8 results about "Satellite attitude control system" patented technology

This invention provides a novel integrated attitude sensor for satellites, relating to the fields of onboard attitude control and electronics. It includes: a star sensor body; a solar sensor body mounted on the star sensor body; a magnetometer body within the star sensor body; and a gyroscope body within the star sensor body. By integrating traditional discrete structures into a single device, the size and weight are reduced, and costs are significantly lowered. Magnetometer and gyroscope data are fused in real-time within an FPGA. This device features rapid adaptability, modular design supporting plug-and-play functionality, and integrated design improving EMC performance. It solves the problems of existing traditional satellite attitude control systems, where various attitude sensors are independently configured and equipped with dedicated processors, resulting in high hardware redundancy, large overall size and weight, high power consumption and cost, hindering further improvements in attitude measurement accuracy and dynamic performance, and leading to high overall design complexity.

The present disclosure provides a satellite attitude control system fault diagnosis method and device based on time-frequency domain feature fusion, belonging to the technical field of satellite fault diagnosis. The method can include: obtaining target satellite data and converting the target satellite data into satellite image data using a Gram angle field; performing feature extraction on the satellite image data to obtain a satellite feature image; extracting global time sequence features of the satellite feature image, wherein the global time sequence features refer to image sequence features extracted from the entire time sequence of the satellite and capable of representing the characteristics of the entire sequence; inputting the global time sequence features into a dense connection model to obtain a fusion time sequence feature map corresponding to the satellite feature image; and obtaining a target fault type corresponding to the target satellite data according to the fusion time sequence feature map. This technical solution can improve the efficiency and accuracy of satellite fault diagnosis.

The application discloses a satellite attitude control system event-triggered STF fault detection method, and belongs to the technical field of detection, which comprises the following steps: establishing a fault model of a satellite attitude control system; introducing an event-triggered mechanism; adopting an STF method to design an event-triggered fault detection filter; obtaining an estimation error dynamic equation and a residual signal through linearization processing of the fault detection filter, realizing complete decoupling of the residual signal and the event-triggered error; converting a design problem of a residual generator into solving a gain matrix of the fault detection filter; calculating a residual evaluation function and comparing the residual evaluation function with a threshold value to judge whether a fault occurs or not. The application utilizes the STF method to design the fault detection filter, can enable the system to keep the tracking ability to a sudden state when reaching a stable state, adopts a brand-new event-triggered framework, realizes complete decoupling of the residual signal and the event-triggered error, and effectively improves the resource utilization rate under the premise of guaranteeing the system performance.

The invention discloses a dual-redundancy commutation control method of a reaction flywheel and a control system of a reaction flywheel system, relates to the field of aviation, effectively overcomes the technical bottleneck of'failure of a Hall element, namely downtime 'in an existing flywheel system, and does not need to add hardware modification and test. And dual-redundancy commutation control of the Hall sensor and the incremental encoder can be realized only through calibration of software. If the Hall sensor operates normally, the reaction flywheel is controlled according to the commutation logic of the Hall sensor; if the Hall sensor fails, whether the reaction flywheel is restarted or not is further judged, and if the reaction flywheel is not restarted, the reaction flywheel is controlled according to phase change logic of an incremental encoder; and if restarting, executing the zero-searching operation until the zero-searching is finished, quitting the zero-searching operation, and controlling the reaction flywheel according to the commutation logic of the incremental encoder. The method is suitable for processing the reaction flywheel of the core execution mechanism of the satellite attitude control system.

This invention discloses a hybrid control configuration method for highly maneuverable micro-nano satellites, which uses three reaction flywheels and a pair of control moment gyroscopes as a hybrid control mechanism. This allows the control moment gyroscopes to exert high maneuverability on a single axis while also serving as backup for the three reaction wheels, thereby improving the reliability of the satellite attitude control system.

The invention belongs to the technical field of satellite structure dynamics and vibration measurement, and aims to provide an in-orbit solar wing low-frequency vibration frequency measurement device and measurement method based on video feature point tracking so as to solve the problem of coupling of the low-frequency vibration frequency of a solar wing and the frequency of a satellite attitude control system when a satellite is in orbit. The measuring device comprises a reaction flywheel used for applying vibration excitation to the solar wing, a reflective target installed at the free end of the solar wing, a solar wing monitoring camera used for shooting, a near-infrared light source and a comprehensive electronic system used for data processing. The measuring method comprises the following steps: estimating the amplitude of the solar wing through kinetic analysis, and designing measuring device parameters; afterwards, a flywheel is utilized to excite the solar wing to vibrate in orbit, and a target motion video is shot through a camera; vibration signals are extracted through image processing, and finally the modal frequency is recognized through frequency domain analysis. According to the invention, non-contact accurate measurement of low-frequency vibration of an in-orbit solar wing is realized, and a key basis is provided for formulating a satellite attitude control strategy.

The present application relates to a kind of flexible solar wing for sun synchronous orbit satellite constellation and on-orbit control method, solar wing is flexible stacked structure, stack on satellite body in retracted state, solar wing includes oppositely arranged single wing, the single wing includes: substrate assembly, it is configured to carry out photoelectric conversion, the substrate assembly includes: rigid substrate and several flexible substrates;Unfolding mechanism, it is configured to provide unfolding stiffness for solar wing, to ensure that the flexible substrate keeps planar form;And unfolding motor, it is configured to drive the unfolding mechanism unfolding or folding, to realize the retraction or unfolding of solar wing;First solar wing driving mechanism and lifting mechanism are provided between oppositely arranged single wing.The present application is overall used flexible stacked structure form retraction envelope size small, light in weight, does not need additional use satellite attitude control system to carry out attitude adjustment and realizes sun tracking.

The application provides a short-wave satellite attitude control system and relates to the technical field of data processing, and comprises the following steps: inputting a three-axis combined control torque instruction into a reaction flywheel controller, converting the three-axis combined control torque instruction into a flywheel motor speed regulation instruction and driving the reaction flywheel to execute; based on actual attitude changes after driving the reaction flywheel to execute, adjusting and analyzing a continuously updated attitude deviation angle to obtain updated sliding mode controller gain parameters and feeding back the parameters of the updated sliding mode controller; based on the parameters of the updated sliding mode controller, controlling, verifying the direction consistency of newly output sun direction vector measurement values, and verifying the actual included angle; if the actual included angle is less than a preset precision threshold, triggering a new round of data acquisition cycle to realize closed-loop control. The application guarantees the timeliness and effectiveness of attitude control and improves the efficiency and reliability of control.