Abstract: A bi-stable magnetic switch assembly comprises a stator having an axis and first and second magnetic portions angularly disposed there around, and a rotor having at least one magnetic region attracted to the first and second portions. The rotor is configured for rotation about the axis between (1) a first latched position wherein the region resides proximate to, but is spaced apart from, the first portion; and (2) a second latched position wherein the region resides proximate to, but is spaced apart from, the second portion. A spring biases the rotor to a position where the region resides intermediate the first and second portions. A coil, which is associated with at least one of the first portion, the second portion, and the region, may be energized to reduce the force of attraction between the region and the first and second portions when in the first and second latched positions, respectively.

Abstract: A bi-stable magnetic switch assembly is provided that comprises a stator and a rotor, which is configured for rotation with respect to the stator between a first latched position and a second latched position. The stator and the rotor cooperate to form a first magnetic path and a magnetic path having a shared portion. A spring, which is coupled to the rotor, biases the rotor toward the first and second latched positions when the rotor is in the second and first latched positions, respectively. At least one magnet is fixedly coupled to either the stator or the rotor. The magnet is included within the first magnetic path and configured to produce a magnetic latching force that biases the rotor toward first latched position when the rotor is closer to the first latched position than to the second latched position, and toward the second latched position when the rotor is closer to the second latched position than to the first latched position.

Abstract: A bi-stable magnetic switch assembly is provided that comprises a stator and a rotor, which is configured for rotation with respect to the stator between a first latched position and a second latched position. The stator and the rotor cooperate to form a first magnetic path and a magnetic path having a shared portion. A spring, which is coupled to the rotor, biases the rotor toward the first and second latched positions when the rotor is in the second and first latched positions, respectively. At least one magnet is fixedly coupled to either the stator or the rotor. The magnet is included within the first magnetic path and configured to produce a magnetic latching force that biases the rotor toward first latched position when the rotor is closer to the first latched position than to the second latched position, and toward the second latched position when the rotor is closer to the second latched position than to the first latched position.

Abstract: A method and system for calculating a control function for a structural system (10) that can be used to determine an appropriate control force to apply to an active member (18) within a stationary member (12) on the structural system (10). An active member (18) and a stationary member (12) are defined as a two-mass system in which the active member (18) and the stationary member (12) move in opposite directions. The stationary member (12) is mounted to an isolation subsystem (14) that is composed of six isolators (28) at multiple degrees of freedom. The isolation subsystem (14) is softer than the stationary member (12), active member (18) and a spacecraft surface (16) due to a damping element (32) of the isolation subsystem (16). The isolation subsystem (16) is mounted to the spacecraft (16) and decouples the spacecraft (16) from the stationary member (12) and thus the active member (18). An accurate control force for the active member (18) can be determined based upon the above structure (10).

Abstract: The present invention provides an optical element switching mechanism that overcomes many of the disadvantages found in the prior art. The switching mechanism uses a balanced arm, with an optical element attached at one end of the arm. The arm is suspended on a axis that allows it to rotate from a first position to a second position. The arm is balanced to provide low force disturbance during this movement. A spring is coupled to the arm that provides the rotational energy to move the arm. The spring is coupled such that its neutral position is between the first and second positions, and thus the spring provides the energy to move the arm from the first position to the second position and vice versa. A latch mechanism is also provided for selectively holding the arm in the first position or second position. Additionally, the latch mechanism can provide additional energy needed to catch and move the arm into final position.

Abstract: A magnetic bi-stable latch with an upper stator and a lower stator, a rotor between the upper stator and lower stator and adapted for rotation between a first latched position and a second latched position. Each of the stators is a magnetic assembly having at least two inner poles and two outer poles of magnetic material, and at least one stator further having a coil disposed in relation to the inner pole and the outer pole to form an electromagnet. The stators are positioned such that the outer poles of the upper stator align with the inner poles of the lower stator and the inner poles of the upper stator align with the outer poles of the lower stator. The rotor has permanent magnets mounted thereon such that in the first latched position the permanent magnets are aligned with poles of the upper and lower stators.

Abstract: A method and system for calculating a control function for a structural system (10) that can be used to determine an appropriate control force to apply to an active member (18) within a stationary member (12) on the structural system (10). An active member (18) and a stationary member (12) are defined as a two-mass system in which the active member (18) and the stationary member (12) move in opposite directions. The stationary member (12) is mounted to an isolation subsystem (14) that is composed of six isolators (28) at multiple degrees of freedom. The isolation subsystem (14) is softer than the stationary member (12), active member (18) and a spacecraft surface (16) due to a damping element (32) of the isolation subsystem (16). The isolation subsystem (16) is mounted to the spacecraft (16) and decouples the spacecraft (16) from the stationary member (12) and thus the active member (18). An accurate control force for the active member (18) can be determined based upon the above structure (10).

Abstract: A method and system for calculating a control function for a structural system (10) that can be used to determine an appropriate control force to apply to an active member (18) within a stationary member (12) on the structural system (10). An active member (18) and a stationary member (12) are defined as a two-mass system in which the active member (18) and the stationary member (12) move in opposite directions. The stationary member (12) is mounted to an isolation subsystem (14) that is composed of six isolators (28) at multiple degrees of freedom. The isolation subsystem (14) is softer than the stationary member (12), active member (18) and a spacecraft surface (16) due to a damping element (32) of the isolation subsystem (16). The isolation subsystem (16) is mounted to the spacecraft (16) and decouples the spacecraft (16) from the stationary member (12) and thus the active member (18). An accurate control force for the active member (18) can be determined based upon the above structure (10).

Abstract: A dynamic unbalance compensation system that compensates for dynamic unbalance of a rotating assembly on a vehicle, such as a spacecraft, to compensate for the presence of a dynamic unbalance moment. The system includes a vehicle, such as a spacecraft, a rotational assembly mounted on the vehicle and rotatable about an axis of rotation relative to the vehicle, and one or more momentum devices mounted on the rotational assembly and generating a momentum vector component perpendicular to the axis of rotation. The one or more momentum devices generate a compensation torque during spinning of the rotational assembly so as to compensate for dynamic unbalance of the rotational assembly.

Abstract: A rotary damper (10) includes a stationary member (12) and a rotating member (14) provided within the stationary member (12) so that a gap (16) is defined between the rotating member (14) and the stationary member (12). The rotating member (14) further includes a central shaft (18) provided therein. A viscous fluid (19) is provided in the gap (16) and has an associated shear that provides a velocity damping within the gap (16). A differential growth in the gap (16) caused by temperature variation compensates for temperature damping variation. A compliant member (20) is provided within the stationary member (12) for providing thermal compensation. A secondary hermetic seal (26) is provided on the stationary member (12) for permitting limited rotation, defining a vacuum environment and preventing viscous fluid leakage to an external environment.

Abstract: A rotary damper (10) includes a stationary member (12) and a rotating member (14) provided within the stationary member (12) so that a gap (16) is defined between the rotating member (14) and the stationary member (12). The rotating member (14) further includes a central shaft (18) provided therein. A viscous fluid (19) is provided in the gap (16) and has an associated shear that provides a velocity damping within the gap (16). A differential growth in the gap (16) caused by temperature variation compensates for temperature damping variation. A compliant member (20) is provided within the stationary member (12) for providing thermal compensation. A secondary hermetic seal (26) is provided on the stationary member (12) for permitting limited rotation, defining a vacuum environment and preventing viscous fluid leakage to an external environment.

Abstract: A strut assembly includes a longitudinal member having a wall and at least a first substantially hollow end portion. A first threaded member is slidably mounted within the first end-portion and is capable of movement along a longitudinal axis of the threaded member between a retracted position and an extended position. The wall has at least a first access opening therein for providing access to the first threaded member. At least a first node is provided having at least one internally threaded radial bore therein which is configured to threadably engage the first threaded member in an extended position.

Abstract: A method and system for calculating a control function for a structural system (10) that can be used to determine an appropriate control force to apply to an active member (18) within a stationary member (12) on the structural system (10). An active member (18) and a stationary member (12) are defined as a two-mass system in which the active member (18) and the stationary member (12) move in opposite directions. The stationary member (12) is mounted to an isolation subsystem (14) that is composed of six isolators (28) at multiple degrees of freedom. The isolation subsystem (14) is softer than the stationary member (12), active member (18) and a spacecraft surface (16) due to a damping element (32) of the isolation subsystem (16). The isolation subsystem (16) is mounted to the spacecraft (16) and decouples the spacecraft (16) from the stationary member (12) and thus the active member (18). An accurate control force for the active member (18) can be determined based upon the above structure (10).

Abstract: The present invention provides an optical element switching mechanism that overcomes many of the disadvantages found in the prior art. The switching mechanism uses a balanced arm, with an optical element attached at one end of the arm. The arm is suspended on a axis that allows it to rotate from a first position to a second position. The arm is balanced to provide low force disturbance during this movement. A spring is coupled to the arm that provides the rotational energy to move the arm. The spring is coupled such that its neutral position is between the first and second positions, and thus the spring provides the energy to move the arm from the first position to the second position and vice versa. A latch mechanism is also provided for selectively holding the arm in the first position or second position. Additionally, the latch mechanism can provide additional energy needed to catch and move the arm into final position.

Abstract: A strut assembly includes a longitudinal member having a wall and at least a first substantially hollow end portion. A first threaded member is slidably mounted within the first end-portion and is capable of movement along a longitudinal axis of the threaded member between a retracted position and an extended position. The wall has at least a first access opening therein for providing access to the first threaded member. At least a first node is provided having at least one internally threaded radial bore therein which is configured to threadably engage the first threaded member in an extended position.

Abstract: A dynamic unbalance compensation system is provided that compensates for dynamic unbalance of a rotating assembly on a vehicle, such as a spacecraft, to compensate for the presence of a dynamic unbalance moment. The system includes a vehicle, such as a spacecraft, a rotational assembly mounted on the vehicle and rotatable about an axis of rotation relative to the vehicle, and one or more momentum devices mounted on the rotational assembly and generating a momentum vector component perpendicular to the axis of rotation. The one or more momentum devices generate a compensation torque during spinning of the rotational assembly so as to compensate for dynamic unbalance of the rotational assembly.

Abstract: A container with an inside surface and a mass mounted for oscillation in the container with a pair of bellows in the container each having a bias spring therein and a removable end to expose the interior of the bellows to exchange the spring for easy tuning of the damping characteristics and a plurality of balls, one each positioned in a plurality of troughs around the periphery of the mass proximate the ends there to bear against the inside surface so as to provide low friction oscillation of the mass in the container.

Abstract: A constant volume damper which has a very constant damping constant over a considerable range of frequencies by including check valves that prevent cavitation as a piston moves in a chamber. The damper is also sealed for use in space application and is temperature compensated.

Abstract: An acoustic vibration isolator for use in preventing damage to a payload connected to a launch vehicle by removing the air around the payload so that acoustic vibrations do not have a medium to travel through to reach the payload.

Abstract: Disclosed is a vibration damping and isolation apparatus having a passive damping mechanism. The passive damping mechanism includes a piston and first and second elements of magnetic material with a shaft extending therebetween. The piston and shaft are linearly movable relative to one another upon application of forces to the damping apparatus. The shaft is spaced from an axial bore of the piston by a restrictive fluid flow annulus that is filled with a viscous fluid. A resilient seal mechanism, having a static stiffness, couples the first and second elements to the piston to define first and second viscous fluid filled chambers in fluid communication with the annulus. Shearing of the fluid as it is displaced through the annulus dissipates the forces. A magnetic mechanism generates magnetic forces that act on the first and second elements to destiffen the static stiffness of the resilient seal mechanism to improve vibration damping and isolation at low frequencies.