Patents by Inventor Rongsheng Li

Rongsheng Li has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).

  • Patent number: 11387883
    Abstract: An estimator that is part of a communication network including a plurality of nodes is disclosed. A centralized portion of the estimator includes one or more processors in wireless communication with the plurality of nodes that are part of the communication network, where the communication network includes one or more pairs of collaborating nodes, and a memory coupled to the one or more processors, the memory storing data into a database and program code that, when executed by the one or more processors, causes the centralized portion of the estimator to determine a local update and a collaborative update. The collaborative update is applied to the respective estimated local state vector for both nodes of the pair of collaborating nodes.
    Type: Grant
    Filed: April 28, 2020
    Date of Patent: July 12, 2022
    Assignee: The Boeing Company
    Inventors: Rongsheng Li, Chang Jin Yoo
  • Publication number: 20220196851
    Abstract: Systems and methods for inertial navigation aided by signals of opportunity (SOOP). One system includes a network operations center (NOC), a reference station, and mobile user equipment. Another system includes a NOC and user equipment without a reference station. In the latter system, the NOC comprises an antenna, a NOC receiver that generates SOOP data derived from SOOP, a computer system that generates SOOP source location/ephemeris data and inter-source clock bias data based on SOOP data generated by the NOC receiver, and a communication device to broadcast the data. The user equipment comprises an antenna, a navigation receiver that generates SOOP data derived from SOOP detected by the antenna of the user equipment, and a navigation computer system that calculates a navigation solution, including a SOOP-derived estimated position of the user equipment, based on SOOP source location/ephemeris data and inter-source clock bias data broadcasted by the NOC and SOOP data generated by the navigation receiver.
    Type: Application
    Filed: September 10, 2021
    Publication date: June 23, 2022
    Applicant: The Boeing Company
    Inventor: Rongsheng Li
  • Publication number: 20220147045
    Abstract: Sensor data fusion systems that provide noise reduction and fault protection. The sensor data fusion system fuses data acquired by respective accelerometers having different attributes. For example, one accelerometer has low noise and high bias, while another accelerometer has high noise and low bias when measuring specific force. The high-noise, low-bias accelerometer may be a gravimeter. Gravimeters and traditional accelerometers measure the same physical variable, i.e., specific force. By combining an expensive gravimeter and low-cost accelerometers, a synthetic sensor having both low noise and low bias may be achieved. Such synthetic sensors may be utilized in a gravity anomaly-referenced navigation system to achieve improved navigation performance.
    Type: Application
    Filed: September 16, 2021
    Publication date: May 12, 2022
    Applicant: The Boeing Company
    Inventors: Rongsheng Li, Chang J. Yoo, Tung-Ching Tsao, Andrey Tolstov, Cody L. Gruebele
  • Publication number: 20220018681
    Abstract: A PNT system for a user includes a plurality of sensors configured to collect measurements, where the sensors are grouped into a plurality of subsets of sensors. The PNT system individually compares a measured value collected by each of the plurality of sensors with a corresponding threshold value. The PNT system determines a potential fault condition for a particular sensor exists when the measured value exceeds the corresponding threshold value. In response to detecting the potential fault condition, the PNT system contains the potential fault condition by determining a replacement value. In response to determining a number of times that the potential fault condition is detected exceeds a predetermined value, the PNT system determines a confirmed fault condition with the particular sensor and re-groups the plurality of subsets of sensors. The PNT system proceeds to a second level of fault detection for determining a plurality of individual navigation solutions.
    Type: Application
    Filed: June 30, 2021
    Publication date: January 20, 2022
    Inventor: Rongsheng Li
  • Patent number: 11168984
    Abstract: A celestial navigation system and method for determining a position of a vehicle. The system includes a star-tracker, a beam director, an inertial measurement unit, and a control module. The star-tracker has a field of view for capturing light. The beam director is configured to change a direction of the light captured in the field of view of the star-tracker. The inertial measurement unit has a plurality of sensors for measuring an acceleration and a rotation rate of the vehicle. The control module executes instructions to correct the attitude, the velocity and the position of the vehicle using the determined magnitude and position of the space objects. The control module also executes instructions to generate corrections to the IMU error parameters, the beam director and star-tracker alignment errors, and RSO ephemeris errors to achieve optimal performance.
    Type: Grant
    Filed: February 8, 2019
    Date of Patent: November 9, 2021
    Assignee: The Boeing Company
    Inventors: Rongsheng Li, Tung-Ching Tsao, Harold A. Klotz, Jr., Bruce M. Pope, Paul J. Haug
  • Publication number: 20210336672
    Abstract: An estimator that is part of a communication network including a plurality of nodes is disclosed. A centralized portion of the estimator includes one or more processors in wireless communication with the plurality of nodes that are part of the communication network, where the communication network includes one or more pairs of collaborating nodes, and a memory coupled to the one or more processors, the memory storing data into a database and program code that, when executed by the one or more processors, causes the centralized portion of the estimator to determine a local update and a collaborative update. The collaborative update is applied to the respective estimated local state vector for both nodes of the pair of collaborating nodes.
    Type: Application
    Filed: April 28, 2020
    Publication date: October 28, 2021
    Inventors: Rongsheng Li, Chang Jin Yoo
  • Patent number: 10993121
    Abstract: A communication network having a plurality of nodes is disclosed. An individual node of the communication network includes a measurement device configured to collect local measurements, an antenna configured to wirelessly connect the individual node to a collaborating node that is part of the communication network, one or more processors in electronic communication with the measurement device and the antenna, a memory coupled to the one or more processors, the memory storing data into a database and program code that, when executed by the one or more processors, causes the individual node to estimate, based on the local measurements, an estimated local state vector for the individual node. The individual node determines a collaborative update based on an estimated collaborative measurement and a collaborative residual, where the collaborative update is applied to the estimated local state vector for the individual node.
    Type: Grant
    Filed: April 28, 2020
    Date of Patent: April 27, 2021
    Assignee: The Boeing Company
    Inventors: Rongsheng Li, Chang Jin Yoo
  • Publication number: 20200256678
    Abstract: A celestial navigation system and method for determining a position of a vehicle. The system includes a star-tracker, a beam director, an inertial measurement unit, and a control module. The star-tracker has a field of view for capturing light. The beam director is configured to change a direction of the light captured in the field of view of the star-tracker. The inertial measurement unit has a plurality of sensors for measuring an acceleration and a rotation rate of the vehicle. The control module executes instructions to correct the attitude, the velocity and the position of the vehicle using the determined magnitude and position of the space objects. The control module also executes instructions to generate corrections to the IMU error parameters, the beam director and star-tracker alignment errors, and RSO ephemeris errors to achieve optimal performance.
    Type: Application
    Filed: February 8, 2019
    Publication date: August 13, 2020
    Inventors: Rongsheng Li, Tung-Ching Tsao, Harold A. Klotz, JR., Bruce M. Pope, Paul J. Haug
  • Patent number: 10694148
    Abstract: Systems and methods for providing improved navigation performance in which camera images are matched (using correlation) against reference images available from a geolocation-tagged database. An image-based navigation system partitions the camera image (corresponding to the area within the field-of-view of the camera) into a plurality of camera sub-images (corresponding to regions in that area), and then further partitions each camera sub-image into a multiplicity of tiles (corresponding to sub-regions within a region). The partitioning into camera sub-images seeks geometric diversity in the landscape. Each tile is checked for quality assurance, including feature richness, before correlation is attempted. The correlation results are further quality-checked/controlled before the results are used by the Kalman filter to generate corrections for use by the inertial navigation system.
    Type: Grant
    Filed: June 26, 2019
    Date of Patent: June 23, 2020
    Assignee: The Boeing Company
    Inventors: Rongsheng Li, Tung-Ching Tsao, Amir Leon Liaghati, Shanshin Chen
  • Patent number: 9846240
    Abstract: Methods and apparatus to monitor GPS/GNSS atomic clocks are disclosed. An example method includes establishing a measured difference between an atomic frequency standard (AFS) and a monitoring device. The method also includes modeling an estimated difference model between the AFS and the monitoring device, and computing a residual signal based on the measured difference and the estimated difference model. In addition, the method includes analyzing, by a first detector, the residual signal at multiple thresholds, each of the thresholds having a corresponding persistency defining the number of times a threshold is exceeded before one or more of a phase jump, a rate jump, or an acceleration error is indicated. Furthermore, the method includes analyzing, by a second detector, a parameter of the estimated difference model at multiple thresholds, each of the thresholds having a corresponding persistency defining the number of times a drift threshold is exceeded before a drift is indicated.
    Type: Grant
    Filed: June 24, 2014
    Date of Patent: December 19, 2017
    Assignee: The Boeing Company
    Inventors: Rongsheng Li, Kamran Ghassemi
  • Publication number: 20170283085
    Abstract: A system is provided for structural load assessment of an aircraft. An approximator may receive parameters related to a ground or flight event and calculate the resulting response load on the aircraft using a machine learning algorithm and a structural dynamics model of the aircraft. An analysis engine may compare the calculated response load to a corresponding design load for determining the structural severity of the ground or flight event on the aircraft. A maintenance engine may then automatically perform or trigger a maintenance activity for the aircraft in instances in which the structural severity of the ground or flight event causes a limit exceedance state of the aircraft or at least one structural element thereof.
    Type: Application
    Filed: April 4, 2016
    Publication date: October 5, 2017
    Inventors: Justin D. Kearns, Rongsheng Li, Naveed Hussain, Kayode T. Ariwodola, Christopher L. Davis, Jack S. Hagelin, Lawrence E. Pado
  • Publication number: 20160245921
    Abstract: Methods and apparatus to monitor GPS/GNSS atomic clocks are disclosed. An example method includes establishing a measured difference between an atomic frequency standard (AFS) and a monitoring device. The method also includes modeling an estimated difference model between the AFS and the monitoring device, and computing a residual signal based on the measured difference and the estimated difference model. In addition, the method includes analyzing, by a first detector, the residual signal at multiple thresholds, each of the thresholds having a corresponding persistency defining the number of times a threshold is exceeded before one or more of a phase jump, a rate jump, or an acceleration error is indicated. Furthermore, the method includes analyzing, by a second detector, a parameter of the estimated difference model at multiple thresholds, each of the thresholds having a corresponding persistency defining the number of times a drift threshold is exceeded before a drift is indicated.
    Type: Application
    Filed: June 24, 2014
    Publication date: August 25, 2016
    Inventors: Rongsheng Li, Kamran Ghassemi
  • Patent number: 8543266
    Abstract: Methods, systems, and computer-readable media are described herein for using a modified Kalman filter to generate attitude error corrections. Attitude measurements are received from primary and secondary attitude sensors of a satellite or other spacecraft. Attitude error correction values for the attitude measurements from the primary attitude sensors are calculated based on the attitude measurements from the secondary attitude sensors using expanded equations derived for a subset of a plurality of block sub-matrices partitioned from the matrices of a Kalman filter, with the remaining of the plurality of block sub-matrices being pre-calculated and programmed into a flight computer of the spacecraft. The propagation of covariance is accomplished via a single step execution of the method irrespective of the secondary attitude sensor measurement period.
    Type: Grant
    Filed: October 3, 2011
    Date of Patent: September 24, 2013
    Assignee: The Boeing Company
    Inventors: Rongsheng Li, Tung-Ching Tsao, Arunkumar P. Nayak
  • Publication number: 20130085628
    Abstract: Methods, systems, and computer-readable media are described herein for using a modified Kalman filter to generate attitude error corrections. Attitude measurements are received from primary and secondary attitude sensors of a satellite or other spacecraft. Attitude error correction values for the attitude measurements from the primary attitude sensors are calculated based on the attitude measurements from the secondary attitude sensors using expanded equations derived for a subset of a plurality of block sub-matrices partitioned from the matrices of a Kalman filter, with the remaining of the plurality of block sub-matrices being pre-calculated and programmed into a flight computer of the spacecraft. The propagation of covariance is accomplished via a single step execution of the method irrespective of the secondary attitude sensor measurement period.
    Type: Application
    Filed: October 3, 2011
    Publication date: April 4, 2013
    Inventors: Rongsheng Li, Tung-Ching Tsao, Arunkumar P. Nayak
  • Patent number: 8370064
    Abstract: A system for navigation and tracking may include an inertial navigation system adapted to generate a replica GNSS signal and a global navigation satellite system. The global navigation satellite system may include a module to digitize a GNSS signal received from a constellation of global navigation satellites. A correlator receives the digitized GNSS signal and the replica GNSS signal. The correlator correlates the digitized GNSS signal to the replica GNSS signal to generate a correlated GNSS signal. A coherent integration module coherently integrates the correlated GNSS signal to generate an integrated signal having a predetermined rate. A filter receives the integrated signal and generates a data signal for navigation and tracking. An output device may present the navigation and tracking information based on the data signal, or the navigation and tracking information may be used to provide guidance for a vehicle or may be used to track a target.
    Type: Grant
    Filed: April 14, 2010
    Date of Patent: February 5, 2013
    Assignee: The Boeing Company
    Inventors: Rongsheng Li, Kamran Ghassemi
  • Patent number: 8259012
    Abstract: A system that provides GPS-based navigation/orbit determination capabilities for high-altitude spacecraft. The system uses an existing spacecraft processor and an easy-to-space-qualify minimum-hardware front end to minimize the need for new space-qualified hardware. The system also uses coherent integration to acquire and track the very weak GPS signals at high altitudes. The system also uses diurnal thermal modeling of a spacecraft clock and precision orbit propagation to enable longer coherent integration, a special Kalman filter to allow weak signal tracking by integrated operation of orbit determination and GPS signal tracking, and a segment-by-segment, post-processing, delayed-time approach to allow a low-speed spacecraft processor to provide the software GPS capability.
    Type: Grant
    Filed: April 14, 2010
    Date of Patent: September 4, 2012
    Assignee: The Boeing Company
    Inventors: Rongsheng Li, Kamran Ghassemi, Clifford W. Kelley
  • Patent number: 8056863
    Abstract: A method of controlling attitude of a spacecraft during a transfer orbit operation is provided. The method includes providing a slow spin rate, determining the attitude of the spacecraft using a unified sensor set, and controlling the attitude of the spacecraft using a unified control law. The use of a unified set of sensors and a unified control law reduces spacecraft complexity, cost, and weight.
    Type: Grant
    Filed: November 3, 2009
    Date of Patent: November 15, 2011
    Assignee: The Boeing Company
    Inventors: H. Grant Wang, Rongsheng Li
  • Publication number: 20110254734
    Abstract: A system that provides GPS-based navigation/orbit determination capabilities for high-altitude spacecraft. The system uses an existing spacecraft processor and an easy-to-space-qualify minimum-hardware front end to minimize the need for new space-qualified hardware. The system also uses coherent integration to acquire and track the very weak GPS signals at high altitudes. The system also uses diurnal thermal modeling of a spacecraft clock and precision orbit propagation to enable longer coherent integration, a special Kalman filter to allow weak signal tracking by integrated operation of orbit determination and GPS signal tracking, and a segment-by-segment, post-processing, delayed-time approach to allow a low-speed spacecraft processor to provide the software GPS capability.
    Type: Application
    Filed: April 14, 2010
    Publication date: October 20, 2011
    Applicant: THE BOEING COMPANY
    Inventors: Rongsheng Li, Kamran Ghassemi, Clifford W. Kelley
  • Patent number: 8019544
    Abstract: A method of estimating the alignment of a star sensor (20) for a vehicle (12) includes generating star tracker data. A vehicle attitude and a star sensor attitude are determined in response to the star tracker data. A current alignment sample is generated in response to the vehicle attitude and the star sensor attitude. A current refined estimate alignment signal is generated in response to the current alignment sample and a previously refined estimate alignment signal via a vehicle on-board filter (38).
    Type: Grant
    Filed: January 3, 2005
    Date of Patent: September 13, 2011
    Assignee: The Boeing Company
    Inventors: David D. Needelman, Rongsheng Li, Yeong-Wei A. Wu
  • Publication number: 20110181465
    Abstract: A multi-constellation GNSS augmentation and assistance system may include a plurality of reference stations. Each reference station may be adapted to receive navigation data from a plurality of different global navigation satellite systems and to monitor integrity and performance data for each different global navigation satellite system. An operation center may receive the integrity and performance data transmitted from each of the plurality of reference stations. A communication network may transmit a message from the operation center to navcom equipment of a user for augmentation and assistance of the navcom equipment.
    Type: Application
    Filed: January 26, 2010
    Publication date: July 28, 2011
    Inventors: Rongsheng Li, Kamran Ghassemi, Jeff R. Bennett, Michael A. Rizzo, JR., Jonathan A. Tekawy, Richard T. Cervisi