Abstract: An embedding component is described which embeds information in a scanned document. The embedding component includes a document acquisition component, which acquires a scanned document from an associated scanning device. An information acquisition component acquires variable information associated with the scanned document. An encoding component generates a machine-readable representation of the variable information. A pattern insertion component uses the machine-readable representation to insert at least one machine readable pattern in the scanned document, to generate a modified document. An output component outputs the modified document to an associated output device, such that when the modified document is rendered on print media, the machine-readable pattern is not noticeable to the unaided eye of a person. A processor implements the document acquisition component, information acquisition component, encoding component, pattern insertion component, and output component.

Abstract: The present invention provides an expandable fusion device capable of being installed inside an intervertebral disc space to maintain normal disc spacing and restore spinal stability, thereby facilitating an intervertebral fusion. In one embodiment, the fusion device includes a body portion, a first endplate, and a second endplate, the first and second endplates capable of being moved in a direction away from the body portion into an expanded configuration or capable of being moved towards the body portion into an unexpanded configuration. The fusion device is capable of being deployed and installed in both configurations.

Abstract: A rotor blade pitch control system (15) comprising a rotor blade (19a, 19b, 19c, 19d) rotatable about both a central axis (20) and a pitch axis (24a, 24b, 24c, 24d), a pitch drive rotor (32a, 32b, 32c, 32d) rotatable about the central axis independently of rotation of the rotor blade about the central axis, a pitch follower (40a, 40b, 40c, 40d) rotatable relative to the pitch drive rotor, the pitch drive rotor and the pitch follower having an eccentric axis (33a, 33b, 33c, 33d), a linkage (50a, 50b, 50c, 50d) between the pitch follower and the rotor blade configured such that the pitch follower rotates with rotation of the rotor blade about the central axis, the pitch drive rotor, the pitch follower and the linkage configured such that the pitch drive rotor may be driven to control an angular displacement of the pitch drive rotor relative to the pitch follower about the central axis and thereby control the pitch of the rotor blade about the pitch axis.

Abstract: A vibration suppression unit for an aircraft comprising a vibration control frame adapted to be mounted to the aircraft and to rotate about a central axis, a first motor configured to rotate the vibration control frame about the central axis, a second motor configured to rotate a first and second center of mass about a first and second axis or rotation, a third motor configured to adjust a variable distance between the first and second centers of mass and the first and second axis of rotation, respectively, and a controller for receiving input signals and outputting command signals to the first, second and third motors.

Abstract: A vibration suppression unit for an aircraft comprising a mass having a center of mass, a first rotor, a second rotor, a first coupling between the first rotor and the mass, a second coupling between the second rotor and the mass, the first and second couplings having first and second coupling centers offset perpendicularly from a central axis of rotation by different radial distances and offset in axially from the center of mass with respect to the central axis by different axial distances, the first and second coupling centers having a selectively variable displacement angle defined by the angle between lines extending between the central axis of rotation and the first coupling center and the second coupling center, respectively, wherein the first rotor and the second rotor are controllable to produce a vibration control force vector having a controllable magnitude and frequency about the central axis.

Abstract: A vibration suppression unit for an aircraft comprising a mass assembly having a center of mass and a frequency rotor having a frequency center axis offset from a central axis of rotation and driven to rotate about the central axis, a vibration control amplitude rotor rotationally coupled to the mass assembly and having an amplitude center axis offset from the central axis driven independently of the frequency rotor to rotate about the central axis, the amplitude center axis and the frequency center axis having a selectively variable displacement angle defined by an inclusive angle between a line extending between the central axis and the amplitude center axis and a line extending between the central axis and the frequency center axis, wherein the amplitude rotor and the frequency rotor are controllable to produce a vibration control force vector having a controllable magnitude and frequency about the central axis of rotation.

Abstract: A rotor blade pitch control system (15) comprising a rotor blade (19a, 19b, 19c, 19d) rotatable about both a central axis (20) and a pitch axis (24a, 24b, 24c, 24d), a pitch drive rotor (32a, 32b, 32c, 32d) rotatable about the central axis independently of rotation of the rotor blade about the central axis, a pitch follower (40a, 40b, 40c, 40d) rotatable relative to the pitch drive rotor, the pitch drive rotor and the pitch follower having an eccentric axis (33a, 33b, 33c, 33d), a linkage (50a, 50b, 50c, 50d) between the pitch follower and the rotor blade configured such that the pitch follower rotates with rotation of the rotor blade about the central axis, the pitch drive rotor, the pitch follower and the linkage configured such that the pitch drive rotor may be driven to control an angular displacement of the pitch drive rotor relative to the pitch follower about the central axis and thereby control the pitch of the rotor blade about the pitch axis.

Abstract: An actuator system comprising a shared link arranged to pivot about a first axis relative to a reference structure, a controlled element arranged to pivot about a second axis relative to the reference structure, a first member arranged to pivot about a third axis relative to the shared link and a fourth axis relative to the controlled member, a first actuator arranged to control a first variable distance between the third axis and fourth axis, a second member arranged to pivot about a fifth axis relative to the shared link and a sixth axis relative to the controlled element, a second actuator arranged to control a second variable distance between the fifth axis and the sixth axis, the system configured such that a change in the first variable distance causes rotation of the controlled element about the second axis when the second variable distance is constant and vice versa.

Abstract: In one aspect of the present disclosure, an object monitoring system for a secured area is provided. The object monitoring system includes an image sensor operable to capture an image of the secured area and a memory configured to store a machine learning algorithm trained to identify a vehicle in the secured area, the machine learning algorithm including feature maps of training images captured by the image sensor. The object monitoring system further includes a processor operably coupled to the image sensor and the memory, the processor configured to calculate a feature descriptor of the image and to utilize the machine learning algorithm and the image of the secured area to determine whether a vehicle is present in the secured area by determining a correlation between the feature descriptor of the image and the feature maps of the training images.

Abstract: A vibration suppression unit for an aircraft comprising a mass having a center of mass, a first rotor, a second rotor, a first coupling between the first rotor and the mass, a second coupling between the second rotor and the mass, the first and second couplings having first and second coupling centers offset perpendicularly from a central axis of rotation by different radial distances and offset in axially from the center of mass with respect to the central axis by different axial distances, the first and second coupling centers having a selectively variable displacement angle defined by the angle between lines extending between the central axis of rotation and the first coupling center and the second coupling center, respectively, wherein the first rotor and the second rotor are controllable to produce a vibration control force vector having a controllable magnitude and frequency about the central axis.

Abstract: A servovalve comprising a motor, a motor bias mechanism, a first stage valve having a first position, a second stage valve movable with movement of the first valve, a reference member in fluid communication with the second valve, a transfer link acting between the first valve and the reference member, an eccentric drive acting between the motor and transfer link, wherein movement of the motor causes the transfer link to move the first valve, movement of the first valve causes the second valve member to move, movement of the second valve applies on the reference member a pressure differential from a load, the pressure differential on the reference member causes movement of the reference member, and movement of the reference member causes the transfer link to move the first valve back to the first position.

Abstract: An actuator assembly comprising an output member rotatable about an output axis, first and second actuators each having an axis of rotation, a drive motor and a hold motor, first and second linkages between each of the first and second actuators and the output member, wherein a torque produced by a drive motor is summed through the linkages at the output member when the respective hold motor is restrained from rotating, and wherein the respective hold motor may be selectively released so that it rotates with a failure of the respective drive motor, and wherein one of the first or second actuators may be driven to selectively rotate the output member with a failure of the drive motor of the other of the first or second actuators. The assembly may comprise a third actuator linked to the output member in the same manner as the first and second actuators.

Abstract: A vibration suppression unit for an aircraft comprising a mass assembly having a center of mass and a frequency rotor having a frequency center axis offset from a central axis of rotation and driven to rotate about the central axis, a vibration control amplitude rotor rotationally coupled to the mass assembly and having an amplitude center axis offset from the central axis driven independently of the frequency rotor to rotate about the central axis, the amplitude center axis and the frequency center axis having a selectively variable displacement angle defined by an inclusive angle between a line extending between the central axis and the amplitude center axis and a line extending between the central axis and the frequency center axis, wherein the amplitude rotor and the frequency rotor are controllable to produce a vibration control force vector having a controllable magnitude and frequency about the central axis of rotation.

Abstract: A vibration suppression unit for an aircraft comprising a vibration control frame adapted to be mounted to the aircraft and to rotate about a central axis, a first motor configured to rotate the vibration control frame about the central axis, a second motor configured to rotate a first and second center of mass about a first and second axis or rotation, a third motor configured to adjust a variable distance between the first and second centers of mass and the first and second axis of rotation, respectively, and a controller for receiving input signals and outputting command signals to the first, second and third motors.

Abstract: Disclosed are exemplary embodiments of apparatus and methods for arresting flame at a gas burner. In an exemplary embodiment, an apparatus for use in burning a gas fuel generally includes a flame arrester device having a screen portion configured for placement between a gas orifice and a burner. The flame arrester device is configured to allow gas emitted from the gas orifice to pass through the screen portion to enter the burner. The flame arrester device is further configured to arrest a flame from the burner before the flame reaches the gas orifice.

Abstract: An actuator system comprising a shared link arranged to pivot about a first axis relative to a reference structure, a controlled element arranged to pivot about a second axis relative to the reference structure, a first member arranged to pivot about a third axis relative to the shared link and a fourth axis relative to the controlled member, a first actuator arranged to control a first variable distance between the third axis and fourth axis, a second member arranged to pivot about a fifth axis relative to the shared link and a sixth axis relative to the controlled element, a second actuator arranged to control a second variable distance between the fifth axis and the sixth axis, the system configured such that a change in the first variable distance causes rotation of the controlled element about the second axis when the second variable distance is constant and vice versa.

Abstract: A servovalve comprising a motor, a motor bias mechanism, a first stage valve having a first position, a second stage valve movable with movement of the first valve, a reference member in fluid communication with the second valve, a transfer link acting between the first valve and the reference member, an eccentric drive acting between the motor and transfer link, wherein movement of the motor causes the transfer link to move the first valve, movement of the first valve causes the second valve member to move, movement of the second valve applies on the reference member a pressure differential from a load, the pressure differential on the reference member causes movement of the reference member, and movement of the reference member causes the transfer link to move the first valve back to the first position.

Abstract: A servovalve (15) comprising a motor (16), a motor bias mechanism (20), a first stage valve member (22) adapted to be moved from a first position to a first off-null position, a second stage member (29) adapted to be moved from a first position to a second position with movement of the first valve member (22), a transfer link (34) acting between the first (22) and second (29) valve members, an eccentric drive member (35) acting between the motor (16) and the transfer link (34), the transfer link (34) and drive member (35) configured such that selective movement of the motor (16) causes the transfer link (34) to move the first valve member (22), movement of the first valve member (22) causes the second valve member (29) to move, and movement of the second valve member (29) causes the transfer link (34) to move the first valve member (22) from the first off-null position back to the null position.

Abstract: An actuator system comprising a shared link (121) arranged to pivot about a first axis (131) relative to a reference structure, a controlled element (125) arranged to pivot about a second axis (126) relative to the reference structure, a first member (146, 152) arranged to pivot about a third axis (134) relative to the shard link and a fourth axis (136) relative to the controlled member, a first actuator arranged to control a first variable distance (LI) between the third axis and fourth axis, a second member (147, 153) arranged to pivot about a fifth axis (133) relative to the shared link and a sixth axis (135) relative to the controlled element, a second actuator (141) arranged to control a second variable distance between the fifth axis and the sixth axis, the system configured such that a change in the first variable distance causes rotation of the controlled element about the second axis when the second variable distance is constant and vice versa.

Abstract: An actuator assembly comprising an output member rotatable about an output axis, first and second actuators each having an axis of rotation, a drive motor and a hold motor, first and second linkages between each of the first and second actuators and the output member, wherein a torque produced by a drive motor is summed through the linkages at the output member when the respective hold motor is restrained from rotating, and wherein the respective hold motor may be selectively released so that it rotates with a failure of the respective drive motor, and wherein one of the first or second actuators may be driven to selectively rotate the output member with a failure of the drive motor of the other of the first or second actuators. The assembly may comprise a third actuator linked to the output member in the same manner as the first and second actuators.