35 results about "Space antenna" patented technology

A method includes performing a first relative calibration of a first plurality of periodically spaced antenna elements of an antenna lattice based on OTA calibration measurements to obtain a calibrated first plurality of periodically spaced antenna elements, performing a second relative calibration of a second plurality of periodically spaced antenna elements of the antenna lattice based on OTA calibration measurements, performing a third relative calibration of complex gains of a first subset of the first plurality of periodically spaced antenna elements and a second subset of antenna elements of the second plurality of periodically spaced antenna elements based on in-line calibration measurements of coupling between a calibration line and respective antenna elements of the first subset of antenna elements and the second subset of antenna elements and calibrating complex gains of the first plurality of periodically spaced antenna elements and the second plurality of periodically spaced antenna elements.

The utility model provides an antenna oscillator and an antenna oscillator array. The antenna oscillator comprises a PCB base plate; the metal structure is arranged on a target area of the PCB bottom plate, the target area comprises an area formed by the outer edge of the antenna oscillator and the outer edge of the radiation structure, and the radiation structure is arranged above the PCB bottom plate. According to the technical scheme of the utility model, the problems of gain reduction, cross polarization deterioration and S parameter deterioration caused by the influence of adjacent antenna oscillators on indexes when antenna oscillators form a narrow-spacing antenna array in the prior art are effectively solved.

The invention relates to a method for dynamic modeling and energy optimization control of a flexible annular space antenna, and belongs to the field of space antenna technology. The invention solves the problem that existing control methods are difficult to achieve a balance between high-precision pointing control, energy optimization, and vibration suppression under complex flexible structures and changeable operating environments. The invention is aimed at a space antenna system with a complex flexible structure, and adopts a modal simplification technique to simplify the dynamic model of the complex flexible structure. Then, a control method capable of dynamically switching control strategies is designed through an energy optimization switching model predictive control method, so as to optimize energy consumption during task switching, and ensure precise pointing and stable operation of the antenna system by effectively suppressing vibrations. It can achieve a dynamic balance between precise pointing control and vibration suppression, and optimize energy consumption. The method of the invention can be applied to the field of space antenna technology.

The application discloses a tight-spacing antenna decoupling method and device based on deep learning, and a storage medium. The method comprises the following steps: acquiring tight-spacing antenna data; inputting the tight-spacing antenna data into an antenna decoupling structure prediction model to obtain decoupling structure parameters; and performing tight-spacing antenna decoupling processing according to the decoupling structure parameters. The antenna decoupling structure prediction model is obtained through the following steps: acquiring rectangular microstrip patch antenna information; calculating patch length and patch width; establishing a binary antenna model; performing electromagnetic field simulation processing by using a preset script program and electromagnetic simulation software to obtain simulation result data sets; constructing an initial convolutional neural network model; inputting the simulation result data sets into the initial convolutional neural network model according to mean square error, so that the initial convolutional neural network model is trained to obtain the antenna decoupling structure prediction model. The application realizes antenna decoupling, improves efficiency and accuracy, and can be widely applied to the field of wireless communication technology.

A deployable space antenna may include a housing and a first telescoping boom and a second telescoping boom extendable from the housing in opposite directions from a stowed position to a deployed position. Each of the first and second telescoping booms may include telescoping boom segments. Each of a plurality of deployable, steerable antennas is carried by respective telescoping boom segment and movable between a stowed position and a deployed position. An antenna controller is configured to steer the deployable, steerable antennas.

The invention discloses a high-isolation and high-performance wifi and Bluetooth common radiator small-space antenna, and relates to the technical field of Bluetooth. A high-isolation and high-performance wifi and Bluetooth common radiator small-space antenna comprises a shell, a PCB, a WIFI 2.4 G antenna, a Bluetooth antenna and a WIFI 5G antenna, the PCB is fixedly installed in the shell, the WIFI 2.4 G antenna and the Bluetooth antenna are both fixedly installed on one side of the PCB, the WIFI 5G antenna is fixed to the side, away from the WIFI 2.4 G antenna, of the PCB, and through the arranged isolation structure, the antenna can be isolated from the WIFI 2.4 G antenna, so that the antenna can be used as an antenna for a wireless communication network. The isolation plate and the isolation copper sheet in sliding connection form a physical barrier, so that electromagnetic coupling between the WIFI 2.4 G antenna and other antennas is effectively reduced, high-isolation design is realized in a small space, space limitation is broken through, isolation performance between the antennas is remarkably improved, and when the sizes and the feed distance of the two antennas are appropriate, the antenna can be used as a high-isolation antenna for the antenna. The antenna can generate a high-efficiency antenna in a differential mode working mode, the common mode and the differential mode of the antenna act together and offset each other, and self-isolation of the two antennas can be improved.

The invention discloses an L-band high-orbit SAR full-link radiometric calibration method based on satellite-ground cooperation, and the method comprises the following steps: S1, obtaining a hardware gain function changing along with a space angle based on echo data and RCS information between a micro-nano satellite carrying an active transponder and a high-orbit SAR satellite; s2, a pre-trained deep learning model is utilized to obtain software gains changing along with working parameters; and S3, performing high-precision radiometric calibration on the input to-be-calibrated high-orbit SAR image by using a full-link gain model obtained based on a hardware gain function and a software gain, and inverting the absolute radar cross-sectional area sigma of the target. According to the method, the problems of high-sea far-field calibration difficulty, long calibration period, uncalibrated ground processing software gain, obvious atmospheric effect influence and the like of a high-orbit SAR satellite can be solved, the separation calibration of the gain of a whole link from a space antenna to the ground processing can be realized, and the difficulty of software and hardware gain coupling in a traditional method is solved.

The invention discloses an integrated supporting and radiating structure of a spaceflight linear array detector. The integrated supporting and radiating structure comprises a bracket, a radiator and a plurality of detector modules, the radiator is composed of a first base plate, a second base plate, a third base plate and a plurality of radiating fins, a retaining assembly is arranged in the inserting groove, and the retaining assembly is composed of a retaining seat, a first hinge piece, a second hinge piece and a limiting piece. According to the integrated supporting heat dissipation structure of the spaceflight linear array detector, the radiator can be installed through the maintaining assembly, the radiator is limited from the overall structure, an integrated structure between the radiator and the support is achieved, the attractive effect can be achieved, and the service life of the radiator is prolonged. And other auxiliary tools are not needed when the radiator is mounted and dismounted, so that the dismounting and mounting process of the radiator is simplified. And meanwhile, stable heat dissipation is carried out on the detector module through the radiator, limitation of parts on the detector module is reduced, and the assembly efficiency of the detector is improved.

The utility model discloses an electromagnetic band gap wave-absorbing structure and an antenna oscillator assembly. The electromagnetic band gap wave-absorbing structure comprises a substrate and two groups of diffuse reflection units. The base body is provided with two non-coplanar mounting surfaces; the two groups of diffuse reflection units are respectively arranged on the two mounting surfaces, the diffuse reflection units in the same group are arranged at intervals, an avoiding gap is formed between every two adjacent diffuse reflection units, and the projection of the avoiding gap on the other mounting surface at least partially falls on the diffuse reflection unit in the other group. In the scheme, electromagnetic waves are continuously diffused back and forth between the two groups of diffuse reflection units which are arranged in a staggered manner, and are continuously absorbed and consumed in the back and forth diffuse reflection process, so that the wave absorbing effect is achieved, the influence of vibrators between columns in an antenna array is reduced, the narrow-spacing antenna index is optimized, and the narrow-spacing antenna is only composed of the base body and the two groups of diffuse reflection units. The structure is relatively simple, and production difficulty and cost are reduced.

A modular space antenna cell skeleton structure with equal rib length and equal gap, a generation method, a system, a medium and an apparatus. In the method, an upper initial skeleton structure of a central cell is generated, where the lines connecting the six vertices of a regular hexagon and the geometric center point form six ribs, which constitute the upper initial skeleton structure of the central cell; skeleton structures of other cells are generated, where the skeleton structures of other cells are generated in units of ribs, and the newly generated ribs are connected to the ribs, so the vertex at one end of the newly generated rib is known, and the two vertices of the newly generated rib serve as key points. The set of key points of all ribs in a single cell serves as the key point of the cell; all ribs and key points are gradually generated along a path from the center to the edge, and all key points are updated to generate gaps between cells; the key points are extended along the direction from the center of the sphere to itself by the distance of a back frame to obtain new key points; and the key points are connected in sequence to obtain the skeleton structure of the entire cell.

The invention discloses a large space antenna on-orbit assembly ground test system and test method. The system comprises an assembling base module, a large space antenna module and an assembling mechanical arm module, the assembling base module comprises a rack fixed to the ground, a hollow rotating platform and a supporting platform, and the hollow rotating platform is used for connecting the rack and the supporting platform; meanwhile, the supporting platform is controlled to rotate to be matched with the assembling mechanical arm module to complete the assembling process, and the supporting platform is used for supporting the large space antenna module; the large space antenna module comprises a plurality of space structure assembly cell elements and passive docking interfaces, and the passive docking interfaces are used for connecting adjacent space structure assembly cell elements; and the assembling mechanical arm module is used for grabbing the space structure assembling cell elements to complete the assembling process. According to the invention, verification of an on-orbit assembly scheme of a large space antenna and docking test of a passive docking interface can be realized, and the system has the characteristics of simple structure, convenient test operation and perfect assembly process.

The invention provides an aerospace ceramic shape memory phenolic composite material and a preparation method and application thereof, and relates to the technical field of aerospace functional composites.The preparation method comprises the steps that S1, a shape memory phenolic resin prepolymer, ceramic powder and blackening filler are mixed, and a mixture is obtained; and S2, sequentially heating and curing the mixture to obtain the air-space ceramization shape memory phenolic composite material. The composite material provided by the invention can be shaped into a temporary shape through thermal stimulation on the ground, and after the space returns to an initial shape through thermal / laser stimulation, a ceramic locking structure is realized through laser irradiation, and the bearing capacity is improved. The technical problem that a space unfolding structure cannot be fixed after being unfolded is solved, the shape memory ceramic structure has the dual functions of shape memory and ceramic, and the shape memory ceramic structure is suitable for aerospace application scenes such as satellite solar panels and space antennas.

The invention relates to the technical field of space docking of spacecrafts, in particular to an antenna module unlockable passive docking device which comprises a shell, a barrel is arranged on the inner wall of the shell, two symmetrically arranged straight notches are formed in the surface of the barrel, two symmetrically arranged round holes are formed in the surface of the barrel, and the straight notches and the round holes are communicated with each other. A fixing rod is fixedly connected to the surface of the circular barrel, a limiting ring is connected to a fixing rod on the surface of the circular barrel, a circular block is fixedly connected to the upper end of the circular barrel, a first fixing hole communicating with the surface of the circular block is formed in the upper end of the circular block, and a first fixing piece is arranged at the upper end of the circular block. The design facilitates the overall installation and fixation of the device, meanwhile, the first fixing hole and the second fixing rod hole are matched with the first fixing piece and the second fixing piece respectively, and the inner walls of the first fixing hole and the second fixing rod hole are slidably connected with the butt joint, so that when butt joint or disassembly is needed, the operation is simple and convenient, and the installation and maintenance efficiency of the space antenna module is improved.

The invention specifically relates to a large-scale space antenna assembly sequence planning method considering structure fundamental frequency maximization, and the method comprises the steps: building a dynamic model of a large-scale space antenna assembly process based on the structural characteristic that a geometric configuration is gradually increased in the assembly process and in combination with a modeling thought of a life-death element method in a finite element method; determining optimization variables and constraint conditions of the assembly sequence in the large space antenna assembly process; based on the dynamic model, considering the time-varying characteristic of the dynamic characteristic of the space antenna in the assembly process, and constructing an evaluation index of the assembly sequence; based on constraint conditions and evaluation indexes of the assembly sequence, an improved self-adaptive discrete particle swarm algorithm is provided, an assembly sequence optimization problem with maximized structural fundamental frequency is solved, and a feasible and optimal assembly sequence is obtained. According to the method, the structural rigidity in the assembling process can be improved, structural vibration in the assembling process is reduced, and the design redundancy of the orbit attitude control system is improved.

The invention relates to a non-shaped ultra-wideband decoupling structure used for loading resistors in a small-spacing antenna array and maintaining the shape of a directional diagram, which is loaded between two antenna units and is positioned above a metal reflection floor. Comprising a dielectric substrate, three pairs of metal branches are symmetrically printed on the front side and the back side of the dielectric substrate, the three pairs of metal branches are of bent structures and are arranged in parallel, the three pairs of metal branches are connected through transmission lines, resistors are loaded on the transmission lines, the heights of the three pairs of metal branches meet the requirement that the branches do not make short-circuit contact, and the total height is equal to the height of the antenna; according to the invention, the non-shaped ultra-wideband decoupling structure loaded with the resistor is loaded in the middle of the array antenna unit, so that the field distribution of the antenna is changed, and the decoupling of space waves is realized. The design height is equivalent to the antenna height, so that the antenna profile is not increased; a plurality of resonant branches are designed to realize the decoupling requirement of the broadband antenna array; the loading resistor is used for absorbing the coupling current on the resonance branch knot, and the shape-preserving design of each frequency point directional diagram is met.

The invention discloses a satellite-borne maximum paraboloid assembled antenna, which comprises a peripheral module unit, a central module unit, a feed source array and a foldable truss module unit, the plurality of peripheral module units are spliced to form the modular reflector by taking the central module unit as a center; a plurality of foldable truss module units are spliced in sequence to form an extension arm truss; one end of the extension arm truss is connected with the satellite, and the other end is connected with the feed source array. According to the satellite-borne maximum paraboloid assembled antenna, the contradiction among the large size, high precision and carrying limitation of a maximum-caliber paraboloid antenna is solved, the modular reflector and the folding and unfolding type feed source array extension arm truss which can be assembled in an on-orbit mode are adopted, and on-orbit construction of a hectometer-scale caliber paraboloid antenna is achieved; ground manufacturing and carrying bottlenecks are broken through, an antenna configuration scheme which can be implemented on orbit is formed, and engineering feasibility support is provided for on-orbit construction of the large-aperture paraboloid space antenna.

The invention discloses an equal-rib-length equal-gap modular space antenna cell skeleton structure, a generation method, a system, a medium and equipment, and the method comprises the steps: generating an upper-layer initial skeleton structure of a central cell, forming six ribs by connecting lines of six vertexes of a regular hexagon and a geometric center point, and forming the upper-layer initial skeleton structure of the central cell by the six ribs; skeleton structures of other cell elements are generated, the skeleton structures of other cell elements are generated with ribs as units, newly generated ribs are connected with the ribs, so that the vertex of one end of each newly generated rib is known, two vertexes of each newly generated rib serve as key points, and a set of the key points of all the ribs in a single cell element serves as the key point of the cell element; gradually generating all ribs and key points through a path from the center to the edge, and updating all the key points to generate gaps among the cell elements; extending the key point by a distance of a back frame along the direction from the sphere center to the key point to obtain a new key point; and connecting the key points in sequence to obtain a skeleton structure of the whole cell element.

The invention belongs to the technical field of satellite navigation and wireless communication, and particularly relates to an anti-interference array antenna layout optimization method in a limited space. According to the method, an antenna layout problem is converted into a structured space filling problem, and automatic solving is realized through parametric modeling and numerical calculation. The method specifically comprises the steps of limited space digital definition, special-shaped polyhedron parameterization generation and optimization, and array element automatic layout and performance evaluation. By adopting the special-shaped polyhedron array layout, a larger effective array layout area is realized in a limited space, enough array element spacing is fundamentally ensured, a mutual coupling effect is reduced, and meanwhile, an internal wide-beam receiving system is formed by the natural multi-orientation characteristic of the special-shaped polyhedron; and the signal receiving robustness in a dynamic attitude is greatly enhanced. The method has the characteristics of high automation degree and high universality, and can be suitable for limited space antenna layout design of various carrier platforms.

The invention belongs to the technical field of space antenna fault detection and identification, and relates to a space antenna fault detection and identification method based on three-dimensional Gaussian sputtering, which comprises the following steps of: performing coarse positioning on the position of a space antenna hinge by using an optimized YOLOv5 model; according to the position of the space antenna hinge, tracking of the space antenna hinge and calibration of a viewpoint pose are achieved through continuous image streams; constructing a 3DGS model of an intact space antenna hinge by using a three-dimensional Gaussian sputtering 3DGS technology, performing defect detection on the tracked and calibrated space antenna hinge, and quantitatively analyzing the size of the defect of the space antenna hinge; according to the invention, monitoring blind areas and fault omission can be reduced; shooting points are accurately estimated, and antenna details are restored with high precision; time resources are saved, and the detection efficiency is improved; three-dimensional Gaussian sputtering is combined with a loss function, a fault area is accurately recognized, and misjudgment and missed judgment are reduced.

A method comprises performing a first relative calibration of a first plurality of periodically spaced antenna elements of an antenna grid based on OTA calibration measurements to obtain a calibrated first plurality of periodically spaced antenna elements, performing a second relative calibration of a second plurality of periodically spaced antenna elements of the antenna grid based on OTA calibration measurements,Performing a third relative calibration of complex gains of a first subset of the first plurality of periodically spaced antenna elements and a second subset of antenna elements of the second plurality of periodically spaced antenna elements based on in-line calibration measurements of a coupling between a calibration line and respective antenna elements of the first subset of antenna elements and the second subset of antenna elements, and calibrating complex gains of the first plurality of periodically spaced antenna elements and the second plurality of periodically spaced antenna elements.

This application discloses a UWB antenna structure and a mobile terminal. The UWB antenna structure includes an antenna region located in the first layer of the UWB antenna structure. The antenna region includes a radiating patch for transmitting and receiving signals in a first frequency band. The radiating patch is rectangular and has multiple spaced antenna grounding holes along its width. The distance from the first antenna grounding hole to the last antenna grounding hole is equal to the width of the radiating patch. The antenna structure of this application reduces the width of the radiating patch, thereby reducing the size of the antenna structure and making its application more flexible.

The invention provides an airborne active phased array meteorological radar measuring tool, and belongs to the technical field of active phased array meteorological radars, the airborne active phased array meteorological radar measuring tool specifically comprises a measuring antenna array surface and a plurality of spaced antenna units, and the topological structure of the measuring antenna array surface is consistent with that of a radar antenna array surface to be measured; one side surface of the metal grid net is fixedly connected with the measuring antenna array surface, the other side surface of the metal grid net is fixedly connected with the to-be-measured radar antenna array surface, and the antenna units on the to-be-measured radar antenna array surface and the measuring antenna array surface are in one-to-one correspondence with grids of the metal grid net; the centers of single antenna units on the to-be-measured radar antenna array plane and the measuring antenna array plane coincide with the centers of corresponding grids, and the grids are used for isolating transmission channels of adjacent antenna units; and the output end of the power divider is electrically connected with the antenna unit for measuring the antenna array surface. Through the processing scheme provided by the invention, the measurement precision of the airborne active phased array meteorological radar is improved.

An antenna is disclosed. The antenna includes a transparent substrate, a first square patch antenna element with a square lattice structure, a second square patch antenna element and a low profile transparent passive decoupling strip. The first square patch antenna element is disposed on the transparent substrate. The first square patch antenna element includes horizontal conductive wires and vertical conductive wires. The horizontal conductive wires and the vertical conductive wires cross each other and are equally spaced to form square spaces between. The second square patch antenna element is disposed on the transparent substrate. The second square patch antenna element has a structure identical to the structure of the first square patch antenna element. The first and the second square patch antenna elements are spaced apart from each other. The low profile transparent passive decoupling strip is disposed between the first and the second square patch antenna elements.

The invention discloses a thermally induced deformation prediction and optimization control method for a spaceborne antenna, and belongs to the technical field of space antenna control. The method solves the problem that an existing control method is low in control precision due to the fact that an existing method cannot effectively cope with antenna thermal deformation caused by a non-constant thermal field. According to the method, the orbit prediction model of the space heat flow is established, the heat flow borne by the whole antenna at different orbit positions and time points can be accurately calculated, the thermal deformation rule and the key stress area of the antenna structure are comprehensively analyzed according to the thermally induced deformation characteristic caused by a time-varying thermal field, the position distribution layout of the actuator is optimally designed, and the space heat flow prediction accuracy is improved. According to the invention, the thermal deformation peak value area and the structure easily affected part are preferentially covered, so that more efficient shape control and vibration suppression are realized, the antenna is ensured to maintain a stable structural form and high-precision working performance in a complex thermal environment, and the control precision is effectively improved. The method can be applied to thermally induced deformation prediction and optimization control of the antenna.

The invention relates to the technical field of antennas, and discloses a radio star calibration method for downlink channel time delay of a deep space antenna array, and the method comprises the steps: enabling a first antenna and a second antenna in the deep space antenna array to be aligned with the same radio star at the same time, and receiving a signal transmitted by the radio star; converting a first signal received by the first antenna and a second signal received by the second antenna into frequency domain signals to obtain a first frequency domain signal and a second frequency domain signal; performing frequency domain correlation on the first signal and the second signal to obtain a third frequency domain signal; obtaining a relative delay inequality between the first signal and the second signal according to the curve of the third frequency domain signal; and obtaining the relative time delay difference between the downlink signal channel of the first antenna and the downlink signal channel of the second antenna according to the relative time delay difference between the first signal and the second signal and the relative space time delay difference between the first signal and the second signal. The method is simple, reliable and convenient to implement, and the system design cost is reduced.

The utility model discloses a novel inclined semi-open type oscillator fixing device. The novel inclined semi-open type oscillator fixing device comprises a fixing seat, a first mounting seat and a second mounting seat, the fixed seat is inclined; the first mounting seat is arranged at the upper end of the fixed seat and is used for connecting the vibrator panel; the second mounting seat is arranged at the lower end of the fixed seat and is used for connecting the oscillator substrate and the reflecting plate; inserting grooves are formed in the fixed seat, the first mounting seat and the second mounting seat and are used for inserting the oscillator Balun plate; according to the structure, the inclined oscillator can be adapted, meanwhile, the material consumption of parts can be effectively reduced, the die manufacturing is simpler, the cost is reduced, the appearance can be better matched and clung to an inclined oscillator balun plate, the stability of mechanical performance is improved, and the advantages of high strength and compact structure are achieved; and the overall layout of the complex and compact-space antenna is facilitated.

The present disclosure relates to the field of deployable antennas for space-based applications and, in particular, to reflector array antenna systems (100) deployable from a spacecraft for communication / planetary observation applications. The disclosure features a rollable and / or Z-foldable reflector array antenna system (100) for satellite / spacecraft (102) applications consisting of at least one or more layers (114) of a top facesheet (502), that acts as an active reflector plane of regions of conductive RF reflective patches (508), bottom facesheet (504), that acts as a ground plane that consists of a continuous conductive layer with the layers separated by a specified distance. The deployment mechanism is stowed in a compact configuration and is deployed by unrolling or unfolding to the operational configuration. The system (100) ensures efficient deployment while maintaining a constant gap between the antenna's patch and ground layers, providing a lightweight, reliable, and self-deploying solution for space missions.

A deployable space antenna may include a housing and a first telescoping boom and a second telescoping boom extendable from the housing in opposite directions from a stowed position to a deployed position. Each of the first and second telescoping booms may include telescoping boom segments. Each of a plurality of deployable, steerable antennas is carried by respective telescoping boom segment and movable between a stowed position and a deployed position. An antenna controller is configured to steer the deployable, steerable antennas.

The present application relates to the field of low-orbit satellite communications and discloses a low-power relay link system for achieving omnidirectional coverage on a low-orbit satellite. The system comprises a primary relay measurement and control unit (MTC) and a backup relay measurement and control unit (MTC). Each unit comprises a space antenna, a ground antenna, a radio frequency electronic switch, a duplexer, a low-noise amplifier, a power amplifier (PA), and a baseband processing unit. The system dynamically switches the communication links between the space antenna and the ground antenna using the RF electronic switch to ensure stable two-way communication between the satellite and the relay satellite and the ground station. When the satellite's attitude changes, the system automatically adjusts the antenna link to ensure uninterrupted communication. By adopting a primary-backup dual-machine redundant design, the system can automatically take over communication tasks when the primary relay measurement and control unit fails, thus avoiding communication interruptions caused by equipment failures, ensuring that communication between the satellite, the relay satellite, and the ground station remains unaffected, and improving system reliability.

A system and method for sequencing of items in a vertical stack is disclosed. The RFID based sequencing system includes first and second towers positioned about a portal, each of the first and the second towers having at least two strategically, vertically spaced antennas configured to acquire information from RFID tags attached to individual assets in a vertical stack of assets. The system further includes an RFID reader in communication with the antenna and with an asset management system that stores computer executable instructions configured to determine a vertical position of each RFID tag in the vertical stack of assets as it moves through the portal between the first and second towers.