Abstract: The present invention is a control system for a seven-degree-of-freedom robotic arm. The robotic arm (10) includes two links (12 and 14), each having two degrees of freedom, and a spherical wrist (26) having three degrees of freedom. The kinematics of the spherical wrist are decoupled from the kinematics of the arm. The four degrees of freedom of the arm create a redundancy which provides versatility in the positioning of the arm. Fixing the redundant arm parameter and locating the end point (24) of the end effectuator path away from areas of limited mobility results in a marked simplification of the algorithms which describe the equations of motion of the arm. Additionally, further computation reduction can be achieved by updating the control gains less frequently than every microprocessor cycle, such as updating once for every five degrees of pitch angle rotation of either joint.

Abstract: A method for controlling transition from thruster control to momentum wheel control to minimize nutation angle and transition time in a three-axis stabilized spacecraft employing an internal body fixed-momentum wheel as an attitude stabilizer. The method employs direct, substantially real-time measurement of momentum components and angular rates and generates paired roll thrust impluses and paired yaw thrust impulses in synchronization with the nutation period of the spacecraft to drive the spacecraft to a state of substantially zero nutation. The controller employs a deadbeat principle in a closed-loop real-time feedback system. In a preferred embodiment, the impulsive thruster firing commands in roll and yaw are simultaneous, spaced one-half nutation period apart in time with the effect that the target momentum is achieved in one to three pairs of impulse firings.