Entries |
Document | Title | Date |
20080203235 | Apparatus for measuring a turbine blade - An erosion gauge for measuring a chord length of an eroded turbine blade in a steam turbine that may include: a jaw that includes a lower jaw that includes a lower jaw surface and an upper jaw that includes an upper jaw surface such that the lower jaw surface and the upper jaw surface oppose each other; a sliding scale that connects the lower jaw to the upper jaw, wherein a first end of the sliding scale is fixed to the lower jaw and a second end of the sliding scale slides through the upper jaw such that the distance between the lower jaw surface and the upper jaw surface may be varied; and an electronic depth gauge that determines the distance between the lower jaw surface and the upper jaw surface. The lower jaw surface may include a valley insert. | 08-28-2008 |
20080203236 | CMC airfoil with thin trailing edge - An airfoil ( | 08-28-2008 |
20080283674 | Low-drag swept wings - The invention relates to an aircraft, and a method for operating an aircraft, the aircraft having a longitudinally unstable configuration and swept wings, the swept wings being based on aerofoils having a leading edge and configured for preventing attachment line transition in conditions of laminar flow over the swept wing for at least a predetermined first range of lift coefficients at a second range of Reynolds numbers. The invention also relates to an aerofoil, and to a method for providing an aerofoil, the airfoil being configured for a thick-sectioned subsonic/transonic swept wing, having a curved leading edge, a trailing edge, a thickness dimension and a chord dimension, wherein the leading edge comprises a leading edge curvature associated with a leading edge radius that is configured for preventing attachment line transition in conditions of laminar flow over the swept wing. | 11-20-2008 |
20080283675 | RIB STRUCTURE FOR TORSION BOXES OF A WING OR HORIZONTAL STABILISER OF AN AIRCRAFT - Rib structure for a torsion box of an aircraft wing or a horizontal stabiliser. The structure comprises a center element which extends between the front spar and the rear spar of the torsion box, a series of vertical stiffening elements arranged between an upper skin and a lower skin of the torsion box. The vertical stiffening element consists of a first lateral wing which extends in the direction of said front spar and a second lateral wing which extends in the direction of said rear spar. These lateral extensions emerge from respective opposite sides of the vertical body and are attached side to side to the center element of the rib. | 11-20-2008 |
20090001225 | High lift longitudinal axis control system - A bipartite, full span airplane flap system having an inboard flap portion and an outboard flap portion, wherein the outboard flap portion includes an integrated aileron mounted on its substantially equivalent spanwise length. The outboard flap portion is adapted to translate between a first and a second position to create a functional slot between a bottom surface of the flap member leading part and a bottom surface of the airfoil trailing part to draw a portion of higher pressure air from the bottom surface of the airfoil through the functional slot to distribute the higher pressure air over a top surface of the outboard flap portion. | 01-01-2009 |
20090039207 | FLYING OBJECT - A flying object wing has a leading edge and a trailing edge and an upper and a lower surface between the edges. A portion between the leading edge and trailing edge provides an upper surface which has a curved shape. From the leading part of the upper surface towards the mid part of the surface there is a concave shape. The lower surface has a curved shape such that from the leading part of the upper surface towards the mid art of the surface there is a convex shape. A transverse aperture in the surfaces of the wing accommodates a propeller for creating thrust for forward flight. The blades of the propeller turn in a plane transverse to a line between the leading edge and the trailing edge of the surface. | 02-12-2009 |
20090039208 | Method for manufacturing a reinforced shell for forming component parts for aircraft and shell for component parts for aircraft - The invention concerns a method for manufacturing a shell, in particular a fuselage shell, a wing shell, a horizontal stabilizer shell or a vertical stabilizer shell, that is reinforced with a plurality of stiffening elements, for forming component parts for aircraft with high dimensional stability, wherein the stiffening elements and a shell skin are made with epoxy resin from at least partially cured carbon fiber reinforced semi-finished parts, the method comprising the following steps:
| 02-12-2009 |
20090057493 | NOISE-SHIELDING WING CONFIGURATION - Embodiments of the invention provide an aircraft configuration that provides for increased engine noise shielding for community noise reduction, while still providing desirable aerodynamic attributes such as good spanwise lift distributions and good structural integration without excessive wing surface area. Specifically, the aircraft is configured to have a longer-chord inboard wing portion and a shorter-chord outboard wing portion. The aircraft engines are positioned in major part over the longer-chord inboard wing portions such that communities below the wing are at least partially shielded by the inboard wing portion from the engine noise. Embodiments of the invention also strategically position fowler flaps or other chord-increasing devices in the region of the wing proximate the engine. Since the fowler motion increases the effective chord of the wing as the flaps are extended, the flaps may be deployed to increase the shielding characteristics of the wing. | 03-05-2009 |
20090065651 | SAIL WING WITH HIGH SPAN EFFICIENCY AND CONTROLLED PITCHING MOMENT - An aircraft comprising a fuselage, a sail wing appended to the fuselage, the sail wing having a sail wing root chord length, and wherein the sail wing includes a sail wing leading edge spar, a sail wing membrane attached to the sail wing leading edge spar, and a sail wing trailing edge wire located at a trailing edge of the sail wing membrane, the aircraft further comprising a wing surface extension, located aft and at an inboard area of the sail wing trailing edge wire, the wing surface extension having a wing surface extension root chord length, and wherein the wing surface extension includes a wing surface extension membrane attached to the sail wing trailing edge wire, and a wing surface extension trailing edge, and wherein the wing surface extension trailing edge is reflexed such that the wing surface extension trailing edge is positioned upwards at a first angle with respect to a plane formed along a centerline of the aircraft and along the lower surfaces of the sail wing. The wing surface extension is further configured to affect a reduced nose-up pitching moment, and to produce a more even coefficient of lift along the wing of the aircraft. | 03-12-2009 |
20090127405 | Aircraft Wing For Over-the-Wing Mounting Of Engine Nacelle - An aircraft wing has an inboard section and an outboard section. The inboard section is attached (i) on one side thereof to the aircraft's fuselage, and (ii) on an opposing side thereof to an inboard side of a turbofan engine nacelle in an over-the-wing mounting position. The outboard section's leading edge has a sweep of at least 20 degrees. The inboard section's leading edge has a sweep between −15 and +15 degrees, and extends from the fuselage to an attachment position on the nacelle that is forward of an index position defined as an imaginary intersection between the sweep of the outboard section's leading edge and the inboard side of the nacelle. In an alternate embodiment, the turbofan engine nacelle is replaced with an open rotor engine nacelle. | 05-21-2009 |
20090173838 | Narrow Wing System for Airplanes - An extra narrow wing system for airplanes combining the advantages of sufficient lift like a conventional airplane wing with reduced space requirements. A V-shaped nudge at the back side of the main wing helps to overcome the limitations of extreme delta-wings and allows very narrow wings with angles of as low as 0 degrees but sufficient lift for a propeller or jet operated plane. Front and tail wings are one aerodynamic system. The system results in very narrow airplane designs useful when operating under space constraints. | 07-09-2009 |
20090184208 | AERODYNAMIC SEALING MEMBER FOR AIRCRAFT - A sealing member for forming a seal in an aircraft, the sealing member comprising: a sealing material; and a stiffening element which provides structural support to the sealing material and comprises a material with a glass transition temperature below +50° C. The stiffening element is relatively flexible when the aircraft is at low altitude (high temperature) but becomes relatively stiff (increasing resistance to seal flutter) when the aircraft is at cruise altitude (low temperature). | 07-23-2009 |
20090308984 | TOWABLE AIRFOIL SYSTEM - A towable lift system and components and accessories therefore, particularly for use in sports and recreational activities coupling the airfoil to a rider. | 12-17-2009 |
20100123047 | Blended Wing Body Unmanned Aerial Vehicle - A Blended Wing Body SUAV and MUAV is disclosed having a novel airfoil profile, wing configuration, rigging and tractor pull propeller placement that provide improved stability and safety characteristics over prior art SUAVs and MUAVs of comparable size and weight. This unique blended wing design includes wing twist on the outboard wing and an inverted “W” shaped planform to provide lateral and longitudinal stability, and smooth, even flight characteristics throughout the range of the expected flight envelope. These flight characteristics are crucial to providing a stable reconnaissance platform with favorable stall speeds, an increased payload and the ability to hand launch without the danger of exposing ones hands or wrist to a propeller. | 05-20-2010 |
20100140417 | Modification of a NASA 4412 airfoil's upper surface produces increased lift - A measurable increase in lift has been discovered by modifying the top surface of a NASA 4412 airfoil. This modification has been demonstrated in a straight wing of a typical plane and a similar circular wing as used in U.S. Pat. No. 5,046,685. the listed ordinates have not been optimized for any particular air speed. These results will benefit ultra-lites, gliders, helicopters or any slow flying aircraft. | 06-10-2010 |
20100308180 | METHOD AND SYSTEM FOR LOADING AND UNLOADING CARGO ASSEMBLY ONTO AND FROM AN AIRCRAFT - A system for loading and unloading a cargo assembly onto and from an aircraft. The system comprises an aircraft and a movable platform. The aircraft comprises a forward fairing, an aft fairing, a spine disposed between the forward fairing and the aft fairing and a plurality of mounts coupled to the spine and configured to structurally engage the cargo container onto the spine. The aft fairing is movable between a fixed position for flight and an open position for at least loading and unloading of the cargo assembly. The aircraft is configured such that an unobstructed passageway is provided in an area underneath the spine during loading or unloading of the cargo assembly. An aft access is provided when the aft fairing is moved to the open position. The movable platform is used to maneuver the cargo assembly for loading and unloading onto and from the spine, respectively. | 12-09-2010 |
20110001018 | COMPOSITE MATERIAL FOR GEOMETRIC MORPHING WING - An airfoil member and an airfoil member altering system are provided for significantly modifying the shape and size of the airfoil member while simultaneously providing an airfoil member with increased adaptability to various flight conditions throughout a flight envelope. The airfoil member comprises at least one motor or actuator, a system controller, a plurality of vehicle performance sensors, at least one temperature controller and airfoil member comprising at least one geometric morphing device that is adjustable in both size and shape and one or more rigid members. | 01-06-2011 |
20110095137 | Laminar flow wing optimized for supersonic cruise aircraft - A method of providing an aircraft having a fuselage and a wing configured for extensive laminar flow at design cruise conditions, the method characterized by a) providing wing biconvex-type airfoils having values of thickness, chord and shape along the wing span which provide substantially optimal aircraft range at design cruise conditions, considering the influences of wing drag and wing weight; b) providing wing leading edges, which are configured to effect laminar flow; c) providing fuselage and wing contours which, in combination, produce reduced total wave drag and produce extensive areas of laminar boundary layer flow on the wing; and d) providing wing sweep angularity that facilitates provision of a), b) and c). | 04-28-2011 |
20110180672 | Airplane with aerodynamic stall-prevention layout and pertinent longitudinal stability arrangement - General purpose airplane with a swept back wing provided with a sharp leading edge as to cause flow separation and stall of the wing in cases where the limits of the regular flight envelope are exceeded in terms of angle of attack, and as a result to cause the front part of the airplane to move downward, said airplane also having positive lift-producing horizontal stabilizer provided with rounded leading edge, which does not stall at this point, therefore holds the tail in level during the process, all together acting to restore the original flight attitude. The horizontal stabilizer is essentially a straight (or similar) wing with a steeper lift-coefficient curve as that of the swept-back wing, therefore, in case of an un-commanded pitch-up of the airplane the greater increase of lift on the horizontal stabilizer together with its greater moment arm provides the stabilizing force to counter such pitching. | 07-28-2011 |
20120018589 | Method For Carrying Out An Aircraft And Aircraft So Obtained - A method to produce an aircraft ( | 01-26-2012 |
20120043429 | Laminar flow wing optimized for transonic cruise aircraft - Aircraft configured to operate at Mach numbers from above 0.80 and up to 1.2 with wing sweep angles defined by the wing outboard leading edge of less than 35 degrees, and incorporating calculated values of the ratio of outboard wing panel aspect ratio raised to an exponent of 0.78, divided by the ratio of maximum thickness divided by chord (t/c), greater than about 45, characterized by one of the following: a) where maximum thickness divided by chord (t/c) is at a location approximately 70% of the distance outboard from the attaching aircraft body to the wing tip, or b) where maximum thickness divided by chord (t/c) is the average value of (t/c)'s located between approximately 50% of the distance outboard from the attaching aircraft body to the wing tip. | 02-23-2012 |
20120043430 | Laminar flow wing optimized for transonic cruise aircraft - On an aircraft designed for maximum efficient cruise speed in the range from about Mach 0.8 to about Mach 1.2, and having fuselage and wings with: (a) less than about 25 degrees of leading edge sweep, in combination with airfoil thickness to chord ratios between about 3% and about 8%, as an average along the wing semi-span outboard from the zone of substantial fuselage influence, and (b) wing leading edge sweep between about 20 degrees and about 35 degrees, in combination with airfoil thickness to chord ratios equal to or below about 3% as an average along the semi-span outboard from the zone of substantial fuselage influence to the wing tip. | 02-23-2012 |
20120211607 | COMPOSITE STRUCTURE - A composite structure has first and second sections, and a curved corner joining the first and second sections. The structure includes a stack of fibre-reinforced plies. First and second external plies run from the first section into the second section round an inside and an outside of the corner, respectively. First and second internal plies are sandwiched between the first and second external plies, and run from the first section into the second section round the corner. The first internal fly is dropped off inside the second section. The second internal ply is dropped off inside the first section. The structure has an increased thickness where the first and second internal plies overlap. | 08-23-2012 |
20120248258 | Flight Path Control System For Aircraft - A method and apparatus for changing a flight path of an air platform. A change for the flight path of the air platform is identified. A weight system associated with the air platform is moved during flight of the air platform such that a center of mass of the air platform changes in a manner that causes the flight path of the air platform to change. | 10-04-2012 |
20130277504 | FIXED WING OF AN AIRCRAFT - A fixed wing of an aircraft, having a main wing extending over a half-span with a wing box including spars extending along the spanwise direction of the main wing, ribs arranged one in back of the other viewed in the spanwise direction, and an outer skin. The wing box includes a wing box base section (K | 10-24-2013 |
20140021304 | PROFILE PLATE PORTION FOR USE AS AN OUTER WALL OF A FLOW BODY, METHOD FOR MANUFACTURING A PROFILE PLATE PORTION AND FLOW BODY COMPONENT COMPRISING A SUCTION-EXTRACTION DEVICE FOR FLUID - A profile plate portion is disclosed for use as an outer wall of a flow body including a first profile plate panel that is fluid permeable, a second profile plate panel extending along the first profile plate panel, and a reinforcing device for supporting the first profile plate panel and the second profile plate panel on one another. Fluid can flow through the reinforcing device, and/or fluid of the flow present at the first profile plate panel, which flows through the first profile plate panel, can flow through the reinforcing device in the local profile plate thickness direction from the first profile plate panel to the second profile plate panel and in some regions can flow through to an inside that is situated opposite the flow side. A method is disclosed for manufacturing a profile plate portion and a flow body component with a suction-extraction device for fluid. | 01-23-2014 |
20140197280 | Delta Wing Unmanned Aerial Vehicle (UAV) and Method of Manufacture of the Same - This disclosure pertains to the field of small-unmanned aerial vehicles (UAVs). The delta wing vehicle consists of an isosceles triangular shaped lifting body milled from Styrofoam. The longitudinal axis is approximately 65% of the lateral axis. The horizontal wing projections, or tiplets, are attached to the main lifting body at an approximately 10 degree upward angle from horizontal, have a 30 degree sweep back leading edge, and each one comprises 5% of the total wing area. The airfoil is a rhomboid or diamond shape. The chord is swept back at a 45-degree angle from the longitudinal centerline. The airfoil is symmetrical about the longitudinal center. The aircraft is controlled by a set of combined elevator/aileron surfaces (elevons) at the rear as well as a vertical stabilizer/rudder combination. This resulting lightweight UAV can make flat (unbanked) unbanked turns, fly in high winds, and has superior flexibility in payload capability. | 07-17-2014 |
20140339370 | TRAILING EDGE OF AN AIRCRAFT AERODYNAMIC SURFACE - The invention discloses a trailing edge ( | 11-20-2014 |
20160068254 | AIRCRAFT - An aircraft comprising a fuselage; a main wing provided on a fuselage lower side and including a center wing and an outer wing; and a fairing covering at least a lower surface of the center wing, and a seal interposed between an end edge in a right-left direction of the fairing and an outer wing lower surface. In the aircraft, a most outboard fitting located on a most outboard side out of fittings respectively provided at a plurality of positions in the right-left direction of the fairing, and an outer wing fitting provided on the outer wing are pin-coupled via a pin or pins extending along a front-rear direction. The outer wing fitting is coupled to the outer wing at a position on an inboard side with respect to the end edge and other than a position of a joining structure for joining the center wing and the outer wing. | 03-10-2016 |
20160114897 | Airplane Suspension Cowling Structure With Wing-Mounted Arrangement - Provided is an airplane suspension ( | 04-28-2016 |
20160144968 | METHOD OF FLYING AN AIRCRAFT - Provided is a fuel-efficient method of flying an aircraft for flying an aircraft. The present invention relates to a method of flying an aircraft | 05-26-2016 |
20160185439 | AIRCRAFT REAR STRUCTURE - An aircraft rear structure that comprises a rear pressure bulkhead, and a lifting surface located at both sides of the fuselage of the aircraft. The lifting surface comprises spars extending in the longitudinal direction of the lifting surface. The pressure bulkhead is aligned with one of the spars of the lifting surface. | 06-30-2016 |