Transition control system for spacecraft attitude control

Claim 2

In a three-axis stabilized spacecraft employing an internal body-fixed momentum wheel as an attitude stabilization means and characterized by a nutation period and a corresponding nutation frequency, a method for controlling transition from thruster control to momentum wheel control to minimize nutation angle and transition time, said method comprising the steps of: (a) obtaining values representative of spacecraft roll angle, spacecraft yaw angle, spacecraft roll rate and spacecraft yaw rate; (b) calculating a spacecraft transverse angular momentum vector from spacecraft moments of inertia and said values representative of spacecraft roll angle, spacecraft yaw angle. spacecraft roll rate and spacecraft yaw rate, said transverse angular momentum vector comprising a roll component and a yaw component; (c) computing from said values representative of spacecraft roll angle, spacecraft yaw angle, spacecraft roll rate and spacecraft yaw rate a firing duration for each one of a set of attitude control thrusters for causing spacecraft motion following thruster firing to reduce nutation amplitude toward a transverse angular momentum of zero; (d) firing said set of attitude control thrusters according to said computed firing duration; and (e) repeating at least once more said steps (a) through (d) at an interval of substantially one-half of said nutation period of said spacecraft.

Claim 3

The method according to claim 1 further including the step of attenuating spurious signals substantially above the nutation frequency of said spacecraft.

Claim 4

The method according to claim 1 further including the step of calculating said nutation period from measured rotational speed of said momentum wheel and from moments of inertia of said wheel and of said spacecraft.

Claim 5

The method according to claim 1 wherein said repeating step is limited to a preselected number of repetitions.

Claim 6

The method according to claim 1 wherein said repeating step is terminated when magnitude of said transverse angular momentum immediately following said firing step is below a preselected value.

Claim 7

The method according to claim 2 wherein further including the step of calculating said nutation period from measured rotational speed of said momentum wheel and from moments of inertia of said wheel and of said spacecraft.

Claim 8

The method according to claim 2 wherein said repeating step is limited to a preselected number of repetitions.

Claim 9

The method according to claim 2 wherein said repeating step is terminated when magnitude of said transverse angular momentum immediately following said firing step is below a preselected value.

Claim 10

The method according to claim 2 wherein said thrusters are disposed at orthogonal angles and wherein said firing step includes simultaneous firings to control roll and to control yaw.

Claim 11

In a three-axis stabilized spacecraft employing an internal body-fixed momentum wheel as an attitude stabilization means and characterized by a nutation period, an apparatus for controlling transition from thruster control to momentum wheel control to minimize nutation angle and transition time, said apparatus comprising: sensor means for obtaining values representative of spacecraft roll angle, spacecraft yaw angle, spacecraft roll rate and spacecraft yaw rate; and means coupled to said sensor means for controlling firing of spacecraft roll and yaw attitude control thrusters at intervals of substantially one-half of said nutation period, including means for calculating a spacecraft transverse angular momentum vector at intervals of one-half of said nutation period from spacecraft moments of inertia and said values representative of spacecraft roll angle, spacecraft yaw angle, spacecraft roll rate and spacecraft yaw rate, said transverse angular momentum vector comprising a roll component and a yaw component, means for computing from said values representative of spacecraft roll angle, spacecraft yaw angle, spacecraft roll rate and spacecraft yaw rate a firing duration for said attitude control thrusters for causing spacecraft motion following thruster firing to reduce nutation amplitude toward a transverse angular momentum of zero, means for causing firing of said roll and yaw attitude control thrusters according to said firing duration, and timing means for sequencing firing of said roll and yaw attitude control thrusters at intervals of substantially one-half of said nutation period of said spacecraft.

Claim 12

In a three-axis stabilized spacecraft employing an internal body-fixed momentum wheel as an attitude stabilization means and characterized by a nutation period, an apparatus for controlling transition from thruster control to momentum wheel control to minimize nutation angle and transition time, said apparatus comprising: sensor means for obtaining values representative of spacecraft roll angle, spacecraft yaw angle, spacecraft roll rate and spacecraft yaw rate; and means coupled to said sensor means for controlling firing of spacecraft roll and yaw attitude control thrusters at intervals of substantially one-half of said nutation period, including means for calculating a spacecraft transverse angular momentum vector at intervals of one-half of said nutation period from spacecraft moments of inertia and said values representative of spacecraft roll angle, spacecraft yaw angle, spacecraft roll rate and spacecraft yaw rate, said transverse angular momentum vector comprising a roll component and a yaw component, means for computing from said values representative of spacecraft roll angle, spacecraft yaw angle, spacecraft roll rate and spacecraft yaw rate a firing duration for said attitude control thrusters for causing spacecraft motion following thruster firing to reduce nutation amplitude toward a transverse angular momentum of zero, means for causing firing of said roll and yaw attitude control thrusters according to said firing duration, and timing means for sequencing firing of said roll and yaw attitude control thrusters at intervals of substantially one-half of said nutation period of said spacecraft.

Claim 13

The apparatus according to claim 10 further including filter means coupled between said sensor means and said controlling means, said filter means for removing spurious signals substantially above a nutation frequency of said spacecraft.