Abstract: A method and apparatus are disclosed for treating fuel to temporarily reduce its combustibility, and thereafter restore its combustibility. As used in an aircraft, the method comprises the following steps: (a) treating aircraft engine fuel to substantially reduce its combustibility in open air; (b) carrying the treated fuel in a fuel tank of an aircraft; (c) increasing the combustibility of a portion of the treated fuel, as needed by the aircraft engine; and (d) supplying the increased restored combustibility fuel to the aircraft engine. Using this method, the preponderance of the fuel on board the aircraft is maintained at low combustibility for safety.

Abstract: A nut system including a nut including a main thread with pitch p1 and arranged along a screwing axis of the nut. A threaded device is coupled in rotation with the nut, the threaded device including a secondary non-screwed thread on the main thread from which it is separated, the secondary thread being arranged along the screwing axis and having a pitch p2 different from p1. Such a nut system may find application with a device for resistance of thrusts generated by an aircraft engine.

Abstract: A flight control system for an airfoil comprises a control surface, a chamber connecting the control surface to the airfoil, and a pneumatic mechanism fluidly connected to the chamber. The chamber may be comprised of at least two cells that may be fluidly separated by a membrane. The pneumatic mechanism is configured to provide differential pressure to the cells in order to alternately increase volume/pressure of the cells to cause deflection of the control surface. The cells may have a stretchable outer surface to allow for changes in the length of the outer surface in response to inflation/deflation of the cells. The outer surface of the cells may be substantially continuous with outer mold lines of the airfoil and of the control surface.

Abstract: Modular configuration for an aircraft interior floor plan design is provided by an fuselage having starboard and port side attachment rails disposed longitudinally parallel to one another. Each of the starboard and port side attachment rails are comprised of outboard and inboard rails and a center rail positioned therebetween. A plurality of interior fixtures are provided with fixed attachment posts asymmetrically oriented relative to a longitudinal centerline plane of the fixture. Such fixtures can therefore be attached to predetermined pairs of the starboard and port side attachment rails to provide for a desired configuration of the fixtures within the fuselage.

Abstract: A method and apparatus for aiding pilots in aerial refueling comprises a primary auto-throttling system (ATS) disposed in a primary aircraft and a secondary ATS disposed in a secondary aircraft. The primary ATS includes logic which generates and transmits an anticipatory signal to the secondary ATS. Based upon the received anticipatory signal, the secondary ATS automatically controls a throttle of the secondary aircraft so as to maintain an airspeed of the primary aircraft. The anticipatory signals include rate of change information including at least one of rate of change of airspeed of the primary aircraft, rate of change of pitch of the primary aircraft, and rate of change of weight of the primary aircraft.

Abstract: A micro aerial vehicle includes: a fuselage; a flapping transmission mechanism mounted on a front portion of the fuselage; a flexible wing frame secured to and driven by the flapping transmission mechanism for producing a figure-eight flapping trajectory for mimicking the flight of a tiny natural flier, such as hummingbird; and a tail wing secured to a tail portion of the fuselage; wherein the flexible wing frame is formed by respectively pivotally or rotatably mounting a wing skin made of parylene foil to a pair of leading-edge arm members made of carbon fiber, and linked to the flapping transmission mechanism to thereby make a miniaturized micro aerial vehicle.

Abstract: Disclosed is an aircraft, configured to have a wide range of flight speeds, consuming low levels of power for an extended period of time, while supporting a communications platform with an unobstructed downward-looking view. The aircraft includes an extendable slat at the leading edge of the wing, and a reflexed trailing edge. The aircraft comprises a flying wing extending laterally between two ends and a center point. The wing is swept and has a relatively constant chord. The aircraft also includes a power module configured to provide power via a fuel cell. The fuel cell stores liquid hydrogen as fuel, but uses gaseous hydrogen in the fuel cell. A fuel tank heater is used to control the boil-rate of the fuel in the fuel tank. The fuel cell compresses ambient air for an oxidizer, and operates with the fuel and oxidizer at pressures below one atmosphere. The aircraft of the invention includes a support structure including a plurality of supports, where the supports form a tetrahedron that affixes to the wing.

Abstract: A liquid bird feeder provides a liquid container having a bottom opening, a liquid tray adapted to attach to the liquid container and adapted to immerse the bottom opening in liquid. The liquid tray includes a bottom port passing through the liquid tray and vertically aligned with the bottom opening, and a valve mechanism adapted to selectively couple the bottom port of the liquid tray to the bottom opening for filling purposes, or to close the bottom port and couple the bottom opening to the liquid tray for supplying liquid from the liquid container to the liquid tray.

Abstract: The present invention provides an airframe structure of an aircraft or spacecraft, with: a hollow body section which can be subjected to an internal pressure; a membrane arrangement which has at least one single-part, multi-curved membrane component for sealing off the internal pressure from an external pressure which acts on the hollow body section and differs from the internal pressure; and a joining structure for a pressure tight joining of the membrane arrangement to a region of the hollow body section; wherein the membrane arrangement forms a receiving well which is accessible from outside the hollow body section, extends at least partially into the hollow body section and is for receiving a component of the aircraft or spacecraft.

Abstract: A fuselage has laterally extending wing-like structures. The wing-like structures have an aperture. A can is positioned in the aperture. The can has an axle. The axle rotatably couples the can to the aperture. The can has an upper cylindrical section and a lower rectilinear section. A multi-blade rotor is rotatably mounted in the upper section. A battery of airfoils is pivotally mounted in the lower section.

Abstract: The present invention comprises, in one embodiment, an inexpensive, lightweight flying vehicle using fixed pitch helicopter blades powered by ramjet engines mounted to a power-ring which transfers torque to the lifting rotors. The use of fixed pitch blades eliminates the need for a tail boom and tail rotor, as well as for variable incidence control of blade pitch and/or cyclic and collective rotor-pitch controls. An optional ballistic parachute may be deployed for emergency landings. A radial shroud encloses the ramjet engines to act as a sound shield. Since the rotor has a fixed pitch, lift may be controlled by rotor speed, where increased speed results in ascent, and decreased speed, descent.

Abstract: A housing system related to the protective housing of a fishing rod and reel, particularly, a fly-fishing rod and reel, during transport. The system comprises a two-part housing adapted to separately compartmentalize the fishing rod and attached fishing reel. A specialized access slot allows easy installation into, and removal from, the housing. The specialized access slot also functions to fixably suspend the fishing reel in the housing interior, thus providing improved protection against damage during transport. A method of manufacture and sale is also disclosed.

Abstract: A linear cavity is provided on the leading edge of an object that is subject to the flow of liquids or gasses, where said cavity preferably has a wall that follows the curvature of a diminishing sine wave, although other configurations are possible that do not follow a specific sine wave. The cavity accepts the flow of liquids or gasses that enter into the cavity, and where the dimensions of the cavity cause the flow of liquids or gases within it to form a pressure node that extends forward of the cavity. The pressure node provides a wedge means to cause oncoming gasses or liquids to divert around the object body ahead of the object body itself, decreasing turbulence around the periphery of the object. The cavity may be spherical, in the instance of a missile, plane, or underwater transportation means, or may be linear, in the instance of an automobile grill that is subject to wind, or a bridge support, where the bridge support has to maintain position against the flow of current.

Abstract: Device for facilitating the lowering of a landing gear by gravity, comprising at least on roller device (4) positioned on at least one closing panel (2) of the hatch for the landing gear in a contact area with the tire (1a) of the landing gear of an aircraft (7) on initiating its descent, the roller device (4) comprising a rigid roller device which can rotate freely about its axis (4a), and being positioned such that its axis is perpendicular to the path of the tire (1a) so that the tire will make the roller device (4) turn without sliding over it.

Abstract: Systems and methods for implementing control linkages that may be employed to produce synchronous motion in two adjacent controlled devices controlled by a common input. In one example implementation, a semi-rigid modified constant velocity (CV) joint control linkage may be provided that is laterally self-stabilizing. The modified constant velocity CV joint control linkage may include an input push rod assembly that is self-aligning, deflectable and of an adjustable length. The CV joint may be configured with a central cage that is allowed to skew to allow for alignment of the controlled devices.

Abstract: A surveillance aircraft recharging system based on energy collection by magnetic induction from the current flowing in a randomly selected alternating current transmission line conductor. The charging energy originates in the magnetic field surrounding the current carrying conductor and is obtained by way of a laminated magnetic circuit surrounding the current carrying conductor and disposable in both an open and transmission line receiving state and a closed and energy collecting state upon command. Latching of the magnetic structure into a condition providing physical suspension stability for the host aircraft as well as an efficient magnetic circuit are provided. Latching of the magnetic structure includes a docking aircraft kinetic energy storage sequence assisting in aircraft deceleration and also providing saved energy useful during an undocking sequence.

Abstract: A fishing lure having a rattling assembly for attracting fish, wherein the sound of the rattling assembly is adjustable. The rattling assembly includes a rattle member and a rod member positioned inside a cavity defined in the body of the fishing lure. The rod member traverses the exterior surface of the fishing lure into the cavity, such that the position of the rod member will determine the ability of the rattling member to travel within the cavity to strike the walls of the cavity.

Abstract: An assembly device for cleaning an animal's paw and assembly methods thereof are disclosed including a container adapted to retain a cleaning agent, the container defining an opening and including a side wall, a cleaning platform disposed in said container and defining a space between said cleaning platform and said container side wall, and a squeegee member substantially covering said opening.

Abstract: A self-cleaning pet litter box has a conveyor to incrementally transport clumped litter material and solid pet waste to a waste receptacle. The conveyor has one end configured to extend into a pet litter container of the self-cleaning litter box and an opposite exit end. The conveyor is configured for reciprocating movement to lift the clumped litter material and solid pet waste from below, transport it some distance along the conveyor, place the material down again, return to its original position, and repeat the motion again to incrementally move the material along the conveyor toward the exit end for subsequent disposal.

Abstract: Separate upper and lower plenums within an aircraft airfoil or a sea hydrofoil conduct fluid under different pressures to nozzle slots from which jets emerge to augment lift in accordance with different travel conditions. Lift is induced by nozzle slot emergence of a primary jet from one of the plenums along a reverse flow path relative to secondary jet outflow from the other plenum. This capability involves angularly adjusted deflection of the primary jet outflow along forward, reverse or vertical directional flow paths from the trailing end of the airfoil or hydrofoil under zero and other different speed conditions by emergence of the secondary wall jet.