JPH06191493A

JPH06191493A - Aircraft

Info

Publication number: JPH06191493A
Application number: JP34430292A
Authority: JP
Inventors: Shiyouji Kitama; 章司北間
Original assignee: Mitsubishi Heavy Industries Ltd
Current assignee: Mitsubishi Heavy Industries Ltd
Priority date: 1992-12-24
Filing date: 1992-12-24
Publication date: 1994-07-12

Abstract

PURPOSE:To provide a tandem two-seat type twin-engined aircraft whose fuselage frontal projected area can be made small while excellent forward field of view is secured for a rear seat. CONSTITUTION:Two engines 2 and 3 are mounted onto an aircraft 1 in such a way as to be arranged in parallel in the vertical direction of its airframe, and air intakes 4 for the engines 2 and 3 are provided for both the sides of its fuselage. A tandem two-seat assembly where a rear seat is disposed higher than a front seat, is provided for the forward half section of the airframe so as to allow a canopy 5 for the tandem two-seat assembly to be secured therein. This constitution thereby enables the aircraft to be formed into the tandem two-seat type aircraft with the air intakes provided for both the sides of the fuselage thus as mentioned above, and moreover enables the field of view for the rear seat to be secured.

Description

【発明の詳細な説明】Detailed Description of the Invention

【０００１】[0001]

【産業上の利用分野】本発明は、タンデム複座式双発航
空機に関する。FIELD OF THE INVENTION The present invention relates to a tandem twin-seat twin-engine aircraft.

【０００２】[0002]

【従来の技術】従来の縦置きエンジン配置の複座式双発
航空機の例を図４および図５に示している。ここに示し
た例のように、機首正面部にエアー・インテーク１１を
配置したノーズ・ピトー式・エアー・インテークと称す
る型式のエアー・インテークを用いると、このエアー・
インテーク１１からエンジンへ空気を導くダクト１４が
胴体全長に亘って貫通する。従って、機体の前後方向に
座席を配置するタンデム複座化が難かしく、図示したも
ののように並列複座式を採用している。2. Description of the Related Art An example of a conventional twin-seat twin-engine aircraft with a vertical engine is shown in FIGS. As in the example shown here, if an air intake of the type called a nose pitot air intake with the air intake 11 arranged at the front of the nose is used, this air intake
A duct 14 for guiding air from the intake 11 to the engine penetrates the entire length of the fuselage. Therefore, it is difficult to make a tandem double-seat arrangement in which seats are arranged in the front-rear direction of the body, and a parallel double-seat type is adopted as shown in the figure.

【０００３】なお複座式航空機のうち左右方向に座席配
置する形式を並列複座式と称し、前後方向に座席配置す
る形式をタンデム複座式と称している。このように、従
来のエンジンを上下に２基縦置きに配置した双発航空機
は、次のような欠点を有する。In the double-seat aircraft, the type in which seats are arranged in the left-right direction is called a parallel double-seat type, and the type in which seats are arranged in the front-back direction is called a tandem double-seat type. As described above, the twin-engine aircraft in which two conventional engines are vertically arranged vertically has the following drawbacks.

【０００４】（１）ノーズ・ピトー式・エアー・インテ
ークを用いているためダクトが胴体全長に亘り貫通して
おり、機体の前後方向に座席を配置するタンデム複座化
が難かしい。(1) Since the nose pitot air intake is used, the duct penetrates the entire length of the fuselage, and it is difficult to form a tandem double seat in which seats are arranged in the front-rear direction of the fuselage.

【０００５】（２）従来機体においては、上記（１）の
理由により座席を横に並置した並列複座式を採用してお
り、このため胴体前面投影面積が増加し、縦置きエンジ
ン配置形式の利点が損なわれている。(2) In the conventional aircraft, the parallel double-seat type in which the seats are arranged side by side is adopted for the reason of the above (1). Therefore, the front projection area of the fuselage is increased and the vertical engine placement type is adopted. The benefits are diminished.

【０００６】[0006]

【発明が解決しようとする課題】本発明は、従来の複座
式双発航空機にみられた前述の欠点を除き、タンデム複
座化を可能とし、胴体前面投影面積を狭めて縦置きエン
ジン配置の利点を発揮させた航空機を提供することを課
題としている。また本発明は後方の座席に対しても良好
な視界を与えうるタンデム複座をもつ航空機を提供する
ことも課題としている。DISCLOSURE OF THE INVENTION The present invention eliminates the above-mentioned drawbacks found in the conventional twin-seat twin-engine aircraft, enables tandem double-seat, narrows the front projected area of the fuselage, and enables vertical engine placement. The challenge is to provide aircraft that demonstrate their advantages. Another object of the present invention is to provide an aircraft having a tandem double-seat capable of giving a good view to the rear seats.

【０００７】[0007]

【課題を解決するための手段】本発明は複座式双発航空
機における前記課題を解決するため、上下方向に重ねて
胴体内に配設された２つのエンジンのためのエアー・イ
ンテークを胴体の左右両側に設け、かつ、胴体内に後席
を前席よりも高い位置にして前後方向にタンデム複座を
配置した構成を採用する。SUMMARY OF THE INVENTION In order to solve the above-mentioned problems in a twin-seat twin-engine aircraft, the present invention provides air intakes for two engines arranged in the fuselage in the vertical direction on the left and right sides of the fuselage. The tandem double seats are installed on both sides and the rear seats are located higher than the front seats in the fuselage.

【０００８】[0008]

【作用】本発明のタンデム複座式双発ジェット航空機に
おいては、後席を前席よりも高い位置にして後席に対し
良好な前方視界を確保しつつ、座席を前後に並べたタン
デム式として胴体前面投影面積および断面形状の機軸前
後方向に対する変化を極力抑える事ができる。これによ
り、本発明による航空機では機体の空気抵抗を減少さ
せ、機体の高速性能を向上できる。In the tandem twin-seat twin-engine jet aircraft of the present invention, the rear seats are positioned higher than the front seats to ensure a good front view of the rear seats, and the fuselage is a tandem type in which the seats are arranged front and rear. Changes in frontal projected area and cross-sectional shape in the longitudinal direction of the axis can be suppressed as much as possible. Accordingly, in the aircraft according to the present invention, the air resistance of the airframe can be reduced and the high speed performance of the airframe can be improved.

【０００９】また本発明による航空機では、前後席に高
低差を設けているので、タンデム複座式練習機等とした
場合、後席ヘッド・アップ・ディスプレイ、すなわち飛
行情報や照準用表示をパイロット正面に表示する装置の
設置を容易にする。Further, in the aircraft according to the present invention, since the height difference is provided in the front and rear seats, in the case of a tandem double-seat trainer or the like, the rear seat head-up display, that is, the flight information or the sighting display is displayed in front of the pilot. Make it easy to install the device shown on.

【００１０】さらに本発明の航空機においては、エンジ
ンが胴体内に上下に重ねて配設され、そのエンジンのた
めのエアー・インテークが胴体の左右に配置されている
ので、必然的にエアー・インテーク中心軸とエンジン中
心軸とがずれるため、脅威電波がエアー・インテーク前
面から直接エンジン正面に到達するのを防止でき、脅威
電波に対する機体のステルス性が向上する。Further, in the aircraft of the present invention, since the engines are arranged one above the other in the fuselage and the air intakes for the engines are arranged on the left and right of the fuselage, the center of the air intake is inevitable. Since the axis and the engine center axis are misaligned, threat radio waves can be prevented from reaching the front of the engine directly from the front of the air intake, and the stealth of the aircraft against threat radio waves is improved.

【００１１】[0011]

【実施例】以下本発明による航空機を図示した実施例に
基いて具体的に説明する。図１において、本航空機１に
は、縦並び即ち機体の上下方向に双発エンジン２，３が
配置され、機体の左右両側にこのエンジン２，３のため
のサイド・エアー・インテーク４が取り付けられてい
る。さらに機体前半部には、前席と後席に十分な高低差
を設けたタンデム複座（図示していない）が配置され、
このタンデム複座用キャノピー５が取り付けられてい
る。これにより後席に対する良好な前方視界を確保しつ
つ、胴体前面投影面積および断面形状の機軸前後方向に
対する変化を極力抑えている。DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS An aircraft according to the present invention will be specifically described below based on illustrated embodiments. In FIG. 1, twin aircraft engines 2 and 3 are arranged vertically in the aircraft 1, that is, in the vertical direction of the body, and side air intakes 4 for the engines 2 and 3 are attached to both left and right sides of the body. There is. In addition, a tandem double seat (not shown) with a sufficient height difference between the front and rear seats is located in the first half of the aircraft,
This tandem double-seat canopy 5 is attached. This ensures a good front view of the rear seats, while suppressing changes in the front surface area of the fuselage and cross-sectional shape in the longitudinal direction of the machine axis as much as possible.

【００１２】本形式において採用可能なエアー・インテ
ークからエンジン２，３へ空気を導くダクトの例を図２
および図３に示している。図２には、合流ダクト形式を
示す。即ち、左右のエアー・インテーク６，７から流入
した空気を合流ダクト８内で合流させ、上下に配置した
エンジン２，３に導くものである。このダクト形式は左
右にインテークを有する単発エンジン機体のダクト形式
と基本的には同一構造である。図３は、独立流ダクト形
式を示す。左右インテーク６，７より流入した空気は曲
った２本の独立流ダクト９を通り、上下に配置されたエ
ンジン２，３それぞれに導かれる。An example of a duct for introducing air from the air intake to the engines 2 and 3 that can be adopted in this form is shown in FIG.
And shown in FIG. FIG. 2 shows a merging duct type. That is, the air that has flowed in from the left and right air intakes 6 and 7 is merged in the merge duct 8 and is guided to the engines 2 and 3 arranged above and below. This duct type is basically the same structure as the duct type of a single-engine engine body having intakes on the left and right. FIG. 3 shows the independent flow duct type. The air that has flowed in from the left and right intakes 6 and 7 passes through two curved independent flow ducts 9 and is guided to the engines 2 and 3 arranged above and below.

【００１３】なお本形式においては、機体が横すべりを
起こすと、風下側インテークとつながったエンジンがサ
ージしやすい。このサージ発生を防ぐため、２本の独立
流ダクト９の密着部側面にダクト間連絡孔１０が設けら
れている。機体が横すべりを起こし、左右インテークか
ら流入する空気流量が異なる場合には、このダクト間連
絡孔１０を通し、圧力上昇側ダクトから圧力低下側ダク
トに空気が送り込まれ、風下側インテークとつながった
エンジンに不足分空気流が供給されてエンジンのサージ
発生を防止できる。In the case of this type, when the machine side slides, the engine connected to the leeward intake is likely to surge. In order to prevent the occurrence of the surge, inter-duct communication holes 10 are provided on the side surfaces of the contact portions of the two independent flow ducts 9. When the airframe causes skidding and the air flow rates flowing from the left and right intakes are different, air is sent from the pressure rising side duct to the pressure lowering side duct through this duct communication hole 10, and the engine is connected to the leeward side intake. A shortage of air flow is supplied to the engine to prevent the occurrence of engine surge.

【００１４】ダクト間連絡孔１０は独立流ダクト９の側
面に設けられているので、左右インテーク６，７から流
入する空気流量が等しい場合には、それぞれのダクト内
の空気流は乱される事なく、上，下方エンジン２，３へ
独立に導かれる。以上、本発明による航空機を図示した
実施例に基づいて具体的に説明したが本発明がこの実施
例に限定されず具体的形状や構造を種々変更してよいこ
とはいうまでもない。Since the inter-duct communication hole 10 is provided on the side surface of the independent flow duct 9, when the air flow rates flowing from the left and right intakes 6, 7 are equal, the air flow in each duct is disturbed. Instead, they are independently guided to the upper and lower engines 2 and 3. Although the aircraft according to the present invention has been specifically described above based on the illustrated embodiment, it goes without saying that the present invention is not limited to this embodiment and various modifications in specific shapes and structures can be made.

【００１５】[0015]

【発明の効果】以上具体的に説明したように、本発明に
よる航空機は、上下方向に重ねて胴体内に配設された２
つのエンジン、前記胴体の側面左右に設けられた前記エ
ンジンのためのエアー・インテーク、および前記胴体内
に前席よりも後席を高い位置にして前後方向に配置され
たタンデム複座をもつ構成を採用しているので、次の効
果を奏するものとすることができる。As described in detail above, the aircraft according to the present invention is arranged in the fuselage so as to be vertically stacked.
One engine, air intakes for the engine provided on the left and right sides of the fuselage, and a tandem double-seat arrangement in the fuselage in which the rear seats are higher than the front seats. Since it is adopted, the following effects can be achieved.

【００１６】（１）タンデム複座式を採用したにも拘ら
ず、後席を前席よりも高い位置に配設して、後席に対す
る良好な前方視界を確保しつつ、タンデム複座式を採用
したことにより胴体前面投影面積および断面形状の機軸
前後方向に対する変化を極力抑えている。(1) Despite adopting the tandem double-seat type, the rear seat is arranged at a position higher than the front seat to ensure a good front view of the rear seat while the tandem double-seat type is used. By adopting this, changes in the frontal projection area and cross-sectional shape of the fuselage in the longitudinal direction of the machine axis are minimized.

【００１７】（２）一般に胴体前面投影面積の増大およ
び機軸前後方向に沿った断面形状の急激な変化は大きな
抵抗増加を招くが、上記（１）の効果により、機体の空
気抵抗が減少し、高速性能が向上する。(2) Generally, an increase in the projected area of the fuselage front face and a rapid change in the cross-sectional shape along the longitudinal direction of the machine axis cause a large increase in resistance, but the air resistance of the machine body decreases due to the effect of (1) above. High speed performance is improved.

【００１８】（３）本発明の採用により、前／後席に十
分な高低差を設けることが可能となるためタンデム複座
式練習機とした場合に、後席ヘッド・アップ・ディスプ
レイの設置が容易となる。(3) By adopting the present invention, it is possible to provide a sufficient height difference between the front and rear seats, so that in the case of a tandem double-seat trainer, the rear seat head-up display can be installed. It will be easy.

【００１９】（４）本発明の採用により、必然的にエア
ー・インテーク中心軸とエンジン中心軸とがずれるた
め、脅威電波が直接エンジン正面に到達する事がなく、
機体のステルス性が向上する。(4) The adoption of the present invention inevitably causes the air intake central axis and the engine central axis to deviate from each other, so that threat radio waves do not reach the front of the engine directly.
The stealth of the aircraft is improved.

【図面の簡単な説明】[Brief description of drawings]

【図１】本発明の実施例に係る航空機の全体構成の斜視
図。FIG. 1 is a perspective view of the overall configuration of an aircraft according to an embodiment of the present invention.

【図２】本発明の実施例に係る航空機における合流ダク
ト形式のダクトを具えた航空機の斜視図。FIG. 2 is a perspective view of an aircraft provided with a duct of a merged duct type in the aircraft according to the embodiment of the present invention.

【図３】本発明の実施例に係る航空機における独立流ダ
クト形式のダクトを具えた航空機の斜視図。FIG. 3 is a perspective view of an aircraft including a duct of an independent flow duct type in the aircraft according to the embodiment of the present invention.

【図４】従来の縦置きエンジン配置複座式航空機を示す
全体図で、（ａ）は平面図、（ｂ）は正面図。FIG. 4 is an overall view showing a conventional vertically-placed engine-positioned double-seat aircraft, in which (a) is a plan view and (b) is a front view.

【図５】従来の縦置きエンジン配置複座式航空機の断面
図。FIG. 5 is a cross-sectional view of a conventional double-seat aircraft with vertically arranged engines.

【符号の説明】[Explanation of symbols]

１航空機２上方エンジン３下方エンジン４サイド・エアー・インテーク５キャノピー６右側インテーク７左側インテーク８合流ダクト９独立流ダクト１０ダクト間連絡孔 1 Aircraft 2 Upper Engine 3 Lower Engine 4 Side Air Intake 5 Canopy 6 Right Intake 7 Left Intake 8 Merging Duct 9 Independent Duct 10 Interducting Hole

Claims

【特許請求の範囲】[Claims]

【請求項１】上下方向に重ねて胴体内に配設された２
つのエンジン、前記胴体の側面左右に設けられた前記エ
ンジンのためのエアー・インテーク、および前記胴体内
に後席を前席よりも高い位置にして前後方向に配置され
たタンデム複座を有することを特徴とする航空機。1. A stack of two members arranged vertically in a body.
One engine, air intakes for the engine provided on the left and right sides of the fuselage, and tandem double seats arranged in the front and rear direction with the rear seat higher than the front seat in the fuselage. Characteristic aircraft.