32results about How to "Compensation System Error" patented technology

The invention relates to a method for establishing an equivalent geometric imaging model of a high-resolution satellite image by using RPC parameters. The method comprises: selecting a random scanningline of a high-resolution satellite image and listing a collinear condition equation of a projection center, an image point and a corresponding object square point; on the basis of operating characteristics and geometric characteristics of the high-resolution satellite, abstracting three rotation angles and six orbital numbers in an equivalent principal distance, a principal point coordinate, andan offset matrix and forming 11 independent parameters of an equivalent geometric imaging model; and with RPC parameters, calculating parameters of the equivalent geometric imaging model directly. Therefore, inherent problems of the over-parameterization of the RPC, strong correlation between parameters, and residual error existence of the fitting tight imaging model are solved; the parameters have the obvious geometric and physical meanings; and modeling analysis can be carried out on various imaging error sources conveniently. The mutual conversion of RPC parameters is realized; and the positioning accuracy of high-resolution satellite image is improved.

The embodiment of the present invention discloses a field test method for infiltration wind, the method includes: testing the wind speed v inside the entrance of the room to be tested; according to the wind speed v and the wind speed v and the first weight i 1 The first correspondence of determines the first weight i 1 , and use the wind speed v to calculate the first infiltration air volume Q 1 ;Test the indoor CO of the room to be tested 2 concentration and outdoor CO 2 Concentration; using indoor CO 2 concentration and outdoor CO 2 Concentration Calculation Second Infiltration Air Volume Q 2 ;according to indoor CO 2 concentration and outdoor CO 2 Concentration difference ΔCO 2 , the first weight i 1 And the second correspondence calculates the second weight i 2 ; Among them, the second corresponding relationship is the concentration difference ΔCO 2 with the first weight i 1 The corresponding relationship of the specific gravity k; the second weight i 2 The calculation formula is i 2 = 1.0‑i 1 k; calculate the infiltration air volume Q of the room to be tested; wherein, the calculation formula of the infiltration air volume Q is Q=i 1 ·Q 1 + i 2 ·Q 2 . Compared with the single test method, the test result of infiltration air volume obtained by this method is more accurate, and the system error is smaller.

The invention belongs to the technical field of spacecraft measurement and control, and discloses a method for measuring deformation of a vertical section of a shipborne large radar base. In view of the lack of available measurement methods for structural deformation in the vertical direction of current shipborne large-scale radar antenna bases, the method for measuring deformation of the verticalsection of the shipborne large radar base utilizes high-precision structural strain measurement capability of a fiber bragg grating sensor, and through an appropriate installation scheme design and acorresponding local strain variable and global deformation value calculation model, the measured value of the deformation of the radar base in the vertical direction is obtained. The method overcomesthe difficulty that a conventional optical deformation measurement method using a direct connection light path is difficult to implement due to the limited installation space inside the radar base. According to the method for measuring deformation of the vertical section of the shipborne large radar base, the fiber bragg grating sensor can be closely installed on the barrel wall of the radar basein an attaching mode, the space occupation is small, the deformation measurement precision is high, and the deformation of the radar base in the vertical direction can be obtained in real time at seadynamic conditions, so that the measurement accuracy of a shipborne radar can be improved.

The invention proposes an adaptive positioning and correction method for multi-frame images of an unmanned aerial vehicle based on an aerial attitude, and belongs to the technical field of remote sensing image processing. The main steps of the present invention are: (1) self-adaptive initialization; different initialization strategies are adopted for different sources of multi-frame images, and different initial values ​​are selected for different flight attitudes. (2) Determine the number of corresponding points with the same name according to the number of input image frames. (3) Use bundle adjustment method to establish constraints between multiple images to establish error equations, and traverse each point of the same name in each image to establish normal equations. (4) Add the correction number to the approximate value and iterate as a new approximate value until the correction number is less than the limit value, and output the correction number. The present invention accurately and real-time performs error correction on multiple acquired images with a common area during the online aerial photography process of the UAV, and improves the accuracy of positioning results.

The invention discloses a light source normalization processing method of a spectral confocal measurement system, which is to calculate the spectral intensity distribution of the light source by collecting the signal of the spectral confocal light source, and convert it into a normalization coefficient. The present invention can normalize the collected measured target signals in the normal measurement process to solve the problem of poor spectral uniformity of the light source, correct the error caused by the uniformity of the light source, and measure other optical devices in the system Error, so that the measurement accuracy and stability of the spectral confocal displacement sensor can be improved.

The invention discloses a current / voltage conversion traceability method for precision alternating current measurement. The method comprises (1) enabling an alternating current voltage-stabilizing source to be input to an alternating voltage proportion standard with known proportional error Eu to perform voltage / voltage proportion conversion, and obtaining standard voltage; (2) enabling the alternating current voltage-stabilizing source to be connected to a voltage type standard resistor with known resistance error Eru, and obtaining standard current; (3) inputting the obtained standard current to a current / voltage converter, performing corresponding current / voltage proportional conversion according to the standard current, and obtaining the converted voltage; (4) comparing the converted voltage with the standard voltage to obtain errors, and using the alternating voltage proportion standard and the voltage type standard resistor to correct the current / voltage converter, namely enabling the proportional conversion accuracy of current / voltage conversion to be traced to the alternating voltage proportion standard and the voltage type standard resistor. According to the current / voltage conversion traceability method, the current / voltage conversion traceability accuracy can be improved.

The invention belongs to large-size measuring technology, aims to acquire scanning light face structure parameters fitted with its actual shape and can improve measuring accuracy of a wMPS system. A three-dimensional coordinate reference field indoor space measuring, positioning and scanning light face calibration method includes: using a laser tracker to measure global control points under multiple stations, and cooperating with a weighting algorithm for optimizing measuring angle errors to acquire a three-dimensional coordinate reference field; taking coordinate field reference as referencefor wMPS scanning light face calibration of an indoor space measuring and positioning system; arranging an emitting station, and measuring and recording moment of each scanning light source when passing each control point; taking a quadric surface as a typical model with scanning light face more fitted with actual shape, establishing a constraint equation through coordinates of the control pointsin reference field space, combining with other constraints, using a least square method to resolve parameters of the scanning light face, and taking the parameters as intrinsic parameters of a wMPS single emitting station for reconfiguration. The method is mainly applied in large-size measuring occasions.

The invention discloses a method for correcting telescope pointing errors based on D-H matrix modeling under a moving platform. The pointing error of the telescope on the moving platform includes the system error of the telescope itself, the measurement error of the attitude sensor and the installation error between the attitude sensor and the telescope. Based on the analysis of error sources, the present invention establishes a correction model for pointing errors on a moving platform through the D-H method, including an error parameter calculation model and a guide value calculation model. The model takes all error sources into consideration at the same time, avoids the influence of error parameter coupling, and improves the pointing correction accuracy. The method of the invention first tracks multiple stars to obtain pointing data, then calculates all the error parameters in one step by using the error parameter calculation model, and then calculates the error-corrected guide value in two steps by using the target information and the guide value calculation model. The method of the invention is easy to implement, has high correction precision and stable performance, and can realize fast and high-precision pointing of the moving platform telescope.

The invention discloses a high precision sunward automatic tracking method. In order to improve the measuring precision, the method comprises the steps of: correcting error after installation of a system to eliminate the original error of the system; rapidly controlling the device according to a rapid control algorithm and a linear work section of a position measurement sensor; automatically adjusting the signal gain by using an intelligent gain adjusting algorithm to improve the measuring precision of the system, and improve the control precision of the device when a measuring signal is weaker; and inputting the measured data to a liquid crystal display screen and a serial port in real time for a user to conveniently observe on site and remotely. According to the high precision sunward automatic tracking method provided by the invention, the control precision of the system can be improved to 0.018 degrees, thereby improving the work efficiency of a solar power generating device.

The invention belongs to the technical field of liquid flow or volume measurement, and particularly relates to a main-standard volume calibration device and a main-standard volume calibration method based on positive and negative strokes of a commutator. A water pump is arranged in a water storage container and is connected with a filter. The filter is connected with a voltage-stabilized container, the voltage-stabilized container is connected with a hand valve, the hand valve is connected with a two-position four-way reversing electrically-operated valve, and the two-position four-way reversing electrically-operated valve is connected with a volume tube. A volume tube piston is positioned in the volume tube. A controller is connected with a photoelectric switch A, a photoelectric switch B and a photoelectric switch C. A light shielding plate is connected with a piston rod of the volume tube piston. The controller is connected with a positive-negative switch, and the positive-negative switch is connected with a two-position three-way reversing electromagnetic valve. The two-position four-way reversing electrically-operated valve is connected with the two-position three-way reversing electromagnetic valve. A weighing container is put on an electric scale and is arranged in a right access of the three-way reversing electromagnetic valve, and a recycling container is arranged in a left access of the three-way reversing electromagnetic valve. During reverse testing, positions of the weighing container and the recycling container are exchanged.

The invention discloses a method for solving an attitude and heading reference system of a four-rotor unmanned aerial vehicle based on gradient descent. The method comprises the following steps of: acquiring attitude information of a micro four-rotor unmanned aerial vehicle through a gyroscope, an acceleration sensor and a geomagnetic sensor, wherein the gyroscope is used for measuring the angular rate of the micro four-rotor unmanned aerial vehicle, the acceleration sensor is used for measuring the linear acceleration of the micro four-rotor unmanned aerial vehicle, and the geomagnetic sensor is used for measuring magnetic field information of the position where the micro four-rotor unmanned aerial vehicle is positioned; fusing data of the acceleration sensor and the geomagnetic sensor with data acquired by the gyroscope by employing a quaternion update algorithm based on gradient descent, and correcting drift of the gyroscope; and solving the attitude angle information of the micro four-rotor unmanned aerial vehicle by employing a quaternion method. By employing a data fusion method based on the gradient descent method, the drift of the gyroscope data is corrected in real time by fully utilizing the data of the acceleration sensor and the geomagnetic sensor, and three-dimensional attitude angle information is output, so that the system error is reduced, and the attitude measurement accuracy and stability are effectively improved.

The invention discloses a fusion method capable of reasonably quantizing the conflict and the coupling degree between measured values of a plurality of satellite sensors. The fusion method is characterized in that the conflict and the consistence between the measured values of the same measured target are quantized by a coupling degree and conflict degree matrix between different measured values and the process of quantizing the conflict and the consistence comprises the following steps: (1) providing a system error correction coefficient for the difference in average values of measurement results of the same batch of target values by the satellite sensors; (2) calculating the coupling degree of data according to an intersection set of a system error interval of each satellite sensor and the measurement result for the same measured target, and calculating a weight of each measured value; (3) calculating the conflict degree of the data according to a complementary set of the intersection set of the system error interval of each satellite sensor and the measurement result for the same measured target, and calculating a weight of each measured value; and (4) calculating the coupling weight and the conflict weight between the measured values for the same target by a plurality of satellite sensors through the system error correction coefficient so as to obtain a fusion value and a fusion error of seawater sea surface temperatures measured by a plurality of satellite sensors.