Sun search method and apparatus for a satellite stabilized in three axes

• US 5,906,338 A
• Filed: 03/22/1996
• Issued: 05/25/1999
• Est. Priority Date: 03/22/1995
• Status: Expired due to Fees

• Current Assignee: Daimler-Benz Aerospace AG (Mercedes-Benz Group AG)
• Original Assignee: Daimler-Benz Aerospace AG (Mercedes-Benz Group AG)
• Inventors: Roche, Christian, Surauer, Michael, Fichter, Walter
• Primary Examiner(s): Mojica, Lissi V.
• Application Number:
  US08/620,287
• Time in Patent Office: 1,159 Days
• Field of Search: 244/164, 244/165, 244/171, 369/455, 369/457, 73/178 R, 701/222, 701/13
• US Class Current: 244/165
• CPC Class Codes: B64G 1/244 Spacecraft control systems
• CPC Class Codes: B64G 1/245 Attitude control algorithms for spacecraft attitude control
• CPC Class Codes: B64G 1/285 using momentum wheels
• CPC Class Codes: B64G 1/363 using sun sensors
• CPC Class Codes: B64G 1/369 using gyroscopes as attitude sensors

Abstract

The sun search method for a satellite stabilized in three axes according to the invention uses a sun sensor device with a visual field possibly containing gaps, and a rotational speed gyro which measures in a measuring axis that is oriented arbitrarily. A regulating law with the form τ=-kGG^T ω is used (τ=regulating torque, k=amplification factor, G=directional vector of measuring axis of rotational speed gyro, ω=rotational speed vector of the satellite). A rotational wheel momentum H which is not parallel to the measuring axis, is generated with the aid of an additional flywheel device.

Claims

1. Method for sun seeking for a satellite stabilized in three axes, by means of a system having

a sun sensor device whose visual field covers one or more partial sectors, separated from one another by gaps, of a preselectable plane of a satellite-integral orthogonal three-axis coordinate system and an area orthogonal to this plane;

a rotational speed gyro which measures uniaxially with a measuring axis oriented arbitrarily;

a first torque generating device other than a flywheel device, for generating torque around all three coordinate axes; and

a regulator which, based on the measuring signals of the rotational speed gyro for purposes of generating regulating torque, outputs positioning signals for the first torque generating device, based on regulating process of the following form;

τ

=-kGG^T ω and

where τ

is a regulating torque, k is an amplification factor, G is the directional vector of the measuring axis with |G|=1, G^T being the vector transposed to G, and ω

is the rotational speed vector of the satellite, said method comprising;

providing a second torque generating device in the form of a flywheel arrangement on said satellite; and

said flywheel arrangement generating a rotation wheel momentum having a momentum vector H that is not parallel to the direction of the measuring axis.

2. Method according to claim 1 wherein:

said sun sensor device has a visual field which covers an angle range of at least π

continuously within the preselectable plane; and

the momentum vector H is generated in a direction which is oriented orthogonally to directional vector G of the measuring axis.

3. Method according to claim 1 further comprising:

adjusting orientation of momentum vector H so that both H and also -H, starting from the origin of the coordinates of the satellite-integral coordinate system, lie within the visual field of the sun sensor system.

4. Method according to claim 3 further comprising:

in the event that rotation of the satellite around the direction of momentum vector H after application of the regulating process is small or zero, causing a rotation around a vector e_R which is chosen so that it lies, together with a vector -e_R, in the preselectable plane within the visual field of the sun sensor system.

5. Method according to claim 4 wherein vector e_R is collinear with momentum vector H.

6. Method according to claim 1 wherein:

sun sensor device has a visual field within the preselectable plane that does not have a partial sector that continuously covers an angle range of at least π

;

and momentum vector H is oriented in such fashion that matrix;

##EQU2## has a rank of 3.

7. Method according to claim 6 wherein momentum vector H encloses an angle of 45°

with measuring axis G.

8. Method according to claim 6 further comprising:

causing at least a rotation of the satellite around at least one rotational axis, taking into account the orientation and value of the partial sectors of the visual field of the sun sensor system, the direction of such at least one rotation ensuring that the sun will eventually appear in one of the partial sectors;

using an observer to estimate an unknown component of the rotational speed vector ω

oriented orthogonally to measuring axis (R).

9. A sun acquisition device for a satellite which is stabilized in three axes, comprising:

a sun sensor system having a visual field that covers one or more partial sectors separated from one another by gaps within a preselectable plane in a satellite-integral, three-axis, orthogonal system of coordinates;

a uniaxially measuring rotational speed gyro having an arbitrarily oriented measuring axis;

a torque generating device that generates torques around all three axes;

a regulator which, based on the measuring signals of the rotational speed gyro for purposes of generating regulating torque, outputs positioning signals for the torque generating device, based on regulating process of the following form;

τ

=-kGG^T ω

, where τ

is a regulating torque, k is an amplification factor, G is the directional vector of the measuring axis with |G|=1, G^T being the vector transposed to G, and ω

is the rotational speed vector of the satellite; and

a flywheel arrangement that is able to generate momentum components around all three coordinate axes;

said flywheel arrangement generating a rotation wheel momentum having a momentum vector H that is not parallel to the direction of the measure axis.

10. Satellite according to claim 9 wherein the flywheel arrangement comprises at least three flywheels with rotational axes that do not all lie in a single plane.

11. Satellite according to claim 10 further comprising:

least one reaction wheel; and

one twist wheel.

12. Satellite according to claim 11 further comprising:

at least two twist wheels with rotational axes enclosing an acute angle; and

at least two reaction wheels arranged orthogonally to one another with respect to their rotational axes;

wherein the two rotational axis planes spanned by two rotational axes are orthogonal to one another; and

bisectors of the angles spanned by the two wheel pairs lying in a plane are oriented orthogonally to the two rotational axis planes.

13. A method for sun seeking for a satellite which is stabilized about plural axes by means of a sun sensor whose visual field covers at least two partial sectors separated from one another by gaps, at least a first torque generating device for generating torques around said plural axes, and a rotational speed gyro which measures rotational speed about an arbitrarily selected measuring axis, said method comprising:

providing a second torque generating device in the form of a flywheel arrangement on said satellite; and

said flywheel arrangement generating a rotational wheel momentum having a momentum vector H that is not parallel to measuring axis of said rotational speed gyro, whereby said satellite rotates about an axis of the momentum vector H.