291results about "Power plant fuel supply" patented technology

A method for collecting video using an unmanned aerial vehicle (UAV) captures video upon the condition that the UAV flies along a preset flight path, stores the captured video in a storage device of the UAV, and directs the UAV to land on a relay station upon the condition that the UAV is at a certain longitude and latitude relative to the relay station. The method further refuels the UAV at the relay station, transmits the captured video stored in the storage device to a computer of the relay station, and directs the UAV to fly to a next relay station along the flight path.

Embodiments of the invention relate to a stringer (108) adapted to transport fluid in an aircraft wing (100). For example, the stringer may be adapted to provide venting to one or more fuel tanks (111) in the aircraft wing, or may be adapted to provide fuel to the one or more fuel tanks. To perform this function, the stringer comprises a duct member (120) providing a duct and a structural member (121) providing an attachment surface for attachment of the stringer to a wing panel (112). Typically, the stringer is formed from a composite material such as carbon fibre reinforced plastic. A method of manufacturing the stringer is also disclosed.

The invention relates to an outer covering of an apparatus made of an energy generating skin. The energy generating skin encloses a fuel that is capable of reacting with oxygen in an electrochemical reaction to form electricity and gaseous products. In preferred embodiments, the energy generating skin is a hydrogen oxygen fuel cell which serves as the outer covering of an aircraft such as a lighter than air ship or an airplane.

A coupling assembly for fuel transfer includes a first inner conduit attached to a first ferrule adapter and a second inner conduit attached to a second ferrule adapter. An inner conduit coupling engages the first inner conduit sealing mechanism and the second inner conduit sealing mechanism, thereby connecting the first inner conduit to the second inner conduit. A first outer conduit surrounds the first inner conduit. The first outer conduit is attached to the first ferrule adapter and the second outer conduit is attached to the second ferrule adapter. An outer conduit coupling engages the first and second outer conduit sealing mechanism thereby connecting the first outer conduit to the second outer conduit.

A system for efficiently transporting hydrogen from where it can be economically made to where it is most needed using specially designed airships. Technologies such as geothermal, wind, solar, wave tidal or hydropower can be used to generate electricity in-situ or very near to the primary energy sources. This electricity can then be used to produce hydrogen directly from water through various methods known in the art. Hydrogen can be delivered from the place where it is produced to the place where it is needed using an airship in which the hydrogen gas can also be used for generating lift, providing propulsion energy and serving ancillary needs. In other embodiments of the invention, the airship of the present invention can be used to dramatically reduce the cost of transportation of freight, the cost of passenger transportation, and to save on the area required for landing at the points of loading/unloading and embarkation/debarkation. And in another embodiment, the airship of the present invention can be used for transporting water and food to areas where needed. A unique docking system can use a remotely piloted unmanned aircraft flown from the mother craft to carry a guide line into a receiving attachment point.

The modular aircraft system includes a single fuselage having a permanently installed empennage and plural sets of wing modules and engine modules, with each wing and engine module optimized for different flight conditions and missions. The fuselage and each of the modules are configured for rapid removal and installation of the modules to minimize downtime for the aircraft. Short wings having relatively low aspect ratio are provided for relatively high speed flight when great endurance and/or weight carrying capacity are not of great concern. Long wings having high aspect ratio are provided for longer range and endurance flights where speed is not absolutely vital. A medium span wing module is also provided. Turboprop, single turbojet, and dual turbojet engine modules are provided for installation depending upon mission requirements for any given flight. The aircraft is primarily adapted for use as an autonomously operated or remotely operated unmanned aerial vehicle.

A flight-operable, truly modular aircraft has an aircraft core to which one or more of outer wings members, fuselage, cockpit, leading and trailing edge couplings, and empennage and tail sections can be removably coupled and/or replaced during the operating life span of the aircraft. In preferred embodiments the aircraft core houses the propulsive engines, avionics, at least 80% of the fuel, and all of the landing gear. The aircraft core is preferably constructed with curved forward and aft composite spars, that transfer loads across the center section, while accommodating a mid-wing configuration. The aircraft core preferably has a large central cavity dimensioned to interchangeably carry an ordnance launcher, a surveillance payload, electronic countermeasures, and other types of cargo. Contemplated aircraft can be quite large, for example having a wing span of at least 80 ft.

A flight-operable, truly modular aircraft has an aircraft core to which one or more of outer wings members, fuselage, cockpit, leading and trailing edge couplings, and empennage and tail sections can be removably coupled and/or replaced during the operating life span of the aircraft. In preferred embodiments the aircraft core houses the propulsive engines, avionics, at least 80% of the fuel, and all of the landing gear. The aircraft core is preferably constructed with curved forward and aft composite spars, that couple to outer wing sections and possibly other sections using hardpoints. The aircraft core preferably has a large central cavity dimensioned to interchangeably carry an ordnance launcher, a surveillance payload, electronic countermeasures, and other types of cargo. Contemplated aircraft can be quite large, for example having a wing span of at least 80 ft.

A method for generating sensor data is presented. A number of wireless power signals is sent to a group of sensor units. A number of wireless data collection signals is sent to the group of sensor units after the number of wireless power signals have been sent to the group of sensor units. Sensor data in a number of wireless response signals is received from the group of sensor units.

A method of measuring a height of a fuel surface of fuel in an aircraft fuel tank. One or more images of the fuel surface are captured, each image including a fuel surface line where the fuel surface meets a structure. Each image is analysed in order to determine a height of the fuel surface line at three or more points in the image. If the fuel surface line is not a straight line, then an average angle of the fuel surface line can be determined from the points in the image by spatial averaging. Preferably a series of images of the fuel surface are captured over a time period, and an average height of the fuel surface is determined from the series of images by time averaging. The height of the fuel surface line(s) at three or more points is used to determine a volume of the fuel, a mass of the fuel, and/or an attitude of the fuel surface.

A fluid line assembly is disclosed that includes an outer fluid line and an inner fluid line disposed substantially within the outer fluid line. The inner and outer fluid lines each include a slip joint. In an embodiment of the invention, at least one of the slip joints includes a reservoir in communication with the interior of the corresponding fluid line. Among other things, the reservoir is suitable for receiving fluid from the corresponding fluid line as the fluid line assembly is contracted and expelling fluid into the corresponding fluid line as the fluid line assembly is extended. In another embodiment of the invention, the inner and outer fluid lines include a ball joint assembly.

The composite tube comprises a tubular arrangement of knitted fiber characterized by a plurality of interlocking loops. Selected knitted patterns provide desired density or spacing between fibers. Selected fibers may include materials such as Kevlar®, carbon fiber, and combinations thereof. The tubular knitted pattern allows for variable electrical, mechanical and geometrical options. A matrix material is applied over the knitted fiber pattern and is allowed to cure. The matrix material may include a combination of resin and epoxy constituents. The matrix material may be applied by a vacuum bag molding process. Electrical and mechanical properties can also be controlled by selecting desired resin and epoxy constituents. The flexible knitted reinforcing layer allows use of an inflatable bladder to hold the reinforcing layer in the desired shape, thereby facilitating tube constructions of varying shapes and diameters. Continuous application of the matrix material avoids overlapping seams that are prone to delamination.

A tube support structure for an aircraft includes: a parallel movement mechanism configured to support the tube movably in parallel; and an angle adjustment mechanism configured to support the tube angle-adjustably. The parallel movement mechanism includes: an eccentric sleeve, through which the tube passes, configured to adjust a position of the tube in a Z direction perpendicular to the X direction, and a Y direction adjustment mechanism configured to adjust a position of the eccentric sleeve in a Y direction perpendicular to the X direction and the Z direction. The angle adjustment mechanism includes: a first member configured to have a first curved surface and support the tube, and a second member configured to have a second curved surface with a shape corresponding to the first curved surface, have contact slidably with the first curved surface at the second curved surface, and support the first member by the second curved surface. Each of the first curved surface and the second curved surface is formed such that a cross-sectional shape in an XZ plane is a circular arc shape, and an angle of the tube is adjusted by sliding the first curved surface with respect to the second curved surface. Thus, a tube support structure for aircraft, which can suppress a preload, is provided.

An aircraft tail cone comprising a fuselage in which avionic equipment is housed. The tail cone comprises two lateral hatches formed in the fuselage, at least one hatch being formed on each of the two opposite sides of the fuselage. Each hatch is mounted removably with respect to the fuselage so as to take up a closed first position in which the hatch closes a lateral opening in the fuselage, and an open second position in which the open hatch allows access to the inside of the tail cone through the corresponding opening The avionic equipment that requires regular inspection and/or maintenance operations is housed in a part of the tail cone which is accessible through the two lateral openings in the fuselage to a person who remains on the outside of the fuselage.

The waste disposal service panel assembly includes a housing, waste drain valve, rinse/fill valve, handle assembly and service panel door. The housing has a tubular side wall and a base near one end of the side wall. The waste drain valve is at least partially mounted within the housing through the base. The waste drain valve includes an outlet positioned within the housing and an inlet configured to couple to a waste collection tank within a aircraft. The service panel door is pivotally coupled to the housing near an end of the side wall remote from the base. The service panel door has an outer surface configured to substantially match an outer contour of the aircraft's skin, and an outer cap coupled to an inner surface of the service panel door. The outer cap is configured and dimensioned to mate with the outlet to seal the outlet when the service panel door is closed.

A method and apparatus for an optical fuel detection system. The optical fuel detection system comprises an outer tube, and inner tube, and a set of optical fibers. The outer tube has a reflective inner surface capable of reflecting light and is configured to allow a liquid fuel to enter an interior of the outer tube on which the reflective inner surface is located. The inner tube is located within the outer tube in which an area is present between the reflective inner surface. The set of optical fibers are mounted to an outer surface of the inner tube. Each optical fiber has a core that is exposed on each part of an optical fiber opposite to the reflective inner surface and the optical fiber has a refractive index that is lower that the liquid fuel but higher than a gaseous form of any gas that may enter the area.

A joint on an aircraft, the joint comprising: a first component; a second component joined to the first component; and a bonding lead which forms an electrical connection between the components with a resistance between 100 kΩ and 10 MΩ. Surprisingly, it has been found that a bonding lead with a relatively high resistance can be used without seriously compromising the static discharge performance of the bonding lead, and that the resulting comparatively low flow of current reduces the risk of sparking in the event of an lightning strike. Bonding leads may be provided as a kit of parts in which at least two of the bonding leads have different lengths and the longer lead is formed from a material having a higher bulk conductivity than the shorter lead. Thus the bonding leads can be made with approximately similar resistances regardless of their lengths.