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.

Abstract: A gear drive having a third order damper operating with the antibacklash gear so as to lower the impact of the antibacklash gear at high torques to reduce gear wear while maintaining good contact with the antibacklash gear at lower torques to maintain high accuracy and bandwidth.

Abstract: A vibration damping and isolation apparatus including a passive damping mechanism and an active enhancement mechanism. The passive damping mechanism operates to dissipate vibratory and shock forces applied to the vibration damping and isolation apparatus. The passive damping mechanism includes first and second spaced damping elements. A first resilient structure connects the first damping element to the second damping element to define a primary fluid chamber between the first and second damping elements. The passive damping mechanism further includes a second resilient structure that defines a secondary fluid chamber which is in fluid communication with the primary fluid chamber via a fluid flow orifice. A fluid fills the primary fluid chamber, the secondary fluid chamber and the fluid flow orifice.

Abstract: A dual mode vibration isolator for reducing transmission of vibrations between a forward body and an aft body includes a mounting member positioned between the forward and aft bodies, a plurality of magnetic actuators each having an armature fixed to the forward body and a stator mounted on the mounting member, and a plurality of linear actuators pivotally connected between the aft body and the mounting member. The magnetic actuators support the forward body relative to the mounting member by magnetically supporting the armatures between paired stator cores in each stator. The magnetic actuators are controlled, preferably through local flux feedback loops, to permit the stators to vibrate relative to the armature without transmitting forces to the armatures, thus isolating the vibration of the aft body and mounting member from the forward body. The linear actuators extend and contract to reposition the forward body and mounting member relative to the aft body.