Honeywell International Inc.

Louis R Jackson

Robert E Winkel

Bruce W Rogers

Brian H Hamilton

Timothy Hindle

Randy W Hostettler

Apparatus, Systems, and Methods are provided for controlling motion of a spacecraft. One apparatus includes a non-contacting actuator and a passive mechanical system coupled in parallel with one another. A system includes a payload, a bus, and a hybrid actuator including a non-contacting actuator and a passive mechanical system coupled in parallel, and coupled between the bus and the payload. The system also includes an inertial actuator configured to maneuver the bus to maintain a relative position and/or attitude of the bus with respect to the payload. One method includes receiving a signal instructing a first controller to change the position and/or attitude of a payload and utilizing a hybrid system to change the position and/or attitude of the payload. The method also includes receiving the signal at a second controller and utilizing a system to change a position and/or attitude of the bus independent of the payload.

Active control of soft hybrid isolation systems

A system and method are provided for operating a control moment gyro (CMG) in a spacecraft. The CMG includes a spin motor, and a CMG rotor that is coupled to the spin motor and is configured to rotate about a spin axis. Electrical power from a power source is supplied to the spin motor to rotate the CMG rotor about the spin axis. A determination is made as to whether the power source can supply sufficient electrical power to the spin motor. If the power source cannot supply sufficient electrical power to the spin motor, the spin motor is rotated by the CMG rotor to generate and supply electrical power to the power source.

Self-powered spacecraft attitude control system and method

Methods and apparatus are provided for active motion damping of a spacecraft whose attitude control system (SACS) has experienced a partial failure. In a preferred embodiment, the apparatus comprises, an attitude control processor (ACP), a motion damping controller (MDC) coupled to the ACP, a control moment gyro (CMG) comprising a gimbal loop controller (GLC) coupled to the MDC and a gimbal motor with input coupled to the GLC and gyroscopic torque output coupled to the satellite. Normally, a gimbal rate command (GRC) from the ACP passes to the GLC for execution to rotate the CMG gimbal and the coupled satellite. If the ACP output becomes invalid, the MDC assumes control and can modify CMG operation in several ways to safely decelerate a moving satellite without hazardous mechanical stress. Following such active motion damping, the CMG remains quiescent until a RESET is received whereby further valid GRCs are then executable.

Satellite active motion damping

A method for monitoring a system operating in real-time includes monitoring the system for a triggering event or events, recording data about the system to a first memory in real time prior to and/or for a set time subsequent to when the triggering event occurs, and sending the stored data from the first memory to a second memory or an interface for retrieval.

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Peoria, AZ, United States of America

Louis R Jackson