US 3,940,096 AGranted

Re-orientation of a spacecraft relative to its angular momentum vector

AssigneeRCA Corporation

InventorsJohn Edward Keigler, Ludwig Muhlfelder

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Abstract

The orientation maneuver of a bias momentum stabilized spacecraft is achieved without the need of attitude determination by sensors and gyros and the like and without the conventional spin-down and spin-up procedures. The spacecraft is provided with a momentum wheel mounted in perpendicular relation to the axis of maximum moment of inertia. The wheel is initially de-energized during the time the spacecraft is initially launched from the ground launching platform until it is desired to orient the spacecraft in the final orbit. The momentum wheel, when energized from zero rotation to increasing rotation speeds, causes the rotation of the spacecraft from spinning about the maximum moment of inertia axis to an axis parallel to the momentum wheel axis with the final convergence of the wheel axis to the momentum vector being effected by energy dissipation in a nutation damper.

A system for orienting the attitude of a spin-stabilized vehicle in a given orbit, said vehicle including a body, a nutation damper, and a momentum wheel, comprising:

means for spinning said vehicle at a first spin rate about a first axis comprising the maximum moment of inertia of said vehicle whereby said first axis is in alignment with the angular momentum vector of the vehicle,
said momentum wheel being affixed to said body and oriented to spin about an axis perpendicular to said maximum moment of inertia axis, said perpendicular axis having a moment of inertia less than said maximum moment of inertia,
means for reducing the spin rate of said vehicle from said first spin rate to a second spin rate such that the angular momentum of said vehicle about said first axis at said second spin rate is substantially equal to a predetermined angular momentum for said vehicle corresponding to a predetermined angular momentum of said vehicle in said given orbit,
means for energizing said momentum wheel to rotate at a rate sufficient to provide and maintain nutational stability of said vehicle whereby said vehicle is effected to move initially in a divergent spiral through an angle in inertial space such that said momentum wheel axis and said transverse axis move toward said angular momentum vector in a converging spiral, and the spin rate of said body about said transverse axis is reduced to a third spin rate, said third spin rate being less than either of said first and second spin rates,
means for moving said transverse axis towards and maintaining coincidence with said angular momentum vector of said vehicle and moving said momentum wheel axis towards and maintaining a parallel relation with said angular momentum vector, said movement comprising damping of nutation by said nutation damper,
the angular momentum of said wheel being greater than the product of said third spin rate times the difference between said maximum moment of inertia and said transverse moment of inertia of said vehicle.

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Abstract

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