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JP2007131288A - Energy-saving type jet plane - Google Patents

Energy-saving type jet plane Download PDF

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Publication number
JP2007131288A
JP2007131288A JP2005356900A JP2005356900A JP2007131288A JP 2007131288 A JP2007131288 A JP 2007131288A JP 2005356900 A JP2005356900 A JP 2005356900A JP 2005356900 A JP2005356900 A JP 2005356900A JP 2007131288 A JP2007131288 A JP 2007131288A
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Japan
Prior art keywords
air
jet
duct
flow velocity
exhaust port
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Pending
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JP2005356900A
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Japanese (ja)
Inventor
Hideo Sunaga
英男 須長
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Individual
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Individual
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Priority to JP2005356900A priority Critical patent/JP2007131288A/en
Priority to PCT/JP2006/320883 priority patent/WO2007055088A1/en
Publication of JP2007131288A publication Critical patent/JP2007131288A/en
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C21/00—Influencing air flow over aircraft surfaces by affecting boundary layer flow
    • B64C21/02—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like
    • B64C21/025—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like for simultaneous blowing and sucking
    • 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
    • Y02T50/10—Drag reduction

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Jet Pumps And Other Pumps (AREA)

Abstract

<P>PROBLEM TO BE SOLVED: To provide an energy-saving type jet place capable of saving energy for the flight by reducing the air resistance on a front face of the jet plane. <P>SOLUTION: An air-feed duct extending from a leading end of a fuselage of a jet plane to a part in a vicinity of a jet orifice of a jet engine is provided on an airframe. In addition, a flow velocity control means for controlling the flow velocity of air in the air-feed duct is provided on the airframe. <P>COPYRIGHT: (C)2007,JPO&INPIT

Description

本発明は、ジェットエンジンを搭載した飛行機に関し、特に飛行機の前面に当たる空気抵抗を低減し、飛行の省エネルギー化を図る技術に関する。The present invention relates to an airplane equipped with a jet engine, and more particularly to a technique for reducing air resistance hitting the front of an airplane and saving energy in flight.

飛行機の前面に当たる空気抵抗を低減し、省エネルギーを図る発明としては次のものがある。
特開平１１−１０５７０８号公報 There are the following inventions that reduce the air resistance hitting the front of the airplane and save energy.
JP-A-11-105708

背景技術の発明は、飛行機胴体先端部にファンを設け、ファンの回転により生じる負の圧力により飛行機の前面に当たる空気抵抗を低減し、省エネルギーを図るものであるが、音速に近いスピードで飛行する旅客機などの場合は、それを上回るスピードでファンを回転させることは困難であり、これを実現するファンの駆動系は高価なものとなる。The invention of the background art provides a fan at the tip of the airplane fuselage and reduces air resistance hitting the front of the airplane due to negative pressure generated by the rotation of the fan, thereby saving energy. In such a case, it is difficult to rotate the fan at a speed higher than that, and the drive system of the fan that realizes this is expensive.

飛行機胴体先端部から飛行機胴体内を通りジェットエンジンの噴射口近傍に至る送風用ダクトを機体に設ける。A blower duct is provided in the fuselage from the tip of the airplane fuselage through the airplane fuselage to the vicinity of the jet engine injection port.

更に、上述の送風用ダクト内の気圧または風速を感知するセンサーを設け、そのセンサーからの気圧情報または風速情報をもとに、送風用ダクトの内径または送風用ダクトの排出口とジェットエンジンの噴出口から排出されるコアジェットまたはファンジェットとの距離または接触面積を制御する流速制御手段を機体に設ける。Further, a sensor for detecting the air pressure or wind speed in the above-described air duct is provided, and based on the air pressure information or wind speed information from the sensor, the inner diameter of the air duct or the discharge port of the air duct and the jet engine jet The airframe is provided with a flow velocity control means for controlling the distance or contact area with the core jet or fan jet discharged from the outlet.

ジェットエンジンの噴出口近傍では、ジェットの噴出により低い気圧の部位が生じるが、本発明はこの低い気圧を送風用ダクトを通して胴体先端部に導く。In the vicinity of the jet outlet of the jet engine, a low pressure portion is generated by jet jetting, but the present invention guides this low pressure to the front end of the body through the air duct.

これにより胴体先端部に空気の吸引力が生じる。As a result, an air suction force is generated at the front end of the body.

本発明により、飛行機胴体先端部に当たった空気はジェットエンジン近傍に排出され、その分、機体の空気抵抗を減少することができる。According to the present invention, the air hitting the tip of the airplane fuselage is discharged in the vicinity of the jet engine, and the air resistance of the airframe can be reduced accordingly.

また胴体先端部から吸引した空気は、ジェット推進力の一部となる。Air sucked from the front end of the body becomes part of the jet propulsion force.

本発明は、背景技術より廉価な仕組みで飛行機の前面に当たる空気抵抗を低減し、これにより飛行の省エネルギー化を図る。The present invention reduces the air resistance hitting the front of an airplane with a mechanism that is less expensive than the background art, thereby saving energy in flight.

図１に、本発明を適用したジェット機の底面図を示す。FIG. 1 shows a bottom view of a jet aircraft to which the present invention is applied.

図１中において、１はジェット機の胴体前方部、２は胴体後方部、３は主翼、４は尾翼、５はジェットエンジンを示す。In FIG. 1, 1 is a fuselage front part of a jet aircraft, 2 is a fuselage rear part, 3 is a main wing, 4 is a tail wing, and 5 is a jet engine.

また図１の機体は、胴体先端部が開放されており吸気口６を形成しており、吸気口６を一端として送風用ダクト７が胴体内を通りジェットエンジン５の噴出口近傍まで続いている。Further, the fuselage of FIG. 1 has an open front end portion of the fuselage to form an intake port 6, and an air duct 6 continues through the fuselage to the vicinity of the jet port of the jet engine 5 with the intake port 6 as one end. .

さらに、送風用ダクト７は、途中にダスト捕獲スポット８を備えている。Further, the air duct 7 includes a dust trapping spot 8 in the middle.

図２に、本発明を適用したジェット機の主翼の断面図を示す。FIG. 2 shows a cross-sectional view of the main wing of a jet aircraft to which the present invention is applied.

図２は、主翼３にジェットエンジン５が埋め込む形で搭載されていることを示す。FIG. 2 shows that the jet engine 5 is embedded in the main wing 3.

図２中において、ジェットエンジン５は、吸気ファン９，空気圧縮室１０，燃焼室１１，コアジェット噴出口１２から成り、エンジンステイ１３により主翼３に固定されている。In FIG. 2, the jet engine 5 includes an intake fan 9, an air compression chamber 10, a combustion chamber 11, and a core jet outlet 12, and is fixed to the main wing 3 by an engine stay 13.

また図２中において、送風用ダクト７は主翼３の内側を通り、エンジンステイ１３の近傍で排気口１４を開口している。In FIG. 2, the air duct 7 passes through the inside of the main wing 3 and opens an exhaust port 14 in the vicinity of the engine stay 13.

この排気口１４の形状は一部切り欠きとなっており、この切り欠き部分に密接し送風用ダクト７と平行して移動し、その移動量に応じて切り欠き部分を覆う面積を自由に変更できる排気口カバー１５と、モーターと歯車を内蔵し排気口カバーを送風用ダクト７と平行して移動させる排気口カバー駆動部１６が排気口１４の近傍に設置されている。The shape of the exhaust port 14 is partially cut out, moves in close contact with the cutout portion and moves in parallel with the air duct 7, and freely changes the area covering the cutout portion according to the amount of movement. An exhaust port cover 15 that can be built, and an exhaust port cover driving unit 16 that incorporates a motor and gears and moves the exhaust port cover in parallel with the air duct 7 are installed in the vicinity of the exhaust port 14.

図３に、請求項２および請求項３に対応した流速制御手段の最良の形態を示す。FIG. 3 shows the best mode of the flow rate control means corresponding to claims 2 and 3.

図３中において、１７ａは、送風用ダクト７の吸気口６内に設置された風速計であり、送風用ダクト７を流れる空気の流速に応じ風車の回転数が増加し、それに応じて出力電圧１８ａを出力する。In FIG. 3, reference numeral 17 a denotes an anemometer installed in the air inlet 6 of the air duct 7, and the rotational speed of the windmill increases according to the flow velocity of the air flowing through the air duct 7, and the output voltage is accordingly increased. 18a is output.

出力電圧１８ａは、Ａ／Ｄ変換器１９ａによりデジタル信号２０ａに変換され、コンピュータ２１に入力される。The output voltage 18a is converted into a digital signal 20a by the A / D converter 19a and input to the computer 21.

図３中において、１７ｂは、吸気口６近傍の胴体前方部１に設置された風速計であり、胴体前方部１近傍を流れる空気の流速に応じ風車の回転数が増加し、それに応じて出力電圧１８ｂを出力する。In FIG. 3, 17b is an anemometer installed in the front part 1 of the fuselage in the vicinity of the intake port 6, and the rotation speed of the windmill increases according to the flow velocity of the air flowing in the vicinity of the front part 1 of the fuselage, and the output is accordingly generated The voltage 18b is output.

出力電圧１８ｂは、Ａ／Ｄ変換１９ｂによりデジタル信号２０ｂに変換され、コンピュータ２１に入力される。The output voltage 18b is converted into a digital signal 20b by an A / D conversion 19b and input to the computer 21.

コンピュータ２１は、排気口カバー駆動部１６を制御するためのデジタル制御信号２４を出力する。The computer 21 outputs a digital control signal 24 for controlling the exhaust port cover driving unit 16.

このデジタル制御信号２４は、Ｄ／Ａ変換器２５によりアナログ制御信号２６に変換され、排気口カバー駆動部１６に内蔵された駆動モーター２７に入力される。The digital control signal 24 is converted into an analog control signal 26 by a D / A converter 25 and input to a drive motor 27 built in the exhaust port cover driving unit 16.

駆動モーター２７は、アナログ制御信号２６に従い所定量だけ回転または逆回転を行い、その回転力は排気口カバー駆動部１６に内蔵された歯車を介して排気口カバー１５に伝えられ、これにより排気口カバー１５は排気口１４の切り欠き部分の開閉動作を行なう。The drive motor 27 rotates or reversely rotates by a predetermined amount in accordance with the analog control signal 26, and the rotational force is transmitted to the exhaust port cover 15 through a gear incorporated in the exhaust port cover driving unit 16, thereby the exhaust port. The cover 15 opens and closes the cutout portion of the exhaust port 14.

また、排気口カバー１５にはスライド式電気抵抗器２８が取り付けられており、その移動量に応じてスライド式電気抵抗器２８の抵抗値が増減するようにしておく。In addition, a slide type electric resistor 28 is attached to the exhaust port cover 15 so that the resistance value of the slide type electric resistor 28 increases or decreases according to the amount of movement.

このスライド式電気抵抗器２８に定電流電源を接続することにより、スライド式電気抵抗器２８の両端に抵抗値に応じた電位差が生じる。By connecting a constant current power source to the slide type electric resistor 28, a potential difference corresponding to the resistance value is generated at both ends of the slide type electric resistor 28.

この電位差をアナログ信号２９として取り出し、Ａ／Ｄ変換器１９ｃによりデジタル信号３０としてコンピュータ２１に入力する。This potential difference is taken out as an analog signal 29 and input to the computer 21 as a digital signal 30 by the A / D converter 19c.

コンピュータ２１は、バス２２を介してハードディスク２３と接続している。The computer 21 is connected to the hard disk 23 via the bus 22.

ハードディスク２３には、流速制御手段全体を統制する制御プログラムが格納されており、コンピュータ２１は、この制御プログラムに従いデジタル制御信号２４を出力する。The hard disk 23 stores a control program for controlling the entire flow rate control means, and the computer 21 outputs a digital control signal 24 in accordance with this control program.

図４に、この制御プログラムのフローチャートを示す。FIG. 4 shows a flowchart of this control program.

図４によれば制御プログラムは、通風用ダクト７の吸気口６内の空気の流速を示す出力電圧１８ａが吸気口６近傍の胴体前方部１における空気の流速を示す出力電圧１８ｂの１３０％を超える場合は、排気口１４の切り欠き部分の面積を拡大させ、出力電圧１８ａが出力電圧１８ｂの１１０％未満の場合は、排気口１４の切り欠き部分の面積を縮小させるように制御する。According to FIG. 4, the control program outputs 130% of the output voltage 18 b indicating the air flow rate in the front part 1 of the fuselage in the vicinity of the intake port 6 so that the output voltage 18 a indicating the air flow rate in the intake port 6 of the ventilation duct 7. When exceeding, the area of the cutout portion of the exhaust port 14 is enlarged, and when the output voltage 18a is less than 110% of the output voltage 18b, the area of the cutout portion of the exhaust port 14 is controlled to be reduced.

この排気口１４の切り欠き部分の面積を拡大／縮小する制御は、コンピュータ２１が出力するデジタル制御信号２４によってなされる。Control for enlarging / reducing the area of the cutout portion of the exhaust port 14 is performed by a digital control signal 24 output from the computer 21.

またスライド式電気抵抗器２８は、排気口カバー１５の動きを監視するためのものであり、排気口１４の切り欠き部分の現在の面積がどの程度であるかは、デジタル信号３０によって知ることができる。The slide type electric resistor 28 is used for monitoring the movement of the exhaust port cover 15, and the current area of the cutout portion of the exhaust port 14 can be known from the digital signal 30. it can.

図５は、ジェットエンジン５近傍の空気の流れを示すものであり、図中、３１は吸気ファン９により圧縮されて排出されたファンジェットの流れを示し、３２はそのファンジェットに接触し排出口１４から排出された送風用ダクト７内の空気の流れを示す。FIG. 5 shows the flow of air in the vicinity of the jet engine 5. In the figure, 31 shows the flow of the fan jet compressed and discharged by the intake fan 9, and 32 is in contact with the fan jet and discharges it. The flow of the air in the duct 7 for ventilation discharged | emitted from 14 is shown.

ファンジェットは、高い圧力の空気の流れであり、直進運動性が高い。A fan jet is a flow of high-pressure air and has high straight movement.

送風用ダクト７内の排気口１４近傍の空気がファンジェットに接触するとそれに巻き込まれ、排気口１４より排出されることになる。When the air in the vicinity of the exhaust port 14 in the air duct 7 comes into contact with the fan jet, it is caught in the air and discharged from the exhaust port 14.

このため、送風用ダクト７内の排気口１４近傍は常に空気が薄く、減圧することになり、これが送風用ダクト７の吸気口６における吸引力となる。For this reason, in the vicinity of the exhaust port 14 in the air duct 7, the air is always thin and the pressure is reduced. This is the suction force at the air inlet 6 of the air duct 7.

排気口カバー１５および排気口カバー駆動部１６は、送風用ダクト７内の排気口１４近傍の空気とファンジェットとの接触面積を制御することによって、送風用ダクト７の吸気口６における吸引力を制御する。The exhaust port cover 15 and the exhaust port cover driving unit 16 control the contact area between the air in the vicinity of the exhaust port 14 in the air duct 7 and the fan jet, thereby reducing the suction force at the air inlet 6 of the air duct 7. Control.

図１におけるダスト捕獲スポット８は、送風用ダクト７の吸気口６に飛び込んだ鳥などを捕獲するためのものであり、送風用ダクト７が詰まることを防止する。The dust capture spot 8 in FIG. 1 is for capturing a bird or the like that has jumped into the air inlet 6 of the air duct 7 and prevents the air duct 7 from being clogged.

図１に示すように通風用ダクト７が曲がる地点に窪みを用意することで、質量を持ち直進運動性の強い鳥などは、曲がりきれずにこの窪み即ちダスト捕獲スポット８に捕獲される。As shown in FIG. 1, by preparing a depression at a point where the ventilation duct 7 bends, a bird having a mass and having a strong straight movement is captured in the depression, that is, the dust trapping spot 8 without being bent.

本発明を適用したジェット機の底面図。The bottom view of the jet aircraft to which the present invention is applied. 本発明を適用したジェット機の主翼の断面図。Sectional drawing of the main wing | blade of the jet aircraft to which this invention is applied. 本発明の流速制御手段の最良の形態の説明図。Explanatory drawing of the best form of the flow velocity control means of this invention. 本発明の制御プログラムのフローチャート。The flowchart of the control program of this invention. ジェットエンジン近傍の空気の流れの説明図。Explanatory drawing of the flow of the air in the jet engine vicinity.

符号の説明Explanation of symbols

１は、ジェット機の胴体前方部。
２は、ジェット機の胴体後方部。
３は、ジェット機の主翼。
４は、ジェット機の尾翼。
５は、ジェットエンジン。
６は、吸気口。
７は、送風用ダクト。
８は、ダスト捕獲スポット。
９は、吸気ファン。
１０は、空気圧縮室。
１１は、燃焼室。
１２は、コアジェット噴出口。
１３は、エンジンステイ。
１４は、排気口１４。
１５は、排気口カバー。
１６は、排気口カバー駆動部。
１７ａは、吸気口６内に設置された風速計。
１７ｂは、胴体前方部１に設置された風速計。
１８ａは、風速計１７ａの出力電圧。
１８ｂは、風速計１７ｂの出力電圧。
１９ａ，１９ｂ，１９ｃは、Ａ／Ｄ変換器。
２０ａは、Ａ／Ｄ変換後の出力電圧１８ａ。
２０ｂは、Ａ／Ｄ変換後の出力電圧１８ｂ。
２１は、コンピュータ。
２２は、バス。
２３は、ハードディスク。
２４は、デジタル制御信号。
２５は、Ｄ／Ａ変換器。
２６は、アナログ制御信号。
２７は、駆動モーター。
２８は、スライド式電気抵抗器。
２９は、スライド式電気抵抗器２８の両端の電位差を示すアナログ信号。
３０は、Ａ／Ｄ変換によりデジタル信号となったアナログ信号２９。
３１は、ファンジェットの流れ。
３２は、排出口１４から排出される空気の流れ。1 is the front part of the fuselage.
2 is a fuselage rear part of a jet aircraft.
3 is the jet wing.
4 is the tail of the jet.
5 is a jet engine.
6 is an intake port.
7 is a duct for ventilation.
8 is a dust capture spot.
9 is an intake fan.
10 is an air compression chamber.
11 is a combustion chamber.
12 is a core jet outlet.
13 is an engine stay.
Reference numeral 14 denotes an exhaust port 14.
15 is an exhaust port cover.
Reference numeral 16 denotes an exhaust port cover driving unit.
An anemometer 17 a is installed in the intake port 6.
17b is an anemometer installed in the front part 1 of the fuselage.
18a is an output voltage of the anemometer 17a.
18b is an output voltage of the anemometer 17b.
19a, 19b, 19c are A / D converters.
20a is an output voltage 18a after A / D conversion.
20b is an output voltage 18b after A / D conversion.
21 is a computer.
22 is a bus.
23 is a hard disk.
24 is a digital control signal.
25 is a D / A converter.
26 is an analog control signal.
27 is a drive motor.
28 is a slide type electric resistor.
Reference numeral 29 denotes an analog signal indicating a potential difference between both ends of the slide type electric resistor 28.
Reference numeral 30 denotes an analog signal 29 which is converted into a digital signal by A / D conversion.
31 is the flow of the fan jet.
32 is a flow of air discharged from the discharge port 14.

Claims (3)

胴体先端部からジェットエンジンの噴出口近傍に至る、空気を吸引しかつ排出するための送風用ダクトを備えたことを特徴とするジェットエンジン搭載の飛行機。An airplane equipped with a jet engine, comprising a blower duct for sucking and discharging air from a front end of a fuselage to a vicinity of a jet outlet of the jet engine. 送風用ダクト内の気圧または機体先端部の気圧を感知する気圧センサーまたは送風用ダクト内の空気の流速または機体外部の空気の流速を測定する風速センサーを備え、その気圧センサーまたは風速センサーからの気圧情報または風速情報を入力し、その情報を元に送風用ダクト内の空気の流速を制御する流速制御手段を備えたことを特徴とする請求項１記載の飛行機。Air pressure sensor that detects the air pressure inside the air duct or the air pressure at the tip of the airframe, or the wind speed sensor that measures the air flow rate inside the air duct or the air flow rate outside the airframe, and the air pressure from the air pressure sensor or wind speed sensor 2. An airplane according to claim 1, further comprising a flow velocity control means for inputting information or wind velocity information and controlling the flow velocity of air in the air duct based on the information. 送風用ダクトの内径または送風用ダクトの排出口とジェットエンジンの噴出口から排出されるコアジェットまたはファンジェットとの距離または接触面積を制御することによって送風用ダクト内の空気の流速を制御する流速制御手段を備えたことを特徴とする請求項１記載の飛行機。A flow velocity that controls the flow velocity of the air in the blower duct by controlling the inner diameter of the blower duct or the distance or contact area between the discharge port of the blower duct and the core jet or the fan jet discharged from the jet outlet of the jet engine. The airplane according to claim 1, further comprising a control means.
JP2005356900A 2005-11-11 2005-11-11 Energy-saving type jet plane Pending JP2007131288A (en)

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