Accession Number:

ADA616257

Title:

Advancements of In-Flight Mass Moment of Inertia and Structural Deflection Algorithms for Satellite Attitude Simulators

Descriptive Note:

Doctoral thesis

Corporate Author:

AIR FORCE INSTITUTE OF TECHNOLOGY WRIGHT-PATTERSON AFB OH GRADUATE SCHOOL OF ENGINEERING AND MANAGEMENT

Personal Author(s):

• Wright, Jonathan W.

Report Date:

2015-03-26

Pagination or Media Count:

181.0

Abstract:

Experimental satellite attitude simulators have been used to test and analyze control algorithms driving down risk before implementation on operational satellites. Ideally, the dynamic response of a terrestrial-based experimental satellite attitude simulator matches that of an on-orbit satellite. Unfortunately, gravitational disturbance torques and poorly characterized moments of inertia introduce uncertainty into the system dynamics leading to questionable experimental results. This research consists of three distinct, but related contributions to the field of developing robust satellite attitude simulators. First, existing approaches to estimate mass moments and products of inertia are evaluated followed by a proposition and evaluation of a new approach that increases both the accuracy and precision of these estimates using typical on-board satellite sensors. Next, to better simulate the micro-torque environment of space, a new approach to mass balancing satellite attitude simulator is presented, experimentally evaluated, and verified. Finally, we experimentally analyzed a control moment gyroscope singularity avoidance steering law.

Descriptors:

• *ALGORITHMS
• *MOMENT OF INERTIA
• *SATELLITE ATTITUDE
• ACCURACY
• ARTIFICIAL SATELLITES
• DEFLECTION
• DYNAMIC RESPONSE
• INFLIGHT
• SIMULATORS
• THESES

Subject Categories:

• Mechanics
• Astronautics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE