Matches 1 - 50 out of 83 1 2 >


Match Document Document Title
US20120043428 HIGH-LIFT FLAP, ARRANGEMENT OF A HIGH-LIFT FLAP TOGETHER WITH A DEVICE FOR INFLUENCING THE FLOW ON THE SAME AND AIRCRAFT COMPRISING SAID ARRANGEMENT  
An aerodynamic body of an aircraft with an air outlet opening and an air intake opening that communicates with the air outlet opening via an air conduit is described. A flow delivery driver device...
US20120168559 Removable Horizontal Stabilizer for Helicopter  
An easily removable and lightweight horizontal stabilizer configured to provide aerodynamic stability for a rotorcraft. The horizontal stabilizer comprising a spar removably coupled to a tailboom...
US20120048995 Method For Enhancing The Aerodynamic Efficiency Of The Vertical Tail Of An Aircraft  
The invention comprises varying the ratio between the control surface local chord (I) and the vertical stabilizer local chord (L) along the height of the vertical tail (2) in order to adapt the...
US20120256047 Method For Improving The Aerodynamic Efficiency Of The Vertical Tail Of An Aircraft  
According to the invention, the thickness (EP1) of the trailing edge (4) of the rudder (9) is varied as a function of the span (E) of the vertical tail (2) to adapt the local value of the...
US20140103159 Tunnel wing system for lift, altitude flight, and ground effect flight  
Aircraft comprising a single wing suspended under a closed sided chassis. The wing spar is mounted to the sides that enclose and channel the airflow over and under the wing to provide lift....
US20120298795 AIRCRAFT WITH A PIVOTABLE REAR PORTION  
The invention relates to an aircraft the fuselage (2) of which extends along a longitudinal axis. The fuselage includes a more or less cylindrical central portion (3) and a rear portion (4) that...
US20140077029 REMOVABLE HORIZONTAL STABILIZER FOR HELICOPTER  
An easily removable and lightweight horizontal stabilizer configured to provide aerodynamic stability for a rotorcraft. The horizontal stabilizer comprising a spar removably coupled to a tailboom...
US20130320137 RUDDER SYSTEM FOR AN AIRCRAFT  
A rudder system for an aircraft includes a centre box, a rudder and actuators, wherein the rudder is pivoted around a hinge line relative to the centre box. The actuators are arranged at an acute...
US20120091267 ADAPTIVE TAIL ASSEMBLY FOR SOLAR AIRCRAFT  
An adaptive aircraft tail assembly includes a tail boom, and a tail structure. The tail structure has a plurality of control surfaces configured to alter or maintain flight characteristics of the...
US20110220758 ARCHITECTURE D'AVION A FUSELAGE LARGE  
A large-capacity airplane principally includes a fuselage which has no region of constant width between the front and the rear and a wing fixed to the fuselage. As a preference, the engines are...
US20150048215 EFFICIENT CONTROL AND STALL PREVENTION IN ADVANCED CONFIGURATION AIRCRAFT  
An apparatus forming an aircraft which is designed for flight by movement through the air, the aircraft has a front and rear portions and a center of mass, with left and right sides when divided...
US20140077026 PITCH STABILIZER AND ROTARY-WING AIRCRAFT EQUIPPED WITH SUCH STABILIZER  
A pitch stabilizer [10] equipped with an upper stabilizer surface [15] and a lower stabilizer surface [20], with the upper stabilizer surface [15] being located in an upper plane [P1] and with the...
US20090173838 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...
US20110095128 AIRCRAFT WITH AT LEAST TWO RUDDER UNITS IN A NON CENTRAL ARRANGEMENT  
An aircraft has at least two rudder units in a non-central arrangement. The rudder units have a profile and are rigidly secured to the aircraft. The profile is adjusted in such a way as to yield...
US20130037657 VORTEX GENERATORS  
A vortex generator, or an array of vortex generators, for attenuating flow separation during flow of fluid over a surface. Vortex generators include a base with a forward end and a leading edge...
US20110147517 PIVOTING STABILISING SURFACE FOR AIRCRAFT  
An aircraft (1) horizontal stabiliser (2) which can vary its sweep angle (6) by rotating around an essentially vertical axis (4) with respect to the direction of flight of the aircraft (1) when...
US20100032519 AIRPLANE WITH A MODIFIABLE SURFACE OF VERTICAL EMPANNAGE  
An aircraft has a vertical fin fastened to the rear and above a fuselage of elongated form, essentially in a vertical plane of symmetry of the aircraft. The vertical fin has at least two stable...
US20130043353 LENTICULAR AIRSHIP AND ASSOCIATED CONTROLS  
A system for controlling yaw associated with an airship may include one or more vertical control surfaces associated with the airship, a first power source and a second power source, each...
US20090256025 STABILIZING AND DIRECTIONAL-CONTROL SURFACE OF AIRCRAFT  
Stabilizing and directional-control surface of an aircraft, said surface comprising a vertical stabilizer (2) and a rudder (3), it being possible for said rudder (3) to be deflected relative to...
US20060108472 Control system for an aircraft  
The invention is a system for controlling an aircraft, the aircraft having a longitudinal axis, vertical and horizontal axis and right and left wings and right and left ailerons mounted on the...
US20090008498 Aircraft stabilizer system and methods of using the same  
An aircraft can include a tail section and a stabilizing system coupled to the tail section. The stabilizing system has a vertical stabilizer and at least one strake that cooperate to generate...
US20090289144 TRIMMABLE HORIZONTAL STABILIZER  
A trimmable horizontal stabilizer is provided adjacent to the fuselage of an aircraft and has a predetermined aerodynamic profile. A movable elevator is arranged adjacent to the horizontal...
US20120138739 AIRCRAFT PROVIDED WITH A TAIL PLANE INCLUDING MEANS FOR COMBATING FLUTTER  
An aircraft (1) provided with a tail boom (4) including a tail plane (100) provided with an airfoil surface (5), the airfoil surface (5) being provided with at least one stabilizer portion (11,...
US20080179454 Lenticular airship  
An airship may include a hull substantially shaped as an oblate spheroid, one or more frame members defining a support structure, wherein the support structure forms at least a partial support for...
US20080128548 Control linkage  
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...
US20070267541 Pivoting coupling system for a large dihedral empennage to the tail fuselage of an aircraft  
Pivoting coupling system of a large dihedral empennage to the tail fuselage of an aircraft, in which the empennage (1) comprises a right lateral box (la) and a left lateral box (1b) arranged at a...
US20100096497 BI-DIRECTIONAL FLIGHT CONTROL SURFACE MECHANISM  
A bi-directional flight control surface mechanism comprises a fixed part V of a vertical stabiliser having leading and trailing edges and a rudder having leading and trailing edges. The rudder is...
US20130119193 METHOD AND DEVICE FOR THE LATERAL STABILIZATION OF AN AIRCRAFT  
The stabilizing device (1) comprises auxiliary stabilizers (6) which are mounted on the horizontal tailplane (2) of the aircraft and which generate a lateral stabilizing effect when brought into a...
US20090020644 CONTRA-BEVEL DRIVEN CONTROL SURFACE  
A contra-bevel driven control mechanism repositions a control surface in a fluid environment such as an aerodynamic or hydrodynamic environment. This involves mechanically coupling an airfoil and...
US20100044496 ANNULAR AIRBORNE VEHICLE  
An airborne vehicle having a wing-body which defines a wing-body axis and appears substantially annular when viewed along the wing-body axis, the interior of the annulus defining a duct which is...
US20080149762 Structural dynamic stability for an aircraft  
An improvement and method for improved structural dynamic stability for 20 and 30 Series Learjets are disclosed. The improvement includes a redistribution of the elevator mass balance to uncouple...
US20140312169 Aircraft System for Reduced Observer Visibility  
An aircraft apparatus is disclosed that has a fuselage boom having proximal and distal ends, a wing coupled to a proximal end of the fuselage boom and at least one transparent stabilizer coupled...
US20100038474 AIRCRAFT HORIZONTAL STABILIZER  
According to the invention, the horizontal stabilizer comprises a fixed intermediate part secured to the structure of said aircraft and at least one mobile edge part able to slide with respect to...
US20100084506 AIRCRAFT RUDDER AUTHORITY CONTROL SYSTEM  
A system that acts on a rudder (L) having its stop parts commanded or moved by an actuator (A) is described. The rudder system comprises a reversible mechanical system with movable stop parts...
US20150183509 AIRCRAFT WITH A TRIMMABLE HORIZONTAL STABILIZER HAVING THE PIVOT ELEMENTS IN ITS FORWARD SIDE  
The invention provides an aircraft with a trimmable horizontal stabilizer (13) that not requires a cut-out in resistant areas of the rear fuselage and that occupies less space that in conventional...
US20090072083 Actuation system with redundant motor actuators  
A multi-redundant motor may be used to implement a relatively small, lightweight redundant actuator assembly package. The motor is implemented as a brushless DC motor and includes N-number of...
US20120111997 ROTORCRAFT EMPENNAGE  
An aircraft is disclosed having an engine and a propeller mounted to a fuselage. An empennage mounts to the aircraft and includes first and second horizontal stabilizers separated by a distance...
US20100155528 AIRCRAFT STABILIZER SURFACE TRAILING EDGE  
Trailing edge (3) of an aircraft stabilizer surface (1), where this surface (1) is manufactured of a composite material and comprises an outer cladding (40) and an inner cladding (41) that are...
US20100163669 Super aircraft structrue  
An aircraft structure is provided. The aircraft structure for an aircraft includes a fuselage, front wings, rear small wings, vertical winglets, and four levels. The fuselage has a cross-section...
US20120104184 AIRCRAFT COMPRISING A DEVICE FOR INFLUENCING THE DIRECTIONAL STABILITY OF THE AIRCRAFT, AND A METHOD FOR INFLUENCING THE DIRECTIONAL STABILITY OF THE AIRCRAFT  
An aircraft including a device for influencing the directional stability of the aircraft is provided. The device includes a control-input device; a flight control device; a sensor device for...
US20100133377 AIRPLANE WITH FLAT REAR FUSELAGE SAID QUEUE-DE-MORUE EMPENNAGE  
An aircraft includes a fuselage having a shape elongated along a longitudinal axis X of the aircraft and at least one wing fixed to the fuselage between the front end and the rear end of the...
US20090159742 Lifting structure for aircraft  
It is essentially applicable to a horizontal stabilizer that includes two side symmetrical boxes that converge at one end (its root) thereof in a shared center area in order to connect integrally...
US20090230240 AERODYNAMIC FAN CONTROL EFFECTOR  
A fan control effector for an aircraft comprises at least one blade configured to be pivotably deployable in a radially outward direction from a retracted position to a deployed position such that...
US20100078518 HORIZONTAL TAIL LOAD ALLEVIATION SYSTEM  
A method for controlling control surfaces. A position limit is identified for movement of a control surface based on a load limit set for the control surface and a number of vehicle current...
US20050178898 Method and apparatus for controlling an airplane  
The present invention is directed a method and apparatus for controlling the light of an airplane, such as a remote controlled airplane. Specifically, on an airplane having a tail section that...
US20090250551 METHOD FOR IMPROVING ROLL STEERING OF AN AIRCRAFT AND AIRCRAFT USING SAME  
The invention concerns a method which consists in subdividing the direction of the control surface into at least two elements (6I, 6S) and, during a roll control using the ailerons (5G, 5D),...
US20120138738 SYSTEM FOR INCREASING CONTROLLABILITY FOR AN AIRCRAFT  
The system includes deflection transmission means (16) to provide a deflection position of the high-lift device (8) for each setting angle position of an adjustable HTP (2). Preferably, the...
US20100148000 AIRCRAFT HORIZONTAL STABILIZER SURFACE  
Aircraft horizontal stabilizer surface (8) in which the sweep angle (40) of this surface (8), where this angle (40) is the one formed by the projection of the reference line of points located at...
US20100163672 FAIRING SYSTEM FOR A HORIZONTAL STABILISER OF AN AIRCRAFT AND PROCESS FOR INSTALLING SAID SYSTEM  
The invention relates to a fairing system for a horizontal stabiliser of an aircraft and to a process for installing said system, such that the fairing system for the sealing of the horizontal...
US20120267473 ELEVON CONTROL SYSTEM  
A system comprising an aerial vehicle or an unmanned aerial vehicle (UAV) (100,400,1000,1500) configured to control pitch, roll, and/or yaw via airfoils (141,142,1345,1346) having resiliently...

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