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US20040245393A1 - Bendable wing for micro air vehicle - Google Patents

Bendable wing for micro air vehicle Download PDF

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Publication number
US20040245393A1
US20040245393A1 US10/731,777 US73177703A US2004245393A1 US 20040245393 A1 US20040245393 A1 US 20040245393A1 US 73177703 A US73177703 A US 73177703A US 2004245393 A1 US2004245393 A1 US 2004245393A1
Authority
US
United States
Prior art keywords
wing
micro air
air vehicle
layer
inches
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.)
Abandoned
Application number
US10/731,777
Other languages
English (en)
Inventor
Peter Ifju
Kyu-Ho Lee
Roberto Albertani
Shawn Mitryk
Frank Boria
Mujahid Abdulrahim
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.)
University of Florida Research Foundation Inc
Original Assignee
University of Florida
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 University of Florida filed Critical University of Florida
Priority to US10/731,777 priority Critical patent/US20040245393A1/en
Assigned to UNIVERSITY OF FLORIDA RESEARCH FOUNDATION, INCORPORATED reassignment UNIVERSITY OF FLORIDA RESEARCH FOUNDATION, INCORPORATED ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: UNIVERSITY OF FLORIDA
Publication of US20040245393A1 publication Critical patent/US20040245393A1/en
Assigned to UNITED STATES AIR FORCE reassignment UNITED STATES AIR FORCE CONFIRMATORY LICENSE (SEE DOCUMENT FOR DETAILS). Assignors: UNIVERSITY OF FLORIDA
Priority to US11/510,013 priority patent/US7331546B2/en
Abandoned legal-status Critical Current

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Classifications

    • A—HUMAN NECESSITIES
    • A63—SPORTS; GAMES; AMUSEMENTS
    • A63H—TOYS, e.g. TOPS, DOLLS, HOOPS OR BUILDING BLOCKS
    • A63H27/00—Toy aircraft; Other flying toys
    • A63H27/007—Collapsible wings, e.g. for catapult aeroplanes
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U30/00—Means for producing lift; Empennages; Arrangements thereof
    • B64U30/10—Wings
    • B64U30/12—Variable or detachable wings, e.g. wings with adjustable sweep
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U50/00—Propulsion; Power supply
    • B64U50/10—Propulsion
    • B64U50/12—Propulsion using turbine engines, e.g. turbojets or turbofans
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/25—Fixed-wing aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U2101/00—UAVs specially adapted for particular uses or applications
    • B64U2101/30—UAVs specially adapted for particular uses or applications for imaging, photography or videography
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U50/00—Propulsion; Power supply
    • B64U50/10—Propulsion
    • B64U50/11—Propulsion using internal combustion piston engines
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U50/00—Propulsion; Power supply
    • B64U50/10—Propulsion
    • B64U50/13—Propulsion using external fans or propellers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U70/00—Launching, take-off or landing arrangements
    • B64U70/20—Launching, take-off or landing arrangements for releasing or capturing UAVs in flight by another aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U80/00—Transport or storage specially adapted for UAVs
    • B64U80/70—Transport or storage specially adapted for UAVs in containers

Definitions

  • This invention is directed generally to micro air vehicles, and more particularly, to wing configurations for micro air vehicles.
  • Micro air vehicles can trace their beginnings to model airplanes, which typically resemble full size airplanes. Micro air vehicles generally encompass all relatively small unmanned flying objects, such as those having wingspans less than about 36 inches. Micro air vehicles are often powered by small gasoline or electric propeller driven engines. Micro air vehicles are relatively lightweight vehicles capable of being used for a variety of purposes, such as for recreation, reconnaissance, and other purposes. Because of their small size, micro air vehicles lend themselves to a variety of uses.
  • micro air vehicles have fixed, rigid wings that are incapable of having their wing span reduced for storage.
  • Micro air vehicles having fixed wings are often difficult to store and do not lend themselves for storage in a knapsack or other item typically carried by military personnel in reconnaissance missions.
  • Some micro air vehicles have collapsible wings that pivot about one or more pivot points.
  • these micro air vehicles require a series of assembly steps to transform the micro air vehicle from a deployable condition to a storage condition, and vice versa.
  • micro air vehicles Because of their small size and ability to go relatively unnoticed, micro air vehicles have been outfitted with cameras, both still frame cameras and video cameras, and used in hostile areas for reconnaissance purposes. However, many of the micro air vehicles are inconvenient to be carried by military personnel because of their cumbersome wing span and shape. Thus, a need exists for a micro air vehicle having wings capable of having their wingspan reduced. In addition, other micro air vehicles having wings with reduceable wingspans require a plurality of assembly steps to transform the wings of the micro air vehicle from a deployable condition to a storage condition, and vice versa. Such requirements prevent these micro air vehicles from being deployed quickly and without human interaction.
  • micro air vehicles were able to be transformed between a storage condition and a deployable condition without assembly steps, the micro air vehicles could be used in a greater variety of applications. Thus, a need exists for a micro air vehicle capable of being transformed between a storage condition and a deployable condition without assembly steps.
  • This invention is directed to a micro air vehicle having a bendable wing enabling the micro air vehicle to be stored in containers substantially smaller than the micro air vehicle and enabling the bendable wing to go from a storage condition to a deployable condition without assembly or user interaction. Rather, the forces used to hold the wing tips of the wing need only be abated.
  • the micro air vehicle may be formed from a central body and one or more wings.
  • the wing may be formed from one or more layers of a resilient material having a camber forming a concave surface facing downward.
  • the wing may be bendable from a steady state position in a first direction such that tips of the wing may be bent toward the concave surface but not in a second direction that is generally opposite to the first direction. In other words, the wing may bent downwards but not upwards.
  • the wing may also be capable of returning to the steady state position upon release the tips of the wing.
  • the wing may have a camber such that a bottom surface of the wing has a generally concave configuration when viewed parallel to a longitudinal axis of the wing.
  • the camber may contribute to the stability of flight of a micro air vehicle to which the wing is attached and allow the wing to be bent downwards by not upwards.
  • the wing may absorb and transfer uplift forces to the central body and allow the wing to be bent downward for storage.
  • the wing may be formed from a support structure covered by a layer of material.
  • the support structure may be formed from one or more ribs, which may be, but are not required to be, generally parallel to each other.
  • the layer of material covering the support structure may be, but is not limited to being, latex or other appropriate materials.
  • the bendable wing enables the wing to be stored is containers smaller than the micro air vehicle to which the wing is attached.
  • the bendable wing having a wing span of about ten inches may be bent around the central body of a micro air vehicle so that the wing may be stored in a container having a diameter of about three inches.
  • Such a characteristic enables a micro air vehicle to which the bendable wing is attached to be used for reconnaissance missions, for deployment from missiles just prior to impact for bomb damage assessment, and carried by special forces operatives in the field on their person.
  • An advantage of this invention is that a micro air vehicle incorporating the bendable wing of this invention may be stored in a small container and deployed without any actions taken to assemble the wings other than to release the tips from restraint. Releasing the wings enables the wings to return to the steady state position.
  • Another advantage of this invention is that the bendable wing has sufficient stiffness to absorb and transfer uplift forces to the body while enabling the wings to be bent downwardly for storage.
  • Yet another advantage of this invention is that by being able to be stored in such a small container, a micro air vehicle may be conveniently carried on a person, such as military personnel, without consuming much room.
  • Still another advantage of this invention is that the bendable wing may be produced relatively inexpensively.
  • Another advantage of this invention is that the wing is durable and capable of withstanding crash landings.
  • FIG. 1 is a perspective view of a top side of an embodiment of this invention
  • FIG. 2 is a perspective view of the embodiment shown in FIG. 1 with a portion of the bendable wing being bent around a central body of a micro air vehicle as a result of a downward force applied to a tip of the wing;
  • FIG. 3 is a front view of a micro air vehicle inserted into a small diameter tube with both sides of the bendable wing bent around the central body of the micro air vehicle;
  • FIG. 4 is a perspective view of an alternative embodiment of the bendable wing of the micro air vehicle
  • FIG. 5 is a perspective view of the alternative embodiment of the bendable wing shown in FIG. 4 in flexed storage condition with the tips of the wing bent around the central body of the micro air vehicle;
  • FIG. 6 is a perspective view of yet another alternative configuration of the bendable wing of this invention.
  • FIG. 7 is a front view of the embodiment shown in FIG. 6;
  • FIG. 8 is a perspective view of still another embodiment of this invention.
  • FIG. 9 is a front view of another embodiment of this invention.
  • FIG. 10 is a perspective view of a top side of the embodiment shown in FIG. 9.
  • This invention is directed to a wing 12 for a micro air vehicle 10 , as shown in FIGS. 1-10, that is bendable to enable the wing 12 to be easily stored in, for instance, a tube or other structure.
  • the wing 12 may be attached to a body 14 that may or may not house an engine capable of providing rotational motion to a propeller 16 .
  • the engine may be, but is not limited to, one of many conventional engines used to power miniature aircraft.
  • Body 14 may include a tail 17 for controlling the micro air vehicle 10 .
  • the tail 17 may be positioned generally orthogonal to the wing 12 , as shown in FIGS. 1, 2, 8 , and 10 , generally parallel to the wing 12 , as shown in FIGS. 4 and 5, or in another position.
  • Micro air vehicle 10 may include other components that are typically found on miniature aircraft.
  • wing 12 may be formed one or more layers formed from resilient materials such that the wing 12 is bendable from a steady state position.
  • the wing 12 may be bent in a first direction, as shown in FIG. 5, such that tips 13 of the wing 12 may be bent downwardly toward a concave surface 15 but not substantially in a second direction that is generally opposite to the first direction.
  • the resilient materials have a high degree of elasticity and are therefore capable of returning the wing 12 to the steady state position upon release of the tips 13 of the wing 12 .
  • the camber of the wing 12 is configured such that a bottom surface of the wing 12 forms a concave surface.
  • Wing 12 may be formed from a leading edge portion 18 , a rear portion 19 , and a trailing edge 25 .
  • Leading edge portion 18 , rear portion 19 , and trailing edge 25 may together form a monolithic structure formed from the same material, or may be different structures formed from the same or different materials and coupled together.
  • the wing 12 as shown in FIG. 4, may be formed from a single layer of material, and, in alternative embodiments, may be formed from two or more layers of material.
  • the wing 12 may be formed from resilient materials, such as, but not limited to: fiber reinforced laminates and fabrics, such as, carbon fiber reinforced polymers, glass reinforced polymers, and aramid reinforced polymers; sheet metal, such as, spring steel, high strength aluminum, stainless steel, and titanium; foam materials; and plastics.
  • leading edge portion 18 may be formed from pre-impregnated carbon/epoxy fiber cloth, which provides sufficient strength to absorb forces encountered from wind gusts while maintaining a sufficiently light weight.
  • the leading edge 18 may be formed from an aramid fiber/epoxy mixture and at least a portion of the remainder of the rear portion 19 may be formed from a single layer of carbon fiber/epoxy weave.
  • Wing 12 is bendable so that the overall size of micro air vehicle 10 may be reduced for storage.
  • Wing 12 may be bent by applying a downward force to the tips 13 of wing 12 , as shown in FIGS. 2 and 5. While wing 21 may be bent downwards, wing 12 resists being bent upwardly as a result of the camber of leading edge portion 18 or the wing 12 , or both. More specifically, the leading edge portion 18 is stiff when loaded with upwardly directed loads, such as aerodynamic loads.
  • the camber provides wing 12 with the structural stability to substantially prevent wing 12 from bending upwardly when subjected to an upwardly directed load.
  • wing 12 can be bent with a downwardly applied force but not with an upwardly applied force because of the configuration of the wing 12 and materials used to form the wing 12 .
  • the wing 12 may be bent so that a substantial portion of the wing 12 may be wrapped around to an opposite side of the body 14 from the steady state position shown in FIGS. 1 and 5.
  • rear portion 19 may be formed from ribs 20 and a skin 22 .
  • Ribs 20 may be formed from unidirectional fibers, such as, but not limited to, carbon fiber strands, and skin 22 may be formed from a lightweight, thin material, such as, but not limited to, latex and other appropriate materials.
  • Ribs 20 may include members positioned generally parallel to body 14 .
  • Rear portion 19 may or may not be concave when viewed from below, as shown in FIG. 10. If rear portion 19 is concave, the concave shape of rear portion 19 may or may not be equal to the concave shape of leading edge portion 18 . If the rear portion 19 is not concave, the leading edge portion 18 has a camber forming a concave face on the bottom surface 15 of the wing 12 . The shape of rear portion 19 may be any shape capable of providing aerodynamic lift when coupled to leading edge portion 18 .
  • Rear portion 19 may include a riser 21 at the rear portion of wing 12 . The riser 21 may form a concave portion on an upper surface 23 of the wing 12 in the rear portion 19 . The riser 21 may extend completely across the trailing edge 25 or may extend across only a portion of the trailing edge 25 .
  • leading edge 18 has a greater thickness than the thickness of the rear portion 19 , wherein the characteristic that wing 12 may be bent downwards but not upwards is attributable to the configuration of leading edge portion 18 .
  • leading edge portion 18 and rear portion 19 may or may not have the same thickness, depending on the strength of the materials used to form leading edge portion 18 and rear portion 19 .
  • Wing 12 may have a wing span between about six inches and about twenty four inches. In one embodiment, wing 12 may have a ten inch wing span enabling it to be stored in a cylinder 24 , as shown in FIG. 3, having a diameter less than three inches. Having the capability of being stored in such small cylinders enables micro air vehicle 10 to be used for reconnaissance missions, for deployment from missiles just prior to impact for bomb damage assessment, and carried by special forces operatives in the field on their person. Micro-air vehicle 10 may be used in other applications as well. In other embodiments, wing 12 may vary in length between about three inches and about 24 inches. As shown in FIGS. 7 and 9, the micro air vehicle 10 may include a camera 30 , which may be, but is not limited to being, a video camera, a still photography camera, or other audio or visual recording devices.
  • a camera 30 which may be, but is not limited to being, a video camera, a still photography camera, or other audio or visual recording devices.
  • wing 12 shown in FIGS. 1-10 and the elastic materials from which the wing 12 is formed enables wing 12 to return to its original, steady state shape, as shown in FIG. 1, 4, and 6 - 10 , after being removed from storage without additional steps or use of mechanical mechanisms, such as servos, motors, piezoelectrics, or shape memory alloys. Instead, wing 12 returns to its original shape because of the elastic characteristics of the wing 12 causes the wing 12 to remain under forces when bent from its original position. These forces abate only when wing 12 is returned to its original position.
  • the materials used to form the wing 12 have great flexibility and elasticity and bend rather than permanently yielding. Thus, micro air vehicle 10 needs only to be removed from a storage container 24 , as shown in FIG. 3, for wing 12 to return to its original shape.
  • the wing 12 is configured such that the wing 12 may be bent severely about the body 14 of the micro air vehicle 10 . In fact, the wing 12 may be bent so severely that the wing tips 13 and wing 12 are rolled up around the body 14 , as shown in FIG. 5. This configuration is very advantageous. However, the wing 12 also prevents substantial bending in the opposite direction. This is not to say that the wing will not flex during use. Rather, the wing 12 will flex, or bow, in the opposite direction under normal stresses associated with flight. However, the wing 12 will not bend substantially in the opposite direction.
  • wing 12 possess numerous aerodynamic advantages including: reduced drag due to the curvature of leading edge portion 18 ; and improved wind gust rejection due to adaptive washout as a result of wing 12 flexing, twisting and decambering.
  • This configuration of wing 12 allows micro air vehicle 12 to fly more smoothly than conventional rigid wing designs in smooth and gusty wind conditions.
  • Wing 12 is also more durable than rigid wings because the configuration of wing 12 bends upon impact with the ground or other structure, rather than breaking.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Remote Sensing (AREA)
  • Toys (AREA)
  • Fittings On The Vehicle Exterior For Carrying Loads, And Devices For Holding Or Mounting Articles (AREA)
US10/731,777 2002-12-09 2003-12-09 Bendable wing for micro air vehicle Abandoned US20040245393A1 (en)

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Application Number Priority Date Filing Date Title
US10/731,777 US20040245393A1 (en) 2002-12-09 2003-12-09 Bendable wing for micro air vehicle
US11/510,013 US7331546B2 (en) 2002-12-09 2006-08-25 Bendable wing for micro air vehicle

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US43192002P 2002-12-09 2002-12-09
US10/731,777 US20040245393A1 (en) 2002-12-09 2003-12-09 Bendable wing for micro air vehicle

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US11/510,013 Expired - Lifetime US7331546B2 (en) 2002-12-09 2006-08-25 Bendable wing for micro air vehicle

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AU (1) AU2003302245A1 (fr)
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US20060284005A1 (en) * 2002-12-09 2006-12-21 University Of Florida Research Foundation, Inc. Bendable wing for micro air vehicle
US20100282906A1 (en) * 2009-05-10 2010-11-11 Raytheon Company Multi-layer metal/shape memory polymer roll-up wing structures for fitment-constrained air vehicles
CN102167155A (zh) * 2011-04-01 2011-08-31 哈尔滨工业大学 一种机翼可扭转飞行器
US8201773B1 (en) * 2008-07-02 2012-06-19 The United States Of America As Represented By Secretary Of The Navy Flexible self-erecting substructures for sensor networks
US20130306789A1 (en) * 2012-05-18 2013-11-21 Textron Systems Corporation Folding configuration for air vehicle
US8698059B2 (en) * 2012-05-03 2014-04-15 Raytheon Company Deployable lifting surface for air vehicle
CN110435875A (zh) * 2019-09-04 2019-11-12 吉林大学 一种仿生柔性变形机翼
US20210061460A1 (en) * 2019-09-04 2021-03-04 Jilin University Rigid-flexible coupled uav morphing wing and additive manufacturing method thereof
CN114802744A (zh) * 2022-04-28 2022-07-29 北京航空航天大学 一种基于复合材料螺旋结构的微型扑翼飞行器仿生翼及制备方法
WO2023043378A3 (fr) * 2021-09-17 2023-04-27 Singapore University Of Technology And Design Monocoptère

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US8720822B2 (en) * 2007-06-13 2014-05-13 Aurora Flight Sciences Corporation Wing load alleviation structure
KR101773206B1 (ko) * 2009-06-05 2017-08-30 에어로바이론먼트, 인크. 비행체 비행 기계장치 및 제어 방법
US8167234B1 (en) 2010-03-21 2012-05-01 Michael Moore Insect-like micro air vehicle having perching, energy scavenging, crawling, and offensive payload capabilities
EP2377757B1 (fr) 2010-04-19 2013-05-29 Gatewing NV Drone
US8700233B1 (en) 2010-07-29 2014-04-15 The United States Of America As Represented By The Secretary Of The Air Force Method for shaping wing velocity profiles for control of flapping wing micro air vehicles
US9669925B2 (en) 2011-02-16 2017-06-06 Aerovironment, Inc. Air vehicle flight mechanism and control method for non-sinusoidal wing flapping
US20140239118A1 (en) * 2013-02-22 2014-08-28 Itzhak Sapir Method and Apparatus for Foldable Wing UAV
US20150367932A1 (en) * 2013-10-05 2015-12-24 Dillon Mehul Patel Delta M-Wing Unmanned Aerial Vehicle
US10017248B2 (en) * 2014-04-28 2018-07-10 University Of Maryland, College Park Flapping wing aerial vehicles
US10287000B2 (en) * 2014-07-25 2019-05-14 Hyalta Aeronautics, Inc. Hybrid lighter-than-air vehicle
CN105383683B (zh) * 2015-11-12 2017-08-18 中国人民解放军国防科学技术大学 一种三段式抗冲击型无人机机翼
WO2021146569A1 (fr) * 2020-01-15 2021-07-22 Northeastern University Structures d'aile de bras pour robots aériens
JP7742101B2 (ja) * 2021-07-08 2025-09-19 国立研究開発法人宇宙航空研究開発機構 モーフィング翼、飛行制御装置、飛行制御方法、及びプログラム
US12134043B2 (en) * 2021-07-29 2024-11-05 Terra Nova Media, LLC Inflatable plane assembly
CN116674747B (zh) * 2023-08-03 2023-10-20 西南石油大学 一种柔性扑翼与涵道螺旋桨混合驱动的仿蝠鲼浮空飞行器

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US7331546B2 (en) 2008-02-19
US20060284005A1 (en) 2006-12-21
CA2550146A1 (fr) 2004-07-22

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