164 results about "Geosynchronous orbit" patented technology

A weather briefing system that may be used in the cockpit to provide near real-time graphic and text weather information. Weather information and pilot reports are fed to the cockpit from, e.g., a satellite in geosynchronous orbit. Once delivered to the aircraft, the system processes the data stream and formats it for delivery to an end user device. The data is collected from an extensive network of sources. The end user device may be a portable electronic flight bag (EFB), panel-mounted display (MFD), or similar device programmed to display the formatted data. The system provides timely and accurate weather information to pilots of all types of aircraft. This information may be used for pre-flight planning and in-flight decision-making.

The invention relates to a method for optimizing an orbital transfer strategy of a geostationary orbit satellite, which comprises the following steps of: 1, determining orbital transfer times, orbital transfer circle times and the controlled variable of each-time orbital transfer; and 2, determining time and a thrust direction in each-time orbital transfer. The process of launching the geostationary orbit satellite at present generally comprises the following steps of: launching the satellite into a highly elliptic transfer orbit with an inclination angle by using a carrier rocket; performing apogee/perigee orbital transfer for several times by using a self-contained liquid engine of the satellite, and transferring to a geosynchronous orbit; and correcting and rounding the inclination angle of the orbit to realize a geostationary orbit. For the satellite, operation for changing the transfer orbit into the geostationary orbit by performing apogee/perigee orbital transfer for several times is complex, so too many orbital transfer times is not suitable, and orbital transfer complexity and risk are prevented from being increased; in addition, factors such as the capacity of the liquid engine of the satellite, arc segment loss in an orbital transfer period, and the like are considered, so too few orbital transfer times is not suitable.

A fire detector is disclosed that successively images a particular area from geosynchronous Earth orbit satellite to attain very good signal-to-noise ratios against Poisson fluctuations within one second. Differences between such images allow for the automatic detection of small fires greater than 12 square meters. Imaging typically takes place in transparent bands of the infrared spectrum, thereby rendering smoke from the fire and light clouds somewhat transparent. Several algorithms are disclosed that can help reduce false fire alarms, and their efficiencies are shown. Early fire detection and response would be of great value in the United States and other nations, as wild land fires destroy property and lives and contribute around five percent of the US global carbon dioxide contribution. Such apparatus would incorporate modern imaging detectors, software, and algorithms able to detect heat from early and small fires, and yield detection times on a scale of minutes.

The invention discloses a geosynchronous orbit constellation orbit determination method based on ground station/satellite link/GNSS combined measurement. The method comprises the steps of (1) establishing the state equation of a GSO constellation orbit determination system in a centralized structure, (2) establishing the measurement equation of the GSO constellation orbit determination system in a centralized structure, (3) carrying out combined optimization of a ground station for orbit determination and GNSS measurement combination, (4) determining the filtering method for realizing orbit parameter estimation according to the above established GSO constellation combined orbit determination system model based on ground station/satellite link/GNSS, and (5) carrying out the concrete realization of a GSO constellation orbit determination method based on ground station/satellite link/GNSS in the centralized structure. According to the method, the combined distribution optimization strategy of ground station and GNSS measurement is established based on a precision factor, and the calculation amount is reduced while the orbit determination precision is ensured.

The invention discloses a double-layer topology routing method based on a satellite communication network design. The method comprises the steps of: constructing a double-layer satellite network constellation system, grouping satellites, calculating a routing path in a geosynchronous orbit and a low earth orbit, and assessing the performance of inter-satellite link routing via end-to-end delay and packet loss rate of data sent via the routing path; calculating a valid link and an availability weight of a satellite network according to the geographic position of a satellite node, the number of hops required by a source-to-destination calculation path and the congestion situation of the inter-satellite link; calculating the total cast for inter-satellite link data transmission in combination with the weight of a low earth orbit satellite initial calculation link and the availability weight of the source-to-destination satellite node; and screening a geosynchronous orbit satellite meeting the service requirement according to the business of low earth orbit satellites and the complexity of the routing path to participate in data transmission. The method can establish a valid path and balance the data transmission demand and the end-to-end delay, thereby optimizing the network performance.

Geosynchronous surveillance is conducted by injecting one or more observer satellites into a retro sub or super geosynchronous orbit at approximately zero inclination. The observer satellite spins about an approximately North-South axis in an Earth frame of reference to sweep a sensor's FOV around the geobelt. Sensor time delay integration (TDI) is synchronized to the observer satellite's spin-rate and possibly the sum of the spin-rate and the target inertial LOS rate to realize longer integration times. This approach facilitates faster scans of the entire geobelt, more timely updates of the catalog of tracked objects and resolution of small and closely spaced objects. An inexpensive small-aperture body-fixed visible sensor may be used.

A method and apparatus for a non-geosynchronous orbit (NGSO) satellite to comply with equivalent power flux density (EPFD) limits are disclosed. The example implementations may allow a constellation of NGSO satellites to comply with EPFD limits without disabling beams transmitted from the NGSO satellites. The power level of one or more beams to be transmitted from the NGSO satellites may be dynamically adjusted according to a beam power back-off schedule. In some aspects, the beam power back-off schedule may specify beam power back-off values as a function of latitude on Earth, and may allow for maximum allowable power levels for beams transmitted from the NGSO satellites without violating any of the EPFD percentile limits.

The invention relates to a method for focusing a geo-synchronization orbit synthetic aperture radar (GEO SAR) in high precision, and belongs to the technical field of radar signal processing. An error of a 'Stop-and-Go' supposition is taken into consideration and applied to a deduction process of an algorithm. Aiming at the problem that a typical low earth orbit synthetic aperture radar (LEO SAR) algorithm cannot process a false equivalent linear model, a norm is adopted to express an inclined distance and high-precision approximation is executed. By the method, the imaging precision is high; the method is applicable to imaging at an ultralong synthetic aperture time; high distance migration and boundedness of the equivalent linear model are overcome; and the problem that the LEO SAR imaging algorithm cannot process the 'Stop-and-Go' supposition is solved.

A bistatic passive radar system for tracking at least one target utilizing means for transmitting radar signals from at least one satellite platform in a geosynchronous orbit with the earth, means for receiving radar signals from a reflection from each target, means for tracking a position of each target over time, and means for computation of a fire control solution of each target.

The invention provides an elevation inversion method for geosynchronous orbit synthetic aperture radar interference. The method comprises the steps that step 1, GEO SAR is selected to obtain a track of interference data, and the interference data on the track are collected; step 2, GEO SAR imaging processing is conducted through a BP algorithm according to the interference data obtained in step 1; step 3, a GEO interference model is built according to the GEO SAR image processed in step 2, and when a phase position vector is separated from an imaging plane, the GEO SAR interference elevation inversion is conducted according to the GEO interference model. According to the elevation inversion method for the geosynchronous orbit synthetic aperture radar interference, due to the fact that the reasonable GEO SAR interference model is built, the effective elevation inversion processing under the condition that the phase position vector and the imaging plane are separated is achieved, the core problem of the elevation inversion of the GEO SAR interference processing, namely, the separation problem of the effective phase position vector and the imaging plane is solved, and the elevation inversion of the GEO SAR interference processing at any position is achieved.

Momentum control is maintained in a geosynchronous orbiting spacecraft that uses a plurality of reaction wheel assemblies and a plurality of magnetic torquers to control the spacecraft momentum, each orbit of the spacecraft being comprised of a set of time steps, by determining a current momentum error for a current time step of a current orbit by adding a system momentum change determined for an immediately preceding orbit to an average system momentum determined for the immediately preceding orbit, and then subtracting a magnetic control torque momentum change determined for the immediately preceding orbit, determining a current duty cycle for each of the magnetic torquers based on the current momentum error and on a torque value applied by each magnetic torquer at each time step of the immediately preceding orbit, and commanding each magnetic torquer to operate at the current time step in accordance with its respective determined current duty cycle, wherein the magnetic torquers apply a magnetic momentum control torque to the spacecraft to offset the current momentum error.

A geosynchronous Solar Power Satellite System is created by an artificial gravity, closed ecology, multiple use structure in low earth orbit that manufactures modular solar power panels and transmitter arrays. This facility takes empty fuel tanks and expended rocket boosters from launch vehicles that are sent into low earth orbit, and re-manufactures them into structural components. These components are mated to solar cells that are launched from earth. The modular solar panels are transported to geosynchronous orbit by vehicles with ion engines, where the panels are mated to other solar panels to collect power. Structural components are also mated to transmitter elements launched from earth. These are likewise transported to geosynchronous orbit. They are mated to the solar power collecting panels and they beam the collected power back to earth.

The invention discloses a method for generating a B code of a time signal of a synchronizing clock of Beidou satellite. The method is characterized by comprising the following steps: a. a Beidou satellite signal is received as the time source of a time synchronizing clock; b. the time signal is subject to maintenance processing to generate a DC B code signal; and c. the generated DC B code is utilized to perform amplitude modulation to generate an AC B code signal. The method has the advantages that as IRIG-B receives the Beidou satellite signal and Beidou navigation system is completely controlled by China, devices have high safety; as the Beidou satellite is positioned on a geosynchronous orbit and does not involve inter-satellite switching, the time service system is good and the time service precision is high; as the time processing part of the IRIG-B adopts a time maintenance technology, the IRIG-B can judge the correctness of the time information output by a Beidou receiving module and maintain the time by self when the Beidou satellite signal is unavailable, therefore the correctness of the time information generated by the IRIG-B can be ensured, and the availability of the system is improved.

The invention relates to a method for reducing satellite communication system switching delay, in particular to a switching method for spot beams in the same gateway station of a geostationary orbit satellite. In the method, a switching position area is acquired by using the position information of a mobile terminal of a satellite communication system and combining historical measurement information; the possibly-spanned switching position area is pre-judged according to a navigation path; a velocity vector of the current mobile terminal is acquired by combining a digital map, if the time when the mobile terminal travels to the switching position area from the current position is less than a certain threshold value, pre-switching is completed and finally, switching confirmation is carried out through measurement. Through the adoption of the method, the satellite beam switching delay can be reduced greatly, and in addition, the switching ping-pong effect can be reduced.

Disclosed is a sub-satellite point circular geosynchronous orbit design method. The method includes: (1) analyzing and determining sub-satellite point circular geosynchronous orbit generating conditions including that (1.1) an orbital semi-major axis is 42164km, (1.2) a satellite drifts back and forth in the north-south direction every day, (1.3) the satellite drifts back and forth in the east-west direction every day, (1.4) the distance of north-south direction drift is equal to that of east-west direction drift, and (1.5) the satellite passes the equator twice every day with relative distance of sub-satellite points when the satellite passes the equator twice equal to east-west direction drift distance of the satellite; (2) according to the conditions in the step (1), determining orbital parameters, satisfying the five conditions at the same time, namely the orbital semi-major axis a, eccentricity ratio e, inclination angle i, right ascension of ascending node Omega, argument of perigee omega and true anomaly theta. Design of a sub-satellite point circular geosynchronous orbit is completed by utilizing the determined orbital parameters.

The invention relates to an improved NCS (Nonlinear Chirp Scaling) imaging algorithm suitable for a geosynchronous orbit (GEO) SAR (Synthetic Aperture Radar), belonging to the technical field of SAR imaging. The NCS imaging algorithm is improved by establishing a curved locus signal model for replacing an equivalent linear model in an original NCS imaging algorithm and evaluating a two-dimensional resolving spectrum expression suitable for the NCS imaging algorithm on the basis of the established curved locus signal model. Compared with the prior art, the improved NCS imaging algorithm has the advantages that: a novel curved locus model suitable for the GEO SAR is obtained with a high-order Taylor expansion method, and the defects of large error of a near equivalent linear model, completely unavailable application of a far equivalent linear model and the like of the GEO SAR can be overcome by adopting the locus model; and meanwhile, a two-dimensional resolving spectrum suitable for the NCS algorithm is obtained on the basis of the equivalent linear model, and various compensation functions of the NCS algorithm can be resolved by using the spectrum, so that the requirement on large-scene imaging of the GEO SAR is met.

A method and apparatus for operating one or more satellites in a non-geosynchronous orbit (NGSO) satellite constellation are disclosed. In some aspects, a coverage area on Earth for a first beam transmitted from a first satellite in the NGSO satellite constellation may be determined, a cone may be projected onto a first region of the beam coverage area, a second region of the beam coverage area may be defined as including portions of the beam coverage area lying outside the first region, and a minimum arc angle for each of a plurality of points within the first region but not the second region of the beam coverage area may be determined.

The invention discloses a hopping pattern optimization method and device based on a time slot allocation algorithm, and a storage medium. The method comprises the following steps: determining a distance threshold according to a relationship between a calculated signal to interference plus noise ratio (SINR) and a distance between beams; constructing a time slot allocation model according to the relationship between the capacity resources and the time slot resources in the downlink of the hopping beam satellite system; obtaining the request capacity of a user in each beam coverage range, and converting the request capacity into the number of request time slots; and for the number of request time slots, adopting a time slot allocation model to allocate the number of time slots for each beam,and completing optimization of a hopping beam pattern according to an interference avoidance principle. By adopting the method and the device, efficient time slot resource allocation can be realizedin a GEO (Geosynchronous Orbit) satellite communication system, and the influence of interference on signal quality is effectively eliminated while the system capacity is improved.

The invention provides a satellite network architecture with a network reconstruction capability. The architecture comprises a space-based network and a land backbone network, the space-based networkcomprises a space-based backbone network, a space-based access network and a space-based sensing network, wherein the space-based backbone network is mainly composed of geosynchronous orbit satellites, the space-based access network is mainly composed of low-orbit satellite constellations, and the space-based sensing network is mainly composed of any one or any combination of remote sensing satellites, meteorological satellites and navigation satellites. The method has the beneficial effects that the architecture design problem of a space-based information network for joint networking and fusion utilization of high, medium and low orbit satellites and cooperative work of communication, navigation and remote sensing satellites is solved, integrated utilization of various satellite resourcesin the existing space is realized, and a hybrid heterogeneous satellite network architecture with a satellite network flexible reconstruction function is built.

The invention discloses a GEO (Geosynchronous orbit)-UAV (unmanned aerial vehicle) Bi-SAR (synthetic aperture radar) route planning method based on differential evolution. The GEO-UAV Bi-SAR route planning method based on differential evolution comprises 1) generating a three dimensional landform; 2) modeling a UAV accepting station route; 3) modeling the route planning as a multiobjective optimization problem for a constraint condition; 4) utilizing a multiobjective differential evolution algorithm to solve; and 5) obtaining the optimal solution, generating a UAV optimal path, and realizing autonomous navigation and Bi-SAR imaging of the UAV in the three dimensional complicated landform. The GEO-UAV Bi-SAR route planning method based on differential evolution models the UAV route planning problem which comprehensively considers the route length, the flight safety and the SAR imaging performance as a multiobjective optimization problem, and utilizes the improved differential evolution algorithm to solve and obtain a set of optimal UAV accepting station flight routes.

A mobile satellite telecommunications system is disclosed including at least one user terminal, at least one satellite in earth orbit, and at least a gateway bidirectionally coupled to a data communications network wherein a user terminal comprises a controller responsive to applications for selecting individual ones of a plurality of Quality of Service modes for servicing different application requirements.

The invention discloses a geosynchronous orbit synthetic aperture radar velocity spatial variability compensating method. According to the method, the velocity spatial variability is compensated through self-adaptive phase compensation processing, so that a core problem, i.e. a velocity spatial variability compensation problem, of geosynchronous orbit synthetic aperture radar (GEO SAR) large-scale scene imaging is solved, the GEO SAR large-scale scene imaging focusing processing of arbitrary position is realized, and a good effect is obtained.