| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 41 | Flugzeugkonfiguration | EP14004141.9 | 2014-12-09 | EP2883792B1 | 2016-06-22 | Stückl, Stefan; van Toor, Jan |
| 42 | MULTI-TASK FRISBEE-UMBRELLA | EP15165141.1 | 2015-04-25 | EP2939922A1 | 2015-11-04 | Mottale, Sima |
The present invention discloses an unmanned aerial vehicle (1) capable of transforming its shape, comprising The present invention relates also to the use of the vehicle.
|
||||||
| 43 | AIRCRAFT ON AN AIR CUSHION WITH AEROSTATIC LOAD RELIEF | EP10845348 | 2010-08-17 | EP2527218A4 | 2014-05-07 | FILIMONOV ALEXANDR IOSIFOVICH; SHLYAKHOV ALEXANDR SERGEEVICH |
| 44 | PERSONAL AIRCRAFT | EP11810313.4 | 2011-07-19 | EP2595882A2 | 2013-05-29 | KROO, Ilan |
| A safe, quiet, easy to control, efficient, and compact aircraft configuration is enabled through the combination of multiple vertical lift rotors, tandem wings, and forward thrust propellers. The vertical lift rotors, in combination with a front and rear wing, permits a balancing of the center of lift with the center of gravity for both vertical and horizontal flight. This wing and multiple rotor system has the ability to tolerate a relatively large variation of the payload weight for hover, transition, or cruise flight while also providing vertical thrust redundancy. The propulsion system uses multiple lift rotors and forward thrust propellers of a small enough size to be shielded from potential blade strike and provide increased perceived and real safety to the passengers. Using multiple independent rotors provides redundancy and the elimination of single point failure modes that can make the vehicle non-operable in flight. | ||||||
| 45 | AIRCRAFT ON AN AIR CUSHION WITH AEROSTATIC LOAD RELIEF | EP10845348.1 | 2010-08-17 | EP2527218A1 | 2012-11-28 | Filimonov, Alexandr Iosifovich; Shlyakhov, Alexandr Sergeevich |
The present invention pertains to the field of aviation and relates to aircraft using a mixed flight principle for transporting super-heavy and oversized loads. The aircraft includes a disc-shaped body in which an aerostatic lift system and a central tunnel are arranged, a pilot-passenger cabin, propulsion units with propellers, and members for landing on an air cushion in the form of an inflatable toroidal balloon with a flexible guard on the front and side portions thereof. A streamlined body provided inside the tunnel comprises a lift propeller on the upper portion thereof and is secured to the tunnel walls by radial partitions. The aircraft includes on each side two or more side wing brackets and a rear tail unit with control and stabilization members in the form of air rudders and jet rudders and elevons for the horizontal tail unit. The fins of the tail unit are arranged on the rear portion of the body on tail beams, and rotating shutters are provided at the inlet of the tunnel. A number of longitudinal aerodynamic fences are provided on the topside of the front portion of the body on either side of the tunnel. The present invention enhances the exploitation take-off and landing characteristics of the aircraft. |
||||||
| 46 | DISPOSITIF DE SUSPENSION D'UN MOBILE | EP09761915.9 | 2009-05-19 | EP2288508A1 | 2011-03-02 | Antenat, Olivier |
| The invention relates to a device comprising a base (1) for receiving a load, connected to two side supporting elements (2) supported by the medium and formed by two hinged assemblies (3) including a swivel lever (31) with two arms (31a, b) forming therebetween an obtuse angle (β) other than 180°, said arms being connected to a central pivot (32, 33) and each arm terminating in a side pivot (35, 36). The central pivot (32, 33) is connected to the base (1) and the side pivots are each connected to a side supporting element (35, 36). The feet of the pivots (33) are positioned on a straight baseline (X oX o) of the base (1) and the two homologous side pivots (36) are positioned on an auxiliary line (X 1X 1) of the side supporting element (2). The lines (X oX o) and (X 1X 1) are parallel to a direction d and the axes of the pivots are parallel and form an angle (α) other than 90° with said direction d. The optimum angles for the suspension device are α = 32.79°, β = 149.70°. | ||||||
| 47 | An aircraft of compact dimensions | EP05425074.1 | 2005-02-15 | EP1690788A1 | 2006-08-16 | Perlo, Pietro; Bollea, Denis |
The aircraft (10) comprises a fuselage (12), a main wing (16) substantially of disc-like shape positioned above the fuselage (12), and a secondary wing (18) which intersects the fuselage (12) and is provided with movable control parts. The aircraft further comprises a main propulsion system including an internal combustion engine intended to drive a propeller (26) positioned at the rear of the fuselage (12) and a secondary propulsion system for the propulsion of the aircraft in a direction perpendicular to the ground. The secondary propulsion system includes a matrix of nozzles (32) positioned on the lower surface of the secondary wing (18) and arranged to emit the exhaust gases coming from the main engine in the form of micro-jets. The main propeller propulsion system and the secondary nozzle propulsion system are selectively controllable in such a way that the aircraft is able to perform three different take-off modes, that is to say a first, conventional take-off mode in which only the main propulsion system is used, a second (STOL) take-off mode in which both the main propulsion system and the secondary propulsion system are used, and a third (VTOL) take-off mode in which only the secondary propulsion system is used.
|
||||||
| 48 | Lift arrangement for lateral aircraft surfaces | EP01500196.9 | 2001-07-24 | EP1176088A1 | 2002-01-30 | Munoz Saiz, Manuel |
Lifting arrangement for lateral aircraft surfaces that consists of numerous lateral flutings, grooves, flutes or riblets parallel to each other, arranged on the lateral surfaces of fuselages, fin units, pylons and gondolas of aircraft with a downward slope from the nose to the tail, with the flow of air passing through such flutings, grooves, etc., towards the rear and downwards, generating lifting by reaction, using small planes orfins to support the engines and flight control fins. |
||||||
| 49 | Flugzeug für Personen- und/oder Frachttransport | EP98101864.1 | 1998-02-04 | EP0857648A2 | 1998-08-12 | Vassiliev, Anatoli J., Prof. Dr.; Eibel, Karl-Heinz |
Flugzeug für Personen- und/oder Frachttransport auf Basis eines bekannten Flugzeugbaumusters mit einem Rumpf mit Nasensektion, Mittelsektion und Schwanzsektion und an der Mittelsektion nahe des Schwerpunktes des Flugzeuges angebrachten und entsprechend des erforderlichen Auftriebs berechneten Tragflächen und im Bereich der Schwanzsektion angeordneten Höhen- und/oder Seitenleitwerken zur Erzeugung von Stabilisierungs- und Steuermomenten, wobei zur Vergrößerung der Transportkapazität des Flugzeuges ausgehend vom vorgegebenen bekannten Flugzeugbaumuster der Rumpf desselben mittels einer zwischen der Nasensektion und dem Schwerpunkt des Flugzeugbaumusters eingefügten Zusatzsektion verlängert ist und die Zusatzsektion in Flugrichtung gesehen vor den als Haupttragflächen dienenden Tragflächen des Flugzeugbaumusters mit als Zusatztragflächen dienenden Tragflächen ausgerüstet ist, wobei als Zusatztragflächen durchkonstruierte und berechnete Tragflächen geeigneter Größe eines bekannten Flugzeugbaumusters eingesetzt sind. |
||||||
| 50 | MULTI-TASK FRISBEE-UMBRELLA | EP15165141.1 | 2015-04-25 | EP2939922B1 | 2018-08-22 | Mottale, Sima |
| The present invention discloses an unmanned aerial vehicle (1) capable of transforming its shape, comprising a) a control apparatus (2) with batteries (2a) b) one or more propellers (3) being fixed to the control apparatus (2), c) a multitude of flaps (4) which are foldable reversibly from an open to a closed position, wherein the flaps (4) provide i) in open position about a disc shape which is about in parallel to the plane of the rotating propeller (3), and ii) in closed position a shuttlecock shape, wherein, at least one of the flaps (4) comprises a battery recharge element, such as a solar panel, photovoltaic element or elements, an electromagnetic harvesting element, a thermoelectric generator and/or a solar thermoelectric generator. The present invention relates also to the use of the vehicle. | ||||||
| 51 | AIRCRAFT HAVING DUAL ROTOR-TO-WING CONVERSION CAPABILITIES | EP17163294.6 | 2017-03-28 | EP3290337A1 | 2018-03-07 | GRONINGA, Kirk Landon; ROBERTSON, Daniel Bryan; STAMPS, Frank Bradley |
A tail sitter aircraft (10) includes a fuselage (12) having a forward portion (14) and an aft portion (16). The forward portion (14) of the fuselage (12) includes first and second rotor stations (18, 20). A first rotor assembly (22) is positioned proximate the first rotor station (18). A second rotor assembly (24) is positioned proximate the second rotor station (20). A tailboom assembly (26) extends from the aft portion (16) of the fuselage (12) and includes a plurality of landing members (28). A pusher propeller (38) extends from the tailboom assembly (26). In a vertical takeoff and landing mode, the first and second rotor assemblies (22, 24) rotate about the fuselage (12) to provide vertical thrust. In a forward flight mode, rotation of the pusher propeller (38) provides forward thrust and the first and second rotor assemblies (22, 24) are non-rotatable about the fuselage (12) forming a dual wing configuration to provide lift.
|
||||||
| 52 | SELF-MOVING APPARATUS AND COMPONENTS THEREOF | EP16769146.8 | 2016-03-18 | EP3272648A2 | 2018-01-24 | Sapargaliyev, Aldan Asanovich |
The present invention relates to SMAs (self-moving apparatuses) which use any type of propulsion means, including, without limitation, an FPGB (propeller-gear block) comprising an FP (propeller) and a drive for supplying power thereto. More particularly, the present invention describes: novel forms of energy-efficient (economical) FPGBs; and novel conceptual designs for SMAs, which make it possible to create economical SMAs with high specific power. The invention can be used for creating novel energy-efficient types of SMAs, and for the widespread (mass) use of compact and environmentally-friendly electric engines instead of environmentally detrimental and bulky internal combustion engines. |
||||||
| 53 | AIRCRAFT WITH SELECTIVELY ATTACHABLE PASSENGER POD ASSEMBLY | EP16185727.1 | 2016-08-25 | EP3263445A1 | 2018-01-03 | McCULLOUGH, John Richard; OLDROYD, Paul K. |
In some embodiments, an aircraft (10) includes a flying frame (12) having an airframe (26), a propulsion system (34) attached to the airframe (26) and a flight control system (68) operably associated with the propulsion system (34) wherein, the flying frame (12) has a vertical takeoff and landing mode and a forward flight mode. A pod assembly (70) is selectively attachable to the flying frame (12) such that the flying frame (12) is rotatable about the pod assembly (70) wherein, the pod assembly (70) remains in a generally horizontal attitude during vertical takeoff and landing, forward flight and transitions therebetween.
|
||||||
| 54 | DRONE VOLANT COMPRENANT DEUX AILES PORTANTES EN TANDEM SUR LESQUELLES SONT COUPLÉES DES CELLULES PHOTOVOLTAÏQUES | EP17150611.6 | 2017-01-09 | EP3192739A1 | 2017-07-19 | David, Benjamin |
L'invention concerne un drone volant (1) comprenant : |
||||||
| 55 | AVION A FUSELAGE A CORPS PORTANTS | EP15305788.0 | 2015-05-26 | EP3098162A1 | 2016-11-30 | Geneste, Jean-François |
Un avion comporte un fuselage et une pluralité de surfaces portantes (20a, 20b, 20c). Le fuselage comporte au moins deux corps portants (10a, 10b), juxtaposés dans un plan horizontal, qui sont maintenus entre eux par des parties des surfaces portantes. Les corps portant (10a, 10b) présente une forme d'ensemble de demi-cône tronqué dont des sections perpendiculaires à un axe longitudinal (13) du cône présentent une forme arrondie dans une partie inférieure et aplatie dans une partie supérieure.
|
||||||
| 56 | SENKRECHTSTARTFÄHIGES FLUGGERÄT | EP14756074.2 | 2014-08-29 | EP3038913A1 | 2016-07-06 | JUDAS, Michael; STRATENBERG, Friederike; VAN TOOR, Jan; SCHOLZ, Werner; KARRAIS, Berthold; STANGL, Wolfgang |
| The invention relates to an aircraft (1) which can both take off and land vertically and can hover and also fly horizontally at a high cruising speed. The aircraft (1) has a support structure (27), a wing structure (15), at least three and preferably at least four lifting rotors (5) and at least one thrust drive (9). The wing structure (15) is designed to generate a lifting force for the aircraft during horizontal motion. To achieve this the wing structure (15) has at least one mainplane (3) provided with a profile that generates dynamic lift. The wing structure (15) is preferably designed as a tandem wing structure. Each of the lifting rotors (5) is fixed to the support structure (27), has a propeller (7) and is designed to generate a lifting force for the aircraft (1) by means of a rotation of the propeller (7), said force acting in a vertical direction. The thrust drive (9) is designed to generate a thrust force on the support structure (27), said force acting in a horizontal direction. The lifting rotors (5) can have a simple construction, i.e. they can have a simple rigid propeller for example, and a vertical take-off or hovering of the aircraft can be controlled, in a similar manner to quadcopters, by a simple control of the speeds of the lifting rotors. High cruising speeds can be achieved as a result of the additional horizontally acting thrust drive (9). | ||||||
| 57 | PERSONAL AIRCRAFT | EP11810313.4 | 2011-07-19 | EP2595882B1 | 2016-06-08 | KROO, Ilan |
| A safe, quiet, easy to control, efficient, and compact aircraft configuration is enabled through the combination of multiple vertical lift rotors, tandem wings, and forward thrust propellers. The vertical lift rotors, in combination with a front and rear wing, permits a balancing of the center of lift with the center of gravity for both vertical and horizontal flight. This wing and multiple rotor system has the ability to tolerate a relatively large variation of the payload weight for hover, transition, or cruise flight while also providing vertical thrust redundancy. The propulsion system uses multiple lift rotors and forward thrust propellers of a small enough size to be shielded from potential blade strike and provide increased perceived and real safety to the passengers. Using multiple independent rotors provides redundancy and the elimination of single point failure modes that can make the vehicle non-operable in flight. | ||||||
| 58 | WING STRUCTURE AND FAIRING DEVICE | EP10822101 | 2010-10-07 | EP2487371A4 | 2015-03-25 | KIMURA YUKIHIDE; MORIMOTO TOMOAKI |
| The invention provides a wing structure 1 including: a main wing 2 that extends in a second direction intersecting a first direction as a fluid flow direction; and an auxiliary wing 3 that is disposed so as to be separated from the main wing 2 and faces the main wing 2 at the front part side of the main wing 2, wherein a wing chord length of the auxiliary wing 3 is shorter than a wing chord length of the main wing 2. According to the invention, a fluid contacts the auxiliary wing 3 which is formed at the front part side of the main wing 2, the fluid is guided between the auxiliary wing 3 and the main wing 2, and the fluid is compressed when passing between the auxiliary wing 3 and the main wing 2, thereby appropriately forming a fluid compression process region on the surface of the main wing 2 and increasing an acting force. | ||||||
| 59 | THREE WING, SIX TILT-PROPULSION UNITS, VTOL AIRCRAFT | EP11831074.7 | 2011-06-16 | EP2625099A1 | 2013-08-14 | OLIVER, Richard, David |
| A vertical takeoff and landing aircraft having a fuselage with three wings and six synchronously tilt-able propulsion units, each one mounted above, below, or on each half of the aforementioned three wings. The propulsion units are vertical for vertical flight, and horizontal for forward flight. The aircraft wings are placed such that the rear wing is above the middle wing which is placed above the front wing. The placement of each of the propulsion units relative to the center of gravity of the aircraft about the vertical axis inherently assures continued stability in vertical flight mode, following the loss of thrust from any one propulsion unit. The placement of the propulsion units, viewing the aircraft from the front, is such that each propulsion units' thrust wake does not materially disturb the propulsion unit to its rear. When engine driven propellers or rotors are utilized, flapped wing panels are attached outboard of the forward and/or rearward propulsion units to provide yaw control during vertical flight. | ||||||
| 60 | THREE WING, SIX TILT-PROPULSION UNIT, VTOL AIRCRAFT | EP11831080.4 | 2011-06-27 | EP2625094A1 | 2013-08-14 | OLIVER, Richard, David |
| A vertical takeoff and landing aircraft having a fuselage with, preferably, three wings and six synchronously tilt-able propulsion units, each one mounted above, below, or on each half of the aforementioned three wings. The propulsion units are oriented vertically for vertical flight and horizontally for forward flight. Each propulsion unit comprises a propeller having a plurality of blades, where the pitch angle associated with the distal end of each blade and the proximal end of each blade are independently adjustable. As such, each of the propellers can be adjusted to exhibit a first blade pitch angle distribution optimized for vertical flight and a second blade pitch angle distribution optimized for forward flight. | ||||||
