47 results about "Sun sensor" patented technology

The invention discloses a tracking type photovoltaic power generation device which comprises a base, a rotating platform is rotatably arranged on the upper end face of the base, a driving mechanism used for driving the rotating platform to rotate is fixedly arranged at the bottom of the base, a vertical plate is fixedly arranged on the upper end face of the rotating platform, and a photovoltaic power generation panel is hinged to the upper end of the vertical plate. An angle adjusting mechanism used for driving the photovoltaic power generation panel to adjust the elevation angle is connected between the side face of the vertical plate and the bottom face of the photovoltaic power generation panel, solar sensors are fixedly arranged at the four corners of the photovoltaic power generation panel correspondingly, and sweeping assemblies used for removing dust on the surfaces of the solar sensors are fixedly arranged on the left side edge and the right side edge of the photovoltaic power generation panel correspondingly. According to the tracking type photovoltaic power generation device, through the automatic cleaning assembly and the intelligent control algorithm module, the requirement for manual intervention is reduced, manual regular cleaning of the solar sensor is not needed, and meanwhile, the tracking type photovoltaic power generation device can still stably operate in various complex environments, so that the tracking type photovoltaic power generation device has good practicability in different geographical environments and weather conditions.

The invention relates to a passive and wireless simulation sun sensor system, comprising: an NFC wireless receiving module configured to provide energy for an NFC simulation sun sensor patch and receive digital information of a solar ray angle sent by the NFC simulation sun sensor patch; the NFC simulation sun sensor patch comprises a four-quadrant battery piece which is configured to generate photo-generated current; the I / V conversion circuit is connected with the four-quadrant battery piece and is configured to convert photo-generated current into analog voltage; the microprocessor is connected with the I / V conversion circuit and the NFC antenna and is configured to process analog voltage to generate digital information of a solar ray angle; the NFC chip is connected with an NFC antenna and the microprocessor; and the NFC antenna is configured to send digital information of a solar ray angle to the NFC wireless receiving module, acquire energy from the NFC wireless receiving module and supply the energy to the NFC chip, the I / V conversion circuit and the microprocessor.

The utility model relates to the technical field of lighting devices, in particular to a novel energy-saving light guide lighting device which comprises a base, the outer wall of the base is fixedly connected with the inner wall of a driving piece, one side of the driving piece is fixedly connected with one side of a lighting piece, and the front face of one end of the lighting piece is fixedly connected with the back face of a lighting piece. The outer wall of the lighting part is fixedly connected with the inner wall of the adjusting part, the inner wall of the base is rotationally connected with the outer wall of the driving part, the inner wall of the lighting part is rotationally connected with the outer wall of the adjusting part, the sun sensor controls the driving motor and the rotating motor, and the driving motor drives the lens lighting assembly to rotate through the supporting shell. The rotating motor drives the lens lighting assembly to rotate through the driving gear, the transmission gear and the rotating rod in sequence, so that the lens lighting assembly tracks, collects and separates sunlight, the collected and separated sunlight is transmitted to the indoor irradiation lamp through the optical fiber, indoor irradiation is achieved, and convenience is brought to use of people.

The invention relates to an antifouling outer cover of a digital sun sensor, and belongs to the technical field of structures. Comprising a digital sun sensor bracket, an antifouling cover body and a digital sun sensor, wherein the digital sun sensor bracket is vertically mounted at the bottom of an external satellite structural plate; the digital sun sensor is mounted in the middle of the lower surface of the digital sun sensor bracket; the antifouling cover body is mounted at the circumferential outer edge of the lower surface of the digital sun sensor bracket to realize circumferential shielding protection of the digital sun sensor; the antifouling cover body is of a gradually-expanded cover body structure with the horizontal section being in an isosceles trapezoid shape. The top of the antifouling cover body is in butt joint with the digital sun sensor support, and the size of the horizontal section of the top of the antifouling cover body is minimum. The size of the horizontal section of the antifouling cover body is gradually increased from top to bottom; the device is simple in structure and convenient to operate, pollutants can be shielded in the satellite-rocket separation process, and the requirement of the field of view of the digital sun sensor can be met.

Sun sensor for a vehicle (100), vehicle with the sun sensor, method for operating the vehicle, wherein the sun sensor comprises several module cells of a photovoltaic module (101) of a photovoltaic system for the vehicle (100), wherein the sun sensor is configured to detect and / or output a sensor value, in particular a radiant power, a voltage, and / or a current, wherein the sensor value characterizes a solar irradiance into a module cell or a solar irradiance into several module cells.

This paper presents a small satellite digital sun sensor polarity automatic test system and method for the polarity test of small satellite digital sun sensors during the overall satellite test phase. This test device consists of an optical system, a support and rotation mechanism, and ground test equipment, creating a digital sun sensor polarity test mode that integrates functions such as simulating the sun light source, controllable irradiation angle, instruction execution, and corner data broadcasting. The optical system generates a simulated sun light source, and the ground test equipment receives test instructions, drives the two-degree-of-freedom rotation mechanism fixed on the support structure to change the irradiation angle, adjusts the relative position relationship between the optical system and the digital sun sensor, and broadcasts the corner data to the test network. The test personnel compare the corner data of the rotation mechanism received by the test network with the telemetry data of the digital sun sensor to determine the correctness of the polarity of the digital sun sensor, realizing the automatic test of the polarity of the small satellite digital sun sensor.

The invention discloses a digital sun sensor based on a linear array CCD (Charge Coupled Device), belongs to the technical field of sun tracking sensors, and aims to solve the problems of high hardware development difficulty, high hardware cost and high power consumption in the prior art. The device comprises an integral shell, and a protection window, a double-rectangular-opening diaphragm sheet, a neutral attenuation sheet, a linear array CCD module, a rotating motor and a main control board which are arranged in the integral shell, the main control board controls the rotating motor to drive the double-rectangular-opening diaphragm piece, the neutral attenuation piece and the linear array CCD module to rotate integrally. The linear array CCD module is electrically connected with the main control board; the double-rectangular-opening diaphragm is provided with two long-strip-shaped rectangular openings, and the long sides of the rectangular openings are perpendicular to the length direction of the linear array CCD module all the time. Sunlight is imaged on the linear array CCD module after sequentially passing through the protection window, the neutral attenuation sheet and the double-rectangular-opening diaphragm, and the main control board calculates the azimuth angle and the elevation angle of the sun according to the centers of images formed on the linear array CCD module at at least two different angles.

The invention discloses a field-of-view expansion type sun sensor based on diffraction order multiplexing, which comprises a dual-band band-pass optical filter, a diffraction type light introducer and a color CMOS (Complementary Metal Oxide Semiconductor) image sensor, and is characterized in that the dual-band band-pass optical filter is used for selecting two pieces of separated sunlight with a preset wave band for incidence; the diffractive light introducer diffracts transmitted sunlight into multi-level light beams; the color CMOS image sensor is used for acquiring a diffraction spot image containing spectral information of two wave bands; the current effective diffraction order can be determined through the mass center positions of the light spots in the two corresponding wave band channels and the mapping relation between the light spot distance and the diffraction order, and finally the sun vector is obtained through calculation in combination with a diffraction optical model. According to the invention, the inherent contradiction that a large view field and high precision of a traditional digital sun sensor cannot be considered is solved, the problem of level ambiguity in a diffraction extended view field is effectively overcome, the lightweight design of the sun sensor adapts to the high-density integration requirement, and technical support is provided for spacecraft attitude measurement.

The invention relates to a solar-panelled wind turbine (100) which combines wind and solar energy, which are renewable energy sources, in a single body instead of using them separately, and wherein the data from the sun sensor (191 ), wind direction sensor (192) and wind speed sensor (193) thereon is interpreted by means of an electronic control unit (182) (ECU) containing an artificial intelligence software, and after this interpretation, the most appropriate direction for the support system (140) and solar-panelled blades (110) is selected and electrical energy generation from both the sun and the wind is achieved.

The utility model relates to an environment-friendly energy-saving display lamp box which is characterized in that a display box electrically connected with a storage battery is embedded in the middle area of a cabinet body, two arc-shaped sliding rails which are concentric and oppositely distributed are fixed above a supporting plate, and a sliding block is arranged on each arc-shaped sliding rail in a sliding mode; a solar panel which is obliquely distributed and electrically connected with the storage battery is arranged above the two arc-shaped sliding rails, two stand columns below the solar panel are fixedly connected with the two sliding blocks correspondingly, and a power mechanism used for driving the solar panel to rotate is fixed to the position, at the circle centers of the arc-shaped sliding rails, of the supporting plate. A sun sensor electrically connected with the controller is fixed to the light facing side of the solar panel, and the power mechanism is electrically connected with the controller. The beneficial effects are that the solar sensor can detect the direction of sunlight and send a detection signal to the controller, the controller then sends an action instruction to the power mechanism, and the power mechanism controls the solar panel to rotate along with the sunlight so as to efficiently utilize the sunlight to enter and exit for charging and energy storage.

An auxiliary device for holding a bottle, comprising: i) a circular ring frame 101 designed to be positioned on the neck of a bottle, wherein an artificial intelligence-based imaging unit 102 is integrated into the frame 101 and paired with a processor to capture and process multiple images near the frame 101 and to determine the dimensions of the bottle neck; ii) a motorized iris diaphragm 201, which is integrated into the inner circumference of the frame 101 and is actuated by a built-in microcontroller to be closed / opened according to the determined dimensions of the neck in order to enclose the neck, wherein several suction units are arranged with the diaphragm 201 to adhere to the surface of the enclosed neck in a secure manner; iii) a solar sensor embedded in the frame 101 to detect the intensity of the sunlight reflected onto the bottle, wherein a vertical plate 103 is arranged on the outer circumference of the frame 101 by means of a motorized circular slide actuated by the microcontroller to move the plate 103 in order to align the plate 103 in the direction of the detected intensity in order to prevent heating of the liquid in the bottle; and iv) a motorized roller 104 wrapped with a belt and arranged on the outer circumference of the frame 101, the belt extending towards the opposite end of the frame 101 to allow a user access to the belt for carrying the secured bottle, wherein, if the user wishes to adjust the length of the belt, voice commands must be given to a microphone 105 integrated into the frame 101, followed by actuation of the roller 104 to unwind / rewind the belt according to the length specified by the user, thereby assisting the user in holding the bottle.

The application discloses a satellite solar cell array rotation angle estimation method, which comprises the following steps: step 1, establishing an earth inertial coordinate system, a satellite body coordinate system and a solar cell array coordinate system, and defining a satellite solar cell array rotation angle; step 2, establishing a state equation of an augmented state composed of a sun vector, the solar cell array rotation angle and a gyro constant drift noise; step 3, calculating an augmented state quantity estimation value by using an extended Kalman filter; and step 4, calculating a satellite solar cell array rotation angle estimation value. The method fuses gyro angular velocity and sun sensor vector data, constructs a nonlinear dynamic model containing a sun vector, a rotation angle and a gyro bias, and designs an EKF algorithm to estimate the solar cell array rotation angle in real time, thereby solving the strong dependence of a traditional scheme on a star sensor and a mechanical sensor, and significantly improving the autonomous recovery capability and energy guarantee reliability of a satellite in an extreme fault scene.

The invention relates to the field of bionic polarized light navigation, and provides a polarized light compass and sun sensor tight combination global autonomous positioning method and device.Firstly, original data output by a sun sensor are processed to calculate a sun direction vector; then, fusing the solar altitude information into the optimization process of the polarization E vector, thereby improving the estimation precision of the polarized light compass on the solar azimuth angle; and finally, calculating the longitude and latitude positions of the carrier by adopting a navigation triangulation method in combination with the solar azimuth angle and elevation angle information obtained in the previous step and course data provided externally. According to the invention, a tightly combined global positioning model of the polarized light compass and the sun sensor is constructed, the error problem of the polarized light compass in estimating the solar elevation angle is overcome, the estimation precision of the solar azimuth angle is obviously improved, efficient fusion of polarized light information and sun position information is realized, and the method is suitable for popularization and application. An effective solution is provided for global approximate positioning under the condition that satellite signals are limited.

The utility model discloses a high slope construction process real-time monitoring device and a mounting support, and relates to the technical field of monitoring device supporting, the high slope construction process real-time monitoring device comprises a mounting plate, two electric push rods, a GNSS receiver, a sun sensor, a GNSS antenna and a solar panel, the mounting plate is rotatably connected with a first supporting rod, the first supporting rod is provided with a servo electric cylinder, and the servo electric cylinder is connected with a second supporting rod. The output end of the servo electric cylinder is connected with a first supporting rod, the output end of the servo electric cylinder is connected with a second supporting rod, a tilt angle sensor is installed in the first supporting rod, the solar panel is connected with the second supporting rod through a rotating assembly, and the GNSS receiver, the sun sensor and the GNSS antenna are all installed at the end, away from the servo electric cylinder, of the second supporting rod; through the combined design of the servo electric cylinder, the electric push rod and the tilt angle sensor, the convenience and accuracy of height and angle adjustment of the mounting bracket are remarkably improved, and through integration of multiple functional structures, the energy supply stability and the operation reliability of equipment are improved.

The invention relates to the technical field of spaceflight, and discloses an astronomical compass attitude drift correction method, device and equipment and a medium, the method comprises the following steps: determining a first measurement error corresponding to an accelerometer in an astronomical compass and a second measurement error corresponding to a sun sensor; determining an initial weight according to the first measurement error and the second measurement error; obtaining observation data of the astronomical compass in a preset time period; determining the attitude drift distance of the astronomical compass according to the initial weight and the observation data; determining whether the attitude drift amount meets a preset correction condition; if the attitude drift amount does not meet the preset correction condition, adjusting the initial weight to obtain an adjusted weight; and recalculating the attitude drift distance based on the adjusted weight until the recalculated attitude drift distance meets a preset correction condition. The correction precision of the astronomical compass can be improved.

The invention discloses a PSD-based high-precision sun sensor system design and calibration method, which combines the performance of a PSD detector and the application scene of a sun sensor, analyzes matters needing attention in the design process of the PSD sun sensor, and provides an innovative method suitable for effective trepanning of a light shield of the PSD detector. And the influence of the saturation current of the PSD detector on the output solar incident angle is effectively solved. Meanwhile, errors existing in the PSD sun sensor are analyzed, a novel high-precision sun component angle calibration scheme is provided, angle calibration of the sun sensor is achieved by combining a curve fitting algorithm and a curved surface fitting algorithm, and the method can be completed only through a small amount of calculation in sun sensor hardware and is easy to achieve. Finally, the PSD sun sensor designed by the invention has the advantages of low energy consumption, fast response, low cost, small volume, strong radiation resistance and the like in the aspect of precision improvement.

This invention discloses a large field-of-view, high-precision sun sensor based on a polarization-multiplexed metasurface array. It includes a CMOS image sensor and a metasurface array serving as a light introducer. The metasurface array achieves field-of-view multiplexing through multiple superimposed metalens units with different deflection phases. Simultaneously, using polarization multiplexing technology, each metalens unit forms a pair of spaced dual-spots on the CMOS image sensor as a line-of-view encoding. By calculating the spacing between these dual-spots, each sub-field of view can be unambiguously identified and the global field of view synthesized, thus resolving the inherent contradiction between large field of view and high precision in traditional digital sun sensors. This invention combines the advantages of a large field of view and high precision, and its lightweight design adapts to high-density integration requirements, providing technical support for spacecraft attitude measurement.

A buoyancy control system, GPS sensor and data analysis engine, a wind direction sensor, and a controller to detect significant wind direction changes. Upon calculation that the desired location within the eye wall has been reached the buoy descends to depths where ocean currents are reduced, preventing drift from the hurricane eye. A solar sensor triggers ascent when sunlight indicates reentry into the eye.

The invention discloses a satellite solar cell array rotation angle estimation method, which comprises the following steps of: 1, establishing an earth inertial coordinate system, a satellite body coordinate system and a solar cell array coordinate system, and defining a satellite solar cell array rotation angle; step 2, establishing a state equation of an augmented state composed of a sun vector, a solar cell array rotation angle and gyro normal drift noise; step 3, calculating an augmented state quantity estimated value by using extended Kalman filtering; and 4, calculating a rotation angle estimation value of the satellite solar cell array. According to the method, the angular velocity of the gyroscope and vector data of the sun sensor are fused, a nonlinear dynamic model containing the sun vector, the rotating angle and the gyroscope bias is constructed, the EKF algorithm is designed to estimate the rotating angle of the solar cell array in real time, the problem that a traditional scheme is highly dependent on a star sensor and a mechanical sensor is solved, and the reliability of the system is improved. And the autonomous recovery capability and the energy guarantee reliability of the satellite in an extreme fault scene are obviously improved.

A water distribution device for a canal, consisting of: i) an inverted U-shaped element 101 with anchor plates 102 at the lower ends of the element 101 for attachment to a bottom surface of the channel to provide primary support; ii) a frame 103 comprising a pair of circular rings 104 arranged on a motorized shaft 105 mounted inside the frame 103, a plurality of hollow cylindrical buckets 106 attached to rods by hinges 107 to an outer circumference of the frame 103 for taking water from the canal in order to transfer the water to a reservoir outside the canal; iii) an artificial intelligence-based imaging unit 108, installed on the element 101 and integrated with a processor for recording and processing images near the element 101, to identify dirt or fish in the water collected in the bucket, to trigger a microcontroller to actuate an L-shaped telescopic arm 109 with a clamp at one end of the arm 109, which is attached to the frame 103 by a ball joint 110 next to each bucket for removing dirt or fish from the water collected; and iv) a solar panel 111 arranged at an upper end of the element 101 by means of a swivel joint 112 to harvest solar energy from sunlight to drive the motorized shaft 105, the hinges 107, the ball joint 110, the arm 109 and the clamp, wherein a sun sensor is provided on the element 101 to detect a position of the sun in order to trigger the microcontroller to actuate the swivel joint 112 to rotate the panel 111 so that it faces the sun.

The application discloses a method for controlling the sun relative to a sailboard driven by an analog sun sensor, which comprises the following steps: determining the position of the sun relative to the satellite body; calculating the two-dimensional angle of the satellite attitude control according to the position of the sun relative to the satellite body; realizing the sun control of the predetermined axis of the satellite by the flywheel control according to the two-dimensional angle; determining the deviation angle Δθ between the current state of the sailboard and the ideal angle; and driving the sailboard to rotate by using the hysteresis control logic and the relationship between the sailboard driving and the deviation angle Δθ based on the deviation angle Δθ. The application can ensure that the illumination condition of the sailboard is maintained all the time after the sun appears relative to the analog sun sensor.

A nano APS sun sensor, comprising: a light introducer, an SOC processing board, a main body structure and a reference mirror; wherein, the light introducer, the SOC processing board and the reference mirror are installed on the main body structure; the reference mirror is used to represent the body coordinate system of the nano APS sun sensor; the light introducer uses a cross slit to realize the attenuation of the sunlight intensity and the introduction of the sun rays, and the SOC processing board realizes image acquisition and image processing and outputs the sun azimuth information through an interface.

A self-charging electric vehicle configured for converting solar energy and wind energy into electrical energy comprising a systems and methods. The vehicle includes a body and frame with a central body structure and centerline cabin and a chassis with a centerline battery compartment and a suspension system. Solar cells mounted to the vehicles top sides can be supplemented with extendable solar panel(s) that can be deployed by a control system to generate solar energy into electrical energy. An omnidirectional sun sensor provides for sun strength, angle and direction. A stowable horizontal-axis wind turbine with an extendable mast mounted to the vehicle that can be deployed by a control system to generate wind energy into electrical energy. A stowable anemometer provides for wind speed and wind direction.

The utility model relates to the technical field of solar cell panel adjustment, in particular to an aluminum alloy solar automatic adjusting device which comprises a supporting rod, an installation frame is installed on one side of the bottom face of the supporting rod, a storage battery and a processing module are installed in the installation frame, and a horizontal supporting frame capable of horizontally rotating is installed at one end of the supporting rod. And a guide rail is mounted on one side of the top surface. Compared with the prior art, the device has the advantages that the device can be conveniently installed on an external electric pole by arranging the supporting frame and the two fixing rings, the processing module is electrically connected with the sun sensor, the first driving motor and the second driving motor, the sun sensor can conveniently sense the sun, and the device is convenient to use. A control signal is sent to the processing module, the first driving motor and the second driving motor are controlled to be powered on and run through processing of the single-chip microcomputer, the direction and the pitching angle of the cell panel body are automatically controlled, the overall structure is simple, design is reasonable, and the use requirement is met.

The invention provides a universal satellite attitude and orbit control test system self-checking device and an implementation method thereof. Comprising the steps of isolation measuring point resistance value detection, flywheel signal simulation, electromagnetic valve detection, magnetic torquer current signal simulation, sun sensor unipolar constant current source acquisition, magnetometer signal acquisition, watchdog reset and star sensor enable signal acquisition, serial port communication detection and electric star mode communication detection. The satellite-borne software communication detection and electromagnetic valve self-locking valve resistance value detection module realizes simulation of performance indexes required by testing of satellite attitude and orbit control satellite-borne products such as a flywheel, a sun sensor, a fixed star sensor, a propulsion electromagnetic valve self-locking valve, a magnetic torquer and a magnetometer. And the attitude and orbit control self-checking device is connected with the attitude and orbit control ground test system cabinet through a standardized connector and a matched cable.

The invention discloses a wind power generation and solar power generation combined system, which comprises a solar photovoltaic array, a wind power generator, a controller A, a master controller, a display screen and a power grid, and is characterized in that the solar photovoltaic array comprises a solar sensor, an orientation adjusting mechanism A, an angle adjusting mechanism, a plurality of photovoltaic panels and a combiner box A; the multiple photovoltaic panels are all connected with the orientation adjusting mechanism A and the angle adjusting mechanism, the sun sensor, the orientation adjusting mechanism A and the angle adjusting mechanism are all electrically connected with the controller A, and the sun sensor is used for monitoring the orientation angle and the inclination angle of the sun. According to the invention, through a mode of combining wind energy and light energy for power generation, the power generation efficiency is improved, and the angle of the photovoltaic panel and the angle of the wind driven generator module can be adjusted according to the angle of sunlight and the wind direction, so that the photovoltaic panel and the wind driven generator module can be continuously irradiated by the sunlight and blown by wind respectively, and the power generation efficiency is improved.

The invention provides a calibration method and system of a sun sensor, electronic equipment and a storage medium. The calibration method comprises the following steps: determining a target installation matrix of the sun sensor on three-axis turntable equipment; determining an initial rotation angle of three axes of the three-axis turntable equipment and a conversion relation between the initial rotation angle and the attitude matrix; after the user adjusts the rotation angles of at least two axes in the three axes according to the preset value every time, an imaging image corresponding to the current rotation angle of the sun sensor and the three axes is obtained; preprocessing each frame of imaging image to obtain a target measurement value set corresponding to each aperture; determining a first target parameter value of the first target aperture according to the target installation matrix, the conversion relation and the target measurement value set; performing optimization solution based on the first target parameter value and a first preset linear equation to obtain a scale factor; determining a second target parameter value of a second target aperture according to the scale factor and a second preset linear equation, wherein the second target aperture is all apertures except the first target aperture in the plurality of apertures; and determining a target calibration parameter of the sun sensor according to the first target parameter value of the first target aperture and the second target parameter value of the second target aperture.

The invention is suitable for the technical field of optical imaging, and provides an all-day space optical sensor optical system, which comprises a configuration I and a configuration II, the configuration I is a sun sensor mode, the configuration II is a star sensor mode, and the configuration I and the configuration II share a common optical path correction lens group. Through an integrated optical structure design, synchronous detection of the sun sensor and the star sensor is realized, an all-day, high-precision and low-power-consumption composite optical navigation mechanism is constructed, and a compact optical lens is also provided. Multi-recombination state optimization is adopted, a weighting function is set for a sun sensor and a star sensor, energy concentration ratio and optical distortion are dynamically balanced, innovative modular combination of refraction and reflection optical elements is utilized, and high-precision synchronous detection is carried out on the sun and a fixed star target through an integrated light path at the same moment. In addition, a serial working mode is optimized into a parallel mode, and high-precision measurement and quick response of the attitude of the spacecraft are realized according to the relative position of the sun and the fixed star.

The invention provides an inertial navigation positioning method and system based on sun vector assistance, electronic equipment, a storage medium and a computer program product. The navigation and positioning method comprises the following steps: acquiring a first sun vector and a position matrix at the current moment under an inertial coordinate system, and a second sun vector, an installation matrix and an attitude matrix obtained by observing the sun through a sun sensor; determining a sun vector measurement model about an inertial navigation position error, an inertial navigation attitude error and a sun sensor installation error; determining a height measurement model about an inertial navigation height error based on measured height information in the initial position information and standard height information obtained based on an altimeter; constructing a target measurement model according to the sun vector measurement model and the height measurement model in combination with a preset state variable; and estimating an inertial navigation position error, an inertial navigation attitude error and a sun sensor installation error according to the target measurement model.

Method for processing measured values ​​from a sun sensor (1) of a motor vehicle (12) comprising at least one partial sensor, wherein the sun sensor (1) measures the intensity of incident light radiation as measured values, wherein a current geodetic position and orientation of the motor vehicle (12) is determined, and in conjunction with current time information, in particular a current date and time, sun position information (4) describing the position of the sun relative to the motor vehicle (12) is determined, characterized in that the sun sensor (1) has a sensor characteristic (2) which assigns a sensitivity of the sun sensor (1) to each pair of elevation angle and azimuth angle of the sun in relation to the sun sensor (1), in particular for each partial sensor.wherein a current elevation angle and azimuth angle of the sun relative to the sun sensor (1) are determined from the sun position information (4) and the corresponding current sensitivity is determined from the sensor characteristic (2) and used for the correction of the measured values ​​of the sun sensor (1), in particular for sub-sensors, wherein the correction as a correction step (5) comprises a multiplication of the inverse of the sensitivity with a measured value to determine a corrected value, wherein as part of the sun position information (4) a maximum measurable solar power value on Earth is also determined from the time information and / or the current geodetic information and / or the sun position and the corrected value is compared with the solar power value in a diffusivity check.