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DE3415976A1 - Flap arrangement on the end plates of mainplanes - Google Patents

Flap arrangement on the end plates of mainplanes

Info

Publication number
DE3415976A1
DE3415976A1 DE19843415976 DE3415976A DE3415976A1 DE 3415976 A1 DE3415976 A1 DE 3415976A1 DE 19843415976 DE19843415976 DE 19843415976 DE 3415976 A DE3415976 A DE 3415976A DE 3415976 A1 DE3415976 A1 DE 3415976A1
Authority
DE
Germany
Prior art keywords
flaps
flap arrangement
flap
arrangement according
deflection
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.)
Withdrawn
Application number
DE19843415976
Other languages
German (de)
Inventor
Hellmuth Dipl.-Ing. 7000 Stuttgart Binder
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.)
BINDER, HELLMUTH, DIPL.-ING., 8720 SCHWEINFURT, DE
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 DE19843415976 priority Critical patent/DE3415976A1/en
Publication of DE3415976A1 publication Critical patent/DE3415976A1/en
Withdrawn legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C5/00—Stabilising surfaces
    • B64C5/08—Stabilising surfaces mounted on, or supported by, wings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C23/00—Influencing air flow over aircraft surfaces, not otherwise provided for
    • B64C23/06—Influencing air flow over aircraft surfaces, not otherwise provided for by generating vortices
    • B64C23/065—Influencing air flow over aircraft surfaces, not otherwise provided for by generating vortices at the wing tips
    • B64C23/069—Influencing air flow over aircraft surfaces, not otherwise provided for by generating vortices at the wing tips using one or more wing tip airfoil devices, e.g. winglets, splines, wing tip fences or raked wingtips
    • B64C23/076—Influencing air flow over aircraft surfaces, not otherwise provided for by generating vortices at the wing tips using one or more wing tip airfoil devices, e.g. winglets, splines, wing tip fences or raked wingtips the wing tip airfoil devices comprising one or more separate moveable members thereon affecting the vortices, e.g. flaps
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C5/00—Stabilising surfaces
    • B64C5/10—Stabilising surfaces adjustable
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Braking Arrangements (AREA)

Abstract

In order to improve the landing characteristics, especially of canard aircraft, flaps are arranged in the end plates of the mainplane, on which, in addition to the braking deflection to the left and right in opposite senses, a control deflection in the same direction can be superimposed, for lateral control. In order to simplify the landing approach, the centre of pressure of the flaps is arranged to be higher than the aircraft centre of gravity, and the rotation axis of the flaps can be inclined to the rear.

Description

Beschreibungdescription

Die Erfindung betrifft eine Klappenanordnung an den Endscheiben von Tragflügeln nach dem Oberbegriff von Anspruch 1.The invention relates to a flap arrangement on the end plates of Airfoils according to the preamble of claim 1.

Es sind Klappenanordnungen bekannt, bei denen der Ausschlag der Klappen entweder zum Steuern oder zum Bremsen des Flugzeuges dient, wie dies z.B. in den Offenlegungsschriften Nr. 1781019 (P 1781019.4) und Nr. 2054656 (P 2054656.9) dargestellt wird.There are known flap arrangements in which the deflection of the flaps is used either to steer or to brake the aircraft, as for example in the Offenlegungsschriften No. 1781019 (P 1781019.4) and No. 2054656 (P 2054656.9) are shown will.

Die Nachteile dieser, wie auch einiger anderer bekannter Anordnungen bestehen darin, daß sie entweder zum Steuern oder zum Bremsen bestimmt sind.The disadvantages of this, as well as of some other known arrangements consist in the fact that they are intended for either steering or braking.

P 2054656.9 ist außerdem ausschließlich unter Verwendung von Leitwerksträgern hinter dem Tragflügel gedacht und so z.B. für Entenflugzeuge nicht verwendbar.P 2054656.9 is also exclusively made using tail girders Thought behind the wing and therefore not usable for duck planes, for example.

Aufgabe der Erfindung ist es, eine Klappenanordnung zu schaffen, welche sowohl die erforderliche Seitensteuerung des Flugzeuges gewährleistet, wie auch gleichzeitig, vor allem während des Landeanfluges, als Luftbremse wirkt.The object of the invention is to create a flap arrangement which both the necessary lateral steering of the aircraft ensured, as well as at the same time, especially during the landing approach, acts as an air brake.

Diese Aufgabe wird erfindungsgemäß durch das kennzeichnende Merkmal von Anspruch 1 gelöst.According to the invention, this object is achieved by the characterizing feature solved by claim 1.

Über eine entsprechende Steuerung können die beiden Klappen nicht nur gleichsinnig nach links oder rechts ausgeschlagen werden, wie es zur Seitensteuerung notwendig ist, oder aber gegensinnig nach links und rechts um eine Bremsung zu erreichen, sondern die Ausschläge können auch beliebig überlagert werden, so daß Seitensteuerung und Bremsung unbeeinflußt voneinander erreicht werden können.The two flaps cannot be controlled via a corresponding control can only be knocked out in the same direction to the left or right, as is the case for the lateral control is necessary, or in opposite directions to the left and right to achieve braking, but the deflections can also be superimposed as desired, so that side control and braking can be achieved unaffected by one another.

Eine wichtige Folge dieser Anordnung ist der geringe Bauaufwand, da für zwei verschiedene Funktionen nur ein einziges Klappenpaar benötigt wird und somit die Kosten niedrig gehalten werden können.An important consequence of this arrangement is the low construction costs because only a single pair of flaps is required for two different functions and thus the costs can be kept low.

Eine zweite Folge ist die Einsparung an Gewicht, was sich vor allem auf die Flugleistungen günstig auswirkt und somit auch den Brennstoffverbrauch niedrig hält.A second consequence is the saving in weight, which is especially important has a favorable effect on flight performance and therefore also low fuel consumption holds.

Weitere vorteilhafte Eigenschaften der Erfindung ergeben sich aus den Unteransprüchen bzw. aus der nachfolgenden Erläuterung und sind anhand der beigefügten Zeichnung verdeutlicht.Further advantageous properties of the invention emerge from the subclaims or from the following explanation and are based on the attached Drawing clarified.

Gemäß Anspruch 2 ist die Drehachse 3 der Klappe 2 mit dem Winkel nach hinten geneigt. Dadurch entsteht bei deren Betätigung eine abwärts gerichtete Komponente W 2 der Widerstandskraft W und somit ein leichtes schwanzlastiges Moment um den Schwerpunkt S mit dem Hebelarm L, welches das Kurvenfliegen und vor allem den Landeanflug erleichtert.According to claim 2, the axis of rotation 3 of the flap 2 is according to the angle tilted back. This creates a downward component when actuated W 2 of the drag force W and thus a slight tail-heavy moment around the Center of gravity S with the lever arm L, which is responsible for turning and especially the landing approach relieved.

Gemäß Anspruch 3 liegt der Druckmittelpunkt D der Klappen 2 höher als der Schwerpunkt S, was ebenfalls dazu beiträgt, daß bei gespreizten Klappen im Landeanflug ein schwanziastiges Moment M=2.W1.H entsteht, welches die Trimmung überflüssig machen kann oder zumindest deren Verringerung bewirkt.According to claim 3, the pressure center point D of the flaps 2 is higher than the center of gravity S, which also helps that when the flaps are spread in the approach to landing a tail-axed moment M = 2.W1.H arises, which the trim can make it superfluous or at least reduce it.

Gemäß Anspruch 4 besitzen;; die Klappen 2 einen aerodynamischen Ausgleich 5, welcher die zur Betätigung notwendige? Kraft herabsetzt.According to claim 4 have ;; the flaps 2 an aerodynamic compensation 5, which one is necessary for actuation? Lowers strength.

Gemäß Anspruch 5 bilden die Klappen 2 mit den Endscheiben 1 einen Schlitz 4, der den Zweck hat, den Luftwiderstand der nach außen gestellten Klappe 2 zu erhöhen.According to claim 5, the flaps 2 with the end plates 1 form one Slot 4, which has the purpose of reducing the air resistance of the flap that is placed outwards 2 to increase.

Gemäß Anspruch 6 können die Klappen 2 aufgrund des in Anspruch 4 erwähnten Ausgleichs 5 mechanisch und von Hand betätigt werden, was vor allem für kleinere Flugzeuge mit 2 bis 6 Sitzen von Bedeutung ist.According to claim 6, the flaps 2 on the basis of what is mentioned in claim 4 Compensating 5 can be operated mechanically and by hand, especially for smaller ones Aircraft with 2 to 6 seats is important.

Für größere Flugzeuge ist eine elektromechanische oder hydraulische Betätigung angezeigt, die aber ebenfalls aufgrund des Ausgleichs mit geringen Kräften auskommt.For larger aircraft, an electromechanical or hydraulic one Actuation indicated, but also due to the compensation with low forces gets by.

Gemäß Anspruch 7 ist der Klappenausschlag bei der kurveninneren Klappe größer als bei der kurvenäußeren, um über den größeren Luftwiderstand der kurveninneren Klappe, zusammen mit dem Giermoment beider (gleichsinnig wirkenden) Klappen ein größeres Gesamtgiermoment zu erhalten.According to claim 7, the flap deflection in the flap on the inside of the curve larger than on the outside of the bend in order to take advantage of the greater air resistance on the inside of the bend Fold in, together with the yaw moment of both (acting in the same direction) flaps to get greater total yaw moment.

- Leerseite -- blank page -

Claims (7)

Patentansprüche 1. Klappenanordnung an den Endscheiben von Tragflügeln, insbesondere von Entenflugzeugen, dadurch gekennzeichnet, daß dem gleichsinnigen Steuerausschlag der Klappen ein rechts gegen links gegensinniger Bremsausschlag beliebiger Größe überlagerbar ist, derart, daß sowohl der Steuer ausschlag als auch der Bremsausschlag voneinander unabhängig betätigt werden kann. Claims 1. Flap arrangement on the end disks of airfoils, in particular of duck planes, characterized in that the same direction Control deflection of the flaps a right to left opposite braking deflection any size can be superimposed in such a way that both the tax rash as well the brake deflection can be operated independently of each other. 2. Klappenanordnung nach Anspruch 1, dadurch gekennzeichnet, daß die Drehachse der Klappen in der Seitenansicht nach hinten geneigt ist.2. Flap arrangement according to claim 1, characterized in that the The axis of rotation of the flaps is inclined to the rear in the side view. 3. Klappenanordnung nach Anspruch 1, dadurch gekennzeichnet, daß der Druckmittelpunkt der Klappen sich über dem Flugzeugschwerpunkt befindet.3. flap arrangement according to claim 1, characterized in that the The center of pressure of the flaps is above the aircraft's center of gravity. 4. Klappenanordnung nach Anspruch 1, dadurch gekennzeichnet, daß die Klappen einen an sich bekannten aerodynamischen Ausgleich besitzen.4. flap arrangement according to claim 1, characterized in that the Flaps have a known aerodynamic compensation. 5. Klappenanordnung nach Anspruch 1, dadurch gekennzeichnet, daß die Klappen in nach außen geschwenktem Zustand mit den Endscheiben einen Schlitz bilden.5. flap arrangement according to claim 1, characterized in that the Flaps in the outwardly pivoted state form a slot with the end plates. 6. Klappenanordnung nach Anspruch 1, dadurch gekennzeichnet, daß die Klappen mechanisch, elektromechanisch oder hydraulisch betätigt werden können.6. flap arrangement according to claim 1, characterized in that the Flaps can be operated mechanically, electromechanically or hydraulically. 7. Klappenanordnung nach Anspruch 1, dadurch gekennzeichnet, daß der Steuerausschlag der kurveninneren Klappe größer ist als der der Kurvenäußeren Klappe.7. flap arrangement according to claim 1, characterized in that the The control deflection of the flap on the inside of the curve is greater than that of the flap on the outside of the curve.
DE19843415976 1984-04-28 1984-04-28 Flap arrangement on the end plates of mainplanes Withdrawn DE3415976A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
DE19843415976 DE3415976A1 (en) 1984-04-28 1984-04-28 Flap arrangement on the end plates of mainplanes

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE19843415976 DE3415976A1 (en) 1984-04-28 1984-04-28 Flap arrangement on the end plates of mainplanes

Publications (1)

Publication Number Publication Date
DE3415976A1 true DE3415976A1 (en) 1985-10-31

Family

ID=6234651

Family Applications (1)

Application Number Title Priority Date Filing Date
DE19843415976 Withdrawn DE3415976A1 (en) 1984-04-28 1984-04-28 Flap arrangement on the end plates of mainplanes

Country Status (1)

Country Link
DE (1) DE3415976A1 (en)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3634250C1 (en) * 1986-10-08 1988-03-03 Dornier Gmbh Aircraft control
DE20211664U1 (en) 2002-07-29 2003-01-09 Kähler, Kai, 20355 Hamburg Controllable side rudders are installed along or close to vertical axis of aircraft above and/or below fuselage and operate synchronously with the tail rudder
DE102008022452A1 (en) * 2008-05-08 2009-12-03 Bauhaus Luftfahrt E.V. Aircraft, has central flight controller adapted such that individual auxiliary wings are adjusted in position independent of other auxiliary wings, where position of auxiliary wings is adjusted to each other and to main wings
FR2948628A1 (en) * 2009-08-03 2011-02-04 Airbus Operations Sas AIRPLANE WITH LACET CONTROL BY DIFFERENTIAL TRAINING
CN112977599A (en) * 2019-12-17 2021-06-18 北汽福田汽车股份有限公司 Steering gear, vehicle steering system and vehicle

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3634250C1 (en) * 1986-10-08 1988-03-03 Dornier Gmbh Aircraft control
DE20211664U1 (en) 2002-07-29 2003-01-09 Kähler, Kai, 20355 Hamburg Controllable side rudders are installed along or close to vertical axis of aircraft above and/or below fuselage and operate synchronously with the tail rudder
DE102008022452A1 (en) * 2008-05-08 2009-12-03 Bauhaus Luftfahrt E.V. Aircraft, has central flight controller adapted such that individual auxiliary wings are adjusted in position independent of other auxiliary wings, where position of auxiliary wings is adjusted to each other and to main wings
DE102008022452B4 (en) * 2008-05-08 2010-09-23 Bauhaus Luftfahrt E. V. Airplane with actively controllable auxiliary wings
FR2948628A1 (en) * 2009-08-03 2011-02-04 Airbus Operations Sas AIRPLANE WITH LACET CONTROL BY DIFFERENTIAL TRAINING
US8876044B2 (en) 2009-08-03 2014-11-04 Airbus Operations S.A.S. Aircraft with yaw control by differential drag
CN112977599A (en) * 2019-12-17 2021-06-18 北汽福田汽车股份有限公司 Steering gear, vehicle steering system and vehicle
CN112977599B (en) * 2019-12-17 2022-06-21 北汽福田汽车股份有限公司 Steering gear, vehicle steering system and vehicle

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Legal Events

Date Code Title Description
8127 New person/name/address of the applicant

Owner name: BINDER, HELLMUTH, DIPL.-ING., 8720 SCHWEINFURT, DE

8141 Disposal/no request for examination