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 Title: |
US5681014:
Torsional twist airfoil control means
[ Derwent Title ]
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| Country: |
US United States of America
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| Inventor: |
Palmer, Harry W.; Denmark, ME 04022
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| Assignee: |
None
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| Published / Filed: |
1997-10-28
/ 1994-10-17
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| Application Number: |
US1994000323779
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| IPC Code: |
Advanced:
B64C 3/52;
Core:
B64C 3/00;
IPC-7:
B64C 3/44;
B64C 3/52;
B64D 15/10;
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| ECLA Code: |
B64C3/52;
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| U.S. Class: |
Current:
244/219;
244/048;
244/134.A;
244/206;
Original:
244/219;
244/048;
244/134.A;
244/206;
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| Field of Search: |
244/201,206,219,134 A,134 E,46,48
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| Priority Number: |
| 1994-10-17 |
US1994000323779 |
| 1992-05-15 |
US1992000885037 |
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| Abstract: |
A control system for aircraft airfoils, which is an improvement over existing aileron, flap, spoiler and deicing technologies, in providing increased roll control and aerodynamic lifting and braking functions; with greatly reduced drag increased airspeed and precise control performance at all airspeeds, due to clean uninterrupted airfoil surfaces and directional conformance of wing to the intended flight path.
This is accomplished by use of a torque tube mounted internally in the aeroelastic airfoil structure, and firmly attached to the airfoil tip structure. In operation the inboard end of the torque tube when rotated differentially on its pivot axis, imposes a helicoidal twist on the aeroelastic airfoil structure, with maximum angle of incidence at the outboard wing tip, providing near perfect lateral roll control or cooperating to provide increased lift and braking or maneuverability, also the foregoing operations provide automatic deicing. The torque tube can be operated by conventional control systems, e.g. cable/pulley, electric/hydraulic servo etc.
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| Primary / Asst. Examiners: |
Mojica, Virna Lissi;
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| Maintenance Status: |
E2 Expired Check current status
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| INPADOC Legal Status: |
Show legal status actions
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| Parent Case: |
This application is a Continuation-in-part of Ser. No. 07/885,037, filed May 15, 1992, now abandoned.
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| Family: |
None
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First Claim:
Show all 14 claims |
I claim as my inventions:
1. An aeroelastic airfoil control means, said aeroelastic airfoil control means providing for aircraft maneuverability control and/or automatic deicing means for a wing of an airplane,
- said airfoil control means including roll control means; wherein said wing provides for slow flight, high lift and maneuverability functions at both low and high airspeeds, said wing means comprising:
- an aircraft aeroelastic wing structure, wherein said aeroelastic wing structure extends outwardly from a fuselage of said airplane, to a wing tip structure of said airplane, said aeroelastic wing structure comprising:
- an airfoil aeroelastic skin cover that is substantially smooth and free of individual control surfaces;
- wherein said aeroelastic skin cover is flexible and compliant;
- said aeroelastic skin cover forms a continuous linear wave form, wherein the pitch and amplitude of the wave are variable in form;
- said aeroelastic wing further including:
- a flexible leading edge structure extending from said fuselage to said wing tip structure;
- a flexible trailing edge structure extending from said fuselage to said wing tip structure;
- a set of flexible rib structures, wherein said flexible rib structures are spaced apart and connected to said flexible leading edge structure and said flexible trailing edge structure;
- an upper aeroelastic wing skin covering, wherein said upper aeroelastic wing covering is attached to the following wing structure: said flexible leading edge structure, said flexible trailing edge structure, said flexible rib structures and to said wing tip structure;
- a lower aeroelastic wing skin covering, wherein said lower aeroelastic wing skin covering is attached to the following wing structure: said flexible leading edge structure, said flexible trailing edge structure, said flexible rib structures and to said wing tip structure;
- a rotatable torque tube mounted internally within said aeroelastic wing structure, said rotatable torque tube extending from said fuselage to said wing tip, wherein said rotatable torque tube is substantially aligned with the aerodynamic center of the airfoil; said rotatable torque tube is positioned for aerodynamic balance.
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| Background / Summary: |
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| Drawing Descriptions: |
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| Description: |
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| Forward References: |
Show 25 U.S. patent(s) that reference this one
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