47 results about "Ground system" patented technology

The invention relates to the technical field of satellite attitude control, in particular to a satellite-borne laser semi-autonomous pointing control method, electronic equipment and a storage medium. The method is completed by cooperation of a ground system and an on-satellite system, the ground system calculates a top target passing moment T * in advance, generates a unified laser pointing control instruction and injects the instruction into a satellite; and the satellite-borne system receives and analyzes the instruction, obtains parameters such as T * and beam selection, and then autonomously controls a specified load for work preparation. And the satellite-borne system autonomously calculates the optimal moment T1 and the target attitude when passing through the calibration field through high-precision orbit extrapolation based on the latest navigation data, finally autonomously executes attitude maneuver and laser pointing tasks, and autonomously returns after the tasks are completed. Instructions in a uniform format are generated and injected from the ground, ground operation is greatly simplified, efficient cooperation of ground decision triggering and on-satellite autonomous execution is achieved, pointing errors caused by orbit extrapolation are greatly reduced, the pointing precision and the task success rate are improved, and universality is good.

The invention discloses a seabed shallow casing section thermal insulation structure for polar region supercritical carbon dioxide drilling, which comprises a casing, a thermal insulation coating, a protective coating, an annular cement slurry layer, an electric heating pipe, a sensor module, a wireless conductive module, a ground system and a seabed wireless transmission module, and is characterized in that the electric heating pipe is fixed on the outer wall of the casing through a hoop; the outer wall of the casing pipe is sequentially coated with a heat preservation coating, a protective coating and an annular cement paste layer from inside to outside, the wireless conductive module is integrated at the end of the casing pipe, and the ground system comprises a ground data acquisition system and a ground control center. The sea surface platform is provided with a ground data acquisition system and a ground control center which are connected with the seabed wireless transmission module through an umbilical cable, and temperature and pressure data acquired by the sensor module are uploaded to the ground control center. According to the invention, the problems of rapid heat loss, annular air channeling, casing mechanical property degradation, poor drilling fluid fluidity and the like of the seabed shallow casing section in the polar region extreme low-temperature environment are solved.

Methods, systems, and apparatus, including computer programs encoded on computer-storage media, for ground system techniques to support flexible reconfigurable satellite payload operation. In some implementations, a satellite communication network is managed to operate in a first configuration. The satellite communication network includes a satellite having a payload that enables dynamic reconfiguration of carriers within a beam. A reconfiguration event is detected, and in response, a second configuration is determined for the satellite communication network. The second configuration differs from the first configuration in at least one of a set of carriers used for the beams or an assignment of the carriers to gateways. The satellite network is managed to operate in the second configuration, including at least one of (i) changing to a second set of carriers for the beams of the satellite or (ii) changing to a second assignment of the carriers to the gateways.

There is provided an artificial satellite and a ground system enabling to efficiently hold data in the artificial satellite. The artificial satellite includes an image processing unit that executes feature amount generation processing of generating a feature amount of a captured satellite image, a storage unit that holds feature amount data obtained as a result of the feature amount generation processing, and a communication unit that transmits the feature amount data to a ground station when communication with the ground station becomes possible. The ground system includes an image processing unit configured to generate complemented data by using complementing data and feature amount data that indicates a feature amount of a satellite image acquired from an artificial satellite and obtained by capturing an image of a ground by the artificial satellite.

This invention relates to the field of remote sensing satellite orbit control technology, and discloses a satellite autonomous pipeline control method based on differential interferometric SAR imaging missions. The method includes: acquiring initial satellite orbit parameters; employing a multi-objective optimization algorithm for orbit optimization under a high-order gravity field; sampling and constructing a reference orbit point set; calculating orbit control deviations based on the actual orbit and the reference orbit; generating orbit control triggering rules and avoidance strategies through ground system simulation; executing orbit control strategy generation and control onboard system; and evaluating orbit control effectiveness and the evolution trend of orbit control deviations through the ground system. Existing technologies mainly rely on ground command injection, making it difficult for satellites to achieve efficient autonomous orbit control when performing heavy-orbit differential interferometric SAR imaging missions, and hindering the decoupling of orbit control and imaging tasks. This invention improves the efficiency and autonomy of orbit control, the execution efficiency of imaging missions, and the safety of on-orbit operation by constructing a closed-loop control system encompassing satellite-ground collaboration, strategy formulation, command execution, and effect evaluation.

To achieve information on a mission device for executing mission other than communication via annular communication network in real time at low cost.SOLUTION: A hybrid constellation 20B formed in a Low Earth Orbit includes a communication constellation in which a plurality of satellites having a communication device communicating with precedent and following satellites in a travel direction on the same orbital plane form annular communication network 702, and a mission satellite 30b which has a communication device communicating with the precedent and following satellites, and a mission device for executing various missions. The mission satellite 30b flies between the plurality of satellites forming the communication constellation, the hybrid constellation 20b is formed by reconstruction of the annular communication network 702 using a plurality of satellites forming the communication constellation forming the annular communication network 702 and the mission satellite 30b.SELECTED DRAWING: Figure 17

This application belongs to the field of unmanned aerial vehicle (UAV) and data communication technology, and specifically relates to a UAV data transmission verification method based on the MD5 algorithm. The method involves extracting flight path data in a pre-defined order, calculating the MD5 "fingerprint" value of the flight path data, and transmitting the MD5 "fingerprint" value to the ground. The ground system calculates the MD5 "fingerprint" value of the ground flight path data in the same pre-defined order and compares it with the MD5 "fingerprint" value transmitted from the UAV. If the MD5 "fingerprint" values ​​match, the flight path stored by the UAV is correct and usable; if the MD5 "fingerprint" values ​​do not match, it indicates that the flight path stored by the UAV is incorrect and needs to be reloaded. The data is protected from interception and is not easily exposed: using the MD5 algorithm to verify the accuracy of flight path data does not require transmitting all flight path data, thus eliminating the risk of data interception. Furthermore, only one frame of data needs to be transmitted back, which significantly reduces the risk of exposure, especially for stealth aircraft.

This invention proposes a method for autonomous collaborative satellite selection for high-orbit tracking and guidance of moving targets, enabling the identification of low-Earth orbit (LEO) satellites. A high-orbit remote sensing satellite detects and tracks a moving target, autonomously detecting the target through onboard information processing and calculating its current position, velocity, direction, shortest side length, and corresponding time as guidance information for collaborative observation. The ground system pre-injects collaborative observation requirements and candidate LEO satellite information onto the high-orbit remote sensing satellite. Based on this candidate LEO satellite information, the high-orbit remote sensing satellite's own on-orbit operation status, and imaging performance parameters, it calculates and assesses the imaging and target recognition capabilities of all candidate LEO satellites when observing the moving target. The high-orbit remote sensing satellite then selects candidate satellites whose estimated imaging and target recognition capabilities meet the collaborative observation requirements, serving as the first round of candidate satellites for collaborative observation.

The invention discloses an anti-ground-touching method and an anti-ground-touching system for a working column, and relates to the technical field of working vehicle construction safety monitoring, the anti-ground-touching method for the working column comprises the steps that real-time monitoring data of a pressure sensor and a strain sensor are acquired, the pressure sensor and the strain sensor are arranged at the connecting position of the working column and a fixing frame, and the pressure sensor and the strain sensor are connected; the real-time monitoring data is used for representing the state of the workbar; comparing the real-time monitoring data with the initial data of the pressure sensor and the strain sensor; if the real-time monitoring data is greater than the initial data, representing that the workbar is in a bearing state, and controlling and keeping the operation state of the workbar; and if the real-time monitoring data is smaller than the initial data, representing that the workbar is in a state of touching the ground or encountering an obstacle, and controlling the operation state of the workbar to perform safety intervention. According to the working bar grounding prevention method, the working platform can be reliably prevented from grounding, the working safety is ensured, and the maintenance cost is reduced.

The invention provides a ground wire detection device and a ground wire detection method. The ground wire detection device comprises a power supply module, a measuring resistor, a regression wire and a control module, the positive electrode of the power module is electrically connected with the first end of the grounding wire and a first grounding system through the measuring resistor, the negative electrode of the power module is electrically connected with the first end of the return wire, and the second end of the return wire is electrically connected with the second end of the grounding wire and a second grounding system. The control module is used for detecting the line voltage between the first end of the grounding line and the first end of the regression line, and according to the line voltage, the power supply voltage between the positive electrode and the negative electrode of the power supply module, the measurement resistance value of the measurement resistor, the regression line resistance value of the regression line and the equivalent resistance value range between the first grounding system and the second grounding system. And obtaining the grounding wire resistance value range of the grounding wire. Current detection does not need to be carried out on the ground wire, and the reliability of the whole impedance detection is improved.

The invention provides a ground system suitable for a whole-process automatic test of a moonlet measurement and control subsystem, and the system comprises a measurement and control signal processing module which comprises an upper frequency conversion sub-module, an intermediate frequency modulation sub-module, an intermediate frequency demodulation sub-module, a lower frequency conversion sub-module, and a local oscillator sub-module; the channel adjusting module comprises an uplink programmable attenuator, a downlink programmable attenuator, a power divider, a combiner, a circulator, an uplink switch, a downlink switch and a coupling detector; the centralized management and control module is used for issuing working parameters of the measurement and control signal processing module and the channel adjustment module, collecting working states and splicing whole-process working nodes; the centralized management and control module comprises an upper computer sub-module and a centralized agent sub-module, the upper computer sub-module is used for configuring and displaying working parameters of the measurement and control signal processing module, establishing a measurement channel for a measurement and control system, resolving and counting data, and the centralized agent sub-module is used for managing each sub-module in the channel adjustment module.

This invention provides a comprehensive evaluation method for the mid-frequency performance of a filter field grounding system, belonging to the field of power grid equipment technology. The invention extracts the resonant frequency distribution by inputting a wideband impedance spectrum into an artificial intelligence frequency domain response identification model based on a coarse spatiotemporal attention mechanism. It then dynamically adjusts the spatial receptive field parameters according to the resonant frequency offset function. A three-dimensional electromagnetic field simulation model is established based on soil frequency domain parameters, and the ground potential and current density distribution are calculated using the radial basis function collocation method and the fast multipole algorithm. The entropy value of current distribution uniformity and the Gini coefficient are calculated to identify current concentration areas and assess local overheating risk. Finally, the analytic hierarchy process (AHP) is used to dynamically weight and comprehensively score indicators such as impedance peak value, resonant frequency, ground potential gradient, current uniformity, and overheating risk. This invention solves the technical problem of inaccurate performance evaluation of filter field grounding systems under mid-frequency impulse conditions.

The application discloses a low-orbit satellite communication system time difference estimation method based on burst time slot capture. In the low-orbit satellite communication system, the satellite and the ground are synchronized with the same time reference, but due to the influence of the low-orbit satellite-ground system time precision, the synchronization is not complete, and even after compensation, there is an unknown residual time difference. Therefore, the burst signal sent by the ground terminal in the low-orbit satellite communication system will be ahead of or lag behind the time slot, the demodulator on the low-orbit satellite accurately calculates the time difference value of the burst signal ahead of or lagging behind the current time slot by using the mathematical relationship between the time counting of each time slot and the capture of the burst signal, takes the time difference value as the time difference estimation value, packs the time difference value as part of the demodulation information, and uploads the time difference value to the upper layer of the satellite for distribution. On the basis of the pre-calculated time difference, the ground terminal repeatedly compensates and corrects the time difference estimation value distributed by the satellite, and the accuracy of the satellite-ground closed-loop time difference adjustment is improved.

This invention discloses a millimeter-level monitoring method and system for geological deformation in mining areas based on an integrated space-air-ground system, relating to the field of geological monitoring technology. The method includes: acquiring time-series synthetic aperture radar (SAR) images, GNSS observation data, and subsurface microseismic data; inverting the physical property parameters of the surface cover medium based on GNSS observation data, calculating the medium phase delay, and compensating for the original interferometric encapsulation phase to obtain the true geometric encapsulation phase; performing spatial clustering based on subsurface microseismic data to extract fault rupture surfaces and generate discontinuous masks, which are then superimposed onto the true geometric encapsulation phase to block cross-fault phase unwrapping paths, dividing the mining area into multiple topologically isolated blocks and performing independent phase unwrapping on each; acquiring the absolute deformation projection values ​​of GNSS stations within each block, combining the unwrapped phase to calculate the reference intercept, and reconstructing the continuous absolute deformation field of the mining area; this invention achieves high-precision monitoring of mining area deformation through medium phase compensation and fault topological constraints.

The application discloses a kind of high-low orbit satellite guidance observation-oriented mission planning methods, belong to the field of spaceflight ground system operation and control.The method is directed to high-orbit satellite guides low-orbit satellite observation scene and low-orbit satellite guides high-orbit satellite observation scene, using the chainable period of two satellites of high-low orbit, the observable period of low-orbit satellite to observation target and relevant parameters, mission planning is carried out, the observation period of high-orbit satellite is determined, and the satellite observation sequence combination of high-low orbit satellite guidance observation task is generated.The application can solve the planning problem of high-low orbit satellite mutual guidance observation, can generate the satellite observation sequence combination of actually usable high-low orbit satellite guidance observation task, improve the overall use efficiency of satellite.

A ground system for satellite-borne synthetic aperture radar external correction comprises an antenna housing which is integrally provided with a receiving antenna and a transmitting antenna; the first azimuth angle adjusting device is used for adjusting the azimuth angle of the antenna shell; the second height adjusting device is used for controlling the height of the antenna shell; a satellite orientation control unit that receives a position of a satellite from the satellite or a satellite regulation server and controls the first azimuth angle adjustment device and the second height adjustment device such that the receiver and the transmitter point to the received position of the satellite; the receiving antenna is used for receiving a synthetic aperture radar signal of a satellite; the amplifier is used for amplifying the satellite radar signal of the receiving antenna; and a transmitting antenna that transmits the satellite radar signal amplified by the amplifier toward a satellite.

This invention relates to the field of remote sensing data processing technology, specifically to a satellite-ground integrated distributed processing method for remote sensing constellation data, comprising the following steps: S1: acquiring raw remote sensing images in orbit; S2: performing data preprocessing on the raw remote sensing data, including radiometric calibration, sensor correction, and geometric coarse correction; S3: performing rapid region segmentation and ground feature classification and initial screening; S4: making task coordination and distribution decisions based on the confidence level C and type Type of each initially screened target; S5: data encapsulation and downlink, encapsulating the data to be transmitted back to the ground; S6: ground system reception, receiving the data packets transmitted from satellite; S7: the ground system distributes the data to the corresponding dedicated processing algorithm for final image interpretation and processing based on the data information. This invention creatively designs a "coarse screening-distribution" satellite-ground collaborative processing flow and a multi-level processing architecture of "main satellite distribution-constellation system-ground fine interpretation".

The application discloses a high-precision angle measurement method based on PNDOR beacon, which can effectively eliminate device group time delay error, improve time delay measurement precision, and improve ground system receiving efficiency; the existing DOR technology implementation steps are improved, a PNDOR beacon and a fast acquisition method thereof are designed, pseudo-code ranging and DOR angle measurement integration are realized; the application proposes that the PNDOR beacon utilizes the broadband characteristics of a signal to realize device group time delay calibration of the system, does not need to rely on external calibration signals, can adapt to slow changes of device time delay, and has higher calibration precision; in the application, a PNDOR signal acquisition method based on an FFT algorithm and an open-loop precise time delay measurement method are introduced, code correlation and carrier phase auxiliary technologies are utilized, and the time delay measurement precision is further improved.

This invention relates to the fields of satellite-to-ground communication and free-space optical communication technologies, and proposes a satellite-to-ground system based on seamless integration of multi-core optical fiber and free-space optical communication. The system includes a ground station and multiple satellite nodes. The ground station uses multi-core optical fiber as the internal concurrent channel backbone. Each fiber core is connected to a multi-channel optical transceiver front-end via a multi-core fan-out / fan-in coupling assembly, driving a multi-beam FSO optical terminal to form multiple spatially separated beams. Each FSO beam corresponds to one satellite node, enabling concurrent uplink from multiple satellites. The downlink process is reversed, with the ground station receiving FSO beams from multiple satellites in parallel and fan-into the multi-core optical fiber output. The proposed architecture ensures isolation of the multi-core concurrent channels through crosstalk suppression design and allows for optional configuration of reconfigurable optical interconnects to achieve channel-level reconfiguration, thereby reducing ground station cabling complexity and improving the integration and scalability of the multi-satellite concurrent link.

1. The name of the design product: satellite communication C-band down converter. 2. The use of the design product: used in satellite communication ground system, frequency conversion of C-BAND satellite signal. 3. The design points of the design product: in shape. 4. The picture or photo that best indicates the design points: perspective view 1.

Provided is a high-frequency module that supports a communication band of a ground system and a communication band of a non-ground system and that can be downsized. A high-frequency module (1) includes a switch (6), a first duplexer (11), and at least one or more second duplexers (12, 13) or at least one or more filters (14, 15). The first duplexer (11) is connected to the switch (6). The first duplexer (11) has a transmission filter (11T) and a reception filter (11R). The transmission filter (11T) has a passband that includes a transmission band of n255. The reception filter (11R) has a passband that includes a reception band of at least one of Band 75, Band 76, and Band 32 and a reception band of n255.

This invention relates to a ground flight control and operation support system for a very low Earth orbit (UEO) satellite constellation. It incorporates predicted space environment information, satellite attitude change information, and orbit control information into the high-precision satellite orbit prediction process, effectively ensuring higher orbit prediction accuracy for the UEO constellation and maximizing the assistance to ground control stations during satellite transits in capturing and tracking the satellite. The satellite attitude and orbit control system simulation module performs real-time simulations of the impact of attitude control and orbit control on orbital maneuvers, thereby achieving higher orbit control accuracy and providing better assurance for the precise execution of missions by the UEO constellation. Automatic scheduling of Earth remote sensing and data transmission tasks, along with ground system fault identification and handling, and collision warning, provide more intelligent support for the operation of the UEO constellation.

This invention discloses a multi-stage rocket timing test channel reuse system, relating to the field of aerospace systems technology. The system includes an onboard system and a ground system. The onboard system includes first- and second-stage onboard timing acquisition channel circuits and additional multi-stage onboard timing acquisition channel circuits. The ground system includes first- and second-stage time-series ground test channel circuits. The first- and second-stage onboard timing acquisition channel circuits of the onboard system are connected to the first- and second-stage time-series ground test channel circuits of the ground system via diodes one and two. The multi-stage onboard timing acquisition channel circuits of the onboard system are connected to the first- and second-stage time-series ground test channel circuits of the ground system via diodes three and four. This invention reuses the same timing acquisition channel for timing data from different stages and time periods to meet the testing requirements of rocket timing. By designing isolation circuits, different timing channels using the same test path are isolated, ensuring that each timing test process does not interfere with the others.

The invention discloses a high-precision angle measurement method based on a PNDOR beacon, which can effectively eliminate the time delay error of an equipment group, improve the time delay measurement precision and improve the receiving efficiency of a ground system. The implementation steps of the existing DOR technology are improved, a PNDOR beacon and a rapid capturing method thereof are designed, and pseudo code ranging and DOR angle measurement are integrated; according to the invention, the device group time delay calibration of the system is realized by using the broadband characteristic of the signal through the PNDOR beacon, an external calibration signal is not needed, the slow change of the device time delay can be adapted, and the calibration precision is higher; a PNDOR signal capturing method based on an FFT algorithm and an open-loop precise time delay measurement method are introduced, and the code correlation and carrier phase auxiliary technology is utilized, so that the time delay measurement precision is further improved.

The application discloses a near-surface elastic parameter inversion method based on a controllable source force signal, and relates to the field of geophysical prospecting. The method comprises the following steps: based on the coupling effect between a weight and a vibration plate and the ground, a mathematical model of a controllable source excitation device reflecting the characteristics of the controllable source excitation device is established; according to the mathematical model of the controllable source excitation device, a force transmission formula of a weight-vibration plate system is derived, and the weighted and ground force of the controllable source excitation system is obtained by using the force transmission formula of the weight-vibration plate system; based on the coupling effect between the vibration plate and the ground, the force transmission formula of a ground coupling system is derived according to the weighted and ground force; according to the force transmission formula of the weight-vibration plate system and the force transmission formula of the ground coupling system, a transfer function between the controllable source weight-vibration plate-ground system is derived; and the near-surface elastic parameter is inverted by using the transfer function between the controllable source weight-vibration plate-ground system. The method is especially suitable for a complex exploration area with a dramatic near-surface change.

The application relates to the technical field of deep space exploration and planetary remote sensing, in particular to a lunar surface parameter monitoring device and method based on a satellite-borne GNSS-R and a compact polarization technology.The device comprises a satellite platform, a GNSS-R receiver, a compact polarization antenna array, an on-orbit processing unit, a data storage and telemetry module and a ground processing system.The method obtains dual-polarization components by receiving direct and moon-reflected signals of a multi-navigation satellite system; generates a delay Doppler map and extracts polarization bit features on orbit; inverses a lunar surface dielectric constant and roughness based on a physical model and a machine learning model; and generates products by the ground system after data storage and transmission.The application realizes high-precision, global coverage and high-frequency monitoring of key physical parameters of the lunar surface, the system has the characteristics of light weight, low power consumption and intelligence, and effectively makes up for the deficiencies of traditional detection technology in terms of time and space continuity, system complexity and cost.

The invention discloses a double-intelligent-reflecting-surface three-frequency aperture-sharing satellite-ground communication system and method, and relates to a satellite-ground communication and quantum communication technology. A low-orbit satellite and a fixed ground station are respectively integrated with a three-frequency shared aperture antenna array, and RIS-s and RIS-u are conformally arranged in a near-field area of the array, so that a double-intelligent-reflecting-surface satellite-ground link based on a ground array-RIS-u-RIS-s-satellite-borne array is formed. Through characteristic mode analysis and series resonator design, the low-frequency segmented spiral sub-array is approximately electromagnetically transparent in middle and high frequency bands, and realizes three-frequency common-caliber work with the planar magnetoelectric dipole sub-array and the RIS. Based on a near field-far field segmented channel model, an off-line generation pattern library and a minimum transmitting power table, joint scheduling and power control are carried out on classical services and quantum entanglement distribution services on multiple frequency bands, and long-term service fairness of a pair of ground stations is achieved. On the premise of ensuring the quantum fidelity and the classical throughput, the emission power consumption of the satellite-ground system is reduced, and the method is suitable for 5G / 6G satellite-ground integrated quantum security communication.

The invention discloses a task planning method for guided observation of high and low orbit satellites, and belongs to the field of aerospace ground system operation and control. According to the method, for an observation scene that a high-orbit satellite guides a low-orbit satellite and an observation scene that a low-orbit satellite guides a high-orbit satellite, task planning is carried out by adopting a link establishment time period of the high-orbit satellite and the low-orbit satellite, an observable time period of the low-orbit satellite to an observation target and related parameters, and an observation time period of the high-orbit satellite is determined; and generating a satellite observation sequence combination of high and low orbit satellite guided observation tasks. According to the method, the planning problem of mutual guidance observation of high and low orbit satellites can be solved, the actually available satellite observation sequence combination of high and low orbit satellite guidance observation tasks can be generated, and the overall use efficiency of the satellites is improved.

The application provides a kind of based on phased array antenna one-dimensional electric scanning satellite-borne SAR sliding bunch mode implementation method and system, comprising: by ground system to compile autonomous imaging schedule and to satellite;Load receives satellite's task instruction and carries out radar operating parameter calculation, and sends attitude parameter to attitude control subsystem;Attitude control subsystem is maneuvered to place according to the parameter provided by load before imaging;Load is driven by satellite attitude maneuver to complete target imaging by wave beam scanning;Satellite attitude yaw maneuver ± 90 °, load can also realize sliding aggregation imaging by SAR antenna azimuth wave beam electric scanning.The application adopts on-board radar parameter autonomous calculation mode, only needs to upload target position information, without ground system frequently instructs to arrange work.In addition, the phased array antenna is designed as one-dimensional electric scanning, reduces the number of component channels, reduces the weight and cost of the whole satellite, meets the use demand of user to lightweight, low-cost SAR satellite.