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    • 4. 发明申请
    • METHOD OF CONTROLLING MISSILE FLIGHT USING ATTITUDE CONTROL THRUSTERS
    • 使用姿态控制雷达控制飞行器的方法
    • WO2011028304A1
    • 2011-03-10
    • PCT/US2010/031676
    • 2010-04-20
    • RAYTHEON COMPANYKINSEY JR, LloydCOOK, James M.
    • KINSEY JR, LloydCOOK, James M.
    • F42B10/66
    • F42B10/661
    • A method of controlling flight of a missile includes using gyroscopes, such as pitch rate gyroscopes, to sense when a factor based on the angular rate of change of the missile exceeds a threshold value. One the threshold value is exceeded, a decision may be made to use one or more compensation thrusters to reduce the angular rate of change. The use of the compensation thrusters may correct residual angular velocities from a pitch over maneuver used to put the missile on an intended course. In addition, the compensation thrusters may be used to compensate for errors in missile heading induced after the pitch over maneuver, such as induced by misalignment of thrust provided by a main rocket motor of the missile. Multiple compensation thrusters may be used to compensate for angular changes in the pitch and yaw directions.
    • 控制导弹飞行的方法包括使用诸如俯仰速率陀螺仪的​​陀螺仪来感测何时基于导弹的角速度变化的因子超过阈值。 超过阈值的一个,可以决定使用一个或多个补偿推进器来减小角速度变化。 补偿推进器的使用可以校正用于将导弹放置在预期路线上的机动的俯仰角的剩余角速度。 此外,补偿推进器可以用于补偿在机动之后引起的导弹航向的误差,例如由导弹的主火箭发动机提供的推力不对准引起的。 可以使用多个补偿推进器来补偿俯仰和偏航方向上的角度变化。