Patent · US Expired

Method for controlling the attitude of a three-axis stabilized, earth oriented bias momentum spacecraft

US5996941A · kind A · utility

18Cited by

5References

3Claims

0Family size

Assignee

Daimler-Benz Aerospace AG · DE

Inventors

Michael Surauer · Chieming, DE
Walter Fichter · Taufkirchen, DE
Peter Zentgraf · Großkarolinenfeld, DE

Key dates

Filing date	Jun 17, 1997
Grant date	Dec 7, 1999
Priority date	—
Expiry date	Jun 17, 2017

Classification

Technology area (CPC B)Performing Operations; Transporting
CPC primaryB64G1/245
WIPO fieldTransport
WIPO sectorMechanical engineering

Abstract

An attitude controller for a 3-axis stabilized, Earth oriented bias momentum spacecraft is described, where only 2-axis attitude measurements from the Earth sensor are available. In contrast to the classical spacecrafts that are controlled w.r.t. a fixed orbital Earth pointing reference frame, (possibly large angle) time varying reference signals are considered here, i.e. the control task consists of a tracking problem. The controller design consists of a decoupling controller and axis-related PID controllers based on yaw observer estimates.

Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.