Honeywell International Inc.

The United States of America As Represented by the Administrator of the

Gary L Gisler

Dennis Wayne Smith

Paul Buchele

Carlos J Stevens

Robert E Winkel

Brett McMickell

Porter Davis

James T Hanks

Mark A Heller

James H Andrus

Roger Nagel

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

A rotor assembly is provided for deployment within the inner gimbal assembly of a control moment gyroscope (CMG). In one embodiment, the rotor assembly includes a rotor shell, a rotor shaft fixedly coupled to the rotor shell, and a rotor rim. The rotor rim includes an annular body and a strain relief member. A first end portion of the strain relief member is fixedly coupled to the annular body, and a second end portion of the strain relief member is fixedly coupled to the rotor shell to form a rim-shell joinder interface. The strain relief member has a flexibility sufficient to reduce the mechanical stress experienced by the rim-shell joinder interface during operation of the CMG.

Rotor assembly including strain relief feature

A valve is provided for use on a control moment gyroscope (CMG) having a housing separating an internal environment from an external environment. The valve includes a valve housing, a valve element, and bellows. The valve housing is configured to couple to the CMG housing and includes an inner surface defining a cavity, an outer surface, and an opening extending therebetween. The valve element is disposed within the valve housing cavity and is movable between a closed position, in which fluid is prevented from flowing through the valve housing opening, and an open position, in which fluid may flow through the valve housing opening. The bellows is disposed within the valve housing and coupled to the valve element and has an internal chamber. The bellows selectively moves the valve element closed and open in response to a differential pressure between the bellows internal chamber and the valve housing cavity.

Passive, double acting, vacuum actuated vent valve

A lubrication medium supply system and method for delivering lubricant to, for example, the spin bearings of a control moment gyro (CMG), includes a reservoir, a motor, and a valve. A lubrication medium is placed within the reservoir, and the motor, which is coupled to the reservoir, compresses, and thereby pressurizes, the lubrication medium. The valve opens in response to the pressurization of the lubrication medium, to thereby dispense a predetermined amount of lubrication medium from the reservoir, while simultaneously depressurizing the lubrication medium in the reservoir.

Control moment gyro spin bearing lubricant delivery system and method

A method and apparatus for measuring vibrational forces emitted by a reaction wheel assembly during rotation of its rotor includes a low mass carriage (12) supported on a large mass base (10). The carriage (12) is in the form of an octagonal frame having an opening which is adapted for receiving the reaction wheel assembly (W) supported thereon by means of a mounting ring (22). The carriage (12) is supported on the base (10) by means of air bearings (A) which support the carriage in a generally frictionless manner when supplied with compressed air from a source (50). A plurality of carriage brackets (34) and a plurality of base blocks (30) provide for physical coupling of the base (10) and carriage (12). The sensing axes of the load cells (B) are arranged generally parallel to the base (10) and connected between the base and carriage such that all of the vibrational forces emitted by the reaction wheel assembly (W) are effectively transmitted through the sensing axes of the load cells. In this manner, a highly reliable and accurate measurement of the vibrational forces of the reaction wheel assembly can be had. The output signals from the load cells (B) are subjected to a dynamic analyzer (42) which analyzes and identifies the rotor and spin bearing components which are causing the vibrational forces.

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Glendale, AZ, United States of America

Gary L Gisler