Spacecraft Attitude Determination Using Global Positioning Satellite Signals
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In which  is the baseline length in wavelengths,  is the angle between a sightline to the GPS satellite,  is the wavelength of the GPS signal,  is the fractional phase difference between the two receivers, and  is the integer phase difference (number of full wavelengths) between the two receivers (Application of Vectorized Attitude Determination Using Global Positioning Signals).
The idea is that if the unit sightline vectors from the spacecraft to at least two GPS satellites in an inertial frame are known, the fractional phase difference between receivers are measured, and the receiver arrangement on the satellite is known, the baseline can essentially be mapped onto the sightline using a transformation matrix from the inertial coordinate frame to the body coordinate frame as shown in figure 2 (Global Positioning System: Theory and Applications Volume II): 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 Download 1.81 Mb. Share with your friends:
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