WO2001004002A1 - Aircraft aerofoil unit - Google Patents

Aircraft aerofoil unit Download PDF

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Publication number
WO2001004002A1
WO2001004002A1 PCT/GB2000/002575 GB0002575W WO0104002A1 WO 2001004002 A1 WO2001004002 A1 WO 2001004002A1 GB 0002575 W GB0002575 W GB 0002575W WO 0104002 A1 WO0104002 A1 WO 0104002A1
Authority
WO
WIPO (PCT)
Prior art keywords
aircraft
common
control surface
aerofoil unit
aerofoil
Prior art date
Application number
PCT/GB2000/002575
Other languages
French (fr)
Inventor
Roy Graham Scott
Original Assignee
Bae Systems Plc
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 Bae Systems Plc filed Critical Bae Systems Plc
Priority to AU56974/00A priority Critical patent/AU5697400A/en
Priority to JP2001509636A priority patent/JP2003504266A/en
Publication of WO2001004002A1 publication Critical patent/WO2001004002A1/en

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C5/00—Stabilising surfaces
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/10—Drag reduction

Definitions

  • This invention relates to an aircraft aerofoil unit, and more particularly to an empennage unit suitable for use in areas of the aircraft such as the wing tips, the tail planes and the fin.
  • the empennage units employed as the wing tips are different in design and construction from those employed for the tail planes, and are different in design and construction again from those employed for the fin.
  • the wing tips including their movable flying control surfaces or ailerons, are of asymmetrical aerofoil or standard naca section in order to provide lift in use.
  • the horizontal tail planes including their movable flying control surfaces or elevators, but in this case a different asymmetric aerofoil or standard naca section will generally be employed.
  • a disadvantage of such design characteristics is the fact that each aerofoil or empennage unit has to be manufactured on an individual basis, and the customer has to hold a substantial number of spares, varying according to those empennage units most vulnerable to damage.
  • an aircraft employing respectively a common aerofoil unit for each of the outboard wing tips of the aircraft wings as well as for at least some and preferably all of the group consisting of : tail planes; and fin.
  • the invention is applicable to all types of aircraft, including civil, military, light, manned, unmanned, jet-powered and propeller-powered aircraft, and also gliders.
  • the aircraft according to the invention advantageously employs a similar aerofoil unit whether it is intended for use as a wing tip, a tail plane or a fin, the unit being interchangeable for all of these areas of the aircraft and hence being non-handed.
  • the common aerofoil unit has a symmetrical aerofoil section.
  • a constant chord design may be utilised.
  • the common aerofoil unit comprises a fixed assembly, a movable control surface supported by the fixed assembly and a control mechanism for moving the control surface.
  • both the fixed assembly and the movable control surface will preferably have a symmetrical section.
  • the common aerofoil unit has a symmetrical aerofoil section
  • aircraft lift will have to be achieved by some other means than the use of an asymmetrical aerofoil section for the full wing length and the tail planes.
  • lift may be achieved by angling inboard portions of the wings relative to the aircraft longitudinal axis, i.e. by giving the wing a dihedral twist relative to the aircraft body.
  • these inboard wing portions may be profiled to have an asymmetric aerofoil section tending towards a symmetrical aerofoil section at the junction with the common aerofoil unit providing the wing tips.
  • a common aerofoil unit for use in such an aircraft.
  • a common aerofoil unit according to the invention for an aircraft for use for the wingtips, the tail planes and/or the fin, comprises a fixed assembly, a movable control surface supported by the fixed assembly, and a control mechanism for operating the movable control surface, wherein the fixed assembly and the movable control surface have a symmetrical aerofoil section.
  • Figure 1 is a plan view of an aircraft according to the invention.
  • Figure 2 is a side elevation of the aircraft shown in Figure 1 ;
  • Figure 3 is a detailed view of a common aerofoil unit for use in the aircraft of Figures 1
  • Figures 1 and 2 show an aircraft 10 according to the invention, having a body 12, a pair of wings 14, a pair of tail planes 16 and a fin 18.
  • the two wings 14 have their wing tips 20 provided by identical empennage units 22, and the tail planes 16 and the fin 18 are also formed by identical such aerofoil units 22.
  • the common aerofoil unit 22, which provides the two wing tips 20, the two tail planes 16 and the fin 18, is shown in greater detail in Figure 3 and comprises a fixed assembly 30 and a movable flying control surface 32.
  • Figure 3 further shows that the fixed assembly 30 comprises a leading edge 36, an outboard edge or tip 38, and an inboard edge 40 for mounting to the aircraft body 12, or wing 14.
  • the movable control surface 32 is at the trailing edge of the fixed assembly.
  • the fixed assembly 30 also has an internal support structure 42, and a control mechanism 44 for effecting movement of the movable flying control surface 32 in use.
  • the control mechanism may comprise a mechanical linkage or a fluid, gas or electrically operated system.
  • the fixed assembly 30 and the movable control surface 32 are of symmetrical aerofoil section. That is, the same aerofoil unit is usable without modification for both left-handed and right-handed aircraft parts, i.e. wing tips and tail planes, and is thus non- handed.
  • the common aerofoil unit is interchangeable and can be employed as an outboard wing tip 20 with the movable control surface 32 acting as an aileron; or as a tail plane 16 with the movable control surface 32 acting as an elevator; or as a fin 18 with the movable control surface 32 acting as a rudder.
  • an inboard portion 34 of each aircraft wing 14 is mounted at an angle relative to the aircraft axis, i.e. is given a dihedral twist relative to the longitudinal axis of the aircraft body.
  • a dihedral twist of 5 degrees over a 7.4m wing span would lift an aircraft of approximately 3000 kg.
  • Wing planform and the angle of dihedral twist are both variables in the parametric equations, and would therefore need balancing.
  • aircraft lift may also be obtained by providing appropriately oriented chines on the aircraft body 12 forward of the wings 14 and/or swept onto or on the inboard portions 34 of the wings 14 having a dihedral twist.
  • the common aerofoil unit may in addition have extra internally fitted items, for example, internal fluid, mechanical or electrical systems, even integral fuel tanks, and/or lights.
  • the common aerofoil unit may be constructed utilising various metallic and non-metallic materials and conventional construction methods, and may be modified in terms of its geometry, size and mass to suit the intended application.

Abstract

The present invention provides an aircraft employing respectively a common aerofoil unit (22) for each of the outboard wing tips (20) of the aircraft wings (14) as well as for at least some and preferably all of the group consisting of: tail planes (16); and fin (18).

Description

Aircraft Aerofoil Unit
This invention relates to an aircraft aerofoil unit, and more particularly to an empennage unit suitable for use in areas of the aircraft such as the wing tips, the tail planes and the fin.
Traditionally, most aircraft have empennage units which are especially designed according to their purpose. Thus, the empennage units employed as the wing tips are different in design and construction from those employed for the tail planes, and are different in design and construction again from those employed for the fin. Normally, the wing tips, including their movable flying control surfaces or ailerons, are of asymmetrical aerofoil or standard naca section in order to provide lift in use. The same is true of the horizontal tail planes, including their movable flying control surfaces or elevators, but in this case a different asymmetric aerofoil or standard naca section will generally be employed.
A disadvantage of such design characteristics is the fact that each aerofoil or empennage unit has to be manufactured on an individual basis, and the customer has to hold a substantial number of spares, varying according to those empennage units most vulnerable to damage.
According to the present invention, there is provided an aircraft employing respectively a common aerofoil unit for each of the outboard wing tips of the aircraft wings as well as for at least some and preferably all of the group consisting of : tail planes; and fin.
The use of a common aerofoil unit for all of the wing tips, the tail planes and the fin has significant advantages both in terms of manufacture and in terms of maintenance. Design, manufacturing and tooling costs can be reduced as a result of the use of the same empennage unit in different areas of the aircraft. Also, the production of an increased volume of identical sub-assemblies and component parts should lead to a more consistent and controlled manufacturing process together with lower parts costs. Furthermore, the overall number of spares held by a customer can be reduced, since repairs to different areas of the aircraft can be achieved with the same common empennage unit. Consequently, maintenance is facilitated and maintenance costs can be minimised.
The invention is applicable to all types of aircraft, including civil, military, light, manned, unmanned, jet-powered and propeller-powered aircraft, and also gliders. The aircraft according to the invention advantageously employs a similar aerofoil unit whether it is intended for use as a wing tip, a tail plane or a fin, the unit being interchangeable for all of these areas of the aircraft and hence being non-handed.
In a preferred form of the invention, the common aerofoil unit has a symmetrical aerofoil section. For example, a constant chord design may be utilised.
Preferably, the common aerofoil unit comprises a fixed assembly, a movable control surface supported by the fixed assembly and a control mechanism for moving the control surface. In this instance, both the fixed assembly and the movable control surface will preferably have a symmetrical section.
Since the common aerofoil unit has a symmetrical aerofoil section, aircraft lift will have to be achieved by some other means than the use of an asymmetrical aerofoil section for the full wing length and the tail planes. For example, lift may be achieved by angling inboard portions of the wings relative to the aircraft longitudinal axis, i.e. by giving the wing a dihedral twist relative to the aircraft body. Alternatively, these inboard wing portions may be profiled to have an asymmetric aerofoil section tending towards a symmetrical aerofoil section at the junction with the common aerofoil unit providing the wing tips.
According to another aspect to the invention, there is provided a common aerofoil unit for use in such an aircraft.
A common aerofoil unit according to the invention, for an aircraft for use for the wingtips, the tail planes and/or the fin, comprises a fixed assembly, a movable control surface supported by the fixed assembly, and a control mechanism for operating the movable control surface, wherein the fixed assembly and the movable control surface have a symmetrical aerofoil section.
The invention is described further by way of example, with reference to the accompanying drawings, in which:
Figure 1 is a plan view of an aircraft according to the invention;
Figure 2 is a side elevation of the aircraft shown in Figure 1 ; and
Figure 3 is a detailed view of a common aerofoil unit for use in the aircraft of Figures 1 Referring to the drawings, Figures 1 and 2 show an aircraft 10 according to the invention, having a body 12, a pair of wings 14, a pair of tail planes 16 and a fin 18. The two wings 14 have their wing tips 20 provided by identical empennage units 22, and the tail planes 16 and the fin 18 are also formed by identical such aerofoil units 22.
The common aerofoil unit 22, which provides the two wing tips 20, the two tail planes 16 and the fin 18, is shown in greater detail in Figure 3 and comprises a fixed assembly 30 and a movable flying control surface 32. Figure 3 further shows that the fixed assembly 30 comprises a leading edge 36, an outboard edge or tip 38, and an inboard edge 40 for mounting to the aircraft body 12, or wing 14. The movable control surface 32 is at the trailing edge of the fixed assembly.
The fixed assembly 30 also has an internal support structure 42, and a control mechanism 44 for effecting movement of the movable flying control surface 32 in use. The control mechanism may comprise a mechanical linkage or a fluid, gas or electrically operated system.
As can be seen from Figure 2, the fixed assembly 30 and the movable control surface 32 are of symmetrical aerofoil section. That is, the same aerofoil unit is usable without modification for both left-handed and right-handed aircraft parts, i.e. wing tips and tail planes, and is thus non- handed.
By virtue of its symmetrical aerofoil section, the common aerofoil unit is interchangeable and can be employed as an outboard wing tip 20 with the movable control surface 32 acting as an aileron; or as a tail plane 16 with the movable control surface 32 acting as an elevator; or as a fin 18 with the movable control surface 32 acting as a rudder.
In order to achieve aircraft lift in use, particularly wing lift, an inboard portion 34 of each aircraft wing 14 is mounted at an angle relative to the aircraft axis, i.e. is given a dihedral twist relative to the longitudinal axis of the aircraft body. Parametric analysis suggests that a dihedral twist of 5 degrees over a 7.4m wing span would lift an aircraft of approximately 3000 kg. Wing planform and the angle of dihedral twist are both variables in the parametric equations, and would therefore need balancing. Additionally, aircraft lift may also be obtained by providing appropriately oriented chines on the aircraft body 12 forward of the wings 14 and/or swept onto or on the inboard portions 34 of the wings 14 having a dihedral twist.
If desired, the common aerofoil unit may in addition have extra internally fitted items, for example, internal fluid, mechanical or electrical systems, even integral fuel tanks, and/or lights.
The common aerofoil unit may be constructed utilising various metallic and non-metallic materials and conventional construction methods, and may be modified in terms of its geometry, size and mass to suit the intended application.

Claims

Claims
1. An aircraft characterised by employing respectively a common aerofoil unit (22) for each of the outboard wing tips (20) of the aircraft wings (14) as well as for at least some and preferably all of the group consisting of: tail planes(l 6) ; and fin (18).
2. An aircraft according to claim 1 wherein the common aerofoil unit has a symmetrical aerofoil section.
3. An aircraft according to claim 1 or 2 wherein the common aerofoil unit is of constant chord design.
4. An aircraft according to any of claims 1 to 3 wherein the common aerofoil unit comprises a fixed assembly (30), a movable flying control surface (32) supported on the fixed assembly, and a control mechanism (44) for moving the flying control surface.
5. An aircraft according to any of claims 1 to 3 wherein the common aerofoil unit comprises a movable control surface employed as an aileron.
6. An aircraft according to any of claims 1 to 3 wherein the common aerofoil unit is employed as a tail plane and wherein the common aerofoil unit comprises a movable control surface employed as an elevator.
7. An aircraft according any of claims 1 to 3 wherein the common aerofoil unit is employed as a fin and wherein the common aerofoil unit comprises a movable control surface employed as a rudder.
8. An aircraft according to any preceding claim wherein the aircraft wing comprise an inboard portion having a dihedral twist and an outboard portion provided by the common aerofoil unit.
9. An aircraft according to any preceding claim provided with chines on the aircraft body forward of the wings and/or on the inboard regions of the wings.
10. A common aerofoil unit for use in an aircraft according to any preceding claim.
11. A common aerofoil unit for an aircraft for use in the wing tips of the aircraft wings as well as the tail planes and/or the fin of the aircraft, said aerofoil unit being characterised by a fixed assembly (30), a movable control surface (32) supported by the fixed assembly, and a control mechanism (44) for operating the movable control surface, wherein the fixed assembly and the movable control surface have a symmetrical aerofoil section.
12. An aircraft wing comprising an inboard portion adapted to have a dihedral twist in relation to a body of the aircraft and an outboard portion providing the wing tip, said outboard portion comprising an aerofoil unit as claimed in claim 1 1.
13. An aircraft wing as claimed in claim 12 wherein the inboard portion is formed with chines.
PCT/GB2000/002575 1999-07-07 2000-07-05 Aircraft aerofoil unit WO2001004002A1 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
AU56974/00A AU5697400A (en) 1999-07-07 2000-07-05 Aircraft aerofoil unit
JP2001509636A JP2003504266A (en) 1999-07-07 2000-07-05 Aircraft airfoil unit

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GBGB9915950.1A GB9915950D0 (en) 1999-07-07 1999-07-07 Air-craft aerofoil
GB9915950.1 1999-07-07

Publications (1)

Publication Number Publication Date
WO2001004002A1 true WO2001004002A1 (en) 2001-01-18

Family

ID=10856846

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/GB2000/002575 WO2001004002A1 (en) 1999-07-07 2000-07-05 Aircraft aerofoil unit

Country Status (4)

Country Link
JP (1) JP2003504266A (en)
AU (1) AU5697400A (en)
GB (1) GB9915950D0 (en)
WO (1) WO2001004002A1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2020216737A1 (en) * 2019-04-26 2020-10-29 Airbus Operations Gmbh Modular aerostruktur assembly

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE300050C (en) * 1900-01-01

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE300050C (en) * 1900-01-01

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2020216737A1 (en) * 2019-04-26 2020-10-29 Airbus Operations Gmbh Modular aerostruktur assembly

Also Published As

Publication number Publication date
AU5697400A (en) 2001-01-30
JP2003504266A (en) 2003-02-04
GB9915950D0 (en) 1999-09-08

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