Spacecraft Attitude Determination Using Global Positioning Satellite Signals

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Experimental Methods
Simulink is used to generate orbital data for the two GPS satellites and orbital and attitude data for the spacecraft of interest. The satellites possess the following characteristics:

Satellite	Altitude (km)	Inclination (deg)	Right Ascension of the Ascending Node (deg)	Argument of Perigee (deg)	Eccentricity
GPS 1	22200	55	0	0	0
GPS 2	22200	55	60	0	0
Spacecraft	560	35	0	0	0

Table 1: Satellite characteristics

Inertia Tensor	kg-m²
Initial Attitude

Directory: COSGC Projects
COSGC Projects -> All-star microgravity Structural Deployment and Attitude Control Test
COSGC Projects -> Deployment and Intelligent Nanosat Operations
COSGC Projects -> Augmentation to Colorado Space Grant Program

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