Abstract: A system for an aircraft includes a compressor for a vapor cycle cooling system (VCCS) for providing cabin air conditioning; an APU for mechanically driving the VCCS compressor; and a starter-generator-motor (SGM) apparatus operable in any of a starter mode, a generator mode, or a motor mode. The SGM apparatus includes: (i) a first coupling element for coupling the SGM apparatus to the APU such that, in the starter mode, the SGM apparatus is used in driving and starting the APU, (ii) a second coupling element for coupling the SGM apparatus to the VCCS compressor such that, in the motor mode, the SGM apparatus mechanically drives the VCCS compressor, and (iii) a set of electrical power terminals at which, in the generator mode, the SGM apparatus provides electrical output power for powering the aircraft electrical system (including the VCCS condenser fan and VCCS evaporator fans) and, in the starter mode and motor mode, the SGM apparatus receives electrical input power from an external electrical power source.

Abstract: A global network is described for accessing aircraft remotely via a wide area network. Aircraft flight and operational data stored on the aircraft may be directly accessed via remote workstation or downloaded by centralized automatic processes for later analysis and diagnosis.

Abstract: An apparatus for testing for the susceptibility of an aircraft system to radio frequencies comprises a wireless module for generating radio signals that sweep each of the 2.4 GHz frequency band and the 5 GHz frequency band. A first amplifier is configured for amplifying signals in the 2.4 GHz band, and a second amplifier is configured for amplifying signals in the 5 GHz band. The apparatus comprises at least one dual band antenna for transmitting the signals in each of the 2.4 GHz and the 5 GHz bands.

Abstract: A system and method for simulating the radio frequency environment of an aircraft is described. Simulated location data and navigational aid data is used to calculate a digital representation of the radio frequency environment of an airplane at the simulated location. The digital representation of the radio frequency environment is converted into an analog signal and provided to the navigational system of the aircraft.

Abstract: A system and method for installing a window panel assembly into an aircraft is disclosed. In one embodiment, the system has a retaining device having an outside edge that is sealed against an inboard surface of the aircraft skin. A biasing member is mounted to an inboard edge of the retaining device, and a plurality of protrusions (which are secured onto the biasing member) press against the window panel. This pushes the window panel outward, maintaining a seal around the edge of the window.

Abstract: A propeller blade assembly including a propeller blade having a leading edge, and a trailing edge extending between a tip and a hub, and an electrically conductive band extending longitudinally on either or both of the leading edge and trailing edge. The electrically conductive band secured to the leading edge of the propeller serves as an entry point on the aircraft and conductive channel into the airframe thereby avoiding the potentially damaging effect of the lightening on the carbon fiber composite propeller.

Abstract: Disclosed is a method for controlling the flammability of fuel vapors in an aircraft main fuel tank that is located in whole or in part in the fuselage contour. The method comprises a fuel system architecture and fuel consumption sequencing maintaining liquid fuel in said main tanks during all normal operations. Ceasing the withdrawal of fuel from the main tank when the fuel reaches a predetermined level thereby limiting the volume and flammability exposure time of the fuel vapor ullage. Once the predetermined level is met the fuel is supplied from wing tanks throughout the remainder of the mission. The predetermined main tank fuel level at which wing tank fuel begins to be consumed is determined by the aircraft flight reserves fuel volume stored in the main tank as well as the amount necessary to continuously submerge the main tank fuel pumps during the entire mission.

Abstract: Disclosed is a foldable tracking table assembly comprising a primary leaf, and a secondary leaf rotatably secured to the primary leaf and a table bracket secured to the opposite end of the primary leaf The table bracket in turn is secured to an adapter plate which is atop one or more pillow blocks. The pillow blocks are disposed atop linear rails upon which the pillow blocks are capable of longitudinally traversing. Adjacent the linear rail is a serrated track parallel to the at least one rail and a serrated pawl capable of locking engagement with the serrated track. A solenoid facilitates the locking engagement of the pawl with the serrated track wherein a user of the table assembly manually activates the solenoid withdrawing the serrated pawl from locking engagement with the serrated track thereby allowing the table assembly to traverse the linear rail to a position that accommodates the user.

Abstract: An improved flight control system is described, providing for increased or reduced pilot input forces necessary to cause desired control surface deflections.

Abstract: A seat base for use in aircraft has a first cross member, a second cross member, a first leg, a second leg, and a base plate having a first bendable tab and a second bendable tab facing away from the first tab. The first cross member, the second cross member, and the base plate are each configured to be secured to the first and second legs in an extended position and a retracted position. The first and second legs are configured to be secured to seat feet and floor tracking rails. The first and second cross members are secured to the base plate so as to allow for selective rotation of the first and second cross members in response to relative vertical movement of the first leg with respect to the second leg.

Abstract: A structure for use with an electrothermal heating element is disclosed comprising a heating element contained in a mat and heater supports attached to one surface of the mat. The heating element is disposed between the skin and internal structure of an aircraft with the heater supports disposed toward the internal structure thereof. The heater supports maintain an insulating layer of air between the mat and the internal structure of the aircraft.

Abstract: An apparatus for controlling positioning of flaps in an aircraft includes a shift lever movable to each of a plurality of shift lever positions to control positioning of the flaps of the aircraft to each of a respective plurality of associated flap positions. A shift lever indexing plate includes a plurality of engagement positions associated with the plurality of shift lever positions, respectively, the shift lever being coupled to an engagement member, the engagement member moving with the shift lever and being biased to selectively engage a selected one of the plurality of the engagement positions associated with a selected one of the shift lever positions to command the aircraft flaps to the flap position associated with the selected one of the shift lever positions.

Abstract: A system and method for removing condensate from an air conditioning unit is disclosed. The system comprises a conduit including an outlet portion that is connected to a chamber of a housing of the unit at a first location. The conduit includes an inlet portion that is connected to the chamber at a second location where condensate accumulates. A gravitational separator portion which extends below the second location is connected to the outlet portion and the inlet portion. A draining portion having an orifice for allowing condensate to exit the conduit is connected to the gravitational separator portion below the second location. The first location is chosen such that during operation of the unit the pressure at the first location is less than the pressure at the second location.

Abstract: A static charge drain system for an aircraft window includes a resistive probe penetrating an outer ply of the aircraft window, a first end of the probe being exposed at an outer surface of the outer ply of the aircraft window. A second end of the probe penetrates an inner surface of the outer ply of the aircraft window. A conductive drain element is disposed between the outer ply of the aircraft window and an inner ply of the aircraft window and is electrically connected between the second end of the probe and a ground point of the aircraft window.

Abstract: A console for aircraft that is located between two seats which face each other. The console includes an open ledge with a cup holder arrangement. The cup holder arrangement includes two removable holder dividers which can be flipped up or down and held into position by a spring-loaded cam arrangement. The console also includes two inwardly facing surfaces which provide connectors for electronic devices resting on the ledge. A light-emitting face is provided on a back wall of the ledge so that any articles resting on the ledge can be seen in dark environments.

Abstract: A panel-mounted control stick for aircraft providing for roll and pitch input that emulates the response of a traditional floor-mounted control stick. The panel-mounted control stick incorporates a pitch beam input assembly and a roll input assembly for translating the movements of the control stick into movements of aircraft control surfaces.

Abstract: A method for optimizing machining parameters for a cutting process performed on a work piece. Finite element analysis of cutting tool and work material interaction is initially performed. Mechanistic modeling of the cutting process, using results of the finite element analysis, is then performed to provide optimized machining parameters for improved rate of material removal and tool life. Optionally, a two-stage artificial neural network may be supplementally employed, wherein a first stage of the network provides output parameters including peak tool temperature and cutting forces in X and Y directions, for a combination of input reference parameters including tool rake angle, material cutting speed, and feed rate.

Abstract: Attachment bolts and tensioned support systems (e.g., aircraft access systems) are set forth herein. According to one embodiment, an attachment bolt for use in a tensioned support system includes a head portion and a shaft portion extending from the head portion. The head portion has an end face, and the shaft portion has at least one thread and a tip distal to the head portion. A cavity extends entirely through the head and shaft portions and has a linearly extruded segment, an extended diameter at the end face, and an enlarged diameter at the tip. The extended diameter is larger than a diameter of the linearly extruded segment, and the enlarged diameter is larger than the diameter of the linearly extruded segment.

Abstract: Disclosed is a method of computer generating a product specification. The specification is dependent on the selection of a number of options by a consumer. The method utilizes a computer program which receives from user a location in which said product will be used. After that, the user is allowed to select product options. Information regarding rules and regulations for that particular location is made available from separately identified data files on a server. Options required in that particular locations will be automatically added to the specification. When additional options are selected, the program determines whether the product is still in compliance in the location selected. If the added option results in the specification running afoul of a regional rule or regulation, the user will be notified, and advised as to how the violation can be overcome. Once the user is satisfied with the options, and these options are in compliance, the specification is completed and useful for making an order.

Abstract: A method and apparatus for draw forming a flat sheet blank into a 3-dimensional-nacelle nose cap for an aircraft engine in two stages; the blank having an outer annular portion and an inner annular portion. Draw forming the inner annular portion into a shape of an arcuate circular inner wall and then draw forming the outer annular portion into an arcuate outer wall adjacent the inner wall with the combination of walls being U-shaped in cross section.