Abstract: An aerial vehicle traffic control system comprising a ground system, an unmanned aerial vehicle, a wireless communications link between the ground system and the unmanned aerial vehicle, the unmanned aerial vehicle configured to travel in a three-dimensional airspace, the three-dimensional airspace partitioned into multiple individual three-dimensional virtual cells, a database having a unique authorization token associated with each of the virtual cells, a transaction processing engine configured to assign each token in the database to no more than one unmanned aerial vehicle at a time, and a controller configured to control the unmanned aerial vehicle such that the unmanned aerial vehicle is restricted from entering a cell without first being assigned the token for such cell.

Abstract: An aerial vehicle traffic control system comprising a ground system, an unmanned aerial vehicle, a wireless communications link between the ground system and the unmanned aerial vehicle, the unmanned aerial vehicle configured to travel in a three-dimensional airspace, the three-dimensional airspace partitioned into multiple individual three-dimensional virtual cells, a database having a unique authorization token associated with each of the virtual cells, a transaction processing engine configured to assign each token in the database to no more than one unmanned aerial vehicle at a time, and a controller configured to control the unmanned aerial vehicle such that the unmanned aerial vehicle is restricted from entering a cell without first being assigned the token for such cell.

Abstract: A plurality of wires (33, 34; 35, 36) are disposed near the bottom (23-25) of blade root sockets (16-18) of a rotating disk 39 of a gas turbine engine by vapor deposition and etching, the wires including connections to excitation nodes (40, 42) and detection nodes (41, 43). A nearby stationary member of the engine mounts an oscillator amplifier (55) which drives a coil (57) that excites the circuitry, and a coil (62) drives an amplifier (65) and a processor (67) which provides an indication of whether or not one or more of the wires are broken by a crack.

Abstract: A plurality of wires (33, 34; 35, 36) are disposed near the bottom (23-25) of blade root sockets (16-18) of a rotating disk 39 of a gas turbine engine by vapor deposition and etching, the wires including connections to excitation nodes (40, 42) and detection nodes (41, 43). A nearby stationary member of the engine mounts an oscillator amplifier (55) which drives a coil (57) that excites the circuitry, and a coil (62) drives an amplifier (65) and a processor (67) which provides an indication of whether or not one or more of the wires are broken by a crack.

Abstract: An apparatus for use in a system having a gas fuel supply and a combustor includes a fuel actuator, a controller; and a premixer. The controller generates a command signal indicative of actuation sought from the fuel actuator. The actuator receives gas fuel from the liquid fuel supply and provides liquid fuel at a modulated rate of flow in response to the command signal. The premixer receives the fuel from the actuator, mixes the fuel with air, and provides the mixture to the combustor.

Abstract: The present invention teaches a system for improving the clarity of a voice spoken within an enclosed space. The system comprises a first microphone, positioned at a first location, for receiving the audible communication and for converting the audible communication at the first location into a first audio signal. The system also comprises a loudspeaker for receiving the first audio signal, and for converting the first audio signal into a first reproduced audible communication, the reproduced audible communication also being fed back and received by the first microphone and converted with the audible communication into the first audio signal.

Abstract: A modular vibratory force generator (10) is adapted to be mounted on a helicopter fuselage (11) and operated to selectively apply a controllable vibratory force (F.sub.R) thereto. The improved generator includes a plurality of force-generating modules (12, 12) and a closed-loop servocontroller (13). Each module has a pair of counter-rotating eccentric masses (20, 21) that are arranged to exert a fixed-amplitude variable-phase individual force at spaced locations on the fuselage. These individual forces (F.sub.1, F.sub.2) combine to exert a controllable-amplitude resultant vibratory force (F.sub.R) on the structure. The servocontroller is adapted to be supplied with a single sinusoidal control signal and is operative to cause the frequency and phase of the resultant vibratory force to be identical to the frequency and phase of the control signal and to cause the amplitude of the resultant vibratory force to be proportional to the amplitude of the control signal.

Abstract: An actively-controlled resonant-type force generator (20) is adapted to be attached to a structure (21), and includes a mass (23) mounted for movement relative to the structure and a plurality of springs (22, 24) operatively arranged between the mass and the structure. A servoactuator (26) is arranged to controllably excite the mass-spring system. The actual force (F.sub.a) transmitted from the mass to the structure is compared with a commanded force (F.sub.c) to produce a force error signal (F.sub.e). The actuator is caused to produce a velocity as a function of the error signal. The gain of the closed force loop is selected so that the resonance of the mass-spring system has an effective damping ratio (.zeta.) greater than about 0.5, and preferably about 0.7. Thus, the mass-spring system will not be substantially resonantly excited by vibrations of the structure near its resonant frequency (.omega..sub.n).

Abstract: An actively-controlled resonant-type force generator (20) is adapted to be attached to a structure (21), and includes a mass (23) mounted for movement relative to the structure and a plurality of springs (22, 24) operatively arranged between the mass and the structure. A servoactuator (26) is arranged to controllably excite the mass-spring system. The actual force (F.sub.a) transmitted from the mass to the structure is compared with a commanded force (F.sub.c) to produce a force error signal (F.sub.e). The actuator is caused to produce a velocity as a function of the error signal. The gain of the closed force loop is selected so that the resonance of the mass-spring system has an effective damping ratio (.zeta.) greater than about 0.5, and preferably about 0.7. Thus, the mass-spring system will not be substantially resonantly excited by vibrations of the structure near its resonant frequency (.omega..sub.n).

Abstract: A device (19) for generating a rotating force vector and an oscillatory couple includes a plurality of non-concentric eccentric masses (22A, 22B, 22C, 22D, 22E, 22F) co-rotating at the same angular speed; and means (24A, 24B, 24C, 24D, 24E, 24F) for individually controlling the angular position of each of the masses; whereby, by selectively controlling the angular position of each eccentric mass, the device may generate a desired rotating force vector and a desired oscillatory couple. In use, the device performs an improved method for opposing the propagation of vibration from a dynamically unbalanced rotating rotor through a supporting structure (12).