Abstract: A helicopter autopilot system includes an inner loop for attitude hold for the flight of the helicopter including a given level of redundancy applied to the inner loop. An outer loop is configured for providing a navigation function with respect to the flight of the helicopter including a different level of redundancy than the inner loop. An actuator provides a braking force on a linkage that serves to stabilize the flight of the helicopter during a power failure. The actuator is electromechanical and receives electrical drive signals to provide automatic flight control of the helicopter without requiring a hydraulic assistance system in the helicopter. The autopilot can operate the helicopter in a failed mode of the hydraulic assistance system. A number of flight modes are described with associated sensor inputs including rate based and true attitude modes.

Abstract: A pilot control interface and method are described for selective control of an autopilot system by a pilot of an aircraft in which the autopilot system is installed. The pilot control interface includes a passive network that is selectively switchable between a plurality of states across an output interface that is made up of no more than two conductors that are in electrical communication with the autopilot system. Modification of a current autopilot flight mode can be performed incrementally or continuously based on respective momentary and continuous pilot input actuations.

Abstract: A pilot control interface and method are described for selective control of an autopilot system by a pilot of an aircraft in which the autopilot system is installed. The pilot control interface includes a passive network that is selectively switchable between a plurality of states across an output interface that is made up of no more than two conductors that are in electrical communication with the autopilot system. Modification of a current autopilot flight mode can be performed incrementally or continuously based on respective momentary and continuous pilot input actuations.

Abstract: An autopilot actuator includes first and second motors each including a rotatable motor output shaft such that either one or both of the motors can drive an actuator output shaft. An autopilot main unit enclosure is removably mounted to the helicopter proximate to a cyclic control and commonly houses autopilot actuators as well as main autopilot electronics. A cyclic vibration isolator is removably supported by an actuator shaft for co-rotation and coupled to the cyclic control to attenuate a cyclic vibration frequency at the actuator shaft while output rotations of the actuator shaft below a resonant frequency are coupled to the cyclic control. A force limited link includes first and second ends and a variable length between. The force limited link having a relaxed length when less than an unseating force is applied and the variable length changes when an applied force exceeds the unseating force to permit pilot override.

Abstract: An autopilot actuator includes first and second motors each including a rotatable motor output shaft such that either one or both of the motors can drive an actuator output shaft. An autopilot main unit enclosure is removably mounted to the helicopter proximate to a cyclic control and commonly houses autopilot actuators as well as main autopilot electronics. A cyclic vibration isolator is removably supported by an actuator shaft for co-rotation and coupled to the cyclic control to attenuate a cyclic vibration frequency at the actuator shaft while output rotations of the actuator shaft below a resonant frequency are coupled to the cyclic control. A force limited link includes first and second ends and a variable length between. The force limited link having a relaxed length when less than an unseating force is applied and the variable length changes when an applied force exceeds the unseating force to permit pilot override.

Abstract: An emergency collective actuator includes an actuator motor to produce an actuation force and an actuator linkage that directly engages a friction control lever that is pivotally supported on the collective stick of a helicopter to apply the actuation force directly to the friction control lever such that the actuation force initially disengages the friction control and then reduces the adjustable pitch toward a minimum collective pitch position. The actuator can include a clutch that slips to allow the pilot to overcome the actuation force and that slips responsive to an engagement of the friction control by the pilot, but otherwise the clutch co-rotates with the motor shaft to bias the adjustable pitch toward a minimum collective pitch position.

Abstract: A pilot control interface and method are described for selective control of an autopilot system by a pilot of an aircraft in which the autopilot system is installed. The pilot control interface includes a passive network that is selectively switchable between a plurality of states across an output interface that is made up of no more than two conductors that are in electrical communication with the autopilot system. Modification of a current autopilot flight mode can be performed incrementally or continuously based on respective momentary and continuous pilot input actuations.

Abstract: A pilot control interface and method are described for selective control of an autopilot system by a pilot of an aircraft in which the autopilot system is installed. The pilot control interface includes a passive network that is selectively switchable between a plurality of states across an output interface that is made up of no more than two conductors that are in electrical communication with the autopilot system. Modification of a current autopilot flight mode can be performed incrementally or continuously based on respective momentary and continuous pilot input actuations.

Abstract: A helicopter autopilot system includes an inner loop for attitude hold for the flight of the helicopter including a given level of redundancy applied to the inner loop. An outer loop is configured for providing a navigation function with respect to the flight of the helicopter including a different level of redundancy than the inner loop. An actuator provides a braking force on a linkage that serves to stabilize the flight of the helicopter during a power failure. The actuator is electromechanical and receives electrical drive signals to provide automatic flight control of the helicopter without requiring a hydraulic assistance system in the helicopter. The autopilot can operate the helicopter in a failed mode of the hydraulic assistance system. A number of flight modes are described with associated sensor inputs including rate based and true attitude modes.

Abstract: A helicopter autopilot system includes an inner loop for attitude hold for the flight of the helicopter including a given level of redundancy applied to the inner loop. An outer loop is configured for providing a navigation function with respect to the flight of the helicopter including a different level of redundancy than the inner loop. An actuator provides a braking force on a linkage that serves to stabilize the flight of the helicopter during a power failure. The actuator is electromechanical and receives electrical drive signals to provide automatic flight control of the helicopter without requiring a hydraulic assistance system in the helicopter. The autopilot can operate the helicopter in a failed mode of the hydraulic assistance system. A number of flight modes are described with associated sensor inputs including rate based and true attitude modes.

Abstract: An autopilot actuator includes first and second motors each including a rotatable motor output shaft such that either one or both of the motors can drive an actuator output shaft. An autopilot main unit enclosure is removably mounted to the helicopter proximate to a cyclic control and commonly houses autopilot actuators as well as main autopilot electronics. A cyclic vibration isolator is removably supported by an actuator shaft for co-rotation and coupled to the cyclic control to attenuate a cyclic vibration frequency at the actuator shaft while output rotations of the actuator shaft below a resonant frequency are coupled to the cyclic control. A force limited link includes first and second ends and a variable length between. The force limited link having a relaxed length when less than an unseating force is applied and the variable length changes when an applied force exceeds the unseating force to permit pilot override.

Abstract: A pilot control interface and method are described for selective control of an autopilot system by a pilot of an aircraft in which the autopilot system is installed. The pilot control interface includes a passive network that is selectively switchable between a plurality of states across an output interface that is made up of no more than two conductors that are in electrical communication with the autopilot system. Modification of a current autopilot flight mode can be performed incrementally or continuously based on respective momentary and continuous pilot input actuations.

Abstract: An autopilot actuator includes first and second motors each including a rotatable motor output shaft such that either one or both of the motors can drive an actuator output shaft. An autopilot main unit enclosure is removably mounted to the helicopter proximate to a cyclic control and commonly houses autopilot actuators as well as main autopilot electronics. A cyclic vibration isolator is removably supported by an actuator shaft for co-rotation and coupled to the cyclic control to attenuate a cyclic vibration frequency at the actuator shaft while output rotations of the actuator shaft below a resonant frequency are coupled to the cyclic control. A force limited link includes first and second ends and a variable length between. The force limited link having a relaxed length when less than an unseating force is applied and the variable length changes when an applied force exceeds the unseating force to permit pilot override.

Abstract: Provided is a method and system for logically articulating planned operations within a software based model. The method includes importing data relating to the planned operations and automatically (i) interrelating the imported data and (ii) producing threads and/or activity models. The threads and activity models are representative of the interrelations. The method also includes displaying the threads or activity models via a graphical user interface.

Abstract: A method for governing the speed of a fluid turbine by establishing a circulating flow and a rotational flow with a rotor, and interrupting the rotational flow with an opposing stator. A related braking apparatus includes a housing, a rotatable shaft, a rotor configured to rotatingly engage the shaft and engage a fluid in the housing with a plurality of radial vanes, and a non-rotating stator comprising a plurality of fluid pockets. The stator is disposed such that the radial vanes of the rotor and the fluid pockets of the stator are oriented in a facing relationship. When the shaft is rotated, the fluid in the housing experiences both a circulating flow and a rotational flow. Thus, the rotational flow is present proximate the radial vanes, but not in the fluid pockets, and the fluid imparts a braking torque on the rotating shaft via the rotor's radial vanes.

Abstract: Provided is a method and system for logically articulating planned operations within a software based model. The method includes importing data relating to the planned operations and automatically (i) interrelating the imported data and (ii) producing threads and/or activity models. The threads and activity models are representative of the interrelations. The method also includes displaying the threads or activity models via a graphical user interface.

Abstract: A rotary jetting tool including a pressure-balanced rotor, which is achieved using a vented volume. Axial movement of the rotor relative to the housing caused by pressure imbalances acting on the rotor selectively uncovers or opens a vent that places the volume in fluid communication with an ambient volume, enabling the rotor to achieve a pressure balanced condition. A plurality of radial clearance seals between the rotor and the housing are used to provide hydrodynamic bearings to reduce friction between the rotor and housing. The diameters of the seals are manipulated to facilitate pressure balancing of the rotor. In one embodiment, the rotor includes a centrifugal brake configured to control a maximum rotational speed of the rotor. Pressurized fluid is introduced into the rotor in an axial direction, enabling a relatively large upstream settling chamber to be incorporated into the rotor, thereby reducing inlet turbulence and improving jet quality.

Abstract: This invention discloses a valve that generates a hydraulic negative pressure pulse and a frequency modulator for the creation of a powerful, broadband swept impulse seismic signal at the drill bit during drilling operations. The signal can be received at monitoring points on the surface or underground locations using geophones. The time required for the seismic signal to travel from the source to the receiver directly and via reflections is used to calculate seismic velocity and other formation properties near the source and between the source and receiver. This information can be used for vertical seismic profiling of formations drilled, to check the location of the bit, or to detect the presence of abnormal pore pressure ahead of the bit. The hydraulic negative pressure pulse can also be used to enhance drilling and production of wells.

Abstract: Rotary jetting tool including a rotor with axially-opposed pressure-balanced mechanical face seals. Vented upper mechanical face seal enables the rotor to be operated with the relativity low starting torque achievable using reaction forces from offset jets energized with a pressurized fluid. When rotor is displaced axially due to set-down conditions, a pressure chamber exerts a pressure imbalance on the rotor, forcing the rotor to return to a normal operating position. Alternate structure to achieve low starting torque includes a volume disposed adjacent to a lower mechanical face seal, the volume being coupled in fluid communication with the pressurized fluid. Mechanical face seal surfaces are fabricated from ultra-hard materials, such as tungsten carbide, silicon carbide, and diamond. A gage ring designed to ensure the jets remove all of the material from the gage of the protective housing before the tool can advance can be incorporated.

Abstract: An impact resistant tilt window assembly includes a window frame with side jambs that have legs that extend in the direction of the exterior of the frame, an upper sash, a lower sash that moves vertically and tilts inwardly and tilt latch assemblies that are positioned on the lower sash, each tilt latch assembly includes a latch bolt with a nose end that includes a notch that is sized to engage the associated jamb leg when the lower sash is in a vertical orientation. The notch has an interior leg that moves along an interior side of the jamb leg and an exterior leg that extends behind an exterior side of the jamb leg and moves along the jamb leg when the sash moves vertically. The window assembly may further include U-shaped reinforcing inserts that are positioned within the jambs such that the tilt latch assemblies engage the inserts when the lower sash is in the closed position.