JP2016000569A - Structure of electrically-operated propulsion unit - Google Patents

Structure of electrically-operated propulsion unit Download PDF

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Publication number
JP2016000569A
JP2016000569A JP2014120813A JP2014120813A JP2016000569A JP 2016000569 A JP2016000569 A JP 2016000569A JP 2014120813 A JP2014120813 A JP 2014120813A JP 2014120813 A JP2014120813 A JP 2014120813A JP 2016000569 A JP2016000569 A JP 2016000569A
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JP
Japan
Prior art keywords
ducted fan
partition
electrically
propulsion device
stabilizer
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.)
Pending
Application number
JP2014120813A
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Japanese (ja)
Inventor
日下部正彦
Masahiko Kusakabe
角田和彦
Kazuhiko Tsunoda
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Individual
Original Assignee
Individual
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Individual filed Critical Individual
Priority to JP2014120813A priority Critical patent/JP2016000569A/en
Publication of JP2016000569A publication Critical patent/JP2016000569A/en
Pending legal-status Critical Current

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    • 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
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Abstract

PROBLEM TO BE SOLVED: To provide an electrically-operated ducted fan propulsion unit that prevents rolling and control of a pitch axis from becoming unstable by being affected by viscosity resistance and reaction torque caused by propeller revolutions of a ducted fan and a fluid air flow jetted backward.SOLUTION: A division plate of a ducted fan comprises a stabilizer 2 and a helm 1 such as a movable vane to cancel out reaction torque and rolling-axial-direction viscosity resistance caused by a vortex. Reliable stability is obtained together with controllability by performing steering as in the case of an elevon and a rudder.

Description

この発明は、ダクテッドファンの構造に関する。   The present invention relates to a ducted fan structure.

従来のダクテッドファンを高性能化する特徴的構造としては次に示すような
ものがある。
１）インテークリップ
２）絞り
３）インペラ後方の整流板
従来のダクテッドファンの構造や飛行を制御し安定させる方法に、
関するものとしては
実開昭61-125899
「ダクトに昇降舵または昇降舵と方向舵を取り付けたタクテッドプロペラ」
特開2012−101598 電動式推進装置
特開2006−123880
ダクテッドファンを推進力に飛行する飛行物体を安定させる構造
といった技術が公開されている。 A characteristic structure for improving the performance of a conventional ducted fan is as follows.
1) Intake clip 2) Aperture 3) Rectifying plate behind the impeller For the conventional ducted fan structure and method of controlling and stabilizing,
As for things related to Sho Aki 61-125899
"Tacted propeller with elevator or elevator and rudder attached to duct"
JP 2012-101598 ELECTRIC PROMOTION DEVICE JP 2006-123880
Technologies such as a structure that stabilizes flying objects flying with a ducted fan as a driving force have been released.

実開昭６１−１２５８９９Akira 61-125899 特開２０１２−１０１５９８JP2012-101598 特開２００６−１２３８８０JP 2006-123880 A

ダクテッドファンはモータの反動トルクと後方噴射流が渦を巻いており
その粘性抵抗の影響を受けている。この渦を整流する構造が重要で、
仕切り板を配する構造が知られているが、その面積や配置によっては
目的の安定性が得られない事がある。
従来の方法にあっては、その安定化の原理を明らかに示されておらず、
コントロールが不安定になるという課題がある。 Ducted fans are affected by the viscous resistance of the reaction torque of the motor and the backward jet flow. The structure that rectifies this vortex is important,
Although a structure with a partition plate is known, the target stability may not be obtained depending on the area and arrangement.
In the conventional method, the principle of stabilization is not clearly shown,
There is a problem that the control becomes unstable.

仕切り板のみまたは、安定板と可動翼のような舵を装備して、エレボン、ラダー
と同様な操舵を行いコントロール性と共に確実な安定性を得る。 Equipped with a partition plate or a rudder such as a stabilizer and movable wings, the same steering as an elevon or rudder is performed to obtain reliable stability as well as control.

反動トルクと渦によるロール軸方向の粘性抵抗を打ち消す事ができ、
ダクテッドファンの取付け誤差、推力線のズレによる不安定（クセ）
があっても可動翼のトリムで簡単に修正できる。 Can cancel the viscous resistance in the roll axis direction caused by reaction torque and vortex,
Ducted fan mounting error, instability due to thrust line misalignment
Even if there is, it can be easily corrected with the trim of the movable wing.

仕切り板を2枚、3枚、4枚とした場合。When the number of dividers is 2, 3, or 4. モーターステイを仕切り安定板とし、可動翼を装備した場合。 高温のガスを噴射しないEDFにおいて有効な、推力軸、飛行軸を制御する方法。When the motor stay is a partition stabilization plate and equipped with movable wings. A method of controlling the thrust axis and flight axis that is effective in EDF that does not inject high-temperature gas.

飛行軸（ピッチ軸、ロール軸、ヨー軸）制御が不安定になりがちな
全翼機などに安定性を与える。 Provides stability to all-wing aircraft that tend to be unstable in flight axis (pitch axis, roll axis, yaw axis) control.

全翼機、ショートスパンな飛翔体、誘導ミサイル。     All-wing aircraft, short span projectiles, guided missiles.

ロケットやジェットのような高温のガスを噴射しない流体噴射式反動推進器
（ダクテッドファン）において有効な制御方法。 This control method is effective for fluid-jet reaction thrusters (ducted fans) that do not inject high-temperature gas such as rockets and jets.

・ 可動翼
・ 安定板
・ シュラウド
・ インペラ
・ モーター ・ Moving wings ・ Stabilizer plate ・ Shroud ・ Impeller ・ Motor

Claims (3)

シュラウド（円筒管）と、その内部に電動モータをステイで結合し、電動モータに
プロペラを具備してなるダクテッドファンを応用した、電動式推進装置の構造に
おいて、渦の悪影響をなくす為に、ダクテッドファンの噴射流体に仕切り安定板
を用いる電動式推進装置の構造。 In order to eliminate the adverse effects of vortices in the structure of an electric propulsion device that uses a ducted fan in which a shroud (cylindrical tube) and an electric motor are coupled with a stay and a propeller is provided in the electric motor, The structure of an electric propulsion device that uses a partition stabilizer for the jet fluid. 飛行軸制御、推力軸制御（スラストベクターコントロール）の為に、
ダクテッドファンの噴射流体に仕切り安定板と可動翼を具備する、
請求項１記載の電動式推進装置の構造。 For flight axis control and thrust axis control (thrust vector control)
A partition stabilizer and movable blades are provided in the ducted fan jet fluid.
The structure of the electric propulsion device according to claim 1. ダクテッドファンのモーターステイと仕切り安定板のみ、または仕切り安定板と
可動翼を兼用する、請求項１記載の電動式推進装置の構造。 The structure of the electric propulsion device according to claim 1, wherein only the motor stay and the partition stabilizing plate of the ducted fan or the partition stabilizing plate and the movable blade are used together.
JP2014120813A 2014-06-11 2014-06-11 Structure of electrically-operated propulsion unit Pending JP2016000569A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
JP2014120813A JP2016000569A (en) 2014-06-11 2014-06-11 Structure of electrically-operated propulsion unit

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP2014120813A JP2016000569A (en) 2014-06-11 2014-06-11 Structure of electrically-operated propulsion unit

Publications (1)

Publication Number Publication Date
JP2016000569A true JP2016000569A (en) 2016-01-07

Family

ID=55076411

Family Applications (1)

Application Number Title Priority Date Filing Date
JP2014120813A Pending JP2016000569A (en) 2014-06-11 2014-06-11 Structure of electrically-operated propulsion unit

Country Status (1)

Country Link
JP (1) JP2016000569A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106477036A (en) * 2016-11-29 2017-03-08 四川特飞科技股份有限公司 A kind of rectangle combination duct aircraft and its flight control system and method
WO2019014795A1 (en) * 2017-07-18 2019-01-24 南砚今 Novel low-noise thruster
CN113443124A (en) * 2021-07-20 2021-09-28 北京理工大学 Boundary layer suction type propeller adopting two-stage large and small blades

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106477036A (en) * 2016-11-29 2017-03-08 四川特飞科技股份有限公司 A kind of rectangle combination duct aircraft and its flight control system and method
WO2019014795A1 (en) * 2017-07-18 2019-01-24 南砚今 Novel low-noise thruster
CN113443124A (en) * 2021-07-20 2021-09-28 北京理工大学 Boundary layer suction type propeller adopting two-stage large and small blades
CN113443124B (en) * 2021-07-20 2022-08-19 北京理工大学 Boundary layer suction type propeller adopting two-stage large and small blades

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