Honeywell International Inc.

Honeywell G.m.b.h.

James H Andrus

Paul Buchele

Brett McMickell

Gary L Gisler

A self-contained momentum control system (MCS) for a spacecraft is provided for small satellites. The MCS features a miniaturized gyroscopic rotor with a rotational speed in excess of 20,000 RPM. The MCS includes at least three control moment gyroscopic mechanical assemblies (CMAs) rigidly mounted within a single enclosure, where each CMA mounted in an orientation whereby the longitudinal axis of each CMA is either orthogonal to every other CMA or is parallel to another CMA but in the opposite orientation. In order to further reduce the size of the MCS, an electronics package that is configured to interface command and control signals with and to provide power to the CMAs is included within the MCS enclosure. A plurality of shock isolation devices are used to secure each of the CMAs to the enclosure in order to reduce the launch load upon the CMAs thereby allowing the use of smaller rotor spin bearings. The MCS enclosure surrounding the CMAs and support structure is hermetically sealed.

Control moment gyroscope based momentum control systems in small satellites

An electromagnetic actuator having a sensor for sensing an amount of applied force is provided. The actuator maintains an adjustable force by adjusting a current in its coils. the actuator includes an armature and a stator. The stator has a U-shaped back iron, which has a first end portion with a first coil and which has a second end portion with a second coil. The coils form a magnetic flux path from the armature through the back iron and back to the armature. There is a flux density between the armature and each polar enlargement of the back iron. A first sensor unit is mounted on the first pole face, and a second sensor unit is mounted on the second pole face of the back iron, for sensing the flux densities. The first sensor includes a first Hall generator subassembly having a first input for receiving a reference voltage and having a first output for providing an output voltage. The second sensor includes a second Hall generator subassembly having a second input connected to the first output and having a second output for providing an output voltage, which is proportional to the square of the flux density, as sensed by the first and second Hall generator subassemblies. The output voltage is directly proportional to the force, which is proportional to the square of the flux density. Each Hall generator subassembly has a first amplifier, a Hall generator unit connected to the first amplifier, and a second amplifier connected to the Hall generator unit. Each Hall generator unit senses the flux density.

Growing community of inventors

Glendale, AZ, United States of America

James H Andrus