Preliminary design of the ORION attitude control system
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Authors
Chappell, David C.
Thaler, George J.(George Julius)
Subjects
Attitude Control System
ORION
ORION
Advisors
Thaler, George Julius
Date of Issue
1987-12
Date
Publisher
Language
en_US
Abstract
This thesis models the motion of the NPS satellite ORION
using the three Euler rotation angles. The simulation
program also models aerodynamic drag and gravity gradient
torques. Simulations are performed to analyze the effect of
changing the inertia ratio on satellite stability and
performance. The active nutation control method was also
simulated and an example of its operation given. The amount
of time required to reduce nutation to an acceptable level
was found to be dependent on the initial nutation angle,
spin rate, and thruster size. The slower the spin rate, the
greater the torque that could be used during a given firing
arc resulting in faster nutation control.
Type
Thesis
Description
Series/Report No
Department
Electrical and Computer Engineering
Organization
Naval Postgraduate School
Identifiers
NPS Report Number
Sponsors
Funder
Format
99 p.
Citation
Distribution Statement
Approved for public release; distribution is unlimited.