Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.