WO2009157781A1 - Personal flight vehicle including control system - Google Patents

Personal flight vehicle including control system Download PDF

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Publication number
WO2009157781A1
WO2009157781A1 PCT/NZ2009/000075 NZ2009000075W WO2009157781A1 WO 2009157781 A1 WO2009157781 A1 WO 2009157781A1 NZ 2009000075 W NZ2009000075 W NZ 2009000075W WO 2009157781 A1 WO2009157781 A1 WO 2009157781A1
Authority
WO
WIPO (PCT)
Prior art keywords
control
pair
fan
personal flight
flight device
Prior art date
Application number
PCT/NZ2009/000075
Other languages
French (fr)
Inventor
Glenn Neil Martin
Colin Cecil Dodge
Mark John Daniel
Original Assignee
Martin Aircraft Company Limited
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Martin Aircraft Company Limited filed Critical Martin Aircraft Company Limited
Priority to BRPI0914968A priority Critical patent/BRPI0914968A2/en
Priority to CN2009801244316A priority patent/CN102076561A/en
Priority to JP2011516194A priority patent/JP5510843B2/en
Priority to US13/001,319 priority patent/US8695916B2/en
Priority to EP09770443.1A priority patent/EP2303690A4/en
Priority to EA201100118A priority patent/EA019547B1/en
Priority to CA2731206A priority patent/CA2731206C/en
Priority to AU2009263091A priority patent/AU2009263091C1/en
Publication of WO2009157781A1 publication Critical patent/WO2009157781A1/en
Priority to IL209952A priority patent/IL209952A/en
Priority to ZA2011/00592A priority patent/ZA201100592B/en

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C39/00—Aircraft not otherwise provided for
    • B64C39/02—Aircraft not otherwise provided for characterised by special use
    • B64C39/026—Aircraft not otherwise provided for characterised by special use for use as personal propulsion unit
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C15/00—Attitude, flight direction, or altitude control by jet reaction
    • B64C15/02—Attitude, flight direction, or altitude control by jet reaction the jets being propulsion jets
    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/20—Rotorcraft characterised by having shrouded rotors, e.g. flying platforms
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/54—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
    • B64C27/56—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement characterised by the control initiating means, e.g. manually actuated
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/54—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
    • B64C27/58—Transmitting means, e.g. interrelated with initiating means or means acting on blades
    • B64C27/59—Transmitting means, e.g. interrelated with initiating means or means acting on blades mechanical
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
    • B64D27/02—Aircraft characterised by the type or position of power plant

Definitions

  • the present invention relates to a vertical take-off and landing personal flight device, i.e. a device which can be secured to the pilot rather like a jet belt, and which gives the pilot controllable powered flight.
  • fuel is fed to a catalyst bed to produce hot gas which is distributed between two spaced counter-rotating turbines to generate vertical thrust from the turbine exhausts.
  • the device is steered by shrouds or deflector rings pivoted to the base of each turbine.
  • ducted fans as their means of propulsion:- for example a device which includes a pair of ducted fans and which is steered by tilting the ducted fans relative to the pilot.
  • a 'shrouded propeller' and a 'ducted fan' essentially is that a ducted fan comprises one or more rotating aerofoils or fans (single or multi-bladed) mounted completely within a duct; the duct increases the overall efficiency of the fan.
  • a shrouded propeller comprises a rotating aerofoil or propeller which is surrounded by a shroud, the only function of the shroud being to protect the propeller - the shroud does not appreciably affect the efficiency of the propeller.
  • a further proposal describes a device which includes a pair of ducted fans.
  • the fans are rigidly secured to the supporting harness, and steering is achieved by control flaps mounted adjacent to the outlet of each fan.
  • control flaps mounted adjacent to the outlet of each fan.
  • the two fans are contra-rotating and thus have to be driven via a gearbox using a relatively complex rigid transmission system; this adds considerable weight to the device.
  • An object of the present invention is a personal flight device which overcomes the disadvantages of the prior art devices described above, and which provides a lightweight yet powerful personal flight device which is comparatively safe to use.
  • the present invention provides a personal flight device which includes:-
  • each fan rotates about an axis of rotation so as to draw air through the corresponding duct from an entry end of the duct to an exit end of the duct;
  • each fan is fixed relative to the housing;
  • one pair of control surfaces being configured to control yaw, one pair of control surfaces being configured to control pitch, and one pair of control surfaces being configured to control roll;
  • control means for controlling the orientation of said control surfaces relative to said fans.
  • each fan may have a separate set of control surfaces (for yaw, pitch and roll) or, if the fans are arranged so that air leaving both or all of the fans on one side of the housing impacts upon a single area (for example if the sets of fans are stacked vertically on each side of the housing) than a single set of control surfaces may be used on each side of the housing.
  • the housing is securable to a pilot by means of a harness, and includes protective shielding between the pilot and the engine and fans.
  • the engine may be any suitable reliable, robust, lightweight engine e.g. a two-stroke or a four-stroke internal combustion engine, rotary engine, or a gas turbine.
  • the drive means may be any reliable lightweight drive means e.g. a chain drive, a fluid drive or a belt drive.
  • the drive means is a flexible belt drive, most preferably a toothed belt drive or a micro-V belt drive.
  • a belt drive is preferred because a belt drive may easily be inspected by a pilot to check for wear or damage, and modern belt drives give a low-weight high-efficiency drive.
  • two or more drive means may be used in parallel.
  • each of the or each pair of control surfaces configured to control yaw is mounted diametrically across the exit end of each duct, being configured to be pivotable about an axis substantially perpendicular to the axis of rotation of the corresponding fan, such that movement of said yaw control surfaces by said control means yaws the device.
  • each of the or each pair of control surfaces configured to control pitch is mounted below the exit end of the corresponding duct, being supported such that in a neutral position when no steering control is applied by said control means, each said control surface lies in a substantially vertical plane; each said control surface being configured to be pivoted about an axis substantially perpendicular to the longitudinal axis of the corresponding fan, such that movement of said pitch control surfaces by said control means pitches the device.
  • each of the or each pair of control surfaces configured to control roll is mounted below the exit end of the corresponding duct, each said control surface being configured to be pivoted about an axis substantially perpendicular to the longitudinal axis of the corresponding fan, such that movement of said roll control surfaces by said control means rolls the device.
  • each of the or each pair of control surfaces configured to control roll is mounted below the exit end of the corresponding duct, with each said control surface being formed as two co-planar vanes mounted one on each side of the corresponding pitch control surface; each said roll control surface being configured to be pivoted about an axis substantially perpendicular to the longitudinal axis of the corresponding fan and substantially perpendicular to the pivot axis of the corresponding pitch control surface, such that movement of said roll control surfaces by said control means rolls the device.
  • Figure 1 is a diagrammatic front view of a device in accordance with the present invention.
  • Figure 2 is a plan view from above of the device of Figure 1 ;
  • Figure 3 is a side view of the device of Figure 1 ;
  • Figure 4 is a view of one ducted fan from below;
  • Figure 5 is a side view of the fan of Figure 4;
  • Figure 6 is a diagram of the drive arrangement
  • FIG. 7 is a diagram of part of the control system
  • Figure 8a and b are diagrams of two different versions of stators
  • Figure 9 is a plan view of a stator of Figure ⁇ b on a larger scale;
  • Figure 10 is a view in the direction of Arrow A of Figure 9;
  • Figure 11 is a plan view from above of one set of pitch/roll controls.
  • a personal flight device 1 includes a pair of ducted fans 2,3 which are supported and spaced apart by a central housing 4, which also supports an engine 6 and a fuel tank (not visible).
  • the ducted fans 2,3 are of known design and consist of a central multi-blade fan 7,8 mounted on, and rotatable with, a hub 7a, 8a, inside a concentric cylindrical duct 9,10.
  • the ducts 9,10 are rigidly mounted on the housing 4 by mounting brackets 4a (visible in Figure. 2 only) and are oriented such that in the "at rest" position shown in Figures 1 and 3, (i.e. when the device is resting on the ground) the axis of rotation of each fan is substantially vertical.
  • the ends of the ducts 9,10 are depicted as open, but may in fact be covered by a protective grill or mesh.
  • the fans 7,8 are driven from the engine 6 by a drive means in the form of a pair of toothed drive belts 11a,11b to the corresponding hub 7a,8a.
  • the toothed belt drive is shown (diagrammatically) in Figures 4 and 6.
  • the engine 6 drives a drive pulley 6a through a flexible coupling 6b, to dampen torsional vibration from the engine 6.
  • Two drive belts 11a,11b are engaged with the drive pulley 6a, one belt alongside the other.
  • the first drive belt 11a passes around the pulley 6a, through an aperture 9b in the duct 9 and around the hub 7a to drive the fan 7.
  • the second drive belt 11b passes around the pulley 6a, through an aperture 10b in the duct 10, and around the hub 8a to drive the fan 8.
  • both fans 7,8 are rotated in the same direction, but the airflow from the bottom 9a, 10a, of each duct 9,10 is made linear (i.e. substantially parallel to the longitudinal axis of the corresponding fan) by the use of a jow of stators 12.
  • the stators 12 are spaced, and extend radially around the inner circumference of each duct 9,10 below the corresponding fan 7,8.
  • Each stator 12 is a 'spoke' which extends radially from the inner wall of the duct towards the hub.
  • FIG 8a shows the simplest arrangement of stators, in which each stator is a flat parallel-sided plate, with the length of each plate extending radially from the inner wall of the duct towards the hub.
  • FIGs 8b,9 and 10 illustrate a more aerodynamically efficient design of stator 12b, in which each stator 12b is a curved aerofoil cross-section plate, one end of which is secured to the inner wall of the duct and the other end of which is secured to the hub. As shown in Figures 9 and 10, each stator 12b twists along its longitudinal axis from the hub to the duct. Stators of this design have a higher efficiency than the simple flat stators 12a, but are more expensive to produce and to fit.
  • the housing 4 is slightly wider than the shoulder width of the pilot, and approximately the same height as the pilot. In the "at rest" position shown in Figures 1 and 3 of the drawings, the device rests on a support 1a which may be of any suitable type.
  • the housing 4 provides head shields 13 and armrests 14,15 ( Figure 1 and 2).
  • the device is provided with controls for controlling yaw, pitch and roll; all of these controls can be operated by the pilot by means of control handles built into the armrests, as described below.
  • Yaw is the angular rotation of the device about a vertical axis; this is controlled by a pair of control vanes 50,51 , one vane in each pair being mounted diametrically across the exit end of each of the ducts 9,10, and arranged to pivot about an axis substantially perpendicular to the axis of rotation of the corresponding fan and hub.
  • Each vane 50,51 has an aerofoil cross-section. Each vane projects partly below the lower edge of the corresponding duct, as shown in Figures 5 and 6, and is made in two sections, one section lying on each side of the lower part of the hub. The two sections of each vane move together as a single unit.
  • the control vanes 50,51 can be moved by cables (not shown) connected to a control lever 17 mounted on the corresponding armrest 14 ( Figure 7).
  • a nonmechanical control system can be used, using, e.g. an electric actuator controlled by movement of the control lever to move the control vanes.
  • the control system is always set so that the movement of one control vane 50 in one direction (e.g. the direction indicated by Arrow A in Figure 7) produces an equal movement of the control vane 51 in the opposite direction (e.g. the direction indicated by Arrow B in Figure 7):- this movement would yaw the device to the left; moving the vanes in the opposite direction would yaw the device to the right.
  • the extent to which the control vanes are moved governs the degree of yaw.
  • Figures 1 and 7 show a single pair of control vanes 50, 51, but it also is possible to use multiple pairs of control vanes 50, 51 , mounted in parallel as shown in Figure 3. The multiple pairs of vanes are used in the same manner as the single pair of vanes.
  • Pitch and roll are governed by aerofoil-cross-section control surfaces 60/61 and 70/71 respectively.
  • Pitch is the angular motion of the device in a vertical plane about a lateral axis; roll is the revolution of the device about a horizontal axis. From the point of view of the pilot of the device, yaw is swinging from side to side about a vertical axis, roll is leaning to one side or the other in a vertical plane, and pitch is leaning forwards or leaning backwards.
  • control surfaces 60/61 and 70/71 are arranged as two sets of control surfaces in a cruciform configuration, with one set 60/70 on one side of the housing and the other set 61/71 on the other side of the housing. Both sets of control surfaces are supported by a support beam 72 which extends at right angles to the longitudinal axis of the device and is mounted across the lower portion of the housing, so that one set of control surfaces lies below the exit end of one duct, and the other set lies below the exit end of the other duct.
  • the control surfaces 60/61 which govern pitch are mounted on the support beam 72, with the longitudinal axis of the surface parallel to that of the support beam 72, and in the neutral position lie in a substantially vertical plane.
  • the control surfaces 60/61 are moved by pivoting the support beam 72 in its bearings (not shown); this movement moves the lower end of the surfaces 60/61 in the directions indicated by the arrows C and D ( Figure 3). If the control surfaces 60/61 move in the direction of Arrow C, the air coming from the exit ends of the ducts 9,10 tends to pitch the device as shown in Figure 3 anticlockwise. If the control surfaces 60/61 move in the direction of Arrow D, the device as shown in Figure 3 is pitched clockwise.
  • surfaces 70/71 move with the surfaces 60/61 , but in the pitching movement described in the preceding paragraph, the surfaces 70/71 remain at a constant angle to the airflow from the ducts and thus do not alter the orientation of the device.
  • the control surfaces 70/71 are each constructed as two equal parts, one on each side of the corresponding surface 60,61.
  • the control surfaces 70/71 can pivot relative to the corresponding surfaces 60/61 as shown in broken lines in Figure 1 ; this pivoting movement is controlled by a control rod 73 which moves the control surfaces 70/71 on bearings 74 mounted on the surfaces 60/61.
  • the control surfaces 70,71 are pivoted in the direction of Arrow E ( Figure 1); to roll the device to the right, the control surfaces 70/71 are pivoted in the direction of Arrow F.
  • the movements of the control surfaces 60/61 , 70/71 are controlled by movements of the control handle 19, mounted on the armrest 15;
  • the armrest 14 also incorporates a twist grip throttle which is connected to the engine 6 and is used to control the acceleration of the engine in known manner.
  • Movements of all of the control surfaces 50/51 , 60/61 and 70/71 , as well as movement of the throttle, may be by means of control cables or rods or using electronic actuators to operate any of a wide range of known hydraulic or electrical servos to act on the control surfaces/throttle.
  • the controls/throttle may be manually controlled by the pilot, or may be remotely controlled via an interface with a microcomputer (the so-called "fly by wire” system).
  • Another possibility is for the device to be primarily manually controlled, but with a safety override provided by computer control, so that if the device is at an unsafe attitude or speed, the override automatically cuts in.
  • the pilot stands in the space 20 ( Figure. 2) and is strapped to the device by means of a parachute type a harness (not shown) which is mounted on the housing 4.
  • a parachute type a harness (not shown) which is mounted on the housing 4.
  • the pilot starts the engine 6 to rotate the fans 7,8 within the ducts 9,10 to give vertical lift to the device.
  • the amount of lift is governed by the acceleration of the engine 6, which is controlled by the throttle. Pitch, roll and yaw are controlled as described above.
  • Rotating both fans 7,8 in the same direction means that the fans can be driven directly from the engine and there is no need for a gearbox to alter the direction of drive. This saves a great deal of additional weight, and also eliminates a component which would need maintenance and be a possible source of failure. Rotating both fans in the same direction would impart torque to the device, making the device difficult or impossible to steer, were it not for the stators which render the airflow leaving the fans 2,3 substantially linear.
  • the device is fitted with a parachute (not shown) which in emergencies can be opened by the pilot to bring the device and the pilot together safely to the ground.
  • a parachute not shown
  • the primary use of the above-described device would be a one-person transport. However, it would be possible to substitute any of a range of remote-control devices for the pilot, and to operate the device remotely.

Abstract

A personal flight device including : a housing securable to the pilot; at least one pair of ducted fans, one fan of each pair mounted to each side of the housing; wherein each fan rotates about an axis of rotation to draw air through the corresponding duct; wherein the axis of rotation of each fan is fixed relative to the housing; at least one engine mounted on the housing for driving the fans, wherein both fans rotate in the same direction for producing thrust; three pairs of control surfaces, with one control surface of each pair mounted below each fan of the one or each pair of fans; such that air leaving said fan impact on said control surface; one pair of control surfaces being configured to control yaw, one pair to control pitch, and one pair to control roll; control means for controlling the orientation of said control surfaces relative to said fans.

Description

PERSONAL FLIGHT VEHICLE INCLUDING CONTROL SYSTEM
Field of the Invention
The present invention relates to a vertical take-off and landing personal flight device, i.e. a device which can be secured to the pilot rather like a jet belt, and which gives the pilot controllable powered flight.
Background of the Invention
It should be noted that any discussion of the prior art throughout the specification is not an admission that such prior art is widely known or forms part of the common general knowledge in the field.
Personal flight devices were developed in the 1960s and 1970s, but were essentially rocket based devices (jet belts) which gave extremely short flight times (typically about 26 seconds) and were difficult to control. Further, these devices were fuelled by rocket fuel which is intrinsically dangerous.
In a related type of device fuel is fed to a catalyst bed to produce hot gas which is distributed between two spaced counter-rotating turbines to generate vertical thrust from the turbine exhausts. The device is steered by shrouds or deflector rings pivoted to the base of each turbine.
More recently, a number of personal flight devices have been proposed which use ducted fans as their means of propulsion:- for example a device which includes a pair of ducted fans and which is steered by tilting the ducted fans relative to the pilot.
A broadly similar type of design has been proposed, using shrouded propellers rather than ducted fans.
As the terms are used in this specification, the distinction between a 'shrouded propeller' and a 'ducted fan' essentially is that a ducted fan comprises one or more rotating aerofoils or fans (single or multi-bladed) mounted completely within a duct; the duct increases the overall efficiency of the fan. A shrouded propeller comprises a rotating aerofoil or propeller which is surrounded by a shroud, the only function of the shroud being to protect the propeller - the shroud does not appreciably affect the efficiency of the propeller.
A further proposal describes a device which includes a pair of ducted fans. In this device, the fans are rigidly secured to the supporting harness, and steering is achieved by control flaps mounted adjacent to the outlet of each fan. However, in this design the two fans are contra-rotating and thus have to be driven via a gearbox using a relatively complex rigid transmission system; this adds considerable weight to the device.
Other prior art proposals have been for single shrouded propellers or ducted fans. Single propeller/fan devices have the drawback that the propeller/fan has to be extremely large to provide adequate lift, and to balance the devices the pilot generally has the propeller/fan above or below him, which is far from ideal from a safety point of view. A further drawback is that the thrust from a single propeller/fan has to be split in some way to give steering and this tends to result in high frictional losses in the steering tubes or ducts.
Summary of Invention
An object of the present invention is a personal flight device which overcomes the disadvantages of the prior art devices described above, and which provides a lightweight yet powerful personal flight device which is comparatively safe to use.
The present invention provides a personal flight device which includes:-
- a housing which is securable to the pilot; - at least one pair of ducted fans, one fan of the pair mounted to one side of the housing, and the other fan of the pair mounted to the other side of the housing;
- wherein each fan rotates about an axis of rotation so as to draw air through the corresponding duct from an entry end of the duct to an exit end of the duct;
- and wherein the axis of rotation of each fan is fixed relative to the housing; - at least one engine mounted on the housing for driving the fans, wherein both fans rotate in the same direction for producing thrust;
- three pairs of control surfaces, with one control surface of each pair mounted below one fan of the one or each pair of fans, and the other control surface of each pair being mounted below the other fan of the or each pair of fans, such that air leaving said fan impact on said control surface;
- one pair of control surfaces being configured to control yaw, one pair of control surfaces being configured to control pitch, and one pair of control surfaces being configured to control roll;
- control means for controlling the orientation of said control surfaces relative to said fans.
It is envisaged that the device probably would use only a single engine and a single pair of fans, since it is important for most applications to keep the overall weight of the device as low as possible. However, it would be possible to use more than one pair of fans, each pair driven by its own engine or both/all pairs driven by a single engine. If more than one pair of fans is used, then, depending upon how the fans are arranged, each fan may have a separate set of control surfaces (for yaw, pitch and roll) or, if the fans are arranged so that air leaving both or all of the fans on one side of the housing impacts upon a single area (for example if the sets of fans are stacked vertically on each side of the housing) than a single set of control surfaces may be used on each side of the housing. Preferably, the housing is securable to a pilot by means of a harness, and includes protective shielding between the pilot and the engine and fans.
The engine may be any suitable reliable, robust, lightweight engine e.g. a two-stroke or a four-stroke internal combustion engine, rotary engine, or a gas turbine.
The drive means may be any reliable lightweight drive means e.g. a chain drive, a fluid drive or a belt drive. Preferably, the drive means is a flexible belt drive, most preferably a toothed belt drive or a micro-V belt drive. A belt drive is preferred because a belt drive may easily be inspected by a pilot to check for wear or damage, and modern belt drives give a low-weight high-efficiency drive. For additional security, two or more drive means may be used in parallel.
Preferably, each of the or each pair of control surfaces configured to control yaw is mounted diametrically across the exit end of each duct, being configured to be pivotable about an axis substantially perpendicular to the axis of rotation of the corresponding fan, such that movement of said yaw control surfaces by said control means yaws the device.
Preferably also, each of the or each pair of control surfaces configured to control pitch is mounted below the exit end of the corresponding duct, being supported such that in a neutral position when no steering control is applied by said control means, each said control surface lies in a substantially vertical plane; each said control surface being configured to be pivoted about an axis substantially perpendicular to the longitudinal axis of the corresponding fan, such that movement of said pitch control surfaces by said control means pitches the device.
Preferably also, each of the or each pair of control surfaces configured to control roll is mounted below the exit end of the corresponding duct, each said control surface being configured to be pivoted about an axis substantially perpendicular to the longitudinal axis of the corresponding fan, such that movement of said roll control surfaces by said control means rolls the device.
Most preferably, each of the or each pair of control surfaces configured to control roll is mounted below the exit end of the corresponding duct, with each said control surface being formed as two co-planar vanes mounted one on each side of the corresponding pitch control surface; each said roll control surface being configured to be pivoted about an axis substantially perpendicular to the longitudinal axis of the corresponding fan and substantially perpendicular to the pivot axis of the corresponding pitch control surface, such that movement of said roll control surfaces by said control means rolls the device.
Brief Description of the Drawings
By way of example only, a preferred embodiment of the present invention is described in detail with reference to the accompanying drawings in which:-
Figure 1 is a diagrammatic front view of a device in accordance with the present invention;
Figure 2 is a plan view from above of the device of Figure 1 ;
Figure 3 is a side view of the device of Figure 1 ;
Figure 4 is a view of one ducted fan from below; Figure 5 is a side view of the fan of Figure 4;
Figure 6 is a diagram of the drive arrangement;
Figure 7 is a diagram of part of the control system;
Figure 8a and b are diagrams of two different versions of stators;
Figure 9 is a plan view of a stator of Figure δb on a larger scale; Figure 10 is a view in the direction of Arrow A of Figure 9; and
Figure 11 is a plan view from above of one set of pitch/roll controls.
Detailed Description of the Invention
Referring to the drawings, a personal flight device 1 includes a pair of ducted fans 2,3 which are supported and spaced apart by a central housing 4, which also supports an engine 6 and a fuel tank (not visible). The ducted fans 2,3 are of known design and consist of a central multi-blade fan 7,8 mounted on, and rotatable with, a hub 7a, 8a, inside a concentric cylindrical duct 9,10. The ducts 9,10 are rigidly mounted on the housing 4 by mounting brackets 4a (visible in Figure. 2 only) and are oriented such that in the "at rest" position shown in Figures 1 and 3, (i.e. when the device is resting on the ground) the axis of rotation of each fan is substantially vertical. The ends of the ducts 9,10 are depicted as open, but may in fact be covered by a protective grill or mesh.
The fans 7,8 are driven from the engine 6 by a drive means in the form of a pair of toothed drive belts 11a,11b to the corresponding hub 7a,8a. The toothed belt drive is shown (diagrammatically) in Figures 4 and 6. As shown in Figure 6, the engine 6 drives a drive pulley 6a through a flexible coupling 6b, to dampen torsional vibration from the engine 6. Two drive belts 11a,11b are engaged with the drive pulley 6a, one belt alongside the other.
The first drive belt 11a passes around the pulley 6a, through an aperture 9b in the duct 9 and around the hub 7a to drive the fan 7. The second drive belt 11b passes around the pulley 6a, through an aperture 10b in the duct 10, and around the hub 8a to drive the fan 8. In use, both fans 7,8 are rotated in the same direction, but the airflow from the bottom 9a, 10a, of each duct 9,10 is made linear (i.e. substantially parallel to the longitudinal axis of the corresponding fan) by the use of a jow of stators 12. The stators 12 are spaced, and extend radially around the inner circumference of each duct 9,10 below the corresponding fan 7,8. Each stator 12 is a 'spoke' which extends radially from the inner wall of the duct towards the hub.
Figure 8a shows the simplest arrangement of stators, in which each stator is a flat parallel-sided plate, with the length of each plate extending radially from the inner wall of the duct towards the hub.
Figures 8b,9 and 10 illustrate a more aerodynamically efficient design of stator 12b, in which each stator 12b is a curved aerofoil cross-section plate, one end of which is secured to the inner wall of the duct and the other end of which is secured to the hub. As shown in Figures 9 and 10, each stator 12b twists along its longitudinal axis from the hub to the duct. Stators of this design have a higher efficiency than the simple flat stators 12a, but are more expensive to produce and to fit. The housing 4 is slightly wider than the shoulder width of the pilot, and approximately the same height as the pilot. In the "at rest" position shown in Figures 1 and 3 of the drawings, the device rests on a support 1a which may be of any suitable type.
The housing 4 provides head shields 13 and armrests 14,15 (Figure 1 and 2).
The device is provided with controls for controlling yaw, pitch and roll; all of these controls can be operated by the pilot by means of control handles built into the armrests, as described below.
Yaw is the angular rotation of the device about a vertical axis; this is controlled by a pair of control vanes 50,51 , one vane in each pair being mounted diametrically across the exit end of each of the ducts 9,10, and arranged to pivot about an axis substantially perpendicular to the axis of rotation of the corresponding fan and hub. Each vane 50,51 has an aerofoil cross-section. Each vane projects partly below the lower edge of the corresponding duct, as shown in Figures 5 and 6, and is made in two sections, one section lying on each side of the lower part of the hub. The two sections of each vane move together as a single unit.
The control vanes 50,51 can be moved by cables (not shown) connected to a control lever 17 mounted on the corresponding armrest 14 (Figure 7). Alternatively, a nonmechanical control system can be used, using, e.g. an electric actuator controlled by movement of the control lever to move the control vanes. The control system is always set so that the movement of one control vane 50 in one direction (e.g. the direction indicated by Arrow A in Figure 7) produces an equal movement of the control vane 51 in the opposite direction (e.g. the direction indicated by Arrow B in Figure 7):- this movement would yaw the device to the left; moving the vanes in the opposite direction would yaw the device to the right. The extent to which the control vanes are moved governs the degree of yaw.
Figures 1 and 7 show a single pair of control vanes 50, 51, but it also is possible to use multiple pairs of control vanes 50, 51 , mounted in parallel as shown in Figure 3. The multiple pairs of vanes are used in the same manner as the single pair of vanes.
Pitch and roll are governed by aerofoil-cross-section control surfaces 60/61 and 70/71 respectively. Pitch is the angular motion of the device in a vertical plane about a lateral axis; roll is the revolution of the device about a horizontal axis. From the point of view of the pilot of the device, yaw is swinging from side to side about a vertical axis, roll is leaning to one side or the other in a vertical plane, and pitch is leaning forwards or leaning backwards.
The control surfaces 60/61 and 70/71 are arranged as two sets of control surfaces in a cruciform configuration, with one set 60/70 on one side of the housing and the other set 61/71 on the other side of the housing. Both sets of control surfaces are supported by a support beam 72 which extends at right angles to the longitudinal axis of the device and is mounted across the lower portion of the housing, so that one set of control surfaces lies below the exit end of one duct, and the other set lies below the exit end of the other duct.
The control surfaces 60/61 which govern pitch are mounted on the support beam 72, with the longitudinal axis of the surface parallel to that of the support beam 72, and in the neutral position lie in a substantially vertical plane. The control surfaces 60/61 are moved by pivoting the support beam 72 in its bearings (not shown); this movement moves the lower end of the surfaces 60/61 in the directions indicated by the arrows C and D (Figure 3). If the control surfaces 60/61 move in the direction of Arrow C, the air coming from the exit ends of the ducts 9,10 tends to pitch the device as shown in Figure 3 anticlockwise. If the control surfaces 60/61 move in the direction of Arrow D, the device as shown in Figure 3 is pitched clockwise.
Because of the cruciform arrangement of the control surfaces, surfaces 70/71 move with the surfaces 60/61 , but in the pitching movement described in the preceding paragraph, the surfaces 70/71 remain at a constant angle to the airflow from the ducts and thus do not alter the orientation of the device.
The control surfaces 70/71 are each constructed as two equal parts, one on each side of the corresponding surface 60,61. The control surfaces 70/71 can pivot relative to the corresponding surfaces 60/61 as shown in broken lines in Figure 1 ; this pivoting movement is controlled by a control rod 73 which moves the control surfaces 70/71 on bearings 74 mounted on the surfaces 60/61. To roll the device to the left, the control surfaces 70,71 are pivoted in the direction of Arrow E (Figure 1); to roll the device to the right, the control surfaces 70/71 are pivoted in the direction of Arrow F.
The movements of the control surfaces 60/61 , 70/71 are controlled by movements of the control handle 19, mounted on the armrest 15;
The armrest 14 also incorporates a twist grip throttle which is connected to the engine 6 and is used to control the acceleration of the engine in known manner.
Movements of all of the control surfaces 50/51 , 60/61 and 70/71 , as well as movement of the throttle, may be by means of control cables or rods or using electronic actuators to operate any of a wide range of known hydraulic or electrical servos to act on the control surfaces/throttle. The controls/throttle may be manually controlled by the pilot, or may be remotely controlled via an interface with a microcomputer (the so-called "fly by wire" system). Another possibility is for the device to be primarily manually controlled, but with a safety override provided by computer control, so that if the device is at an unsafe attitude or speed, the override automatically cuts in.
In use, the pilot stands in the space 20 (Figure. 2) and is strapped to the device by means of a parachute type a harness (not shown) which is mounted on the housing 4. Once strapped in, the pilot starts the engine 6 to rotate the fans 7,8 within the ducts 9,10 to give vertical lift to the device. The amount of lift is governed by the acceleration of the engine 6, which is controlled by the throttle. Pitch, roll and yaw are controlled as described above.
Rotating both fans 7,8 in the same direction means that the fans can be driven directly from the engine and there is no need for a gearbox to alter the direction of drive. This saves a great deal of additional weight, and also eliminates a component which would need maintenance and be a possible source of failure. Rotating both fans in the same direction would impart torque to the device, making the device difficult or impossible to steer, were it not for the stators which render the airflow leaving the fans 2,3 substantially linear.
The device is fitted with a parachute (not shown) which in emergencies can be opened by the pilot to bring the device and the pilot together safely to the ground.
It is envisaged that the primary use of the above-described device would be a one-person transport. However, it would be possible to substitute any of a range of remote-control devices for the pilot, and to operate the device remotely.

Claims

Claims:
1. A personal flight device which includes:-
- a housing which is securable to the pilot; - at least one pair of ducted fans, one fan of the pair mounted to one side of the housing, and the other fan of the pair mounted to the other side of the housing;
- wherein each fan rotates about an axis of rotation so as to draw air through the corresponding duct from an entry end of the duct to an exit end of the duct;
- and wherein the axis of rotation of each fan is fixed relative to the housing; - at least one engine mounted on the housing for driving the fans, wherein both fans rotate in the same direction for producing thrust;
- three pairs of control surfaces, with one control surface of each pair mounted below one fan of the one or each pair of fans, and the other control surface of each pair being mounted below the other fan of the or each pair of fans, such that air leaving said fan impact on said control surface;
- one pair of control surfaces being configured to control yaw, one pair of control surfaces being configured to control pitch, and one pair of control surfaces being configured to control roll;
- control means for controlling the orientation of said control surfaces relative to said fans.
2. The personal flight device as claimed in claim 1 wherein each fan is secured to the housing such that the axis of rotation of each fan is substantially vertical when the device is secured to a pilot standing upright .
3. The personal flight device as claimed in claim 1 of claim 2, wherein the housing includes a protective shielding for shielding the pilot from the engine and fans.
4. The personal flight device as claimed in any one of the preceding claims, wherein the housing includes a harness for securing the device to a pilot.
5. The personal flight device as claimed in any one of the preceding claims wherein the engine is selected from the group consisting of: two-stroke internal combustion engines, four stroke internal combustion engines, rotary engines, gas turbine engines.
6. The personal flight device as claimed in any one of the preceding claims, further including a drive means arranged to be driven by the at least one engine, said drive means being configured to drive the at least one pair of fans.
7. The personal flight device as claimed in claim 6, wherein the drive means comprises a single drive.
8. The personal flight device as claimed in claim 6, wherein the drive means comprises a double drive.
9. The personal flight device as claimed in any one of claims 6 - 8, wherein the drive means includes a drive selected from the group consisting of: chain drives, fluid drives, belt drives.
10. The personal flight device as claimed in any one of the preceding claims, wherein the device further includes a set of stators arranged in each fan duct to straighten the airflow leaving that fan.
11. The personal flight device as claimed in claim 10, wherein the stators of each set have one end secured to an inner wall of the duct and another end secured to a hub of the fan within the duct.
12. The personal flight device as claimed in claim 11 wherein each stator has a curved aerofoil cross-section.
13. The personal flight device as claimed in any one of the preceding claims, wherein each of the or each pair of control surfaces configured to control yaw is mounted diametrically across the exit end of each duct, being configured to be pivotable about an axis substantially perpendicular to the axis of rotation of the corresponding fan, such that movement of said yaw control surfaces by said control means yaws the device.
14. The personal flight device as claimed in claim 13, wherein the or each pair of control surfaces configured to control yaw is configured to be controlled by the control means such that movement of one said control surface in a first direction produces an equal movement of the other control surface in the opposite direction.
15. The personal flight device as claimed in any one of the preceding claims, wherein each of the or each pair of control surfaces configured to control pitch is mounted below the exit end of the corresponding duct, being supported such that in a neutral position when no steering control is applied by said control means, each said control surface lies in a substantially vertical plane; each said control surface being configured to be pivoted about an axis substantially perpendicular to the longitudinal axis of the corresponding fan, such that movement of said pitch control surfaces by said control means pitches the device.
16. The personal flight device as claimed in any one of the preceding claims, wherein each of the or each pair of control surfaces configured to control roll is mounted below the exit end of the corresponding duct, each said control surface being configured to be pivoted about an axis substantially perpendicular to the longitudinal axis of the corresponding fan, such that movement of said roll control surfaces by said control means rolls the device.
17. The personal flight device as claimed in claim 15, wherein each of the or each pair of control surfaces configured to control roll is mounted below the exit end of the corresponding duct, with each said control surface being formed as two co-planar vanes mounted one on each side of the corresponding pitch control surface; each said roll control surface being configured to be pivoted about an axis substantially perpendicular to the longitudinal axis of the corresponding fan and substantially perpendicular to the pivot axis of the corresponding pitch control surface, such that movement of said roll control surfaces by said control means rolls the device.
18. The personal flight device as claimed in any one of claims 13 to 17, wherein each of the said control surfaces is formed as a vane with an aerofoil cross-section.
19. The personal flight device as claimed in any one of the preceding claims, wherein the housing further includes a mounting for a throttle control and controls for said control means.
20. The personal flight device as claimed in any one of the preceding claims wherein said control means is selected from the group consisting of: mechanical control cables; electric actuators; hydraulic actuators.
21. The personal flight device as claimed in any one of the preceding claims wherein the device includes only a single pair of ducted fans and a single engine.
PCT/NZ2009/000075 2008-06-27 2009-05-13 Personal flight vehicle including control system WO2009157781A1 (en)

Priority Applications (10)

Application Number Priority Date Filing Date Title
BRPI0914968A BRPI0914968A2 (en) 2008-06-27 2009-05-13 personal flight vehicle including control system
CN2009801244316A CN102076561A (en) 2008-06-27 2009-05-13 Personal flight vehicle including control system
JP2011516194A JP5510843B2 (en) 2008-06-27 2009-05-13 Personal flying vehicle including control system
US13/001,319 US8695916B2 (en) 2008-06-27 2009-05-13 Personal flight vehicle including control system
EP09770443.1A EP2303690A4 (en) 2008-06-27 2009-05-13 Personal flight vehicle including control system
EA201100118A EA019547B1 (en) 2008-06-27 2009-05-13 Personal flight vehicle including control system
CA2731206A CA2731206C (en) 2008-06-27 2009-05-13 Personal flight vehicle including control system
AU2009263091A AU2009263091C1 (en) 2008-06-27 2009-05-13 Personal flight vehicle including control system
IL209952A IL209952A (en) 2008-06-27 2010-12-13 Personal flight vehicle including control system
ZA2011/00592A ZA201100592B (en) 2008-06-27 2011-01-24 Personal flight vehicle including control system

Applications Claiming Priority (2)

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NZ569454A NZ569454A (en) 2008-06-27 2008-06-27 Propulsion device including control system
NZ569454 2008-06-27

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WO2009157781A1 true WO2009157781A1 (en) 2009-12-30

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EP (1) EP2303690A4 (en)
JP (1) JP5510843B2 (en)
KR (1) KR20110028523A (en)
CN (1) CN102076561A (en)
AU (1) AU2009263091C1 (en)
BR (1) BRPI0914968A2 (en)
CA (1) CA2731206C (en)
EA (1) EA019547B1 (en)
IL (1) IL209952A (en)
NZ (1) NZ569454A (en)
WO (1) WO2009157781A1 (en)
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Families Citing this family (33)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
NZ569455A (en) * 2008-06-27 2009-10-30 Martin Aircraft Company Ltd Propulsion device incorporating radiator cooling passage
JP5920557B2 (en) * 2011-06-30 2016-05-18 株式会社Ihi Vertical take-off and landing aircraft
RU2476920C1 (en) * 2011-09-16 2013-02-27 Открытое акционерное общество "ОКБ Сухого" Multi-task aircraft control data system
US20140103165A1 (en) * 2012-10-09 2014-04-17 Personal Water Craft Product Maneuvering and Stability Control System for Jet-Pack
JP6108077B2 (en) 2013-01-29 2017-04-05 株式会社Ihi Vertical take-off and landing aircraft
CN105283384B (en) * 2013-05-03 2018-03-27 威罗门飞行公司 VTOL (VTOL) aircraft
CN103224024B (en) * 2013-05-17 2015-12-02 谷承露 Two main duct microlight-type vertical takeoff and landing individual lift device
CN103274048B (en) * 2013-06-08 2015-10-28 无锡振华机械有限公司 Can at the aircraft of complex-terrain landing
CN103274044B (en) * 2013-06-08 2015-07-08 无锡振华机械有限公司 Aircraft rudder plate transmission mechanism
ITRM20130473A1 (en) * 2013-08-12 2013-11-11 Unit 1 Srl CONVERTIPLATE WITH NEW TECHNICAL AND AERODYNAMIC SOLUTIONS THAT CAN MAKE THE MEANS ALSO IN SAFE AND ULTRA-LIGHT AIRCRAFT SOLUTIONS
CN103921931A (en) * 2014-04-28 2014-07-16 龙川 Duct wing system and aircraft using same
US9120023B1 (en) * 2014-05-08 2015-09-01 Elizabeth Wales Burroughs Human flying apparatus
JP6456641B2 (en) * 2014-09-29 2019-01-23 国立研究開発法人産業技術総合研究所 Attitude stabilization controller for multi-rotor craft
WO2016112124A2 (en) * 2015-01-08 2016-07-14 Vantage Robotics, Llc Unmanned aerial vehicle with propeller protection and high impact survivability
US10850866B2 (en) * 2015-02-11 2020-12-01 Aerovironment, Inc. Pod cover system for a vertical take-off and landing (VTOL) unmanned aerial vehicle (UAV)
WO2016130721A2 (en) 2015-02-11 2016-08-18 Aerovironment, Inc. Survey migration system for vertical take-off and landing (vtol) unmanned aerial vehicles (uavs)
US11021266B2 (en) 2015-02-11 2021-06-01 Aerovironment, Inc. Pod operating system for a vertical take-off and landing (VTOL) unmanned aerial vehicle (UAV)
US9880563B2 (en) 2015-02-11 2018-01-30 Aerovironment, Inc. Geographic survey system for vertical take-off and landing (VTOL) unmanned aerial vehicles (UAVs)
WO2016130847A1 (en) 2015-02-11 2016-08-18 Aerovironment, Inc. Pod launch and landing system for vertical take-off and landing (vtol) unmanned aerial vehicles (uavs)
KR101718962B1 (en) 2015-06-17 2017-04-04 한국원자력연구원 Apparatus for maintaining flight of flying object
CN105000176A (en) * 2015-08-10 2015-10-28 徐金鹏 Jet aircraft
WO2017083406A1 (en) * 2015-11-10 2017-05-18 Matternet, Inc. Methods and systems for transportation using unmanned aerial vehicles
US10926874B2 (en) * 2016-01-15 2021-02-23 Aurora Flight Sciences Corporation Hybrid propulsion vertical take-off and landing aircraft
US10124880B1 (en) * 2016-02-03 2018-11-13 Lockheed Martin Corporation Rotatable control surface assembly for an unmanned aerial vehicle
EP3416887B1 (en) 2016-02-17 2021-01-27 ARDN Technology Limited Multicopter with different purpose propellers
CN105835038B (en) * 2016-05-19 2017-10-27 成都润惠科技有限公司 One kind can flight ectoskeleton
US10364028B1 (en) * 2017-01-31 2019-07-30 Joshua C. Wilhour Flight system for humans
TWI643790B (en) * 2017-12-06 2018-12-11 林瑤章 Thrust vector controller
GB201802611D0 (en) * 2018-02-17 2018-04-04 Panelplane Ltd Teleporter
US11148805B2 (en) * 2018-04-10 2021-10-19 Government Of The United States, As Represented By The Secretary Of The Army Enclosure for an unmanned aerial system
WO2021000028A1 (en) * 2019-07-03 2021-01-07 Alberto Carlos Pereira Filho Vertical take-off and landing cocoon-type flying vehicle
JP7342250B2 (en) * 2019-10-09 2023-09-11 キティー・ホーク・コーポレーション Hybrid power system for different flight modes
CN114560083A (en) * 2022-04-11 2022-05-31 杭州师范大学 Bee bird imitating type helicopter and flying method thereof

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB268279A (en) * 1926-03-25 1927-04-14 Anton Lutsch
GB900095A (en) * 1958-10-20 1962-07-04 Wilhelm Binder Air-craft having an annular wing and a propulsion means fitted into the latter
WO2002047978A2 (en) * 2000-12-13 2002-06-20 Trek Aerospace, Inc. Aircraft and control system
US20020104919A1 (en) * 2001-01-30 2002-08-08 Nick Geranio Counter rotating ducted fan flying vehicle
US20060196991A1 (en) 2005-03-04 2006-09-07 Martin Glenn N Propulsion device

Family Cites Families (44)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2417896A (en) * 1943-08-10 1947-03-25 Charles H Zimmerman Helicopter flying apparatus
US2461347A (en) * 1945-10-17 1949-02-08 Horace T Pentecost Helicopter adapted to be attached to a pilot
US2955780A (en) * 1958-08-11 1960-10-11 Fluid sustained and fluid propelled flying vehicle
US3023980A (en) * 1958-10-13 1962-03-06 Thompson Ramo Wooldridge Inc Turbo-fan lift device
US3063655A (en) * 1959-08-24 1962-11-13 Skavinsky Anthony Vertical-lift, horizontal flight aircraft
US3184183A (en) * 1962-01-15 1965-05-18 Piasecki Aircraft Corp Flying platform
US3265329A (en) * 1963-08-27 1966-08-09 Postelson Steven Flying platform-automobile-boat and air suspension car combination
US3173629A (en) * 1963-09-13 1965-03-16 Uhor Emil Body attached flying device
US3149799A (en) * 1963-09-19 1964-09-22 Bell Aerospace Corp Individual propulsion
US3494575A (en) * 1966-04-25 1970-02-10 David Budworth Ltd Ground and air vehicles
US3474987A (en) * 1967-07-24 1969-10-28 Ludwig F Meditz Helicopter device
US3556438A (en) * 1969-09-02 1971-01-19 Ludwig F Meditz Airborne vehicle
DE2021043A1 (en) 1970-04-24 1971-11-11 Hans Winkler Aircraft, in particular helicopters with a swiveling drive unit
US3994453A (en) * 1973-06-04 1976-11-30 Firestone Floyd A Method and apparatus for the safe and beautiful solo flight of side-by-side dual-control aircraft from centerplane seat
DE2552888A1 (en) 1975-11-25 1977-06-02 Stefan Bernecker Miniaturised VTOL equipment for 1 or 2 persons - uses ducted multi stage blowers on either side of framework
JPS582706B2 (en) * 1977-09-06 1983-01-18 マブチモ−タ−株式会社 helicopter model equipment
US4379532A (en) * 1980-10-22 1983-04-12 Igor Dmitrowsky Aircraft attachable to the body of a pilot
US4575341A (en) * 1983-08-29 1986-03-11 Bryant Billy O Training apparatus for ultralight aircraft
FR2667568B1 (en) 1990-10-09 1994-05-13 Eugen Vintila INDIVIDUAL POWERED FLIGHT APPARATUS.
DE4302791A1 (en) 1993-02-02 1994-08-04 Juergen Schuster Portable helicopter attachment for lifting single person
US5505407A (en) * 1993-09-09 1996-04-09 Fran Rich Chi Associates Air-land vehicle
US5779188A (en) * 1993-09-21 1998-07-14 Frick; Alexander Flight device
ES2107858T3 (en) * 1993-09-21 1997-12-01 Bil Innovations Stiftung FLYING DEVICE.
RU2135393C1 (en) 1995-02-17 1999-08-27 Николайчук Александр Петрович Individual flying vehicle
CN1203167A (en) * 1997-06-24 1998-12-30 宫晓明 Manned aerobat capable of landing or taking-off vertically
CN2320533Y (en) * 1997-10-30 1999-05-26 黄永吉 Knapsack aircraft
JPH11217099A (en) * 1998-01-30 1999-08-10 Baitekkusu:Kk Aero-carrier
US6293492B1 (en) * 1998-09-02 2001-09-25 Engineering System Co., Ltd. Coaxial twin-rotor type helicopter
CA2354583A1 (en) * 1998-12-11 2000-07-13 Moller International, Inc. Stabilizing control apparatus for robotic or remotely controlled flying platform
US6488232B2 (en) 1998-12-16 2002-12-03 Trek Aerospace, Inc. Single passenger aircraft
US6488504B1 (en) * 1999-10-13 2002-12-03 Scott D. Patterson Helicopter flight training vehicle
US6353789B1 (en) * 1999-12-13 2002-03-05 United Technologies Corporation Predicting broadband noise from a stator vane of a gas turbine engine
FR2809026B1 (en) * 2000-05-18 2003-05-16 Philippe Louvel ELECTRIC FLYING SAUCER, PILOTED AND REMOTELY POWERED
US6848649B2 (en) * 2000-10-03 2005-02-01 Charles Gilpin Churchman V/STOL biplane aircraft
US6464166B1 (en) * 2001-05-29 2002-10-15 Romeo Yankee Ltd. Ducted fan vehicles particularly useful as VTOL aircraft
US6824095B2 (en) * 2001-11-29 2004-11-30 Youbin Mao VSTOL vehicle
JP3861224B2 (en) * 2001-12-07 2006-12-20 有限会社新科学開発研究所 Aerial vehicle
ITTO20020666A1 (en) * 2002-07-26 2004-01-26 Fiat Ricerche VTOL AIRCRAFT
JP4223921B2 (en) * 2003-10-24 2009-02-12 トヨタ自動車株式会社 Vertical take-off and landing flight device
US20050178879A1 (en) * 2004-01-15 2005-08-18 Youbin Mao VTOL tailsitter flying wing
EP1721123A4 (en) * 2004-02-03 2011-01-19 Drag Tag Pty Ltd Vehicle steering sensing apparatus
PL1855941T3 (en) * 2005-03-04 2015-08-31 Martin Aircraft Company Ltd Propulsion device
JP2007118891A (en) * 2005-10-31 2007-05-17 Japan Aerospace Exploration Agency Lift-fan vertical taking-off/landing craft, and its posture and motion control method
NZ569455A (en) * 2008-06-27 2009-10-30 Martin Aircraft Company Ltd Propulsion device incorporating radiator cooling passage

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB268279A (en) * 1926-03-25 1927-04-14 Anton Lutsch
GB900095A (en) * 1958-10-20 1962-07-04 Wilhelm Binder Air-craft having an annular wing and a propulsion means fitted into the latter
WO2002047978A2 (en) * 2000-12-13 2002-06-20 Trek Aerospace, Inc. Aircraft and control system
US20020104919A1 (en) * 2001-01-30 2002-08-08 Nick Geranio Counter rotating ducted fan flying vehicle
US20060196991A1 (en) 2005-03-04 2006-09-07 Martin Glenn N Propulsion device

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See also references of EP2303690A4

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BRPI0914968A2 (en) 2015-10-20
EA019547B1 (en) 2014-04-30
EP2303690A4 (en) 2013-11-27
CA2731206A1 (en) 2009-12-30
KR20110028523A (en) 2011-03-18
AU2009263091B2 (en) 2013-06-27
NZ569454A (en) 2009-10-30
EA201100118A1 (en) 2011-08-30
JP5510843B2 (en) 2014-06-04
CA2731206C (en) 2014-06-03
AU2009263091A1 (en) 2009-12-30
CN102076561A (en) 2011-05-25
JP2011525879A (en) 2011-09-29
AU2009263091C1 (en) 2013-12-12
EP2303690A1 (en) 2011-04-06
IL209952A0 (en) 2011-02-28
US20110133037A1 (en) 2011-06-09
IL209952A (en) 2014-04-30
US8695916B2 (en) 2014-04-15
ZA201100592B (en) 2011-10-26

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