JP4478509B2 - High lift generator - Google Patents

High lift generator Download PDF

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JP4478509B2
JP4478509B2 JP2004165258A JP2004165258A JP4478509B2 JP 4478509 B2 JP4478509 B2 JP 4478509B2 JP 2004165258 A JP2004165258 A JP 2004165258A JP 2004165258 A JP2004165258 A JP 2004165258A JP 4478509 B2 JP4478509 B2 JP 4478509B2
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main wing
flap
outer skin
plate
high lift
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JP2005343310A (en
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雅文 佐々木
敏充 荻巣
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Subaru Corp
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Fuji Jukogyo KK
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    • 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
    • Y02T50/40—Weight reduction

Description

本発明は、高揚力発生装置に関し、特に、コアンダ効果による循環制御を実現させて高揚力を発生させる高揚力発生装置に関する。   The present invention relates to a high lift generating device, and more particularly to a high lift generating device that realizes circulation control by the Coanda effect and generates high lift.

現在、航空機の離着陸時（低速飛行時）に高揚力を発生させるための高揚力発生装置が種々提案され、実用化されている。従来の高揚力発生装置としては、図３（ａ）に示すように主翼１００の後縁に取り付けられたファウラフラップ２００が提案されている。ファウラフラップ２００は、クランク２１０、カム２２０、レール２３０、リンク２４０等からなるメカニカルな機構によって、図３（ｂ）に示すように主翼１００の後縁から後方及び下方に延出するように構成され、揚力面を増大させて高揚力を発生させるものである。   Currently, various high-lift generators for generating high lift during aircraft take-off and landing (during low-speed flight) have been proposed and put into practical use. As a conventional high lift generator, a foul wrap 200 attached to the rear edge of the main wing 100 as shown in FIG. The fowl lap 200 is configured to extend rearward and downward from the rear edge of the main wing 100 as shown in FIG. 3B by a mechanical mechanism including a crank 210, a cam 220, a rail 230, a link 240, and the like. The lift surface is increased to generate a high lift force.

また、近年においては、主翼の後縁に沿ってスパン方向に延在する円筒体を配置し、主翼内に導いた高速のジェット気流をこの円筒体の上面から周方向に噴射することにより、コアンダ効果を利用して円筒体の外周に沿った強い循環流を発生させて高揚力を発生させる高揚力発生装置が提案されている（例えば、特許文献１参照。）。かかる高揚力発生装置は、主翼の後縁に配置される円筒体を前後に移動させるためのメカニカルな機構を備えており、巡航時には円筒体を主翼の内部に収納して、抵抗の増大や巡航速度の低下を抑制することができる。
特開平９−１１９９１号公報 In recent years, a cylindrical body extending in the span direction is arranged along the trailing edge of the main wing, and a high-speed jet stream guided into the main wing is jetted from the upper surface of the cylindrical body in the circumferential direction. There has been proposed a high lift generator that generates a high lift by generating a strong circulating flow along the outer periphery of a cylindrical body by using the effect (see, for example, Patent Document 1). Such a high lift generator is equipped with a mechanical mechanism for moving the cylindrical body arranged at the trailing edge of the main wing back and forth. During cruising, the cylindrical body is housed inside the main wing to increase resistance and cruise. A decrease in speed can be suppressed.
JP-A-9-11991

しかし、従来の高揚力発生装置であるファウラフラップ２００は、図３に示すように複雑な機構（クランク２１０、カム２２０、レール２３０、リンク２４０等）を有しているため、製造費用やメンテナンス費用が嵩むという問題がある。また、特許文献１に記載の高揚力発生装置も、主翼の後縁に配置された円筒体を移動させるための大掛かりな機構（ガイドレールやリンク等）を有しているため、製造費用やメンテナンス費用は多大なものとなる。   However, the Fowl Lap 200, which is a conventional high lift generator, has a complicated mechanism (crank 210, cam 220, rail 230, link 240, etc.) as shown in FIG. There is a problem that increases. Further, the high lift generating device described in Patent Document 1 also has a large mechanism (guide rail, link, etc.) for moving the cylindrical body arranged at the trailing edge of the main wing, so that the manufacturing cost and maintenance are high. The cost is tremendous.

また、従来のメカニカルな高揚力発生装置においては、フラップ駆動用に油圧アクチュエータが多用されているが、かかる油圧アクチュエータを使用すると、配管や作動油の重量によって機体の軽量化が妨げられることとなり、しかも作動油漏れが懸念されるため信頼性にも問題があった。また、従来のメカニカルな高揚力発生装置を使用すると、フラップの駆動時に発生する構造的な間隙（ギャップ）や、フラップの端部から発生する渦に起因して、エアフレームノイズが発生する場合があった。   Further, in the conventional mechanical high lift generator, hydraulic actuators are frequently used for flap driving, but if such hydraulic actuators are used, weight reduction of the airframe will be hindered by the weight of piping and hydraulic oil, In addition, there was a problem in reliability because there was concern about hydraulic oil leakage. If a conventional mechanical high lift generator is used, air frame noise may occur due to structural gaps (gap) generated when the flap is driven or vortices generated from the end of the flap. there were.

本発明の課題は、高揚力発生装置において、製造費用及びメンテナンス費用を格段に低減するとともに大幅な軽量化を図りながら、コアンダ効果による循環制御を実現させて高揚力を効果的に発生させることである。   An object of the present invention is to generate high lift effectively by realizing the circulation control by the Coanda effect while significantly reducing the manufacturing cost and the maintenance cost in the high lift generating device and greatly reducing the weight. is there.

以上の課題を解決するために、請求項１に記載の発明は、主翼の上面の後方に形成される噴射口からジェット気流を噴射させてコアンダ効果による循環制御を実現させる高揚力発生装置において、前記主翼の上面の後縁端から下方に離隔した位置に配置され円弧形状に成形された翼型部と、柔軟性を有し前記翼型部の少なくとも上面を被覆する外皮部と、を有するフラップと、前記フラップの前記外皮部の上方部分を上方に移動させて前記主翼の上面の後縁端と前記外皮部の上面とを連接させるような付勢力を前記外皮部に加えるバイアスバネと、前記フラップの前記外皮部の上方部分を下方に移動させて前記翼型部に密着させるような付勢力を前記外皮部に加える形状記憶合金製バネと、を備え、特定温度以上に加熱された前記形状記憶合金製バネの付勢力により、前記主翼の上面の後縁端と前記フラップの前記外皮部の上面との間に前記噴射口を形成するとともに、前記フラップの前記外皮部の上方部分を前記翼型部に密着させることにより前記フラップを円弧形状にすることを特徴とする。   In order to solve the above-described problems, the invention according to claim 1 is a high lift generator that realizes circulation control by the Coanda effect by injecting a jet stream from an injection port formed behind the upper surface of the main wing. A flap having an airfoil portion disposed in a position spaced downward from a rear edge of the upper surface of the main wing and formed in an arc shape, and a skin portion having flexibility and covering at least the upper surface of the airfoil portion And a bias spring that applies an urging force to the outer skin portion so as to connect the rear edge of the upper surface of the main wing and the upper surface of the outer skin portion by moving the upper portion of the outer skin portion of the flap upward. A shape memory alloy spring that applies an urging force to the outer skin portion so as to move the upper portion of the outer skin portion of the flap downward and bring it into close contact with the airfoil portion, and the shape heated above a specific temperature Memory The urging force of the spring is used to form the injection port between the rear edge of the upper surface of the main wing and the upper surface of the outer skin portion of the flap, and the upper portion of the outer skin portion of the flap is the airfoil portion. The flap is formed into a circular arc shape by being brought into close contact therewith.

請求項１に記載の発明によれば、主翼の上面の後縁端から若干下方に離隔した位置に配置された翼型部と、この翼型部の少なくとも上面を覆うように配置された柔軟性を有する外皮部と、を有するフラップを備えている。そして、特定温度以上に加熱された形状記憶合金製バネが、フラップの外皮部の上方部分を翼型部の上面に密着させるような付勢力を外皮部に加えることにより、主翼の上面の後縁端とフラップの外皮部の上面との間に噴射口を形成するとともに、外皮部の上方部分を翼型部に密着させることによりフラップを円弧形状にすることができる。すなわち、クランク、レール、リンク等の複雑な機構を採用することなく、形状記憶合金の特性を有効に利用して、噴射口を形成するとともに、コアンダ効果に適したフラップ形状を形成することができる。   According to the first aspect of the present invention, the airfoil portion disposed at a position slightly separated from the rear edge of the upper surface of the main wing, and the flexibility disposed so as to cover at least the upper surface of the airfoil portion. And a flap having a skin portion. Then, the shape memory alloy spring heated above a specific temperature applies a biasing force to the outer skin part so that the upper part of the outer skin part of the flap is in close contact with the upper surface of the airfoil part. While forming the injection port between the end and the upper surface of the outer skin portion of the flap, the flap can be formed into an arc shape by bringing the upper portion of the outer skin portion into close contact with the airfoil portion. That is, without adopting complicated mechanisms such as cranks, rails, links, etc., it is possible to form the injection port and to form a flap shape suitable for the Coanda effect by effectively utilizing the characteristics of the shape memory alloy. .

従って、従来のメカニカルな高揚力装置と比較して、製造費用やメンテナンス費用を格段に低減することができるとともに大幅な軽量化を達成することができる。そして、主翼の上面の後方に形成された噴射口からジェット気流を、コアンダ効果に適したフラップ形状に沿って噴射させることにより、コアンダ効果による循環制御を実現させて高揚力を効果的に発生させることができる。また、可動部に起因する構造的な間隙（ギャップ）が少なくなる上に、ジェット噴射によりフラップ端部からの渦の発生が抑制されるため、従来のメカニカルな高揚力装置を採用した場合に発生し易かったエアフレームノイズを抑制することもできる。   Therefore, compared with the conventional mechanical high lift device, the manufacturing cost and the maintenance cost can be remarkably reduced and a significant weight reduction can be achieved. And by jetting a jet stream from the injection port formed behind the upper surface of the main wing along a flap shape suitable for the Coanda effect, the circulation control by the Coanda effect is realized and high lift force is effectively generated. be able to. In addition, structural gaps due to moving parts are reduced, and vortex generation from the flap end is suppressed by jet injection, which occurs when a conventional mechanical high lift device is used. It is also possible to suppress air frame noise that was easy to do.

請求項２に記載の発明は、請求項１に記載の高揚力発生装置において、前記形状記憶合金製バネが前記特定温度未満まで冷却された場合に、前記バイアスバネの付勢力により、前記主翼の上面の後縁端と前記フラップの前記外皮部の上面とを連接して前記噴射口を遮蔽することを特徴とする。   According to a second aspect of the present invention, in the high lift generating device according to the first aspect, when the shape memory alloy spring is cooled to below the specific temperature, the biasing force of the bias spring causes the main wing to The injection port is shielded by connecting the rear edge of the upper surface and the upper surface of the outer skin portion of the flap.

請求項２に記載の発明によれば、形状記憶合金製バネが特定温度未満まで冷却された場合に、バイアスバネが、フラップの外皮部の上方部分を上方に移動させるような付勢力を外皮部に加えることにより、主翼の上面の後縁端とフラップの外皮部の上面とを連接して噴射口を遮蔽することができる。従って、高揚力が不要な高速飛行時（巡航時）において、高揚力装置に起因する抵抗を低減することができるので、航空機の巡航速度の低下や燃料消費率の増加を抑制することができる。   According to the second aspect of the present invention, when the shape memory alloy spring is cooled to a temperature lower than the specific temperature, the bias spring applies a biasing force that moves the upper portion of the outer skin portion of the flap upward. By adding to the above, the injection port can be shielded by connecting the rear edge of the upper surface of the main wing and the upper surface of the outer skin portion of the flap. Accordingly, during high-speed flight that does not require high lift (cruise), the resistance caused by the high lift device can be reduced, so that the decrease in the cruise speed of the aircraft and the increase in the fuel consumption rate can be suppressed.

請求項３に記載の発明は、請求項１又は２に記載の高揚力発生装置において、前記主翼の内部の下方に配置された柔軟性を有する板状体と、前記板状体を前記主翼の前後方向に移動させる板状体移動手段と、を備え、前記噴射口が形成された場合に、前記板状体移動手段が前記板状体を前記主翼の後縁側に移動させて、前記フラップの上面に前記板状体の端部を近接ないし当接させることにより、前記主翼の内部から前記噴射口へといたるジェット気流誘導面を形成することを特徴とする。   According to a third aspect of the present invention, in the high lift generating device according to the first or second aspect, a flexible plate-like body disposed below the inside of the main wing, and the plate-like body of the main wing. Plate-like body moving means for moving in the front-rear direction, and when the injection port is formed, the plate-like body moving means moves the plate-like body to the trailing edge side of the main wing, and A jet air flow guide surface from the inside of the main wing to the injection port is formed by bringing an end portion of the plate-like body close to or in contact with the upper surface.

請求項３に記載の発明によれば、噴射口が形成された場合に、板状体移動手段が、主翼の内部の下方に配置された柔軟性を有する板状体を主翼の後縁側に移動させて、フラップの上面に板状体の端部を近接ないし当接させる。これにより、主翼の内部から噴射口へといたるジェット気流誘導面を形成することができ、主翼の内部のジェット気流を噴射口まで効果的に導くことができる。   According to the invention described in claim 3, when the injection port is formed, the plate-like body moving means moves the flexible plate-like body arranged below the inside of the main wing to the trailing edge side of the main wing. Then, the end of the plate-like body is brought close to or in contact with the upper surface of the flap. As a result, a jet air flow guiding surface from the inside of the main wing to the injection port can be formed, and the jet air flow inside the main wing can be effectively guided to the injection port.

請求項４に記載の発明は、請求項３に記載の高揚力発生装置において、前記前記板状体移動手段は、特定温度以上に加熱された場合に前記板状体を前記主翼の後縁側に移動させるような付勢力を加える形状記憶合金製バネを有することを特徴とする。   According to a fourth aspect of the present invention, in the high lift generating device according to the third aspect, the plate-like body moving means moves the plate-like body to the trailing edge side of the main wing when heated to a specific temperature or higher. It has a shape memory alloy spring that applies an urging force to move it.

請求項４に記載の発明によれば、板状体移動手段は、特定温度以上に加熱された場合に板状体を主翼の後縁側に移動させるような付勢力を加える形状記憶合金製バネを有するので、必要に応じてジェット気流誘導面を形成することができる。従って、効果的かつ安定した循環制御技術による高揚力装置の性能が確保されるとともに、製造費用の低減及び機体の軽量化に寄与することができる。   According to the fourth aspect of the present invention, the plate-like body moving means includes the shape memory alloy spring that applies a biasing force to move the plate-like body to the trailing edge side of the main wing when heated to a specific temperature or higher. Therefore, the jet air flow guide surface can be formed as necessary. Therefore, the performance of the high lift device by the effective and stable circulation control technology can be ensured, and the manufacturing cost can be reduced and the weight of the aircraft can be reduced.

本発明によれば、形状記憶合金製バネ及びバイアスバネの付勢力を利用して、必要に応じて主翼の後縁端とフラップの上面との間における噴射口の形成・遮蔽を行うとともにフラップ形状の変形を行うことができる。従って、高揚力が必要となる離着陸時においては、噴射口を形成して、ジェット気流をコアンダ効果に適したフラップ形状に沿って噴射させることにより、コアンダ効果による循環制御を実現させて高揚力を効果的に発生させることができる。一方、高揚力が不要な巡航時においては、噴射口を遮蔽することにより、航空機の巡航速度の低下や燃料消費率の増加を抑制することができる。この結果、効果的かつ安定した循環制御技術による高揚力装置の性能が確保される。また、形状記憶合金製バネ及びバイアスバネから構成されるアクチュエータは構成が簡素かつ軽量であるため、従来のメカニカルな高揚力装置と比較して、製造費用やメンテナンス費用を格段に低減することができるとともに大幅な軽量化を達成することができる。   According to the present invention, by using the biasing force of the shape memory alloy spring and the bias spring, the injection port is formed and shielded between the trailing edge of the main wing and the upper surface of the flap as necessary, and the flap shape is used. Can be modified. Therefore, during takeoff and landing where high lift is required, an injection port is formed and a jet stream is injected along the flap shape suitable for the Coanda effect, thereby realizing circulation control by the Coanda effect and high lift. It can be generated effectively. On the other hand, during cruises that do not require high lift, it is possible to suppress a decrease in the cruise speed of the aircraft and an increase in the fuel consumption rate by shielding the injection port. As a result, the performance of the high lift device by the effective and stable circulation control technology is ensured. In addition, since the actuator composed of the shape memory alloy spring and the bias spring is simple and lightweight, the manufacturing cost and the maintenance cost can be significantly reduced compared with the conventional mechanical high lift device. At the same time, significant weight reduction can be achieved.

以下、本発明の実施の形態を、図を用いて詳細に説明する。   Hereinafter, embodiments of the present invention will be described in detail with reference to the drawings.

まず、図１及び図２を用いて、本実施の形態に係る高揚力発生装置の構成について説明する。   First, the configuration of the high lift generator according to the present embodiment will be described with reference to FIGS. 1 and 2.

本実施の形態に係る高揚力発生装置は、図１に示すように、航空機の主翼１の後縁部に取り付けられたフラップ１０、形状記憶合金（Shape Memory Alloys）で調製されたバネ（以下「ＳＭＡバネ」という）２０、バイアスバネ３０、主翼１の内部に設けられた板状体４０、等を備えて構成されている。高揚力発生装置は、図２（ａ）に示すように、ＳＭＡバネ２０及びバイアスバネ３０の付勢力を利用して主翼１の後縁端２とフラップ１０との間における噴射口Ｓの形成・遮蔽を行うとともに、フラップ１０の形状の変形を行うものであり、離着陸時には噴射口Ｓを形成し、この噴射口Ｓから、コアンダ効果に適した円弧形状に変形されたフラップ１０に沿ってジェット気流を噴射させてコアンダ効果による循環制御を実現させるものである。   As shown in FIG. 1, the high lift generator according to the present embodiment includes a flap 10 attached to the rear edge of the main wing 1 of an aircraft, and a spring (hereinafter referred to as “shape memory alloy”). (Referred to as “SMA spring”) 20, a bias spring 30, a plate-like body 40 provided inside the main wing 1, and the like. As shown in FIG. 2A, the high lift generating device uses the biasing force of the SMA spring 20 and the bias spring 30 to form the injection port S between the trailing edge 2 of the main wing 1 and the flap 10. In addition to shielding, the shape of the flap 10 is deformed. At the time of takeoff and landing, an injection port S is formed, and a jet airflow is generated from the injection port S along the flap 10 deformed into an arc shape suitable for the Coanda effect. To achieve circulation control by the Coanda effect.

フラップ１０は、図１及び図２に示すように、翼型部１１及び外皮部１２を有するとともに、主翼１の後縁部にヒンジ３を介して回動自在に取り付けられており、従来型の油圧式又は電動式アクチュエータにより駆動する。   As shown in FIGS. 1 and 2, the flap 10 has an airfoil portion 11 and an outer skin portion 12 and is rotatably attached to a rear edge portion of the main wing 1 via a hinge 3. It is driven by a hydraulic or electric actuator.

フラップ１０の翼型部１１は、図２に示すように、主翼１の後縁端２から若干下方に離隔した位置に配置されており、その上面は主翼１の後縁端２よりも若干下方に位置している。翼型部１１の前縁部上方の曲面は、後述するコアンダ効果に適した円弧形状に成形されている。また、翼型部１１の下面は、フラップ１０の舵角δfが零の場合に主翼１の下面４に連続するような平坦面とされている。 As shown in FIG. 2, the airfoil portion 11 of the flap 10 is disposed at a position slightly separated from the trailing edge 2 of the main wing 1, and its upper surface is slightly below the trailing edge 2 of the main wing 1. Is located. The curved surface above the front edge portion of the airfoil portion 11 is formed into an arc shape suitable for the Coanda effect described later. Further, the lower surface of the airfoil portion 11 is a flat surface that is continuous with the lower surface 4 of the main wing 1 when the steering angle δ f of the flap 10 is zero.

フラップ１０の外皮部１２は、翼型部１１の上面全体及び下面の一部を被覆する板状体であり、柔軟性を有する材料（ゴム材料、樹脂材料、樹脂材料を強化繊維で補強した複合材等）で調製されている。外皮部１２は、図２に示すように、その一方の端部１２ａが翼型部１１の後縁端に固着され、その他方の端部１２ｂが翼型部１１の下面側に配置され、全体として、翼型部１１の上部、前縁部及び下部の一部に巻き付けられたような状態とされている。   The outer skin portion 12 of the flap 10 is a plate-like body that covers the entire upper surface and a part of the lower surface of the airfoil portion 11, and has a flexible material (a rubber material, a resin material, a composite in which a resin material is reinforced with reinforcing fibers) Etc.). As shown in FIG. 2, the outer skin portion 12 has one end portion 12 a fixed to the rear edge end of the airfoil portion 11, and the other end portion 12 b disposed on the lower surface side of the airfoil portion 11. As described above, the airfoil 11 is wound around a part of the upper part, the front edge part, and the lower part of the airfoil part 11.

フラップ１０の翼型部１１に対して外皮部１２を相対移動させることにより、フラップ１０の外形や翼厚を変更することができる。例えば、図２（ａ）に示すように、外皮部１２の上方部分を翼型部１１の表面に密着させることにより、フラップ１０の翼厚を小さくすることができる。一方、図２（ｂ）に示すように外皮部１２の上方部分を上方に移動させることにより、フラップ１０の翼厚を大きくすることができる。   By moving the outer skin portion 12 relative to the airfoil portion 11 of the flap 10, the outer shape and blade thickness of the flap 10 can be changed. For example, as shown in FIG. 2A, the blade thickness of the flap 10 can be reduced by bringing the upper portion of the outer skin portion 12 into close contact with the surface of the airfoil portion 11. On the other hand, the blade thickness of the flap 10 can be increased by moving the upper part of the outer skin part 12 upward as shown in FIG.

ＳＭＡバネ２０及びバイアスバネ３０は、翼型部１１に対して外皮部１２を相対移動させるアクチュエータとして機能するものであり、図２に示すようにフラップ１０の内部に設けられている。   The SMA spring 20 and the bias spring 30 function as actuators that move the outer skin portion 12 relative to the airfoil portion 11, and are provided inside the flap 10 as shown in FIG.

ＳＭＡバネ２０は、特定温度未満の低温域において低い剛性を有し、特定温度以上の高温域において高い剛性を有する「形状記憶合金」で調製された弾性体である。ＳＭＡバネ２０は、図２に示すように、その一方の端部２１が翼型部１１の内部後方部分に固定され、その他方の端部２２が連結部材６０を介して外皮部１２の他方の端部１２ｂに連結されている。   The SMA spring 20 is an elastic body made of a “shape memory alloy” having low rigidity in a low temperature range below a specific temperature and high rigidity in a high temperature range above a specific temperature. As shown in FIG. 2, one end 21 of the SMA spring 20 is fixed to the inner rear portion of the airfoil 11, and the other end 22 is connected to the other end of the outer skin 12 via the connecting member 60. It is connected to the end 12b.

ＳＭＡバネ２０は、外皮部１２の他方の端部１２ｂを後方に引っ張るような付勢力を外皮部１２に常時加えている。ＳＭＡバネ２０の第１の付勢力は、形状記憶合金の特性により、特定温度以上の高温域において大きくなり、特定温度未満の低温域において小さくなる。   The SMA spring 20 constantly applies an urging force to the outer skin portion 12 so as to pull the other end portion 12 b of the outer skin portion 12 backward. The first urging force of the SMA spring 20 increases in a high temperature region above a specific temperature and decreases in a low temperature region below the specific temperature due to the characteristics of the shape memory alloy.

バイアスバネ３０は、外皮部１２の上方部分を上方に移動させるような付勢力を外皮部１２に加える弾性体である。バイアスバネ３０は、図２に示すように、その一方の端部３１が翼型部１１の内部に設けられた桁部１１ａに固定され、その他方の端部３２が外皮部１２の上方部分の内面に取り付けられている。   The bias spring 30 is an elastic body that applies an urging force to the outer skin portion 12 to move the upper portion of the outer skin portion 12 upward. As shown in FIG. 2, one end 31 of the bias spring 30 is fixed to a spar 11 a provided inside the airfoil 11, and the other end 32 is an upper portion of the outer skin 12. It is attached to the inner surface.

バイアスバネ３０の付勢力は、ＳＭＡバネ２０の高温域における付勢力よりも小さくなるように設定されている。このため、ＳＭＡバネ２０が特定温度以上に加熱された場合には、ＳＭＡバネ２０の付勢力により外皮部１２の他方の端部１２ｂが後方に引っ張られる。この結果、図２（ａ）に示すように、外皮部１２の上方部分が翼型部１１の上面に密着して、主翼１の後縁端２とフラップ１０の外皮部１２の上面との間に噴射口Ｓが形成されるとともに、フラップ１０がコアンダ効果に適した円弧形状に成形される。   The biasing force of the bias spring 30 is set to be smaller than the biasing force of the SMA spring 20 in the high temperature region. For this reason, when the SMA spring 20 is heated to a specific temperature or higher, the other end portion 12 b of the outer skin portion 12 is pulled backward by the urging force of the SMA spring 20. As a result, as shown in FIG. 2A, the upper part of the outer skin portion 12 is in close contact with the upper surface of the airfoil portion 11, and between the trailing edge 2 of the main wing 1 and the upper surface of the outer skin portion 12 of the flap 10. And the flap 10 is formed into an arc shape suitable for the Coanda effect.

一方、バイアスバネ３０の付勢力は、ＳＭＡバネ２０の低温域における付勢力よりも大きくなるように設定されている。このため、ＳＭＡバネ２０が冷却されて特定温度未満となった場合には、バイアスバネ３０の付勢力により外皮部１２の上方部分が上方に移動する。この結果、図２（ｂ）に示すように、主翼１の後縁端２とフラップ１０の外皮部１２の上面とが連接され、噴射口Ｓは遮蔽されることとなる。   On the other hand, the biasing force of the bias spring 30 is set to be larger than the biasing force of the SMA spring 20 in the low temperature region. For this reason, when the SMA spring 20 is cooled to a temperature lower than the specific temperature, the upper portion of the outer skin portion 12 is moved upward by the biasing force of the bias spring 30. As a result, as shown in FIG. 2B, the trailing edge 2 of the main wing 1 and the upper surface of the outer skin portion 12 of the flap 10 are connected, and the injection port S is shielded.

板状体４０は、図１に示すように、主翼１の後縁側内部空間Ａの下方に配置されており、柔軟性を有する材料（ゴム材料、樹脂材料、樹脂材料を強化繊維で補強した複合材等）で調製されている。板状体４０は、図１に示すように、略Ｖ字状に折り曲げられてその一方の端部４１が若干上方に位置するようにされており、この一方の端部４１がフラップ１０の前縁近傍に達している。また、板状体４０の他方の端部４２は、図１に示すように、板状体移動用バネ５０及び連結部材７０を介して、主翼１の後縁側内部空間Ａに固定された構造部材５に取り付けられている。   As shown in FIG. 1, the plate-like body 40 is disposed below the inner space A on the trailing edge side of the main wing 1 and has a flexible material (a rubber material, a resin material, a composite material in which a resin material is reinforced with reinforcing fibers). Etc.). As shown in FIG. 1, the plate-like body 40 is bent into a substantially V shape so that one end 41 thereof is positioned slightly above, and this one end 41 is in front of the flap 10. Near the edge. Further, as shown in FIG. 1, the other end portion 42 of the plate-like body 40 is a structural member fixed to the rear edge side internal space A of the main wing 1 via a plate-like body moving spring 50 and a connecting member 70. 5 is attached.

板状体移動用バネ５０は、板状体４０を主翼１の後縁側に移動させるような付勢力を有するＳＭＡバネと、このＳＭＡバネに直列に配置され板状体４０を主翼１の前縁側に移動させるような付勢力を有するバイアスバネと、から構成された弾性体である。板状体移動用バネ５０は、図１に示すように、その一方の端部５１が連結部材７０を介して主翼１の構造部材５に連結され、その他方の端部５２が板状体４０の他方の端部４２に取り付けられている。   The plate-like body moving spring 50 includes an SMA spring having an urging force that moves the plate-like body 40 toward the trailing edge of the main wing 1, and the plate-like body 40 arranged in series with the SMA spring on the leading edge side of the main wing 1. And a bias spring having an urging force to be moved to the elastic body. As shown in FIG. 1, the plate-like body moving spring 50 has one end 51 connected to the structural member 5 of the main wing 1 via a connecting member 70, and the other end 52 as the plate-like body 40. It is attached to the other end 42 of the.

板状体移動用バネ５０は、特定温度未満の低温域においては、バイアスバネの付勢力がＳＭＡバネの付勢力より大きくなるように設定しているので、バイアスバネの付勢力により伸長した状態となる。一方、板状体移動用バネ５０は、特定温度以上の高温域においては、ＳＭＡバネの付勢力がバイアスバネの付勢力より大きくなるように設定しているので、ＳＭＡバネの付勢力により収縮することにより、板状体４０を主翼１の前後方向に移動させるアクチュエータとして機能する。すなわち、板状体移動用バネ５０は、本発明における板状体移動手段である。   Since the plate-like body moving spring 50 is set so that the biasing force of the bias spring is larger than the biasing force of the SMA spring in a low temperature range below a specific temperature, Become. On the other hand, the plate-like body moving spring 50 is set so that the urging force of the SMA spring is larger than the urging force of the bias spring in a high temperature range above a specific temperature, and therefore contracts due to the urging force of the SMA spring. This functions as an actuator that moves the plate-like body 40 in the front-rear direction of the main wing 1. That is, the plate-like body moving spring 50 is a plate-like body moving means in the present invention.

板状体移動用バネ５０を特定温度以上に加熱して、その構成要素であるＳＭＡバネの付勢力で収縮させることにより、板状体４０を主翼１の後縁側に移動させて、図２（ａ）に示すように板状体４０の一方の端部４１をフラップ１０の外皮部１２の上面に近接ないし当接させることができる。このように板状体４０の一方の端部４１をフラップ１０の外皮部１２の上面に近接ないし当接させることにより、主翼１の内部から噴射口へといたるジェット気流誘導面を形成することができる。一方、板状体移動用バネ５０を特定温度未満まで冷却して、その構成要素であるバイアスバネの付勢力で伸長させることにより、図１及び図２（ｂ）に示すように板状体４０を主翼１の前縁側に移動させることができる。   The plate-like body moving spring 50 is heated to a specific temperature or more and contracted by the urging force of the SMA spring, which is a constituent element thereof, to move the plate-like body 40 to the trailing edge side of the main wing 1, and FIG. As shown in a), one end 41 of the plate-like body 40 can be brought close to or in contact with the upper surface of the outer skin 12 of the flap 10. Thus, by bringing one end portion 41 of the plate-like body 40 close to or in contact with the upper surface of the outer skin portion 12 of the flap 10, a jet airflow guiding surface from the inside of the main wing 1 to the injection port can be formed. it can. On the other hand, the plate-like body moving spring 50 is cooled to a temperature lower than a specific temperature and is extended by the biasing force of the bias spring which is a component of the plate-like body moving spring 50, as shown in FIGS. 1 and 2B. Can be moved to the leading edge side of the main wing 1.

次に、図１〜図３を用いて、本実施の形態に係る高揚力発生装置の動作について説明する。   Next, the operation of the high lift generator according to the present embodiment will be described with reference to FIGS.

＜離着陸時における高揚力発生動作＞
最初に、航空機の離着陸時（低速飛行時）における高揚力発生動作について説明する。航空機の離着陸時において、図１に示した主翼１の後縁側内部空間Ａに、高温のエンジン抽気ガスやコンプレッサで圧縮された高温・高圧ガスが充填されることにより、高揚力発生装置のＳＭＡバネ２０が特定温度以上に加熱される。すると、ＳＭＡバネ２０の付勢力がバイアスバネ３０の付勢力よりも大きくなるため、ＳＭＡバネ２０の付勢力により外皮部１２の他方の端部１２ｂが後方に引っ張られる。この結果、図２（ａ）に示すように、外皮部１２の上方部分が翼型部１１の上面に密着して、主翼１の後縁端２とフラップ１０の外皮部１２の上面との間に噴射口Ｓが形成されるとともに、フラップ１０がコアンダ効果に適した円弧形状に成形される。 <High lift generation during take-off and landing>
First, the operation of generating high lift when the aircraft takes off and landing (at low speed flight) will be described. At the time of takeoff and landing of the aircraft, the SMA spring of the high lift generator is filled by filling the internal space A on the trailing edge side of the main wing 1 shown in FIG. 1 with high-temperature engine bleed gas or high-temperature / high-pressure gas compressed by a compressor. 20 is heated above a specific temperature. Then, since the biasing force of the SMA spring 20 becomes larger than the biasing force of the bias spring 30, the other end 12b of the outer skin portion 12 is pulled backward by the biasing force of the SMA spring 20. As a result, as shown in FIG. 2 (a), the upper part of the outer skin portion 12 is in close contact with the upper surface of the airfoil portion 11, and between the trailing edge 2 of the main wing 1 and the upper surface of the outer skin portion 12 of the flap 10. And the flap 10 is formed in an arc shape suitable for the Coanda effect.

また、航空機の離着陸時においては、主翼１の後縁側内部空間Ａに充填された高温・高圧のガスによって、板状体移動用バネ５０の構成要素であるＳＭＡバネが特定温度以上に加熱されることにより、板状体移動用バネ５０の他の構成要素であるバイアスバネの付勢力よりもＳＭＡバネの付勢力が大きくなって収縮するため、板状体４０が主翼１の後縁側に移動する。この結果、図２（ａ）に示すように、板状体４０の一方の端部４１がフラップ１０の外皮部１２の上面に近接ないし当接して、主翼１の内部から噴射口Ｓへといたるジェット気流誘導面が形成される。   Further, at the time of takeoff and landing of the aircraft, the SMA spring, which is a component of the plate-like body moving spring 50, is heated to a specific temperature or higher by the high-temperature and high-pressure gas filled in the rear edge side internal space A of the main wing 1. As a result, the biasing force of the SMA spring becomes larger than the biasing force of the bias spring, which is another component of the plate-like body moving spring 50, and the plate-like body 40 moves toward the trailing edge of the main wing 1. . As a result, as shown in FIG. 2A, one end 41 of the plate-like body 40 comes close to or comes into contact with the upper surface of the outer skin 12 of the flap 10 and reaches from the inside of the main wing 1 to the injection port S. A jet airflow guiding surface is formed.

このように航空機の離着陸時においては、主翼１の上面の後方に噴射口Ｓが形成され、主翼１の内部にジェット気流誘導面が形成されるため、主翼１の後縁側内部空間Ａに充填された高温・高圧のガスは、ジェット気流誘導面に沿って噴射口Ｓに向かって流れ、ジェット気流となって噴射口Ｓから主翼１の外部に噴射される。さらに、コアンダ効果に適した円弧形状に成形されたフラップ１０に沿って噴射されるジェット気流により、主翼１の後縁周りの流れが押し下げられ（コアンダ効果）、主翼周りの循環が強化されることにより高揚力が発生することとなる。なお、ジェット気流の噴射量によってフラップ１０の舵角δfを変化させて、空気抵抗を調整することもできる。 Thus, when the aircraft takes off and landing, the injection port S is formed behind the upper surface of the main wing 1 and the jet airflow guiding surface is formed inside the main wing 1, so that the inner space A on the trailing edge side of the main wing 1 is filled. The high-temperature and high-pressure gas flows toward the injection port S along the jet air flow guide surface, and is jetted from the injection port S to the outside of the main wing 1 as a jet air flow. Furthermore, the flow around the trailing edge of the main wing 1 is pushed down by the jet air stream injected along the flap 10 formed in an arc shape suitable for the Coanda effect (Coanda effect), and the circulation around the main wing is strengthened. As a result, high lift is generated. Note that the air resistance can be adjusted by changing the steering angle δ f of the flap 10 according to the amount of jet air flow.

＜巡航時における噴射口遮蔽動作＞
続いて、航空機の巡航時（高速飛行時）における噴射口遮蔽動作について説明する。航空機の巡航時においては、主翼１の後縁側内部空間Ａへの高温ガスの導入が停止されるため、巡航時の高高度の外気により高揚力発生装置のＳＭＡバネ２０が特定温度未満に冷却される。すると、ＳＭＡバネ２０の付勢力がバイアスバネ３０の付勢力よりも小さくなるため、バイアスバネ３０の付勢力により外皮部１２の上方部分が上方に移動する。この結果、図１及び図２（ｂ）に示すように、主翼１の後縁端２とフラップ１０の外皮部１２の上面とが連接され、噴射口Ｓは遮蔽される。また、主翼１の内部に配置された板状体移動用バネ５０の構成要素であるＳＭＡバネ特定温度未満に冷却されることにより、板状体移動用バネ５０の他の構成要素であるバイアスバネの付勢力がＳＭＡバネの付勢力よりも大きくなって伸長するため、板状体４０が主翼１の前縁側に移動する。 <Injection shielding operation during cruise>
Next, the injection port shielding operation when the aircraft is cruising (at high speed flight) will be described. During the cruise of the aircraft, the introduction of the high-temperature gas into the inner space A on the trailing edge side of the main wing 1 is stopped, so that the SMA spring 20 of the high lift generator is cooled below a specific temperature by the high altitude outside air during the cruise. The Then, since the biasing force of the SMA spring 20 is smaller than the biasing force of the bias spring 30, the upper portion of the outer skin portion 12 is moved upward by the biasing force of the bias spring 30. As a result, as shown in FIGS. 1 and 2B, the trailing edge 2 of the main wing 1 and the upper surface of the outer skin portion 12 of the flap 10 are connected, and the injection port S is shielded. Further, by being cooled to below the SMA spring specific temperature that is a component of the plate-like body moving spring 50 disposed inside the main wing 1, a bias spring that is another component of the plate-like body moving spring 50. The plate-like body 40 moves to the front edge side of the main wing 1 because the urging force of the SMA spring becomes larger than that of the SMA spring and extends.

このように航空機の巡航時においては主翼１の後方における噴射口Ｓが遮蔽されるため、主翼１の上面の後縁端２とフラップ１０の上面とが連接されて、主翼１の後縁部でシャープな形状が形成されるため、空気抵抗を大幅に低減することができる。   Thus, when the aircraft is cruising, the injection port S behind the main wing 1 is shielded, so that the rear edge 2 of the upper surface of the main wing 1 and the upper surface of the flap 10 are connected to each other at the rear edge of the main wing 1. Since a sharp shape is formed, air resistance can be significantly reduced.

以上説明した実施の形態に係る高揚力発生装置においては、主翼１の上面の後縁端２から若干下方に離隔した位置に配置されコアンダ効果に適した円弧形状に成形された翼型部１１と、この翼型部１１の上面を覆うように配置された柔軟性を有する外皮部１２と、を有するフラップ１０を備えている。そして、航空機の離着陸時において特定温度以上に加熱されたＳＭＡバネ２０が、フラップ１０の外皮部１２の上方部分を翼型部１１の上面に密着させるような付勢力を外皮部１２に加えることにより、主翼１の上面の後縁端２とフラップ１０の外皮部１２の上面との間に噴射口Ｓを形成するとともに、外皮部１２の上方部分を翼型部１１に密着させることによりフラップ１０を円弧形状にすることができ、コアンダ効果に適したフラップ形状に沿って噴射口Ｓからジェット気流を噴射させることにより、コアンダ効果による循環制御を実現させて高揚力を効果的に発生させることができる。   In the high lift generator according to the embodiment described above, the airfoil portion 11 is disposed at a position slightly spaced from the rear edge 2 of the upper surface of the main wing 1 and is formed in an arc shape suitable for the Coanda effect. A flap 10 having a flexible outer skin portion 12 disposed so as to cover the upper surface of the airfoil portion 11 is provided. Then, the SMA spring 20 heated to a specific temperature or more at the time of takeoff and landing of the aircraft applies an urging force to the outer skin portion 12 such that the upper portion of the outer skin portion 12 of the flap 10 is in close contact with the upper surface of the airfoil portion 11. The injection port S is formed between the rear edge 2 of the upper surface of the main wing 1 and the upper surface of the outer skin portion 12 of the flap 10, and the upper portion of the outer skin portion 12 is brought into close contact with the airfoil portion 11 so that the flap 10 is It can be formed into an arc shape, and by jetting a jet stream from the injection port S along a flap shape suitable for the Coanda effect, circulation control by the Coanda effect can be realized and high lift can be generated effectively. .

また、以上説明した実施の形態に係る高揚力発生装置においては、航空機の巡航時においてＳＭＡバネ２０が特定温度未満まで冷却された場合に、バイアスバネ３０が、フラップ１０の外皮部１２の上方部分を上方に移動させるような第２の付勢力を外皮部１２に加えることにより、主翼１の上面の後縁端２とフラップ１０の外皮部１２の上面とを連接して噴射口Ｓを遮蔽することができる。従って、高揚力が不要な高速飛行時（巡航時）において、高揚力装置に起因する抵抗を低減することができるので、航空機の巡航速度の低下や燃料消費率の増加を抑制することができる。この結果、効果的かつ安定した循環制御技術による高揚力装置の性能が確保される。   In the high lift generating device according to the embodiment described above, when the SMA spring 20 is cooled to a temperature lower than a specific temperature during the cruise of the aircraft, the bias spring 30 is an upper portion of the outer skin portion 12 of the flap 10. By applying a second urging force to the outer skin portion 12 so as to move the upper portion of the main wing 1 upward, the rear edge 2 of the upper surface of the main wing 1 and the upper surface of the outer skin portion 12 of the flap 10 are connected to shield the injection port S. be able to. Accordingly, during high-speed flight that does not require high lift (cruise), the resistance caused by the high lift device can be reduced, so that the decrease in the cruise speed of the aircraft and the increase in the fuel consumption rate can be suppressed. As a result, the performance of the high lift device by the effective and stable circulation control technology is ensured.

また、以上説明した実施の形態に係る高揚力発生装置で使用されるＳＭＡバネ２０及びバイアスバネ３０から構成されるアクチュエータは、構成が簡素かつ軽量であるため、従来のメカニカルな高揚力装置と比較して、製造費用やメンテナンス費用を格段に低減することができるとともに大幅な軽量化を達成することができる。また、可動部に起因する構造的な間隙（ギャップ）が少なくなる上に、ジェット噴射によりフラップ端部からの渦の発生が抑制されるため、従来のメカニカルな高揚力装置を採用した場合に発生し易かったエアフレームノイズを抑制することもできる。   In addition, the actuator composed of the SMA spring 20 and the bias spring 30 used in the high lift generating device according to the embodiment described above is simple and lightweight, so it is compared with a conventional mechanical high lift device. Thus, manufacturing costs and maintenance costs can be significantly reduced, and a significant reduction in weight can be achieved. In addition, structural gaps due to moving parts are reduced, and vortex generation from the flap end is suppressed by jet injection, which occurs when a conventional mechanical high lift device is used. It is also possible to suppress air frame noise that was easy to do.

また、以上説明した実施の形態に係る高揚力発生装置においては、航空機の離着陸時において板状体移動用バネ５０が特定温度以上に加熱されて、その構成要素であるＳＭＡバネの付勢力がバイアスバネの付勢力より大きくなって収縮することにより、主翼１の内部の下方に配置された柔軟性を有する板状体４０を主翼１の後縁側に移動させて、板状体４０の端部４１をフラップ１０の上面に近接ないし当接させることができる。これにより、主翼１の内部から噴射口Ｓへといたるジェット気流誘導面を形成することができ、主翼１の内部のジェット気流を噴射口Ｓまで効果的に導くことができる。また、航空機の巡航時においては、板状体移動用バネ５０が特定温度未満に冷却されて、その構成要素であるバイアスバネの付勢力がＳＭＡバネの付勢力より大きくなって伸長することにより、板状体４０を主翼１の前縁側に移動させて格納することができる。従って、効果的かつ安定した循環制御技術による高揚力装置の性能が確保される。   Further, in the high lift generating apparatus according to the embodiment described above, the plate-like body moving spring 50 is heated to a specific temperature or higher during takeoff and landing of the aircraft, and the biasing force of the SMA spring as a component is biased. By contracting larger than the biasing force of the spring, the flexible plate-like body 40 disposed below the inside of the main wing 1 is moved to the trailing edge side of the main wing 1, and the end portion 41 of the plate-like body 40 is moved. Can be brought close to or in contact with the upper surface of the flap 10. As a result, a jet air flow guiding surface from the inside of the main wing 1 to the injection port S can be formed, and the jet air flow inside the main wing 1 can be effectively guided to the injection port S. Further, when the aircraft is cruising, the plate-like body moving spring 50 is cooled to below a specific temperature, and the biasing force of the bias spring, which is a component thereof, becomes larger than the biasing force of the SMA spring, thereby extending. The plate-like body 40 can be moved and stored to the front edge side of the main wing 1. Therefore, the performance of the high lift device by the effective and stable circulation control technology is ensured.

なお、以上の実施の形態においては、主翼１の後縁側内部空間Ａに充填された高温・高圧のガスによってＳＭＡバネ２０及び板状体移動用バネ５０を加熱した例を示したが、これらＳＭＡバネ２０等を通電によって加熱することもできる。   In the above embodiment, an example in which the SMA spring 20 and the plate-like body moving spring 50 are heated by the high-temperature and high-pressure gas filled in the inner space A on the trailing edge side of the main wing 1 has been shown. The spring 20 or the like can be heated by energization.

また、以上の実施の形態においては、ＳＭＡバネ２０をフラップ１０の下方に配置し、ＳＭＡバネ２０の付勢力により外皮部１２の端部１２ｂを後縁側に引っ張ることにより、外皮部１２の上方部分を翼型部１１の上面に密着させて噴射口Ｓを形成した例を示したが、ＳＭＡバネ２０の位置や、外皮部１２の端部１２ｂの位置はこれに限定されるものではない。   In the above embodiment, the SMA spring 20 is disposed below the flap 10, and the end portion 12 b of the outer skin portion 12 is pulled to the rear edge side by the urging force of the SMA spring 20, whereby the upper portion of the outer skin portion 12. However, the position of the SMA spring 20 and the position of the end portion 12b of the outer skin portion 12 are not limited to this.

また、以上の実施の形態においては、バイアスバネ３０をフラップ１０の上方に配置し、バイアスバネ３０の付勢力により外皮部１２の上方部分を上方に移動させて噴射口Ｓを遮蔽した例を示したが、バイアスバネ３０の位置もこれに限定されるものではない。   In the above embodiment, an example is shown in which the bias spring 30 is disposed above the flap 10 and the upper portion of the outer skin portion 12 is moved upward by the biasing force of the bias spring 30 to shield the injection port S. However, the position of the bias spring 30 is not limited to this.

（ａ）は本発明の実施の形態に係る高揚力発生装置を搭載した主翼の断面図であり、（ｂ）は（ａ）のＢ部分（高揚力発生装置）の拡大断面図である。(A) is sectional drawing of the main wing carrying the high lift generator which concerns on embodiment of this invention, (b) is an expanded sectional view of the B section (high lift generator) of (a). （ａ）は図１（ｂ）のII部分（高揚力発生装置のフラップ近傍部分）の離着陸時における拡大断面図であり、（ｂ）は図１（ｂ）のII部分（高揚力発生装置のフラップ近傍部分）の巡航時における拡大断面図である。(A) is an enlarged sectional view at the time of takeoff and landing of II part (part near the flap of the high lift generator) of FIG. 1 (b), and (b) is II part (high lift generator of FIG. 1 (b)) It is an expanded sectional view at the time of cruising (flap vicinity part). 従来のメカニカルな高揚力発生装置（ファウラフラップ）の構造を説明するための説明図である。It is explanatory drawing for demonstrating the structure of the conventional mechanical high lift generator (fouling lap).

符号の説明Explanation of symbols

１ 主翼
２ 後縁端
１０ フラップ
１１ 翼型部
１２ 外皮部
２０ ＳＭＡバネ（形状記憶合金製バネ）
３０ バイアスバネ
４０ 板状体
５０ 板状体移動用バネ（板状体移動手段）
Ｓ 噴射口 DESCRIPTION OF SYMBOLS 1 Main wing 2 Trailing edge 10 Flap 11 Airfoil part 12 Outer part 20 SMA spring (Spring made of shape memory alloy)
30 Bias spring 40 Plate body 50 Plate body moving spring (plate body moving means)
S injection port

Claims (4)

主翼の上面の後方に形成される噴射口からジェット気流を噴射させてコアンダ効果による循環制御を実現させる高揚力発生装置において、
前記主翼の上面の後縁端から下方に離隔した位置に配置され円弧形状に成形された翼型部と、柔軟性を有し前記翼型部の少なくとも上面を被覆する外皮部と、を有するフラップと、
前記フラップの前記外皮部の上方部分を上方に移動させて前記主翼の上面の後縁端と前記外皮部の上面とを連接させるような付勢力を前記外皮部に加えるバイアスバネと、
前記フラップの前記外皮部の上方部分を下方に移動させて前記翼型部に密着させるような付勢力を前記外皮部に加える形状記憶合金製バネと、を備え、
特定温度以上に加熱された前記形状記憶合金製バネの付勢力により、前記主翼の上面の後縁端と前記フラップの前記外皮部の上面との間に前記噴射口を形成するとともに、前記フラップの前記外皮部の上方部分を前記翼型部に密着させることにより前記フラップを円弧形状にすることを特徴とする高揚力発生装置。 In a high lift generator that realizes circulation control by the Coanda effect by injecting a jet stream from the injection port formed at the rear of the upper surface of the main wing,
A flap having an airfoil portion disposed in a position spaced downward from a rear edge of the upper surface of the main wing and formed in an arc shape, and a skin portion having flexibility and covering at least the upper surface of the airfoil portion When,
A bias spring that applies an urging force to the outer skin portion so as to connect the rear edge of the upper surface of the main wing and the upper surface of the outer skin portion by moving the upper portion of the outer skin portion of the flap upward;
A shape memory alloy spring that applies an urging force to the outer skin portion so as to move the upper portion of the outer skin portion of the flap downward and bring it into close contact with the airfoil portion,
With the biasing force of the shape memory alloy spring heated to a specific temperature or higher, the injection port is formed between the rear edge of the upper surface of the main wing and the upper surface of the outer skin portion of the flap, and the flap An apparatus for generating a high lift force, wherein the flap is formed into an arc shape by bringing an upper portion of the outer skin portion into close contact with the airfoil portion. 前記形状記憶合金製バネが前記特定温度未満まで冷却された場合に、前記バイアスバネの付勢力により、前記主翼の上面の後縁端と前記フラップの前記外皮部の上面とを連接して前記噴射口を遮蔽することを特徴とする請求項１に記載の高揚力発生装置。   When the shape memory alloy spring is cooled to a temperature lower than the specific temperature, the biasing force of the bias spring connects the rear edge of the upper surface of the main wing and the upper surface of the outer skin of the flap to connect the jet. The high lift generator according to claim 1, wherein the mouth is shielded. 前記主翼の内部の下方に配置された柔軟性を有する板状体と、
前記板状体を前記主翼の前後方向に移動させる板状体移動手段と、を備え、
前記噴射口が形成された場合に、前記板状体移動手段が前記板状体を前記主翼の後縁側に移動させて、前記フラップの上面に前記板状体の端部を近接ないし当接させることにより、前記主翼の内部から前記噴射口へといたるジェット気流誘導面を形成することを特徴とする請求項１又は２に記載の高揚力発生装置。 A flexible plate-like body disposed below the inside of the main wing;
Plate-like body moving means for moving the plate-like body in the front-rear direction of the main wing,
When the injection port is formed, the plate-like body moving means moves the plate-like body to the trailing edge side of the main wing so that the end of the plate-like body comes close to or abuts on the upper surface of the flap. Thus, the high air flow generating device according to claim 1 or 2, wherein a jet air flow guide surface from the inside of the main wing to the injection port is formed. 前記板状体移動手段は、
特定温度以上に加熱された場合に前記板状体を前記主翼の後縁側に移動させるような付勢力を加える形状記憶合金製バネを有することを特徴とする請求項３に記載の高揚力発生装置。 The plate-like body moving means is
4. The high lift generator according to claim 3, further comprising a shape memory alloy spring that applies a biasing force to move the plate-like body toward the trailing edge of the main wing when heated to a specific temperature or higher. .
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US10875658B2 (en) 2015-09-02 2020-12-29 Jetoptera, Inc. Ejector and airfoil configurations
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