13 results about "Space antenna" patented 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 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.

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 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.

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.

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 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 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.

The invention relates to an antenna deformation on-orbit microwave measurement method based on combination of virtual and real apertures. According to the method, factors such as space environment, equipment envelope and weight, equipment wide coverage scanning capability, measurement precision and the like are comprehensively considered, on the basis of a microwave measurement technology, an observation aperture as large as possible can be obtained under a limited space envelope by utilizing a time division orthogonal waveform and virtual aperture expansion technology, and meanwhile, the measurement precision is improved. The two-dimensional observation capability, system complexity and low cost of an antenna are considered, the two-dimensional high-resolution measurement capability of orientation and pitching is obtained by adopting a mode of combining virtual and real apertures, in addition, the problem of near-field measurement of a large antenna is considered, and a high-order weight vector is utilized to perform matched beam forming, so that centimeter-level spatial resolution can be realized. On the basis of obtaining the two-dimensional observation information of the spatial large-scale antenna, the net surface deformation data of the spatial large-scale antenna can be obtained by using the time observation sequence.