WO1990001002A1 - Helicopter rotor blades - Google Patents

Helicopter rotor blades Download PDF

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Publication number
WO1990001002A1
WO1990001002A1 PCT/AU1989/000311 AU8900311W WO9001002A1 WO 1990001002 A1 WO1990001002 A1 WO 1990001002A1 AU 8900311 W AU8900311 W AU 8900311W WO 9001002 A1 WO9001002 A1 WO 9001002A1
Authority
WO
WIPO (PCT)
Prior art keywords
rotor
disc
blades
rotor arrangement
lift
Prior art date
Application number
PCT/AU1989/000311
Other languages
French (fr)
Inventor
Richard Henry Tollervey
Original Assignee
Richard Henry Tollervey
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 Richard Henry Tollervey filed Critical Richard Henry Tollervey
Publication of WO1990001002A1 publication Critical patent/WO1990001002A1/en

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/003—Variable-diameter propellers; Mechanisms therefor
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/32—Rotors
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/32—Rotors
    • B64C27/46—Blades

Definitions

  • the present invention relates to helicopter rotor blades, and in particular, to improved helicopter rotor blades which provides for high speed flight and vertical take-off and landing capabilities.
  • the object of the present invention is to provide improved helicopter rotor blades which substantially overcomes or ameliorates the abovementioned disadvantages in respect of forward maximum velocity.
  • a rotor arrangement comprising a disc member and a plurality of blades pivotally attached to the periphery of said disc member and extending outwardly from the disc member, wherein the disc member is shaped to produce aerodynamic lift on forward movement of said rotor and the outward extension of said rotor blades is variable.
  • Fig. la is a schematic plan view of a four rotor blade arrangement on a disc with three rotor blades shown in the stowed position and the other shown in an extended position,
  • Fig. lb is a schematic plan view of a six rotor blade arrangement on the disc in a similar layout to that of Fig. la,
  • Fig. 2a is a side view of the four rotor blade arrangement of Fig. la illustrating lift flaps in a raised position
  • Fig. 2b is a side view of the rotor blade layout of Fig. la with the lift flaps closed
  • Fig. 3 is a schematic plan view of the disc with lift flaps closed
  • Fig. 3a is a side view of a disc with flap and duct system with the flaps shown in the raised position
  • Fig. 3b is side view similar to Fig. 3a showing the 11ft flaps closed
  • Fig. 3c is a plan view of the disc of 3a
  • Fig. 3d shows the principle of the duct system of Fig. 3a
  • Fig. 3e shows the duct system in another position
  • Fig. 3f is a Inverse plan view of the disc of Fig. 3a
  • Fig. 4a is a plan view of a rotor blade
  • Fig. 4b is a side view of the rotor blade
  • Fig. 51 s a cross-sectional view of the rotor blade of Fig. 4a
  • Fig. 6 is a side view of the disc of Fig. la with one of the blades in an extended position
  • Fig. 7 is a cross-section of the internal support members of the disc
  • Fig. 8 is a perspective view of the support members of the disc
  • Fig. 9 is a view of an aircraft having the rotor and disc arrangement of the preferred embodiment
  • Fig. 10 illustrates the aircraft in varying operational modes.
  • Fig. 11 Is a schematic plan view of a four rotor blade arrangement of another embodiment with all four rotor blades shown in the stored position
  • Fig. 12 is a side view of the rotor blade arrangement of Fig. 11
  • Fig. 13 is a schematic plan view of the rotor blade arrangement of Fig. 11 showing the four rotor blades in the extended position
  • Fig. 14 is a plan view of the disc showing the four rotor blades in the extended position.
  • Fig. 15 is a perspective view of an aircraft having a pair of discs according to Fig. 1 ,
  • Fig. 16a is a plan view of the aircraft of Fig. 11
  • Fig. 16b is a side view of the aircraft of Fig. 11
  • Fig. 16c is a front view of the aircraft of Fig. 11.
  • BEST MODE OF CARRYING OUT THE INVENTION The rotor arrangement 1 of two preferred embodiments are illustrated in Figs, la and lb.
  • the rotor arrangement 1 comprises a disc 2 with four and six rotor blades 3 respectively. In Figs, la and lb, only one of the rotor blades is shown in the extended position whereby the rest of the rotor blades 3 are shown in the stowed position.
  • the rotor blades 3 are hinged and are pivotable about a hinge 10.
  • the rotor blades 3 are able to be locked in position.
  • the locking mechanism is not illustrated.
  • the rotor blade 3 is illustrated in Figs. 4 and 5. As seen in F1g. 4a, the rotor blades 3 are crescent shaped and when extended the blades 3 are at right angles to the disc 2.
  • the shape of the rotor blade 3 is illustrated 1n Fig. 5 having a leading edge 11 and a trailing edge 12, and has a typical aerofoil cross-section.
  • rotor arrangement 1 1s illustrated.
  • rotor blades 3 on a disc 2.
  • FIG. 3 are shown In the stowed position.
  • the lift flaps 4 Positioned on the upper side of the disc 2.
  • the lift flaps 4 have a hinge edge 5 and a raising edge 6.
  • the lift flaps 4 are able to be raised for lift of the rotor arrangement 1.
  • Fig. 2a the 11ft flaps 4 are raised to 20° against the air-flow whilst in Fig. 2b the lift flaps 4 are closed.
  • W Illustrates the direction of air flow whilst in Fig. 3, E illustrates the direction of rotation of the rotor arrangement 1.
  • Figs. 3a, 3b and 3c illustrate another embodiment of a system to obtain extra 11ft for the disc 2. In this system the lift flaps 4 are raised when extra lift is required and inclined into the direction of air flow.
  • the raised flaps 4 forces air down ducts 8 and out through the base 9 of the disc 2. This movement of air produces lift and the flaps are able to be raised to different angles of incidence to the direction of travel for varying degress of lift.
  • Fig. 3a the flaps 4 are shown in the raised position and inclined to the air flow W whilst in Fig. 3b the flaps
  • F1g. 3d shows the principle of the lift duct system in greater detail, whereby the figures 1s a cross-section of the disc at a duct 8.
  • the flap 4 is illustrated in the closed position in Fig. 3d and a sliding panel 13 is also shown in the closed position.
  • the sliding panel 13 is shown in the open position with the flap 4 in a raised position.
  • the base of the disc 9 is Illustrated in Fig. 3f with sliding panels 13 illustrated in their closed position.
  • Figs. 7 and 8 Illustrated in Figs. 7 and 8 is the internal support member 14 which in Fig. 8 has three separate beams 15 which are connected at a middle point 16. This particular support member 14 is used for a six blade rotor arrangement. At the ends of the beams 15 the hinge 10 for the rotor blade 3 1s located. The beams 15 provide the strength for the structure of the rotor arrangement 1.
  • Figs. 9 and 10 Illustrated in Figs. 9 and 10, is an aircraft 20 having the rotor arrangement 1 with ducted flap system applied to its fuselage 21 which also has a pair of jet motors 22 applied to the sides thereof.
  • the rotor blades 3 are extended in Fig. 9 for vertical take-off of the aircraft 20.
  • the lift flaps 4 in the vertical take-off configuration A are raised.
  • in configuration B the rotor blades 3 are stowed and the lift flaps 4 are 1n their raised position. Whilst in configuration
  • the rotor blades 3 are extended and the rotor arrangement 1 is rotated to thereby lift the aircraft 20.
  • the flaps 4 are in the raised position.
  • the angle of the rotor arrangement 1 to the direction of travel is varied and thrust from the main engines makes the aircraft begin to travel in a forward direction 1n a conventional manner of helicopters or the like.
  • the rotor blades 3 are retracted and locked into the stowed position whilst the lift flaps 4 are raised on the disc 2 in a transitional mode to maintain lift.
  • the flaps 4 are able to be lowered to the closed position and the aircraft 20 is able to continue at this fast speed.
  • the rotor blades have the same curvature as the disc edge when stowed and therefore offer no wind resistance or drag.
  • the shape of the disc 2 is that of an inverted saucer with a convex top and flat underside. When rotated and propelled forward 1t creates lift. The extra 11ft required during flight is obtained by the lift flaps 4 which induce drag but increase lift.
  • rotor blades 3 will be able to be locked in any position from fully extended to the stowed position for varying the degrees of lift for flight requirements.
  • FIG. 15 and 16 Illustrated in Figs. 15 and 16 is another aircraft 30 having a pair of discs 2 which operate in a similar method to those of aircraft 20.
  • the aircraft 30 has more vertical lift potential and is designed to provide extra lift when travelling forward by the shape and location of fuel tanks 31 located on the lower sides of its fuselage 32.
  • the engines 33 are used to power the aircraft 30.
  • Illustrated in Figs. 11 to 14 is another embodiment of the rotor blades.
  • the rotor blades 51 have a typical aerofoil cross-section and are substantially straight in the longitudinal axis.
  • the rotor blades 52 are attached at the inside end to a one sided elongate rack apparatus 52.
  • the rack has gears 54 which mate with a geared wheel 53 which is fixed to the disc 55 by an axle 56. As the geared wheel 53 is rotated the rotor blades 52 travel inwardly or outwardly from the periphery of the disc 55.
  • Figs. 11 to 13 The various positions of the rotor blades 51 are illustrated in Figs. 11 to 13. In Figs. 11 and 12 the blades 51 are stored in the positions while in Fig. 13 the blades 52 are shown in the extended position. In Fig. 14 the blades 52 are shown in conjunction with the rotor disc having the duct system of the preferred embodiment. The use of the rotor blade apparatus of this embodiment is similar to the first embodiment described.

Abstract

A rotor blade arrangement for an aircraft comprises a disc member (2) and a plurality of blades (3) which are extendable outwardly from the periphery of the disc member (2). Both the disc member (2) and blades (3) are shaped aerodynamically to provide aerodynamic lift of the aircraft during travel. The outward extension of the rotor blades (3) is variable.

Description

HELICOPTER ROTOR BLADES
The present invention relates to helicopter rotor blades, and in particular, to improved helicopter rotor blades which provides for high speed flight and vertical take-off and landing capabilities. BACKGROUND ART
It has been found in practice that helicopters, although they have vertical take-off and landing capabilities, with conventional rotor blades their forward maximum velocity is approximately 400 to 500 kilometres per hour. This forward maximum velocity limitation is due to rotor blades cavitation, the fact that the rotor blade tips reach the sound barrier causing shock waves and loss of lift on the retreating blades, which all cause instability at speeds higher than this limitation.
OBJECT OF THE INVENTION The object of the present invention is to provide improved helicopter rotor blades which substantially overcomes or ameliorates the abovementioned disadvantages in respect of forward maximum velocity.
DISCLOSURE OF THE INVENTION According to one aspect of the present invention there is disclosed a rotor arrangement comprising a disc member and a plurality of blades pivotally attached to the periphery of said disc member and extending outwardly from the disc member, wherein the disc member is shaped to produce aerodynamic lift on forward movement of said rotor and the outward extension of said rotor blades is variable.
BRIEF DESCRIPTION OF THE DRAWINGS According to another aspect of the present invention there is disclosed an aircraft having a rotor as described above.
Some embodiments of the present invention will now be described with reference to the drawings in which:
Fig. la is a schematic plan view of a four rotor blade arrangement on a disc with three rotor blades shown in the stowed position and the other shown in an extended position,
Fig. lb is a schematic plan view of a six rotor blade arrangement on the disc in a similar layout to that of Fig. la,
Fig. 2a is a side view of the four rotor blade arrangement of Fig. la illustrating lift flaps in a raised position,
Fig. 2b is a side view of the rotor blade layout of Fig. la with the lift flaps closed,
Fig. 3 is a schematic plan view of the disc with lift flaps closed, Fig. 3a is a side view of a disc with flap and duct system with the flaps shown in the raised position,
Fig. 3b is side view similar to Fig. 3a showing the 11ft flaps closed, Fig. 3c is a plan view of the disc of 3a,
Fig. 3d shows the principle of the duct system of Fig. 3a, Fig. 3e shows the duct system in another position, Fig. 3f is a Inverse plan view of the disc of Fig. 3a, Fig. 4a is a plan view of a rotor blade, Fig. 4b is a side view of the rotor blade,
Fig. 51s a cross-sectional view of the rotor blade of Fig. 4a, Fig. 6 is a side view of the disc of Fig. la with one of the blades in an extended position,
Fig. 7 is a cross-section of the internal support members of the disc,
Fig. 8 is a perspective view of the support members of the disc, Fig. 9 is a view of an aircraft having the rotor and disc arrangement of the preferred embodiment,
Fig. 10 illustrates the aircraft in varying operational modes. Fig. 11 Is a schematic plan view of a four rotor blade arrangement of another embodiment with all four rotor blades shown in the stored position, Fig. 12 is a side view of the rotor blade arrangement of Fig. 11, Fig. 13 is a schematic plan view of the rotor blade arrangement of Fig. 11 showing the four rotor blades in the extended position, Fig. 14 is a plan view of the disc showing the four rotor blades in the extended position.
Fig. 15 is a perspective view of an aircraft having a pair of discs according to Fig. 1 ,
Fig. 16a is a plan view of the aircraft of Fig. 11, Fig. 16b is a side view of the aircraft of Fig. 11, and Fig. 16c is a front view of the aircraft of Fig. 11. BEST MODE OF CARRYING OUT THE INVENTION The rotor arrangement 1 of two preferred embodiments are illustrated in Figs, la and lb. The rotor arrangement 1 comprises a disc 2 with four and six rotor blades 3 respectively. In Figs, la and lb, only one of the rotor blades is shown in the extended position whereby the rest of the rotor blades 3 are shown in the stowed position. The rotor blades 3 are hinged and are pivotable about a hinge 10. The rotor blades 3 are able to be locked in position. The locking mechanism is not illustrated. The rotor blade 3 is illustrated in Figs. 4 and 5. As seen in F1g. 4a, the rotor blades 3 are crescent shaped and when extended the blades 3 are at right angles to the disc 2. The shape of the rotor blade 3 is illustrated 1n Fig. 5 having a leading edge 11 and a trailing edge 12, and has a typical aerofoil cross-section.
In Fig. 2, one embodiment of the rotor arrangement 1 1s illustrated. There are four rotor blades 3 on a disc 2. The rotor blades
3 are shown In the stowed position. There are four lift flaps 4. Positioned on the upper side of the disc 2. The lift flaps 4 have a hinge edge 5 and a raising edge 6. The lift flaps 4 are able to be raised for lift of the rotor arrangement 1. In Fig. 2a, the 11ft flaps 4 are raised to 20° against the air-flow whilst in Fig. 2b the lift flaps 4 are closed. W Illustrates the direction of air flow whilst in Fig. 3, E illustrates the direction of rotation of the rotor arrangement 1. Figs. 3a, 3b and 3c illustrate another embodiment of a system to obtain extra 11ft for the disc 2. In this system the lift flaps 4 are raised when extra lift is required and inclined into the direction of air flow. The raised flaps 4 forces air down ducts 8 and out through the base 9 of the disc 2. This movement of air produces lift and the flaps are able to be raised to different angles of incidence to the direction of travel for varying degress of lift. In Fig. 3a, the flaps 4 are shown in the raised position and inclined to the air flow W whilst in Fig. 3b the flaps
4 are closed.
F1g. 3d shows the principle of the lift duct system in greater detail, whereby the figures 1s a cross-section of the disc at a duct 8. The flap 4 is illustrated in the closed position in Fig. 3d and a sliding panel 13 is also shown in the closed position. In Fig. 3e, the sliding panel 13 is shown in the open position with the flap 4 in a raised position. The base of the disc 9 is Illustrated in Fig. 3f with sliding panels 13 illustrated in their closed position.
Illustrated in Figs. 7 and 8 is the internal support member 14 which in Fig. 8 has three separate beams 15 which are connected at a middle point 16. This particular support member 14 is used for a six blade rotor arrangement. At the ends of the beams 15 the hinge 10 for the rotor blade 3 1s located. The beams 15 provide the strength for the structure of the rotor arrangement 1.
Illustrated in Figs. 9 and 10, is an aircraft 20 having the rotor arrangement 1 with ducted flap system applied to its fuselage 21 which also has a pair of jet motors 22 applied to the sides thereof. The rotor blades 3 are extended in Fig. 9 for vertical take-off of the aircraft 20. The lift flaps 4 in the vertical take-off configuration A are raised. In Fig. 10, in configuration B, the rotor blades 3 are stowed and the lift flaps 4 are 1n their raised position. Whilst in configuration
C both the rotor blades 3 and the lift flaps 4 are stowed and closed.
In operation, for vertical take-off of the aircraft 20, the rotor blades 3 are extended and the rotor arrangement 1 is rotated to thereby lift the aircraft 20. During vertical take-off, the flaps 4 are in the raised position. Once the aircraft 20 has obtained a certain altitude, the angle of the rotor arrangement 1 to the direction of travel is varied and thrust from the main engines makes the aircraft begin to travel in a forward direction 1n a conventional manner of helicopters or the like. Once a desired speed has been obtained,the rotor blades 3 are retracted and locked into the stowed position whilst the lift flaps 4 are raised on the disc 2 in a transitional mode to maintain lift. Once the aircraft 20 has reached a desired fast forward speed mode the flaps 4 are able to be lowered to the closed position and the aircraft 20 is able to continue at this fast speed. The rotor blades have the same curvature as the disc edge when stowed and therefore offer no wind resistance or drag. The shape of the disc 2 is that of an inverted saucer with a convex top and flat underside. When rotated and propelled forward 1t creates lift. The extra 11ft required during flight is obtained by the lift flaps 4 which induce drag but increase lift. It is envisage that the drive, disc control and blade control (pitch control) etc are conventional and that when the rotor blades 3 are stowed, the propulsion of the aircraft 20 is obtained by the thrust of the lift disc drive engine and/or from the extra jet engines 22 on the fuselage 21 of the aircraft 20. It is a matter of what configuration depth suits the particular requirements of an aircraft.
It is envisage that rotor blades 3 will be able to be locked in any position from fully extended to the stowed position for varying the degrees of lift for flight requirements.
Illustrated in Figs. 15 and 16 is another aircraft 30 having a pair of discs 2 which operate in a similar method to those of aircraft 20. The aircraft 30 has more vertical lift potential and is designed to provide extra lift when travelling forward by the shape and location of fuel tanks 31 located on the lower sides of its fuselage 32. The engines 33 are used to power the aircraft 30. Illustrated in Figs. 11 to 14 is another embodiment of the rotor blades. In this embodiment the rotor blades 51 have a typical aerofoil cross-section and are substantially straight in the longitudinal axis. The rotor blades 52 are attached at the inside end to a one sided elongate rack apparatus 52. The rack has gears 54 which mate with a geared wheel 53 which is fixed to the disc 55 by an axle 56. As the geared wheel 53 is rotated the rotor blades 52 travel inwardly or outwardly from the periphery of the disc 55.
The various positions of the rotor blades 51 are illustrated in Figs. 11 to 13. In Figs. 11 and 12 the blades 51 are stored in the positions while in Fig. 13 the blades 52 are shown in the extended position. In Fig. 14 the blades 52 are shown in conjunction with the rotor disc having the duct system of the preferred embodiment. The use of the rotor blade apparatus of this embodiment is similar to the first embodiment described.
The foregoing describes only some embodiments of the present invention, and modifications obvious to those skilled in the art can be made thereto without departing from the scope of the present invention.

Claims

1. A rotor arrangement comprising a disc member and a plurality of blades pivotally attached to the periphery of said disc member and extending outwardly from said disc member, wherein the disc member is shaped to produce aerodynamic lift on forward movement of said rotor and the outward extension of said rotor blades is variable.
2. The rotor arrangement as claimed in claim 1 wherein said plurality of blades are able to be locked in a plurality of positions from the fully extended position to a stowed position, wherein the fully extended position is substantially 90° outwardly from a tangent of said disc member, and the stowed position is substantially adjacent said disc.
3. The rotor arrangement as claimed 1n claim 1 or 2 wherein the said plurality of blades are shaped aerodynamically for lift and have longitudi¬ nal axes which are substantially arcuate in shape.
4. The rotor arrangement as claimed in claim 3 wherein said plurality of rotor blades have longitudinal axes which are substantially straight.
5. The rotor arrangement as claimed in claim 4 wherein said plurality of blades are movable in a radially outward direction.
6. The rotor arrangement as claimed in claim 5 wherein a greared rack cooperates with a rotational geared means to move said plurality of blades simultaneously.
7. The rotor arrangement as claimed in any one of the preceding claims wherein said disc is a circular member having a substantially convex top side and a substantially flat base, and provides a housing for said plurality of rotor blades, and produces lift by its rotation, when travelling in a forward direction.
8. The rotor arrangement as claimed in any one of the preceding claims wherein said disc further comprises a plurality of flap means to provide for extra lift of said rotor arrangement when said arrangement travelling in a forward direction.
9. The rotor arrangement as claimed in any one of the preceding claims wherein said flap means comprises a plurality of aerodynamically shaped members radiating outwardly from the centre of the disc wherein as said disc rotates air-flow is forced over the flaps inducing drag and lift of the rotor arrangement.
10. The rotor arrangement as claimed in claim 6 wherein said flap means further comprising a duct system associated with said flap to provide for extra lift.
11. An aircraft having a fuselage having at least one rotor arrangement as claimed in any one of the preceding claims.
PCT/AU1989/000311 1988-07-27 1989-07-24 Helicopter rotor blades WO1990001002A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
AU20045/88 1988-07-27
AU20045/88A AU587363B1 (en) 1988-07-27 1988-07-27 Improvements to helicopter rotor blades

Publications (1)

Publication Number Publication Date
WO1990001002A1 true WO1990001002A1 (en) 1990-02-08

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Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5473060A (en) * 1993-07-02 1995-12-05 Lynx Therapeutics, Inc. Oligonucleotide clamps having diagnostic applications
US5543390A (en) * 1990-11-01 1996-08-06 State Of Oregon, Acting By And Through The Oregon State Board Of Higher Education, Acting For And On Behalf Of The Oregon Health Sciences University Covalent microparticle-drug conjugates for biological targeting
US5827819A (en) * 1990-11-01 1998-10-27 Oregon Health Sciences University Covalent polar lipid conjugates with neurologically active compounds for targeting
US5830658A (en) * 1995-05-31 1998-11-03 Lynx Therapeutics, Inc. Convergent synthesis of branched and multiply connected macromolecular structures
WO2001056879A1 (en) * 2000-02-01 2001-08-09 Simicon As Device by a horizontally and vertically flying aircraft
FR3031958A1 (en) * 2015-01-23 2016-07-29 Franck Andre-Marie Guigan VARIABLE GEOMETRY PROPELLER
WO2017165456A1 (en) * 2016-03-23 2017-09-28 Amazon Technologies, Inc. Coaxially aligned propellers of an aerial vehicle
US10399666B2 (en) 2016-03-23 2019-09-03 Amazon Technologies, Inc. Aerial vehicle propulsion mechanism with coaxially aligned and independently rotatable propellers
WO2019202493A1 (en) * 2018-04-18 2019-10-24 Vondrasek Vaclav A rotating uplift and carrier disk for vertical take-off and landing and also for forward flight, the mode of flight and its use
US10526070B2 (en) 2016-03-23 2020-01-07 Amazon Technologies, Inc. Aerial vehicle propulsion mechanism with coaxially aligned propellers
US10583914B2 (en) 2016-03-23 2020-03-10 Amazon Technologies, Inc. Telescoping propeller blades for aerial vehicles
US10723440B2 (en) 2016-03-23 2020-07-28 Amazon Technologies, Inc. Aerial vehicle with different propeller blade configurations
US11286037B2 (en) 2018-10-12 2022-03-29 Textron Innovations Inc. Ducted rotor blade tip extension
US11286036B2 (en) 2018-10-12 2022-03-29 Textron Innovations Inc. Ducted rotor blade tip extension
US11305874B2 (en) 2016-03-23 2022-04-19 Amazon Technologies, Inc. Aerial vehicle adaptable propeller blades
US11565799B2 (en) 2020-06-12 2023-01-31 Textron Innovations Inc. Adjustable ducted rotor blade tip extension

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1521047A (en) * 1924-05-22 1924-12-30 John H Reynolds Flying machine
US1961996A (en) * 1932-03-02 1934-06-05 Selden T Williams Airplane construction
US2020235A (en) * 1933-01-26 1935-11-05 Bradbury John Hinchcliffe Rotor screw suitable for helicopters
US2036011A (en) * 1934-05-14 1936-03-31 Carl A Barrett Aircraft
US2604950A (en) * 1946-04-23 1952-07-29 Charles O Sipe Helicopter rotor
FR1085378A (en) * 1953-02-02 1955-02-02 Rotary wing aircraft
GB797019A (en) * 1954-11-30 1958-06-25 Georges Libert Ghislain Marie Improvements relating to aircraft
DE1936123A1 (en) * 1969-07-16 1971-01-28 Friedrich Fricke Lens rotor

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
AU412346B2 (en) * 1968-03-08 1971-04-15 Thomas Hupf Martin Aircraft
AU512179B2 (en) * 1976-09-28 1980-09-25 J. F Wallace Autogyros
CA1161413A (en) * 1980-10-10 1984-01-31 Roderick A. Maclennan Automatic lock-positioning of foldable helicopter blades

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1521047A (en) * 1924-05-22 1924-12-30 John H Reynolds Flying machine
US1961996A (en) * 1932-03-02 1934-06-05 Selden T Williams Airplane construction
US2020235A (en) * 1933-01-26 1935-11-05 Bradbury John Hinchcliffe Rotor screw suitable for helicopters
US2036011A (en) * 1934-05-14 1936-03-31 Carl A Barrett Aircraft
US2604950A (en) * 1946-04-23 1952-07-29 Charles O Sipe Helicopter rotor
FR1085378A (en) * 1953-02-02 1955-02-02 Rotary wing aircraft
GB797019A (en) * 1954-11-30 1958-06-25 Georges Libert Ghislain Marie Improvements relating to aircraft
DE1936123A1 (en) * 1969-07-16 1971-01-28 Friedrich Fricke Lens rotor

Cited By (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6024977A (en) * 1990-11-01 2000-02-15 Oregon Health Sciences University Covalent polar lipid conjugates with neurologically active compounds for targeting
US5543390A (en) * 1990-11-01 1996-08-06 State Of Oregon, Acting By And Through The Oregon State Board Of Higher Education, Acting For And On Behalf Of The Oregon Health Sciences University Covalent microparticle-drug conjugates for biological targeting
US5543391A (en) * 1990-11-01 1996-08-06 State Of Oregon, Acting By And Through The Oregon State Board Of Higher Education, Acting For And On Behalf Of The Oregon Health Sciences University Covalent microparticle-drug conjugates for biological targeting
US6436437B1 (en) 1990-11-01 2002-08-20 Oregon Health And Science University Covalent polar lipid conjugates with neurologically active compounds for targeting
US6339060B1 (en) 1990-11-01 2002-01-15 Oregon Health & Science University Conjugate of biologically active compound and polar lipid conjugated to a microparticle for biological targeting
US5827819A (en) * 1990-11-01 1998-10-27 Oregon Health Sciences University Covalent polar lipid conjugates with neurologically active compounds for targeting
US6858582B2 (en) 1990-11-01 2005-02-22 Oregon Health And Sciences University Composition containing porous microparticle impregnated with biologically-active compound for treatment of infection
US5840674A (en) * 1990-11-01 1998-11-24 Oregon Health Sciences University Covalent microparticle-drug conjugates for biological targeting
US5473060A (en) * 1993-07-02 1995-12-05 Lynx Therapeutics, Inc. Oligonucleotide clamps having diagnostic applications
US6048974A (en) * 1993-07-02 2000-04-11 Lynx Therapeutics, Inc. Oligonucleotide clamps having diagnostic and therapeutic applications
US5817795A (en) * 1993-07-02 1998-10-06 Lynx Therapeutics, Inc. Oligonucleotide clamps having diagnostic and therapeutic applications
US5741643A (en) * 1993-07-02 1998-04-21 Lynx Therapeutics, Inc. Oligonucleotide clamps
US7423010B2 (en) 1994-05-19 2008-09-09 Oregon Health & Science University Nonporous microparticle-prodrug conjugates for treatment of infection
US5830658A (en) * 1995-05-31 1998-11-03 Lynx Therapeutics, Inc. Convergent synthesis of branched and multiply connected macromolecular structures
WO2001056879A1 (en) * 2000-02-01 2001-08-09 Simicon As Device by a horizontally and vertically flying aircraft
FR3031958A1 (en) * 2015-01-23 2016-07-29 Franck Andre-Marie Guigan VARIABLE GEOMETRY PROPELLER
WO2017165456A1 (en) * 2016-03-23 2017-09-28 Amazon Technologies, Inc. Coaxially aligned propellers of an aerial vehicle
US10399666B2 (en) 2016-03-23 2019-09-03 Amazon Technologies, Inc. Aerial vehicle propulsion mechanism with coaxially aligned and independently rotatable propellers
US10526070B2 (en) 2016-03-23 2020-01-07 Amazon Technologies, Inc. Aerial vehicle propulsion mechanism with coaxially aligned propellers
US10583914B2 (en) 2016-03-23 2020-03-10 Amazon Technologies, Inc. Telescoping propeller blades for aerial vehicles
US10723440B2 (en) 2016-03-23 2020-07-28 Amazon Technologies, Inc. Aerial vehicle with different propeller blade configurations
US11305874B2 (en) 2016-03-23 2022-04-19 Amazon Technologies, Inc. Aerial vehicle adaptable propeller blades
WO2019202493A1 (en) * 2018-04-18 2019-10-24 Vondrasek Vaclav A rotating uplift and carrier disk for vertical take-off and landing and also for forward flight, the mode of flight and its use
US11286037B2 (en) 2018-10-12 2022-03-29 Textron Innovations Inc. Ducted rotor blade tip extension
US11286036B2 (en) 2018-10-12 2022-03-29 Textron Innovations Inc. Ducted rotor blade tip extension
US11565799B2 (en) 2020-06-12 2023-01-31 Textron Innovations Inc. Adjustable ducted rotor blade tip extension

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