39 results about "Satellite antennas" patented technology

This invention discloses a virtual splicing and assembly method for satellite antennas based on the cooperative optimization of gravitational potential energy functions. The method includes: constructing a virtual assembly initialization scenario driven by multi-source data; constructing a global gravitational potential energy field based on theoretical surfaces, converting the geometric surface errors of the sub-lobes into global potential energy values; constructing a local cooperative constraint potential energy field based on boundary topological relationships, which includes an elastic tensile potential energy component characterizing the gap width and a torsional potential energy component characterizing the step difference and normal deflection; treating the sub-lobes to be assembled as rigid bodies, solving for the differential of pose parameters based on the total potential energy function, and obtaining the virtual net external force and virtual net torque acting on the centroid of the sub-lobes; based on the virtual net external force and virtual net torque, synchronously updating the spatial position and attitude angle of all sub-lobes along the opposite direction of the potential energy gradient, and recalculating the global gravitational potential energy function and the local cooperative constraint potential energy function until the total potential energy converges. This invention achieves efficient and accurate virtual splicing and assembly of satellite antennas.

The application discloses a high-order overtone DOR measurement method, system, device and medium, relates to the technical field of information acquisition and processing, and comprises the following steps: performing local correlation processing on a carrier channel signal acquired through a satellite antenna to obtain interference phases in multiple first integral periods, and determining a first phase polynomial of a carrier model based on all the interference phases; determining a high-order overtone model based on the phase polynomial of the carrier model; correcting multiple high-order overtone signals acquired through the satellite antenna based on the high-order overtone model; determining a residual phase corresponding to each high-order overtone signal through the multiple corrected high-order overtone signals; and determining a DOR time delay observation corresponding to each high-order overtone signal through a multi-side tone DOR time delay calculation method based on the residual phase corresponding to each high-order overtone signal. The application can realize acquisition of a DOR measurement time delay observation, and has a wide application prospect in the field of deep space interferometric measurement.

1. The name of the design product: satellite antenna support. 2. The use of the design product: used for matching antenna installation, sending and receiving signals. 3. The design points of the design product: in shape. 4. The picture or photo that best shows the design points: perspective view 2.

This utility model discloses a shipborne communication device for offshore wind farms, belonging to the field of mobile communication installation technology. Addressing the problem of inconvenient installation and disassembly, it includes a base plate, a support rod, and a mounting plate. A positioning frame is fixedly connected to the mounting plate, and a positioning mechanism is provided on the positioning frame. A connecting mechanism is connected to the positioning frame via the positioning mechanism. A satellite antenna body is mounted on the upper part of the connecting mechanism. The satellite antenna body is detachably installed on the connecting mechanism via the positioning mechanism. A positioning seat is fixedly connected to the bottom of the satellite antenna body, and a positioning hole is provided on the outside of the positioning seat. This utility model, through the combination of the connecting mechanism and the positioning mechanism, not only enables stable installation and fixation of the satellite antenna body but also allows for convenient and quick disassembly, facilitating future maintenance and thus improving the practicality of the device.

This invention discloses a satellite antenna component manufacturing and processing equipment and method, belonging to the field of satellite antenna components. The satellite antenna component manufacturing and processing equipment further includes: a fixed fan and a stirring device, fixedly installed on the inner bottom wall of the processing platform. A speed regulator is fixedly connected to the side of the fixed fan via a pipe. A conversion driver is provided between the fixed fan and the stirring device. Drive blades are provided on the inner wall of the conversion driver. A connecting rod is installed at one end of the drive blades passing through the conversion driver, and the connecting rod is installed between the conversion driver and the stirring device. This invention, through the coordinated use of the fixed fan, stirring device, conversion driver, and clamping device, facilitates the simultaneous clamping of injection-molded component molds and the clamping of injection-molded materials. Compared with existing satellite antenna component manufacturing and processing equipment, this device can effectively improve the mass production of components.

The present specification provides a satellite communication antenna and electronic equipment, the antenna comprises a first radiation branch and a parasitic unit, the parasitic unit is a ring branch, and at least part of the branch is close to the first radiation branch and is coupled, and the parasitic unit is connected to the ground through at least one ground point.The satellite communication antenna of the embodiment of the present specification forms circular polarization by using the coupling effect of the parasitic unit, greatly improves the antenna gain compared with linear polarization satellite antenna, and improves the actual experience of satellite communication.And the radiation direction of the satellite communication antenna is mainly towards the zenith region, so that the antenna efficiency is higher, the satellite searching and communication efficiency in the state of user handheld mobile phone is improved, and the user experience is improved.

This invention discloses a vehicle lane correction system based on real-time fusion of video stream and satellite positioning. The system includes a processor, an Ethernet switch, a low-latency camera, a GNSS satellite antenna, and a receiver connected in sequence. The low-latency camera collects real-time video stream data of the ground lane lines and transmits it to the processor via the Ethernet switch. The GNSS satellite antenna receives satellite positioning signals, and the receiver decodes the received satellite signals. The processor preprocesses the video stream data and uses a lightweight deep learning segmentation model to segment the lane lines. Combining this with GNSS positioning information, a dynamic confidence-weighted fusion algorithm is used to fuse multi-source information, outputting the vehicle's lateral offset status and lane correction control signals to the vehicle control system. This invention is easy to install and maintain, has a low system failure rate, and can balance visual and GNSS output results, effectively improving the accuracy of the lane correction results.

The utility model belongs to the technical field of turnover tools, and particularly relates to a turnover tool of a satellite antenna. The turnover tool of the satellite antenna comprises a support, a turnover mechanism and a locking mechanism. Wherein the turnover mechanism is arranged on the bracket in a rotatable manner, and is configured to fix a satellite antenna; the locking mechanism is arranged on the support and is configured to prevent the overturning mechanism from overturning relative to the support under the action of the elastic force of the locking mechanism and overcome the elastic force under the action of the first external force so that the overturning mechanism can drive the satellite antenna to overturn relative to the support under the action of the second external force. The turnover tool is compact and stable in design, the locking mechanism of the turnover tool is quick in response, the turnover mechanism can be locked efficiently and timely, the satellite antenna is effectively prevented from accidentally falling off, colliding or being damaged, and the safety and integrity of the satellite antenna are ensured.

The application provides a satellite antenna automatic pointing method based on PPO reinforcement learning, comprising: initializing an antenna controller, a sensor group and a satellite orbit prediction module, loading a pre-trained PPO reinforcement learning model, defining a state space and a continuous action space; based on real-time antenna angle and signal strength data obtained by the sensor group, combining theoretical position data calculated by the satellite orbit prediction module, performing data fusion processing to generate a dynamic state vector; based on the dynamic state vector, performing policy inference processing through an Actor network to generate a continuous action, and performing safety evaluation processing on the continuous action through a Critic network to obtain a safety decision result; based on the obtained state change data after the antenna rotates, performing dynamic reward calculation to obtain a reward value, and storing the reward value and the state change data into an experience pool. By using the method, high-precision pointing control can be realized in a dynamic environment through real-time policy optimization of the continuous action space.

This invention belongs to the field of satellite communication technology, and particularly relates to a method for enhancing satellite antenna control channel coverage based on dynamic beamspan. The method includes: determining the number of symbols and symbol positions of the uplink and downlink control channels to initialize the satellite antenna control channels; wherein the number of symbols and symbol positions of the uplink and downlink control channels correspond to the symbol time slots of the initialized satellite antenna control channels; judging scheduling events based on the initialized satellite antenna control channels to determine the beamspanning mode of the uplink and downlink control channels; and transmitting and / or receiving the uplink control channels after beamspanning in the symbol time slots of the initialized satellite antenna control channels, thereby completing the satellite antenna control channel coverage enhancement. This invention achieves effective coverage of the access beam area by the uplink and downlink control channels of the data beam, thereby eliminating uplink scheduling and uplink periodic signal blind spots.

The application relates to the field of antennas, and discloses a small satellite antenna selection and layout method, device and medium. In the design process of the antenna layout, the whole-satellite antenna selection and layout are predicted and designed, electromagnetic compatibility analysis is performed in combination with antenna task requirements, an antenna layout design result is obtained, the antenna layout design result meets the antenna task requirements and can normally operate, the small satellite antenna applicability to specific tasks and electromagnetic compatibility problems can be solved, resource waste caused by subsequent design compensation can be avoided, and task failure can be avoided.

This invention discloses a satellite antenna edge-winding machine, comprising a support plate, a pressure plate, a drive assembly, and an edge-winding assembly. The edge-winding assembly includes a fixing base, a retaining member, a locking member, and a winding head. This satellite antenna edge-winding machine uses the retaining member and the locking member to rotatably lock the rotating shaft within the limiting area of ​​the retaining member. This not only facilitates quick and easy installation of the rotating shaft on the winding head, but also, through the cooperation of the retaining member and the locking member, secures the rotating shaft, preventing the winding head from detaching when winding the satellite edge, ensuring rapid edge winding of the satellite antenna and improving overall winding efficiency.

Systems, methods, and articles for a wearable and lightweight portable power case are disclosed. The portable power case is comprised of a cylindrical housing, at least two battery elements connected to a printed circuit board (PCB), and at least one separating barrier between the at least two batteries and the PCB. The portable power case is operable to supply power to an amplifier, a radio, a wearable battery, a mobile phone, a tablet, a portable satellite dish and / or any other power consuming device. The portable power case is operable to be charged using solar panels, vehicle batteries, AC adapters, non-rechargeable batteries, and / or generators.

1. The name of the design product: electronic product fixing support (back clamping type). 2. The use of the design product: used for the adsorption type fixing support of satellite antenna, star chain terminal equipment and other electronic products. 3. The design points of the design product: in shape. 4. The picture or photo that can best show the design points: perspective view 1.

The utility model relates to satellite communication technical field discloses a satellite antenna testing arrangement, including support column, the top of support column rotatory connection has a plurality of pivot no.

Polyhedral antenna systems are described for improving satellite communication links. Using conventional planar satellite antennas, user terminals closer to the edge of coverage (EoC) of the antenna tend to experience appreciable scan loss relative to user terminals closer to the nadir. Polyhedral antenna systems described herein (e.g., pyramidal antennas) include planar sub-antennas pointing in both nadir and EoC directions, which manifests an improved aggregate antenna response relative to conventional antenna approaches. For example, in orbit, the boresight of at least one sub-antenna is pointing substantially in a nadir direction, and the boresight of at least another of the sub-antennas is pointing substantially in the EoC direction. Embodiments can use interference mitigation techniques to reduce interference between sub-antennas. Ground terminals can be assigned to whichever of the sub-antennas provides the ground terminal with the highest-gain satellite link.

This application discloses a method, apparatus, device, and medium for adjusting the angle of a ship's satellite antenna, belonging to the field of marine equipment. It includes: determining the calculation period of ship sensing data based on wave height data of the waters where the ship is located, and acquiring ship sensing data according to the calculation period; identifying whether the ship sensing data meets preset trigger conditions; if it does, acquiring wave period data of the waters where the ship is located, and calculating the theoretical elevation and theoretical azimuth angles of the satellite antenna at the maximum port and starboard tilt of the ship using the ship sensing data; generating a calibration command for the satellite antenna, and adjusting the angle according to the theoretical elevation and theoretical azimuth angles and the wave period data. This technical solution, by determining the theoretical elevation and theoretical azimuth angles based on ship sensing data and adjusting the angle according to the wave period data, achieves real-time and precise angle adjustment of the satellite antenna, ensuring that the satellite antenna is always aligned with the satellite direction, thereby guaranteeing signal quality.

The application discloses a satellite antenna with a precise servo lifting rotating mechanism and relates to the field of satellite communication.The satellite antenna comprises a base, a rotating motor fixed in the base, a rotating platform arranged on the base in a rotating mode through bearings and fixedly connected with the output end of the rotating motor at the bottom, a lifting cylinder body embedded and fixed at the shaft position of the rotating platform, a bearing seat fixed at the output end of the lifting cylinder body, a satellite antenna hinged to the bearing seat, a pitching cylinder body hingedly connected with one end of the bearing seat and the other end of the satellite antenna, a plurality of self-locking assemblies uniformly arranged at the upper end surface of the rotating platform at one end and detachably arranged at the side wall of the bearing seat at the other end, and a supporting assembly slidably sleeved on the outer wall of the base.

A method for determining the on-orbit radiation pattern of a satellite antenna considering multiple field effects is presented. This includes: order reduction of the satellite structure finite element model, whole-satellite attitude dynamics modeling, whole-satellite on-orbit thermal analysis modeling, solar radiation moment and Earth's gravity modeling, and their coupled simulation analysis. This invention solves the problems of single-field coupling being unable to solve for continuous attitude changes, difficulties in predicting satellite electrical performance under the coupled effects of structural deformation and thermal analysis, and low computational efficiency. It provides an analytical method and implementation means for accurately predicting the on-orbit electrical performance of satellites with large flexible payloads.

This application relates to a stitch structure and sewing method for splicing multiple pieces of warp-knitted metal mesh, and pertains to the field of application technology of medium and large-sized metal mesh for satellite antenna reflector surfaces. The method for splicing and sewing warp-knitted metal mesh includes: S1, providing at least two pieces of warp-knitted metal mesh to be spliced; S2, overlapping the edges of adjacent pieces of mesh with a width of 1-1.5cm to form an overlap area; S3, using polyimide or aramid filaments with a specification of 200-600D as sewing thread, and sewing along the overlap area using sewing equipment, wherein the stitch spacing is 0.8-1.2cm and the stitch density is 3-5 stitches / cm. This application improves surface accuracy by using an overlap width of 1-1.5cm and automated parameter control for sewing, a stitch length of 0.8-1.2cm, a density of 3-5 stitches / cm, and high-performance polyimide or aramid thread of 200-600D. This effectively avoids the problems of easy aging and embrittlement of traditional polyester thread or webbing, and improves long-term stability.

A method for determining the hinge reaction torque in the event of a holding-moment hinge deployment impact includes: establishing the system dynamic equations; setting the current values ​​(HoldMarker_H5, HoldMarker_H6) of the holding hinge flags for hinges H5 and H6, and the updated values ​​(HoldMarker_H5_update, HoldMarker_H6_update) of the holding hinge flags for hinges H5 and H6; updating the system generalized coordinate matrix q, the generalized coordinate first-order derivative matrix with respect to time, and obtaining the system generalized coordinate q at the next moment. i The constraint reaction force of each hinge is compared with the structural strength of the hinge. This invention solves the problem of high safety design and testing costs of the entire satellite hinge caused by the large impact torque during satellite antenna deployment.

A method includes sending, to a satellite of a non-terrestrial network, an instruction to lock into a radio frequency test band and channel as the satellite is passing over a testing area and to enter a co-channel receive mode, sending, to a user endpoint device that is located in the testing area, an instruction to lock into the radio frequency test band and channel and to initiate a continuous upload data stream to a base station of a terrestrial network, determining an I / Q component of the continuous upload data stream observed by the satellite, determining the I / Q component of the continuous upload data stream observed by the base station, correlating the I / Q component observed by the satellite with the I / Q component observed by the base station, and calculating an estimated link loss and a change in a gain of an antenna of the satellite based on the correlating.

The features described generally refer to adjusting the native radiation pattern of a satellite antenna to adapt communications through it. For example, a communications satellite might include an antenna with a feed assembly, a reflector, and a linear actuator coupled between the feed assembly and the reflector. The feed assembly might have multiple feeds to transmit signals associated with a communications service, and the reflector might be configured to reflect the transmitted signals between the feed assembly and one or more target devices. The linear actuator might have an adjustable length or provide an adjustable position between the feed assembly and the reflector. By adjusting the position of the feed assembly relative to the reflector, the communications satellite can provide communications service according to various native radiation patterns.

The utility model relates to satellite antenna technical field discloses a satellite antenna test rotary table, including mounting seat, mounting disc and pre -buried box, the mounting seat fixed setting in pre -buried box, the one side of mounting disc is provided with installation subassembly, is used for installing satellite antenna body, the top of mounting seat is provided with opening, the opening is provided with lifting drive arrangement, the drive end of lifting drive arrangement is provided with guide rod, the guide rod is provided with adjusting mechanism, the drive end of adjusting mechanism is provided with connecting rod, the other end of connecting rod is provided with limit disc, the one side of limit disc is provided with recess, both sides in recess are provided with limit socket, and the device completes satellite antenna installation on the ground, and the installation process is very convenient and laborsaving, just needs to aim at recess with mounting disc, solves the inconvenient problem of the prior art because of the volume and weight of satellite antenna body are bigger, when installing.

This invention belongs to the field of satellite antenna technology, specifically a satellite signal receiver; it includes a satellite antenna; the satellite antenna includes a parabolic reflector; an arc-shaped cylindrical cavity is provided on the back of the parabolic reflector; a rotating cylinder is rotatably mounted on the middle of the arc-shaped cylindrical cavity and the parabolic reflector; a first arc plate is fixed on the outer ring surface of the rotating cylinder; a sliding column slides inside the rotating cylinder; a rectangular groove is formed inside the sliding column; a second arc plate rotates within the rectangular groove via a torsion spring and a rotating shaft; a rectangular frame is fixed on the back of the arc-shaped cylindrical cavity; a triangular block is fixed at the bottom of the rectangular frame; a mounting bracket is provided below the triangular block; the side of the triangular block closest to the first electric push rod is rotated on the mounting bracket via a rotating rod; by setting the arc-shaped cylindrical cavity, this invention can avoid optical path difference shift and destructive interference of reflected signals caused by surface deformation, ensure the stability of the antenna main lobe gain, and reduce the risk of signal-to-noise ratio degradation and signal loss.

The application provides a target stereoscopic positioning method and system based on multi-node joint processing of a spaceborne radar, wherein the method comprises the following steps: deploying multiple satellites, obtaining a downward angle and a space cone angle of a target relative to the satellites; calculating three-dimensional coordinates of the target in a satellite antenna panel coordinate system; constructing a hierarchical conversion model from a geodetic coordinate system to a coordinate system of each satellite antenna panel; constructing an over-determined equation group with the target coordinates in the geodetic coordinate system as unknown quantities; solving the equation group by using a least square algorithm to obtain the three-dimensional coordinates of the target in the geodetic coordinate system; and finally converting the three-dimensional coordinates into longitude, latitude and height. The application utilizes the joint observation of multiple satellites to form redundant information, and introduces a rigorous hierarchical coordinate conversion model considering the orbit, the earth rotation and the installation attitude, so that the multi-satellite heterogeneous observation is unified to the same reference, and the over-determined equation group is solved, thereby significantly improving the accuracy and robustness of the target stereoscopic positioning.

The utility model provides a kind of for satellite antenna radiation surface detection's automation device, it is related to radiation surface detection technical field, comprising: work platform, the top of the work platform is fixedly connected with support frame, the top of the support frame is provided with telescopic traverse mechanism;The telescopic traverse mechanism includes first electric telescopic link, the bottom of the first electric telescopic link is fixedly connected with transmission table, the bottom of the transmission table is fixedly connected with configuration plate.The utility model in, unique telescopic traverse mechanism can be flexibly adjusted the position of detection probe in two-dimensional space, can adapt to the detection demand of different specifications, different shape satellite antenna radiation surface, effectively eliminate detection blind area, the spring design of flexible detection mechanism, so that detection probe can automatically adjust pressure according to the actual situation of radiation surface, both ensure the accuracy of detection data, also avoid damage to antenna radiation surface.

This invention provides a method, apparatus, electronic device, and computer-readable storage medium for precision control of satellite antenna profiles, relating to the field of spaceborne satellite technology. The precision control method includes: acquiring the array strain and key coordinates of the satellite antenna profile; inputting the array strain and key coordinates into the array structural mechanical model of the satellite antenna to evaluate the profile deviation coordinates; and performing profile precision control of the satellite antenna based on the profile deviation coordinates. This addresses at least the problems of low efficiency, poor consistency, and lag in precision adjustment in related technologies. It is suitable for antenna offset prediction and control scenarios.

This application relates to an antenna module and electronic device. The antenna module includes a first antenna and a second antenna. The first antenna includes a first feed and a first radiating stub, and the second antenna includes a second feed and a second radiating stub. When the first antenna needs to operate, the first feed point is connected to the first feed, so that the first feed excites the first radiating stub to operate in the satellite communication frequency band; the second feed point is connected to ground, so that the second antenna is not operational. When the first antenna does not need to operate, the first feed point is connected to ground, and the second feed point is simultaneously connected to the second feed, so that the second feed excites the second radiating stub to operate in the first frequency band. Therefore, the first antenna and the second antenna are designed independently, resulting in low system withstand voltage risk. While maintaining high overall efficiency, it improves the isolation between the satellite antenna and other antennas, reducing interference.

This invention discloses a method for constructing a space brightness temperature radiation model for on-orbit satellite antennas, specifically in the field of remote sensing measurement. It completes multi-coordinate system transformation of antenna radiation patterns; preprocesses cold-space brightness temperature mapping data, and constructs a cold-space radiation background database by combining piecewise binary linear interpolation and linear fitting. Based on brightness temperature thresholds, the Milky Way region is identified, and the upper and lower boundaries are solved by fitting the center line of the Milky Way strip using weighted least squares, thus establishing a Milky Way brightness temperature strip model. A land-sea segmentation model is used to classify land and sea using latitude and longitude coordinates, generating surface brightness temperature data. A standardized surface brightness temperature background database is constructed through interpolation and surface fitting. The spatial pointing of each radiometer beam is determined; surface-pointing beams are matched with surface brightness temperature data, while non-surface-pointing beams use cold-space background data to solve for the spatial brightness temperature of each beam, generating a satellite antenna background radiation value vector. The antenna brightness temperature integral effect is numerically calculated using the brightness temperature integral formula, completing the overall construction of the space brightness temperature radiation background model.