知搜-全球专利检索

  1. 登录
  2. 注册

搜索结果

889 条记录 (耗时 0.022 秒)

    MANEUVERING SPACECRAFT HAVING SOLAR SAILS
    3.
    发明公开
    MANEUVERING SPACECRAFT HAVING SOLAR SAILS 审中-公开

    公开(公告)号：US20240182184A1

    公开(公告)日：2024-06-06

    申请号：US18060764

    申请日：2022-12-01

    申请人： International Business Machines Corporation

    发明人： Sarbajit K. RAKSHIT ,  Sathya SANTHAR ,  Sridevi KANNAN

    IPC分类号： B64G1/24 ,  B64G1/36 ,  B64G1/40 ,  B64G3/00

    CPC分类号： B64G1/242 ,  B64G1/363 ,  B64G1/407 ,  B64G3/00

    摘要： Embodiments herein describe maneuvering a spacecraft using a solar sail when sunlight is not available. Smaller satellites may rely solely on solar sails in order to maneuver to different locations (e.g., different orbits) to adjust for orbital decay, avoid collisions with other satellites, or to avoid space junk. However, solar sails cannot rely on the sun when orbiting on the dark side of a planet (e.g., when in the earth's shadow). When a spacecraft should maneuver but the sun is not available as a power source, the embodiments herein describe identifying other spacecraft within line-of-sight (LOS) of the spacecraft and using these spacecraft to direct lasers (or reflecting sunlight if available) at the spacecraft to maneuver it to a desired path (e.g., a new orbit).

    System and Method for Controlling a Motion of a Spacecraft in a Multi-Object Celestial System
    8.
    发明公开
    System and Method for Controlling a Motion of a Spacecraft in a Multi-Object Celestial System 审中-公开

    公开(公告)号：US20230182927A1

    公开(公告)日：2023-06-15

    申请号：US17646491

    申请日：2021-12-30

    申请人： Mitsubishi Electric Research Laboratories, Inc.

    发明人： Abraham Vinod ,  Avishai Weiss ,  Stefano Di Cairano

    IPC分类号： B64G1/24 ,  B64G1/40 ,  B64G1/36

    CPC分类号： B64G1/242 ,  B64G1/40 ,  B64G1/36

    摘要： The present disclosure provides a system and a method for controlling a motion of a spacecraft in a multi-object celestial system while avoiding an unauthorized entry into a keep-away region during a normal and an abnormal operation of the spacecraft. The method includes executing, during the normal operation of the spacecraft, a nominal control law subject to constraints on maintaining a state of the spacecraft within a union of a plurality of control invariant sets of values of the state of the spacecraft. The state of the spacecraft includes a location of the spacecraft and at least one or a combination of a velocity and an acceleration of the spacecraft. The method further includes executing, upon detecting the abnormal operation of the spacecraft, an abort control law associated with the control invariant set including a current state of the spacecraft.

    Precision landing for rockets using deep reinforcement learning
    9.
    发明授权
    Precision landing for rockets using deep reinforcement learning 有权

    公开(公告)号：US11613384B2

    公开(公告)日：2023-03-28

    申请号：US17156943

    申请日：2021-01-25

    申请人： Brian Haney

    发明人： Brian Haney

    IPC分类号： B64G1/36 ,  B64G1/62 ,  G06N5/04 ,  G06N3/04 ,  B64G1/40 ,  B64G1/24

    摘要： The invention is methods for landing rockets with precision using deep reinforcement learning for control. Embodiments of the invention are comprised of three steps. First, sensors collect data about the rocket's physical landing environment, passing information to rocket's database and processors. Second, the processors manipulate the information with a deep reinforcement learning program to produce instructions. Third, the instructions command the rocket's control system for optimal performance during landing.

    ORBITAL ATTITUDE CONTROL DEVICE, SATELLITE, ORBITAL ATTITUDE CONTROL METHOD, AND RECORDING MEDIUM
    10.
    发明申请
    ORBITAL ATTITUDE CONTROL DEVICE, SATELLITE, ORBITAL ATTITUDE CONTROL METHOD, AND RECORDING MEDIUM 有权

    公开(公告)号：US20220402633A1

    公开(公告)日：2022-12-22

    申请号：US17791903

    申请日：2020-02-26

    申请人： Mitsubishi Electric Corporation

    发明人： Kenji KITAMURA ,  Takeya SHIMA ,  Katsuhiko YAMADA

    IPC分类号： B64G1/24 ,  B64G1/26 ,  B64G1/36

    摘要： In an orbital attitude control device (1150), an ideal thrust axis direction calculator (1505) calculates an ideal thrust axis direction based on information of a predetermined orbit, an ideal attitude calculator (1506) calculates an ideal attitude of the satellite based on the ideal thrust axis direction and a solar direction, and a control torque calculator (1510) calculates an ideal control torque that makes the attitude of the satellite follow the ideal attitude and a torque restraint plane in which the solar direction is orthogonal to a rotational axis of the solar array panel, defines an evaluation function obtained by weighting a distance from the ideal control torque and a distance from the torque restraint plane and then summing the weighted distances, and calculates the control torque that allows the drive constraint to be satisfied and the evaluation function to be minimized.