30 results about "Earth's orbit" patented technology

A mobile device having array antenna can be used to communicate with Earth orbiting satellites and base stations on the ground. The display screen of the mobile device has an array antenna capable of transmitting and receiving radio frequency (RF) signals in the range of 0.6 GigaHertz (GHz) to 100 GHz. The configuration of the array antenna, including the number of arrays and the dimension of the arrays, is software programmable by activating and deactivating antenna elements for multiple beams and their beam characteristics.

A space surveillance method for detecting space objects in orbit around the Earth in images captured during the daytime, the method including the following steps: capturing a plurality of infrared images of the daytime sky using a camera including at least one infrared sensor, detecting space objects in orbit around the Earth on the basis of the images, the detection of bright spots being implemented by a deep-learning artificial intelligence system, and identifying each object detected from a catalogue of known space objects in orbit around the Earth.

Mitigation of erosive effects of atomic oxygen encountered by telescope systems deployed in low earth orbit (LEO is effected by providing an array of multiple very small projections on the interior surface of an open-ended tubular metering shell extending forwardly from a mirror to be protected. The projections are made of material that is geometrically configured to deflect AO atoms one or more times within the shell at angles that ultimately direct the atoms away from the mirror surface and back out through the forward end of the shell.

The invention relates to an autonomous capturing method and system for an earth orbit non-cooperative target. The method comprises the following steps: acquiring left and right images of the earth orbit non-cooperative target; inputting the left image and the right image into a DETR model for target detection, and outputting a semantic identifier of a target component; performing nonlinear mapping and binocular parallax calculation on the semantic identifier to obtain two-dimensional world plane coordinates and depth information, and fusing the semantic identifier, the two-dimensional world plane coordinates and the depth information to generate three-dimensional space positioning of the target component; the method comprises the following steps: converting a task instruction in a natural language form into a standardized control instruction based on a framework combining semantic analysis and a rule base; and mechanical arm forward kinematics is established on the basis of a D-H parameterized model, a standardized control instruction is converted into a target tail end pose through inverse kinematics solution, and high-precision capture of a non-cooperative target is achieved. Compared with the prior art, the method provided by the invention has the advantages of precision and real-time performance of spatial non-cooperative target autonomous capture and the like.

Mitigation of erosive effects of atomic oxygen encountered by telescope systems deployed in low earth orbit (LEO is effected by providing an array of multiple very small projections on the interior surface of an open-ended tubular metering shell extending forwardly from a mirror to be protected. The projections are made of material that is geometrically configured to deflect AO atoms one or more times within the shell at angles that ultimately direct the atoms away from the mirror surface and back out through the forward end of the shell.

This invention discloses a multipath error fusion correction method and system based on BeiDou multi-orbit differences. The method includes: collecting BeiDou carrier phase observation data from a reference station and a monitoring station; obtaining double-difference residuals through preprocessing and double-difference calculation, and converting them into single-difference residual sequences; classifying BeiDou satellites into three categories based on their orbital types: geostationary orbit satellites, inclined geosynchronous orbit satellites, and medium Earth orbit satellites; extracting stable background information from the GEO residuals, slowly changing information from the IGSO residuals, and anomalous disturbance information from the MEO residuals by combining satellite azimuth and elevation angle information; constructing a basic hemispherical model based on the stable background information of each satellite, and using the stable background information, slowly changing information, and anomalous disturbance information to constrain and update the basic background correction value, generating the current epoch multipath correction value; and applying the correction value to the corresponding satellite observation value to complete the observation correction and deformation monitoring calculation.

A rocket propulsion and satellite deployment system, comprising a rocket comprising at least a base sector, an operating sector, and a transport sector; the base sector comprises a propellant and is configured to transport the sectors to a mission target; the operating sector comprises a rotating robotic arm pivoted to the operating sector; the transport sector is configured to hold a load intended to be delivered to the target by means of a rotation of the rotating robotic arm with respect to the operating sector, accelerating the load itself which is subsequently released in a direction opposite to the speed of the rocket, increasing, due to conservation of momentum, the speed of the rocket itself. The system is based on a so-called 'useful propellant', consisting of the satellites, rovers and orbiters themselves, which, through the rotational acceleration system, are used to increase the speed of the rocket in space. As well as providing an alternative to traditional propulsion, this system provides an innovative way of putting satellites into orbit, especially in non-earth orbit, which can also be used for longer missions with more than just one target.

A Low Earth orbit (LEO) satellite congestion control routing method is disclosed, including: Step 1: A LEO satellite periodically detecting queue lengths of a plurality of ports and informing a Geostationary Earth Orbit (GEO) satellite of queue lengths of congested ports in the plurality of ports; Step 2: The GEO satellite sending the queue lengths of congested ports to a ground station, and a computing center of the ground station calculating link status weights according to the queue lengths of congested ports; Step 3: According to the link status weights, the computing center of the ground station determining a congestion area; Step 4: The computing center of the ground station calculating a routing table of satellites in the congestion area, and the ground station sending the routing table to a LEO satellite inside the congestion area; Step 5: The LEO satellite in the congestion area receiving the routing table, and performing end-to-end transmission of data packets to a destination LEO satellite according to the routing table.

A global, rapid acquisition, centimeter-level accuracy, high-integrity, space-based positioning service for autonomous ground vehicles, unmanned aerial vehicles (UAS), air taxis, all-weather aircraft precision landing, precision agriculture, and offshore machine control is presented. Low Earth orbit (LEO) constellations of satellites are a means to enhance medium Earth orbit (MEO) global satellite navigation systems (GNSS). An efficient spectrum broadcast “underlay” that enables users to access LEO carrier phase signals and their broad applications. User equipment employs coherent feed forward of the MEO GNSS ambiguous solution to recover the LEO carrier phase broadcast via robust coherent signal processing gain. Subsequently, the LEO carrier phase residuals enable rapid resolution of the unknown carrier phase biases to yield rapid acquisition of high-performance user positioning.

This item is a ground station antenna capable of receiving radio waves from LEO (low earth orbit) satellites.

A kind of relative navigation reference deviation calibration method of star and pulsar information fusion is disclosed, which comprises the following steps: configuring a star angular distance measuring sensor and an X-ray detector on a spacecraft; observing stars by the star angular distance measuring sensor to extract navigation information contained in two kinds of relativistic effects, i.e., star aberration caused by the movement of the spacecraft and light deflection caused by celestial gravitational field; observing pulsars by the X-ray detector to obtain pulse arrival time difference observations; combining spacecraft and earth orbit dynamics model to predict the state; processing star angular distance and pulse arrival time difference observations by an extended Kalman filter to correct the state prediction value, and obtaining the estimation of the spacecraft position and velocity, the geocenter position and velocity, and the sensor system error parameters, so as to realize the calibration of two kinds of reference deviations, i.e., earth ephemeris error and sensor system error. The present application provides a new way to improve the performance of relativistic navigation system.

A space communication system that includes multiple space communication transfer stations strategically positioned outside an earth's orbit. The space communication transfer stations can detect blind spots on earth and quickly transmit signals from spacefaring objects to the earth.

Techniques for a low Earth orbit (LEO) satellite to route data through optimal satellite paths based on latency thresholds (and / or other QoS thresholds) for the application generating the data. The LEO satellite may identify the latency threshold from a data packet, where the latency threshold indicates an amount of time for the data packet to be relayed back down to a destination ground device. The LEO satellite determines available satellite paths through which data packets may be routed to destination ground stations. Further, the LEO satellite may determine latencies for transmitting traffic over the available satellite paths. The LEO satellite may compare the latency threshold for the data packet with the latencies of the available satellite paths, and select a satellite path that is optimal for transmitting the data packet. In this way, LEO satellites intelligently route data through satellite paths based on the type of traffic being transmitted.

The invention discloses a low-orbit narrowband Internet of Things constellation system and method based on satellite processing and hybrid backhaul, and belongs to the technical field of satellite communication. Comprising a space section formed by a plurality of satellites deployed in a specific inclination angle low earth orbit, a ground section provided with a plurality of gateway stations and operation and control centers in a global middle and low latitude area, and a plurality of Internet of Things terminals; wherein the satellite is configured with a communication load with on-satellite processing capability, and is used for receiving and processing an uplink short message sent by the terminal, and adaptively selecting a real-time forwarding mode or a store-and-forward mode to return the processed data to the ground based on the real-time visibility of the satellite and the gateway station. Through optimization design of constellation configuration and combination of on-satellite processing and hybrid backhaul mechanisms, efficient and reliable coverage of global key areas is realized under the condition that inter-satellite links are not needed, terminal power consumption and system complexity and cost are remarkably reduced, and the method is particularly suitable for burst short message services of wide-area distributed Internet of Things.

Described herein are techniques for implementing a low earth orbit (LEO) satellite network and routing communications (e.g., packets) over that network. In embodiments, the techniques may comprise receiving, at a first ground station computing device, a request to determine destination information for a communication, determining, at the first ground station computing device based on information about the communication, a target computing device to which the communication is to be routed, determining, at the first ground station computing based on the target computing device, a location of a destination ground station, determining, at the first ground station computing by mapping orbital data to the location of the destination ground station, a destination satellite, generating the destination information to include at least an address for the destination satellite, and providing the destination information in response to the request.

An innovative Elliptical Low Earth Orbit (eLEO) Satellite Constellation combines the benefits of geostationary (GEO), middle Earth orbits (MEO) and low Earth orbit (LEO) satellites. This hybrid constellation aims to minimize latency and maximize coverage with fewer satellites, reducing capital and operational costs. The design features orbits with LEO-like perigee and extended apogee to optimize visibility and minimize collision risks, enhancing communication capabilities particularly over remote areas. The constellation offers flexible deployment options, including 24, 48 and 96 satellite configurations, tailored to different coverage and budgetary requirements. Strategic advantages include improved data transmission rates, enhanced satellite longevity, and robust support for both civilian and defense applications. This system represents a significant advancement in satellite communication technology, promising to meet diverse global communication needs efficiently.

This invention provides a rapid prediction method for lunar orbit rendezvous guidance, achieving high-precision and rapid prediction to meet mission requirements. The prediction method of this invention applies the gravitational field acceleration calculation method used for GPS autonomous orbit determination of Earth orbit satellites to the field of lunar orbit rendezvous. Addressing the problems that the algorithm cannot be directly applied to the design of lunar orbit rendezvous guidance strategies, improvements and upgrades are made one by one, resulting in a high-precision and rapid algorithm suitable for lunar orbit rendezvous flight control missions to meet mission requirements. Specifically, this invention is the first to transplant this algorithm to the field of lunar orbit applications, which is unprecedented. Considering the special characteristics of the lunar gravitational field, where the acceleration measures of various gravitational perturbations are of similar order and cannot be approximated by the J2 term alone, the J22 term perturbation acceleration is added to the algorithm, thereby significantly improving the computational accuracy and numerical stability of the algorithm.

A space domain awareness (SDA) system includes several sensor spacecraft, some in Earth orbit and others in cislunar space. Each sensor spacecraft can include a sensor payload of an active optical sensor (e.g., a laser emitter and laser detector) and an SDA processor. The processor detects, tracks, and characterizes resident space objects (RSOs) using the output from the active optical sensor. In some embodiments, the sensor payload also includes a passive optical sensor, an electromagnetic sensor, and / or a plasma sensor; the SDA processor can use the outputs of these optional additional sensors to detect, track, and characterize RSOs as well. It is also contemplated that the SDA system can include a plurality of debris capture spacecraft, each of which includes a debris impact pad that includes a series of shield and stuffing layers that respectively increase in density along an intercept direction.

The application relates to the field of low earth orbit battery packaging, in particular to a low earth orbit (LEO) perovskite solar cell packaging structure and process, the structure comprising a docking module and a frame, the module comprising a top sealing layer, an epoxy adhesive layer, a packaging isolation film layer, a battery piece and a substrate layer, and the inner adhesive layer of the frame comprising an epoxy adhesive layer, a fluororubber layer and a chloroprene rubber adhesive layer. The process comprises isolation film material cutting, isolation film material and battery piece bonding, module face sealing, packaging backboard bonding, frame slot insertion after frame slot glue coating, U-shaped frame and one-shaped frame combination, normal temperature curing and excess glue trimming. The sealing stability, space adaptability and stress control of the whole packaging are strengthened, the negative phenomena such as delamination and cracking easily occurring in the space environment are avoided, and the battery piece can keep long-term reliable operation in the extreme environment of high humidity, high frequency and high temperature cycle, and high vacuum.

The present application belongs to the technical field of satellite navigation, and specifically discloses an ionospheric delay correction method of a space-based data driven broadcast ionospheric model. The present application aims to use the occultation observation data of a low earth orbit (LEO) constellation to directly obtain global total electron content (TEC) which is independent of ground stations by integrating from the occultation electron density profile; and to introduce a neural network model to quickly calibrate and optimize the quality of the space-based TEC data; finally, to directly drive the NTCM-G broadcast ionospheric model using the calibrated TEC product which is high-precision and globally uniformly covered, to generate its global broadcast correction coefficients and broadcast them to users. The present application method establishes a new method of realizing a broadcast ionospheric model with space-based data as the core driving source, avoids the limitations of the ground-based observation network from the data source, and improves the autonomy, complete coverage and overall precision of the ionospheric correction service of the global navigation system.

The invention provides a software-defined low earth orbit satellite network service function chain deployment method, and belongs to the technical field of communication networks. Constructing a low earth orbit satellite network model and a service function chain request model; each service function chain request is defined as one agent; each agent comprises a strategy network, a first value network and a second value network; the strategy network outputs a virtual network function deployment action and a route selection action in stages, and the intelligent agent executes the virtual network function deployment action and the route selection action to perform service function chain deployment; action rewards are calculated according to deployment cost and service delay optimization; action rewards and observation information are stored in an experience playback buffer; and randomly extracting a batch of data from the experience return visit cache to update the value network and the strategy network. The high dynamic topology of the low earth orbit satellite network is effectively processed through time expansion graph modeling. And the reward function and the optimization target associate the deployment cost and the end-to-end delay to realize collaborative optimization of the two.

Methods, systems, and devices for communication operations are described. A first satellite may be in a first orbit, and a set of second satellites may be in second orbits that are lower than the first orbit. The second satellites may detect signal components of a signal originating from a geographic area and relay the respective signal components to the first satellite. A beamformer coupled with the first satellite may form a beam associated with the geographic area. The beamformer may also obtain a beam signal based on the respective signal components and a return channel, where the return channel includes at least a channel component between the geographic area and the set of second satellites.

Embodiments herein leverage medium Earth orbit (MEO) satellite signals to increase a likelihood of establishing communication with a low Earth orbit (LEO) satellite. The disclosed embodiments may receive MEO satellite signal data and, in response to determining that the MEO satellite signal data indicates a signal quality below a threshold value, provide an indication to move a user device to get a better signal quality. The disclosed embodiments may also receive a LEO satellite position, and indicate the LEO satellite position to lead a user to move the user device for a better chance to establish communication with the LEO satellite. The disclosed embodiments may determine a time of day based on the MEO satellite signal data, receive light sensor data, and provide an indication to move the user device to an open sky condition to increase the likelihood of establishing communication with the LEO satellite.

The invention discloses a low earth orbit satellite mobile network satellite base station switching method. According to the method, a time interval is initialized and sampled, a satellite orbit parameter and a machine learning signal prediction model are combined, the signal intensity of each satellite at multiple moments in the future is calculated in a prospective mode, and then a switching time interval when a target satellite and a signal intersect is intelligently determined. And the time interval and the interval range are reduced through iteration, and an accurate switching time point is finally determined through successive approximation, so that accurate and smooth switching synchronous with the core network is realized. Compared with the prior art, switching delay and signal interruption can be effectively avoided, and communication quality and user experience are remarkably improved.

This item is a ground station antenna capable of receiving radio waves from LEO (low earth orbit) satellites.

A packet analysis module receives traffic from a Low Earth Orbit (LEO) satellite network system 2 and determines the source of the traffic. When the source of the traffic is a mobile network, the traf

The invention relates to a method for detecting a rollover of a motor vehicle. The invention also relates to a computer device (100) implementing such a method, as well as a motor vehicle (1) comprising such a device (100). Figure for the abstract: 1

The invention discloses a low earth orbit satellite orthogonal time-frequency spatial modulation system channel estimation method and device, and the method comprises the steps: receiving a time domain signal transmitted from a low earth orbit satellite, removing a cyclic prefix and windowing, then sequentially carrying out the Wiener transformation and the ShengFourier transformation, intercepting a preset part, and stacking the preset part into a vector, thereby obtaining a DD domain receiving signal; a DD domain receiving signal is utilized to carry out channel estimation based on a horseshoe-shaped prior variation sparse Bayesian learning channel estimation method, meanwhile, contraction of global variables is adjusted in combination with noise features so as to improve the precision of the channel estimation method, and finally a channel estimation value is obtained. The method is higher in precision.

There is provided a telescope for use in an optical terminal system configured for free space optical communication, FSOC, configured to operate in earth orbit, and / or for terrestrial line- of-sight links. The optical terminal system comprises the telescope and an optical bench. The telescope (200) is configured to receive an incident light beam (500) and to focus the light beam to a telescope focal plane (250) as input to the optical bench. The telescope comprising: a primary mirror; a secondary mirror; and a tertiary mirror. At least one mirror comprises a freeform mirror configured to control the distribution of light in the focal plane to provide correction of wavefront aberrations across a field of view of the system. Also provided is an optical terminal system comprising the telescope and an optical bench.