Honeywell International Inc.

Other

Bruce W Rogers

Robert E Winkel

Louis R Jackson

Paul W Schwerman

Douglas Edward Smith

John R Leonard

Leigh Pelton

Ivan S Rogers

A high precision clipping regulator circuit includes a first protection diode, a second protection diode, a first offset clamp voltage regulator, and a second offset clamp voltage regulator. The first protection diode is configured to conduct when a voltage potential exceeds a first protection voltage magnitude, and is operable to exhibit variations in the first protection voltage magnitude. The second protection diode is configured to conduct when a voltage potential exceeds a second protection voltage magnitude, and is operable to exhibit variations in the second protection voltage magnitude. The first reference and second voltage regulator circuits are configured to determine when the first and second protection voltages vary and, in response thereto, to vary the first and second variable offset clamp voltages so that a difference in voltage across the protection diodes remains substantially constant.

High precision clipping regulator circuit

Methods are provided for calibrating a tachometer or generator device to reduce residual errors associated with the tachometer-generator device. A shim structure is positioned within the air gap of the tachometer-generator device. A physical characteristic or location of placement of the shim structure is selected to reduce variation in an output voltage of the tachometer-generator device.

Calibration of a generator device

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 tool structure to effect a twisting alignment of carpentry studs for use is arranged to include cooperative first and second legs, with the first leg pivotally mounting a third leg that in turn is secured to the second leg, with a fourth leg secured to the third leg. A fifth leg pivotally mounted above the third leg is arranged for abutment with the fourth leg to effect projection of the second leg relative to the first leg. In this manner, securement of the associated carpentry stud is permitted accommodating its subsequent twisting for alignment and use.

Growing community of inventors

Glendale, AZ, United States of America

Bruce W Rogers