Attitude control process and device for a spacecraft to be rotated around an axis of a body

• US 5,433,402 A
• Filed: 06/23/1994
• Issued: 07/18/1995
• Est. Priority Date: 09/06/1991
• Status: Expired due to Fees

• Current Assignee: Deutsche Aerospace AG (Mercedes-Benz Group AG)
• Original Assignee: Deutsche Aerospace AG (Mercedes-Benz Group AG)
• Inventors: Surauer, Michael, Bittner, Helmut
• Primary Examiner(s): Barefoot, Galen L.
• Application Number:
  US08/199,330
• Time in Patent Office: 390 Days
• Field of Search: 244/176, 244/164, 244/165, 244/169, 244/170, 244/171, 364/437, 364/434, 364/499, 318/581, 318/584, 318/585, 318/586, 318/629
• US Class Current: 244/164
• CPC Class Codes: B64G 1/244 Spacecraft control systems
• CPC Class Codes: B64G 1/36 using sensors, e.g. sun-sensors, horizon sensors

Abstract

This device is used for controlling the attitude of a spacecraft to be rotated about a body'"'"'s axis of rotation. Actuators generate torques about the axis of rotation and two lateral axes. Angular velocity signals ω_X, ω_Y with respect to the lateral axes are in each case fed to first and second signal paths. The latter contain an integrator. Modulators, which each comprise a variable dead zone, supply control signals for the actuators. In order to limit the nutation amplitude to a constant value in a reliable manner, multiplication elements are provided in the first and second signal paths. The lateral-axis angular velocity signals ω_X, ω_Y or the angular position signals Φ, θ are acted upon by factors which are proportional to the rotation axis angular velocity signal ω_Z or its square in the multiplication elements. Furthermore, the thresholds of the dead zones of the modulators are varied proportionally to ω_Z². A corresponding process for the attitude control is also described.

Claims

1. An attitude control device for a spacecraft rotatable about an axis of rotation, comprising

actuators for generating torques about said axis of rotation and two lateral axes orthogonal to each other and said axis of rotation;

sensors for forming angular velocity signals (ω

_X, ω

_Y, ω

_Z) with respect to the axes;

two modulators having variable dead zones, each one of said two modulators being coupled in front of said actuators assigned to one of said two lateral axes, said two modulators emitting control signals to said actuators;

two regulator networks, each one of said two regulator networks receiving an angular velocity signal for one of said lateral axes, each one of said two regulator networks furnishing a control signal for one of said two modulators, said two regulator networks having first and second paths connected in parallel, each path including two signal paths;

an integrator coupled in said second signal path;

two first multiplication elements, one of said two first multiplication elements being connected in each of said two first signal paths, said two first multiplication elements using multiplication factors proportionally dimensioned (b_X, b_Y) to an angular velocity signal (ω

_Z) of said axis of rotation;

two second multiplication elements, one of said two second multiplication elements being connected in each of said two second signal paths following said integrator, said two second multiplication elements using multiplication factors proportionally dimensioned (a_X, a_Y) to a square (ω

_Z²) of the angular velocity signal (ω

_Z) of said axis of rotation; and

devices for varying the dead zone of each of said two modulators proportionally (c_X, c_Y) to the square (ω

_Z²) of the angular velocity signal of said axis of rotation.

2. A device according to claim 1, further comprising a filter connected into each of the two first and second signal paths, each of said filters receiving a lateral-axis angular velocity signal (ω

_X, ω

_Y), said filters having a transmission function in a numerator at least of the first degree.

3. A device according to claim 1, wherein the integrator in the second path is a combined integrator in which two angular position signals Φ

and θ

are formed as output signals by the integration of the following equations;

space="preserve" listing-type="equation">Φ

=ω

.sub.X +Θ

ω

.sub.Z

space="preserve" listing-type="equation">Θ

=ω

.sub.Y -Φ

ω

.sub.Z

wherein ω

_X and ω

_Y are the two lateral-axis angular velocity signals;

ω

_Z is the rotation axis angular velocity signal; and

Φ and

θ

are time derivations of the angular position signals determined by the integration.

4. A device according to claim 2, wherein the integrator in the second path is a combined integrator in which two angular position signals Φ

and θ

are formed as output signals by the integration of the following equations;

space="preserve" listing-type="equation">Φ

=ω

.sub.X +Θ

ω

.sub.Z

space="preserve" listing-type="equation">Θ

=ω

.sub.Y -Φ

ω

.sub.Z

wherein ω

_X and ω

_Y are the two lateral-axis angular velocity signals;

ω

_Z is the rotation axis angular velocity signal; and

Φ and

θ

are time derivations of the angular position signals determined by the integration.

5. A device according to claim 2, wherein said transmission function has a numerator of the second degree.

6. An attitude control process for a spacecraft to be rotated about a body'"'"'s axis of rotation, said spacecraft being equipped with actuators for generating controlling torques about the axis of rotation as well as about two lateral axes orthogonal to the axis of rotation and to one another, sensors for forming angular velocity signals (ω

_X, ω

_Y, ω

_Z, ) with respect to the three axes, and modulators, each provided with a variable dead zone, for emitting control signals for the actuators assigned to the lateral axes (X, Y), a first signal fraction being formed in a first signal path from each of the two lateral-axis angular velocity signals (ω

_X, ω

_Y); and

a second signal fraction being formed in a second signal path, said second signal path being connected in parallel to the first signal path and containing an integrator, a second signal fraction being a sum of the two signal fractions being fed to the respective modulator as a control signal, wherein the process comprises the steps of;

in the two first signal paths, performing one multiplication using a factor which is proportional (b_X, b_Y) to the rotation axis angular velocity signal (ω

_Z);

in the two second signal paths, performing one multiplication, following the integrator, using a factor (a_X, a_Y) which is proportional to the square of the rotation axis angular velocity signal (ω

_Z²) and;

varying the thresholds of the dead zones proportionally (c_X, c_Y) to the square of the rotation axis velocity signal (ω

_Z²).

7. A process according to claim 6, wherein in the case of a geostationary satellite, the process further comprises the step of obtaining the rotation axis angular velocity signal (ω

_Z) by an estimation from measurements of sun sensors.

8. A process according to claim 6, wherein the lateral-axis angular velocity signals (ω

_X, w_Z), before being fed into the first and second signal paths, are subject to filtering in a filter whose transmission function in the numerator is at least of the first degree.

9. A process according to claim 7, wherein the lateral-axis angular velocity signals (ω

_X, ω

_Z), before being fed into the first and second signal paths, are subject to filtering in a filter whose transmission function in the numerator is at least of the first degree.

10. A process according to claim 6, wherein in the first and second signal paths, before the multiplication, a filtering takes place in a filter whose transmission function in the numerator is at least of the first degree.

11. A process according to claim 7, wherein in the first and second signal paths, before the multiplication, a filtering takes place in a filter whose transmission function in the numerator is at least of the first degree.

12. A process according to claim 6, wherein the integrations to be carried out in the integrator of the two second signal paths are linked with one another via the following equations to be integrated:

space="preserve" listing-type="equation">Φ

=ω

.sub.X +Θ

ω

.sub.Z

space="preserve" listing-type="equation">Θ

=ω

.sub.Y -Φ

ω

.sub.Z

13. A process according to claim 6, wherein the proportional action constants b_X, b_Y in the factors of the multiplications taking place in the two first signal branches have the following form:

##EQU5## wherein I_X, I_Y are the two moments of inertia of the lateral axes;

I_Z is the moment of inertia of the axis of rotation;

T_CX is the controlling torque about the X-axis of the vehicle;

T_CY is the controlling torque about the Y-axis of the vehicle, and d is a damping factor to be selected in the range of 1≧

d≧

0.1.

14. A process according to claim 6, wherein the proportional action constants a_X, a_Y in the factors of the multiplications to be carried out in the two second signal paths have the following form:

##EQU6## wherein β

_N max is the highest permissible nutation amplitude, and Φ

_max, θ

_max are the maximal amplitudes of the angular movement about the lateral axes.

15. A process according to claim 6, wherein the proportional action constants having an effect during the variation of the thresholds of the dead zones have the following form:

##EQU7##