Abstract: The invention relates to pseudo porosity standards, and methods for their manufacture and use, which may substantially mimic the effect porosity has on ultrasonic sound as it passes through a composite laminate. An ultrasonic inspection reference standard for composite materials having porosity may include a member having at least one thickness. The member may be defined by at least one hollow, non-spherical shaft. The member may be manufactured from a fiber-free polymer resin using a stereo lithography process. The non-spherical shaft may scatter and attenuate ultrasonic energy. The reference standard may replace more costly, porous, fiber-reinforced, composite reference standards in the aircraft industry and in other non-aircraft applications.

Abstract: A navigation system takes a graphical input and translates it into an alpha-numeric entry generally including latitude and longitude information. The system interprets the graphical entry, determines if a waypoint already exists or is depicted at the geographical location identified by the graphical entry and creates a new waypoint if no waypoint already exists or is depicted at the geographical location.

Abstract: A method of and a system for controlling personal air vehicle (PAV) traffic provides a take-off-and-landing zone, and a forward flight zone. The take-off-and-landing zone may be from the ground up to a first altitude. The forward flight zone may be from the first altitude up to a second altitude. A maximum airspeed is provided in the take-off-and-landing zone. Minimum and maximum airspeeds are provided in the forward flight zone. In the forward flight zone there is a single heading for each altitude. Any change in heading must be accompanied by a change in altitude.

Abstract: The invention relates to methods of measuring an aircraft under simulated flight-loads while the aircraft is not in-flight. While the aircraft is under the simulated flight-loads, positions of one or more portions of the aircraft may be measured in order to determine how the aircraft is performing under such loads. The aircraft may be readjusted and/or redesigned based on the measurements in order to reduce drag on the aircraft.

Abstract: A method of controlling attitude of a spacecraft during a transfer orbit operation is provided. The method includes providing a slow spin rate, determining the attitude of the spacecraft using a unified sensor set, and controlling the attitude of the spacecraft using a unified control law. The use of a unified set of sensors and a unified control law reduces spacecraft complexity, cost, and weight.

Abstract: The invention relates to the use of one or more targets to measure surfaces. The target may comprise a first portion adapted to reflect a laser beam towards a laser tracking device, a second portion adapted to reflect a light beam towards a photogrammetry device, and a third portion adapted to identify to a computer a unique identifier of the target.

Abstract: A window assembly and method for its installation is provided. The window assembly may include multiple transparent panels covering an opening of an aircraft fuselage. One or more retainer members and a flexible clip member may be utilized to secure the window assembly over the opening of the fuselage.

Abstract: A net shaped latex vacuum bag as used in the fabrication of composite structural parts having complex shapes. Liquid latex is first allowed to air dry in the form of a thin flat, flexible sheet. The latex sheet is then vacuum formed over a tool having the complex shape of the part to be fabricated and assumes the shape and configuration of the tool's outer surface. The latex sheet is then rapidly cured at an elevated temperature, so as to permanently assume the part's shape for subsequent use in forming composite structural parts of the same complex shape. In one embodiment, the latex sheet may be formed on the tool by dipping the tool in liquid latex, allowing the latex coating to dry, and cutting the dry latex coating to permit separation of the tool from the latex coating which is then used in composite part fabrication.

Abstract: Reference signals are combined with a chop frequency signal in a pulse width modulator (PWM) to provide plural inputs to a multi-phase H-bridge amplifier. Also provided to the bridge amplifier is a high voltage DC input which is converted by the pulsed inputs to the bridge amplifier to a variable AC voltage for driving a motor. The AC drive voltage is also provided to a variable frequency voltage-controlled oscillators (VCOs) in a feedback arrangement, with the variable frequency VCO outputs heterodyned with each of plural outputs of a multi-phase ring oscillator to provide plural baseband signals having a constant phase relationship at a high frequency. The baseband signals form the aforementioned reference signals provided to the PWM in the feedback arrangement with closed loop control and frequency and phase discrimination using phase lock loop techniques for synchronous motor control over a range of DC-100 kHz with 0-25 MHz VCOs.

Abstract: In one embodiment, a backfire antenna comprises a cup-shaped member defining an outer aperture and an interior cavity, a splash-plate disposed within a plane, and a dipole assembly comprising first and second arms. The first and second arms are both oriented non-parallel to the splash-plate towards the plane.

Abstract: A data delivery system is provided for delivering updated data information from a sending database system to a receiving database system. The sending database system periodically obtains, from a database updating system, a new data set having both updated data objects and unchanged data objects relative to a loaded data set stored, for example, at a receiving database system. The sending database system performs individual validity checks on the updated data objects and the unchanged data objects. A master validity check is also performed by the sending database system on the individual validity checks for the updated data objects and the unchanged data objects. The individual validity checks and the master validity check may, for example, be cyclic redundancy checks. The receiving database system, such as a flight information system associated with an aircraft, receives the individual validity checks, the master validity check and the updated data objects delivered from the sending database system.

Abstract: In one embodiment, an automated system for mating a launch device to a launch platform may include a launch platform having a first electrical connector, and a interface member attached to the launch device. The interface member may include a second electrical connector configured to automatically couple to the first electrical connector of the launch platform.

Abstract: In one embodiment, an aircraft comprises a plurality of hoop frame support members and a landing gear enclosure comprising a curved surface. The plurality of support frame support members abut against and extend over the curved surface to provide support to the landing gear enclosure. In another embodiment, loads are transferred from a landing gear strut through a strut fitting, through at least one inner surface of the landing gear enclosure, through at least one outer surface of the landing gear enclosure, and into the plurality of hoop frame support members.

Abstract: An apparatus for providing auxiliary signals on a high speed electrical signal network is provided such that the auxiliary signals may be used for independent monitoring or communication of monitored information without affecting data or bit error rates for the primary high speed data signals. The auxiliary signals may be used as part of a built-in testing of a network, including electrical time-domain reflectometry measurements to determine fault locations in a network.

Abstract: Methods are disclosed for producing a hole in a work-piece having first and second layers of material. The first layer of material contains a full-sized hole through the first layer of material. The first layer of material is positioned adjacent the second layer of material. An orbital drill is secured to the first layer of material to position a cutting tool of the drill within the through-hole. During operation, when the cutting tool is used to cut a hole in the second layer of material, the alignment keeps the orbital drill stationary.

Abstract: The invention relates to systems and methods which may allow the determination of a correction factor between full scale antennas and scale antennas in order to determine the coupling loss of the full scale antennas on full scale structures based on models of the full scale structures.

Abstract: Systems and methods are provided for determining a final heading of a turning vehicle, such as a rotorcraft. The system may include an algorithm that calculates an advance prediction of a final heading that will be achieved after control input is terminated.

Abstract: The invention discloses differing embodiments of methods, aircraft, and apparatus for communicating the braking conditions of a runway. In one embodiment, braking information may be determined from a first aircraft which has landed on the runway. The braking information may be communicated to air traffic control and/or a second aircraft. Communication of the braking information may take place utilizing an Automatic Dependent Surveillance Broadcast system (ADS-B) and/or other type of automatic networking system.