Abstract: An aircraft fuel tank system includes at least one fuel tank having a plurality of interconnected bays and a vent arranged so as to allow an inward venting of atmospheric air. The system is arranged so as to direct the inwardly vented air along a vent duct. The vent duct is arranged so as to convey the inwardly vented air to substantially each one of the interconnected bays.

Abstract: A turboshaft engine includes an inlet, a swirl frame mounted downstream of the inlet, and an inlet seal mounted to one of the inlet and the swirl frame extending toward the other of the inlet and the swirl frame. The inlet seal includes a support member and an elastomeric member extending from a first end portion coupled to the support member to a second, cantilevered end portion.

Abstract: The invention concerns a structure (3) for feeding air to an auxiliary power unit (2) of an aircraft (1) comprising a pressurized cabin (10) and an auxiliary power unit (2), the structure comprising: a pipe (30) for feeding air to the auxiliary power unit; a unit (4) for controlling the airflow fed to the auxiliary power unit; and a valve (31) for the intake of air outside the aircraft, disposed at the inlet of the feed pipe (30), the opening of the valve being driven by the control unit (4). The structure is characterized in that it further comprises a circuit (32) for injecting air from the pressurized cabin into the auxiliary power unit feed pipe. The invention also concerns a method for feeding air to an auxiliary power unit.

Abstract: The purpose of this invention, which is referred to as a vacuustat, is to generate buoyancy in the atmosphere by means of an evacuated or partially evacuated container, rather than by using a lighter-than-air lifting gas such as hydrogen or helium. This particular vacuustat design comprises a flexible airtight membrane supported by a fractal tensegrity internal structure consisting of a relatively small mass of compressive members forced into higher-order buckling modes through use of tension members. The advantages of such a design over conventional aerostats include superior buoyancy control for ascent and descent, greatly increased flight endurance, and cost-effectiveness in operation. This particular vacuustat design has a much greater lifting efficiency than previous designs, and should also be easier and more cost-effective to manufacture.

Abstract: A fuselage portion of a vehicle (e.g., an aircraft) is disclosed. The fuselage portion comprises a frame; a floor beam attached to the frame and comprising ends; a structural stanchion comprising a first end and a second end; a first structural coupling joining the first end of the structural stanchion and the floor beam; a second structural coupling joining the second end of the structural stanchion and the frame; a non-structural stanchion comprising a third end and a fourth end; a first non-structural coupling joining the third end of the non-structural stanchion and the floor beam; and a second non-structural coupling joining the fourth end of the non-structural stanchion and the frame.

Abstract: A laminar flow control surface having a foraminous section (also referred to below as a foraminous portion, 251) of a skin (250) of a vehicle to permit low temperature fluid to flow through the foraminous section to a heat exchanger (236), to reduce drag of the vehicle and to dissipate heat from the heat exchanger. The foraminous section (251) and the heat exchanger (236) synergistically reduce drag and transfer heat from the heat exchanger. The vehicle may be an aircraft with a laminar flow control system including a foraminous portion on a leading edge of the aircraft. While the aircraft is in flight, a portion of air impinging near the foraminous portion may flow laminarly about the leading edge, and another portion of the impingingair may flow through the foraminous portion to a heat exchanger to transfer heat from the heat exchanger to the air.

Abstract: A method of supersonic thrust generation includes generating a thrust supersonic exhaust plume having a first average velocity from an engine, and expelling a bypass exhaust plume having a second average velocity from the engine, the first average velocity greater than the second average velocity, so that the bypass exhaust plume inhibits coalescence of an engine exhaust plume compression shockwave.

Abstract: Systems and methods are provided for swapping the battery on an unmanned aerial vehicle (UAV) while providing continuous power to at least one system on the UAV. The UAV may be able to identify and land on an energy provision station autonomously. The UAV may take off and/or land on the energy provision station. The UAV may communicate with the energy provision station. The energy provision station may store and charge batteries for use on a UAV. The UAV and/or the energy provision station may have a backup energy source to provide continuous power to the UAV.

Abstract: A system and method for detaching an extractable unit from an extraction unit pulling the extractable unit in an extraction direction out of a cargo bay of an aerospace vehicle for aerial delivery. The system includes a detachment unit which is connectable to an extractable unit and which is operable for controllably detaching an extraction unit from the extractable unit, a guiding system and a release unit. The release unit is movably attached to the guiding system and physically connected to the detachment unit such that the release unit is movable with an extractable unit to which the detachment unit has been connected in the extraction direction along the guiding system. The release unit is controllable to operate the detachment unit to which the release unit is connected for detaching an extraction unit from the extractable unit.

Abstract: A wing for an aircraft, comprising a main wing, a slat, and a connection assembly for movably connecting the slat to the main wing. The connection assembly comprises first and second link elements. The first link element has a first link end rotatably mounted to the slat via a first joint, and a second link end rotatably mounted to the main wing via a second joint. The second link element has a first element end rotatably mounted to the slat via a third joint, and a second element end rotatably mounted to the main wing via a fourth joint. The first joint, the second joint and the third joint are formed as spherical joints or as universal joints, while the fourth joint is formed as a hinged joint, wherein the hinge axis is inclined between a wing thickness direction and a wing span direction.

Abstract: A supply system for providing at least oxygen depleted air and water in a vehicle includes at least one hydrogen supply means, an air channel having an inlet and an outlet, an air cooled fuel cell unit couplable with the hydrogen supply means and arranged inside the air channel and at least one catalytic converter couplable with the hydrogen supply means and arranged between the fuel cell unit and the outlet of the air channel inside the air channel. The air cooled fuel cell unit is adapted for conducting a fuel cell process under consumption of air flowing from the inlet of the air channel through the air cooled fuel cell unit and hydrogen from the hydrogen supply means. At least one catalytic converter is adapted for producing water and oxygen depleted air under consumption of hydrogen from the at least one hydrogen supply means and air.

Abstract: In some implementations, in an emergency in the vehicle, an emergency evacuation path is illuminated using the light emitted from the emergency evacuation rope where at least a portion of the emergency evacuation path extends to a location outside the vehicle. Egress of occupants along the emergency evacuation path is enabled using an emergency evacuation rope.

Abstract: A multilayered active surface is presented whose rugosity can be controlled by an applied electrical field. Varying the applied electrical field can control the rugosity of the surface which makes contact with a fluid, and thereby can affect instabilities of the boundary layer. A middle layer of the multilayered active surface can be made of a compliant electroactive material. In some cases, a pre-stretch in the middle layer can predefine a rugosity of the multilayered active surface without an applied electrical field, in which case an applied electrical field can further alter the rugosity in both amplitude and spatial periodicity and ultimately result to a smooth surface for a higher value of the applied electrical field. A top layer and a bottom layer are constructed using conductive material and uses as electrodes coupled to a voltage source to generate the electric field that controls the rugosity of the surface.

Abstract: A refueling device for use in in-flight refueling operation between a tanker aircraft and a receiver aircraft includes a selectively steerable body and a controller. The selectively steerable body configured for being towed by a tanker aircraft via a fuel hose at least during in-flight refueling, and includes a boom member having a boom axis and configured to enable fuel to be transferred from the fuel hose to a receiver aircraft along the boom axis during the in-flight refueling operation. The controller is configured for selectively steering the body to an engagement enabling position spaced with respect to the receiver aircraft and for aligning the boom axis in an engagement enabling orientation at the spaced position, and for subsequently moving the boom member along the boom axis towards the receiver aircraft for enabling fuel communication therebetween.

Abstract: A de-icing device is provided that includes a piccolo tube integrated with a front bulkhead for limiting an inner volume of a perforated front lip. The piccolo tube is in contact with a noise reduction cellular structure provided with perforations and hot air circulation channels delivered by the piccolo tube, the de-icing hot air being diffused through the perforations and channels of the cellular structure, on the perforations facing the front lip.

Abstract: A fuselage structure includes a pressure bulkhead and a frame being arranged behind the pressure bulkhead. The fuselage structure includes a first beam element with a first cantilever and a second cantilever, while the first beam element extends in a vertical direction of the fuselage structure. The first cantilever and the second cantilever protrude from the first beam element in a first direction toward the frame. The first direction of both cantilevers is inclined at a first angle with respect to a longitudinal direction of the fuselage structure. An aircraft with a fuselage structure and a method for manufacturing a fuselage structure are also described.

Abstract: The invention relates to a method for mounting an engine (1) on an aircraft strut (3) comprising engine suspension members (31) integral with the strut, the engine being integral with a suspension cradle (6) whereby it is suspended from the strut, the method comprising a step of hoisting the engine in a vertical direction as far as the strut then a step of approaching the strut by a movement of the engine in another direction, characterised in that an intermediate part (7) is fixed to the strut beforehand, by attaching it to said suspension members (31), said intermediate part (7) having an interface intended to cooperate with a complementary interface provided on the cradle (6), in such a way as to position the cradle relative to the intermediate part at the end of the approach movement to the strut. The invention also relates to the system for implementing the method.

Abstract: An exhaust arrangement is for an aircraft having sensing equipment and a front prop engine. An extension mounts on the underside along an edge of the fuselage to direct exhaust from the engine's exhaust pipes to a point to or past the sensing equipment typically exposed at the mid-section of the aircraft. An extension inlet mounts adjacent the pipe and defines a funnel or conical orifice not directly affixed to the pipe. One or more conductors for the extension then extend from the inlet to convey the exhaust to an outlet of the extension. Preferably, multiple conductors can be used with an expansion joint provided between them. The outlet preferably diverts exhaust away from the tail end of the aircraft. To mount the extension to the aircraft, several arrangements of supports including rods, lugs, angles, and the like hold the extension in vertical, lateral, and axial directions to the aircraft.

Abstract: An embodiment of a jet engine air inlet providing anti-icing, and optionally, engine noise reduction, includes a rigid frame defining a gridwork of contiguous cells. A cap skin has an outer surface sealingly attached to an inner surface of the frame. An outer skin has an inner surface sealingly attached to an outer surface of the frame and contains a plurality of openings therein. Each of the openings is disposed in fluid communication with a corresponding one of the cells, each of which can comprise a Helmholtz resonator. A serpentine manifold extends adjacent to an inner end of each of the cells and contains a plurality of apertures in a sidewall thereof, each of which is disposed in fluid communication with a corresponding one of the cells.

Abstract: A method for controlling in-flight refueling of a receiver aircraft having a fuel receptacle, comprising: automatically steering a refueling device to an engagement enabling position, including: repeatedly determining a spatial disposition of the refueling device with respect to the receiver aircraft, the refueling device being capable of engaging and refueling the receiver aircraft via a boom member, when the device arrives to the engagement enabling position at which the boom member is in a predetermined spaced and spatial relationship with respect to the fuel receptacle of the receiver aircraft; repeatedly calculating steering commands based at least on the repeatedly determined spatial dispositions and characteristics of a spatial control system of the refueling device; sending the steering commands to the spatial control system; whereby at the engagement enabling position, the boom member of the refueling device is capable of engaging with the fuel receptacle to enable refueling of the receiver aircraft.