Space Orbit Or Path Patents (Class 701/531)
  • Patent number: 9344182
    Abstract: The present invention relates to satellite systems and more particularly, to the provision of a satellite system for weather and climate monitoring, communications applications, and scientific research at higher latitudes, referred to as the circumpolar region and defined here as the area with latitudes greater than 60°, in either the northern hemisphere or the southern hemisphere. Contrary to the teachings in the art it has been discovered that a satellite system and method may be provided using satellites in 24 sidereal hour orbits (geosynchronous) with inclinations (70° to 90°), orbital planes, right ascensions and eccentricities (0.275-0.45) chosen to optimize coverage of a particular service area located at high latitudes. A constellation of two satellites can provide continuous coverage of the circumpolar region. The satellites in this orbit avoid most of the Van Allen Belts.
    Type: Grant
    Filed: September 30, 2011
    Date of Patent: May 17, 2016
    Assignee: TELESAT CANADA
    Inventors: Andre E. Bigras, Peter Megyeri, Jack Rigley, Alireza Shoamanesh, Paul Ng, Surinder Pal Singh
  • Patent number: 9026365
    Abstract: A method of determining the appropriateness of satellite orbit modeling is provided. The method includes calculating values of parameters, that the predetermined model has, on the basis of predicted position data including a first predicted position at a first point of time and a second predicted position at a second point of time of a positioning satellite in time series, calculating a first and a second calculated positions of the positioning satellite derived from the predetermined model by using the values of the parameters; and determining the appropriateness of the predetermined model using the values of the parameters, on the basis of first difference between the first predicted position and the first calculated position, and seconded difference between the second predicted position and the second calculated position. The predetermined model is used when approximating a satellite orbit of the poisoning satellite.
    Type: Grant
    Filed: February 29, 2012
    Date of Patent: May 5, 2015
    Assignee: Seiko Epson Corporation
    Inventor: Kenji Onda
  • Patent number: 9014964
    Abstract: A navigation apparatus is capable of image-capturing and is used to implement a navigation method including the steps of: a) obtaining current location information associated with the navigation apparatus, and location information of a reference target along a planned route that is being traversed; b) capturing real-time navigation images of the planned route according to an image-capture configuration parameter; c) obtaining a display screen position associated with the reference target with reference to the current location information, the target location information, and the image-capture configuration parameter; and d) showing on the display device the navigation images together with a mark corresponding in position to the display screen position.
    Type: Grant
    Filed: April 20, 2011
    Date of Patent: April 21, 2015
    Assignee: Mitac International Corp.
    Inventor: Hsing-Ping Kuo
  • Patent number: 8972184
    Abstract: An apparatus and method for determining an orbit of a geostationary satellite is provided. The orbit of the geostationary satellite may be determined using at least one pseudo-range of the geostationary satellite calculated based on an orbit and a position of at least one global positioning system (GPS) satellite, position information of the geostationary satellite, and an angle between the geostationary satellite and each GPS satellite.
    Type: Grant
    Filed: March 14, 2013
    Date of Patent: March 3, 2015
    Assignee: Electronics and Telecommunications Research Institute
    Inventors: Yoo La Hwang, Byoung Sun Lee
  • Patent number: 8954207
    Abstract: A method of enhancing on-board state estimation for a spacecraft utilizes a network of assets to include planetary-based assets and space-based assets. Communication signals transmitted from each of the assets into space are defined by a common protocol. Data is embedded in each communication signal transmitted by the assets. The data includes a time-of-transmission for a corresponding one of the communication signals and a position of a corresponding one of the assets at the time-of-transmission. A spacecraft is equipped to receive the communication signals, has a clock synchronized to the space-wide time reference frame, and has a processor programmed to generate state estimates of the spacecraft. Using its processor, the spacecraft determines a one-dimensional range from itself to at least one of the assets and then updates its state estimates using each one-dimensional range.
    Type: Grant
    Filed: September 6, 2013
    Date of Patent: February 10, 2015
    Assignee: The United States of America as Represented by the Administrator of the National Aeronautics and Space Administration
    Inventors: Evan John Anzalone, Jason C. H. Chuang
  • Patent number: 8930088
    Abstract: The present invention provides methods for positioning at least one component, in particular a seat, in or on an aircraft or spacecraft comprising the following steps: controlling at least one light source of the aircraft or spacecraft to display at least one desired position of at least one component; and positioning the at least one component in the at least one desired position displayed.
    Type: Grant
    Filed: December 15, 2010
    Date of Patent: January 6, 2015
    Assignee: Airbus Operations GmbH
    Inventors: Hans-Achim Bauer, Andre Zybala
  • Patent number: 8825236
    Abstract: A method of determining the reliability of long-term predicted orbit data, includes: determining the reliability of long-term predicted orbit data, which is acquired by predicting a satellite orbit in a target period of at least one day, using predicted position data including predicted positions of a positioning satellite in time series and actual position data including actual positions of the positioning satellite corresponding to the predicted positions.
    Type: Grant
    Filed: October 9, 2009
    Date of Patent: September 2, 2014
    Assignee: Seiko Epson Corporation
    Inventor: Kyoichi Tomita
  • Patent number: 8782055
    Abstract: A geospatial object property assessment apparatus comprises a processing resource (102) arranged to support a geospatial object property processor (206) comprising a subject data source input (212) capable of receiving a first metadata associated with 10 quality of current source information content used to define a property (408) of a geospatial object; a resource data source input (214) capable of receiving a second metadata associated with quality of candidate resource information content for updating the definition of the property (408) of the geospatial object.
    Type: Grant
    Filed: April 23, 2010
    Date of Patent: July 15, 2014
    Assignee: TomTom North America, Inc.
    Inventors: Terry William Johnson, Peter Aloysius Moeykens, Patricia Jane Lawler
  • Patent number: 8781652
    Abstract: An amount of propellant remaining in an orbiting satellite can be estimated in a more accurate manner than is possible with conventional approached. Pressure and temperature telemetry data received from the satellite can be analyzed using a maximum likelihood estimation approach that reconstructs a predicted tank pressure signal using the temperature data and determines a pressurant volume necessary to make the reconstructed pressure signal match the received pressure signal. Drift of the pressure data received from pressure transducers in the satellite can also be addressed using the current subject matter, as can issues including but not limited to inaccessible propellant due to satellite spin, tank expansion under pressure, and the like. Independent determinations of the amounts of propellant remaining can be made using moment of inertia calculations in situations in which an axis of spin of the satellite is known a priori.
    Type: Grant
    Filed: July 27, 2012
    Date of Patent: July 15, 2014
    Assignee: LinQuest Corporation
    Inventor: Hoai Xuan Vu
  • Patent number: 8781741
    Abstract: A method of generating orbital transfers for spacecraft. The method provides an innovative technique for transferring spacecraft from one Earth orbit to another Earth orbit using significant solar gravitational influences. In one particular implementation, the multi-bodies in the transfer determination are the Earth (about which the spacecraft is to orbit) and the Sun (e.g., the Earth and the Sun are the first and second celestial bodies providing multi-body dynamics). The transfer orbit or trajectory is determined to make use of efficient tangential maneuvers by leveraging solar gravitational influences to improve transfer performance. Based on the generated transfer orbit, the spacecraft is controlled to perform one or more maneuvers to achieve a transfer orbit that traverses into a regime where the spacecraft's trajectory is significantly affected by gravity from both the Sun and the Earth. The spacecraft performs a near-tangential orbit insertion maneuver to enter the final orbit.
    Type: Grant
    Filed: March 22, 2012
    Date of Patent: July 15, 2014
    Assignee: Geryon Space Technologies
    Inventor: Bradley Cheetham
  • Patent number: 8768622
    Abstract: A technique to assist guidance techniques for a free-flying inspection vehicle for inspecting a host satellite. The method solves analytically in closed form for relative motion about a circular primary for solutions that are non-drifting, i.e., the orbital periods of the two vehicles are equal, computes the impulsive maneuvers in the primary radial and cross-track directions, and parameterizes these maneuvers and obtain solutions that satisfy constraints, for example collision avoidance or direction of coverage, or optimize quantities, such as time or fuel usage. Apocentral coordinates and a set of four relative orbital parameters are used. The method separates the change in relative velocity (maneuvers) into radial and crosstrack components and uses a waypoint technique to plan the maneuvers.
    Type: Grant
    Filed: September 16, 2013
    Date of Patent: July 1, 2014
    Assignee: The United States of America, as represented by the Secretary of the Navy
    Inventor: Liam M. Healy
  • Patent number: 8743064
    Abstract: A computing apparatus and method of manipulating a displayed orbit of an object by detecting a gesture having a correspondence between body movements as the gesture and a resulting change to one or more orbital parameters within a displayed orbit system, changing an orbital parameter of the displayed orbit system according to detection of the gesture, and changing visualization on the computer display screen of the orbit system according to the change to the orbital parameter.
    Type: Grant
    Filed: September 16, 2011
    Date of Patent: June 3, 2014
    Assignee: A.I. Solutions, Inc.
    Inventors: Robert William Conde, Stefan Novak, Paige Thomas Scaperoth, Jonathan C. Ruel
  • Publication number: 20140100778
    Abstract: A first position of a satellite is calculated at a first time in dependence on received orbit data corresponding to an orbit path of the satellite. An orbit path of the satellite is modeled from the first position at the first time to a second time to determine a second position of the satellite at the second time. A third position of the satellite is then calculated at the second time in dependence on the received orbit data. The second position and third position are compared to determine a validity of the orbit data.
    Type: Application
    Filed: December 13, 2013
    Publication date: April 10, 2014
    Applicant: STMICROELECTRONICS (RESEARCH & DEVELOPMENT) LIMITED
    Inventor: Peter Bagnall
  • Patent number: 8676501
    Abstract: An improved approach to satellite-based navigation (e.g., GPS) is provided. In one embodiment, a method includes receiving a first set of tracking information. A nominal orbital path for the navigation satellite is determined using the first set of tracking information. Ephemeris data corresponding to the nominal orbital path is computed and uploaded to the navigation satellite. Long-term navigation information corresponding to the nominal orbital path is transmitted to a communication system for broadcast to a plurality of navigation devices. A second set of tracking information is received, an orbital path of the navigation satellite using the second set of tracking information is predicted, and a difference between the predicted orbital path and the nominal orbital path is determined. Commands configured to instruct the navigation satellite to adjust an actual orbital path of the navigation satellite to substantially conform to the nominal orbital path are uploaded to the navigation satellite.
    Type: Grant
    Filed: December 22, 2006
    Date of Patent: March 18, 2014
    Assignee: The Boeing Company
    Inventors: Jonathan A. Tekawy, Raymond S. DiEsposti, Clifford W. Kelley
  • Patent number: 8655589
    Abstract: A motion of an object is controlled from a geostationary transit orbit (GTO) of an earth to an orbit of a moon. A first trajectory of the motion of the object is determined from an intermediate orbit of an earth to a neighborhood of a stable manifold of a first Lagrange point (L1). A second trajectory of the motion of the object is determined from the GTO to the intermediate orbit. A third trajectory of the motion of the object is determined from the neighborhood to the stable manifold to an L1 orbit, and a fourth trajectory of the motion of the object is determined from the L1 orbit to the orbit of the moon. A trajectory from the GTO to the orbit of the moon is determined based on a combination of the first, the second, the third, and the fourth trajectories.
    Type: Grant
    Filed: March 30, 2012
    Date of Patent: February 18, 2014
    Assignee: Mitsubishi Electric Research Laboratories, Inc.
    Inventors: Piyush Grover, Christian Andersson
  • Patent number: 8620580
    Abstract: The invention relates to a navigation systems and elements. A network element (M) includes a receiver (M.2.2) for forming assistance data relating to at least one navigation system. The network element (M) inserts indication of the navigation system and a selected mode into the assistance data and constructs the assistance data according to the selected mode. The network element (M) has a transmitting element (M.3.1) for transmitting the assistance data via a communications network (P) to a device (R). The device (R) includes a positioning receiver (R.3) for performing positioning on the basis of one or more signals of the at least one satellite navigation system; a receiver (R.2.2) for receiving the assistance data from the network element (M); and an examining element (R.1.1) adapted to examine the received assistance data. The assistance data is adapted to be used by the positioning receiver for performing positioning of the device (R).
    Type: Grant
    Filed: February 28, 2006
    Date of Patent: December 31, 2013
    Assignee: Nokia Corporation
    Inventors: Kimmo Alanen, Lauri Wirola, Jari Syrjarinne
  • Patent number: 8600676
    Abstract: A flight dynamics subsystem (FDS), a velocity increment calculation module, and operational methods of the same are provided. A used fuel quantity actually used in a satellite is calculated, and a velocity increment is calculated using the calculated fuel quantity. Therefore, an orbit of the satellite may be estimated more accurately.
    Type: Grant
    Filed: December 22, 2011
    Date of Patent: December 3, 2013
    Assignee: Electronics and Telcommunications Research Institute
    Inventors: Yoo La Hwang, Byoung Sun Lee, Soo Jeon Lee, Jae Hoon Kim
  • Patent number: 8583297
    Abstract: A method and a device are provided for the optimization of the mass of a satellite. The method includes: a step of calculation of an elliptical second orbit obtained by rotation of a first orbit about an axis connecting the periapsis and the apoapsis, the elliptical second orbit being associated with a second maximum eclipse duration less than a first maximum eclipse duration; a step of determination of a maneuver enabling the satellite to move to the second orbit; and a step of calculation of a second battery mass making it possible to maintain the satellite in operation during the second maximum eclipse duration and of calculation of a mass of fuel necessary to effect the maneuver.
    Type: Grant
    Filed: January 18, 2011
    Date of Patent: November 12, 2013
    Assignee: Thales
    Inventors: Vincent Martinot, Olivier Fratacci, Hervé Sainct
  • Patent number: 8538606
    Abstract: Certain embodiments of the invention may include systems, methods, and apparatus for sensing flight direction of a spacecraft. According to an example embodiment of the invention, a method is provided for determining flight direction of a spacecraft. The method includes providing at least one imaging detector associated with a spacecraft; imaging at least a portion of a celestial body onto the at least one imaging detector; acquiring, by the at least one imaging detector, sequential images of at least a portion of the celestial body; and determining the spacecraft flight direction relative to the celestial body based at least in part on processing the sequential images, wherein the processing is performed by one or more computer processors.
    Type: Grant
    Filed: November 3, 2010
    Date of Patent: September 17, 2013
    Assignee: The Aerospace Corporation
    Inventors: Siegfried W. Janson, Jerome K. Fuller
  • Patent number: 8528316
    Abstract: Systems and methods of controlling solid propellant gas pressure and vehicle thrust are provided. Propellant gas pressure and a vehicle inertial characteristic are sensed. Propellant gas pressure commands and vehicle thrust commands are generated. A propellant gas pressure error is determined based on the propellant gas pressure commands and the sensed propellant gas pressure, and vehicle thrust error is determined based on the vehicle thrust commands and the sensed vehicle inertial characteristic. Reaction control valves are moved between closed and full-open positions based on the determined propellant gas pressure error and on the determined vehicle thrust error. The system and method allow the reaction control valves to operate at variable frequencies or at fixed frequencies. The system and method also allows propellant pressure to be commanded to follow a predetermined pressure profile or commanded to vary “on-the-fly.
    Type: Grant
    Filed: April 23, 2009
    Date of Patent: September 10, 2013
    Assignee: Honeywell International Inc.
    Inventors: Mark H. Baker, Steve Abel, George Woessner
  • Patent number: 8532861
    Abstract: A protective device for an electronic unit on a space exploration vehicle. A Laplace transform calculation unit generates a Laplace transform of an electronic unit state. A system parameter identification unit identifies system parameters based on the Laplace transform of electronic unit states. A Fourier transform calculation unit generates a ratio of the ground contacting mechanism state to a highest dominant frequency of the measured electronic unit state. A critical travel speed calculation unit generates a critical travel speed based on the identified system parameters. A calculation unit for threshold of travel speed generates a threshold of a travel speed based on the critical travel speed. An autonomous motion controller generates a control signal that drives the space exploration vehicle based on the threshold of the travel speed.
    Type: Grant
    Filed: June 2, 2012
    Date of Patent: September 10, 2013
    Inventor: Fukashi Andoh
  • Patent number: 8498760
    Abstract: According to one embodiment of the disclosure, a method for use in telemetry processing includes receiving telemetry data originating from a satellite, such that the telemetry data comprises a plurality of data segments. The method includes processing the plurality of data segments simultaneously and transmitting a signal to the satellite, in response to the processing, for effecting a change in the direction of the satellite.
    Type: Grant
    Filed: December 27, 2007
    Date of Patent: July 30, 2013
    Assignee: Raytheon Company
    Inventors: Gerald E. Kaas, Derek L. Bassett
  • Patent number: 8489258
    Abstract: The invention set forth herein describes propulsive guidance methods and apparatus for controlling and shaping an atmospheric skip reentry trajectory for a space vehicle. Embodiments of the invention may utilize a powered explicit guidance algorithm to provide a closed-loop control method for controlling a space vehicle during a skip reentry maneuver.
    Type: Grant
    Filed: March 26, 2010
    Date of Patent: July 16, 2013
    Assignee: The Charles Stark Draper Laboratory, Inc.
    Inventors: Stephen C. Paschall, II, Garrett O. Teahan
  • Patent number: 8473206
    Abstract: Provided are an apparatus and method for executing a telecommand on a geostationary satellite, and an apparatus and method for verifying a telecommand execution status on a geostationary satellite ground control system. When a telecommand on a satellite is executed, the satellite generates command execution verification words for the executed telecommand and adds the generated command execution verification words to a telemetry transfer frame, and thus a satellite ground control system can easily verify the telecommand execution.
    Type: Grant
    Filed: May 2, 2008
    Date of Patent: June 25, 2013
    Assignee: Electronics and Telecommunications Research Institute
    Inventors: In Jun Kim, Won Chan Jung, Jae Hoon Kim
  • Patent number: 8473210
    Abstract: A method for transmitting additional information in a satellite navigation system includes providing a navigation message having a plurality of parameters, selecting at least one parameter from the plurality of parameters for the transmitting of the additional information, replacing the at least one parameter, at least partially, by the additional information so as to form a changed navigation message, and sending the changed navigation message.
    Type: Grant
    Filed: December 15, 2008
    Date of Patent: June 25, 2013
    Assignee: Astrium GmbH
    Inventor: Hans L. Trautenberg
  • Patent number: 8386099
    Abstract: A method of determining an orbit of an orbital object includes computing predicted tracking measurement values based on the orbit computed from the initial conditions factoring in any modeled environmental forces and realistic maneuvers; computing the differences between the actual and predicted tracking measurements; determining an improved estimate of the initial conditions that reduces the measurement errors using a minimization or root finding algorithm; after the algorithm has converged, reviewing the hypothetical maneuvers in the force model, taking each value and determining which values came up as near-zero in the minimized solutions and which values came up as those of measurable thrust; determining overall burn duration using the first and last burn times; determining the thrust profile of the orbital object over the observation period using the integrated thrust values; and determining the actual maneuver based on the observation data.
    Type: Grant
    Filed: February 5, 2010
    Date of Patent: February 26, 2013
    Assignee: Applied Defense Solutions
    Inventors: John Paul Carrico, Jr., Timothy Adam Craychee, Henry Casmir Grabowski, III
  • Patent number: 8386098
    Abstract: The present invention relates to image satellite planning, and more particularly to a method for allowing a deeper search for high value targets in a time-limited planning environment. In an exemplary embodiment, a method of computing an ordered subset of targets includes using an approximation for the time needed for the satellite to re-orient to a new target, rather than calculating each maneuver time between targets. By approximating the maneuver time rather than calculating it, the calculation time is reduced. Each iteration through the traveling salesman problem takes less time, and more iterations can be accomplished between imaging windows. The iterative process can search deeper into the traveling salesman problem to find a better solution.
    Type: Grant
    Filed: August 3, 2009
    Date of Patent: February 26, 2013
    Inventor: David A. Bailey
  • Patent number: 8355868
    Abstract: A method and system for a multi-spectrum celestial navigation system includes a first sensor responsive to at least a first and a second wavelength band of electromagnetic radiation. The sensor is configured to generate a first output related to the first wavelength band of electromagnetic radiation and to generate a second output related to the second wavelength band of electromagnetic radiation. The system also includes a processor programmed to receive the first and second outputs, determine a position of the sensor with respect to one or more stars using a stored star catalog and the received first and second outputs, and output the determined position.
    Type: Grant
    Filed: September 30, 2009
    Date of Patent: January 15, 2013
    Assignee: GE Aviation Systems LLC
    Inventor: Terrell Michael Brace
  • Patent number: 8332085
    Abstract: The particle swarm-based micro air launch vehicle trajectory optimization method is carried out by formulating a parameter optimization problem, which is solved using a particle swarm optimization procedure. The optimization problem is formulated using a single objective function having the explicit objective to maximize the payload mass. Constraints on terminal conditions are imposed.
    Type: Grant
    Filed: August 30, 2010
    Date of Patent: December 11, 2012
    Assignee: King Fahd University of Petroleum and Minerals
    Inventors: Hanafy M. Omar, Moumen M. Idres, Raed Kafafy
  • Patent number: 8275495
    Abstract: Disclosed is a method and device, which provide an enhanced ability to monitor the navigation of an aircraft during a phase of flight in which the aircraft is close to the ground in which the aircraft uses positional information supplied by a satellite positioning system for the navigation. A display screen is used to display a first characteristic sign representing a selected setpoint value for a height parameter of the aircraft. The display screen also displays a second characteristic sign representing a current auxiliary value expressed in the form of an achievable height parameter. An alert is emitted when the second characteristic sign is determined to be within a predetermined height value of the first characteristic sign, and the alert is shown in visual format on the display screen. An alarm is also emitted following a predetermined time after the alert is emitted, if the setpoint value is not replaced by a new setpoint value.
    Type: Grant
    Filed: October 7, 2009
    Date of Patent: September 25, 2012
    Assignees: Airbus Operations SAS, Airbus
    Inventors: Fabien Joyeux, Adrien Ott, Melanie Morel, Romain Merat, Stephane Dattler, Francois Barre, Armelle Seillier
  • Publication number: 20120239295
    Abstract: A Parametric Systematic Error Correction (ParSEC) method is disclosed which provides improved accuracy for image navigation and registration (INR). This method may be employed in imaging systems that exhibit systematic distortion. The ParSEC method comprises employing a Parametric Systematic Error Correction (ParSEC) system wherein coefficients for the system are determined by employing an nth order Taylor Series.
    Type: Application
    Filed: April 11, 2012
    Publication date: September 20, 2012
    Inventors: Ahmed Kamel, Jonathan Sheffield, Mark McLaren
  • Patent number: 8265804
    Abstract: A method for controlling a vehicle may include sensing a position of each of a plurality of stars relative to the vehicle. The method may also include determining an attitude of the vehicle using the sensed positions of the plurality of stars, and the attitude may be determined either with or without using information from a gyro or sensor for measuring angular velocity. The method may additionally include implementing a set of strategies to optimize determination of the attitude of the vehicle when using only the sensed positions of the plurality of stars, without information from the sensor for measuring angular velocity. The method may further include controlling the vehicle based on the determined attitude of the vehicle.
    Type: Grant
    Filed: May 29, 2009
    Date of Patent: September 11, 2012
    Assignee: The Boeing Company
    Inventors: David S. Uetrecht, David D. Needelman, Tung-Ching Tsao
  • Patent number: 8259011
    Abstract: An improved network enabled extended ephemeris navigation system includes a network server able to collect ephemeris, clock, and almanac information from orbiting GPS satellites, and to use that information to build up extended ephemeris predictions that will be valid and useful for at least a week. A mobile client is able to request and use the extended ephemeris predictions to search for and track orbiting GPS satellites visible to it. The improvement is characterized by a satellite position and clock compact model construction and database unit that constructs a compact short-term satellite model to be sent first in response to a request for extended ephemeris predictions from the mobile client, and that constructs several consecutive long-term satellite models each representing a unique portion of a day in at least a seven day series.
    Type: Grant
    Filed: March 23, 2010
    Date of Patent: September 4, 2012
    Assignee: Furuno Electric Co., Ltd.
    Inventors: Paul W. McBurney, Shahram Rezaei
  • Publication number: 20120166084
    Abstract: A flight dynamics subsystem (FDS), a velocity increment calculation module, and operational methods of the same are provided. A used fuel quantity actually used in a satellite is calculated, and a velocity increment is calculated using the calculated fuel quantity. Therefore, an orbit of the satellite may be estimated more accurately.
    Type: Application
    Filed: December 22, 2011
    Publication date: June 28, 2012
    Applicant: ELECTRONICS AND TELECOMMUNICATONS RESEARCH INSTITUTE
    Inventors: Yoo La HWANG, Byoung Sun Lee, Soo Jeon Lee, Jae Hoon Kim
  • Publication number: 20120072112
    Abstract: A first position of a satellite is calculated at a first time in dependence on received orbit data corresponding to an orbit path of the satellite. Anan orbit path of the satellite is modeled from the first position at the first time to a second time to determine a second position of the satellite at the second time. A third position of the satellite is then calculated at the second time in dependence on the received orbit data. The second position and third position are compared to determine a validity of the orbit data.
    Type: Application
    Filed: September 20, 2011
    Publication date: March 22, 2012
    Inventor: Peter Bagnall
  • Publication number: 20120046863
    Abstract: Improved orbit/covariance estimation and analysis (OCEAN) system and method are presented utilizing ground station observations collected from satellites passing overhead to estimate the positions, velocities, and other parameters of multiple satellites using weighted least squares (WLS) batch and/or Kalman filter smoothing (KFS) estimation algorithms to estimate each parameter, with or without a priori knowledge of the errors involved with each observed parameter.
    Type: Application
    Filed: August 12, 2011
    Publication date: February 23, 2012
    Applicant: The Government of the US, as represented by the Secretary of the Navy
    Inventors: Alan Scott Hope, Jay W. Middour, Jacques Fein, Bryan Brown, Patrick Binning, Peter Melvin, Mark Soyka, Mark Davis