Abstract: A wearable device for monitoring and providing real-time feedback about a swimmer's body motion and performance, in particular, body orientation and forward speed, is provided. The device comprises a three-axis accelerometer, optionally a three-axis gyroscope, a memory, and a microcontroller configured to process the sensor input, calculate a swimmer's performance and provide feedback to the swimmer through an output. The output can be an earpiece or a swimming goggle with a digital display.

Abstract: A wearable device for monitoring and providing real-time feedback about a swimmer's body motion and performance, in particular, body orientation and forward speed, is provided. The device comprises a three-axis accelerometer, optionally a three-axis gyroscope, a memory, and a microcontroller configured to process the sensor input, calculate a swimmer's performance and provide feedback to the swimmer through an output. The output can be an earpiece or a swimming goggle with a digital display.

Abstract: A spacecraft attitude control system and method in which an attitude controller is configured for sensing three-dimensional attitude of the spacecraft, and producing torque signals for stabilizing the spacecraft in a prescribed attitude in space. At least four mutually skew reaction wheels are rotated in response to the torque control signals for storing three-dimensional angular momentum, and speeds of rotation of the wheels are measured. A reaction wheel speed control processor, responsive to reaction wheel torque and speed for producing reaction wheel spin control signals, implements an infinity-norm algorithm for causing the nullspace components of wheel speed to re-distribute a desired three-dimensional stabilizing momentum of the spacecraft in such a manner that the maximum speeds of rotation of all the reaction wheels is minimized. As a result, periods between successive momentum dumping maneuvers are prolonged to the maximum possible.

Abstract: A method for correcting differences in measurements between sensors. Misalignment of a roll error of a sun sensor alignment is estimated with respect to a reference roll value measured by an earth sensor. Sun sensor assembly elevation angle residual is calculated utilizing the estimated sun sensor assembly roll misalignment. A yaw attitude of the spacecraft is updated based upon the calculated sun sensor assembly elevation residual.

Abstract: A method for maintaining three axis control of a geosynchronous spacecraft without body rate measurements using reaction wheel assemblies. Earth sensor assembly angle measurements are utilized for high-bandwidth roll and pitch control. A positive pitch momentum bias is stored in the reaction wheel assemblies. A gyroscopic feedforward torque is applied to rotate reaction wheel assembly momentum in a yaw/roll plane of the spacecraft at orbit rate. A dynamic mode that couples yaw and roll axes and that results from applying the gyroscopic feedforward torque and the high-bandwidth roll control is damped based on earth sensor assembly roll measurements.