| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 141 | Hybrid aircraft | EP02075630.0 | 1996-10-24 | EP1211173A3 | 2002-11-27 | Bothe, Hans-Jurgen |
A hybrid aircraft having VTOL R-VTOL and S-STOL capabilities having a lifting body hull (1) and four wing sections (20) arranged in tandem which are pivotally moveable about their neutral axis. Each wing section has mounted thereon a pivotal propeller-rotor (21) assembly for providing thrust substantially in a range between horizontal and vertical. The wings and propellers are integrated to the hull by an outrigger designed to be very stiff and to distribute forces from the wings and propellers from the hull. The hull is shaped to provide aerodynamic lift in an airstream and to facilitate construction by minimizing the number of panels of differing curvature required. The hull is formed of a pressure tensioned frame covered with semi-rigid panels, a lower cladding frame and bow and stem cladding nose cones. The semi-rigid panels covering the frame are formed of gas-tight and abrasion resistant laminate material and are connected to the frame by means of an interface rib and latch system. The frame is formed of a plurality of curved elongate segments arranged in series orthogonal to the long axis of the hull and connected by means of torsion members. A turbo-electric drive system can be used to drive the aircraft. An advanced hybrid aircraft is also described having about 8 to 12 high speed fans in place of the propeller-rotors. |
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| 142 | Hybrid aircraft | EP02075631.8 | 1996-10-24 | EP1209076A3 | 2002-11-27 | Bothe, Hans-Jurgen |
A hybrid aircraft having VTOL R-VTOL and S-STOL capabilities having a lifting body hull (1) and four wing sections (20) arranged in tandem which are pivotally moveable about their neutral axis. Each wing section has mounted thereon a pivotal propeller-rotor (21) assembly for providing thrust substantially in a range between horizontal and vertical. The wings and propellers are integrated to the hull by an outrigger designed to be very stiff and to distribute forces from the wings and propellers from the hull. The hull is shaped to provide aerodynamic lift in an airstream and to facilitate construction by minimizing the number of panels of differing curvature required. The hull is formed of a pressure tensioned frame covered with semi-rigid panels, a lower cladding frame and bow and stem cladding nose cones. The semi-rigid panels covering the frame are formed of gas-tight and abrasion resistant laminate material and are connected to the frame by means of an interface rib and latch system. The frame is formed of a plurality of curved elongate segments arranged in series orthogonal to the long axis of the hull and connected by means of torsion members. A turbo-electric drive system can be used to drive the aircraft. An advanced hybrid aircraft is also described having about 8 to 12 high speed fans in place of the propeller-rotors. |
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| 143 | HYBRID AIRCRAFT | EP96934255.9 | 1996-10-24 | EP0854821B1 | 2002-05-02 | Bothe, Hans-Jurgen |
| A hybrid aircraft having VTOL R-VTOL and S-STOL capabilities having a lifting body hull (1) and four wing sections (20) arranged in tandem which are pivotally moveable about their neutral axis. Each wing section has mounted thereon a pivotal propeller-rotor (21) assembly for providing thrust substantially in a range between horizontal and vertical. The wings and propellers are integrated to the hull by an outrigger designed to be very stiff and to distribute forces from the wings and propellers from the hull. The hull is shaped to provide aerodynamic lift in an airstream and to facilitate construction by minimizing the number of panels of differing curvature required. The hull is formed of a pressure tensioned frame covered with semi-rigid panels, a lower cladding frame and bow and stem cladding nose cones. The semi-rigid panels covering the frame are formed of gas-tight and abrasion resistant laminate material and are connected to the frame by means of an interface rib and latch system. The frame is formed of a plurality of curved elongate segments arranged in series orthogonal to the long axis of the hull and connected by means of torsion members. A turbo-electric drive system can be used to drive the aircraft. An advanced hybrid aircraft is also described having about 8 to 12 high speed fans in place of the propeller-rotors. |
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| 144 | Aircraft lift arrangement | EP00500262.1 | 2000-12-20 | EP1112927A1 | 2001-07-04 | Munoz Saiz, Manuel |
An aircraft lift arrangement that has a fuselage (1), wings (2), a nose (7), a tail (10) and a landing gear (11) and comprises a stretched, flattened fuselage (3) which produces the lift both during forward movement and in side winds, the bottom of which is preferably flat and the top rounded, with narrow lengthened wings used mainly to carry the engines (14) and provide the flight control surfaces (19), the nose inclined with a positive leading angle, the bottom surface (5) flat and the top rounded, and the tail sloping downward, its lower surface flat and the top rounded, to prevent release of the limit layer in upper areas, with large leading angles. The landing gear (11) is moved rearward somewhat to allow greater nose pitch up attitude during takeoff and landing. |
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| 145 | Anlage zum quasi-freien Fliegen in einem Fluggerät | EP98117888.2 | 1998-09-21 | EP0905021A1 | 1999-03-31 | Oepen, Wilhelm; Oepen, Siegfried; Oepen, Karl; Heiders, Hans-Peter; Harrap, Neil |
Die Erfindung betrifft eine Anlage zum quasi-freien Fliegen in einem Fluggerät innerhalb eines begrenzten Raumes. Mit der Anlage soll es jedermann möglich sein, in einem Fluggerät selbständig und individuell zu fliegen, ohne daß dafür eine spezielle Ausbildung erforderlich ist. Vorgeschlagen wird eine Anlage mit mindestens einem im Abstand über dem Erdboden und im wesentlichen parallel zu diesem verlaufenden, aus mindestens einem, an seinem jeweiligen Ende abgespannten Seil (1) bestehenden Seilverbund. An dem Seilverbund ist über mindestens ein mit dem Seilverbund drehbar verbundenes Tragelement mindestens ein Fluggerät (5) aufgehängt, das mindestens einen Fluggast aufnehmen kann und das mit einer motorisch angetriebenen Luftschraube (8) oder einem Düsenantrieb ausgerüstet ist. |
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| 146 | HYBRID AIRCRAFT | EP96934255.0 | 1996-10-24 | EP0854821A2 | 1998-07-29 | Bothe, Hans-Jurgen |
| A hybrid aircraft having VTOL R-VTOL and S-STOL capabilities having a lifting body hull (1) and four wing sections (20) arranged in tandem which are pivotally moveable about their neutral axis. Each wing section has mounted thereon a pivotal propeller-rotor (21) assembly for providing thrust substantially in a range between horizontal and vertical. The wings and propellers are integrated to the hull by an outrigger designed to be very stiff and to distribute forces from the wings and propellers from the hull. The hull is shaped to provide aerodynamic lift in an airstream and to facilitate construction by minimizing the number of panels of differing curvature required. The hull is formed of a pressure tensioned frame covered with semi-rigid panels, a lower cladding frame and bow and stem cladding nose cones. The semi-rigid panels covering the frame are formed of gas-tight and abrasion resistant laminate material and are connected to the frame by means of an interface rib and latch system. The frame is formed of a plurality of curved elongate segments arranged in series orthogonal to the long axis of the hull and connected by means of torsion members. A turbo-electric drive system can be used to drive the aircraft. An advanced hybrid aircraft is also described having about 8 to 12 high speed fans in place of the propeller-rotors. |
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| 147 | FLYING VEHICLE | EP93905682 | 1993-01-21 | EP0596131B1 | 1997-12-29 | SAVITSKY ANATOLY IVANOVICH; SCHUKIN LEV NIKOLAEVICH; KARELIN VIKTOR GEORGIEVICH; PUSHKIN ROSTISLAV; MASS ALEXANDR MIKHAILOVICH; SHIBANOV ANATOLY PETROVICH; SCHUKIN ILYA LVOVICH; KHUTSISCHVILI VLADIMIR GEORGIE; FISCHENKO SERGEI VIKTOROVICH; ERMISCHIN ALEXANDR VIKTOROVICH; SOBKO ALEXANDR PAVLOVICH |
| The invention relates to aviation namely to flying vehicles adapted to ride on an air cushion and to effect a take-off and landing on aerodromes of any category. The goal of the invention is to design a flying vehicle capable of aerodynamically efficient flight both at low and high level flight, as well as take-off and landing from non-prepared aerodromes and from water under the conditions of stabilization and movement control of all flight regimes. The goal is achieved due to the fact that in a flying vehicle comprising a fuselage in the form of a carrying wing, a power installation, a take-off and landing air cushion device, a gasodynamic system of boundary layer control, a device for controlling the position of flow leaving the trailing edge as well as stabilization and flight control systems, the take-off and landing air cushion device consists of a propelling slot nozzle (12) and side skegs (17) between which are mounted rotatable flaps (21, 22, 23) controlling the flight of the vehicle and regulating the position of the pressure centre on the bottom. The fuselage has the form of a cylindrical segment conjugating at its sides with spherical fairings. | ||||||
| 148 | FLYING VEHICLE. | EP93905682 | 1993-01-21 | EP0596131A4 | 1994-10-19 | SAVITSKY ANATOLY IVANOVICH; SCHUKIN LEV NIKOLAEVICH; KARELIN VIKTOR GEORGIEVICH; PUSHKIN ROSTISLAV MIKHAILOVICH; MASS ALEXANDR MIKHAILOVICH; SHIBANOV ANATOLY PETROVICH; SCHUKIN ILYA LVOVICH; KHUTSISCHVILI VLADIMIR GEORGIE; FISCHENKO SERGEI VIKTOROVICH; ERMISCHIN ALEXANDR VIKTOROVICH; SOBKO ALEXANDR PAVLOVICH |
| The invention relates to aviation namely to flying vehicles adapted to ride on an air cushion and to effect a take-off and landing on aerodromes of any category. The goal of the invention is to design a flying vehicle capable of aerodynamically efficient flight both at low and high level flight, as well as take-off and landing from non-prepared aerodromes and from water under the conditions of stabilization and movement control of all flight regimes. The goal is achieved due to the fact that in a flying vehicle comprising a fuselage in the form of a carrying wing, a power installation, a take-off and landing air cushion device, a gasodynamic system of boundary layer control, a device for controlling the position of flow leaving the trailing edge as well as stabilization and flight control systems, the take-off and landing air cushion device consists of a propelling slot nozzle (12) and side skegs (17) between which are mounted rotatable flaps (21, 22, 23) controlling the flight of the vehicle and regulating the position of the pressure centre on the bottom. The fuselage has the form of a cylindrical segment conjugating at its sides with spherical fairings. | ||||||
| 149 | Rescue craft | EP88306623.5 | 1988-07-20 | EP0300746B1 | 1993-08-18 | Brant, Harry |
| 150 | Rescue craft | EP88306623.5 | 1988-07-20 | EP0300746A2 | 1989-01-25 | Brant, Harry |
A rescue craft (1) includes a self-propelled car or elevator type of flying machine for rescuing persons from high-rise buildings, during fires, or other emergencies. The craft is powered by fan-jet engines (2) capable of lifting the unit (1) in vertical take-offs. A cable (18) attached to a ground structure is used to control the craft (1) and facilitate descent to ground level. An internal guidance system provides 360° maneuverability around the cable (18) and facilitates docking against the sides of buildings, etc. The ground structure (10) comprises a flat-bed tractor/trailer equipped to transport the craft to the scene of an emergency. The ground structure is fully self-contained with diesel power, a winch for the cable, lighting, refueling capability, and is fully ballasted and outrigged and capable of launching and receiving the rescue craft. |
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| 151 | SYSTEM INTENDED FOR CAPTURING AND/OR COLLECTING AEROBIOLOGICAL PARTICLES BY MEANS OF MULTI-ROTORS | PCT/ES2016070671 | 2016-09-26 | WO2017051055A4 | 2017-04-27 | GARCÍA MEDINA FRANCISCO JAVIER; ROLDÁN HERNÁNDEZ JORGE; BELMONTE SOLER JORDINA |
| The invention relates to a system intended for capturing and/or collecting area biological particles by means of multi-rotors (1), wherein, firstly, the system for capturing aerobiological particles can be disposed on any part of the multi-rotor where there is a positive airflow caused by the blades of same or by the surrounding air current generated, and, secondly, the system incorporates measuring sensors, installed together with the capturing system, the measuring sensors being able to obtain the flow, quantity and speed of the air and temperature, moisture and CO2 levels. | ||||||
| 152 | AIRBORNE PLATFORM | PCT/PT2012000007 | 2012-03-15 | WO2012125052A3 | 2012-12-27 | COSTA DUARTE PARDAL TIAGO; MARQUES DOS SANTOS SILVA PEDRO MIGUEL |
| The invention pertains to aeronautical engineering and consists of an airborne platform that can be built to large sizes without requiring a rigid structure of comparable dimensions and which uses both buoyancy and the aerodynamic Magnus effect for lift. The aerodynamic lift is generated in lifting bodies (1), which also contain buoyant gas. The" lifting bodies (1) are stacked in a column, at the bottom of which there is a structural anchoring module (2) which also contains buoyant gas. ^The lifting bodies (1) and anchoring modules (2) are connected by slender structural elements which, when taken together as a whole form a non-rigid assembly. The platform may be tethered or configured as an aircraft, for which purpose other features may be added, such as a propulsion system (11), a crew gondola (6), cables to (7) and from (8) a swivel (12) and a payload (10) connected to said cables. | ||||||
| 153 | THE DEVICE TO GENERATE LIFT FORCE (OPTIONS) | PCT/KZ2011000010 | 2011-06-06 | WO2012091533A2 | 2012-07-05 | AKHMEJANOV ALIBI |
| The options of the invention relate to the aviation and can be used in order to create lifting vehicle as well as load lifting devices. In order to achieve technical result - the decrease of energy losses on the while creating and change of vector of moving, aerodynamic, composite force, including as a component a lift force, - in the device to generate lift force containing a tubiform frame, superchargers, the wings having in section an aerofoil profile oriented by the leading edge to the direction of working medium exhaust out of the super-charger, adjusting units for a wing, guiding devices, each of those is installed in front of leading edge of each wing, the system to maintain the required working temperature of medium, unit to connect outdoor environment, as per the invention in the first option of the device a tubiform frame is of the form of a tore, in the second option - the form of closed volumetric loop, in the third option - a cylindrical form. Meanwhile each option of the device is equipped with relevant distinguishing units, providing the achieving of a technical result. | ||||||
| 154 | HYBRID AIRCRAFT | PCT/CA9600705 | 1996-10-24 | WO9715492A2 | 1997-05-01 | BOTHE HANS-JURGEN |
| A hybrid aircraft is taught having VTOL, R-VTOL and S-STOL capabilities. The aircraft has a lifting body hull (1) and four wing sections (20) arranged in tandem which are pivotally moveable about their neutral axis. Each wing section has mounted thereon a pivotal propeller-rotor (21) assembly for providing thrust substantially in a range between horizontal and vertical. The wings and propellers are integrated to the hull by an outrigger designed to be very stiff and to distribute forces from the wings and propellers to the hull. The hull is shaped to provide aerodynamic lift in an airstream and to facilitate construction by minimizing the number of panels of differing curvature required. The hull is formed of a pressure tensioned frame covered with semi-rigid panels, a lower cladding frame and bow and stem cladding nose cones. The semi-rigid panels covering the frame are formed of gas-tight and abrasion resistant laminate material and are connected to the frame by means of an interface rib and latch system. The frame is formed of a plurality of curved elongate segments arranged in series orthogonal to the long axis of the hull and connected by means of torsion members. A turbo-electric drive system can be used to drive the aircraft. An advanced hybrid aircraft is also described having about 8 to 12 high speed fans in place of the propeller-rotors. | ||||||
| 155 | MODULAR AND MORPHABLE AIR VEHICLE | PCT/US2011036564 | 2011-05-14 | WO2011146349A3 | 2014-03-27 | PIASECKI JOHN W; FREDERICK PIASECKI W; BRIAN GEIGER; JOHNSON DOUGLAS; PITCAIRN DAVID |
| An unmanned air module includes one or more rotors, engines, a transmission and avionics. Any of several different ground modules may be attached to the air module. The air module may fly with and without the ground module attached. The ground module may be a vehicle ground module and may be manned. The vehicle ground module may transport the attached air module across the ground. The air module may have two rotors, which may be ducted fans, and three different configurations: a tandem rotor configuration, a side-by-side configuration, and a tilted-rotor configuration. | ||||||
| 156 | AIRCRAFT SYSTEM FOR REDUCED OBSERVER VISIBILITY | PCT/US2012051176 | 2012-08-16 | WO2013070296A2 | 2013-05-16 | FISHER CHRISTOPHER; CHAMBERS STEVEN; BELIK PAVIL; GUNDER AUSTIN; ZWAAN JOHN PETER |
| An aircraft apparatus is disclosed that has a fuselage boom (102) having proximal (110) and distal (103) ends, a wing (108) coupled to a proximal end (110) of the fuselage boom (102) and at least one transparent stabilizer (104, 106) coupled to a distal end (103) of the fuselage boom (102). | ||||||
| 157 | AIRBORNE PLATFORM | PCT/PT2012000007 | 2012-03-15 | WO2012125052A4 | 2013-02-21 | COSTA DUARTE PARDAL TIAGO; MARQUES DOS SANTOS SILVA PEDRO MIGUEL |
| The invention pertains to aeronautical engineering and consists of an airborne platform that can be built to large sizes without requiring a rigid structure of comparable dimensions and which uses both buoyancy and the aerodynamic Magnus effect for lift. The aerodynamic lift is generated in lifting bodies (1), which also contain buoyant gas. The" lifting bodies (1) are stacked in a column, at the bottom of which there is a structural anchoring module (2) which also contains buoyant gas. ^The lifting bodies (1) and anchoring modules (2) are connected by slender structural elements which, when taken together as a whole form a non-rigid assembly. The platform may be tethered or configured as an aircraft, for which purpose other features may be added, such as a propulsion system (11), a crew gondola (6), cables to (7) and from (8) a swivel (12) and a payload (10) connected to said cables. | ||||||
| 158 | MAGNETIC LEVITATION ROPE TRANSPORT SYSTEM | PCT/IB2007050157 | 2007-01-17 | WO2008087496A2 | 2008-07-24 | ILYANOK ALEXANDER MIKHAILOVICH |
| The invention relates to three variants of magnetic levitation rope transport systems, i.e. aviation, space lift, electromagnetic lift and to method of operation thereof. They are linked by a single general inventive concept and by single technical characterising feature, which is the displacement of a magnetically levitated transport module along an ultrastrong light rope (ropes) exhibiting high electrical conductivity. The rope is produced according to nanotechnology using carbon and other natotubes in such a way that the strength thereof is at least one hundred times greater than the strength of steel and weight thereof is several times lower. The electrical conductivity of the rope is at least one hundred times greater than the electrical conductivity of aluminium or copper at a room temperature and, at the limit, said rope is embodied in the form of a high-temperature superconductor (up to 93.5°C). The magnetic levitation and the displacement along the rope are carried out by means of a linear electric motor, the coil of which is made of a material which is similar to the rope material. The interaction of the magnetic fields of the motor and ropes makes it possible to simultaneously produce levitation and propulsion. The electric power required for motion is supplied from a power source via the ropes. | ||||||
| 159 | REDUCED VISIBILITY ROTORCRAFT AND METHOD OF CONTROLLING FLIGHT OF REDUCED VISIBILITY ROTORCRAFT | PCT/US2004016776 | 2004-05-27 | WO2005019029A3 | 2006-02-16 | DAMMAR MICHAEL A |
| A rotary aircraft (rotorcraft) in which the entire aircraft rotates about its center of mass as it flies, and in which the center of mass is located external to the aircraft in the generally triangular region formed by the aircraft's single wing and two propellers. As the aircraft flies, the two propellers provide torque about the center of mass and rotate the wing, which provides lift for the aircraft. The aircraft is controllable via a stationary radio transmitter that sends commands for pitch, roll, yaw and altitude. A receiver in the aircraft uses the transmitted signal to establish the aircraft's instantaneous orientation in combination with the sent commands to generate control signals that drive the propeller motors that affect the aircraft's attitude. Pitch and roll are controlled by pulse width modulation of the propeller motor voltages in order to affect the thrust at specific portions of the aircraft's rotation cycle. | ||||||
| 160 | CENTRIFUGAL ACCELERATOR REVERSE GRAVITY TRANSPORTER AND INERTIA REACTIVE ACCELERATION PROPULSER | PCT/US9507860 | 1995-06-27 | WO9600497A2 | 1996-01-11 | ARNTZ FRIEDRICH OTTOKAR WILHEL |
| This invention deals with a new propulsion system coupled to a new type of Tranportvehicule having suitably made and appropriately installed prime energy input converters converting prime energy input into programmable UNIDIRECTIONAL FORCE by means of suitable pairs of CONTRA-ROTATIVE/CONTRA-REVOLVIVE Bladevane-equipped ROTORS being rotated in GUIDED ALIGNMENT within suitable SHROUDCASINGS, such BLADE-VANE-ROTORS having their specially constructed vanes form a circular row of balance-spaced LOAD-POCKET-CAVITIES, wherein such cavities are placed and installed along a circumferential perimeter band of each rotor further wherein such perimeter vane-pocket-cavities are loaded with a suitable MASS LIQUID throughout an essentially LESS than 180 DEG HALFCIRCULAR rotational plane while the remaining 180 DEG plus, PART-CIRCULAR rotative plane of aforesaid Rotor-pockets are NOT loaded with such MASS LIQUID, that is to say, are rotated in an EMPTY CONDITION and whereinfurther such MASS LIQUID is suitably S I D E -injected in suitable manner effecting the MOST EFFICIENT and the MOST VOLUMINOUS MASS LIQUID TRANSFER into THE LOADING and LOADED PART of ROTATED ROTOR during rotatio. This way UNIDIRECTIONAL FORCE is CREATED in the TWO QUADRANT areas contained within an arc extending from essentially the 12 o'clock position THROUGH the 3 o'clock position TO the 6 o'clock position in the CLOCKWISE rotated ROTOR unit and such UNIDIRECTIONAL FORCE is CREATED in the TWO QUADRANT areas contained within an arc extending essentially FROM the 12 o'clock position THROUGH the 9 o'clock position TO the 6 o'clock position in the COUNTERCLOCKWISE rotated ROTOR unit. | ||||||
