ranging, significantly improves the ranging data quality, and provides reliable data support for high-precision lunar-orbit orbit determination.

The application discloses a kind of low time jitter single-photon detection systems and methods and satellite laser ranging method, comprising: input light module, high voltage bias module, detection chip, temperature control module, passive gate quenching circuit module, output delay measurement module, constant ratio timing module and time compensation module.The technical scheme of the present application integrates the output delay measurement technology, time compensation technology, constant ratio timing technology and semiconductor patch refrigeration technology on the basis of conventional APD, integrates the above functions, modularization, solves the time jitter problem caused by the non-constant characteristics of APD bias voltage in passive gate circuit, improves the ranging accuracy of system.At the same time, the detection system is small and exquisite, and has strong compatibility and is easy to install.

This invention relates to a method, apparatus, and medium for analyzing elevation errors in satellite laser altimeter foothold positioning, belonging to the field of satellite surveying technology. The method includes acquiring sensor data from satellite sensors and discrete full-waveform data of laser light transmitted by a satellite laser altimeter; establishing a satellite laser ranging error model and determining influencing error factors, including laser ranging error; inputting the discrete full-waveform data into the satellite laser ranging error model to obtain the laser ranging error value; and obtaining a comprehensive elevation error value for satellite laser foothold positioning based on the sensor data and the laser ranging error value. This invention can calculate the laser ranging error value through the satellite laser ranging error model, thereby obtaining the comprehensive elevation error value for satellite laser foothold positioning from the laser ranging error value and data detected by other sensors, without requiring input of terrain parameters within the laser footprint, thus improving the usability of the model.

The invention belongs to the technical field of satellite precision measurement, and discloses an inter-satellite laser interference ranging frequency deviation calibration method and device, and the method comprises the steps: obtaining a double-satellite position vector, and carrying out the calculation to obtain an inter-satellite baseline vector; calculating according to the inter-satellite baseline vector to obtain an inter-satellite distance variation rate; obtaining an interference phase and an initial laser absolute frequency, and calculating to obtain an LRI instantaneous distance variation rate; according to the inter-satellite distance variability and the LRI instantaneous distance variability, calculating to obtain an LRI instantaneous variability scale factor; obtaining a daily scale factor value according to the LRI instantaneous variable rate scale factor; constructing a linear trend model according to the daily scale factor value and obtaining a scale factor observation value; iteratively calculating the scale factor observation value to obtain the iterated scale factor observation value; judging whether a convergence condition is met; and if yes, outputting the iterated scale factor observation value. The method can improve the calculation precision and efficiency of calculating the absolute frequency of the laser in the inter-satellite laser ranging by using the satellite orbit data.

This application belongs to the field of satellite precision measurement technology and discloses a method and apparatus for calibrating the frequency deviation of inter-satellite laser interferometric ranging (LRI). The method includes: acquiring the position vectors of two satellites and calculating the inter-satellite baseline vector; calculating the inter-satellite distance variation based on the inter-satellite baseline vector; acquiring the interferometric phase and the initial absolute laser frequency and calculating the instantaneous LRI distance variation; calculating the LRI instantaneous variation scale factor based on the inter-satellite distance variation and the LRI instantaneous distance variation; obtaining the day-scale factor value based on the LRI instantaneous variation scale factor; constructing a linear trend model based on the day-scale factor value and obtaining the scale factor observation value; iteratively calculating the scale factor observation value to obtain the iteratively calculated scale factor observation value; determining whether the convergence condition is met; if so, outputting the iteratively calculated scale factor observation value. This application can improve the calculation accuracy and efficiency of the absolute laser frequency in inter-satellite laser ranging using satellite orbit data.

The invention discloses a lunar orbit satellite laser ranging data error correction and precision analysis method, and belongs to the technical field of deep space measurement, and the method comprises the steps: setting an internal coincidence error and an external coincidence error of a whole laser ranging process; performing calibration and modeling processing on system errors and random errors in the internal coincidence errors, correcting system delay in real time by adopting a calibration target, and synthesizing a random error standard deviation to evaluate data precision; establishing a physical model for correcting the relativistic effect, atmospheric refraction, earth tide, observation station offset, corner reflector offset and the like in the external coincidence error; and finally, through comparison with an external reference value, a residual error root-mean-square error is calculated, and data accuracy is evaluated. According to the method, systematic correction and precision quantitative analysis of the laser ranging full-link error of the lunar orbit satellite are realized, the ranging data quality is remarkably improved, and reliable data support is provided for high-precision lunar orbit determination.

The present invention discloses a hierarchical rapid search method for high-precision lunar-orbit satellite laser ranging echo signals, which belongs to the field of deep-space laser ranging technology. The method comprises: a ground-side laser emission system tracks and points to a target position according to a guidance file; emitting a long-pulse-width laser signal, and if no tracking target point echo is detected, performing a target point airspace search based on an Archimedean spiral search model; after receiving the tracking target point echo signal at the current position, stopping the Archimedean spiral search, and continuing to track the trend of the predicted orbit guidance file with the current position as the correction origin; if the tracking target point echo signal quality reaches a predetermined recognition threshold, emitting a narrow-pulse-width laser signal, entering a precision measurement mode, and acquiring high-precision laser measurement data. The present invention can effectively shorten the search time for lunar-orbit satellite angular reflection echoes, and improve the success rate of capturing satellite angular reflection laser echo signals in a complex and far-reaching Earth-Moon space environment.

The invention provides a reflector layout optimized laser attitude measurement and identification method, which comprises the following steps of: installing a plurality of laser corner reflectors in an L-shaped layout, and obtaining a measurement distance difference of the plurality of laser corner reflectors based on satellite laser ranging; the spacing ratio of the plurality of laser corner reflectors which are collinearly arranged is used as an identity identification code; defining the measurement distance differences in sequence and calculating a discriminant; determining a target identity and a reflection sequence by taking an invariant of the discriminant as a matched identity identification code; and determining the one-to-one correspondence relationship between the distance measurement data and the laser corner reflectors according to the reflection sequence, respectively calculating the included angles between the two base lines and the measurement direction vector, and carrying out attitude calculation in combination with the coordinates of the observation station and the target carrier to obtain the attitude of the target carrier. According to the invention, through special arrangement of the laser corner reflectors and satellite laser ranging data, rapid identification and complete attitude real-time measurement of satellites are realized.

The application provides a laser attitude measurement and identification method with reflector layout optimization, comprising the following steps: installing multiple L-shaped laser corner reflectors, obtaining the measurement distance difference of the multiple laser corner reflectors based on satellite laser ranging, taking the spacing ratio of the multiple laser corner reflectors arranged in a same line as an identity code, defining and calculating the discriminant of the measurement distance difference in sequence, taking the invariant of the discriminant as the matched identity code, determining the target identity and the reflection sequence, determining the one-to-one correspondence between the ranging data and the laser corner reflectors according to the reflection sequence, respectively calculating the included angle between the two baselines and the measurement direction vector, and then combining the coordinates of the station and the target carrier to perform attitude calculation and obtain the attitude of the target carrier. The application realizes the rapid identification of the satellite and the real-time measurement of the complete attitude by the special arrangement of the laser corner reflectors and the satellite laser ranging data.

This invention relates to the interdisciplinary fields of satellite navigation and satellite dynamics. Specifically, it presents a GRACE-FO orbit determination accuracy assessment method with fixed integer ambiguity. Based on onboard GPS observations, it generates floating-point solutions and IAR fixed-solution orbits using kinematic, simplified dynamics, and dynamic methods, respectively. Using the JPL PSO precise orbit as a reference, it statistically analyzes the three components of the RTN and the three-dimensional position difference (RMS). Simultaneously, it utilizes the K-band inter-satellite ranging (KBR) and satellite laser ranging (SLR) residuals for external verification and conducts frequency domain error spectrum analysis to characterize the error variation with frequency. The quantitative results of this invention can provide a basis for the selection of IAR application strategies and accuracy assessment for low-Earth orbit satellites.

The invention relates to the technical field of satellite navigation, and particularly discloses a global positioning method based on combination of a mobile radar and satellite laser ranging. The method mainly comprises the following steps: observing a specific space target by using a radar, and determining the initial position of the radar; and then observing the laser satellite by using a radar to obtain distance information from the radar station to the laser satellite. Laser and radar data are used for resolving observation station coordinates, the position of a radar station relative to a global laser satellite constellation is obtained, and then precise coordinate information of the radar station is obtained through coordinate conversion. The technical scheme of the invention aims to solve the problems that the existing GPS or Beidou navigation system depends on a special satellite signal, the system construction and maintenance cost is high, and the navigation signal is easy to interfere or shield to cause positioning failure. The core of the invention lies in that a satellite constellation is constructed by using existing on-orbit satellites provided with laser corner reflectors, and autonomous and high-precision global positioning of a ground observation station is realized by combining a flowing radar and a satellite laser ranging technology.