US20010006207A1 - Control surface for an aircraft - Google Patents

Control surface for an aircraft Download PDF

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Publication number
US20010006207A1
US20010006207A1 US09/784,771 US78477101A US2001006207A1 US 20010006207 A1 US20010006207 A1 US 20010006207A1 US 78477101 A US78477101 A US 78477101A US 2001006207 A1 US2001006207 A1 US 2001006207A1
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US
United States
Prior art keywords
aircraft
surface
elastomer
control surface
attached
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Granted
Application number
US09/784,771
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US6349903B2 (en
Inventor
John Caton
Michael Hobey
John Groeneveld
Jack Jacobs
Robert Wille
Lawrence Brase
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Boeing Co
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Boeing Co
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Publication date
Priority to US93294797A priority Critical
Priority to US09/517,838 priority patent/US6209824B1/en
Application filed by Boeing Co filed Critical Boeing Co
Assigned to BOEING COMPANY, THE reassignment BOEING COMPANY, THE ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: BRASE, JR., LAWRENCE OTTO
Priority to US09/784,771 priority patent/US6349903B2/en
Publication of US20010006207A1 publication Critical patent/US20010006207A1/en
Publication of US6349903B2 publication Critical patent/US6349903B2/en
Application granted granted Critical
Anticipated expiration legal-status Critical
Application status is Expired - Lifetime legal-status Critical

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    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C7/00Structures or fairings not otherwise provided for
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C27/00Rotorcraft; Rotors peculiar thereto
    • B64C27/54Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
    • B64C27/58Transmitting means
    • B64C27/59Transmitting means mechanical
    • B64C27/615Transmitting means mechanical including flaps mounted on blades
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C9/00Adjustable control surfaces or members, e.g. rudders
    • B64C9/02Mounting or supporting thereof
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C27/00Rotorcraft; Rotors peculiar thereto
    • B64C27/54Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
    • B64C27/72Means acting on blades
    • B64C2027/7205Means acting on blades on each blade individually, e.g. individual blade control [IBC]
    • B64C2027/7261Means acting on blades on each blade individually, e.g. individual blade control [IBC] with flaps
    • B64C2027/7266Means acting on blades on each blade individually, e.g. individual blade control [IBC] with flaps actuated by actuators
    • B64C2027/7288Means acting on blades on each blade individually, e.g. individual blade control [IBC] with flaps actuated by actuators of the memory shape type
    • YGENERAL 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
    • Y02TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02TCLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00Aeronautics or air transport
    • Y02T50/30Wing lift efficiency
    • Y02T50/32Optimised high lift wing systems
    • YGENERAL 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
    • Y02TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02TCLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00Aeronautics or air transport
    • Y02T50/30Wing lift efficiency
    • Y02T50/34Helicopter rotor blades lift efficiency

Abstract

A control surface (152) for an aircraft has a reinforced elastomer surface (154) on a surface of the aircraft and has a perimeter (156) attached to the aircraft. An actuation mechanism (160) moves the reinforced elastomer surface (154) from a first position, substantially conforming to a moldline of the aircraft, to a second position, protruding from the moldline of the aircraft.

Description

    FIELD OF THE INVENTION
  • The present invention relates generally to the field of aircraft and more particularly to a control surface for an aircraft. [0001]
  • BACKGROUND OF THE INVENTION
  • Aircraft incorporate control surfaces to provide roll, pitch and yaw control, as well as high lift devices such as flaps. Present control surfaces are rigid panels that are pivoted out of the surrounding moldline of the aircraft to create the control moment. These control surfaces have gaps that result in aerodynamic spillage, that reduce the effectiveness of the control surface. Present control surfaces are particularly in effective in tailless aircraft designs. Tailless designs provide increased aerodynamic efficiency and agility. However, to provide adequate yaw control thrust-vectoring engine nozzles are required. Thrust-vectoring nozzles are expensive and heavy. [0002]
  • Thus there exists a need for a control surface that does not have aerodynamic spillage and can replace heavy, expensive thrust-vectoring nozzles on tailless aircraft designs. [0003]
  • SUMMARY OF THE INVENTION
  • A control surface for an aircraft that overcomes these and other problems has a reinforced elastomer surface on a surface of the aircraft and has a perimeter attached to the aircraft. An actuation mechanism moves the reinforced elastomer surface from a first position, substantially conforming to a moldline of the aircraft, to a second position, protruding from the moldline of the aircraft. [0004]
  • BRIEF DESCRIPTION OF THE DRAWINGS
  • FIG. 1 is a perspective view of a wing of an aircraft with a prior art control surface; [0005]
  • FIG. 2 is a perspective view of a reinforced elastomer panel; [0006]
  • FIG. 3 is a perspective view of an embodiment of a control surface for an aircraft according to the invention; [0007]
  • FIG. 4 is a cross sectional view of the control surface of FIG. 3 taken along the A-A line; [0008]
  • FIG. 5 is a cross sectional view of the control surface of FIG. 3 taken along the A-A line, in an actuated position; [0009]
  • FIG. 6 is a cross sectional view of the control surface of FIG. 3 taken along the B-B line; [0010]
  • FIG. 7 is a cross sectional view of the control surface of FIG. 3 taken along the B-B line, in an actuated position; [0011]
  • FIG. 8 is a cross section view of an embodiment of a flexible spine used in the control surface of FIG. 3; [0012]
  • FIG. 9 is a cross section view of another embodiment of a flexible spine used in the control surface of FIG. 3; [0013]
  • FIG. 10 is perspective view of a tailless aircraft having an embodiment of a control surface according to the invention; [0014]
  • FIG. 11 is a perspective view of an embodiment of a control surface according to the invention; [0015]
  • FIG. 12 is a cross sectional view of an embodiment of the control surface of FIG. 11; [0016]
  • FIG. 13 is a cross sectional view of an embodiment of the control surface of FIG. 11; [0017]
  • FIG. 14 is a cross sectional view of an embodiment of the control surface of FIG. 11; [0018]
  • FIG. 15 is a perspective view of the control surface of FIG. 14; [0019]
  • FIG. 16 is a perspective view of an aircraft having an embodiment of a control surface according to the invention; [0020]
  • FIG. 17 is a top view of the control surface of FIG. 16; [0021]
  • FIG. 18 is a cross sectional view of the control surface of FIG. 16; taken along the C-C line; [0022]
  • FIG. 19 is a perspective view of a rotor blade for a helicopter; and [0023]
  • FIG. 20 is a perspective view of an embodiment of a control surface for a rotor. [0024]
  • DETAILED DESCRIPTION OF THE DRAWINGS
  • FIG. 1 is a perspective view of a wing [0025] 50 of an aircraft with a prior art control surface 52. The prior art control surface 52 allows aerodynamic spillage through the gaps 54 between the wing and the control surface 52. This significantly limits the aerodynamic effectiveness of the control surface.
  • The key to building an improved control surface for an aircraft is to design a control surface that takes advantage of the elastomer panel [0026] 60 as shown FIG. 2 in the design. The elastomer panel 60 has a rod block 62 attached along one edge to an elastomer skin 64. The elastomer skin 64 is capable of stretching to 100% of its unstressed length. In addition, the elastomer skin 64 is capable of twisting. A plurality of rods 66 are attached to the rod block 62 and are allowed to slide freely inside the elastomer skin 64. The rods 66 are made from quartz, epoxy or composites and flex without breaking. The stiffness of these reinforcements is designed to yield a specific expanded shape. The rods 66 provide the elastomer skin 64 with a curvilinear shape when the elastomer panel 60 is elongated, deflected or twisted. This curvilinear shape provides a good aerodynamic shape without any discontinuities that cause turbulence and drag.
  • A second rod block [0027] 68 is attached to an opposite edge of the elastomer skin 64. The second rod block 68 has a plurality of holes through which the plurality of rods 66 are allowed to slide freely. Both the rod block 62 and the second rod block 68 have attachment provisions 70, for attaching the elastomer panel 60 to the surface of an aircraft.
  • FIG. 3 is a perspective view of an embodiment of a control surface [0028] 80 for an aircraft according to the invention. The control surface includes a rigid structural panel 82 pivotally attached to the aircraft. The rigid structural panel 82 has a long edge 84 and a pair of short edges 86. A pair of flexible struts 88, 90 extend from each of the pair of short edges 86 to the aircraft. The flexible struts 88, 90 in one embodiment are formed from a high durometer rubber. A long elastomer panel 92 is attached between the aircraft and the long edge 84 of the rigid structural panel 82. The long elastomer panel 92 is a reinforced elastomer panel as shown in FIG. 2. The reinforcing rods are shown as the lines running perpendicular to the long edge 84. A pair of short elastomer panels 94, 96 are connected between the aircraft and the rigid structural panel 82. In addition the short elastomer panels 94, 96 are connected to the struts 88, 90. The elastomer panels 94, 96 differ from the elastomer panel of FIG. 2, in that they contain a flexible spine 98. The flexible spine 98 will be described in greater detail in connection with FIGS. 8 & 9.
  • FIGS. 4 & 5 are cross sectional views of the control surface of FIG. 3 taken along the A-A line. The long elastomer panel [0029] 92 consists of two elastomer panels one on the top and one on the bottom. The rigid structural panel 82 pivots along an axis 100 between the elastomer panels. One of the elastomer panels expands to cover the gap in FIG. 5 and the other elastomer panel contracts to cover the gap on the other side.
  • FIGS. 6 & 7 are cross sectional view of the control surface of FIG. 3 taken along the B-B line. The elastomer panels [0030] 96 consist of a top and a bottom elastomer panel. A flexible spine 98 runs through the center of the elastomer panels. The reinforcing rods attach to the rod blocks 102 and then slide within a plurality of bushings in the spine 98. FIGS. 8 & 9 are two embodiments of the flexible spine 98. The reinforcing rods 120 are shown embedded in the elastomer sheet 122. The rods 120 terminate in a bushing 124. The bushing 124 in an embodiment is made of a high durometer rubber. The rods 120 are allowed to slide freely within the cavity of the bushing 124. The spines 98 of FIGS. 8 & 9 differ in how the support brace 126 is designed. In FIG. 8 the support brace is a “C” shaped flexible member 128 with a reinforcing rod 130 embedded in the perpendicular side of the member 128. The parallel members are bonded to the bushing 124. In one embodiment, the “C” shaped flexible member is made of a high durometer rubber.
  • The spine [0031] 98 in FIG. 9 has a composite plate 132 bonded to a pair of flexible footers 134, 136. The flexible footers 134, 136 are bonded to the bushings 124 and the elastomer sheet 122. In one embodiment the flexible footers 134, 136 are made of elastomer.
  • FIG. 10 is perspective view of a tailless aircraft [0032] 150 having an embodiment of a control surface 152 according to the invention. The control surface 152 is mounted on the surface of the aircraft 150. FIG. 11 is a perspective view of an embodiment of the control surface 152. The control surface 152 has a reinforced elastomer surface 154. A perimeter 156 of the reinforced elastomer surface 154 is formed of rigid material and is attached to the aircraft. The reinforced elastomer surface 154 has a spine 158 extending along its center. The spine 158 in one embodiment is made of a high durometer rubber and has a plurality of cavities (bushings) into which the reinforcing rods slide.
  • FIG. 12 is a cross sectional view of an embodiment of the control surface of FIG. 11. In this embodiment, a pneumatic pump (actuation mechanism) [0033] 160 is connected to a bladder 164 between the elastomer surface 154 and aircraft. By inflating the bladder 164 the control surface is moved from a first position, conforming to the moldline of the aircraft, to a second position, where the control surface is outside the moldline of the aircraft.
  • FIG. 13 is a cross sectional view of another embodiment of the control surface [0034] 152 of FIG. 11. In this case the actuation mechanism 170 uses a plunger (rigid surface) 172 to move the control surface, by pushing on the spine 158. The actuation mechanism 170 can be mechanical, electromechanical or hydraulic. In another embodiment, shape memory alloy wires (slats) are embedded into the elastomer sheet 154. The shape memory alloy wires actuate the control surface by applying a current to change the state of the wires.
  • FIG. 14 is a cross sectional view of another embodiment of the control surface [0035] 152 of FIG. 11. In this embodiment a rigid panel 180 is pivotally attached to the aircraft along the perimeter 156. An actuation mechanism 182 is attached to the rigid panel 180. In one embodiment the rigid panel 180 is formed out of a composite. An elastomer sheet 182 (not reinforced in one embodiment) connects a perimeter edge 184 of the rigid panel 180 to the aircraft. Another elastomer sheet 186 (not reinforced) is connected to the traveling edge 188 of the rigid panel 180. A collar 190 is attached to the elastomer sheet 186. The collar 190 in one embodiment is made of a high durometer rubber. The reinforcing rods 192 of the reinforced elastomer panel 194 connect to the collar 190. The other end of the reinforced elastomer panel 194 slide in a rod block along the perimeter 156.
  • FIG. 15 is a perspective view of an embodiment of the control surface of FIG. 14. In this embodiment two rigid panels [0036] 180 are adjacent to each other. An elastomer panel 200 connects the two elastomer panels 180. The elastomer panel 200 has a spine 202 running through the center of the elastomer panel 200. The spine 202 is similar to the spine 190 and the reinforcing rods of the elastomer panel 200 slide within bushings in the spine 202. The other end of the reinforcing rods are connected to the rigid panels 180. The design provides a control surface with a variable control area.
  • FIG. 16 is a perspective view of an aircraft [0037] 220 having an embodiment of a control surface 222 according to the invention. In this embodiment, the control surface is on a nose 224 of the aircraft 220. This control surface 222 provides yaw control for the aircraft 220 at high angles of attack, where conventional control surfaces are less effective. Generally, the control surface 222 would be placed on both sides of the aircraft. FIG. 17 is a top view of the control surface 222. A rigid panel 226 is surrounded by elastomer panels. A perimeter 228 of the control surface is attached to the aircraft 224. A portion of the elastomer sheet 230 without reinforcing rods is connected between the rigid panels 226 and the perimeter 228. A pair of side reinforced elastomer panels 232 connect the sides of the rigid panel to the perimeter 228. A pair of struts 234 are connected between the top edge of the rigid panel 226 and the perimeter 228. A top reinforced elastomer panel 236 connects between the struts 234 and the perimeter 228. A floating strut 238 defines an elastomer panel 240 without reinforcing rods. The elastomer panel 240 allows the control surface to have a sharply sloping back surface 242 (see FIG. 18). FIG. 18 shows a cross section of the control surface taken along the C-C line. A pivot mechanism 244 attaches the rigid panel 226 to the aircraft. An actuation mechanism 246 is pivotally attached to the rigid panel 226 and moves the rigid panel from a first position (conformable surface) to a second position (protuding position). The control surface 222 is light weight and provides control without any gaps that reduce the effectiveness of conventional control surfaces. In addition, the control surface 222 is a novel control surface that has not been used on aircraft to date and provides yaw control at high angles of attack.
  • FIG. 19 is a perspective view of a rotor blade [0038] 300 for a helicopter (aircraft). A static tab 302 is used to balance the blade 300 from rotational instability. An active flap 304 is used to provide active rotational stability. Active stability can improve rotor efficiency and increase the rotor blade's life. By using the reinforced elastomer panels in a tab design, gaps around the tabs can be eliminated. The gaps reduce efficiency and create vortices that the trailing blade hits. This reduces the lifetime of the rotor blades. FIG. 20 is a perspective view of an embodiment of a control surface 304 for a rotor blade 300. A rigid panel 306 is connected to an actuator 308. In one embodiment the actuator 308 is a shape memory alloy (SMA) actuation system. A SMA actuation system can be made small enough to fit within the confines of the rotor blade 300. The rigid panel 306 has a pair of side reinforced elastomer panels 310 and a back reinforced elastomer panel 312 that encases the rigid panel 306. Another embodiment of the control surface 304 includes struts and spines similar to those shown in FIG. 3.
  • Thus there has been described a control surface that eliminates gaps, weighs less than vectored nozzles and provides control surfaces that do not exist in the art. While the invention has been described in conjunction with specific embodiments thereof, it is evident that many alterations, modifications, and variations will be apparent to those skilled in the art in light of the foregoing description. Accordingly, it is intended to embrace all such alterations, modifications, and variations in the appended claims. [0039]

Claims (18)

What is claimed is:
1. A control surface for an aircraft comprising:
a reinforced elastomer surface on a surface of the aircraft and having a perimeter attached to the aircraft; and
an actuation mechanism moving the reinforced elastomer surface from a first position, substantially conforming to a moldline of the aircraft, to a second position, protruding from the moldline of the aircraft.
2. The control surface of
claim 1
, wherein the reinforced elastomer surface is attached to a nose of an aircraft.
3. The control surface of
claim 1
, wherein the reinforced elastomer surface is attached to a wing of an aircraft.
4. The control surface of
claim 1
, wherein the actuation mechanism includes a bladder adjacent to a lower surface of the reinforced elastomer and a pneumatic pump attached to the bladder.
5. The control surface of
claim 1
, wherein the actuation mechanism includes a rigid surface adjacent to a lower surface of the reinforced elastomer surface and a mechanical actuator attached to the rigid surface.
6. The control surface of
claim 5
, wherein the rigid panel is pivotally attached to the aircraft along the perimeter.
7. A control surface for an aircraft comprising,
an elastomer surface on a surface the aircraft and attached to the aircraft along a perimeter;
an actuator attached to the aircraft and displacing the elastomer surface from a conformable position, where the elastomer surface essentially conforms to a moldline of the aircraft, to a protruding position, where the elastomer surface extends outside the moldline of the aircraft.
8. The control surface of
claim 7
, wherein the actuator is a mechanical mechanism.
9. The control surface of
claim 7
, wherein the actuator is a hydraulic mechanism.
10. The control surface of
claim 7
, wherein the actuator is a pneumatic mechanism.
11. The control surface of
claim 7
, wherein the actuator is a shape memory alloy system.
12. The control surface of
claim 7
, wherein the elastomer surface further includes a rigid panel.
13. A control surface for an aircraft comprising,
a rigid structural panel pivotally attached to the aircraft, the rigid structural panel having a long edge and a pair of short edges;
a pair of flexible struts, one of the pair of flexible struts extending between each of the pair of short edges and the aircraft;
a long elastomer panel attached to the aircraft and the long edge of the rigid structural panel; and
a pair of short elastomer panels, each of the pair of short elastomer panels attached to the aircraft, one of the pair of struts and one of the pair of short edges.
14. The control surface of
claim 13
, wherein the pair of short elastomer panels are reinforced by a plurality of rods.
15. The control surface of
claim 14
, wherein each of the pair of short elastomer panels include a flexible spine, having a plurality of bushings.
16. The control surface of
claim 15
, wherein each of the plurality of rods slide within one of the plurality of bushings.
17. A control surface for an aircraft having a rotor, the control surface comprising:
a rigid section pivotally attached to the rotor;
an actuator contained in the rotor and coupled to the rigid section; and
an elastomer surface attached to the rotor and to the rigid section.
18. The control surface of
claim 1
, wherein the elastomer surface is reinforced by a plurality of flexible rods.
US09/784,771 1997-09-17 2001-02-15 Control surface for an aircraft Expired - Lifetime US6349903B2 (en)

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US93294797A true 1997-09-17 1997-09-17
US09/517,838 US6209824B1 (en) 1997-09-17 2000-03-02 Control surface for an aircraft
US09/784,771 US6349903B2 (en) 1997-09-17 2001-02-15 Control surface for an aircraft

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US09/784,771 US6349903B2 (en) 1997-09-17 2001-02-15 Control surface for an aircraft

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Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20050011994A1 (en) * 2003-06-03 2005-01-20 Seiya Sakurai Multi-function trailing edge devices and associated methods
US20050216141A1 (en) * 2004-03-10 2005-09-29 Phillips Warren F Apparatus and method for reducing induced drag on aircraft and other vehicles
US20060124801A1 (en) * 2004-11-12 2006-06-15 Wood Jeffrey H Shape changing structure
US20070114329A1 (en) * 2005-11-21 2007-05-24 The Boeing Company Aircraft trailing edge devices, including devices with non-parallel motion paths, and associated methods
WO2007079855A1 (en) * 2005-12-21 2007-07-19 Eurocopter Deutschland Gmbh Rotor blade for a rotary wing aircraft
US20080149779A1 (en) * 2006-12-14 2008-06-26 Phillips Warren F Apparatus and method for twisting a wing to increase lift on aircraft and other vehicles
US7575807B1 (en) 2004-05-28 2009-08-18 Hrl Laboratories, Llc Hybrid active deformable material structure
US20090212158A1 (en) * 2007-06-29 2009-08-27 The Boeing Company Aircraft Systems with Shape Memory Alloy (SMA) Actuators, and Associated Methods
US7708231B2 (en) 2005-11-21 2010-05-04 The Boeing Company Aircraft trailing edge devices, including devices having forwardly positioned hinge lines, and associated methods
US7721999B2 (en) 2005-05-20 2010-05-25 The Boeing Company Aerospace vehicle fairing systems and associated methods
US7828250B2 (en) 2004-09-30 2010-11-09 The Boeing Company Leading edge flap apparatuses and associated methods
US20110303796A1 (en) * 2010-06-15 2011-12-15 The Boeing Company Morphing control surface transition
US20120153086A1 (en) * 2010-12-15 2012-06-21 United States Of America As Represented By The Administrator Of The National Aeronautics And Spac Elastically Deformable Side-Edge Link for Trailing-Edge Flap Aeroacoustic Noise Reduction
US20130277503A1 (en) * 2012-04-19 2013-10-24 Paul F. Geders Continuous moldline technology (cmt) elastomeric control surface
US9975623B2 (en) * 2016-03-08 2018-05-22 Northrop Grumman Systems Corporation Elastomeric transition

Families Citing this family (43)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6209824B1 (en) * 1997-09-17 2001-04-03 The Boeing Company Control surface for an aircraft
AU2002323407A1 (en) * 2001-08-24 2003-03-10 University Of Virginia Patent Foundation Reversible shape memory multifunctional structural designs and method of using and making the same
US6588709B1 (en) * 2002-03-20 2003-07-08 The Boeing Company Apparatus for variation of a wall skin
EP1531983A1 (en) * 2002-05-30 2005-05-25 University Of Virginia Patent Foundation Active energy absorbing cellular metals and method of manufacturing and using the same
US6877695B2 (en) * 2002-12-13 2005-04-12 The Boeing Company Hinge cover integration into door seal edges
WO2004110740A1 (en) * 2003-05-28 2004-12-23 University Of Virginia Patent Foundation Re- entrant cellular multifunctional structure for energy absorption and method of manufacturing and using the same
US6799739B1 (en) 2003-11-24 2004-10-05 The Boeing Company Aircraft control surface drive system and associated methods
US7424350B2 (en) * 2004-02-02 2008-09-09 The Boeing Company Vehicle control systems and corresponding sizing methods
US7357358B2 (en) * 2004-02-27 2008-04-15 The Boeing Company Aircraft leading edge device systems and corresponding sizing methods
US20050198777A1 (en) * 2004-03-09 2005-09-15 Mabe James H. Hinge apparatus with two-way controllable shape memory alloy (SMA) hinge pin actuator and methods of making two-way SMA parts
US7270305B2 (en) * 2004-06-15 2007-09-18 The Boeing Company Aircraft leading edge apparatuses and corresponding methods
US7494094B2 (en) * 2004-09-08 2009-02-24 The Boeing Company Aircraft wing systems for providing differential motion to deployable lift devices
US7322547B2 (en) * 2005-01-31 2008-01-29 The Boeing Company Aerospace vehicle leading edge slat devices and corresponding methods
US7338018B2 (en) * 2005-02-04 2008-03-04 The Boeing Company Systems and methods for controlling aircraft flaps and spoilers
US7246524B1 (en) 2005-05-02 2007-07-24 Sandia Corporation MEMS fluidic actuator
US7500641B2 (en) * 2005-08-10 2009-03-10 The Boeing Company Aerospace vehicle flow body systems and associated methods
US7444813B1 (en) 2005-08-19 2008-11-04 Hrl Laboratories; Llc Volume-conversion techniques for active-materials-based morphing structures
US7611099B2 (en) * 2005-09-07 2009-11-03 The Boeing Company Seal assemblies for use with drooped spoilers and other control surfaces on aircraft
US7611095B1 (en) 2006-04-28 2009-11-03 The Boeing Company Aerodynamic re-entry vehicle control with active and passive yaw flaps
ES2301360B1 (en) * 2006-05-16 2009-05-01 Airbus España, S.L. System sealing gap between the fuselage and the orientable height rudders horizontal stabilizer of an aircraft, extended with an aerodynamic fairing for sealing the opening between the fuselage and the orientable horizontal stabilizer.
WO2007139814A2 (en) 2006-05-23 2007-12-06 University Of Virginia Patent Foundation Method and apparatus for jet blast deflection
DE102006036389B4 (en) * 2006-08-02 2013-08-08 Eads Deutschland Gmbh Free gap aerodynamic profile, in particular rotor blade
US7954769B2 (en) 2007-12-10 2011-06-07 The Boeing Company Deployable aerodynamic devices with reduced actuator loads, and related systems and methods
US7766282B2 (en) * 2007-12-11 2010-08-03 The Boeing Company Trailing edge device catchers and associated systems and methods
US20090159749A1 (en) * 2007-12-19 2009-06-25 Achim Etzkorn Connector element for connecting two component parts
US8418962B2 (en) * 2008-01-19 2013-04-16 The Boeing Company Distribution of point loads in honeycomb panels
US8225478B2 (en) * 2008-01-30 2012-07-24 The Boeing Company Memory shape bushings and bearings
DE102008020390A1 (en) * 2008-04-23 2009-11-05 Airbus Deutschland Gmbh Hydrofoil for an aircraft
US8382045B2 (en) 2009-07-21 2013-02-26 The Boeing Company Shape-changing control surface
GB201018924D0 (en) * 2010-11-09 2010-12-22 Airbus Operations Ltd Seal
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US9227721B1 (en) 2011-10-07 2016-01-05 The United States of America as represented by the Administrator of the National Aeronautics & Space Administration (NASA) Variable camber continuous aerodynamic control surfaces and methods for active wing shaping control
US20130309089A1 (en) * 2012-05-16 2013-11-21 Casey Lyn Madsen Shape memory alloy active spars for blade twist
US9174723B2 (en) * 2013-04-03 2015-11-03 The Boeing Company Shape memory alloy rods for actuation of continuous surfaces
US9581145B2 (en) 2013-05-14 2017-02-28 The Boeing Company Shape memory alloy actuation system for variable area fan nozzle
US9428268B2 (en) * 2013-07-02 2016-08-30 Sikorsky Aircraft Corporation Flexbeam hinge for helicopter blade active trailing edge flap
DE102013012169A1 (en) * 2013-07-20 2015-01-22 Airbus Defence and Space GmbH Form variable gap cover between control surfaces and adjacent structural components of aircraft
FR3014410B1 (en) * 2013-12-11 2017-08-11 Airbus Operations Sas Hinge of aircraft provided between a movable panel and a supporting structure
GB201409424D0 (en) * 2014-05-28 2014-07-09 Agustawestland Ltd Device which is subject to fluid flow
US9981421B2 (en) 2014-07-16 2018-05-29 The Boeing Company Adaptive composite structure using shape memory alloys
US10000274B2 (en) * 2015-08-20 2018-06-19 The Boeing Company Mitigation of surface discontinuities between flight control surfaces and an airframe of an aircraft
EP3187412A1 (en) * 2015-12-30 2017-07-05 Airbus Defence and Space GmbH Aircraft wing with an adaptive shock control bump
US20180257759A1 (en) * 2017-03-08 2018-09-13 The Boeing Company Flexible control surfaces and related methods

Family Cites Families (46)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1942867A (en) 1932-05-17 1934-01-09 Goodrich Co B F Deicer for aeroplanes
US2152029A (en) 1936-05-28 1939-03-28 Robert W Cone Airplane wing construction
US2173262A (en) 1938-05-06 1939-09-19 Monegan Edgar Dana Deicer for airships
US2368702A (en) 1943-04-08 1945-02-06 Raymond D Bourne Streamlined hinge line for aircraft
US2504684A (en) 1946-01-30 1950-04-18 Goodrich Co B F Extensible structure for varying the configuration of an aircraft surface
US2716460A (en) 1952-02-28 1955-08-30 Raymond A Young Blade and control mechanism for helicopters
US2731221A (en) 1952-06-25 1956-01-17 North American Aviation Inc Aircraft door installation
SE331952B (en) 1967-12-22 1971-01-18 Ingelman Sundberg A
US4296900A (en) 1979-04-23 1981-10-27 Vought Corporation Airfoil construction
US4461913A (en) * 1981-11-24 1984-07-24 Tennessee Valley Authority Production of urea phosphate
US4461611A (en) 1982-05-20 1984-07-24 United Technologies Corporation Helicopter rotor with blade trailing edge tabs responsive to control system loading
US4427169A (en) 1982-06-08 1984-01-24 Boeing Commercial Airplane Company Variable camber flap end seal
US4429844A (en) 1982-09-29 1984-02-07 The Boeing Company Variable camber aircraft wing tip
US4706913A (en) 1982-12-28 1987-11-17 The Boeing Company Variable camber leading edge assembly for an airfoil
US4966802A (en) 1985-05-10 1990-10-30 The Boeing Company Composites made of fiber reinforced resin elements joined by adhesive
US4892626A (en) 1988-01-21 1990-01-09 Boeing Company Method for plating one side of a woven fabric sheet
US5094412A (en) 1989-10-13 1992-03-10 Bell Helicopter Textron Inc. Flaperon system for tilt rotor wings
US5222699A (en) 1990-04-16 1993-06-29 Ltv Aerospace And Defense Company Variable control aircraft control surface
US5481184A (en) 1991-12-31 1996-01-02 Sarcos Group Movement actuator/sensor systems
US5374011A (en) 1991-11-13 1994-12-20 Massachusetts Institute Of Technology Multivariable adaptive surface control
US5288039A (en) 1992-07-29 1994-02-22 Delaurier James D Spanwise graded twist panel
US5326050A (en) 1993-02-08 1994-07-05 The United States Of America As Represented By The Administrator Of National Aeronautics And Space Administration Aerodynamic surface distension system for high angle of attack forebody vortex control
US5366176A (en) 1993-04-16 1994-11-22 United Technologies Corp. Feedback-stabilized aerodynamically overbalanced lifting/control surface for aircraft
US5367970A (en) 1993-09-27 1994-11-29 The United States Of America As Represented By The Secretary Of The Navy Controllable camber fin
US5662294A (en) 1994-02-28 1997-09-02 Lockheed Martin Corporation Adaptive control surface using antagonistic shape memory alloy tendons
US5487351A (en) 1995-01-13 1996-01-30 The United States Of America As Represented By The Secretary Of The Navy Control surface for underwater vehicle
JP2617281B2 (en) 1995-03-27 1997-06-04 株式会社コミュータヘリコプタ先進技術研究所 Flap with a helicopter rotor
AU5923096A (en) 1995-05-19 1996-11-29 Mcdonnell Douglas Corporation Airfoil lift management device
US5803405A (en) 1995-06-07 1998-09-08 Northrop Grumman Corporation Expandable aircraft section
US5794893A (en) 1995-06-07 1998-08-18 Northrop Grumman Corporation Elastomeric transition for aircraft control surface
US5975463A (en) 1995-12-21 1999-11-02 Mcdonnell Douglas Expandable aircraft bay and method
US5700337A (en) 1996-03-01 1997-12-23 Mcdonnell Douglas Corporation Fabrication method for composite structure adapted for controlled structural deformation
US5810291A (en) 1996-03-19 1998-09-22 Geiger; Michael Watson Continuous moldline technology system
US5839700A (en) 1996-06-03 1998-11-24 The United States Of America As Represented By The Secretary Of The Navy Articulated fin
US6048581A (en) 1996-09-24 2000-04-11 Mcdonnell Douglas Corporation Elastic ground plane and method
US5918834A (en) 1997-02-27 1999-07-06 Mcdonnell Douglas Retractable sensor system for an aircraft
US5947422A (en) 1997-04-29 1999-09-07 Mcdonnell Douglas Tail for an aircraft
US5979828A (en) 1997-04-30 1999-11-09 Mcdonnell Douglas Apparatus for eliminating gaps in an aircraft
US5941480A (en) 1997-05-08 1999-08-24 Mcdonnell Douglas Hinge line skin system for an aircraft
US5896191A (en) 1997-05-13 1999-04-20 Mcdonnell Douglas Reinforced elastomer panel with embedded strain and pressure sensors
US5927651A (en) 1997-05-15 1999-07-27 Mcdonnell Douglas Expandable fuel cell
US5931422A (en) 1997-06-09 1999-08-03 Mcdonnell Douglas Active reinforced elastomer system
US5892877A (en) 1997-06-30 1999-04-06 Tii Industries, Inc. Optical fiber strain relief system
US5947417A (en) 1997-07-25 1999-09-07 Mcdonnell Douglas Fairing for an expandable bay
US5913494A (en) 1997-07-25 1999-06-22 Mcdonnell Douglas Blade seal for an aircraft
US6209824B1 (en) * 1997-09-17 2001-04-03 The Boeing Company Control surface for an aircraft

Cited By (29)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7243881B2 (en) * 2003-06-03 2007-07-17 The Boeing Company Multi-function trailing edge devices and associated methods
US20050011994A1 (en) * 2003-06-03 2005-01-20 Seiya Sakurai Multi-function trailing edge devices and associated methods
US20050216141A1 (en) * 2004-03-10 2005-09-29 Phillips Warren F Apparatus and method for reducing induced drag on aircraft and other vehicles
US6970773B2 (en) 2004-03-10 2005-11-29 Utah State University Apparatus and method for reducing induced drag on aircraft and other vehicles
US7575807B1 (en) 2004-05-28 2009-08-18 Hrl Laboratories, Llc Hybrid active deformable material structure
US7828250B2 (en) 2004-09-30 2010-11-09 The Boeing Company Leading edge flap apparatuses and associated methods
US20060124801A1 (en) * 2004-11-12 2006-06-15 Wood Jeffrey H Shape changing structure
US7216831B2 (en) * 2004-11-12 2007-05-15 The Boeing Company Shape changing structure
US7721999B2 (en) 2005-05-20 2010-05-25 The Boeing Company Aerospace vehicle fairing systems and associated methods
US8567726B2 (en) 2005-11-21 2013-10-29 The Boeing Company Aircraft trailing edge devices, including devices having forwardly positioned hinge lines, and associated methods
US20070114329A1 (en) * 2005-11-21 2007-05-24 The Boeing Company Aircraft trailing edge devices, including devices with non-parallel motion paths, and associated methods
US7708231B2 (en) 2005-11-21 2010-05-04 The Boeing Company Aircraft trailing edge devices, including devices having forwardly positioned hinge lines, and associated methods
US20090269198A1 (en) * 2005-12-21 2009-10-29 Eurocopter Deutschland Gmbh Rotor blade for a rotary wing aircraft
WO2007079855A1 (en) * 2005-12-21 2007-07-19 Eurocopter Deutschland Gmbh Rotor blade for a rotary wing aircraft
US8162607B2 (en) 2005-12-21 2012-04-24 Eurocopter Deutschland Gmbh Rotor blade for a rotary wing aircraft
US7883060B2 (en) 2006-12-14 2011-02-08 Utah State University Apparatus and method for twisting a wing to increase lift on aircraft and other vehicles
US20080149779A1 (en) * 2006-12-14 2008-06-26 Phillips Warren F Apparatus and method for twisting a wing to increase lift on aircraft and other vehicles
US7878459B2 (en) * 2007-06-29 2011-02-01 The Boeing Company Aircraft systems with shape memory alloy (SMA) actuators, and associated methods
US20090212158A1 (en) * 2007-06-29 2009-08-27 The Boeing Company Aircraft Systems with Shape Memory Alloy (SMA) Actuators, and Associated Methods
US8118264B2 (en) * 2007-06-29 2012-02-21 The Boeing Company Shape memory alloy actuator
US20110101170A1 (en) * 2007-06-29 2011-05-05 The Boeing Company Shape memory alloy actuator
US8342447B2 (en) * 2010-06-15 2013-01-01 The Boeing Company Morphing control surface transition
US20110303796A1 (en) * 2010-06-15 2011-12-15 The Boeing Company Morphing control surface transition
US20120153086A1 (en) * 2010-12-15 2012-06-21 United States Of America As Represented By The Administrator Of The National Aeronautics And Spac Elastically Deformable Side-Edge Link for Trailing-Edge Flap Aeroacoustic Noise Reduction
US8695925B2 (en) * 2010-12-15 2014-04-15 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Elastically deformable side-edge link for trailing-edge flap aeroacoustic noise reduction
US20130277503A1 (en) * 2012-04-19 2013-10-24 Paul F. Geders Continuous moldline technology (cmt) elastomeric control surface
JP2013224136A (en) * 2012-04-19 2013-10-31 Boeing Co:The Continuous moldline technology (cmt) elastomeric control surface
US8814100B2 (en) * 2012-04-19 2014-08-26 The Boeing Company Continuous moldline technology (CMT) elastomeric control surface
US9975623B2 (en) * 2016-03-08 2018-05-22 Northrop Grumman Systems Corporation Elastomeric transition

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