31results about How to "Improve autonomous operation ability" patented technology

The present invention discloses a sky-base mobile communication wireless resource management system. The system comprises a ground control center, which assigns the wireless resource for each satellite according to the operation status of the satellite communication system, a plurality of gateway stations, which are connected with the ground control center to manage the wireless resource of the satellite in the area covered by the gateway signal and control the satellite to assign wireless resource, and a plurality of satellites, which manage and assign the wireless resource related to the satellite according to the control signal of the gateway station and the ground control center. The present invention simplifies the control function of the ground, decreases the ground control dependence of the satellite mobile communication system and improves the anti-ruin ability of the system. Different management strategies can be conveniently implemented in different regions, thus the flexibility of the system operating is improved.

The invention discloses a single satellite autonomous orbit measuring method adopting on-satellite push-broom remote sensing image information. The method includes the following steps that S1, the push-broom remote sensing image information is preprocessed, and multiple mark points, used for autonomous orbit measuring, in a push-broom remote sensing image are obtained; S2, an orbit measuring system model based on the multiple mark points of the remote sensing image is established according to the mark points, used for autonomous orbit measuring, in the push-broom remote sensing image; S3, a preset solving algorithm is adopted for solving orbit information of the orbit measuring system model, after multiple pieces of position information of a satellite on an orbit are obtained, satellite orbit parameters are fit through multipoint orbit position information, and single satellite autonomous orbit measuring is completed. The satellite orbit information is reversed through ground high-precision mark point information, and the autonomy and reliability of remote sensing satellite orbit measuring are remarkably improved.

The invention discloses a geosynchronous orbit constellation orbit determination method based on ground station / satellite link / GNSS combined measurement. The method comprises the steps of (1) establishing the state equation of a GSO constellation orbit determination system in a centralized structure, (2) establishing the measurement equation of the GSO constellation orbit determination system in a centralized structure, (3) carrying out combined optimization of a ground station for orbit determination and GNSS measurement combination, (4) determining the filtering method for realizing orbit parameter estimation according to the above established GSO constellation combined orbit determination system model based on ground station / satellite link / GNSS, and (5) carrying out the concrete realization of a GSO constellation orbit determination method based on ground station / satellite link / GNSS in the centralized structure. According to the method, the combined distribution optimization strategy of ground station and GNSS measurement is established based on a precision factor, and the calculation amount is reduced while the orbit determination precision is ensured.

A micro-satellite independent request orbit service system, which includes a ground measurement and control system, on-board management and control application software, and satellite-ground data interaction interface; the ground measurement and control system, including a measurement and control center and a measurement and control station, is used for remote control command injection and telemetry data reception processing and precise orbit determination; the spaceborne management and control application software includes an autonomous orbit determination module, a high-precision orbit forecast module, and a task scheduling management module; the satellite-ground data interaction interface is used to realize the format agreement of the satellite-ground uplink data and downlink data. The purpose of the present invention is to provide a micro-satellite autonomous control technology that can maintain orbit prediction results equivalent to the accuracy of orbit calculations on the ground on the satellite, so as to solve the problem that the existing technology can only meet the requirements of satellites in general micro-satellite orbit prediction tasks. The medium precision requirements of the position are difficult to meet the technical problems of high precision requirements for satellite payload applications such as autonomous mission planning.

The invention relates to a navigation anti-interference enhancement load system and method based on a low-orbit satellite. The system comprises a GNSS signal receiving antenna, a GNSS signal down-conversion module, a baseband processing module, a navigation anti-interference signal upper side frequency module, a power amplifier module, a navigation anti-interference signal broadcast antenna, a frequency synthesizer and a constant temperature crystal oscillator. Through a navigation anti-interference signal broadcasted by a navigation anti-interference enhancement load, sensitivity and an anti-interference ability of a ground navigation receiver are increased, and availability of a ground satellite navigation receiver in a complex environment is solved.

The invention discloses an initial synchronization method for multiple hot backup computers. The initial synchronization method comprises the steps that each hot backup computer receives the same externally-inputted synchronous clock signal; each hot backup computer finishes the initialization work and then transmits information A to other units, wherein the contents of the information A are that a local computer has synchronous working conditions; a certain hot backup computer receives the information A transmitted by all other hot backup computers and transmits information B to other hot backup computers, wherein the contents of the information B are that when a rising edge of next synchronous clock signal comes in, the current hot backup computer starts to work; after a certain computer receives the information B, the certain computer transmits the information B to other computers; if a certain hot backup computer does not receive the information A transmitted by other computers within continuous N (N is a preset value) synchronous clock cycles, the certain hot backup computer transmits the information B to the other computers. According to the initial synchronization method disclosed by the invention, initial synchronization of the multiple hot backup computers can be realized, and the reliability and the independent operation ability of the hot backup computer are improved.

The present invention is an electric propulsion position maintenance method based on star time drive, which preprocesses the electric propulsion ignition task parameters, and divides them into strategy parameters and attribute parameters according to whether the parameters change according to the characteristics of the task; through star time drive, the parameters are sequentially chronologically Carry out the initialization work before the ignition of each rail of the electric thruster, the steering adjustment of the vector adjustment mechanism, the parameter configuration of the electric thruster, and the processing of the starting arc. The invention realizes the electric propulsion multi-orbit and multi-arc automatic ignition task, improves the satellite's autonomous operation capability, the number of ignition orbits and the number of arcs can be flexibly configured on the ground, and has better flexibility and scalability.