Abstract: A method and system of managing an aerial vehicle trajectory is provided. The remote trajectory management system (RTMS) for a fleet of aircraft includes an input specification module configured to manage information specifying flight-specific input data used to generate a trajectory, an aircraft model module including data that specifies a performance of the aircraft and engines of the aircraft, a predict 4D trajectory module configured to receive the specified inputs from the input specification module and an aircraft performance model from aircraft model module and to generate a 4D trajectory for a predetermined flight, and a trajectory export module configured to transmit a predetermined subset of the predicted trajectory to the aircraft.

Abstract: Method for conditioning a power supply for starting a jet engine having an electrical starting system with an auxiliary power unit in parallel with a DC power supply.

Abstract: Methods for determining a flight path for a data-collecting aircraft having a sensor may include defining a data-collecting area, subdividing the data-collecting area into zones, defining a waypoint for each of the zones to define a set of waypoints, and determining a flight path for the data-collecting aircraft incorporating the waypoints.

Abstract: A heat dissipating assembly, for dissipating heat, having at least one heat producing component and a heat sink having phase change material conductively coupled to the at least one heat producing component.

Abstract: A method and system for an integrated ejector valve assembly is provided. The integrated ejector valve assembly includes a first valve assembly configured to control a flow of relatively lower pressure fluid from a first inlet port, a second valve assembly configured to control a flow of relatively higher pressure fluid from a second inlet port, a first actuation chamber configured to close the first valve assembly, a second actuation chamber configured to close the second valve assembly, and a third actuation chamber configured to open the second valve assembly.

Abstract: A mounting bracket assembly for an electrical cable having a Faraday shield configured to allow at least one conductor passing through the assembly to a fire detector wherein the Faraday shield electrically terminates into the receiving end of the assembly without the need for additional electrical connections.

Abstract: A method of flying an aircraft, where the aircraft has an associated performance envelope, along a flight path based determining an altitude profile for a cruise-climb along the flight path based on the performance envelope of the aircraft and flying the aircraft along the flight path to approximate the altitude profile.

Abstract: An actuator having a first actuating channel, having a first motor, and a second actuating channel having a second motor where the output of the first actuating channel and the output of the second actuating channel are synchronized and methods of mechanically synchronizing two outputs of a two channel actuator.

Abstract: A method and hold path computation system for automatically generating a hold path for an aircraft flying in a holding pattern, wherein the holding pattern is defined by one or more orbits within a selectable holding area are provided. The system includes a processor configured to receive a hold departure time indicating a time the aircraft is to leave the hold path to meet a required time of arrival (RTA) at a waypoint, determine a present position of the aircraft within the holding pattern, and determine an amount of time to complete a current hold orbit. The processor is also configured such that if the determined amount of time to complete a current hold orbit is less than or equal to the hold departure time, maintain the aircraft flying in the holding pattern and determine an amount of time by which to shorten the next orbit to exit the holding pattern at the hold departure time.

Abstract: A method and system for a fan assembly that includes a fan casing having a longitudinal centerline axis extending from an upstream inlet opening to a downstream outlet opening is provided. The fan assembly also includes a first substantially cylindrical casing segment extending circumferentially about and substantially axially aligned with tips of a plurality of blades extending from a rotor hub, the first casing segment including a first inner diameter that is greater than the rotor diameter, a second casing segment configured to extend axially in a direction opposite a flow of fluid through the fan casing, the second casing segment including a second inner diameter, the second inner diameter less than the first inner diameter and the rotor diameter, and a third casing segment including the first inner diameter along a first circumferential edge, the second inner diameter along a second circumferential edge, and a surface extending therebetween.

Abstract: A method and system operating an aircraft system are provided. The gas turbine engine system includes a low-pressure (LP) shaft, a high-pressure (HP) shaft, a constant speed mechanical drive assembly having an input and an output, the input mechanically coupled to the LP shaft, the output mechanically coupled to a constant frequency (CF) electrical generator, and an accessory gearbox assembly having an input and an output, the input mechanically coupled to the HP shaft, the output mechanically coupled to a variable frequency (VF) electrical generator.

Abstract: A method and system for a refueling drogue coupling system are provided. The system includes a coupling latch assembly coupled to the coupling outlet wherein the coupling latch assembly includes a latch member configured to matingly engage a complementary latch-receiving member of a refueling probe. The coupling latch assembly further includes a latch member actuator operatively coupled to the latch member to permit the latch member to move from a first locked position to a second unlocked position. A probe position sensor is configured to detect a position of the refueling probe. A hose tension sensor is configured to measure a tension in a hose coupled to the coupling inlet. A drogue control system is positioned on the refueling drogue coupling system and communicatively coupled to the latch member actuator, the probe position sensor, and the hose tension sensor.

Abstract: A communication system and method includes a main bus that operates in accordance with a standard limited to a linear topology, a bus controller coupled to the main bus and configured to send and receive messages on the main bus, and a first remote terminal coupled to the main bus and configured to send and receive messages on the main bus including the messages sent by the bus controller. The system and method also includes a repeater coupled to the main bus and configured to send and receive messages on the main bus including the messages sent by the bus controller and by the first remote terminal, and second and third remote terminals coupled to the repeater, wherein the second and third remote terminals send and receive messages on the main bus via the repeater.

Abstract: A method of transmitting aircraft flight data for an aircraft from the aircraft to a destination server via a wireless communication link with the method including determining an operational status of the aircraft, determining flight data to be transmitted, and transmitting the determined flight data to be transmitted to the destination server.

Abstract: A method assembling a cable connector system and an alignment insert are provided. The alignment insert includes a body having a first planar surface, a second planar surface, and a thickness extending therebetween. The body includes an outer peripheral surface sized complementarily to an inner surface of a first connector portion and further including one or more slots therethrough and extending from the outer peripheral surface inwardly a first predetermined distance. A first width of each of the one or more slots and the predetermined distance based on an orientation of a connector pin positioned within the first connector portion.

Abstract: An electrical architecture for an aircraft providing power for the aircraft by generating power from a high pressure spool and a low pressure spool of a turbine engine. The spools can be used to drive corresponding generators; the power from which can be used to supply the various loads of the aircraft.

Abstract: A flight management system for use in automatically generating a flight path trajectory for an aircraft. The flight path trajectory includes a plurality of waypoints and a plurality of vectors that extend between each waypoint of the plurality of waypoints. The flight management system includes a processor that is configured to calculate a first flight path trajectory including an origin waypoint and a destination waypoint. A tactical command that indicates a change in flight trajectory is received. A second flight path trajectory based at least in part on the tactical command is calculated. The calculated second flight path trajectory includes a departure waypoint along the first flight path trajectory, an intercept waypoint along the first flight path trajectory, and a departure vector from the departure waypoint to the intercept waypoint.

Abstract: A method and apparatus for protecting a heat sensitive component from high temperature, mechanical shock and moisture are provided. An enclosure includes an outer housing surrounding an inner cavity configured to receive a heat sensitive component therein, a cover configured to matingly engage the outer housing such that the inner cavity is sealed from an environment external to the enclosure, wherein at least one of the outer housing and the cover are formed from a ceramic material.

Abstract: Methods for flying multiple aircraft in a predetermined formation in which a relative navigation grid is emitted from at least one of the aircraft, a spatial relationship is calculated based on the emitted relative navigation grid, and a relative position of at least one aircraft is altered to position the aircraft in the predetermined formation when the spatial relationship does not conform with the predetermined formation.

Abstract: A butterfly valve for controlling the flow of fluid within a bore, including a butterfly and at least one ring extending at least one of substantially and completely around a perimeter of the butterfly and adapted to develop an expansion force in the radial direction when the at least one ring is in a contracted state with respect to the radial direction, wherein the at least one ring is secured to the butterfly in the contracted state and radial expansion due to the developed expansion force of the at least one ring is effectively restrained, wherein the butterfly valve is adapted to operate, when placed in a bore, without friction or substantially without friction between the at least one ring and the bore when the butterfly valve is placed in a closed position within the bore.