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Precision Attitude Control of Symmetric Spinning Bodies.

AD730854

Publication Date	1971
Personal Author	Lorell, K. R.; Lange, B.
Page Count	147
Abstract	Motivated by the arc-second pointing requirement of the Unsupported Gyroscope experiment and other satellite applications, this research investigates the problems associated with the precision attitude control of symmetric spinning bodies. An attitude control system is synthesized and then is studied by analog simulation. Controller performance and limitations are evaluated, using a laboratory model called the Spinning Vehicle Simulator (SVS). A technique devised at Stanford University in 1966 that simplifies the design of spinning-vehicle attitude controllers is used to select controller gains. The resulting system, simulated on an analog computer, produces excellent response characteristics and is insensitive to vehicle parameter or gain changes. The magnitude of the attitude error is shown to have zero-frequency and spin-frequency components proportional to the magnitude of body-fixed and inertially fixed moments, respectively. (Author)
Keywords	Attitude control systems Scientific satellites Mathematical models Stabilized platforms Spin stabilization Star trackers Gyroscopes Equations of motion Telemeter systems Experimental data Computerized simulation Computer aided analysis Station keeping
Source Agency	Invalid Source Agency Code
NTIS Subject Category	84C - Manned Spacecraft 84D - Spacecraft Trajectories & Flight Mechanics
Corporate Authors	Stanford Univ Calif Dept Of Aeronautics And Astronautics
Document Type	Technical Report
NTIS Issue Number	197122
Contract Number	F33615-67-C-1245 F33615-70-C-1637

Precision Attitude Control of Symmetric Spinning Bodies.

Precision Attitude Control of Symmetric Spinning Bodies.
AD730854

Publication Date	1971
Personal Author	Lorell, K. R.; Lange, B.
Page Count	147
Abstract	Motivated by the arc-second pointing requirement of the Unsupported Gyroscope experiment and other satellite applications, this research investigates the problems associated with the precision attitude control of symmetric spinning bodies. An attitude control system is synthesized and then is studied by analog simulation. Controller performance and limitations are evaluated, using a laboratory model called the Spinning Vehicle Simulator (SVS). A technique devised at Stanford University in 1966 that simplifies the design of spinning-vehicle attitude controllers is used to select controller gains. The resulting system, simulated on an analog computer, produces excellent response characteristics and is insensitive to vehicle parameter or gain changes. The magnitude of the attitude error is shown to have zero-frequency and spin-frequency components proportional to the magnitude of body-fixed and inertially fixed moments, respectively. (Author)
Keywords	Attitude control systems Scientific satellites Mathematical models Stabilized platforms Spin stabilization Star trackers Gyroscopes Equations of motion Telemeter systems Experimental data Computerized simulation Computer aided analysis Station keeping
Source Agency	Invalid Source Agency Code
NTIS Subject Category	84C - Manned Spacecraft 84D - Spacecraft Trajectories & Flight Mechanics
Corporate Authors	Stanford Univ Calif Dept Of Aeronautics And Astronautics
Document Type	Technical Report
NTIS Issue Number	197122
Contract Number	F33615-67-C-1245 F33615-70-C-1637