21 results about "Medium Earth orbit" patented technology

The invention provides a centimeter-level broadcast ephemeris method and device based on a GNSS precise ephemeris, and the method comprises the steps: converting a classical Kepler orbit element into a nonsingular orbit element for the near-zero eccentricity rate of a middle earth orbit satellite; performing fast Fourier transform on a satellite orbit, selecting a certain number of additional parameters from the optional additional parameter set according to a spectral analysis result of the Fourier transform, and combining the additional parameters with an original broadcast ephemeris model to construct a centimeter-level broadcast ephemeris model; interpolating the precise ephemeris to obtain dense ephemeris data points, and determining centimeter-level broadcast ephemeris model parameters; calculating an error in a geocentric inertial coordinate system, converting the error into an orbital coordinate system, and determining the precision of a centimeter-level broadcast ephemeris model by using a space signal ranging error; and broadcasting the centimeter-level broadcast ephemeris model for satellite orbit determination and user high-precision positioning. The method provides support for real-time high-precision satellite positioning application.

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.

Navigation satellite, especially for a Medium Earth Orbit (MEO), with - a case (12), - a navigation antenna (16) connected to the housing (12) for radiating navigation signals in a preferred direction, - an optical communication device (22) for unidirectional or bidirectional signaling with at least one other satellite leading in the direction of movement in the direction of a first communication axis (19) and / or with at least one other satellite trailing in the direction of movement in the direction of a second communication axis (21) and - a holder which is rotatably arranged on the housing (12) about an axis of rotation (17), wherein the axis of rotation (17) is substantially perpendicular to the first communication axis (19) and the second communication axis (21), wherein the holder is directly rotatable about this axis of rotation (17), - wherein the optical communication device (22) is arranged on the holder.

The invention belongs to the technical field of satellite communication, and relates to a rhythmicity sensing method and system for dynamically updating resource information reporting frequency and a readable medium, and the method comprises the steps: automatically detecting the updating state of dynamically updating resource information through a low-orbit satellite, and generating a resource state packet; determining a list sequence and a priority sequence of the low earth orbit satellites through the medium earth orbit satellites; dividing a fixed period into continuous time slots, and distributing a processing sequence of the low-orbit satellites according to a priority sequence; according to the processing sequence of the low-orbit satellites, resource state packets corresponding to the low-orbit satellites are sent in corresponding time slots, and resource information ages are calculated in real time; and if the resource information age exceeds the threshold value, sensing the corresponding low-orbit satellite, and dynamically updating parameters of the sensing method at the next time according to the resource information age. According to the method, the low-orbit satellites report the resource information to the medium-orbit satellites at the non-fixed frequency according to the resource change speed, so that the multi-satellite multi-dimensional resource sensing frequency weighted sum is minimized, and the sensing efficiency is improved.

The present invention relates to a composite shielding method for total radiation dose in medium-orbit space, comprising the following steps: S1. calculating the total radiation dose at any position of a spacecraft in medium-orbit space; S2. calculating the energy loss per unit distance of protons in the material; S3. selecting a shielding material based on the energy loss per unit distance of protons in the material; and S4. coating aluminum with the selected shielding material to construct a composite shielding material for spacecraft radiation protection in medium-orbit space. The method provides reliable protection for spacecraft against the total radiation dose in medium-orbit space at a minimal cost in mass and volume.

Various approaches for the deployment and coordination of network operation processing, compute processing, and inter-satellite communication coordination, within one or multiple satellite non-terrestrial networks, are discussed. Among other examples, a data center located at one or more satellites operating in a middle Earth orbit (MEO) plane, geosynchronous orbit (GEO) plane, or high-Earth elliptical orbit (HEO) plane, may be used to provide network and data processing operations for a low-Earth orbit (LEO) constellation.

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.

A positioning method and device, the method comprising: receiving a first request for requesting positioning; receiving a first signal from a first satellite and a second signal from a second satellite; receiving first information for indicating a first time delay, the first time delay being an ionospheric time delay between the first satellite and the second satellite; and determining a position of a terminal device according to the first signal, the second signal and the first time delay. The method can realize joint positioning of the terminal device based on high medium earth orbit satellites and low earth orbit satellites, help to improve positioning efficiency and positioning accuracy of the terminal device, and can also expand the positioning range as much as possible.

The application provides a kind of low-orbit satellite constellation-oriented computing resource arrangement method, system and equipment, it is related to satellite communication technical field, including: low-orbit satellite receives remote sensing satellite in current time slot under the task set generated, and the computing resource arrangement problem of task set is decomposed into task scheduling subproblem and resource allocation subproblem;Low-orbit satellite models task scheduling subproblem as Markov decision process, utilizes the scheduling strategy network based on deep reinforcement learning to solve Markov decision process, to determine the target low-orbit satellite corresponding to task, and issues task to target low-orbit satellite;Low-orbit satellite models resource allocation subproblem as convex optimization process, utilizes Lagrange multiplier algorithm to solve convex optimization process, to allocate target computing resource for the task received by low-orbit satellite.The application can significantly improve the problem of task demand diversification, satellite resource limited heterogeneity and satellite load imbalance in low-orbit satellite constellation.

This application provides a routing method and related equipment. The method includes: constructing a satellite link topology based on the spatial geometric attributes of an Earth orbit constellation acquired within an operational cycle; determining the satellites visible to a destination node within a frame based on the acquired service information of the source node and the topology; determining routing information based on the visibility of the source node to the destination node; and transmitting services based on the routing information. Embodiments of this application rationally plan the topology through inter-satellite spatial geometric relationships, establishing a dynamically changing topology matrix. Based on this dynamically changing topology matrix and relying on a routing mechanism that runs through the dynamic topology in the time domain, stable data transmission between nodes under a highly dynamic topology structure is achieved.

A satellite communications (satcom) terminal apparatus includes an active electronically scanned array (AESA) having stowed and deployed configurations and attachable atop a mobile platform or other flat surface. The AESA comprises a set of panels, each panel a subarray of AESA elements. A set of side panels are attached to a flat surface and an apex panel attached to the top edge of each side panel. When stowed, the apex and side panels lie flat (e.g., for geostationary earth orbit (GEO) operations). When deployed, the side panels and apex panel form a truncated pyramid with a hemispherical field of view for middle earth orbit (MEO) or low earth orbit (LEO) operations. The side panels may be pivoted to any desired slant angle and each subarray panel configured for transmission or reception of electromagnetic energy at a desired frequency or polarization, enabling simultaneous mobile operations with multiple satellites or constellations.

The application relates to a medium earth orbit (MEO) multi-channel SAR ground moving target motion parameter estimation method and belongs to the field of radar signal processing. A signal model of a distance equation of a first channel and a second channel of MEO SAR based on third-order Taylor expansion is established, a first-order phase coefficient, a second-order phase coefficient, a third-order phase coefficient and an intermediate parameter are estimated based on a CPF method, along-course velocity and radial acceleration in the second-order phase coefficient are adjusted by combining multi-channel information, and along-course velocity, radial velocity, along-course acceleration and radial acceleration of the target are estimated based on a coupling relationship. The method solves the problem of difficult motion parameter estimation of a moving target caused by the coupling relationship.

This application proposes a testing method and apparatus for a satellite simulation demonstration system. The testing method includes: dividing different physical orbit regions based on the orbital characteristics of low Earth orbit, medium Earth orbit, and high Earth orbit; defining the spatial boundary coordinates and simulation coverage of the simulation layered regions according to the altitude range and orbital characteristics of each physical orbit region; dividing the satellite cluster into multiple satellite groups; configuring corresponding functional testing strategies and performance parameter acquisition strategies for each simulation layered region based on the number, spatial distribution, and on-orbit trajectory of the satellite clusters corresponding to each simulation layered region; generating a general simulation scenario compatible with both functional and performance testing; simultaneously acquiring the functional and performance test items corresponding to the general simulation scenario; and determining whether the overall operating condition of the general simulation scenario meets the preset test requirements. The technical solution of this application can accurately and comprehensively determine the overall operating condition of the system, improving testing accuracy and reliability.

The invention discloses an SSA image compression distributed task unloading method based on double-layer hybrid satellite nodes, and the method comprises the steps: constructing a hierarchical satellite control structure composed of a bottom-layer LEO satellite calculation node and an upper-layer centralized medium orbit (MEO) satellite control node, and solving an unloading task of the hierarchical satellite control structure based on an orbit dual depth Q network; an optimized task unloading decision is obtained, and the end-to-end delay of the task is minimized. According to the low earth orbit (LEO) satellite image sparse coding method, aiming at a low earth orbit (LEO) satellite image sparse coding task, the transmission data volume is obviously reduced and the overall efficiency of a data link is improved by optimizing task unloading, so that the task processing capability of a constellation system under a limited resource condition is enhanced, compression and coding tasks can be flexibly distributed among a plurality of LEO satellite nodes, and the complexity of a constellation system is reduced. Therefore, available resources are utilized to the maximum extent, task processing is accelerated, and system execution efficiency and response speed are integrally improved.

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.

The application relates to the technical field of satellite communication, in particular to a dynamic beam adjustment system for medium and low orbit satellite communication. The system comprises a beam demand perception unit, a dynamic beam calculation unit, a beam execution adjustment unit and a satellite-ground coordination unit. The dynamic beam calculation unit offsets the influence of complex environment on beam coverage through a multi-factor collaborative compensation mechanism. The beam execution adjustment unit realizes accurate beam pointing and interference suppression through an adaptive phase optimization algorithm. The application calculates the theoretical pointing angle of the beam based on spherical geometry, determines the compensation amount in combination with satellite movement, user movement and atmospheric refraction, dynamically adjusts the weight of each compensation amount and combines the compensation amounts into a total compensation amount according to the satellite elevation angle, user terminal movement speed and communication link signal-to-noise ratio, and finally obtains the actual beam pointing angle, so that the coupling influence of multi-factors on beam coverage in complex environment is effectively offset, and the beam pointing precision is improved.

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 relates to a forbidden zone avoidance method for a shipborne communication-in-motion antenna of a medium orbit satellite and the antenna. The method comprises the following steps: determining a safety angular distance corresponding to a forbidden area based on the transmitting power of a communication-in-moving antenna on a ship, the minimum space distance between the forbidden area and the communication-in-moving antenna, and a preset power density threshold and a preset graph gain function corresponding to the forbidden area; by taking the safety angular distance as a reference, performing external expansion on the spherical polygonal area corresponding to the forbidden area in the normal direction to obtain a forbidden area projection corresponding to the forbidden area; if the satellite direction of the medium orbit satellite falls into the forbidden zone projection, generating a reference attitude trajectory of the communication-in-moving antenna by taking a target point as a base point; the target point is a point which has the minimum angle distance with the satellite direction on the spherical surface in the boundary of the projection of the forbidden zone. By adopting the method, the electromagnetic exposure can be controlled within a safety threshold value while the communication continuity and the link quality are ensured.

1. The name of the design product: the middle rail satellite ground station rack type time system server. 2. The use of the design product: providing network time service for internal network equipment by obtaining satellite time data. 3. The design points of the design product: in shape. 4. The picture or photo that best indicates the design points: perspective view 1.

The invention provides a satellite Internet of Things system, a construction method, an application method and a storage medium, and a satellite constellation in the system comprises a perception application satellite used for collecting multi-source monitoring data and transmitting the multi-source monitoring data to a network transmission satellite; the network transmission satellite is used for transmitting the multi-source monitoring data to the calculation storage satellite; the calculation storage satellite is used for carrying out real-time preprocessing on the multi-source monitoring data and sending a data processing result to the ground station; the sensing application satellite is deployed at the top of a low earth orbit or a near space, the network transmission satellite is deployed at a middle earth orbit or a GEO adjacent orbit, the calculation storage satellite is deployed at a geosynchronous orbit, and laser links are respectively established between the network transmission satellite and the sensing application satellite and between the network transmission satellite and the calculation storage satellite. Through satellite function decoupling and reconstruction deployment, the reliability of the system is improved, wide-area coverage space complementing is realized, an emerging Internet of Things industry support is formed, and emergency communication guarantee requirements are met.

A satellite system is disclosed including a plurality of optical modems with digital signal processing circuitry supporting programmable modulation formats. A processor assigns subsets of the modems to establish inter-satellite links and ground links, and selects modulation formats based on link performance requirements such as connection distance and bandwidth demand. The system enables an express mesh inter-satellite topology, providing direct optical links among satellites positioned according to ground traffic sources and sinks, thereby reducing the number of hops, network latency, and power consumption. The processor may further adjust forward error correction coding, transmitted optical power, and wavelength allocation to optimize link performance. Satellites may dynamically reassign modems, power down unused modems, and operate in Low Earth Orbit (LEO) or Medium Earth Orbit (MEO). The disclosed methods and architectures allow efficient, low-latency satellite networking through coherent optical communications adaptable to evolving traffic patterns and environmental conditions.