Abstract: Systems and methods are provided for an air-driven augmentor fan equipped aircraft propulsor. The augmentor fan may increase the effective bypass ratio of the aircraft propulsor and reduce fuel consumption and carbon emissions of the aircraft. The augmentor fan may be driven by air energized by a ducted fan powered by the core engine of the aircraft propulsor. The energized air may be received by an inlet, flowed through a flow path, and exhausted out the outlet to drive the augmentor fan. The exhausted energized air may impart a torque on the augmentor fan or blades of the augmentor fan. One or more of the inlet, flow path, or outlet may be variable in size to control the volume of air flowed through the flow path.

Abstract: An aircraft includes an engine mounted to a wing by a first support, such as a strut, configured to secure the engine to the wing in a position above the wing. A second support, secured to a fuselage portion of the aircraft, is defined by a bridge structure configured to separately and independently secure the engine to the fuselage. The engine is thus secured by the first support directly to the aircraft wing, and via the second support, in concert with the first, to a portion of an aircraft fuselage spaced laterally of the engine-to-wing attachment. In one embodiment the bridge structure, which extends between the engine and fuselage, may be bowed upwardly so as to define a convex curvature when viewed along the longitudinal axis of the aircraft. Such a curvature may, inter alia, optimize aerodynamic spacing of the bridge from the wing to minimize undesirable shock waves.

Abstract: The revolving overhead windmill includes airfoils that harvest wind energy using a configuration, in the class of vertical axis wind turbines, wherein the airfoils are modestly elevated above a water or ground surface through the use of buoyancy forces and elongated structural members. The airfoil angle of attack is controlled in a periodic manner as each airfoil revolves around a closed circuit of revolution, in order to optimize system energy harvest as measured by metrics such as megawatts of electric power generation under rated wind conditions. Typical large-scale applications in high wind, offshore locations can substantively contribute to utility-scale renewable energy production and also contribute towards climate change mitigation targets.

Abstract: An aircraft includes an engine mounted to a wing by a first support, such as a strut, configured to secure the engine to the wing in a position above the wing. A second support, secured to a fuselage portion of the aircraft, is defined by a bridge structure configured to separately and independently secure the engine to the fuselage. The engine is thus secured by the first support directly to the aircraft wing, and via the second support, in concert with the first, to a portion of an aircraft fuselage spaced laterally of the engine-to-wing attachment. In one embodiment the bridge structure, which extends between the engine and fuselage, may be bowed upwardly so as to define a convex curvature when viewed along the longitudinal axis of the aircraft. Such a curvature may, inter alia, optimize aerodynamic spacing of the bridge from the wing to minimize undesirable shock waves.

Abstract: Cryogenic fuels tanks for use in aircraft structures are disclosed herein. An example apparatus disclosed herein an airfoil-shaped structure disposed outboard of a fuselage of an aircraft. The example apparatus also includes a first cryogenic fuel tank disposed inside the airfoil-shaped structure.

Abstract: An aircraft includes a fuselage, having a crown section and a keel, a first passenger cabin, having a first floor, located in an aft portion the fuselage, and a first cargo deck, located below at least a portion of the first passenger cabin. A forward split level cabin including an upper second cabin having a second floor above the level of the first floor, and a lower third cabin beneath the upper second cabin and having a third floor below the level of the first floor. A second cargo deck is located in the forward portion of the fuselage and beneath at least a portion of the lower third cabin. The crown section has a substantially constant cross-sectional shape fore-to-aft above the first passenger cabin and the split level cabin.

Abstract: An aircraft configuration having a crown cabin above a main cabin, with the crown cabin having a hanging floor structure. This enables a fuselage design that substantially increases passenger seating capacity relative to traditional single-passenger-deck configurations, while minimizing fuselage perimeter and fuselage wetted area relative to double-passenger-deck configurations.

Abstract: An aircraft for carrying passengers and/or cargo has first, second and third cabins arranged in a split level floor configuration within a fuselage. The cabin floors are connected by stairs, elevators or escalators. Two of the cabins are stacked above a reduced height lower hold which acts as an energy absorbing crush zone in the event of a crash.

Abstract: Increased utilization of solar power is highly desirable as solar power is a readily available renewable resource with power potential far exceeding total global needs; and as solar power does not contribute to pollutants associated with fossil fuel power, such as unburned hydrocarbons, NOx and carbon dioxide. The present invention provides low-cost inflatable heliostatic solar power collectors, which a range of embodiments suitable for flexible utilization in small, medium, or utility scale applications. The inflatable heliostatic power collectors use a reflective surface or membrane “sandwiched” between two inflated chambers, and attached solar power receivers which are of concentrating photovoltaic and optionally also concentrating solar thermal types. Floating embodiments are described for certain beneficial applications on. Modest concentration ratios enable benefits in both reduced cost and increased conversion efficiency, relative to simple prior-art flat plate solar collectors.

Abstract: The invention provides a revolving overhead windmill which includes airfoil means for interfacing with a fluid current comprising an air current or wind, and which includes energy harvesting means utilizing fluid current driven periodic motion of the fluid-foil means for capturing fluid-dynamic renewable energy and converting it into usable energy in a desired form such as electricity. The invention provides devices, methods and systems for harvesting renewable energy for medium-scale, large-scale and ultra-large-scale applications, to provide real and substantial benefits towards efficiently fulfilling energy needs while also more broadly serving humanity and our global environment. The various embodiments of the invention provide energy with zero consumption of fossil fuels and zero emissions of greenhouse gases.

Abstract: An internal wall in an aircraft cabin separates a lavatory and a galley of the aircraft. The internal wall has an intermediate notch that increases a lateral width dimension of the lavatory above the notch and thereby improves the spatial environment of the lavatory.

Abstract: An aircraft includes an engine mounted to a wing by a first support, such as a strut, configured to secure the engine to the wing in a position above the wing. A second support, secured to a fuselage portion of the aircraft, is defined by a bridge structure configured to separately and independently secure the engine to the fuselage. The engine is thus secured by the first support directly to the aircraft wing, and via the second support, in concert with the first, to a portion of an aircraft fuselage spaced laterally of the engine-to-wing attachment. In one embodiment the bridge structure, which extends between the engine and fuselage, may be bowed upwardly so as to define a convex curvature when viewed along the longitudinal axis of the aircraft. Such a curvature may, inter alia, optimize aerodynamic spacing of the bridge from the wing to minimize undesirable shock waves.

Abstract: Wing load alleviation methods and apparatus are disclosed. An example winglet system for an aircraft includes a first winglet including a body portion having a leading edge and a trailing edge, a base portion to be coupled to an outboard end of a wing such that the body portion projects at an upward angle from the wing during all modes of airplane operation, a control surface coupled to the body portion proximate to the trailing edge, and at least one of a spoiler and an aileron coupled to the outboard end of the wing; and a processor to, in response to at least one input signal indicative of one of a subset of flight conditions, command actuated deflections of both the control surface of the first winglet and the at least one of the spoiler and the aileron to create an incremental pressure field in an airflow region inboard of the first winglet.

Abstract: An aircraft capable of carrying passengers and cargo includes a fuselage, having a crown section and a keel, a first passenger cabin, having a first floor, located in a forward portion the fuselage, and a first cargo deck, located below at least a portion of the first passenger cabin. A split level cabin is located in an aft portion of the fuselage, the split level cabin including an upper second cabin having a second floor above the level of the first floor, and a lower third cabin beneath the upper second cabin and having a third floor below the level of the first floor. A second cargo deck is located in the aft portion of the fuselage and beneath at least a portion of the lower third cabin. The crown section has a substantially constant cross-sectional shape fore-to-aft above the first passenger cabin and the split level cabin, and the keel below the second cargo deck is lowered compared to the keel below the first cargo deck.

Abstract: Cryogenic fuels tanks for use in aircraft structures are disclosed herein. An example apparatus disclosed herein an airfoil-shaped structure disposed outboard of a fuselage of an aircraft. The example apparatus also includes a first cryogenic fuel tank disposed inside the airfoil-shaped structure.

Abstract: An internal wall in an aircraft cabin separates a lavatory and a galley of the aircraft. The internal wall has an intermediate notch that increases a lateral width dimension of the lavatory above the notch and thereby improves the spatial environment of the lavatory.

Abstract: A hybrid fuel airplane and methods are presented. A cryogenic fuel is transferred to an airplane propulsor from an airplane fuel system comprising a cryogenic fuel tank and a jet fuel tank. The cryogenic fuel tank conforms to an outer mold line and carries a cryogenic fuel, and is located in a portion of the airplane body while not extending beyond the outer mold line. The jet fuel tank carries a jet fuel and is located in an airplane wing, or an airplane body, or both. A dynamic aircraft load is born on the cryogenic fuel tank, and the airplane propulsor is operated using the cryogenic fuel to generate thrust for the hybrid fuel airplane. An aerodynamic lift is generated using the airplane wing coupled to the airplane body.

Abstract: A method and apparatus comprising a plurality of seating systems and a frame for use in a passenger aircraft. A first seating system in the plurality of seating systems may have different dimensions from a second seating system in the plurality of seating systems. A frame may be configured to be connected to the plurality of seating systems.

Abstract: A method and apparatus comprising a plurality of seating systems and a frame for use in a passenger aircraft. A first seating system in the plurality of seating systems may have different dimensions from a second seating system in the plurality of seating systems. A frame may be configured to be connected to the plurality of seating systems.

Abstract: An aircraft cargo compartment container crane system including an aircraft having an upper passenger compartment and at least one lower cargo compartment, wherein the passenger compartment and the cargo compartment are separated by a floor and a crane assembly connected to a structural element of the cargo compartment beneath the floor, wherein the crane assembly is configured to lift and move a cargo container within the cargo compartment along a longitudinal axis of the aircraft.