Accession Number:

ADA179424

Title:

Star Sensor Fine Attitude Pointing Model for a Spinning Geosynchronous Satellite.

Descriptive Note:

Master's thesis,

Corporate Author:

AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING

Personal Author(s):

Report Date:

1986-12-01

Pagination or Media Count:

152.0

Abstract:

A fine attitude determination model is developed for a spinning geosynchronous satellite, based upon stellar observations from a V-slit star scanner and ground supplied satellite ephemerides. A true attitude model is determined through numerical integration of Eulers moment equations for a torque-free, rigid, axisymmetric body, and kinematic relations which consist of pitch, roll, yaw, orientation angles. Next, the closed form solutions to the Euler equations are coupled with first-order approximate solutions of the kinematic relations to develop a second order kinematics model. Observation relations, relating stellar slit-plane crossing times, a priori star identification assumed, to attitude states, are then developed. Finally, a nonlinear least-squares estimation algorithm is used to identify the full satellite attitude state. Simulation is tested for single scan and multiple-scan capability using exact and noise ridden data. Keywords satellite attitude determination star sensors star trackers autonomous spacecraft navigation. Theses

Subject Categories:

  • Space Navigation and Guidance
  • Astronautics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE