Your Ad Here
freepatentsonline.com: Aeronautics Home
Sitemap

freepatentsonline.com: Aeronautics


Device for facilitating the lowering of a landing gear by gravity
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 ( 1 a ) 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 ( 4 a ), and being positioned such that its axis is perpendicular to the path of the tire ( 1 a ) so that the tire will make the roller device ( 4 ) turn without sliding over it.

Bendable wing for micro air vehicle
A micro air vehicle having a bendable wing enabling the micro air vehicle to fly. The bendable wing may be bent downwards so that the wingspan may be reduced for storing the micro air vehicle. The bendable wing may be formed from one or more layers of material, and the wing may have a camber such that a concave surface of the wing faces downward. The wing may substantially resist flexing upwards and may transfer uplift forces to a central body of the micro air vehicle. In addition, the wing may be bent severely downwards by applying a force to tips of the wing. The micro air vehicle is capable of being stored in a small cylindrical tube and may be deployed from the tube by simply releasing the micro air vehicle from the tube.

Aircraft archway
An architectural archway for an aircraft. The archways can be positioned individually, or in pairs or other sets along the length of an aircraft fuselage. The archways are used to run or connect various transport elements, such as electrical wiring, water lines, and environmental control system conduits, between the upper crown, lower bay and passenger cabin of the aircraft. The invention simplifies installation complexity and eliminates the installation and variability associated with running transport elements between the various sections of the aircraft.

Control linkage for T-tail aircraft elevator surfaces
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.

Rocket-powered sensor target assembly
A rocket tube for housing a reloadable rocket motor is connected to a spacer element and a wire-rider element. A sensor target for reflecting radar signals is screwably attached to the rocket tube. The sensor target is provided with a plug for effectively sealing one end of the rocket tube with the other end of the rocket tube being utilized to reload a rocket motor upon completion of a test firing. A guide wire is threaded through the wire-rider element with the guide wire serving as a travel path. The rocket tube, spacer element, and wire-rider element are connected in an easily assembled, aerodynamic manner that allows for multiple radar tests using the same components within a brief time period.

Device for indicating a beat level
A device for indicating a beat level L, the device including an analyzer which responds to a reference frequency Ω and a harmonic coefficient B to extract from an evaluation signal E a first acceleration signal γ B at a frequency equal to the product of reference frequency Ω multiplied by harmonic coefficient B; and a second acceleration signal γ B-1 at a frequency equal to the product of reference frequency Ω multiplied by the harmonic coefficient minus one; and it further includes a control circuit CC which receives acceleration signal γ B , γ B-1 to produce beat level L.

Flow restrictors for aircraft inlet acoustic treatments, and associated systems and methods
Flow restrictors for aircraft inlet acoustic cores, and associated systems and methods are disclosed. A system in accordance with one embodiment of the invention includes an inlet flow surface having multiple openings, and an acoustic treatment positioned adjacent to the inlet flow surface. The acoustic treatment can have multiple cells in fluid communication with the openings in the inlet flow surface. A fluid collector passage can be positioned to collect liquid entering the acoustic treatment through the multiple openings, and can have an exit aperture through which the liquid drains. The fluid collector passage can include at least one flow restrictor positioned to at least restrict the flow of air from the exit aperture through the fluid collector passage to the multiple openings.

Deployable receptacle
A deployable receptacle includes a tray for supporting an object thereon and being movable between a storing position and a deploying position. The tray stores an object thereon when the tray is disposed in the storing position and deploys the object therefrom when the tray is disposed in the deploying position. A lever is coupled to the tray for moving the tray between the storing position and the deploying position.

Method of conversion of continuous medium flow energy and device for conversion of continuous medium flow energy
A device and method for conversion of the energy of medium flows are provided. The proposed device and method ensure suppression of the vortex streams in the flow on the leg of its motion along the radially converging trajectories and concentration of the flow energy, which is expressed by the increase of its velocity and decrease of the summary area of the cross section of the converging trajectories. As the flow runs along the first system of helical trajectories the following takes place: the harmful secondary vortex jets continue attenuating, the degree of concentration of the flow energy increases and velocity components form in the flow, which correspond to natural vortex streams, for instance, tornadoes, whirlpools. The formation of a vortex as the flow runs along the first system of trajectories results in a concentrated steady vortex flow with an effective concentration of the pressure differential into kinetic energy of the motion of particles and into a rotational moment, which are required for complete transfer of the energy to the rotational moment and energy receiver.

Method and apparatus for fighting a fire in an enclosed space in an aircraft
Fire that has started in an enclosed space in an aircraft is smothered by closing or at least partly closing any air flow inlet and any air flow outlet of the enclosed space in response to a temperature rise caused by a fire in the enclosed space such as a toilet or crew quarters, galley cabinets, or the like. For this purpose fireproof, intumescent material is installed next to and along any apertures or openings in the enclosed space. When the temperature in the enclosed space exceeds the expansion temperature of the fireproof intumescent material the material expands into these apertures, thereby sealing or at least partly sealing these apertures, whereby air and thus oxygen access to the fire is reduced or even prevented, thereby smothering the fire. Preferably a guide surface guides the expanding intumescent material into the apertures or openings at least when the expansion starts.