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CubeSat Attitude Determination and Helmholtz Cage Design.

ADA557488

Publication Date	2012
Personal Author	Brewer, M. R.
Page Count	105
Abstract	A method of 3-axis satellite attitude determination utilizing six body-fixed light sensors and a 3-axis magnetometer is analyzed. A Helmholtz cage is designed, built, and tested to provide a dynamic, 3-axis, uniform magnetic field to cancel the Earth's magnetic field and create an environment similar to the geomagnetic field a satellite would experience on-orbit. A CubeSat is provided the inertial magnetic vector and 'Sun' vector, which are combined with data from the light sensors and magnetometer in a CubeSat. Attitude is estimated on-board the CubeSat via the optimal fast quaternion estimation algorithm. The capabilities of the Helmholtz cage, including the uniformity of the produced magnetic field, are examined as is the accuracy of the on-board attitude determination. The results show that a support column in the vicinity of the cage impacts the uniformity of the magnetic field. The desired +/- 2 Gauss magnetic field was achieved in two of three directions, and the cage was equipped to simulate a dynamic magnetic field as would be experienced in orbit. Attitude determination with the OFQEA is achieved to within +/- 6 degrees of error.
Keywords	Artificial satellites Attitude control systems Magnetic fields Magnetometers Optical detectors Satellite attitude Algorithms Attitude indicators Geomagnetism Helmholtz equations Theses Satellite attitude determination Cubesat Helmholtz cage design Light sensors Helmholtz coils
Source Agency	Non Paid ADAS
NTIS Subject Category	63C - Infrared & Ultraviolet Detection 46 - Physics 84G - Unmanned Spacecraft 84D - Spacecraft Trajectories & Flight Mechanics
Corporate Authors	Air Force Inst. of Tech., Wright-Patterson AFB, OH. Graduate School of Engineering and Management.
Supplemental Notes	The original document contains color images.
Document Type	Thesis
Title Note	Master's thesis.
NTIS Issue Number	201217

CubeSat Attitude Determination and Helmholtz Cage Design.

CubeSat Attitude Determination and Helmholtz Cage Design.
ADA557488

Publication Date	2012
Personal Author	Brewer, M. R.
Page Count	105
Abstract	A method of 3-axis satellite attitude determination utilizing six body-fixed light sensors and a 3-axis magnetometer is analyzed. A Helmholtz cage is designed, built, and tested to provide a dynamic, 3-axis, uniform magnetic field to cancel the Earth's magnetic field and create an environment similar to the geomagnetic field a satellite would experience on-orbit. A CubeSat is provided the inertial magnetic vector and 'Sun' vector, which are combined with data from the light sensors and magnetometer in a CubeSat. Attitude is estimated on-board the CubeSat via the optimal fast quaternion estimation algorithm. The capabilities of the Helmholtz cage, including the uniformity of the produced magnetic field, are examined as is the accuracy of the on-board attitude determination. The results show that a support column in the vicinity of the cage impacts the uniformity of the magnetic field. The desired +/- 2 Gauss magnetic field was achieved in two of three directions, and the cage was equipped to simulate a dynamic magnetic field as would be experienced in orbit. Attitude determination with the OFQEA is achieved to within +/- 6 degrees of error.
Keywords	Artificial satellites Attitude control systems Magnetic fields Magnetometers Optical detectors Satellite attitude Algorithms Attitude indicators Geomagnetism Helmholtz equations Theses Satellite attitude determination Cubesat Helmholtz cage design Light sensors Helmholtz coils
Source Agency	Non Paid ADAS
NTIS Subject Category	63C - Infrared & Ultraviolet Detection 46 - Physics 84G - Unmanned Spacecraft 84D - Spacecraft Trajectories & Flight Mechanics
Corporate Authors	Air Force Inst. of Tech., Wright-Patterson AFB, OH. Graduate School of Engineering and Management.
Supplemental Notes	The original document contains color images.
Document Type	Thesis
Title Note	Master's thesis.
NTIS Issue Number	201217