초록 ▼

Methods and systems for stabilizing satellite spin about an intermediate inertia axis (Z) are disclosed. A set of gyros (22) sense the X component and the Y component of the angular velocity of the satellite body. A single degree of freedom momentum wheel (26) has a fixed transverse orientation with

Methods and systems for stabilizing satellite spin about an intermediate inertia axis (Z) are disclosed. A set of gyros (22) sense the X component and the Y component of the angular velocity of the satellite body. A single degree of freedom momentum wheel (26) has a fixed transverse orientation with respect to the intermediate axis in order to store momentum. In one embodiment, the momentum wheel (26) is oriented to store momentum parallel to the Y axis. A tachometer (30) senses the rotation rate of the momentum wheel (26). A processor (24) forms a control signal representative of a control torque to be applied to the momentum wheel (26). The control torque is based upon the X component and the Y component of angular velocity of the satellite, and the angular velocity of the momentum wheel (26). These methods and systems may also be used to invert the spin direction of spinning satellites, ensure tumble recover to a preferred orientation, and stabilize the body spin axis against nutation, dynamic imbalance and external torques.

대표청구항 ▼

1. A system for reorienting an angular rate vector of a spinning satellite from an initial direction to a desired direction, the system comprising:at least one gyro for sensing at least one component of the angular rate vector; a single degree of freedom momentum storage device having an orientation

1. A system for reorienting an angular rate vector of a spinning satellite from an initial direction to a desired direction, the system comprising:at least one gyro for sensing at least one component of the angular rate vector; a single degree of freedom momentum storage device having an orientation of variation substantially perpendicular to the desired direction; and a processor coupled to the at least one gyro and the single degree of freedom momentum storage device, the processor operative to form a control signal based upon the at least one component of the angular rate vector and to apply the control signal to the single degree of freedom momentum storage device so that the satellite has a stable equilibrium spin aligned substantially parallel to the desired direction and an unstable equilibrium spin aligned substantially antiparallel to the desired direction, whereby the angular rate vector becomes substantially aligned with the desired direction.