JPH0563358B2 - - Google Patents
Info
- Publication number
- JPH0563358B2 JPH0563358B2 JP14441486A JP14441486A JPH0563358B2 JP H0563358 B2 JPH0563358 B2 JP H0563358B2 JP 14441486 A JP14441486 A JP 14441486A JP 14441486 A JP14441486 A JP 14441486A JP H0563358 B2 JPH0563358 B2 JP H0563358B2
- Authority
- JP
- Japan
- Prior art keywords
- rudder
- control
- steering
- aircraft
- rudders
- 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.)
- Expired - Lifetime
Links
Landscapes
- Mechanical Control Devices (AREA)
- Steering-Linkage Mechanisms And Four-Wheel Steering (AREA)
- Gears, Cams (AREA)
- Retarders (AREA)
Description
【発明の詳細な説明】
〔産業上の利用分野〕
本発明は、航空機の操縦舵装置に関し、特に相
互に隣接する操縦舵相互の干渉の低減を図つた航
空機用操縦舵装置に関する。DETAILED DESCRIPTION OF THE INVENTION [Field of Industrial Application] The present invention relates to an aircraft steering system, and more particularly to an aircraft steering system that aims to reduce interference between adjacent steering wheels.
従来、第７図に示すように、航空機の翼（主翼
および尾翼等）１１には、その後縁側において、
複数（図中では２枚）の操縦舵１２，１３が互い
に隣接してそなえられる箇所がある。
Conventionally, as shown in FIG. 7, the wings (main wings, tail, etc.) 11 of an aircraft have, on the trailing edge side,
There are places where a plurality of (two in the figure) steering rudders 12 and 13 are provided adjacent to each other.
ところで、上述のように操縦舵１２，１３が隣
接してそなえられる場合、例えば第８図に示すよ
うに、操縦舵１２のみを作動させると、操縦舵１
２の左右側縁部から後方へ向けて渦流６，６が発
生する。
By the way, when the steering rudders 12 and 13 are provided adjacent to each other as described above, if only the steering rudder 12 is operated, as shown in FIG. 8, for example, the steering rudder 1
Vortex flows 6, 6 are generated rearward from the left and right side edges of 2.
そして、操縦舵１２と操縦舵１３との隣接部分
近傍において発生する渦流６が、第９図に示すよ
うに操縦舵１３の翼面を操縦舵１２の作動方向と
反対の方向へ力F1で押圧して、操縦舵１３が操
縦舵１２に逆らう向きへ動かされてしまう。この
ように操縦舵１２と操縦舵１３とが干渉して、操
縦舵１２の作動による操舵効果が低下するという
問題点がある。 Then, the vortex 6 generated near the adjacent portion of the control rudder 12 and the control rudder 13 applies a force F 1 to the wing surface of the control rudder 13 in the opposite direction to the operating direction of the control rudder 12, as shown in FIG. Due to the pressure, the steering rudder 13 is moved in a direction opposite to the steering rudder 12. There is a problem in that the steering rudder 12 and the steering rudder 13 interfere with each other as described above, and the steering effect due to the operation of the steering rudder 12 is reduced.
本発明は、上述の問題点の解決を図ろうとする
もので、操縦舵の相互に隣接する縁部から発生す
る渦流を利用して同渦流により生じる操舵効果の
低減を防止できるようにした航空機用操縦舵装置
を提供することを目的とする。 The present invention is an attempt to solve the above-mentioned problems, and is intended to provide an aircraft for use in which a reduction in the steering effect caused by the vortices can be prevented by utilizing the vortices generated from the mutually adjacent edges of the control rudder. The purpose is to provide a steering and rudder device.
このため、本発明の航空機用操縦舵装置は、航
空機に相互に隣接して配設される操縦舵をそな
え、上記操縦舵のうちの一方の舵が、その他方の
舵との隣接部近傍において上記他方の舵の後方ま
で延在する補助舵面を有していることを特徴とす
る。
For this reason, the aircraft control rudder of the present invention includes control rudders disposed adjacent to each other on the aircraft, and one of the control rudders is located near the adjacent portion of the other rudder. It is characterized by having an auxiliary control surface extending to the rear of the other rudder.
上述の本発明の航空機用操縦舵装置では、他方
の操縦舵を作動させると、同他方の操縦舵の両側
縁部で後方へ向かう渦流が発生し、同渦流のうち
の一方の操縦舵近傍で発生する渦流により、上記
一方の操縦舵の隣接部近傍において同一方の操縦
舵を上記他方の操縦舵と反対向きに作動するよう
な方向に空気力を与えられるとともに、上記一方
の操縦舵の有する補助舵面に、上記空気力と逆向
きの、上記一方の操縦舵を上記他方の操縦舵と同
じ方向に作動するような方向への空気力が与えら
れる。
In the above-mentioned aircraft control rudder of the present invention, when the other control rudder is operated, a rearward vortex is generated at both side edges of the other control rudder, and a vortex flows toward the rear near one of the vortexes. The generated vortex gives an aerodynamic force near the adjacent portion of the one steering rudder in a direction that operates the same one steering rudder in the opposite direction to the other steering rudder, and also An aerodynamic force is applied to the auxiliary control surface in a direction opposite to the aerodynamic force such that the one control rudder is actuated in the same direction as the other control rudder.
以下、図面により本発明の一実施例について説
明すると、第１図はその平面図、第２図はその作
用を示すための後面図、第３〜６図はそれぞれそ
の変形例を示す平面図である。
Hereinafter, one embodiment of the present invention will be explained with reference to the drawings. Fig. 1 is a plan view thereof, Fig. 2 is a rear view showing its operation, and Figs. 3 to 6 are plan views showing modifications thereof. be.
第１図に示すように、航空機の翼１の後縁部
に、２枚の操縦舵２，３が隣接して配設され、こ
の操縦舵２，３は、それぞれ前方でヒンジ軸５に
より上下方向に回動可能に枢着され、通常は航空
機の翼１と面一となるよう設定される。そして、
各操縦舵２，３は、図示しない駆動系に駆動され
て航空機の翼１の面に対して上下方向に作動す
る。 As shown in FIG. 1, two control rudders 2 and 3 are disposed adjacent to each other on the trailing edge of a wing 1 of an aircraft, and these control rudders 2 and 3 are moved up and down by hinge shafts 5 in front of each other. It is pivotably mounted so as to be rotatable in the direction, and is normally set to be flush with the wing 1 of the aircraft. and,
Each of the control rudders 2 and 3 is driven by a drive system (not shown) and operates in the vertical direction with respect to the plane of the wing 1 of the aircraft.
また、この作動は、操縦舵２および操縦舵３の
それぞれ個々に行なえるようになつている。 Further, this operation can be performed individually for the steering rudder 2 and the steering rudder 3.
操縦舵３の操縦舵２との隣接部近傍の後縁に
は、操縦舵２の後方まで延在するように形成され
た補助舵面４がそなえられている。 An auxiliary control surface 4 formed to extend to the rear of the control rudder 2 is provided at the trailing edge of the control rudder 3 near a portion adjacent to the control rudder 2 .
本発明の一実施例としての航空機用操縦舵装置
は、上述のごとく構成されているので、航空機の
飛行中等において、操縦舵２を作動させると（第
８図参照）、操縦舵２の両側縁部から後方へ向け
て渦流６，６が発生する。 The aircraft control rudder as an embodiment of the present invention is configured as described above, so that when the control rudder 2 is operated during flight of the aircraft (see FIG. 8), both side edges of the control rudder 2 Vortex flows 6, 6 are generated from the rearward direction.
この渦流６，６のうち、操縦舵２と操縦舵３と
の隣接部近傍で発生する渦流６の一部は、操縦舵
３が操縦舵２の作動方向と反対方向に向くように
操縦舵３の下面を空気力F1で押圧する。 Among these vortices 6, 6, a part of the vortex 6 generated in the vicinity of the adjacent portion between the steering rudder 2 and the steering rudder 3 is transmitted to the steering rudder so that the steering rudder 3 faces in the opposite direction to the operating direction of the steering rudder 2. The lower surface of is pressed by air force F 1 .
また、渦流６の残りは、操縦舵２と操縦舵３と
の間から補助舵面４の上方へ回り込んで補助舵面
４の上面を空気力F2で押圧する。 Further, the remainder of the vortex 6 flows around above the auxiliary control surface 4 from between the control rudder 2 and the control rudder 3, and presses the upper surface of the auxiliary control surface 4 with the aerodynamic force F2 .
このように補助舵面４に加わる空気力F2は、
空気力F1とは逆に、操縦舵３を操縦舵２の作動
方向と同方向に向くように働く。 In this way, the aerodynamic force F 2 applied to the auxiliary control surface 4 is
Opposite to the aerodynamic force F 1 , it acts to direct the steering rudder 3 in the same direction as the operating direction of the steering rudder 2 .
このため、操縦舵３に働く操舵上で有害な空気
力F1が、空気力F2によつて相殺され、つまり操
縦舵２と操縦舵３との干渉が低減されて操縦舵２
の作動による所要の操舵効果を確保することがで
きる。 Therefore, the aerodynamic force F 1 acting on the steering rudder 3 that is harmful to steering is canceled out by the aerodynamic force F 2 , that is, the interference between the steering rudder 2 and the steering rudder 3 is reduced, and the steering rudder 2
The required steering effect can be ensured by the operation of the steering wheel.
本実施例では、補助舵面４が操縦舵３の後縁か
ら後方へ部分的に突出するように設けられている
が、第３図に示すように、操縦舵３の後縁全体を
操縦舵２の後縁より後方まで延在するようにして
もよく、第４図に示すように操縦舵２および操縦
舵３の後縁全体は、ほぼ同一線上に設定し、操縦
舵２と操縦舵３との隣接部近傍において、操縦舵
２の後部を削除し、操縦舵３から同削除部分ま
で、延在するように補助舵面４を配設してもよ
い。 In this embodiment, the auxiliary control surface 4 is provided so as to partially protrude rearward from the rear edge of the control rudder 3, but as shown in FIG. As shown in FIG. The rear part of the steering rudder 2 may be removed in the vicinity of the adjacent portion, and the auxiliary control surface 4 may be provided so as to extend from the steering rudder 3 to the removed portion.
また、第５図に示すように、操縦舵２と操縦舵
３との隣接部分において、操縦舵２の側縁部を後
方にいくにしたがい航空機の翼１の外方へ向くよ
うな傾斜した直線状に形成して、同操縦舵２の側
縁部と対応するように操縦舵３の側縁部を後方に
いくにしたがい航空機の翼１の外方へ向くような
傾斜した直線状に形成してもよい。さらに、第６
図に示すように、操縦舵２と操縦舵３との隣接部
分において、操縦舵２および操縦舵３側縁部を、
ヒンジ側ではまつすぐ後方に向け、途中から第５
図に示すものと同様な方向への傾斜した直線状に
してもよい。 In addition, as shown in FIG. 5, in the adjacent portion between the control rudder 2 and the control rudder 3, as the side edge of the control rudder 2 goes rearward, an inclined straight line is formed that points outward of the wing 1 of the aircraft. The side edge of the control rudder 3 is formed into a straight line that slopes toward the outside of the wing 1 of the aircraft as it goes rearward so as to correspond to the side edge of the control rudder 2. It's okay. Furthermore, the sixth
As shown in the figure, in the adjacent portion of the steering rudder 2 and the steering rudder 3, the side edges of the steering rudder 2 and the steering rudder 3 are
On the hinge side, point the lash immediately backwards, and from the middle, turn the 5th eye.
It may also be a straight line inclined in a direction similar to that shown in the figure.
以上詳述したように、本発明の航空機用操縦舵
装置によれば、航空機に相互に隣接して配設され
る操縦舵をそなえ、上記操縦舵のうちの一方の舵
が、その他方の舵との隣接部近傍において上記他
方の舵の後方まで延在する補助舵面を有している
という簡素な構成により、隣接する操縦舵相互の
干渉を低減でき、操縦舵の作動により所要の操舵
効果を確保できる利点がある。
As described in detail above, according to the aircraft control rudder of the present invention, the aircraft is provided with control rudders disposed adjacent to each other, and one of the control rudders is connected to the other rudder. With the simple structure of having an auxiliary control surface extending to the rear of the other rudder near the adjacent part, mutual interference between adjacent control rudders can be reduced, and the desired steering effect can be achieved by operating the control rudder. This has the advantage of ensuring that
第１〜６図は本発明の一実施例としての航空機
用操縦舵装置を示すもので、第１図はその平面
図、第２図はその作用を示すための後面図、第３
〜６図はそれぞれその変形例を示す平面図であ
り、第７〜９図は従来の航空機用操縦舵装置を示
すもので、第７図はその平面図、第８図はその渦
流を示すための斜視図、第９図はその作用を示す
ための後面図である。
１……航空機の翼、２，３……操縦舵、４……
補助舵面、５……ヒンジ軸、６……渦流、F1，
F2……空気力。
1 to 6 show an aircraft control system as an embodiment of the present invention. FIG. 1 is a plan view thereof, FIG. 2 is a rear view showing its operation, and FIG.
Figures 6 to 6 are plan views showing modified examples thereof, and Figures 7 to 9 show conventional aircraft control and rudder systems. FIG. 9 is a rear view showing its function. 1... Aircraft wing, 2, 3... Control rudder, 4...
Auxiliary control surface, 5... Hinge axis, 6... Vortex, F 1 ,
F 2 ...Air force.
Claims (1)
そなえ、上記操縦舵のうちの一方の舵が、その他
方の舵との隣接部近傍において上記他方の舵の後
方まで延在する補助舵面を有していることを特徴
とする、航空機用操縦舵装置。1. An auxiliary rudder in which an aircraft is provided with control rudders arranged adjacent to each other, and one of the rudders extends to the rear of the other rudder in the vicinity of the adjacent part with the other rudder. An aircraft control and rudder device characterized by having a surface.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP14441486A JPS62299496A (en) | 1986-06-20 | 1986-06-20 | Steering gear for aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP14441486A JPS62299496A (en) | 1986-06-20 | 1986-06-20 | Steering gear for aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPS62299496A JPS62299496A (en) | 1987-12-26 |
| JPH0563358B2 true JPH0563358B2 (en) | 1993-09-10 |
Family
ID=15361617
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP14441486A Granted JPS62299496A (en) | 1986-06-20 | 1986-06-20 | Steering gear for aircraft |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS62299496A (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP5046115B2 (en) * | 2007-12-27 | 2012-10-10 | 独立行政法人 宇宙航空研究開発機構 | Control surface noise reduction device |
| JP5830086B2 (en) | 2011-03-30 | 2015-12-09 | 一般社団法人日本航空宇宙工業会 | Aircraft high lift device |
| JP5956803B2 (en) * | 2012-03-29 | 2016-07-27 | 一般社団法人日本航空宇宙工業会 | Aircraft high lift device |
-
1986
- 1986-06-20 JP JP14441486A patent/JPS62299496A/en active Granted
Also Published As
| Publication number | Publication date |
|---|---|
| JPS62299496A (en) | 1987-12-26 |
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