Abstract: Embodiments of control moment gyroscopes (CMGs) are provided, as are embodiments of a method for fabricating CMGs. In one embodiment, a CMG includes a stator housing, an inner gimbal assembly (IGA), and a torque motor coupled to the stator housing and configured to rotate the IGA about a gimbal axis to selectively generate a desired output torque during operation of the CMG. The IGA includes, in turn, an IGA support structure rotatably coupled to the stator housing, a monolithic CMG rotor rotatably mounted to the IGA support structure, and a spin motor coupled to the IGA support structure and configured to rotate the monolithic CMG rotor about a spin axis.

Abstract: A control moment gyroscope (CMG) includes a stator housing, an inner gimbal assembly (IGA), and a torque motor coupled to the stator housing and configured to rotate the IGA housing about a gimbal axis to selectively generate a desired output torque during operation of the CMG. The IGA includes, in turn, an IGA housing rotatably coupled to the stator housing, a CMG rotor rotatably mounted within the IGA housing, and a spin motor coupled to the IGA housing and configured to rotate the CMG rotor about a spin axis. The CMG rotor includes a rotor shaft, a rotor rim circumscribing the rotor shaft, and a plurality of radially-compliant spokes extending between the rotor shaft and the rotor rim.

Abstract: Embodiments of control moment gyroscopes (CMGs) are provided, as are embodiments of a method for fabricating CMGs. In one embodiment, a CMG includes a stator housing, an inner gimbal assembly (IGA), and a torque motor coupled to the stator housing and configured to rotate the IGA housing about a gimbal axis to selectively generate a desired output torque during operation of the CMG. The IGA includes, in turn, an IGA support structure housing rotatably coupled to the stator housing, a monolithic CMG rotor rotatably mounted to the IGA support structure housing, and a spin motor coupled to the IGA support structure housing and configured to rotate the monolithic CMG rotor about a spin axis.

Abstract: A control moment gyroscope assembly including, but not limited to, a rotor that includes a shaft, a primary rim and a web that connects the shaft to the primary rim. The rotor is made from a metal material and is adapted to spin about the shaft. The control moment gyroscope assembly further includes a secondary rim that is made of the metal material and that is disposed around the rotor. The secondary rim is configured to compress the rotor in the direction of the shaft.

Abstract: Embodiments of control moment gyroscopes (CMGs) are provided, as are embodiments of a method for fabricating CMGs. In one embodiment, a CMG includes a stator housing, an inner gimbal assembly (IGA), and a torque motor coupled to the stator housing and configured to rotate the IGA housing about a gimbal axis to selectively generate a desired output torque during operation of the CMG. The IGA includes, in turn, an IGA housing rotatably coupled to the stator housing, a CMG rotor rotatably mounted within the IGA housing, and a spin motor coupled to the IGA housing and configured to rotate the CMG rotor about a spin axis. The CMG rotor includes a rotor shaft, a rotor rim circumscribing the rotor shaft, and a plurality of radially-compliant spokes extending between the rotor shaft and the rotor rim.

Abstract: Embodiments of a low frequency isolation device are provided, as are embodiments of a spacecraft isolation system including a plurality of low frequency isolation devices. In one embodiment, the low frequency isolation device includes a three parameter isolator and a break frequency-reducing series spring mechanically coupled in series with the three parameter isolator and having a predetermined axial stiffness (KS AXIAL) and a predetermined lateral stiffness (KS LATERAL). The predetermined axial stiffness (KS AXIAL) of the break frequency-reducing series spring is less than the predetermined lateral stiffness (KS LATERAL) thereof.

Abstract: A mounting assembly is provided. The mounting assembly comprises an outer ring having a plurality of insert portions, each of the plurality of insert portions extending toward the center of the outer ring and having an insert cavity, a plurality of vibration isolation assemblies, each of the vibration isolation assemblies disposed in one of the insert cavities, each of the plurality of vibration isolation assemblies comprising a first bellows portion and a second bellows portion, a passageway formed therein and connecting the first and second bellows portions, and a contact portion adapted to receive a force, an inner ring having a plurality of contact cavities, each contact cavity adapted to receive a contact portion from one of the plurality of vibration isolation assemblies, and a central ring coupled to the outer ring by the plurality of insert portions, and to the inner ring by a plurality of bridge portions.

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 control moment gyroscope assembly including, but not limited to, a rotor that includes a shaft, a primary rim and a web that connects the shaft to the primary rim. The rotor is made from a metal material and is adapted to spin about the shaft. The control moment gyroscope assembly further includes a secondary rim that is made of the metal material and that is disposed around the rotor. The secondary rim is configured to compress the rotor in the direction of the shaft.

Abstract: A mounting assembly is provided. The mounting assembly comprises an outer ring having a plurality of insert portions, each of the plurality of insert portions extending toward the center of the outer ring and having an insert cavity, a plurality of vibration isolation assemblies, each of the vibration isolation assemblies disposed in one of the insert cavities, each of the plurality of vibration isolation assemblies comprising a first bellows portion and a second bellows portion, a passageway formed therein and connecting the first and second bellows portions, and a contact portion adapted to receive a force, an inner ring having a plurality of contact cavities, each contact cavity adapted to receive a contact portion from one of the plurality of vibration isolation assemblies, and a central ring coupled to the outer ring by the plurality of insert portions, and to the inner ring by a plurality of bridge portions.

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.