Abstract: A phase locked distributed time reference system for use in multiplexed communication bus structures. This system is composed of two parts, a master and a slave time reference or clock. The master time reference is a high accuracy clock that is a dedicated distributed clock system which uses an appropriate communication bus, such as the MIL-STD-1553, for distribution but which completely bypasses the other bus protocols and operations. This master time reference would ideally be placed on the processor bus for immediate access. The high order segment, which extend the master time reference to the desired range, i.e. 30 days or longer, is transmitted via the normal bus communications without the need for any special data handling. The only requirement is to update the signal at a cyclic rate faster than the roll over time of the low order segment plus any delay in transmission and assembly of the two halves.

Abstract: An active damage interrogation (ADI) system (and method) which utilizes an array of piezoelectric transducers attached to or embedded within the structure for both actuation and sensing. The ADI system actively interrogates the structure through broadband excitation of the transducers. The transducer (sensor) signals are digitized and the transfer function of each actuator/sensor pair is computed. The ADI system compares the computed transfer function magnitude and phase spectrum for each actuator/sensor pair to a baseline transfer function for that actuator/sensor pair which is computed by averaging several sets of data obtained with the structure in an undamaged state. The difference between the current transfer function and the baseline transfer function for each actuator/sensor pair is normalized by the standard deviation associated with that baseline transfer function.

Abstract: The present invention is directed to a new and improved flexible hose assembly for transmitting pressurized air, gases and/or fluids between two spaced apart components. The hose assembly includes an inner liner surrounded by a helix formed of thermoplastic material having a substantially flat surface portion for bonding with the inner liner, eliminating the need for a outer cord to prevent the helix from floating relative to the liner. A self-adjusting retainer ring serves to compress the flexible hose onto the beaded end portion of a component with increasing pressure as the pressure increases within the hose assembly. Preferably the retainer ring is formed from a single piece of thermoplastic material.

Abstract: The present invention is directed to a unique foldable winglet assembly adaptable for use with an aircraft for maximizing the wing span of the aircraft during cruise operation while reducing wing bending moment during extreme flight maneuvers. A foldable winglet is pivotally joined to the aircraft wing and is rotatable during flight between a retracted position and a fully extended position. An actuator is mounted on the aircraft wing and attached to the foldable winglet. When the aircraft reaches cruise operation, the actuator can be manually or automatically energized to pivot the winglet from a substantially vertical, retracted position to a fully extended position wherein the winglet becomes an extension of the wing. During cruise, the wing and winglet form an enlarged wing that serves to maximize lift of the aircraft.

Abstract: An insulation system for the fuselage walls of an aircraft. The insulation is a formed-in-place, sprayed-on foam that is applied against a barrier material that is draped against the inside of the exterior skin of the fuselage and over any inwardly projecting structural members attached to the exterior skin. No substantial portion of the barrier material passes underneath any laterally projecting portions of the structural members, so that the subsequently solidified, semi-flexible foam (i.e. insulation) can be removed at a later time for necessary inspections of the aircraft, without being trapped behind these lateral projections. The foam is preferably fire retardant and hydrophobic. An additional protective layer may also be sprayed on to the outside surface of the insulating foam.

Abstract: An intercept missile testing method which includes the steps of launching a test missile threat from a first location on a substantially vertical trajectory, e.g., with a flight path angle greater than about 70.degree., towards an intercept point, and launching a test intercept missile from a second location on a substantially vertical trajectory, e.g., with a flight path angle greater than about 70.degree., towards the intercept point. The flight paths are selected so that the test intercept missile will intercept the test missile threat exoatmospherically, at an intercept (engagement crossing) angle of less than about 30.degree.. Preferably, the launch velocities and trajectories of the test intercept missile and the test missile threat are selected so that the intercept will occur exoatmospherically when the test missile threat is on a downward trajectory at a velocity of 5-8 km/sec, while the test intercept missile is on an upward trajectory at a velocity 5-9 km/sec.

Abstract: A method for compensating a reference signal used in a coherent receiver of a micro-doppler sensor having a transmitter includes the steps for: (a) repeatedly measuring phase differences between a signal emitted by the transmitter a first time and a previous signal emitted at a previous time so as to produce a plurality of phase error signals; (b) accumulating the phase error signals over a propagation time between the transmitter and the coherent receiver so as to produce a cumulative phase error signal; and (c) modulating a signal produced by the transmitter at the end of the propagation period so as to generate a compensated reference signal having a phase characteristic substantially identical to the signal produced by the transmitter at the beginning of the propagation period. A phase error or noise compensator, which can form part of a micro-doppler ladar system, is also described.