JPH1035590A - Outer wing variable sweepback angle aircraft - Google Patents
Outer wing variable sweepback angle aircraftInfo
- Publication number
- JPH1035590A JPH1035590A JP18926396A JP18926396A JPH1035590A JP H1035590 A JPH1035590 A JP H1035590A JP 18926396 A JP18926396 A JP 18926396A JP 18926396 A JP18926396 A JP 18926396A JP H1035590 A JPH1035590 A JP H1035590A
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- Prior art keywords
- wing
- angle
- outer wing
- aircraft
- swept
- 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.)
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Abstract
Description
【０００１】[0001]
【発明の属する技術分野】本発明は、高亜音速ないし超
音速において、速度性能および運動性能が優れるととも
に、遠方から照射される電波の反射を少くする低反射性
を向上できる外翼可変後退角航空機に関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to an outer wing variable swept angle capable of improving speed performance and kinetic performance at high subsonic speed or supersonic speed and improving low reflectivity for reducing reflection of radio waves irradiated from a distance. About aircraft.
【０００２】[0002]
【従来の技術】航空機、特に戦闘用航空機においては、
侵攻／戦闘航法時には、レーダー照射に対する電波の低
反射性（以下低反射性という）を高め、いわゆるステル
ス性に優れたものにするとともに、巡航時，離着陸時、
若しくは近距離格闘戦時には、誘導抵抗を少くして速度
性能を向上させ、また高い揚力を大迎角まで維持させて
離着陸性能を向上させ、さらには、舵面類の動きを高め
て運動性能に優れた機動性の高いものにする必要があ
る。2. Description of the Related Art In aircraft, especially in combat aircraft,
At the time of invasion / battle navigation, while increasing the low reflectivity (hereinafter referred to as low reflectivity) of radio waves with respect to radar irradiation, so as to provide superior so-called stealth, at the time of cruising, takeoff and landing,
Or, during short-range combat, reduce inductive resistance to improve speed performance, maintain high lift up to a large angle of attack to improve take-off and landing performance, and further enhance control surface movement to improve athletic performance. It needs to be excellent and highly mobile.
【０００３】これらの要求のなかで、低反射性を高める
手段としては、翼前縁及び機体各部の陵線や継ぎ目を後
方へ大きく傾斜させ、大後退角にした、いわゆる大後退
角低反射形態にすることが有効であることが知られてい
る。特に、図６（ａ）に示すように、先端部から後端部
まで一定の大きい前縁後退角Λにした主翼０２具える無
尾翼機は、ステルス性に優れたものにできることがわか
っている。[0003] In these demands, as means for increasing the low reflectivity, a so-called large swept-back low-reflection mode in which the leading edges of the wings and the ridges and seams of various parts of the fuselage are greatly inclined rearward to have a large swept angle. Is known to be effective. In particular, as shown in FIG. 6A, it is known that a tailless wing machine having a main wing 02 having a constant large leading edge swept angle Λ from the front end to the rear end can have excellent stealth properties. .
【０００４】また、高迎角特性を高める手段としては、
図６（ｂ）に示すように前縁を大後退角Λにした内翼０
３と、小後退角Λ′にした外翼０４とを組み合わせた、
いわゆるダブルデルタ翼形態の主翼０５にすることによ
り、内翼０３前縁剥離渦と外翼０４前縁渦との干渉によ
って、高い揚力を大迎角まで維持できるので、有効であ
ることがわかっている。As means for improving the high angle of attack characteristics,
As shown in FIG. 6 (b), the inner wing 0 with the leading edge set to a large swept angle Λ
3 and the outer wing 04 with a small swept angle Λ '
The main wing 05 having a so-called double delta wing configuration is effective because a high lift can be maintained up to a large angle of attack due to interference between the inner wing 03 leading edge separation vortex and the outer wing 04 leading edge vortex. I have.
【０００５】さらに、低速性能と高速性能とを高める手
段としては、図６（ｃ）に示すように、主翼０６を付け
根付近に設けた回転軸０７まわりに、矢視で示すよう
に、水平面内で回転可能にする、いわゆる可変後退翼形
態にすることが有効であることがわかっている。Further, as means for improving the low-speed performance and the high-speed performance, as shown in FIG. 6 (c), as shown by an arrow, a horizontal plane 07 is provided around a rotation axis 07 provided near the base of the main wing 06. It has been found that it is effective to adopt a so-called variable swept wing configuration that enables rotation at a rotational speed.
【０００６】また、この可変後退翼形態では、主翼０６
に大後退角を設定する後退位置にすることによって、前
述した大後退角低反射形態主翼０２に近い形態にでき、
低反射性を向上させることができるとともに、主翼０６
を小後退角に設定する前進位置にすることによって、前
述したダブルデルタ形態の主翼０５に近い形態にでき、
高迎角特性を高めることができる。さらには、主翼０６
を前進位置にすることに伴い、主翼０６の前縁部、若し
くは後縁部に翼幅方向に装備される舵面類が、外部流と
正対に近い配置となり、動きが良くなり運動性能に優れ
たものにすることができる。In this variable swept wing configuration, the main wing 06
By setting the swept position to set a large swept angle to the large swept angle low-reflection form main wing 02 described above,
The low reflectivity can be improved, and the wing 06
Is set to a small swept-back angle, thereby making the above-mentioned main wing 05 in the double delta form possible,
High angle of attack characteristics can be enhanced. Furthermore, the wing 06
To the forward position, the control surfaces mounted in the wing width direction on the leading edge or the trailing edge of the main wing 06 are arranged close to the external flow, and the movement is improved and the motion performance is improved. It can be excellent.
【０００７】このように、それぞれの形態にすることに
よる利点がある反面、次に示す不具合が各形態にある。
すなわち、図６（ａ）に示す大後退角低反射形態のもの
では、翼幅（アスペクト比）が小さいため、特に大迎角
時に誘導抵抗が大きくなり、速度性能が落ちるととも
に、揚力勾配が小さく、高迎角にしても高揚力が得られ
ず、離着陸滑走距離が長くなり、離着陸性能に劣るもの
となる。As described above, although each of the embodiments has advantages, each embodiment has the following disadvantages.
That is, in the case of the large retreat angle low reflection type shown in FIG. 6A, since the wing width (aspect ratio) is small, especially at large angles of attack, the induction resistance increases, the speed performance decreases, and the lift gradient decreases. However, even at a high angle of attack, a high lift cannot be obtained, and the takeoff and landing run distance becomes longer, resulting in poor takeoff and landing performance.
【０００８】また、前縁だけでなく、後縁も大後退角を
有するものとなるため、これらの前縁および／又は後縁
に沿って配設され、舵面を枢着するヒンジラインも大後
退角のものとなり、舵面の効きが面積に比して悪いもの
になり、運動性能が悪くなるという不具合がある。さら
に、機体重心位置の後方に位置する外翼部には、下向き
の揚力（ダウンフォース）を発生させて、内翼部で発生
した機体の頭下げモーメントを打消すようにしているこ
とに伴う後述する不具合もある。In addition, since not only the leading edge but also the trailing edge has a large receding angle, the hinge line disposed along the leading edge and / or the trailing edge and pivotally connecting the control surface is also large. There is a disadvantage that the control surface becomes ineffective compared to the area due to the backward angle, and the exercise performance deteriorates. Further, a downward lift (downforce) is generated in the outer wing located behind the position of the center of gravity of the aircraft, so that the head lowering moment of the aircraft generated in the inner wing is counteracted. There is also a defect.
【０００９】また、図６（ｂ）に示すダブルデルタ翼形
態のものでは、低反射性において大後退角低反射形態に
劣るものとなり、ステルス性が不充分で、侵攻／戦闘航
法時に不利になるという致命的な不具合がある。The double delta wing configuration shown in FIG. 6 (b) is inferior in large reflection angle low reflection configuration in low reflectivity, insufficient in stealth, and disadvantageous in invasion / battle navigation. There is a fatal defect.
【００１０】これらの大後退角低反射性形態、およびダ
ブルデルタ形態の航空機の不具合を解消するために考え
だされた可変後退翼形態の航空機では、前述した形態の
航空機の不具合は、飛行ミッションに対応させて、図６
（ｃ）に示す矢視で示すように、主翼０６を回転軸０７
まわり回転させることによって、形態を変えて解消でき
るため、これまで米国のＦ−１１１，Ｆ−１４等で採用
され、運用されている。[0010] In the large swept-back low-reflection type and the variable swept-wing type aircraft devised to solve the problems of the double delta type aircraft, the above-mentioned types of aircraft problems are caused by the flight mission. Figure 6
As shown by the arrow shown in FIG.
By rotating around, the form can be changed and eliminated, so that it has been adopted and used in F-111, F-14 and the like in the United States.
【００１１】しかしながら、これらの従来の可変後退翼
形態の航空機では、主翼０６全体を付け根部付近から回
転させるようにしたため、可動機構の重量が大きくなる
とともに、主翼０６に発生する膨大な空気力が可動機構
に集中して、飛行ミッションに対応した形態の円滑な変
更を困難にし、形態の変更に信頼性が欠けるものとなる
不具合がある。[0011] However, in these conventional variable swept-wing aircraft, the entire main wing 06 is rotated from the vicinity of the root, so that the weight of the movable mechanism increases and the enormous aerodynamic force generated in the main wing 06 is generated. Concentrating on the movable mechanism, it is difficult to smoothly change the form corresponding to the flight mission, and there is a problem that the form change becomes unreliable.
【００１２】また、回転軸０７が機体重心０８付近に設
けられていることと、回転する部分の面積が大きいこと
により、主翼０６の回転に伴う圧力中心の移動が大きく
なって、機体を水平飛行の姿勢にする、いわゆるトリム
の大幅な補正が必要となる不具合もある。Further, since the rotating shaft 07 is provided near the aircraft center of gravity 08 and the area of the rotating portion is large, the movement of the pressure center accompanying the rotation of the main wing 06 becomes large, and the aircraft flies horizontally. There is also a problem that a large correction of the so-called trim is required.
【００１３】[0013]
【発明が解決しようとする課題】本発明は、飛行ミッシ
ョンに対応して、種々の特性が要求される戦闘用航空機
に使用されている、外翼翼端部を前進、若しくは後退さ
せて後退角を変えて飛行するようにした外翼可変後退角
航空機、いわゆる、従来の可変後退翼形態の航空機の不
具合を解消するため、形態を変更するために回転する翼
の面積を小さくして、可変機構を重量の小さい、信頼性
の高いものにできるとともに、形態を変更するために、
機体重心から離れた位置の翼を回転させるようにして、
回転に伴う圧力中心の移動を少なくし、トリムの補正を
少いものにできる外翼可変後退角航空機を提供すること
を課題とする。SUMMARY OF THE INVENTION In accordance with the present invention, the present invention relates to a fighting aircraft requiring various characteristics in accordance with a flight mission. In order to eliminate the problem of the variable wing angle of the outer wing, which is a so-called conventional variable wing type aircraft, the area of the wing rotating to change the form is reduced, and the variable mechanism is changed. In order to make it lightweight and reliable, and to change the form,
By rotating the wing away from the center of gravity of the machine,
It is an object of the present invention to provide an outer wing variable swept-angle aircraft capable of reducing movement of a pressure center due to rotation and reducing trim correction.
【００１４】[0014]
【課題を解決するための手段】このため、本発明の外翼
可変後退角航空機は、次の手段とした。SUMMARY OF THE INVENTION For this reason, an outer wing variable swept angle aircraft according to the present invention has the following means.
【００１５】（１） 大後退角にされるとともに、後端
部を機体重心位置よりも、後方にまで延設した前縁を具
えた内翼を設けた。なお、内翼は、無尾翼機のように、
前縁の先端部が機体の先端部まで延設されたものでも良
く、又は機体重心位置より前方の胴体の途中まで延設し
たもので良く、さらには、大後退角にされた前縁の先端
部を、小さい後退角の前縁を設けるようにしたものでも
良い。また、前縁の先端部より前方に、カナードを設け
たカナード機に設けるようにすることもできる。(1) An inner wing having a large swept angle and a leading edge extending rearward from the center of gravity of the machine to the rear end is provided. The inner wing, like a tailless aircraft,
The leading end of the leading edge may extend to the leading end of the fuselage, or may extend to the middle of the fuselage in front of the position of the center of gravity of the aircraft. The portion may be provided with a leading edge with a small swept angle. Further, it can be provided on a canard machine provided with a canard ahead of the front end portion of the leading edge.
【００１６】（２） 機体重心よりも後方に翼付根部が
設けられ、その前縁が、内翼の大後退角にされた前縁と
略同一直線上、若しくは略平行になるように後退した大
後退角位置と、内翼の大後退角にされた前縁よりも小さ
な後退角になるように前進させた小後退角位置とに、翼
付根部の回動により設定できる外翼を設けた。なお、小
後退角位置とは、外翼翼端部の前進、換言すれば前縁の
後退角を小さくすることによって、外翼の前縁部、およ
び／又は後縁部に沿って設けられるヒンジラインに枢着
された舵面の効きが向上する位置に、舵面が外部流に対
して配置されるようになる位置をいう。(2) A wing root is provided behind the center of gravity of the aircraft, and the leading edge of the wing is retreated so as to be substantially collinear with or substantially parallel to the leading edge of the inner wing that is set to a large retreat angle. An outer wing that can be set by turning the root of the wing is provided at a large retreat angle position and a small retreat angle position where the inner wing is advanced so as to have a smaller swept angle than the leading edge of the inner wing that is set to a large swept angle. . The small swept-back position refers to a hinge line provided along the leading edge and / or the trailing edge of the outer wing by advancing the outer wing tip, in other words, reducing the swept angle of the leading edge. Means a position where the control surface is arranged with respect to the external flow at a position where the effect of the control surface pivotally attached to is improved.
【００１７】（３） 機体に設定される垂直軸（鉛直
軸）方向から、前，後および／又は左，右方向に傾斜さ
せて翼取付部に立設され、翼取付部が軸着された外翼
を、そのまわりに回動させ、外翼の翼端部を後退させて
外翼を大後退角位置に設定するとともに、外翼の翼端部
を前進させて外翼を小後退角位置に設定する回転軸を設
けた。(3) From the vertical axis (vertical axis) direction set on the fuselage, the wing mounting portion is erected at an angle to the front, rear, and / or left and right directions, and the wing mounting portion is axially mounted. Rotate the outer wing around it, retreat the wing tip of the outer wing to set the outer wing to the large swept position, and advance the outer wing tip to move the outer wing to the small swept position. A rotation axis to be set is provided.
【００１８】本発明の外翼可変後退角航空機は、上述
（１）〜（３）の手段により、侵攻／戦闘航法時には、
外翼を回転軸まわりに回転させて、後退させ、前縁後退
角を内翼の前縁の後退角と揃えることにより、前方から
のレーダー照射に対する低反射性を向上させることがで
きる。According to the above-mentioned means (1) to (3), the outer wing variable swept angle aircraft of the present invention can be used during invasion / battle navigation.
By rotating the outer wing around the rotation axis to make it retreat and aligning the leading edge retreat angle with the retreat angle of the leading edge of the inner wing, it is possible to improve low reflectivity against radar irradiation from the front.
【００１９】また、低反射性を必要としない巡航時や離
着陸時、または機動性に対する要求が低反射性に対する
要求に優先する近距離格闘戦時には、外翼を回転軸まわ
りに回転させて前進させ、後退角を減少させて、ダブル
デルタ形態を形成することにより、翼幅（アスペクト
比）が増大し、誘導抵抗が減少し、速度性能が向上する
ほか、内翼前縁剥離渦と外翼前縁剥離渦の干渉によっ
て、高い揚力を大迎角まで維持できるという、ダブルデ
ルタ翼形態の利点を享受できる。また、外翼に装備され
た舵面類も、後退角が減少することによって、動きが向
上する。このように、巡航性能，離着陸性能，および機
動性が、大後退角低反射形態に比して向上した航空機に
できる。Further, at the time of cruising or take-off and landing that does not require low reflectivity, or at the time of short-range combat where the demand for maneuverability precedes the request for low reflectivity, the outer wing is rotated around the rotation axis to move forward. By reducing the swept angle and forming a double delta configuration, the wing width (aspect ratio) is increased, the induction resistance is reduced, the speed performance is improved, and the inner wing leading edge separation vortex and the outer wing front are reduced. Due to the interference of the edge separation vortex, the advantage of the double delta wing configuration that a high lift can be maintained up to a large angle of attack can be enjoyed. In addition, the control surfaces of the outer wings are improved in movement by reducing the swept angle. In this manner, an aircraft having improved cruising performance, take-off and landing performance, and maneuverability as compared with the large reverse angle low-reflection mode can be provided.
【００２０】さらに、回転軸を回転させて、外翼を前進
させ、又は後退させる可変機構は、回転する外翼部分が
比較的小さく、また空力的負荷も小さいため、比較的軽
量にできるとともに、円滑に作動でき、信頼性に富むも
のにできるほか、回転軸及び可動範囲が機体の重心位置
から離れているため、回転に伴う圧力中心の移動が少く
なり、トリムの変化量を小さくでき、大幅な補正が不要
になる。なお、比較的小さいながら、トリム変化の発生
は起こり得るが、この補正は、従来通り舵面によって行
うこともできるが、回転軸を鉛直軸から傾斜させて立設
したことによって、外翼の前進位置と後退位置とで、外
翼の取付け角を自動的に変化し、トリムの補正を自動的
に行うことができる。Further, the variable mechanism for rotating the rotating shaft to advance or retreat the outer wing has a relatively small rotating outer wing portion and a small aerodynamic load. Smooth operation and high reliability can be achieved.In addition, since the rotation axis and movable range are far from the center of gravity of the fuselage, the movement of the pressure center due to rotation is reduced, and the amount of trim change can be reduced, greatly reducing No special correction is required. Although a relatively small change in the trim may occur, this correction can be performed by the control surface as in the past.However, since the rotation axis is inclined from the vertical axis, the outer wing moves forward. The mounting angle of the outer wing can be automatically changed between the position and the retreat position, and the trim can be automatically corrected.
【００２１】また、ステルス性に優れた、無尾翼機のよ
うに、大後退角低反射形態の航空機においては、外翼部
には下向き揚力（ダウンフォース）を発生させて、頭上
げモーメントを発生させ、内翼部の発生する頭下げモー
メントを打消すようにしているが、回転軸をわずかに
（数 deg. 程度）内傾，または後傾させることによっ
て、この鉛直軸から傾斜させた回転軸に軸着された外翼
は、前進位置において、後退位置にあるときよりも取付
角を減らすことができ、外翼の前進によって生じるモー
メントアームの減少を外翼に発生する下向き揚力の増大
によって打消すことができる。Also, in an aircraft having a large swept angle and low reflection, such as a tailless aircraft having excellent stealth properties, a downward lift (downforce) is generated on the outer wing to generate a head-lifting moment. The head lowering moment generated by the inner wing part is canceled out, but the rotation axis is tilted slightly (about several degrees) inward or backward to incline from this vertical axis. The outer wing shaft mounted on the outer wing can have a smaller mounting angle in the forward position than in the retreat position, and the reduction of the moment arm caused by the forward movement of the outer wing can be achieved by increasing the downward lift generated in the outer wing. Can be turned off.
【００２２】また、カナードの装備や、フライ・バイ・
ワイヤ・システムの活用による重心位置の後退によっ
て、頭上げモーメントが大きくなるようなことがある場
合は、上述とは逆に、前進位置において、後退位置にあ
るよりも取付角が増えるよう、回転軸を外傾、または前
傾させることによって、外翼に生じる揚力を増大させる
ことにより、頭上げモーメントを小さくすることができ
る。Also, canard equipment and fly-by
If the lifting moment of the center of gravity can be increased due to the retraction of the center of gravity due to the use of the wire system, conversely to the above, the rotation axis is set so that the mounting angle is larger in the advanced position than in the retracted position. Is tilted outward or forward to increase the lift generated on the outer wing, thereby reducing the head-lifting moment.
【００２３】[0023]
【発明の実施の形態】以下、本発明の外翼可変後退角航
空機の実施の一形態を、図面にもとづき説明する。図１
は、本発明の外翼可変後退角航空機の実施の第１形態を
示す図で、図１（ａ）は平面図、図１（ｂ）は側面図、
図１（ｃ）は背面図である。DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS An embodiment of an outer wing variable sweep angle aircraft according to the present invention will be described below with reference to the drawings. FIG.
1 is a diagram showing a first embodiment of an outer wing variable swept-angle aircraft of the present invention, wherein FIG. 1A is a plan view, FIG. 1B is a side view,
FIG. 1C is a rear view.
【００２４】本実施の形態は、無尾翼機に適用したもの
で、機体の先端部には大後退角Λの前縁をもつ内翼２が
取付けられている。内翼２の前縁先端は機体の略先端ま
で延設されるとともに、前縁後端は機体の重心位置４よ
りも後方になるように配設されている。The present embodiment is applied to a tailless aircraft, and an inner wing 2 having a leading edge with a large swept angle Λ is attached to the tip of the fuselage. The leading edge of the inner wing 2 extends substantially to the tip of the fuselage, and the trailing edge of the leading edge is located rearward of the center of gravity 4 of the fuselage.
【００２５】また、外翼１は、翼付根部５が重心位置４
より後方に立設された回転軸３に軸着されて、大後退角
位置１ａと小後退角位置１ｂの２位置に設定できる。す
なわち、外翼１は、その前縁の後退角が大後退角Λにさ
れて、内翼２の前縁の延長線上に、前縁が配置がされる
大後退角位置１ａと、回転軸３まわりの回動によって、
翼端部が前進して、図１のＡ部である、図２（ａ）に示
す外翼１の前縁部および後縁部に設けた舵面６に、外部
流が効果的に作用して舵面６の効きが向上する小後退角
Λ′に前縁が配置される小後退角位置１ｂとに設定でき
る。In the outer wing 1, the root portion 5 of the wing is located at the center of gravity 4.
It can be set at two positions, a large retreat angle position 1a and a small retreat angle position 1b, by being mounted on the rotating shaft 3 which is provided upright at the rear. That is, the outer wing 1 has a large swept-back position 1a where the leading edge is disposed on an extension of the leading edge of the inner wing 2 with the swept angle of the leading edge thereof set to a large swept angle Λ, and the rotating shaft 3 By turning around,
The wing tip advances, and the external flow effectively acts on the control surface 6 provided at the leading edge and the trailing edge of the outer wing 1 shown in FIG. Thus, it is possible to set the small retreat angle position 1b where the leading edge is disposed at the small retreat angle Λ 'at which the effectiveness of the control surface 6 is improved.
【００２６】また、回転軸３は機体の垂直軸（鉛直軸）
方向から後方にθb ，内側にθi 傾斜させて立設されて
いる。The rotation axis 3 is a vertical axis (vertical axis) of the body.
It is erected at an angle θ b backward and θ i inward from the direction.
【００２７】外翼１を大後退角位置１ａに設定した、無
尾翼機においては、前述したように重心位置４より後方
の外翼１に発生する下向きの揚力−Ｌによって、内翼２
によって生じる頭下げモーメントを打消すようにしてお
り、外翼１の後退角の減少、すなわち外翼１の圧力中心
の重心位置への接近により、この頭下げモーメントを打
消すモーメントの発生が小さくなるが、回転軸３をθi
だけ内傾させるとともに、θb だけ後傾させているた
め、図２（ｃ）に示すように、外翼１が前進して小後退
角位置１ｂに設定されたときの取付角ε、すなわち外翼
１の翼面と、機軸に平行な鉛直面との交線が水平面とな
す角は、図２（ｂ）に示す外翼０１が後退して大後退角
位置１ｂにあるときの取付角εよりも小さくなり、すな
わち前縁下げ気味になり、下向きの揚力を大きくでき、
圧力中心の重心位置４への接近による頭上げモーメント
の減少を、この取付角との変動により打消すことができ
る。In a tailless wing aircraft in which the outer wing 1 is set to the large swept-back position 1a, the inner wing 2 is caused by the downward lift -L generated on the outer wing 1 behind the center of gravity 4 as described above.
The head lowering moment generated by the outer blade 1 is canceled out, and the reduction of the swept angle of the outer blade 1, that is, the approach of the pressure center of the outer blade 1 to the position of the center of gravity reduces the generation of the moment for canceling the head lowering moment. But the rotation axis 3 is θ i
Together to the inner inclined only, since inclined rearwards by theta b, as shown in FIG. 2 (c), setting angle epsilon, i.e. outside when the outer blade 1 is set to a small receding angle position 1b advances The angle formed by the intersection of the wing surface of the wing 1 and the vertical plane parallel to the machine axis with the horizontal plane is the mounting angle ε when the outer wing 01 shown in FIG. Smaller, that is, the leading edge is slightly lowered, the downward lift can be increased,
The decrease in the lifting moment due to the approach of the center of pressure to the position of the center of gravity 4 can be counteracted by the variation with the mounting angle.
【００２８】次に、回転軸３の内傾角θi 及び後傾角θ
b を媒介変数とした、後退角Λと取付角εの関係を図２
に示す。なお、図においては、Λ＝０のとき，ε＝０，
また上下反角Γも０とした場合の例を示しているが、実
際にはΛ＝０までの可動範囲は、必ずしも必要ない。Next, the inclining angle θ i and the backward inclining angle θ of the rotating shaft 3
Fig. 2 shows the relationship between the receding angle Λ and the mounting angle ε with b as a parameter.
Shown in In the figure, when Λ = 0, ε = 0,
In addition, although an example is shown in which the upside-down angle と し た is also set to 0, the movable range up to Λ = 0 is not always necessary.
【００２９】また、Λ＝０のときのε，Γをεo ，Γo
としたとき，εとεo ，Γo ，θi，θb ，Λの関係
は、数１で表わされる。但し，ε，εo ，Γo ，θi ，
θb を微小と仮定した。Further, ε, と き when Γ = 0 is defined as ε o , Γ o
Then, the relationship between ε and ε o , Γ o , θ i , θ b , Λ is expressed by Equation 1. Where ε, ε o , Γ o , θ i ,
θ b was assumed to be small.
【００３０】[0030]
【数１】 (Equation 1)
【００３１】次に、図４は、本発明の外翼可変後退角航
空機の実施の第２形態として、フライ・バイ・ワイヤ・
システム等によって、重心位置の後退に伴う縦静安定が
負となることを許容した場合の無尾翼機を示す図で、図
４（ａ）は平面図、図４（ｂ）は側面図、図４（ｃ）は
背面図である。Next, FIG. 4 shows a fly-by-wire system according to a second embodiment of the outer wing variable sweep angle aircraft of the present invention.
FIG. 4 (a) is a plan view, FIG. 4 (b) is a side view, and FIG. 4 (b) is a view showing a tailless wing aircraft in a case where the system or the like allows negative vertical stability due to the retreat of the center of gravity. FIG. 4C is a rear view.
【００３２】本実施の形態では、重心位置４が図１に示
す実施の第１形態のものより後方にあるため、外翼１に
は上向き揚力Ｌを発生させにようにしている。In the present embodiment, since the position of the center of gravity 4 is behind the first embodiment shown in FIG. 1, an upward lift L is generated on the outer wing 1.
【００３３】このため、回転軸３は外側に傾斜させた外
傾角θi にするとともに、前方に傾斜させた前傾角θb
にして、外翼１の翼取付部５に立設した。これにより、
外翼１が前進した小後退角位置１ｂでは、外翼１が後退
した大後退角位置１ａよりも取付角が大きく（頭上げ気
味に）なり、外翼１の圧力中心の，重心位置４への接近
による頭下げモーメントの減少を外翼１に発生する揚力
の増加で打消すことができる。For this reason, the rotating shaft 3 has an outward inclination angle θ i inclined outward and a forward inclination angle θ b inclined forward.
Then, the outer wing 1 was erected on the wing mounting portion 5. This allows
At the small retreat angle position 1b in which the outer wing 1 has advanced, the mounting angle is larger (head-up) than the large retreat angle position 1a in which the outer wing 1 has retreated, and the pressure center of the outer wing 1 moves to the center of gravity position 4. The decrease in the head-down moment due to the approach of the wing can be canceled by the increase in the lift generated in the outer wing 1.
【００３４】次に、図５は、本発明の外翼可変後退角航
空機の実施の第３形態として、カナード機に適用した場
合を示す図で、図５（ａ）は平面図、図５（ｂ）は側面
図、図５（ｃ）は背面図である。FIG. 5 is a diagram showing a third embodiment of an outer wing variable sweep angle aircraft of the present invention applied to a canard aircraft. FIG. 5 (a) is a plan view and FIG. FIG. 5B is a side view, and FIG. 5C is a rear view.
【００３５】本実施の形態では、機体の先端部に装備し
たカナード８が頭上げモーメントを発生するため、外翼
１には上向き揚力Ｌを発生させて、カナード５で発生す
るモーメントとの釣合いをとるようにしている。このた
め、回転軸３は外側に傾斜させた外傾角θi にするとと
もに、前方の傾斜させた前傾角θb にして、外翼１の翼
取付部５に立設した。これにより、外翼１が前進した小
後退角位置１ｂでは、外翼１が後退した大後退角位置１
ａより取付角が大きく（頭上げ気味に）なり、外翼１の
圧力中心の、重心位置４への接近による頭下げモーメン
トの減少を外翼に発生する揚力の増分により打消すこと
ができる。In this embodiment, since the canard 8 provided at the tip of the fuselage generates a head-lifting moment, an upward lift L is generated on the outer wing 1 to balance the moment generated by the canard 5. I am taking it. Therefore, the rotary shaft 3 while the outer inclination angle theta i which is inclined outwardly, in the inclination angle theta b before was the forward tilt and standing on blade attaching portion 5 of the outer blade 1. Thus, at the small retreat angle position 1b where the outer wing 1 has advanced, the large retreat angle position 1 where the outer wing 1 has retreated.
Since the mounting angle is larger than (a), the head lowering moment due to the pressure center of the outer wing 1 approaching the position of the center of gravity 4 can be canceled by the increase in the lift generated on the outer wing.
【００３６】[0036]
【発明の効果】以上説明したように、本発明の外翼可変
後退角航空機によれば、特許請求の範囲に示す構成によ
り、 （１） 侵攻／戦闘航法時の低反射性と、良好な離着陸
性能，巡航／格闘戦時の低誘導抵抗を、大後退角低反射
形態とダブルデルタ形態との間の変換を、比較的軽量な
可変後退機構によって行うことにより、両立させること
ができる。As described above, according to the outer wing variable sweep angle aircraft of the present invention, the following features are provided: (1) low reflectivity during invasion / battle navigation and good takeoff and landing Performance and low induction resistance during cruising / combat battle can be achieved by converting between the large reverse angle low reflection type and the double delta type by using a relatively lightweight variable retraction mechanism.
【００３７】（２） また、外翼を前進させ又は後退さ
せる可変機構は、回転する外翼部分が比較的小さく、ま
た空力的負荷も小さいため、比較的軽量で済み、信頼性
の高いものにできるほか、回転軸及び可動範囲が機体の
重心位置から離れているため、回転に伴う圧力中心の移
動が少くなり、トリムの変化量を小さくできる。(2) The variable mechanism for moving the outer wing forward or backward has a relatively small rotating outer wing and a small aerodynamic load. In addition, since the rotation axis and the movable range are separated from the position of the center of gravity of the body, the movement of the pressure center due to the rotation is reduced, and the amount of change in trim can be reduced.
【００３８】（３） また、可変機構の回転軸を傾斜さ
せ、後退角の変化と共に外翼の取付角を変化させること
により、圧力中心の移動に伴うトリム変化を補正し、舵
面の負荷を軽減することができる。(3) In addition, by changing the rotation axis of the variable mechanism and changing the mounting angle of the outer wing together with the change of the sweepback angle, the trim change accompanying the movement of the pressure center is corrected, and the load on the control surface is reduced. Can be reduced.
【図１】本発明の外翼可変後退角航空機の実施の第１形
態を示す図で、図１（ａ）は平面図、図１（ｂ）は側面
図、図１（ｃ）は背面図、FIG. 1 is a view showing a first embodiment of an outer wing variable swept-angle aircraft of the present invention, wherein FIG. 1 (a) is a plan view, FIG. 1 (b) is a side view, and FIG. 1 (c) is a rear view. ,
【図２】図１に示すＡ部の詳細を示す図で、図２（ａ）
は平面図、図２（ｂ）は図２（ａ）の矢視Ａ−Ａにおけ
る外翼の水平面からの取付角を示す断面図、図２（ｃ）
は図２（ａ）の矢視Ｂ−Ｂにおける外翼の水平面からの
取付角を示す断面図、FIG. 2 is a diagram showing details of a portion A shown in FIG. 1, and FIG.
2B is a plan view, FIG. 2B is a cross-sectional view showing the mounting angle of the outer wing from a horizontal plane taken along the line AA in FIG. 2A, and FIG.
FIG. 2A is a cross-sectional view showing the mounting angle of the outer wing from a horizontal plane, taken along the line BB in FIG.
【図３】回転軸の内傾角θi と後傾角θb とを媒介変数
とした、後退角と取付角の関係を示す図、FIG. 3 is a diagram showing a relationship between a receding angle and a mounting angle, using the inclining angle θ i and the backward tilting angle θ b of the rotation axis as parameters;
【図４】実施の第２形態を示す図で、図４（ａ）は平面
図、図４（ｂ）は側面図、図４（ｃ）は背面図、4 (a) is a plan view, FIG. 4 (b) is a side view, FIG. 4 (c) is a rear view,
【図５】実施の第３形態を示す図で、図５（ａ）は平面
図、図５（ｂ）は側面図、図５（ｃ）は背面図、5 (a) is a plan view, FIG. 5 (b) is a side view, FIG. 5 (c) is a rear view,
【図６】従来の戦闘用航空機の１例を示す平面図で、図
６（ａ）は大後退角低反射形態の航空機、図６（ｂ）は
ダブルデルタ翼形態の航空機、図６（ｃ）は可変後退翼
形態の航空機である。6 (a) is a plan view showing an example of a conventional fighting aircraft, FIG. 6 (a) is an aircraft having a large retreat angle low reflection type, FIG. 6 (b) is an aircraft having a double delta wing type, FIG. 6 (c) ) Is a variable swept-wing aircraft.
１ 外翼 １ａ 大後退角位置外翼 １ｂ 小後退角位置外翼 ２ 内翼 ３ 回転軸 ４ 重心位置 ５ 翼取付部 ６ 舵面 ７ カナード DESCRIPTION OF SYMBOLS 1 Outer wing 1a Outer wing in large swept angle position 1b Outer wing in small swept angle position 2 Inner wing 3 Rotation axis 4 Center of gravity position 5 Wing mounting part 6 Control surface 7 Canard
Claims (1)
を前進、若しくは後退させて、後退角を変え、飛行を行
う外翼可変後退角航空機において、大後退角にされた前
縁を機体の重心位置よりも後方まで延設した内翼と、前
記重心位置より後方に翼付根部が設けられ、前縁が前記
内翼の前縁と略平行になる大後退角位置と、前縁の後退
角が前記内翼の前縁の後退角より小さくなる小後退角位
置とに設定される外翼と、鉛直方向から傾斜させて前記
翼付根部に立設され、軸着された前記外翼を回動させ
て、前記大後退角位置、若しくは前記小後退角位置に設
定する回転軸とを設けたことを特徴とする外翼可変後退
角航空機。1. An outer wing variable swept-aft aircraft that changes a swept angle by advancing or retreating an outer wing tip corresponding to a flight mission, and that a large swept front edge of an aircraft is An inner wing extending to the rear of the center of gravity, a wing root portion provided rearward of the center of gravity, a large retreat angle position where a leading edge is substantially parallel to a leading edge of the inner wing, and a retreat of the leading edge An outer wing whose angle is set to a small retreat angle position that is smaller than the retreat angle of the leading edge of the inner wing, and the outer wing, which is tilted from the vertical direction and is erected at the root of the wing and is axially attached, An outer wing variable swept-angle aircraft, comprising: a rotating shaft that is rotated to set the large swept angle position or the small swept angle position.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP18926396A JPH1035590A (en) | 1996-07-18 | 1996-07-18 | Outer wing variable sweepback angle aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP18926396A JPH1035590A (en) | 1996-07-18 | 1996-07-18 | Outer wing variable sweepback angle aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH1035590A true JPH1035590A (en) | 1998-02-10 |
Family
ID=16238388
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP18926396A Withdrawn JPH1035590A (en) | 1996-07-18 | 1996-07-18 | Outer wing variable sweepback angle aircraft |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH1035590A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2003098739A1 (en) * | 2002-05-15 | 2003-11-27 | Saab Ab | Stealth craft |
| CN110775249A (en) * | 2018-07-24 | 2020-02-11 | 李世平 | Aircraft with invisible double wings |
| CN113511333A (en) * | 2021-06-04 | 2021-10-19 | 沈阳航空航天大学 | Morphing flying wing type airplane and morphing method thereof |
-
1996
- 1996-07-18 JP JP18926396A patent/JPH1035590A/en not_active Withdrawn
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2003098739A1 (en) * | 2002-05-15 | 2003-11-27 | Saab Ab | Stealth craft |
| CN110775249A (en) * | 2018-07-24 | 2020-02-11 | 李世平 | Aircraft with invisible double wings |
| CN110775249B (en) * | 2018-07-24 | 2021-05-04 | 李世平 | Aircraft with invisible double wings |
| CN113511333A (en) * | 2021-06-04 | 2021-10-19 | 沈阳航空航天大学 | Morphing flying wing type airplane and morphing method thereof |
| CN113511333B (en) * | 2021-06-04 | 2023-10-03 | 沈阳航空航天大学 | Variant flying wing type airplane and variant method thereof |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| A300 | Withdrawal of application because of no request for examination |
Free format text: JAPANESE INTERMEDIATE CODE: A300 Effective date: 20031007 |