[go: up one dir, main page]

WO2009002206A1 - Gouverne pouvant être mise en drapeau - Google Patents

Gouverne pouvant être mise en drapeau Download PDF

Info

Publication number
WO2009002206A1
WO2009002206A1 PCT/RU2007/000347 RU2007000347W WO2009002206A1 WO 2009002206 A1 WO2009002206 A1 WO 2009002206A1 RU 2007000347 W RU2007000347 W RU 2007000347W WO 2009002206 A1 WO2009002206 A1 WO 2009002206A1
Authority
WO
WIPO (PCT)
Prior art keywords
feathering
control surface
aircraft
rudder
fuselage
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.)
Ceased
Application number
PCT/RU2007/000347
Other languages
English (en)
Russian (ru)
Inventor
Oleg Gerol'dovich Kiryushin
Vsevolod Igorevich Kiryushin
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 PCT/RU2007/000347 priority Critical patent/WO2009002206A1/fr
Publication of WO2009002206A1 publication Critical patent/WO2009002206A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C9/00—Adjustable control surfaces or members, e.g. rudders
    • B64C9/04—Adjustable control surfaces or members, e.g. rudders with compound dependent movements
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C9/00—Adjustable control surfaces or members, e.g. rudders
    • B64C9/10—Adjustable control surfaces or members, e.g. rudders one surface adjusted by movement of another, e.g. servo tabs

Definitions

  • the inventive feathering steering wheel relates to aircraft, and in particular to aircraft controls, and can be used to create manned and unmanned aerial vehicles of any type and size with adjustable control surfaces in the form of feathering rudders.
  • the invention is known according to the patent of the Russian Federation N ⁇ > 2087381 (PROTOTYPE), MPK-6: B64C13 / 28; 39/12, dated 06/11/1993, published on 08/20/1997, which describes an aircraft according to the “ytka” scheme with feathering rudders, where the action on the rudders through a spring drive, which generates a torque on the rudder axis, whose vector is directed along the axis of the rudder, which makes these rudders “fully feathering”.
  • the disadvantages of the prototype are: control of feathering rudders is not carried out at all angles of attack of the aircraft; the impact on the steering wheel through the springs leads to a shift in the focus of the aircraft closer to the center of mass, which reduces the stability of the aircraft compared to a fully feathering wheel; using a spring drive may cause vibration aircraft.
  • the main disadvantages are, in particular, incomplete feathering, complexity and cumbersome construction.
  • the differences of the claimed technical solution from the prototype are that the prototype device is implemented using an improved traditional steering scheme, without using the full feathering effect and without using fully feathering steering wheels.
  • feathering is carried out in the entire range of rotation of the steering wheel.
  • the purpose of the development of the claimed technical solution is the creation of a feathering rudder, which will ensure effective control of the aircraft at all possible angles of attack, including supercritical, in addition, the claimed device will ensure the safety of an emergency landing in case of engine failure.
  • the technical task was to create a lifting force on the aerodynamic plane of the feathering rudder, which depends only on the magnitude of the impact on this plane and does not depend on the angle of attack of the entire aircraft.
  • This goal is achieved in that the rotation of the aerodynamic plane can be carried out by any known method of influencing the control plane (mechanical, electrical, hydraulic, jet), which does not create additional torque, the vector of which is directed along the axis of attachment of the feathering rudder to the aircraft fuselage, which is principal difference inventions from traditional aircraft control devices.
  • the control plane mechanical, electrical, hydraulic, jet
  • the feathering rudder includes a rudder impact device, wherein the rudder rotates freely on the main axis of the rudder attachment to the fuselage and the rudder consists of an aerodynamic plane rotating by a control action around the secondary axis, which is connected to the main axis of the entire rudder by a crank, this creates a lifting force on the main axis of the steering wheel to the fuselage by creating an angle of attack of the aerodynamic plane, that is, by changing the angle between the chord of the aerodynamic plane and the shoulder crank, and as a device for influencing the steering wheel, a drive lever is used.
  • the essence of the claimed device is presented in figure 1.
  • the main axis 2 is pivotally attached to the fuselage 1, and the only aerodynamic plane 3 rotates around the secondary axis 5 due to the impact control moment M to the drive lever 4, while the secondary axis is connected to the main axis by crank 6.
  • Deviation of the aerodynamic plane of the feathering wheel from the neutral position in the incoming air flow V and the creation of a lifting force P on the main axis of the feathering wheel is carried out by changing the relative position of its components, namely, by changing the angle between the chord of the aerodynamic plane and the crank arm.
  • Fig. 2 shows an aircraft containing the fuselage 1 with two feathering rudders controlling this aircraft and freely rotating on the main axes 2 of the attachment of the rudders to the fuselage.
  • the feathering wheel itself consists of an aerodynamic plane 3, which rotates around the secondary axis 5 due to the actions: Ml- for the left feathering steering wheel and M2- for the right feathering steering wheel in the first one look at the drive lever 4, while the secondary axis is connected to the main axis by crank 6
  • a plurality of left and right rudders can be achieved.
  • the technical solution for a feathering rudder can be a rudder consisting of elements that change their relative position. Deviation of the aerodynamic plane of the steering wheel from a neutral position in the incoming air flow is carried out by changing the angle between the chord of the aerodynamic plane and the crank arm, followed by changing the angle of attack of the aerodynamic plane of the steering wheel.
  • the inventive device operates as follows: The pilot controls the steering mechanisms acting on the drive levers 4, which deflect the aerodynamic planes of the left and right winged rudders, changing the angles between the chords of the aerodynamic planes and the shoulders of the cranks 6. This will change the aerodynamic the quality of each of the feathering rudders will cause a change in the lifting forces in the incoming ambient air flow, which, being applied to the main axes of the rudders attachment to the fuselage, will allow controlling the aircraft by changing the angle of attack or the angle of heel of the aircraft itself.
  • the technical result of the application of the claimed technical solution is an aircraft control device with a fully feathering rudder, a lifting force is generated on the main axis of its attachment to the fuselage, which depends only on the magnitude of the impact on the steering plane of the steering wheel and does not depend on the angle of attack of the entire aircraft.
  • this aircraft control device will ensure the safety of an emergency landing in the event of an emergency engine failure.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Toys (AREA)

Abstract

L'invention concerne des moyens de commande d'un aéronef. Une gouverne pouvant être mise en drapeau comprend un dispositif agissant sur la gouverne qui pivote librement sur un axe principal de fixation de la gouverne au fuselage. La gouverne est constituée d'une surface aérodynamique qui pivote grâce à l'action de commande autour d'un axe secondaire reliée à l'axe principal de l'intégralité de la gouverne par une manivelle de manière à créer la portance sur l'axe principal de fixation de la gouverne au fuselage grâce à la création d'un angle d'attaque de la surface aérodynamique et du bras de la manivelle. Le dispositif d'action sur la gouverne se présente comme un levier de commande. L'invention vise à augmenter l'efficacité de commande de l'aéronef à des angles d'attaque critiques.
PCT/RU2007/000347 2007-06-27 2007-06-27 Gouverne pouvant être mise en drapeau Ceased WO2009002206A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PCT/RU2007/000347 WO2009002206A1 (fr) 2007-06-27 2007-06-27 Gouverne pouvant être mise en drapeau

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/RU2007/000347 WO2009002206A1 (fr) 2007-06-27 2007-06-27 Gouverne pouvant être mise en drapeau

Publications (1)

Publication Number Publication Date
WO2009002206A1 true WO2009002206A1 (fr) 2008-12-31

Family

ID=40185851

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/RU2007/000347 Ceased WO2009002206A1 (fr) 2007-06-27 2007-06-27 Gouverne pouvant être mise en drapeau

Country Status (1)

Country Link
WO (1) WO2009002206A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2017032795A1 (fr) 2015-08-25 2017-03-02 Novo Nordisk A/S Nouveaux dérivés de l'insuline et leurs utilisations médicales
WO2017032797A1 (fr) 2015-08-25 2017-03-02 Novo Nordisk A/S Nouveaux dérivés de l'insuline et leurs utilisations médicales

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB511188A (en) * 1938-01-13 1939-08-15 Francis Thomas Courtney Aeroplane
RU2093417C1 (ru) * 1993-06-08 1997-10-20 Владимир Григорьевич Григорьев Аэродинамическая схема летательного аппарата
US20040251383A1 (en) * 2001-05-24 2004-12-16 Mcdonnell William R Use of aerodynamic forces to assist in the control and positioning of aircraft control surfaces and variable geometry systems
EA008818B1 (ru) * 2006-03-28 2007-08-31 Алексей Николаевич Юрконенко Крылатый летательный аппарат с флюгерным горизонтальным оперением

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB511188A (en) * 1938-01-13 1939-08-15 Francis Thomas Courtney Aeroplane
RU2093417C1 (ru) * 1993-06-08 1997-10-20 Владимир Григорьевич Григорьев Аэродинамическая схема летательного аппарата
US20040251383A1 (en) * 2001-05-24 2004-12-16 Mcdonnell William R Use of aerodynamic forces to assist in the control and positioning of aircraft control surfaces and variable geometry systems
EA008818B1 (ru) * 2006-03-28 2007-08-31 Алексей Николаевич Юрконенко Крылатый летательный аппарат с флюгерным горизонтальным оперением

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2017032795A1 (fr) 2015-08-25 2017-03-02 Novo Nordisk A/S Nouveaux dérivés de l'insuline et leurs utilisations médicales
WO2017032797A1 (fr) 2015-08-25 2017-03-02 Novo Nordisk A/S Nouveaux dérivés de l'insuline et leurs utilisations médicales

Similar Documents

Publication Publication Date Title
US8777152B2 (en) Method and an aircraft provided with a swiveling tail rotor
US9845150B2 (en) Personal aircraft
KR102290333B1 (ko) 비행체 비행 기계장치 및 제어 방법
EP3000722B1 (fr) Avion
US5265827A (en) Paddle wheel rotorcraft
EP3774530B1 (fr) Véhicule aérien à manoeuvrabilité améliorée et procédé mis en oeuvre à cet effet
JP7037826B2 (ja) プロペラ式飛行体
CN101389532B (zh) 用于飞机的转向舵面的电气控制系统
JP2022501265A (ja) 航空機の制御方法及び航空機（変異形）
JP2009051381A (ja) サイクロイダル・ブレード
GB2419122A (en) Vertical take-off and landing aircraft
KR101985688B1 (ko) 개인비행장치
GB2553604B (en) Aerodynamically fully actuated drone (Sauceron) and drone chassis aerodynamic supporting trusses (Lings)
CN117545690A (zh) 垂直起飞的飞行器
WO2008099192A1 (fr) Orientation de poussée dans des véhicules aériens
WO2009002206A1 (fr) Gouverne pouvant être mise en drapeau
EP3878739B1 (fr) Rotor d'aéronef bidirectionnel
US2697568A (en) Aircraft rudder control
CN101289115A (zh) 复合旋转式“扑翼”飞机
WO2008123789A1 (fr) Unité à mise en drapeau
CN101080345A (zh) 改进飞机的侧倾操纵的方法和应用该方法的飞机
US20200387170A1 (en) System and method for enhanced altitude control of an autogyro
US1842250A (en) Aeroplane
US20090171517A1 (en) Shooshoo
RU2716386C1 (ru) Орган управления полетом летательного аппарата

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 07861019

Country of ref document: EP

Kind code of ref document: A1

NENP Non-entry into the national phase

Ref country code: DE

122 Ep: pct application non-entry in european phase

Ref document number: 07861019

Country of ref document: EP

Kind code of ref document: A1