초록 ▼

A preselected axis other than the axis of maximum moment of inertia of a momentum stabilized spacecraft is oriented for alignment with the total angular momentum vector of the spacecraft by rotating one or more rotors to a critical rate of rotation. The rotation of the rotor or rotors is maintained

A preselected axis other than the axis of maximum moment of inertia of a momentum stabilized spacecraft is oriented for alignment with the total angular momentum vector of the spacecraft by rotating one or more rotors to a critical rate of rotation. The rotation of the rotor or rotors is maintained at the critical rate to effect the desired rotation. The axis of the rotor or the effective angular momentum vector of the resultant momentum of a plurality of rotors is aligned with the axis of the desired spacecraft orientation. Energy dissipation assures stability by dissipating energy on the spacecraft body at a faster rate of dissipation than the rate of energy dissipation on the rotor.

대표청구항 ▼

A method of orienting a vehicle in inertial space from an initial orientation to a final desired orientation, said vehicle having three principal axes that are mutually orthogonal, wherein one of said principal axes defines the maximum moment of inertia axis of said vehicle, said vehicle further hav

A method of orienting a vehicle in inertial space from an initial orientation to a final desired orientation, said vehicle having three principal axes that are mutually orthogonal, wherein one of said principal axes defines the maximum moment of inertia axis of said vehicle, said vehicle further having a total angular momentum the vector of which being essentially constant in inertial space, said maximum moment of inertia axis not being initially in alignment with said vector of the total angular momentum of said vehicle and said vehicle having a platform and a rotor adapted for rotation about a preselected axis on said platform, which preselected axis is fixed relative to said platform, said preselected axis having an initial axial orientation relative to inertial space which is different by a certain angle from a desired final axial orientation, said final desired orientation being parallel to the total angular momentum vector, comprising the steps of: rotating said rotor to a constant rate of rotation such that the platform rotates in a given direction and rate of rotation, said constant rate of rotation of said rotor selected to produce a unique minimum of kinetic energy due to platform rotation at said desired orientation; said unique minimum of kinetic energy defining an energy state wherein no other minimum of kinetic energy due to platform rotation exists for said constant rate of rotation; and dissipating rotational kinetic energy on the platform of said vehicle at a rate greater than the rate of energy dissipation of said rotor; whereby as the energy of said platform is dissipated at a greater rate than the energy dissipated by said rotor, said rotor axis converges to said final desired orientation in which the axis of rotation of said rotor coincides with the total angular momentum vector and said vehicle is momentum stabilized.