Aeronautics inventions 10/06

20060237580 - Canard position and dihedral for boom reduction and pitch/directional control: A supersonic aircraft comprises a fuselage extending forward and aft, wings coupled to lateral sides of the fuselage, and canards coupled to lateral sides of the fuselage forward of the wings. The individual canards are configured to generate shocks that wrap around the fuselage and intersect with wing leading edges...

20060237581 - Retractable lifting blades for aircraft: A rotor blade assembly for providing vertical lift to an aircraft, having a rotor head and a plurality of blades, with each blade attached to a mechanism such as a cam surface, whereby movement of the mechanism causes the radial distance between the distal tip of the attached blade and...

20060237582 - Aircraft engine nacelle inlet having access opening for electrical ice protection system: An aircraft engine nacelle inlet is provided with an inlet cowling. The inlet cowling includes an inner lip, an outer lip, and a leading edge portion connecting the inner and outer lips. Heating elements are provided proximate the leading edge, either on an inside surface of the cowling or on...

20060237583 - Combined fuel cell aircraft auxiliary power unit and environmental control system: Combined aircraft hybrid fuel cell auxiliary power unit and environmental control system and methods are disclosed. In one embodiment, an auxiliary power unit includes a fuel cell component which chemically converts combustible fuel into electrical energy. Unutizlied fuel emitted by the fuel cell component is combusted by a burner to...

20060237584 - Dual brace-determinate landing gear: Disclosed is an arrangement in which the main landing gear assemblies of a large commercial airplane are each joined to the airplane at four attachment points. Two of the attachment points connect the landing gear side brace and drag brace to the airplane. The two remaining attachment points are aft...

20060237585 - Airplane interior systems: Interior architectural structures and lighting for aircraft, particularly commercial passenger airplanes. Light diffusers and ceiling panels in a “wing-shape” and other secondary panels are utilized to create different interior designs and structures. A permeable secondary panel is utilized in one passenger cabin in order to provide a more private-type space....

20060237586 - Adjustable attenuation system for a space re-entry vehicle seat: An adjustable attenuation system 10 for a space re-entry vehicle seat having a frame 12 that supports at least one seat 14 mounted to and supported on the frame 12 at the seat back. A plurality of struts 16 is attached to the frame 12 in predetermined locations 18. The...

20060237588 - Composite structural member having an undulating web and method for forming the same: Composite structural members and methods for forming the same are disclosed. In one embodiment, a composite structural member includes a central structural portion that extends in a first direction and having a first flange portion and a second flange portion that are spaced apart in a second direction perpendicular to...

20060237587 - Integral frame member for an aircraft: According to an exemplary embodiment of the present invention, a frame member for an aircraft is provided comprising a clip region and a frame region. According to an aspect of this exemplary embodiment of the present invention, the clip region, shear web region and the frame region are integrated into...

20060237589 - Aircraft wet wing: An aircraft wing (12) comprising a structural casing (14) defining a leading edge, a fuel cell (16) within the structural casing (14), a deicer (18) having electrical lines which receive a supply of electrical power from an onboard power source, and a trip line (20). The trip line (20) is...

20060237590 - Aircraft engine nacelle inlet having electrical ice protection system: An aircraft engine nacelle inlet is provided with an inlet cowling. The inlet cowling includes an inner lip, an outer lip, and a leading edge portion connecting the inner and outer lips. Heating elements are provided proximate the leading edge, either on an inside surface of the cowling or on...

20060237591 - Operational ground support system having automated fueling: An aircraft fueling system (890) includes an underground fuel supply (904). A fuel pump (906) is coupled to the underground fuel supply 904 and is used to supply fuel to an aircraft (902). A fuel probe (908) is coupled to the fuel pump (906) and is extendible to an aircraft...

20060237592 - Sonobuoy loading method: Disclosed is a system for loading and deploying equipment from a flying aircraft. The system comprises a container containing the equipment, the container having a first end, a second end below the first end and a piston which prior to deployment, is located towards the first end of the container;...

20060237593 - Detachable line management device for traction kites: A device for managing lines of a kite has a means for securing the device to a control bar of a kite and a line attachment portion of the device, the line attachment portion having a plurality of means for detachably retaining lines of a kite. The means for securing...

20060237594 - Aircraft multi-axis modal suppression system: Vibrations due to excitation of the natural modes of an aircraft's body are suppressed by an active multi-axis modal suppression system. Dedicated sensors are positioned in the aircraft at optimal locations for sensing modal induced vibrations. The sensor produced signals are processed through control logic which, in response thereto, and...

20060237595 - Wing for an aircraft or spacecraft: The invention relates to a wing, a wing, a tail unit or grid fins for a flying object moving with supersonic speeds. The wing comprises leading edges and tailing edges. According to the invention, the contour of at least one of the leading contour and the tailing contour has a...

20060237596 - Wing, particularly airfoil of an aircraft, having changeable profile: A wing, particularly an airfoil of an aircraft, having a changeable profile, which extends in the wing depth direction (5) running essentially in the flow direction and transversely thereto in the wing span direction and has a first planking (55a) and a second planking (55b), and having a flexible area...

20060231675 - Gyro-stabilized air vehicle: A vertical takeoff and landing (VTOL) air vehicle disclosed. The air vehicle can be manned or unmanned. In one embodiment, the air vehicle includes two shrouded propellers, a fuselage and a gyroscopic stabilization disk installed in the fuselage. The gyroscopic stabilization disk can be configured to provide sufficient angular momentum,...

20060231676 - Vertical take-off aircraft - e: A vertical take-off aircraft is disclosed. Looking at the aircraft it can be seen that the aircraft comprises a main rotor assembly 1 at the top of the aircraft which consists of an assembly of blades 2, 3 and a rotor 4. Rotation of the main rotor assembly 1 is...

20060231677 - Rotary-wing vehicle system and methods patent: A rotary-wing apparatus that is aeronautically stable, easy to fly with a multidimensional control, small size, and safe to fly and low cost to produce. The rotary-wing apparatus includes a coaxial counter rotating rotor drive providing lifting power with an inherent aeronautical stability; Auxiliary propellers that face the direction of...

20060231678 - High speed airship: A high speed airship (10) with multiple inflatable chambers (11) arranged in a multiplicity of tubular clusters to enhance structural strength and to create a centrally located passenger or cargo tunnel (18) to increase passenger safety. A conical shaped rigid frame front cabin (14) attached to the front end of...

20060231679 - Gas turbine engine mounting arrangement: A gas turbine engine mounting arrangement for attaching a gas turbine engine to a support structure, such as a pylon of an aircraft, comprises a main mounting member adapted to interconnect the engine with the pylon and transmit loads therebetween under normal engine operating conditions, and an auxiliary mounting member...

20060231680 - Integrated power and pressurization system: An integrated power and pressurization management system supplies electrical power and cabin pressurization and cooling air during both airborne and ground operations. The system includes an integral auxiliary power unit (APU) that has a compressor, a motor-generator, and a power turbine all mounted on one shaft. The integral APU can...

20060231681 - Floor for an aircraft cargo compartment and method for the assembly thereof: In conventional aircraft cargo compartments panels or similar flat floor elements are fastened to floor beams or similar supporting elements that are installed in the body of the aircraft. Subsequently functional units such as roller elements latches or PDUs are mounted and connected to one another by way of appropriate...

20060231682 - Multi-ring system for fuselage barrel formation: An aircraft fuselage barrel (10) includes a skin (12) and a shear tie (18). The shear tie (18) resides within and is integrally formed with the skin (12). The shear tie (18) is separate from and configured for frame attachment thereon. A multi-ring system (79) for fuselage barrel formation includes...

20060231683 - Aircraft & motor vehicle protection system that eliminates eleven safety and environmental hazards associated with aircraft and vehicles parked or tied down and exposed to the elements and animals: The Aircraft & motor vehicle protection system invention eliminates the safety and environmental hazards associated with the safety and environmental elements such as (1) sun, (2) heat, (3) thunderstorms, (4) hail, (5) rain & fuel contamination, (6) bird and animal nesting and droppings, (7) freezing rain, (8) frost, (9) ice,...

20060231684 - Reefing assembly for a circular parachute: A reefing assembly for a circular parachute having a canopy including a skirt portion, and suspension lines attached to the skirt portion. The assembly includes a tension structure bounding a central opening and having a plurality of straight segments. A plurality of cords, each cord having two ends, are each...

20060226280 - Stowable design for unmanned aerial vehicle: An unmanned aerial vehicle (UAV) having a design for optimum stowability and low cost. The UAV having a collapsible wing section which can be easily removed from the fuselage, allowing for quick assembly and disassembly and ease of portability. The unmanned aerial vehicle includes a primary wing assembly, a fuselage,...

20060226281 - Ducted fan vertical take-off and landing vehicle: A vertical take-off and landing vehicle comprised of a fuselage having a front, a rear, and two lateral sides and a set of four thrusters set to the front, the left, the right, and the rear of said fuselage. The thrusters are either independently powered thrusters or could utilize a...

20060226282 - Deflection system for a gas stream in a nozzle: Deflection system for a gas stream 11 in an exhaust nozzle 10 of a flying craft, comprising fixed structural housings 18,20 which extend perpendicularly to the gas stream 11 and which are fed with deflection gas through one of their ends external to the nozzle 10, these housings 18,20 containing...

20060226283 - Hybrid transonic-subsonic aerofoils: A hybrid transonic-subsonic airfoil is provided that combines subsonic and transonic features for achieving simultaneously acceptable aerodynamic characteristics at low subsonic and high transonic Mach numbers....

20060226284 - Pneumatically launched folding wing glider toy: A glider toy has pivoting wings that may be locked in a retracted position prior to launch. Upon launching of the glider, the wings may be unlocked. During flight, the wings extend forward for an entertaining glide at the urging of one or more elastic members. A launcher includes an...

20060226285 - Local backup hydraulic actuator for aircraft control systems: A backup system is provided that has a local electric motor and pump for some or all of the hydraulic actuators on an aircraft. A local backup hydraulic actuator has two power sources, hydraulic as primary and electrical as backup. During normal operation, the hydraulic actuator receives pressurized fluid from...

20060226286 - Anti-flip landing gear for aircraft: A system for controlling landing gear of an aircraft is disclosed. The apparatus includes a sensor for sensing water, wherein the sensor is coupled to the landing gear and a retracting device for retracting the landing gear when the sensor senses a body of water. In one alternative, the aircraft...

20060226288 - Floor for aircraft: The invention relates to an aircraft floor (4), preferably a cockpit floor, this floor comprising a plurality of spars (14) running along a longitudinal direction (X) of the aircraft and a plurality of cross-beams (16) assembled to the spars and running along a transverse direction (Y) of the aircraft, the...

20060226287 - Structural panels for use in aircraft fuselages and other structures: Structural panels for use in manufacturing aircraft fuselages and other structures are disclosed herein. In one embodiment, a structural panel configured in accordance with the invention includes a skin having at least one offset surface. The structural panel can further include at least first and second stiffeners. The first stiffener...

20060226289 - Method and apparatus for an adaptive suspension support system: A method and apparatus for an adaptive, multi-axis suspension support system providing both coarse and fine suspension to a payload. Coarse suspension control is provided to maintain the payload within a coarse range of position. Fine suspension control is provided by monitoring and analyzing vibration characteristics in both time and...

20060226290 - Vane assembly with metal trailing edge segment: Embodiments of the invention relate to a vane assembly formed by a forward airfoil segment and an aft airfoil segment. The aft segment is made of metal and can define the trailing edge of the vane assembly. The forward segment can be made of ceramic, CMC or metal. The forward...

20060226291 - Wing unit, in particular spar box, for forming aerodynamically active surfaces of an aircraft, in particular airfoils, horizontal tail units or rudder units of a plane: The invention relates to a wing unit, in particular a spar box for forming aerodynamically active surfaces of an aircraft, in particular airfoils, horizontal tail units, or rudder units of a plane. Aerodynamic improvements can be obtained due to a surface geometry of the aerodynamically active surfaces, which surface geometry...

20060226292 - Dual-channel deicing system for a rotary wing aircraft: A deicing system includes dual deice system components to provide a redundant deice system. Each redundant portion of the system generally includes a controller, an air data computer, an ice rate controller, and an ice rate probe. The controller communicating a heating cycle which defines a multiple of electric pulse...

20060226293 - Optical tracking system for refueling: An aerial refueling system including a refueling drogue assembly including a refueling drogue and a refueling hose in captive relation with the refueling drogue and a drogue positioning system. The drogue positioning system including a radiation emitter, a radiation receiver and a signal processor. Then the radiation emitter is adapted...

20060226294 - Kite control device: A control device for use with an aerodynamic wing including a bar having a fixed trim adjustment located between the bar and the user. The invention also includes a stopper that permits the user to quickly adjust the range of available dynamic trim. Preferably, the stopper does not lock until...

20060226295 - Lifting body tuned for passive re-entry: A high performance (high L/D ratio) launch vehicle is tuned for passive or limited control re-entry. In one embodiment, the re-entry vehicle (100) includes a fuselage portion (102) and wing portions (104 and 106) extending from opposite sides thereof. Various vehicle configuration parameters are tuned to allow for passive or...

20060226296 - Pivoted flap mechanism for adjusting an aerodynamic pivoted flap associated with a wing: A pivoted flap mechanism for adjusting an aerodynamic pivotable flap associated with a wing, including: an actuating device including a gear device; a drive device including a drive arm that rotates about an axis, and which is structured and arranged to load the actuating device; and a flap support composed...

20060226297 - Wing with extendable aerodynamic pivoted flaps: A structure with at least one flap connected to a wing, including: at least one drive device; at least one actuating device including a gear device coupled to the at least one drive device and the at least one flap; and a fairing housing swivellably mounted on the wing, at...

20060219838 - Attachment means for hang glider simulator: An attachment means for hang glider simulator generally comprises a rod, pole or similar oblong means which is articulately attached at both ends to brackets able to rotate along three axes. One such bracket being attached to a vehicle while the other bracket is attached to a seating assembly attached...

20060219839 - Guided kinetic penetrator: The disclosed system, device and method for guiding a hypersonic kinetic penetrator projectile (300) generally includes a kinetic penetrator body (110, 230) and a slip-over electronic guidance unit (120, 220), where the kinetic penetrator body slidably mounts through the slip-over electronic guidance unit. Disclosed features and specifications may be variously...

20060219840 - Constant vertical state maintaining cueing system: This invention relates to the concept of managing the rate of change of energy in a helicopter or other aeronautical vehicle. The invention uses energy management calculations to determine the maximum longitudinal and lateral inputs that can be made while still enabling the vehicle to maintain a desired vertical state....

20060219841 - Suspension for suspending a jet engine on an aircraft strut: This suspension is characterized in that the beam comprises a clevis 13 for housing the first connecting pin 31 of the central link 30, and the said first pin is distant from the platform 11 so that a space is provided between the platform 11 and the central link 30,...

20060219842 - Systems and methods for cargo compartment air conditioning using recirculated air: The present invention comprises systems and methods for providing conditioned air to a selected portion of an aircraft cabin. In one embodiment, a system includes a cargo compartment air recirculation system fluidly coupled to the cargo compartment and having an air moving device to extract air from the compartment and...

20060219843 - Furniture unit for a vehicle, especially an aircraft: e

20060219844 - Window airflow damper: A device that alters the breather hole configuration currently being employed in aircraft window assemblies. The device provides a means to allow slow moving air to pass and breathe through the breather hole, while stopping or significantly blocking non-steady air pulses from passing through. The device uses a combination of...

20060219845 - Hybrid fiberglass composite structures and methods of forming the same: Hybrid fiberglass composite structures and methods for forming the same are disclosed. In one embodiment, a hybrid fiberglass composite structure includes a first laminate substrate and a second opposing laminate substrate. At least one of the first laminate substrate and the second laminate substrate includes at least one polymer fiber...

20060219846 - Multipurpose modular spacecraft: A reentry vehicle includes a nose section, a modular section comprised of two or more connected modules, a flared section. The nose section is connected to a first end of the modular section, and the flared section is positioned proximate a second end of the modular cylindrical section....

20060219847 - Conformal aero-adaptive nozzle/aftbody: The present invention provides flow field control techniques that adapt the aft body region flow field to eliminate or mitigate the development of massive separated flow field zones and associated unsteady vortical flow field structures. Embodiments of the present invention use one or more distributed arrays of flow control devices...