8 results about "Satellite laser ranging" patented technology

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.

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.

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 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.