378 results about "Satellite antennas" patented technology

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.

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.

The invention discloses a satellite antenna dynamic pointing calibration method and system based on satellite autonomous gradient optimization, relates to the technical field of satellite communication, and realizes closed-loop calibration without ground intervention by processing signal to noise ratio (SNR) data uploaded by a ground station on a satellite in real time and combining a multi-physical field coupling model of a temperature and stress sensor. And the pointing error in a dynamic environment is reduced from more than 2.0 degrees of a traditional scheme to less than 0.3 degrees.

The invention discloses a plane matrix type high folding and unfolding bionic antenna truss structure with a negative Poisson's ratio effect, and relates to the technical field of space folding and unfolding mechanisms, the plane matrix type high folding and unfolding bionic antenna truss structure comprises a plurality of cell elements and a plurality of cell element connecting rods, transverse cell elements are connected through the cell element connecting rods, and longitudinal cell elements are fixedly connected through adjacent cell element cross beams; the cell element connecting rods are hinged to the cell elements on the two sides respectively, and the cell elements are three-level positioning inwards-concave hexagonal cell elements; the folding and unfolding antenna truss structure is in a folded state during launching, transportation and silent latency and is in an unfolded working state during on-orbit task execution, the high folding and unfolding ratio characteristic of the antenna provides bionic improvement inspiration for various urgent properties such as stealth and size reduction of a satellite antenna structure, the shape of the antenna folding and unfolding array can be changed in a multi-stage mode, and the antenna folding and unfolding array is suitable for large-scale popularization and application. Therefore, the functions of optimal frequency band adjustment, optimal area expansion, switching of different scanning ranges and the like are realized.

The invention discloses a satellite antenna servo system vibration sound signal sample enhancement method based on a physical constraint generative adversarial network, and the method comprises the steps: carrying out the multi-mode signal collection and fault simulation, and providing a high-fidelity signal source for training; fault physical parameter modeling is carried out, and a fault physical parameter vector and a fault frequency equation are defined; constructing a physical constraint generative adversarial network training model, and designing a double-branch generator and a physical constraint discriminator; training the physical constraint generative adversarial network, and outputting a high-fidelity vibration sound sample; according to the invention, intelligent fault early warning and diagnosis support is provided for stable operation of a satellite communication system.

The invention relates to the technical field of satellite communication, and provides a high-orbit and low-orbit fused satellite antenna tracking method and system. The method comprises the following steps: constructing a global satellite database and carrying out time-space coordinate unified coding; predicting visible time according to the satellite coordinates, and identifying a visible time window overlapping region and a corresponding tracking satellite pair; based on the types of the satellite pairs in the overlapping time, tracking path optimization under space-time unified coordinates is carried out, and optimization control parameters are output; switching points and scanning tracks are spliced according to the control parameters, and antenna tracking control parameters are obtained and used for adjusting an antenna. According to the invention, the technical problem that the stability of a satellite communication link is reduced due to switching delay and signal interruption risks when a traditional ground station system dynamically tracks high and low orbit satellites is solved, seamless switching and continuous high-gain tracking of the satellite communication link are realized through cooperative tracking and real-time optimization operation of the multi-orbit satellites, and the stability of the satellite communication link is improved. And the link stability and the resource utilization rate of satellite communication are improved.

The utility model provides a mobile terminal. The mobile terminal comprises three shells and an antenna system, wherein the three shells are sequentially and rotatably connected. The antenna system comprises a satellite antenna, the satellite antenna comprises a satellite radio frequency link, a first radiator, a second radiator, a third radiator, a first tuning circuit and a second tuning circuit, and the satellite radio frequency link is coupled with the third radiator. The first radiator, the second radiator and the third radiator are respectively arranged in different shells, and the three radiators are located at one end of the mobile terminal. The first radiator is coupled with the first tuning circuit, and the second radiator is coupled with the second tuning circuit. By adopting the scheme, when the satellite antenna is in a working state, the first radiating body and the first tuning circuit as well as the second radiating body and the second tuning circuit as well as the third radiating body can be utilized to jointly generate the target directional diagram of the satellite antenna, so that the optimization of the directional diagram of the satellite antenna and / or the gain of the satellite antenna is facilitated; therefore, the communication performance of the satellite antenna can be improved.

The invention relates to a dynamic path prediction method for satellite antenna tracking and computer equipment, and the method comprises the steps: collecting satellite antenna tracking angle data which comprise original data and actual data; calculating a first deviation sequence and a second deviation sequence based on the original data and the actual data; performing curve fitting on the first deviation sequence and the second deviation sequence through a fitting algorithm, substituting a fitting result into a pre-constructed mathematical model to obtain a prediction model, and extrapolating and predicting a prediction deviation of a preset time point through the prediction model; and compensating the predicted deviation to original data corresponding to the preset time point, and generating a dynamic range instruction, so that the satellite antenna is aligned with the communication satellite under the action of the dynamic range instruction. And the satellite antenna can continuously align to the real position of the communication satellite.

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.

The invention discloses a multi-beam VICTS antenna and a communication terminal, and the multi-beam VICTS antenna is of a multi-layer structure, and comprises a continuous cross section node slot radiation layer, a slow wave structure wave guide layer and a microstrip Rotmann lens feed network layer which are sequentially arranged from top to bottom. An air gap between the continuous section nodal gap radiation layer and the slow wave structure wave guide layer forms a quasi-plane parallel plate waveguide. An electromagnetic wave signal emitted by a satellite antenna enters a quasi-planar waveguide formed by the continuous cross section and the slow wave structure wave guide layer through a gap in the continuous cross section joint gap radiation layer, and electromagnetic waves are transmitted in the quasi-planar waveguide and are sent to the microstrip Rotmann lens feed network through the connection waveguide. And the beam is output from the beam port of the microstrip Rotmann lens. The multi-beam VICTS antenna provided by the invention can utilize multi-beam scanning in the same time period, has larger space coverage capability, and is beneficial to quick satellite finding when a communication-in-moving system is started and quick satellite recapturing after a satellite signal is lost.

An antenna system for tracking multiple satellites comprises an RF lens (homogeneous or multiple layer Luneburg) with numerous feeds placed around the lens in a tightly packed arrangement to maintain high cross-over points between beams and high circularity. High-quality circular polarization, consisting of low axial ratio and low cross polarization levels, is maintained using a novel dielectric slab to compensate for the slight mismatch in phase delay through the lens from the two canonical polarizations vertical and horizontal. A weighted combination of beams is used to keep the resultant beam peak fixed on a satellite with the ability to use this approach in a number of places simultaneously, and simultaneously using one or more of these methods at multiple frequency bands.

The invention provides an integrated antenna integrating Beidou, low-orbit and Tiantong satellite communication and high-precision navigation positioning. A low-orbit satellite microstrip antenna, a GNSS high-precision microstrip antenna, a Tiantong microstrip antenna and a Beidou short message microstrip antenna are sequentially stacked on the upper surface of a PCB in a conical mode. A shielding cover is arranged on the lower side of the PCB; antenna radiation patches of the low-orbit satellite microstrip antenna are arranged on the outer edges of the upper surface and the lower surface of the low-orbit satellite antenna substrate and are not covered by the GNSS high-precision microstrip antenna; circuits of the low-orbit satellite microstrip antenna and the sky-pass microstrip antenna are arranged on the upper surface of the PCB circuit substrate. And circuits of the GNSS high-precision microstrip antenna and the Beidou short message microstrip antenna are arranged on the lower surface of the PCB. According to the invention, the four-in-one combined design of the antenna, the low-orbit satellite antenna, the Beidou short message antenna and the high-precision navigation antenna is adopted, so that the problem of performance insufficiency when each antenna is used independently is solved, complementation among the antenna, the low-orbit satellite antenna, the Beidou short message antenna and the high-precision navigation antenna is realized, and the cost is reduced; the electromagnetic compatibility between the antennas is improved through frequency band and polarization isolation design, and the stability of a communication link is guaranteed through interference resistance of the peripheral low-orbit satellite antenna.

The invention provides a robust hybrid beam forming method for cooperative communication of multiple low-orbit satellites, which relates to the technical field of satellite communication and comprises the following steps of: S1, constructing a joint optimization problem for joint beam forming and user scheduling; s2, the minimum channel gain of all users is maximized, when the number of satellite antennas is larger than a preset threshold value, the step S3 is executed, and otherwise, the step S5 is executed; s3, constructing a minimum signal to interference plus noise ratio maximization problem, and solving to obtain an optimal all-digital precoding matrix; s4, based on the optimal all-digital precoding matrix, constructing a digital-analog hybrid precoding matrix design problem to obtain a digital-analog hybrid precoding matrix; and S5, constructing and solving an analog pre-coding matrix design problem based on maximization of the signal leakage and noise ratio to obtain an optimal analog pre-coding matrix, and then solving an optimal digital pre-coding matrix. According to the invention, the overall performance and the service quality of the multi-low-orbit satellite communication network can be obviously enhanced.

The invention relates to the technical field of antennas, in particular to a low-orbit satellite antenna board card. Comprising a first radiation unit, a second radiation unit and a PCB. The first radiation unit and the second radiation unit are circularly polarized antennas and respectively work in different frequency bands. The first radiation unit is of a cross-shaped structure, the second radiation unit is of a hollow structure, and the first radiation unit and the second radiation unit are both made of metal materials. The first radiation unit and the second radiation unit are nested on the PCB, the upper surface of the PCB is provided with a thermal control material, the lower surface of the PCB is provided with a heat conduction material, the antenna board card provided by the invention is suitable for being used outside a cabin, the application of the PCB to the outside of the cabin becomes possible, and thus light weight and low cost of a low-orbit satellite antenna are realized.

The mobile terminal provided by the invention comprises a satellite antenna system. The satellite antenna system comprises a satellite communication chip and at least two antennas. The at least two antennas comprise a first antenna and a second antenna, and the first antenna and the second antenna are used for receiving radio frequency signals of a communication satellite and realizing downlink communication of the mobile terminal. The first antenna and the second antenna are respectively connected with the satellite communication chip. At least one part of the first radiator of the first antenna and at least one part of the second radiator of the second antenna are located on different sides of the mobile terminal. The weak receiving sensitivity area of each angle of the first antenna and the strong receiving sensitivity area of each angle of the second antenna at least partially coincide, and the sum of the areas covered by the strong receiving sensitivity area of each angle of the first antenna and the strong receiving sensitivity area of each angle of the second antenna is large, so that the satellite alignment difficulty in the use process is reduced; the mobile terminal can receive the radio frequency signal of the communication satellite in many poses.

The invention discloses electronic equipment, and relates to the technical field of electronic products. The electronic equipment comprises a satellite antenna, the satellite antenna comprises a feed circuit, a first radiator and a bent radiator, the first radiator is a metal section in a top frame of the electronic equipment, and the first radiator and the bent radiator are arranged at intervals. The first radiating body and the bending radiating body are respectively and electrically connected with the feed circuit; under the condition that the first radiating body and the bent radiating body are respectively connected with a feed signal from the feed circuit, the first radiating body generates a first polarization mode, the bent radiating body generates a second polarization mode, the polarization direction of the first polarization mode is the length direction of the top frame, and the polarization direction of the second polarization mode is the length direction of the top frame. The polarization direction of the second polarization mode is the thickness direction of the electronic equipment, and the first polarization mode and the second polarization mode generate circular polarization.

The invention relates to a satellite mobile communication antenna adaptive beam prediction and control method, which comprises the following steps: acquiring motion data of a user terminal, signal state data of a satellite antenna receiving end, satellite-ground attitude data of a satellite and environment interference data of the ground, and processing to obtain a multi-source data set; the method comprises the following steps: constructing a geometric correlation feature, a gain correlation feature, a sidelobe correlation feature and an array element phase correlation feature of a multi-source data set and beam parameters, constructing a correlation matrix, and splicing the correlation matrix with the multi-source data set to obtain a complete input feature set; a beam prediction model is constructed, and training and verification are carried out; and converting the output of the beam prediction model into a control signal to drive an antenna array element to adjust, correcting model parameters based on the link signal-to-noise ratio, the bit error rate and the throughput collected by the user terminal, and splitting / combining the beam. According to the method, the beam parameter prediction precision and environment adaptability can be improved, interference is suppressed, resource allocation is optimized, and stability and high efficiency of satellite communication in a high-dynamic complex environment are guaranteed.

The present application discloses a compact dual - frequency circularly polarized satellite antenna and its array. The antenna includes a dielectric substrate, a feeding element, a high - frequency radiation patch, and a low - frequency radiation patch. The high - frequency radiation patch is disposed on the upper surface of the dielectric substrate, and the feeding element is disposed on the dielectric substrate. The high - frequency radiation patch is fed through the feeding element. There are at least two vertical angles in the high - frequency radiation patch that are distributed at diagonal positions. On the outer sides of the two vertical sides corresponding to any vertical angle of the high - frequency radiation patch, a low - frequency radiation patch is respectively arranged. The two low - frequency radiation patches are respectively parallel to the corresponding vertical sides and are coupled and fed with the high - frequency radiation patch within the upper surface. The present application realizes the setting of a dual - frequency circularly polarized antenna on the same layer, only uses the feeding element to be connected to the high - frequency radiation patch, and enables the high - frequency radiation patch to be coupled and fed with the low - frequency radiation patch, reducing the number of feeding ports required when constructing a dual - frequency circularly polarized antenna and its array.

The invention provides a mobile terminal. The mobile terminal comprises three shells and an antenna system, wherein the three shells are rotationally connected in sequence. The antenna system comprises a satellite antenna, the satellite antenna comprises a satellite radio frequency link, a first radiator, a second radiator, a third radiator, a first tuning circuit and a second tuning circuit, and the satellite radio frequency link is coupled with the third radiator. The first radiator, the second radiator and the third radiator are respectively arranged in different shells, and the three radiators are located at one end of the mobile terminal. The first radiator is coupled with the first tuning circuit, and the second radiator is coupled with the second tuning circuit. By adopting the scheme, when the satellite antenna is in a working state, the first radiating body and the first tuning circuit as well as the second radiating body and the second tuning circuit as well as the third radiating body can be utilized to jointly generate the target directional diagram of the satellite antenna, so that the optimization of the directional diagram of the satellite antenna and / or the gain of the satellite antenna is facilitated; therefore, the communication performance of the satellite antenna can be improved.

The utility model discloses turnover equipment suitable for a flat plate satellite, and belongs to the technical field of turnover equipment. Comprising a support, a satellite mounting frame, a supporting unit and a position adjusting handle, the support comprises a bottom frame, supports are fixed to the two sides of the bottom frame, and guide holes are formed in the tops of the two supports in a right opposite mode; the satellite mounting frame comprises a frame body, supporting blocks are fixed to the four corners of the inner side of the frame body, and a plurality of mounting screw holes are formed in the supporting blocks; guide columns penetrate through the middles of the two sides of the frame body in an opposite mode, beam plates are fixed to the ends of the guide columns, and the beam plates and the frame body are fastened through bolts. The guide columns are movably connected with the guide holes in an inserted mode. The turnover equipment suitable for the flat plate satellite supports 0-360-degree rotation of the flat plate satellite, and supports manual and mechanical force rotation driving; the equipment is of an oil-free structure and can be used for a vacuum thermal test; the antenna can support the unfolding of a flat satellite antenna mechanism, and can be used for testing the performance of an antenna by matching with a wave-absorbing heat sink in a vacuum thermal test.

1. The name of the design product: Starlink adapter base. 2. The use of the design product: Starlink adapter base is a device used to install and fix Starlink satellite antennas. 3. The design points of the design product: in shape. 4. The picture or photo that best indicates the design points: perspective view.

The embodiment of the invention provides an antenna attitude adjustment method, a vehicle-mounted satellite antenna and a device. The method comprises the steps that a satellite connection instruction is received, the satellite connection instruction is used for carrying out communication connection on a vehicle-mounted satellite antenna and a satellite, the vehicle-mounted satellite antenna comprises an antenna, an antenna tray, a horizontal tray and a base, and the satellite connection instruction comprises satellite position information; determining the current relative position of the vehicle-mounted satellite antenna and the satellite according to the satellite position information; determining the current state of the horizontal tray, and when the current state is a horizontal state, obtaining the current attitude information of the antenna tray; and adjusting the current attitude of the antenna tray according to the current relative position and the current attitude information to obtain a target attitude of the antenna tray so as to align the antenna to the satellite. The antenna attitude adjustment efficiency can be improved.

The present application relates to a vehicle-mounted communication device having a satellite communication function, and a vehicle. The vehicle-mounted communication device of the present application comprises a microcontroller module and a satellite communication module; the microcontroller module is connected to the satellite communication module, and the satellite communication module is configured to be connected to a satellite antenna; and the satellite communication module receives and sends a satellite signal by means of the satellite antenna and communicates with the microcontroller module. In the present application, a vehicle-mounted satellite communication function is integrated into a TBox, thereby providing two-way satellite messaging and satellite calling services, realizing the vehicle-mounted satellite communication function.

1. The name of the design product: rotor unmanned aerial vehicle satellite communication antenna. 2. The use of the design product: for airborne dynamic satellite antenna. 3. The design points of the design product: in shape. 4. The picture or photo that best indicates the design points: perspective view 1.

A radio communication route enables communication from an originating ground station to a destination ground station via one of multiple randomly orbiting satellites with no active attitude control. The ground stations and satellites include multi-feed parabolic antennas for receiving radio signals from and transmitting radio signals in multiple directions. The satellites store an address of a destination ground station from which an initial information signal is transmitted and antenna information identifying the satellite antenna feed on which the initial information signal was received. Plural satellite antennas transmit linking information identifying the satellite to the originating ground station. Data transmissions received at the originating ground station that designate a particular destination are transmitted by the originating ground station using the antenna on which the linking information was received and the satellite retransmits the data transmission using the satellite antenna feed identified by the stored antenna information.

The invention provides a mobile terminal. The mobile terminal comprises a first antenna, a first radio frequency front-end module and a second radio frequency front-end module, the working frequency band of the first antenna comprises the working frequency band of satellite communication; the first radio frequency front-end module comprises a first switch and a first signal transmission path, and the first switch is connected with the first antenna and the first signal transmission path; the second radio frequency front-end module comprises a satellite communication receiving channel, and the satellite communication receiving channel is connected with the first signal transmission channel; the first switch is used for cutting off the connection between the first signal transmission path and the first antenna in response to sending of a non-satellite radio frequency signal and receiving of the non-satellite radio frequency signal; and communicating the first antenna with the first signal transmission path in response to receiving the satellite radio frequency signal. Therefore, the satellite radio frequency signal can be received through the first antenna, a satellite antenna is omitted, the number of antennas is reduced, the internal space burden of the mobile terminal is reduced, and the manufacturing cost and weight of the mobile terminal are reduced.

The present invention relates to the technical field of satellite antennas, and discloses a foldable satellite antenna structure, wherein a piston seat is disposed in a storage cylinder and is movable along the axial direction of the storage cylinder. A driving device is connected to the piston seat and drives the piston seat to move along the axial direction of the storage cylinder. A feed horn is disposed on top of the piston seat, a secondary reflector platform is slidably mounted on the feed horn, the secondary reflector is located above the feed horn, and is connected to the secondary reflector platform via a connecting bracket. The top end of a spring is connected to the bottom of the secondary reflector platform, and the bottom end of the spring is connected to the top of the piston seat. A plurality of foldable ribs are provided, the foldable ribs including a root rib and a top rib. The first end of the root rib is hinged to the side of the piston seat via a first hinge, and the second end of the root rib is hinged to the first end of the top rib via a second hinge. The first hinge and the second hinge are respectively provided with elastic components. The present invention has the characteristics of a small folded size, a large unfolded size, and a lightweight structure.

The invention provides a novel dual-frequency dual-circularly polarized satellite antenna, and relates to the technical field of satellite antennas. The satellite antenna comprises a ground plane, a single-feed-point coaxial line, a dielectric substrate and a metal patch connected to the dielectric substrate. A gap layer is arranged between the ground plane and the dielectric base. The single-feed-point coaxial line passes through the gap layer and the dielectric substrate so as to be electrically connected with the ground plane and the metal patch. The metal patch comprises a circular patch on the inner layer and a rectangular patch arranged on the outer layer of the circular patch in a sleeving mode. The circular patch is provided with a rectangular groove so as to realize right-handed circular polarization. Two opposite sides of the rectangular patch are respectively provided with a long branch knot and a short branch knot so as to realize left-hand circular polarization. The four corners or the positions close to the four corners of the rectangular patch are electrically connected to the circular patch. The antenna has good dual-frequency coverage, circular polarization characteristic and gain performance in the L and S frequency bands.

The present invention discloses a method and system for detecting and suppressing anti-suppression deception interference. Combining the advantages of fully autonomous navigation of inertial navigation and satellite signal anti-interference processing technology, it comprehensively utilizes inertial / satellite combined navigation, multi-element satellite antenna array adaptive zeroing filtering algorithm, beamforming algorithm and other methods to achieve detection and suppression of anti-suppression deception interference. The solution of the embodiment of the present invention integrates the combined navigation, multi-element satellite antenna array zeroing adaptive algorithm and satellite navigation anti-suppression interference signal processing method into one system, and combines the beam direction vector calculated by the combined navigation with the zeroing adaptive algorithm based on the multi-element satellite antenna array and the anti-suppression interference module to achieve detection and suppression of suppression deception interference signals. The solution provided by the embodiment of the present invention has good anti-interference suppression deception effect.

A radome for a submarine satellite antenna according to one aspect of the invention includes a cap having a form of a hollow dome; a cap bracket secured to the cap by way of a screw-on structure, where the cap bracket has an open top and an open bottom and has a cylindrical form with its interior communicating with the interior of the cap; and a body made of a molybdenum-added stainless alloy, where the body is secured to the cap bracket by way of a screw-on structure, and the body has a cylindrical form with only its upper surface open.