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US3873049A - Flying machine - Google Patents

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Publication number
US3873049A
US3873049A US393285A US39328573A US3873049A US 3873049 A US3873049 A US 3873049A US 393285 A US393285 A US 393285A US 39328573 A US39328573 A US 39328573A US 3873049 A US3873049 A US 3873049A
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rotors
machine
hull
rearwardly
air
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US393285A
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Paul V Horsdal
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/04—Helicopters
    • B64C27/08—Helicopters with two or more rotors

Definitions

  • a VTOL flying machine has four rotors rotating about respective vertical shafts and each shaped to draw air downwardly.
  • the rotors are in pairs spaced longitudinally and transversely relative to a hull beneath the rotors, and the machine is propelled forwardly by air discharged rearwardly from between the rotors.
  • Each rotor has an inverted dish-shape with radial slots having upwardly projecting trailing edges for directing air to the underside of the rotor.
  • Baffles control the direction of discharge of the rearwardly discharged air to facilitate turning at low speeds.
  • the present invention relates to flying machines, and i more particularly to flying machines intended for verticaltakeoff and landing.
  • helicopters employ one or more powerdriven rotors, in the form of horizontal propellers, instead of the wings of a fixed type of winged aircraft.
  • helicopters are provided at their tails with small propellers providing lateral thrust for counteracting rotation of the fuselage which would otherwise be caused by reaction to the rotation of the horizontal propeller or propellers.
  • a flying machine comprising a hull and four lifting rotors mounted for rotation about respective vertical shafts above the hull, each rotor being shaped to draw air downwardly to beneath the rotor on rotation thereof, the rotors being disposed so that each rotor is spaced longitudinally of the hull from another of the rotors and transversely of the hull from a further one of the rotors, and means for rotating the rotors in directions such that the inboard sides of the rotors rotate towards the rear of the hull.
  • each of the rotors comprises an inverted dish-shaped structure having radial slots, each of the radial slots being defined by an edge projecting forwardly and outwardly from the dish-shaped structure and a further edge projecting inwardly and rearwardly from the dish-shaped structure.
  • the machine may be provided an adjustable baffle structure rearwardly of the rotors for controlling the flow of air impelled rearwardly by the rotors on rotation of the latter.
  • this rearwardly discharged air provides forward propulsion of the machine, and by adjusting the baffles to allow a greater or lesser amount of this air to flow past the baffles and rearwardly off the machine, the rate of forward propul sion of the machine can be varied.
  • the baffles By moving the baffles into a closed" position, in which the baffles do not allow any of the air to flow rearwardly past the baffles, the forward propulsion of the machine can be interupted to allow the machine to hover.
  • the drive means may include a drive transmission linking the four rotor shafts, and in order to avoid disaster in the case of enginefailure, the drive means preferably comprises at least two engines connected to impart drive to the drive transmission, so that if one en-,
  • the other engine or engines can ensure that the machine remains airborne.
  • the hull preferably has a pair of stabilizer fins projecting from opposite sides of the hull, and a tailplane, the tailplane including a rudder for directional control of the forward movement of the machine.
  • FIG. 1 shows a view in perspective of a flying machine
  • FIG. 2 shows a plan view of the machine of FIG. 1;
  • FIG. 3 shows a side view of one of the rotors of the machine of FIGS. 1 and 2;
  • FIG. 4 shows a plan view of the rotor of FIG. 3.
  • the machine has a hull indicated generally by reference numeral 10, a tailplane indicated generally by reference numeral 11, and four rotors 12 to 15. r
  • the hull 10 which has ovoidal upper and lower surfaces 17 and 18, is provided around its periphery with windows 19.
  • the rotors 12 to 15 are disposed so that each rotor is spaced longitudinally of the hull from another of the rotors, and transversely of the hull from a further one of the rotors.
  • the rotors are arranged in two pairs 12, 14 and l3, 15, the rotors of each of these pairs being spaced transversely of the hull from one another and longitudinally of the hull from a respective one of the rotors of the other pair.
  • the rotors 12m 15 are rotated in directions such thatthe inboard side of each of the rotors rotates towards the rear of the hull.
  • the starboard rotors 12 and 13 are rotated in an anticlockwise direction, as viewed from above, and the port rotors 14, 15 are rotated in a clockwise direction, as viewed from above.
  • the rotation of the rotors is effected by a drive transmission comprising drive shafts 21, 22 and 23 and vertical shafts 24, 25, 26 and 27, which carry the rotors 12 to 15;
  • the shafts 21 to 23 are in driving connection, at the ends thereof, with the shafts 24 to 27 through suitable bevel gears (not shown) and are driven by three internal combustion engines 30, 31 and 32.
  • the engines are sufficiently powerful to ensure that the machine can remain airborne even if one of the engines fails.
  • the rotor 12 has an inverted, dish-shape structure and is formed with three radially-extending slots 35.
  • Each of the radially-extending slots 35 is defined by an edge 36 which projects forwardly, in the direction of rotation of the rotor, and outwardly from the dishshaped structure, and an edge 37 which projects inwardly of the dish-shaped structure and rearwardly, with reference to the direction of rotation of the rotor.
  • the edge 36 is thus the trailing edge of the slot 35, and the inturned edge 37 is the leading edge of the slot 35.
  • This rearwardly-flowing airstream effects forward propulsion of the machine.
  • an air baffle structure 38 For controlling the forward propulsion of the ma chine, an air baffle structure 38, shown in FIG. 1, is provided at the rear of the hull 10.
  • the air baffle structure 38 is adjustable to control the amount of the rear wardly-flowing air stream which is allowed to flow through the air baffle structure 38 for effecting the forv ward propulsion of the machine.
  • By adjusting the air baffle structure 38 to reduce or even interrupt the rearward flow of the air stream the forward propulsion of the machine can be correspondingly-reduced or interrupted.
  • the tailplane 11 which is provided on twin booms 39, has a rudder 40 for controlling the direction of forl.
  • a flying machine comprising, in combination;
  • said drive shafts and said rotors being disposed in two pairs, with the two rotors of each pair spaced apart transversely of said machine and with said pairs spaced apart longitudinally of said machine;
  • each of said rotors being dish-shaped and having its concave side facing downwardly;
  • each of said rotors having means defining a plurality of radial slots therein;
  • said slot defining means comprising, for each of said slots, a first edge extending upwardly from, and forwardly in the direction of rotation of, the respective one of said rotors and a second edge extending downwardly from, and rearwardly in the direction of rotation of,- said respective rotor;

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Toys (AREA)

Abstract

A VTOL flying machine has four rotors rotating about respective vertical shafts and each shaped to draw air downwardly. The rotors are in pairs spaced longitudinally and transversely relative to a hull beneath the rotors, and the machine is propelled forwardly by air discharged rearwardly from between the rotors. Each rotor has an inverted dish-shape with radial slots having upwardly projecting trailing edges for directing air to the underside of the rotor. Baffles control the direction of discharge of the rearwardly discharged air to facilitate turning at low speeds.

Description

United States Patent [1 1 Horsdal Mar. 25, 1975 FLYING MACHINE [76] Inventor: Paul V. Horsdal, 60 Sparks St.,
Ottawa, Ontario, Canada [22] Filed: Aug. 31, 1973 21 Appl. No.: 393,285
[30] Foreign Application Priority Data [5 6] References Cited UNITED STATES PATENTS 1,749,572 3/1930 Dorgan 244/17.11 2,414,766 1/1947 Platt 244/17.23 2,420,823 5/1947 Hays 244/17.19 2,540,404 2/1951 Neale 244/17.1l 3,292,864 12/1966 244/52 X 3,336,010 8/1967 Conn 416/183 pl 12' L;
3,563,496 2/1971 Zuck 244/17.19 X
FOREIGN PATENTS OR APPLICATIONS 385,030 2/1965 Switzerland 244/1723 241,243 10/1925 United Kingdom 244/6 725,820 3/1955 United Kingdom 244/17.l1 1,085,378 2/1955 France 244/17.11
Primary ExaminerTrygve M. Blix Assistant Examiner-Barry L. Kelmachter Attorney, Agent, or Firm-Browdy and Neimark [57] ABSTRACT A VTOL flying machine has four rotors rotating about respective vertical shafts and each shaped to draw air downwardly. The rotors are in pairs spaced longitudinally and transversely relative to a hull beneath the rotors, and the machine is propelled forwardly by air discharged rearwardly from between the rotors. Each rotor has an inverted dish-shape with radial slots having upwardly projecting trailing edges for directing air to the underside of the rotor. Baffles control the direction of discharge of the rearwardly discharged air to facilitate turning at low speeds.
1 Claim, 4 Drawing Figures FLYING MACHINE The present invention relates to flying machines, and i more particularly to flying machines intended for verticaltakeoff and landing.
Conventional helicopters employ one or more powerdriven rotors, in the form of horizontal propellers, instead of the wings of a fixed type of winged aircraft. In addition, helicopters are provided at their tails with small propellers providing lateral thrust for counteracting rotation of the fuselage which would otherwise be caused by reaction to the rotation of the horizontal propeller or propellers.
The use of such small propellers for providing lateral thrust can be avoided by employing two counterrotating horizontal propellers, spaced laterally or longitudinally of the helicopter or rotating about a common axis.
In both cases, forward propulsion of the helicopter is effected by tilting the rotor.
It is an object of the present invention to provide a novel and improved flying machine employing rotors for lifting the machine, in which forward propulsion of the machine can be achieved without tilting the rotors.
According, to the present invention, there is provided a flying machine comprising a hull and four lifting rotors mounted for rotation about respective vertical shafts above the hull, each rotor being shaped to draw air downwardly to beneath the rotor on rotation thereof, the rotors being disposed so that each rotor is spaced longitudinally of the hull from another of the rotors and transversely of the hull from a further one of the rotors, and means for rotating the rotors in directions such that the inboard sides of the rotors rotate towards the rear of the hull.
With this arrangement of rotors, at least a portion of the air drawn downwardly by the rotors and discharged centrifugally from the rotors will be discharged rearwardly of the hull from between the rotors. Thisportion of the air can be employed to effect forward propulsion of the aircraft.
Preferably, each of the rotors comprises an inverted dish-shaped structure having radial slots, each of the radial slots being defined by an edge projecting forwardly and outwardly from the dish-shaped structure and a further edge projecting inwardly and rearwardly from the dish-shaped structure. On rotation of the rotors, air flows through the slots to beneath the rotors, thus providing lift for raising the machine.
The machine may be provided an adjustable baffle structure rearwardly of the rotors for controlling the flow of air impelled rearwardly by the rotors on rotation of the latter. As mentioned above, this rearwardly discharged air provides forward propulsion of the machine, and by adjusting the baffles to allow a greater or lesser amount of this air to flow past the baffles and rearwardly off the machine, the rate of forward propul sion of the machine can be varied. By moving the baffles into a closed" position, in which the baffles do not allow any of the air to flow rearwardly past the baffles, the forward propulsion of the machine can be interupted to allow the machine to hover.
The drive means may include a drive transmission linking the four rotor shafts, and in order to avoid disaster in the case of enginefailure, the drive means preferably comprises at least two engines connected to impart drive to the drive transmission, so that if one en-,
gine should fail, the other engine or engines can ensure that the machine remains airborne.
To facilitate stabilization of the machine, the hull preferably has a pair of stabilizer fins projecting from opposite sides of the hull, and a tailplane, the tailplane including a rudder for directional control of the forward movement of the machine.
The invention will be more readily understood from the following description of a preferred embodiment thereof given by way of example with reference to the accompanying drawings, in which:
FIG. 1 shows a view in perspective of a flying machine;
FIG. 2 shows a plan view of the machine of FIG. 1;
FIG. 3 shows a side view of one of the rotors of the machine of FIGS. 1 and 2; and
FIG. 4 shows a plan view of the rotor of FIG. 3.
As shown in FIG. 1, the machine has a hull indicated generally by reference numeral 10, a tailplane indicated generally by reference numeral 11, and four rotors 12 to 15. r
The hull 10, which has ovoidal upper and lower surfaces 17 and 18, is provided around its periphery with windows 19.
As shown in FIGS. 1 and 2, the rotors 12 to 15 are disposed so that each rotor is spaced longitudinally of the hull from another of the rotors, and transversely of the hull from a further one of the rotors. In other words, the rotors are arranged in two pairs 12, 14 and l3, 15, the rotors of each of these pairs being spaced transversely of the hull from one another and longitudinally of the hull from a respective one of the rotors of the other pair.
As indicated by arrows A, B, C and D in FIG. 2, the rotors 12m 15 are rotated in directions such thatthe inboard side of each of the rotors rotates towards the rear of the hull. Thus, the starboard rotors 12 and 13 are rotated in an anticlockwise direction, as viewed from above, and the port rotors 14, 15 are rotated in a clockwise direction, as viewed from above.
The rotation of the rotors is effected by a drive transmission comprising drive shafts 21, 22 and 23 and vertical shafts 24, 25, 26 and 27, which carry the rotors 12 to 15; The shafts 21 to 23 are in driving connection, at the ends thereof, with the shafts 24 to 27 through suitable bevel gears (not shown) and are driven by three internal combustion engines 30, 31 and 32. The engines are sufficiently powerful to ensure that the machine can remain airborne even if one of the engines fails.
The rotor 12 is illustrated in greater detail in FIGS. 3 and 4, and it is to be understood that the construction of the rotors 13, 14 and 15 is similar to that of the rotor 12.
As can be seen in FIGS. 3 and 4, the rotor 12 has an inverted, dish-shape structure and is formed with three radially-extending slots 35.
Each of the radially-extending slots 35 is defined by an edge 36 which projects forwardly, in the direction of rotation of the rotor, and outwardly from the dishshaped structure, and an edge 37 which projects inwardly of the dish-shaped structure and rearwardly, with reference to the direction of rotation of the rotor. The edge 36 is thus the trailing edge of the slot 35, and the inturned edge 37 is the leading edge of the slot 35.
On rotation of the rotor, air is deflected downwardly by the outwardly-extending edge 36, and flows through the slot 35 to beneath the rotor. The air is then discharged peripherally from beneath the rotor. As indicated by arrows E in FIG. 2, a portion of this peripherally-discharged air is discharged at the inboard side of the periphery of each of the rotors 12 to 15 and flows rearwardly of the hull 10 from between the rotors.
This rearwardly-flowing airstream effects forward propulsion of the machine.
For controlling the forward propulsion of the ma chine, an air baffle structure 38, shown in FIG. 1, is provided at the rear of the hull 10. The air baffle structure 38 is adjustable to control the amount of the rear wardly-flowing air stream which is allowed to flow through the air baffle structure 38 for effecting the forv ward propulsion of the machine. By adjusting the air baffle structure 38 to reduce or even interrupt the rearward flow of the air stream, the forward propulsion of the machine can be correspondingly-reduced or interrupted.
The tailplane 11, which is provided on twin booms 39, has a rudder 40 for controlling the direction of forl. A flying machine comprising, in combination;
a hull;
four vertical drive shafts extending upwardly from said hull,
four rotors respectively mounted on said shafts above said hull;
said drive shafts and said rotors being disposed in two pairs, with the two rotors of each pair spaced apart transversely of said machine and with said pairs spaced apart longitudinally of said machine;
means for rotating said vertical drive shafts in directions such that the inboard sides of said rotors travel towards the rear of said machine;
each of said rotors being dish-shaped and having its concave side facing downwardly; and
each of said rotors having means defining a plurality of radial slots therein;
1 said slot defining means comprising, for each of said slots, a first edge extending upwardly from, and forwardly in the direction of rotation of, the respective one of said rotors and a second edge extending downwardly from, and rearwardly in the direction of rotation of,- said respective rotor;
an air baffle structure disposed rearwardly of said r0- tors for deflecting air discharged rearwardly by said rotors;
a pair of stabilizer flaps projecting horizontally from opposite sides of said hull; and
a tailplane provided rearwardly of said baffle structure.

Claims (1)

1. A flying machine comprising, in combination; a hull; four vertical drive shafts extending upwardly from said hull; four rotors respectively mounted on said shafts above said hull; said drive shafts and said rotors being disposed in two pairs, with the two rotors of each pair spaced apart transversely of said machine and with said pairs spaced apart longitudinally of said machine; means for rotating said vertical drive shafts in directions such that the inboard sides of said rotors travel towards the rear of said machine; each of said rotors being dish-shaped and having its concave side facing downwardly; and each of said rotors having means defining a plurality of radial slots therein; said slot defining means comprising, for each of said slots, a first edge extending upwardly from, and forwardly in the direction of rotation of, the respective one of said rotors and a second edge extending downwardly from, and rearwardly in the direction of rotation of, said respective rotor; an air baffle structure disposed rearwardly of said rotors for deflecting air discharged rearwardly by said rotors; a pair of stabilizer flaps projecting horizontally from opposite sides of said hull; and a tailplane provided rearwardly of said baffle structure.
US393285A 1973-07-13 1973-08-31 Flying machine Expired - Lifetime US3873049A (en)

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Cited By (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4874291A (en) * 1987-05-25 1989-10-17 University Of Sydney Rotor arrangement for a rotorcraft
US20040251377A1 (en) * 2003-05-27 2004-12-16 Dammar Michael A. Reduced visibility rotorcraft and method of controlling flight of reduced visibility rotorcraft
US20070018037A1 (en) * 2005-02-15 2007-01-25 Crf Societa Consortile Per Azioni Aircraft of compact dimensions
US20070034739A1 (en) * 2003-10-27 2007-02-15 Urban Aeronautics Ltd. Ducted fan VTOL vehicles
US20070034734A1 (en) * 2005-04-15 2007-02-15 Urban Aeronautics Ltd. Flight control system especially suited for VTOL vehicles
US20070095971A1 (en) * 2005-06-07 2007-05-03 Urban Aeronautics Ltd. Apparatus for generating horizontal forces in aerial vehicles and related method
US20070105474A1 (en) * 2005-11-09 2007-05-10 Taiyo Kogyo Co., Ltd. Radio control flying toy
US20080142643A1 (en) * 2001-06-04 2008-06-19 Urban Aeronautics, Ltd. Vehicles particularly useful as VTOL vehicles
US20080283673A1 (en) * 2005-01-10 2008-11-20 Urban Aeronautics Ltd. Ducted Fan Vtol Vehicles
US20090039206A1 (en) * 2007-04-10 2009-02-12 Bird Stanley W Bird vortex flying machine
US20090084907A1 (en) * 2006-03-01 2009-04-02 Urban Aeronautics Ltd. Ground Effect Vanes Arrangement
US20090140102A1 (en) * 2001-05-29 2009-06-04 Urban Aeronautics, Ltd. Ducted fan vehicles particularly useful as VTOL aircraft
US20090159757A1 (en) * 2006-05-03 2009-06-25 Raphael Yoeli Ducted Fan Vtol Vehicles
WO2009147630A1 (en) * 2008-06-03 2009-12-10 Urban Aeronautics Ltd. Vtol vehicle with offset engine
US20100051753A1 (en) * 2006-11-27 2010-03-04 Raphael Yoeli Wall effects on vtol vehicles
US20100051740A1 (en) * 2008-09-02 2010-03-04 Urban Aeronautics Ltd. Vtol vehicle with coaxially tilted or tiltable rotors
US20100076625A1 (en) * 2006-11-30 2010-03-25 Raphael Yoeli Flight control cockpit modes in ducted fan vtol vehicles
US20100270419A1 (en) * 2007-12-14 2010-10-28 Raphael Yoeli Redundancies and flows in vehicles
US20110049306A1 (en) * 2007-05-02 2011-03-03 Raphael Yoeli Control flows and forces in vtol vehicles
US8876038B2 (en) 2010-10-05 2014-11-04 Urban Aeronautics Ltd. Ducted fan for VTOL vehicles with system and method to reduce roll moments
US9242714B2 (en) 2013-01-10 2016-01-26 SZ DJI Technology Co., Ltd Transformable aerial vehicle
US9896195B2 (en) 2014-06-26 2018-02-20 SZ DJI Technology Co., Ltd. Aerial vehicle and a signal line protection assembly thereof
US10518595B2 (en) 2013-03-15 2019-12-31 Terrafugia, Inc. Combined flying/driving vehicle with vertical takeoff and fixed-wing cruise capabilities
US11067164B2 (en) 2016-04-15 2021-07-20 Terrafugia, Inc. Electronic gear shifter assembly for a dual-mode flying and driving vehicle
US20240239531A1 (en) * 2022-08-09 2024-07-18 Pete Bitar Compact and Lightweight Drone Delivery Device called an ArcSpear Electric Jet Drone System Having an Electric Ducted Air Propulsion System and Being Relatively Difficult to Track in Flight
US12145753B2 (en) * 2023-08-08 2024-11-19 Pete Bitar Compact and lightweight drone delivery device called an ArcSpear electric jet drone system having an electric ducted air propulsion system and being relatively difficult to track in flight

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US1749572A (en) * 1928-02-11 1930-03-04 George W Yeoman Aeroplane
US2414766A (en) * 1943-12-03 1947-01-21 Rotary Res Corp Rotary wing drive
US2420823A (en) * 1943-10-16 1947-05-20 Russell R Hays Helicopter
US2540404A (en) * 1949-01-04 1951-02-06 Pennine Aircraft Ltd Multirotor helicopter
US3292864A (en) * 1965-01-21 1966-12-20 Gen Electric Thrust reverser and deflector
US3336010A (en) * 1966-01-18 1967-08-15 Leroy J Conn Blender rotor
US3563496A (en) * 1967-06-12 1971-02-16 Daniel R Zuck Compound helicopter

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US1749572A (en) * 1928-02-11 1930-03-04 George W Yeoman Aeroplane
US2420823A (en) * 1943-10-16 1947-05-20 Russell R Hays Helicopter
US2414766A (en) * 1943-12-03 1947-01-21 Rotary Res Corp Rotary wing drive
US2540404A (en) * 1949-01-04 1951-02-06 Pennine Aircraft Ltd Multirotor helicopter
US3292864A (en) * 1965-01-21 1966-12-20 Gen Electric Thrust reverser and deflector
US3336010A (en) * 1966-01-18 1967-08-15 Leroy J Conn Blender rotor
US3563496A (en) * 1967-06-12 1971-02-16 Daniel R Zuck Compound helicopter

Cited By (54)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4874291A (en) * 1987-05-25 1989-10-17 University Of Sydney Rotor arrangement for a rotorcraft
US7918416B2 (en) 2001-05-29 2011-04-05 Urban Aeronautics, Ltd. Ducted fan vehicles particularly useful as VTOL aircraft
US20090140102A1 (en) * 2001-05-29 2009-06-04 Urban Aeronautics, Ltd. Ducted fan vehicles particularly useful as VTOL aircraft
US7789342B2 (en) 2001-06-04 2010-09-07 Urban Aeronautics, Ltd. Vehicles particularly useful as VTOL vehicles
US20080142643A1 (en) * 2001-06-04 2008-06-19 Urban Aeronautics, Ltd. Vehicles particularly useful as VTOL vehicles
US7101246B1 (en) 2003-05-27 2006-09-05 Veratech Aero-Rpv Corporation Reduced visibility rotorcraft and method of controlling flight of reduced visibility rotorcraft
US20060214051A1 (en) * 2003-05-27 2006-09-28 Veratech Aero-Rpv Corporation Reduced visibility rotorcraft and method of controlling flight of reduced visibility rotorcraft
US7104862B2 (en) 2003-05-27 2006-09-12 Veratech Aero-Rpv Corporation Reduced visibility rotorcraft and method of controlling flight of reduced visibility rotorcraft
US7059931B2 (en) 2003-05-27 2006-06-13 Veratech Aero-Rpv Corporation Reduced visibility rotorcraft and method of controlling flight of reduced visibility rotorcraft
US20050258304A1 (en) * 2003-05-27 2005-11-24 Veratech Aero-Rpv Corporation Reduced visibility rotorcraft and method of controlling flight of reduced visibility rotorcraft
US20040251377A1 (en) * 2003-05-27 2004-12-16 Dammar Michael A. Reduced visibility rotorcraft and method of controlling flight of reduced visibility rotorcraft
US20070034739A1 (en) * 2003-10-27 2007-02-15 Urban Aeronautics Ltd. Ducted fan VTOL vehicles
US8622335B2 (en) 2003-10-27 2014-01-07 Urban Aeronautics, Ltd. Ducted fan VTOL vehicles
US7857253B2 (en) 2003-10-27 2010-12-28 Urban Aeronautics Ltd. Ducted fan VTOL vehicles
US20110168834A1 (en) * 2003-10-27 2011-07-14 Urban Aeronautics Ltd. Ducted fan vtol vehicles
US7806362B2 (en) 2005-01-10 2010-10-05 Urban Aeronautics Ltd. Ducted fan VTOL vehicles
US20080283673A1 (en) * 2005-01-10 2008-11-20 Urban Aeronautics Ltd. Ducted Fan Vtol Vehicles
US20070018037A1 (en) * 2005-02-15 2007-01-25 Crf Societa Consortile Per Azioni Aircraft of compact dimensions
US7946528B2 (en) 2005-04-15 2011-05-24 Urban Aeronautics, Ltd. Flight control system especially suited for VTOL vehicles
US20070034734A1 (en) * 2005-04-15 2007-02-15 Urban Aeronautics Ltd. Flight control system especially suited for VTOL vehicles
US7717368B2 (en) 2005-06-07 2010-05-18 Urban Aeronautics Ltd. Apparatus for generating horizontal forces in aerial vehicles and related method
US20070095971A1 (en) * 2005-06-07 2007-05-03 Urban Aeronautics Ltd. Apparatus for generating horizontal forces in aerial vehicles and related method
US20070105474A1 (en) * 2005-11-09 2007-05-10 Taiyo Kogyo Co., Ltd. Radio control flying toy
US20090084907A1 (en) * 2006-03-01 2009-04-02 Urban Aeronautics Ltd. Ground Effect Vanes Arrangement
US8020804B2 (en) 2006-03-01 2011-09-20 Urban Aeronautics, Ltd. Ground effect vanes arrangement
US20090159757A1 (en) * 2006-05-03 2009-06-25 Raphael Yoeli Ducted Fan Vtol Vehicles
US8833692B2 (en) 2006-11-27 2014-09-16 Urban Aeronautics Ltd. Wall effects on VTOL vehicles
US20100051753A1 (en) * 2006-11-27 2010-03-04 Raphael Yoeli Wall effects on vtol vehicles
US20100076625A1 (en) * 2006-11-30 2010-03-25 Raphael Yoeli Flight control cockpit modes in ducted fan vtol vehicles
US8011614B2 (en) 2007-04-10 2011-09-06 Bird Stanley W Bird vortex flying machine
US20090039206A1 (en) * 2007-04-10 2009-02-12 Bird Stanley W Bird vortex flying machine
US20110049306A1 (en) * 2007-05-02 2011-03-03 Raphael Yoeli Control flows and forces in vtol vehicles
US8496200B2 (en) 2007-05-02 2013-07-30 Urban Aeronautics Ltd. Control flows and forces in VTOL vehicles
US20100270419A1 (en) * 2007-12-14 2010-10-28 Raphael Yoeli Redundancies and flows in vehicles
WO2009147630A1 (en) * 2008-06-03 2009-12-10 Urban Aeronautics Ltd. Vtol vehicle with offset engine
US8342441B2 (en) 2008-09-02 2013-01-01 Urban Aeronautics Ltd. VTOL vehicle with coaxially tilted or tiltable rotors
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