JPS59128098A - High lift device for aircraft - Google Patents
High lift device for aircraftInfo
- Publication number
- JPS59128098A JPS59128098A JP71683A JP71683A JPS59128098A JP S59128098 A JPS59128098 A JP S59128098A JP 71683 A JP71683 A JP 71683A JP 71683 A JP71683 A JP 71683A JP S59128098 A JPS59128098 A JP S59128098A
- Authority
- JP
- Japan
- Prior art keywords
- flap
- mounting bracket
- aircraft
- lift device
- pivotally connected
- 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.)
- Granted
Links
Landscapes
- Actuator (AREA)
- Internal Circuitry In Semiconductor Integrated Circuit Devices (AREA)
Abstract
(57)【要約】本公報は電子出願前の出願データであるた
め要約のデータは記録されません。(57) [Summary] This bulletin contains application data before electronic filing, so abstract data is not recorded.
Description
【発明の詳細な説明】 〔発明の技術分野〕 本発明は航空機用高揚力装置に関する。[Detailed description of the invention] [Technical field of invention] The present invention relates to high-lift devices for aircraft.
航空機に用いられる、いわゆる前縁フラップ、後縁フラ
ップ等の高揚力装置は、離着陸に際して一時的に高揚力
を得る目的で母翼に対して相対的に下げられるものであ
り、巡航時には引上げられて０翼の前縁または後縁の一
部をなす。High-lift devices used in aircraft, such as leading edge flaps and trailing edge flaps, are lowered relative to the mother wing for the purpose of temporarily gaining high lift during takeoff and landing, and are pulled up during cruise. 0 Forms part of the leading or trailing edge of the wing.
フラップを円弧軌跡を描いて作動させるには、一般に、
第５図に示すようにフラップＦの円弧運動の軌跡の中心
点Ｏにフラップの取付金具１を支持する（ヒンジ式）か
、円弧軌跡に沿う形状のレールを設けてこのレール上を
フラップが移動するようにする（レール式）かの方式を
とることが多い。To operate the flaps in an arcuate trajectory, generally
As shown in Fig. 5, the flap mounting bracket 1 is supported at the center point O of the trajectory of the arcuate motion of the flap F (hinge type), or a rail shaped to follow the arcuate trajectory is provided and the flap moves on this rail. In most cases, the rail type is used.
ところが、ヒンジ式の場合はヒンジ用の取付金具２等が
常に下方に突出していて巡航時の空力抵抗の点で好まし
くない。一方、レール式の場合には、常に所要軌跡範囲
にレールが存在するため、それがフラップ自身の作動、
または他の部材の作動の邪魔になることが多い。さらに
、レール式は、レールおよびそれに沿って転勤するロー
ラの加工が高価な機械加工および精密な熱処理を必要と
する点およびＭ量が増加する点で好ましくない。However, in the case of the hinge type, the hinge mounting fittings 2 and the like always protrude downward, which is unfavorable in terms of aerodynamic resistance during cruising. On the other hand, in the case of the rail type, the rail is always present within the required trajectory range, so it is the flap's own operation.
Or it often gets in the way of the operation of other parts. Furthermore, the rail type is undesirable because processing the rail and the rollers that move along the rail requires expensive machining and precise heat treatment, and the amount of M increases.
本発明は前述の問題点のない航空機用高揚力装置を得る
ことを目的とする。The object of the present invention is to obtain a high-lift device for an aircraft that does not have the above-mentioned problems.
本発明によれば、０翼の取付金具とフラップ（またはス
ラット）の取付金具との間に介在する連結機構か、互い
に側辺において枢着された複数の台形状または扇形状連
結部材により構成されるとともに、両端部の連結部材が
前記取付金具に端部側辺で枢着され、連結部材同士のお
よび連結部材と取付金具の枢着部の軸線が一点で交差す
るようにされる。According to the invention, the connecting mechanism is interposed between the mounting bracket of the zero wing and the mounting bracket of the flap (or slat), or is constituted by a plurality of trapezoidal or fan-shaped connecting members pivoted to each other at the sides. At the same time, the connecting members at both ends are pivotally connected to the mounting bracket at the side edges of the end portions, so that the axes of the connecting members and the pivoting portions of the connecting member and the mounting bracket intersect at one point.
かかる構成によって、本発明では０翼の基本無形から極
力離れない位置に連結機構を位置させることができ、こ
れによって巡航時の空力抵抗を低くすることが可能とな
る。また、本発明では簡単で安価な構造をもつ連結部材
の使用により、加工面での有利性が得られる。With this configuration, in the present invention, the connecting mechanism can be located at a position as close as possible to the basic shapeless shape of the 0 wing, thereby making it possible to lower aerodynamic drag during cruising. Further, the present invention provides advantages in terms of processing due to the use of a connecting member having a simple and inexpensive structure.
次に、図面について本発明の詳細な説明する。 Next, the present invention will be described in detail with reference to the drawings.
第１図および第２図において、Ｗは０翼を、Ｆはフラッ
プをそれぞれ示す。０翼Ｗは下面に取付金具３を有し、
フラップＦは下面に取付金具４を有している。これらの
取付金具３，４は母ｇｗおよびフラップＦに一体的に固
定されている。In FIGS. 1 and 2, W indicates a zero wing and F indicates a flap, respectively. 0 wing W has a mounting bracket 3 on the lower surface,
The flap F has a mounting bracket 4 on the lower surface. These fittings 3 and 4 are integrally fixed to the mother gw and the flap F.
両数付金具３，４は連結機構５によって連結されている
。連結機構５は複数（図示の場合は４個）の連結部材５
ａ、５ｂ、５ｃ、５ｄによって構成されている。これら
の連結部材の各々は台形状をなしており、それらの側辺
において互いに枢着されている。Both number fittings 3 and 4 are connected by a connecting mechanism 5. The connecting mechanism 5 includes a plurality of (four in the illustrated case) connecting members 5.
It is composed of a, 5b, 5c, and 5d. Each of these connecting members has a trapezoidal shape and are pivotally connected to each other at their sides.
第３図にさらに詳しく示すように台形状の連結部材５ａ
ないし５ｄは隣接する側辺部で互いに入り組んだ形状を
有し、枢軸６によって枢着されている。また、一方の端
部の連結部材５ａと取付金具３とは枢軸７により、また
他方の端部の連結部材５ｄと取付金具４も枢軸８によっ
て枢着されている。これらの枢軸６，７および８の軸線
はフラップＦの円弧運動の軌跡の中心Ｏにおいて交わる
ようにされる。As shown in more detail in FIG. 3, a trapezoidal connecting member 5a
5 d to 5 d have mutually convoluted shapes on adjacent sides and are pivotally connected by a pivot 6 . Further, the connecting member 5a at one end and the mounting bracket 3 are pivotally connected by a pivot 7, and the connecting member 5d at the other end and the mounting bracket 4 are also pivotally connected by a pivot 8. The axes of these pivots 6, 7 and 8 are made to intersect at the center O of the trajectory of the arcuate movement of the flap F.
取付金具３，４はフラップ駆動装置１ｏによって連結さ
れている。図示の例では駆動装置１ｏは油圧式アクチュ
エータである。駆動装置としては他の任意形式のものを
用いることができる、。The fittings 3 and 4 are connected by a flap drive device 1o. In the illustrated example, the drive device 1o is a hydraulic actuator. Any other type of drive device can be used.
連結機構５は上述の構成により屏風状をなすものであっ
て、第１図に示すように駆動装置ｉｏを収縮させてフラ
ップＦを引上げた巡航状態ではジグザク状に折れ曲って
短かくなり、また、第２図に示すように駆動装置１０を
伸長させフラップＦを下降させて高揚力状態を得た時に
は最も伸長する。The coupling mechanism 5 has the shape of a folding screen due to the above-mentioned configuration, and as shown in FIG. As shown in FIG. 2, when the drive device 10 is extended and the flap F is lowered to obtain a high-lift state, it is extended to the maximum.
第１図の位置から第２図の位置へフラップＦが変位する
間中、連結部材の枢軸６，７および８の延長線はすべて
中心Ｏを通るためフラップは中心０まわりの円弧に沿っ
て移動する。During the displacement of the flap F from the position shown in Figure 1 to the position shown in Figure 2, the extension lines of the pivot axes 6, 7 and 8 of the connecting members all pass through the center O, so the flap moves along an arc around the center 0. do.
以上のように構成される装置においては、フラップＦ上
の定点の描く軌跡は０翼Ｗに対して相対的に球面の一部
となり得るけれども、同じ装置をスパン方向に２つ以上
設ければ、原理的にはフラップの軌跡が球面軌跡ではな
く円弧軌跡になるように拘束することができる。In the device configured as described above, the locus drawn by the fixed point on the flap F can be a part of a spherical surface relative to the zero blade W, but if two or more of the same devices are provided in the span direction, In principle, the trajectory of the flap can be constrained to be an arcuate trajectory rather than a spherical trajectory.
フラップの軌跡を円弧軌跡にする他の方法の１例として
は、図に示すように取付金具３とフラップＦとをリンク
機構１１によって連結する。このリンク機構１１は、取
付金具３にビン１２で一端を枢着されたリンクｌｌａと
、フラップＦの先端に一端をビン１３で枢着されたリン
クｌｌｂとからなり、これらのリンクｌｌａ、ｌｌｂは
他端でビン１４により枢着されている。リンク機構１１
はフラップＦが図の紙面に沿って変位するよう拘束する
。なお、球面軌跡を円弧軌跡に拘束する方法としては、
上に述べた以外の任意の方式を選ぶことができる。Another example of a method for making the trajectory of the flap an arcuate trajectory is to connect the mounting bracket 3 and the flap F by a link mechanism 11 as shown in the figure. This link mechanism 11 consists of a link lla whose one end is pivotally connected to the mounting bracket 3 with a pin 12, and a link llb whose one end is pivotally connected to the tip of the flap F with a pin 13, and these links lla and llb are It is pivotally connected at the other end by a pin 14. Link mechanism 11
restrains the flap F so that it is displaced along the plane of the drawing. In addition, as a method to constrain a spherical trajectory to a circular arc trajectory,
Any method other than those mentioned above can be chosen.
以上に述べた実施例では連結部材５ａないし５ｄは板材
で構成されているが、連結部材は板材でな（てもよい。In the embodiments described above, the connecting members 5a to 5d are made of plate materials, but the connecting members may not be made of plate materials.
第４図に示す実施例では、連結部材５ａ７Ｚいし５ｄは
フレーム状部材により構成されている。In the embodiment shown in FIG. 4, the connecting members 5a7Z to 5d are constituted by frame-like members.
また、実施例はフラップの場合についてのものであるが
、本発明の原理はスラットその他の補助機構に適用する
ことが可能である。Furthermore, although the embodiments are directed to flaps, the principles of the present invention can be applied to slats and other auxiliary mechanisms.
本発明によれば、突出部分か少ないことによって空力抵
抗を減らすことができる。また、フラップ等の軌跡の中
心となる枢着部か他の物体との干渉の関係で使用できな
い場合に本発明を用いると効果的である。さらに、本発
明の高揚力装置の連結機構は簡単で安価に製造すること
ができるにもかかわらず、フラップ等を所定の軌跡に沿
って正確に移動させることかできる。According to the present invention, aerodynamic drag can be reduced by reducing the number of protruding parts. Further, the present invention is effective when the pivot point, which is the center of the trajectory of the flap, cannot be used due to interference with other objects. Furthermore, although the high-lift device coupling mechanism of the present invention is simple and inexpensive to manufacture, it is still possible to accurately move the flaps and the like along predetermined trajectories.
第１図は本発明の高揚力装置の巡航位置における縦断面
図、第２図は同高揚力位置におり゛る縦断面図、第３図
は第２図の一部の拡大図、第４図は第３図の変形例を示
す図、第５図は公知例を示す図である。
Ｗ・・・０翼、Ｆ・・・フラップ、３，４・・・取付金
具、５・・・連結（幾構、５ａ 、５ｂ 、５ｃ 、５
ｄ＝・連結部材、６，７．８・・・枢軸、Ｏ・・・円弧
運動の軌跡の中心、１０・・・駆動装置、１１・・・リ
ンク機構。Fig. 1 is a longitudinal cross-sectional view of the high-lift device of the present invention in the cruising position, Fig. 2 is a longitudinal cross-sectional view of the same in the high-lift position, Fig. 3 is an enlarged view of a part of Fig. 2, The figure shows a modification of FIG. 3, and FIG. 5 shows a known example. W...0 wing, F...flap, 3, 4...mounting bracket, 5...connection (structure, 5a, 5b, 5c, 5
d=-Connection member, 6, 7.8... Pivot, O... Center of locus of circular arc movement, 10... Drive device, 11... Link mechanism.
Claims (1)
ットに固定された取付金具と、これらの両取付金具を、
０翼に対するフラップまたはスラットの所要変位を可能
にするように連結する連結機構とｔ有し、この連結機構
は互いに側辺において枢着された複数の台形状または扇
形状連結部材により構成されるとともに、両端部の連結
部材が前記取付金具に端部側辺で枢着され、連結部材同
士のおよび連結部材と取付金具の枢着部の軸線が一点で
交差するようにされ、かつフラップまたはスラットの作
動のための駆動装置が設げられている航空機用高揚力装
置。 ２）連結部材が板材よりなる特許請求の範囲脇１項記載
の航空機用高揚力装置。 ３）連結部材かフレーム材よりなる特許請求の範囲第１
項記載の航空機用高揚力装置。[Claims] 1) A mounting bracket fixed to the mother wing, a mounting bracket fixed to the flap or slat, and both of these mounting brackets,
a connecting mechanism connecting to enable the required displacement of the flap or slat with respect to the wing; the connecting mechanism is constituted by a plurality of trapezoidal or fan-shaped connecting members pivotally connected to each other at the sides; , the connecting members at both ends are pivotally connected to the mounting bracket at the end sides, and the axes of the connecting members and the pivoting parts of the connecting member and the mounting bracket intersect at one point, and the flap or slat An aircraft high-lift device provided with a drive for actuation. 2) The high-lift device for an aircraft according to claim 1, wherein the connecting member is made of a plate material. 3) Claim 1 consisting of a connecting member or a frame material
High-lift device for aircraft as described in .
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP71683A JPS59128098A (en) | 1983-01-06 | 1983-01-06 | High lift device for aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP71683A JPS59128098A (en) | 1983-01-06 | 1983-01-06 | High lift device for aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPS59128098A true JPS59128098A (en) | 1984-07-24 |
| JPS6324879B2 JPS6324879B2 (en) | 1988-05-23 |
Family
ID=11481480
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP71683A Granted JPS59128098A (en) | 1983-01-06 | 1983-01-06 | High lift device for aircraft |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS59128098A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2009508737A (en) * | 2005-09-23 | 2009-03-05 | エアバス・ドイチュラント・ゲーエムベーハー | Aircraft wing altitude trailing edge control surface |
-
1983
- 1983-01-06 JP JP71683A patent/JPS59128098A/en active Granted
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2009508737A (en) * | 2005-09-23 | 2009-03-05 | エアバス・ドイチュラント・ゲーエムベーハー | Aircraft wing altitude trailing edge control surface |
| US8336829B2 (en) | 2005-09-23 | 2012-12-25 | Airbus Operations Gmbh | Advanced trailing edge control surface on the wing of an aircraft |
Also Published As
| Publication number | Publication date |
|---|---|
| JPS6324879B2 (en) | 1988-05-23 |
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