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

US5433402A · kind A · utility

Assignee

• Deutsche Aerospace AG · DE

Inventors

• Michael Surauer · Chieming, DE
• Helmut Bittner · Munich, DE

Key dates

• Filing date: Jun 23, 1994
• Grant date: Jul 18, 1995
• Expiry date: Jun 23, 2014

Classification

• Technology area (CPC B): Performing Operations; Transporting
• CPC primary: B64G1/244
• WIPO field: Transport
• WIPO sector: Mechanical engineering

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 .omega..sub.X, .omega..sub.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 .omega..sub.X, .omega..sub.Y or the angular position signals .PHI., .theta. are acted upon by factors which are proportional to the rotation axis angular velocity signal .omega..sub.Z or its square in the multiplication elements. Furthermore, the thresholds of the dead zones of the modulators are varied proportionally to .omega..sub.Z.sup.2. A corresponding process for the attitude control is also described.