GB2403460A - Vertical take off rotating wing aircraft - Google Patents

Vertical take off rotating wing aircraft Download PDF

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Publication number
GB2403460A
GB2403460A GB0315325A GB0315325A GB2403460A GB 2403460 A GB2403460 A GB 2403460A GB 0315325 A GB0315325 A GB 0315325A GB 0315325 A GB0315325 A GB 0315325A GB 2403460 A GB2403460 A GB 2403460A
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GB
United Kingdom
Prior art keywords
aircraft
rotor
aerofoil section
attack
varied
Prior art date
Legal status (The legal status 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 status listed.)
Withdrawn
Application number
GB0315325A
Other versions
GB0315325D0 (en
Inventor
Reginald John Atherton
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Individual
Original Assignee
Individual
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 Individual filed Critical Individual
Priority to GB0315325A priority Critical patent/GB2403460A/en
Publication of GB0315325D0 publication Critical patent/GB0315325D0/en
Publication of GB2403460A publication Critical patent/GB2403460A/en
Withdrawn legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C39/00—Aircraft not otherwise provided for
    • B64C39/003—Aircraft not otherwise provided for with wings, paddle wheels, bladed wheels, moving or rotating in relation to the fuselage
    • B64C39/005—Aircraft not otherwise provided for with wings, paddle wheels, bladed wheels, moving or rotating in relation to the fuselage about a horizontal transversal axis
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
    • B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
    • B64C29/0016—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers
    • B64C29/0025—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers the propellers being fixed relative to the fuselage

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Wind Motors (AREA)

Abstract

An aircraft includes at least one elongate rotor having a rotational axis extending laterally to the fuselage 5 of the aircraft. The rotor comprises a plurality of aerofoil section blades 2 spaced equidistantly circumferentially and disposed equidistantly from and rotating around its rotational axis. The aerofoil section blades 2 are interconnected so that their angle of attack is varied with circumferential position about the axis of the rotor and are symmetric about their chord lines. The aircraft may include a further rotor, so that the two rotors having a common axis are disposed either side of the fuselage. The blades 2 may have their attitude controlled by actuator rods in order to obtain four different modes of flight, namely; lift, thrust, lift with thrust and a fixed gliding mode. A tail rotor 4 may be provided at the rear of the fuselage 5.

Description

Vertical Take OffRotatina Wing Aircraft Conventional helicopters typically
fly at maximum speeds of 200 mph and suffer this maximum limit because the airfoil tips cannot exceed mach I without shattering. Coupled with this they suffer from an assymetric lift lift distribution caused by some rotor blades moving up- wind & some downward this is obviated by the use of a rather complicated 'swash plate' and forward propulsion is obtained by tilting the plane of the main rotor yawing control by means of a vertical tail rotor.
This invention eliminates the assymetric lift distribution problem and although the airfoil sections are inhibited by mach. I it is anticipated that speeds of approx twice that of a conventional helicopter will be attainable. The machine is capable of vertical take off& a fixed wing configuration.
Fig. 1. shows 4 symetrical airfoil sections. Rotating about a common centre C0 the 2 sections(2) at 6 o'clock & 12 o'clock are inclined to the horizontal at a small angle & generate lift. The 2 sections(2) at 3 o'clock & 9 o'clock are both vertical and generate neither lift nor thrust. This is the vertical take off mode. The attitude ofthe 4 airfoils shown is controlled by 4 actuator rods (1) which are shown centred about Cl, C2 is an intermediate modal centre which generates both lift and thrust. C3 is that mode generating max. forward speed and C4 is the fixed wing gliding configuration.
Fig. 2. shows a typical configuration of the complete airplane 2 rotor units are disposed about a fuselage (5) which supports a horizontal tail rotor (4).
Inherent stability in roll is provided by the rotor units being inclined above the horizontal.
Control in roll is provided by independent power supply to left & right units. Control in yaw is provided by the attitude rods (1) Fig 1. pitch control is by means ofthe tail rotor unit (4) Fig 2.
Some means of controlling & reducing wing tip drag is considered essential though not shown.

Claims (4)

  1. Claims 1. An aircraft, including at least one elongate rotor having a
    rotational axis extending equidistant laterally of the body of the aircraft, the elongate rotor comprises a plurality of aerofoil section blades spaced equidistant radially and disposed equidistant from and connected to the elongate rotors rotational axis, the aerofoil section blades are interconnected in such a manner so that in use their angle of attack is varied dependent upon their radial position about the rotational axis of the elongate rotor and the aerofoil sections are symmetrical about their own chord lines.
  2. 2. An aircraft as claimed in claim 1, including a further elongate rotor, the two rotors having a common rotational axis and located laterally either side of the body of the aircraft.
  3. 3. An aircraft as claimed in any previous claim, having at least four modes of operation, the first mode where the angle of attack of the aerofoil section blades are varied so as to provide vertical lift only, the second mode where the angle of attack of the aerofoil section blades are varied so as to provide both vertical lift and forward thrust, the third mode where the angle of attack of the aerofoil section blades are varied so as to provide maximum forward thrust and the fourth mode where the angle of attack of the aerofoil section blades are varied so as to provide a fixed gliding configuration.
  4. 4. An aircraft as claimed in any previous claim, including a horizontally rotating tail rotor located at the rear of and disposed centrally over the aircraft fuselage.
GB0315325A 2003-07-01 2003-07-01 Vertical take off rotating wing aircraft Withdrawn GB2403460A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB0315325A GB2403460A (en) 2003-07-01 2003-07-01 Vertical take off rotating wing aircraft

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB0315325A GB2403460A (en) 2003-07-01 2003-07-01 Vertical take off rotating wing aircraft

Publications (2)

Publication Number Publication Date
GB0315325D0 GB0315325D0 (en) 2003-08-06
GB2403460A true GB2403460A (en) 2005-01-05

Family

ID=27676395

Family Applications (1)

Application Number Title Priority Date Filing Date
GB0315325A Withdrawn GB2403460A (en) 2003-07-01 2003-07-01 Vertical take off rotating wing aircraft

Country Status (1)

Country Link
GB (1) GB2403460A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2011046218A (en) * 2009-08-25 2011-03-10 Yuji Imai Rotary wing flying body

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB248028A (en) * 1924-10-28 1926-03-01 Carl Bruno Strandgren Improvements in feathering paddle wheel propellors and motors
GB280849A (en) * 1926-11-22 1928-02-09 Bruno Nagler Improvements in flying machines employing rotating wing systems
GB369249A (en) * 1930-12-11 1932-03-11 Haviland Hull Platt Improvements in heavier-than-air type of aircraft
GB480750A (en) * 1936-08-26 1938-02-28 George William Walton Improvements in aircraft of the cyclogyro type
US5265827A (en) * 1991-06-17 1993-11-30 Northrop Corporation Paddle wheel rotorcraft
DE19529700A1 (en) * 1995-08-11 1997-02-13 Pflug Jochen Dipl Ing Fh Aircraft with rotating wings - uses adjustment of left and right control points to determine drive and thrust

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB248028A (en) * 1924-10-28 1926-03-01 Carl Bruno Strandgren Improvements in feathering paddle wheel propellors and motors
GB280849A (en) * 1926-11-22 1928-02-09 Bruno Nagler Improvements in flying machines employing rotating wing systems
GB369249A (en) * 1930-12-11 1932-03-11 Haviland Hull Platt Improvements in heavier-than-air type of aircraft
GB480750A (en) * 1936-08-26 1938-02-28 George William Walton Improvements in aircraft of the cyclogyro type
US5265827A (en) * 1991-06-17 1993-11-30 Northrop Corporation Paddle wheel rotorcraft
DE19529700A1 (en) * 1995-08-11 1997-02-13 Pflug Jochen Dipl Ing Fh Aircraft with rotating wings - uses adjustment of left and right control points to determine drive and thrust

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2011046218A (en) * 2009-08-25 2011-03-10 Yuji Imai Rotary wing flying body

Also Published As

Publication number Publication date
GB0315325D0 (en) 2003-08-06

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Legal Events

Date Code Title Description
WAP Application withdrawn, taken to be withdrawn or refused ** after publication under section 16(1)