Title

Precision Attitude Control of Symmetric Spinning Bodies

Date

1971

Index Abstract

Not Available

Photo Quality

Complete

Report Number

AFAL TR 71-224

Creator

Lorell, Kenneth R.

Lange, Benjamin

Corporate Author

Stanford University Department of Aeronautics and Astronautics

Laboratory

Air Force Avionics Laboratory

Extent

152

NTRL Accession Number

AD730854

Identifier

AD0730854

Access Rights

Approved for public release; distribution unlimited

Distribution Classification

1

Contract

F33615-67-C-1245

DoD Project

5102

DoD Task

510215

DTIC Record Exists

No

Distribution Change Authority Correspondence

None

Abstract

Motivated by the arc-second pointing requirement of the Unsupported Gyroscope experiment and other satellite applications, this research investigates the problems associated with the precision attitude control of symmetric spinning bodies. An attitude control system is synthesized and then is studied by analog simulation. Controller performance and limitations are evaluated, using a laboratory model called the Spinning Vehicle Simulator (SVS). A technique devised at Stanford University in 1966 that simplifies the design of spinning-vehicle attitude controllers is used to select controller gains. The resulting system, simulated on an analog computer, produces excellent response characteristics and is insensitive to vehicle parameter or gain changes. The magnitude of the attitude error is shown to have zero-frequency and spin-frequency components proportional to the magnitude of body-fixed and inertially fixed moments, respectively.

Report Availability

Full text available

Date Issued

1971-04

Provenance

Lockheed Martin Missiles & Fire Control

Type

report

Format

1 online resource