Abstract: Method and apparatus for measuring the alertness level of the flight crew of an aircraft and raising it when necessary. The system also detects departures from the planned flight profile and provides aural warning.

Abstract: A method for optical signaling for electrical switch control, and in addition, optical powering of the electrohydraulic servovalve by means of opto-electric conversion using solar cells with a battery backup and dual redundancy for reliability. Optical power sources are e.g., laser diode, LED, or high intensity lamp.

Abstract: The method of operating a synchronous machine through estimation of the stator flux utilizing synchronous machine equations and then stabilizing the flux estimation process by providing stabilizing feedback signals with a predetermined transfer function.

Abstract: A control system for an aircraft's electrically driven hydraulic pump. An electronic motor controller having closed loop feedback is utilized to directly control the prime mover speed in response to pump loading.

Abstract: An aircraft modal suppression system which recognizes that the frequency and phase of the body bending mode varies when the weight of the aircraft differs from the design gross weight. An active damper notch filter which is tabulated as a function of aircraft gross weight is utilized, thereby enabling not only the frequency, but also the width and depth of the notch filter to vary according to the gross weight of the aircraft.

Abstract: A phased array design in the shape of a logarithmic spiral. By distributing the elements of the array along a logarithmic spiral-shaped curve, spatial regularities are avoided and the array is therefore able to function over a wide frequency range.

Abstract: An aircraft modal suppression system which recognizes that the frequency and phase of the body bending mode varies when the weight of the aircraft differs from the design gross weight. An active damper notch filter which is tabulated as a function of aircraft gross weight is utilized, thereby enabling not only the frequency, but also the width and depth of the notch filter to vary according to the gross weight of the aircraft.

Abstract: A digital bond tester operating at frequencies in the kHz range and relying upon vibrational modes which can excite all or substantial portions of the test object.

Abstract: A system for starting synchronous motor from a pulse-width-modulated static inverter without using rotor position or speed measurements. The system monitors supply current to the stator and derives a relationship between that current and the magnetizing flux. The system utilizes a narrowband filter that is tuned to pass only the motor currents fundamental component and whose tuned frequency changes with variations in motor speed. Furthermore, the system reduces the excitation provided to the motor after a certain value of line voltage is sensed.

Abstract: A process and method for manufacturing fiber reinforced composite structures without trapping volatiles in the resin matrix. Volatiles from the curing cycle are absorbed into a silicone rubber layer,and a gas impermeable barrier layer outside the silicone rubber layer prevents autoclave atmosphere from permeating into the part. The process is to layer the finished ply build-up, with a ply of FEP (fluorinated ethylene propylene), a layer of silicone rubber to absorb the volatiles, and a layer of impermeable elastomer. The layer of fluoroelastomer is bonded to the silicone rubber to form a reusable, impermeable elastomeric vacuum bag, eliminating the need for disposable edge and surface breathers.

Abstract: An Aircraft Communication, Addressing, and Reporting System (ACARS) to VHF transceiver interface unit (AVIU) which allows direct pilot control of the VHF mode (voice or data) and also commands the ACARS into the proper mode.

Abstract: A corrosion resistant gasket combined with an aircraft antenna, and more particularly to encapsulation of a conductive mesh in a pliable fluorosilicone compound that will not become bonded to mating surfaces and will also migrate upon compression during installation to the threads of attaching hardware utilized between the instrument, antenna, and aircraft structure, thereby reducing corrosion through the attaching hardware, by providing a hermetic seal around the periphery of the envelope of the attached device.

Abstract: In a Frequency Modulated Continuous Wave (FMCW) radar, a radar return signal is mixed with a delayed frequency sweep waveform to gain a ranging signal to noise ratio (RSNR) higher than the RSNR available from mixing the return signal with a transmitted waveform.

Abstract: A high speed packet switch which is inherently non-blocking, requires a minimum amount of buffering, is modular and degrades gracefully with failures. The output destination buffers can each absorb data at the full switch rate to avoid contention and they are filled evenly to minimize buffer size. The architecture only requires few parts types (multiplexers, demultiplexers and crosspoint switches) to operate at high speeds. The output list offers considerable flexibility in the way the data is output, whether it is by priority and/or by time division multiplexed sub destinations.

Abstract: Adjacent wheel brake assemblies on aircraft multi-wheel landing gear are interconnected by a ring spring damped brake rod for torque compensation and to provide the added function of vibration damping.

Abstract: Very large aircraft landing gear using single mounted eight wheel bogie on dual shock struts. A primary or main two-stage shock absorber and a semi-articulating secondary or auxiliary single-stage shock absorber, each of which are mounted using the second and third axles as pivot joints in a four axle, eight wheel truck beam.

Abstract: An apparatus and process for assembling interior components in an aircraft fuselage. A rotating laser is utilized with at least three reference targets and at least one associated part locating target. The reference targets are located in the fuselage and the rotating laser unit establishes a reference plane based on those targets. After establishing the reference plane, a part to be installed is put in approximately its final location and the lasers are used to locate the part based on the at least one attached target for each plane. A control and analysis system is provided in order to properly determine whether the part is in its appropriate position.

Abstract: A remote indication system for a cargo door which indicates the following conditions: Opened, Closed, Latched, Unlocked and Locked. The entire system, including sensors, is independent of the standard flight deck warning system. This provides the required redundancy for the system so that direct observation is not required. An independent system from the standard flight deck warning system and/or the indication for each step of the process rather than just "open/closed" is utilized in the present cargo door control and indicating system.

Abstract: A jet engine fan noise reduction system. The noise reduction system includes active noise control to suppress fan tone noise of an airplane flyover noise signature. The active noise control includes microphones with acoustic transducers upstream and downstream of the engine fan and fan exit guide vane stage to sense control system errors. Control signals are derived from the fan angular speed or blade passing frequency and the error signals sensed by the acoustic transducers. The control output signals actuate (modulate) air control valves on each side of the fan stage to direct conditioned (pressure and temperature regulated) high pressure primary air flow, thereby producing acoustic canceling of fan tone noise.

Abstract: A cable clamp which utilizes a bayonet coupling attachment mechanism when coupled into an electrical connector. Helical ramp grooves formed in the interior of a coupling ring act against bayonet pins mounted on the electrical connector to effect coupling between the two components. A preloaded disc cone shape spring washer becomes effected during the coupling procedure to maintain a no-motion condition on the cable clamp used in high vibration or large shock forces areas. Additionally, a plurality of detent pins are automatically shifted into a holding position at the completion of the coupling action, thereby further contributing to the maintenance of the coupled condition between the cable clamp and electrical connector. Also, a grounding spring is centrally located on the cable clamp body which when coupled to an electrical connector makes interengageable contact thus providing low impedance and additional mechanical strengthening properties to the cable clamp.