DE102010025488A1 - Retractable engine for airplanes, has building block secured at low end of circular, uniformly wide motor carrier, which is connected to upper and lower edges by guide elements in halt frame near fuselage aperture - Google Patents

Retractable engine for airplanes, has building block secured at low end of circular, uniformly wide motor carrier, which is connected to upper and lower edges by guide elements in halt frame near fuselage aperture Download PDF

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DE102010025488A1
DE102010025488A1 DE102010025488A DE102010025488A DE102010025488A1 DE 102010025488 A1 DE102010025488 A1 DE 102010025488A1 DE 102010025488 A DE102010025488 A DE 102010025488A DE 102010025488 A DE102010025488 A DE 102010025488A DE 102010025488 A1 DE102010025488 A1 DE 102010025488A1
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circular
engine
guide elements
building block
motor carrier
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DE102010025488B4 (en
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Anmelder Gleich
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C31/00—Aircraft intended to be sustained without power plant; Powered hang-glider-type aircraft; Microlight-type aircraft
    • B64C31/02—Gliders, e.g. sailplanes
    • B64C31/024—Gliders, e.g. sailplanes with auxiliary power plant
    • 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
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Arrangement Or Mounting Of Propulsion Units For Vehicles (AREA)
  • Toys (AREA)

Abstract

The engine has a building block secured at a low end of the circular motor carrier (4), where the building block is fed in a circular link guide (5). The carrier is connected to upper and lower edges by guide elements (3) i.e. ball-bearing rollers, in a halt frame (8) near a fuselage aperture (1). A spindle motor (7) performs retracting and extending of the motor carrier. The motor carrier is guided along a circular path.

Description

Klapptriebwerke für Flugzeuge üblicher Bauart benötigen für den Einbau in den Flugzeugrumpf eine große Rumpföffnung und lange verschließbare Rumpfklappen, damit der Mechanismus aus- und eingefahren werden kann. Damit wird jedoch der Flugzeugrumpf erheblich geschwächt und auch die Aerodynamik des Flugzeuges wird durch die große Klappenöffnung negativ beeinflusst.Folding engines for aircraft of conventional design require for installation in the fuselage a large hull opening and long lockable hull flaps so that the mechanism can be retracted and retracted. This, however, the aircraft fuselage is significantly weakened and the aerodynamics of the aircraft is adversely affected by the large flap opening.

Einen Schritt zur Optimierung dieser oben genannten Nachteile sind Kulissentriebwerke. Diese Art der Triebwerke versucht die benötigte Rumpföffnung zu verkleinern, dadurch dass der Motorträgerarm nicht geklappt, sondern aus dem Rumpf geschoben wird. Der bisher bei den Kulissentriebwerken übliche Verschwenkarm ( DE-101 52 447 A1 ) hat am Haltegestell eine Kulissenführung und ein Kulissenbaustein. Am Motorträgerarm befindet sich eine zweite Kulissenführung und ein weiterer Kulissenbaustein. In Summe liegen bei dieser Erfindung also zwei Kulissenführungen vor und es werden mindestens zwei Kulissenbausteine benötigt. Die Notwendigkeit einer zweiten Kulisse im Träger ergibt sich aus der Tatsache, dass der Träger nicht gleichförmig in der Breite und nicht kreisförmig ist. Bei dem weiteren bisher üblichen Triebwerk ( DE-10 2004 008 073 A1 ) wird mindestens eine Kulissen mit mindestens zwei Kulissenbausteinen benötigt. Beim Aus- und Einfahrvorgang wird die Richtung ausschließlich für den gesamten Weg von der Kulissenführung vorgegeben. Eine Führung des Trägers durch feste Führungselemente an der Rumpföffnung ist nicht vorgesehen und geometrisch aufgrund des geradlinigen Motorträgers nicht möglich.One step to optimize these above-mentioned disadvantages are sliding-link engines. This type of engines trying to reduce the required hull opening, characterized in that the engine support arm is not folded, but is pushed out of the fuselage. The pivoting arm previously used in the scenery engines ( DE-101 52 447 A1 ) has on the holding frame a link guide and a link block. On the motor arm is a second link guide and another link block. In sum, there are two slide guides in this invention and at least two slide blocks are needed. The need for a second link in the carrier results from the fact that the carrier is not uniform in width and non-circular. In the other previously customary engine ( DE-10 2004 008 073 A1 ) at least one scenery with at least two gate blocks is needed. During extension and retraction, the direction is specified exclusively for the entire path from the slotted guide. A guide of the carrier by fixed guide elements on the hull opening is not provided and geometric not possible due to the rectilinear engine mount.

Die im Patentanspruch 1 angegebene Erfindung liegt das Problem zugrunde, einen ausfahrbaren Klapptriebwerksmechanismus zu schaffen, der mit einer minimalen Rumpföffnung den Mechanismus ausfährt und im eingefahrenen Zustand den schweren Hauptmotor sicher lagert. Besonders bei Flugzeuglandungen treten große vertikal Beschleunigungen auf, die zu Beschädigungen des Motorträgers führen, wenn lange Hebelkräfte auf den Motorträger wirken.The specified in claim 1 invention is based on the problem to provide an extendable retractable engine mechanism, which extends with a minimum hull opening the mechanism and stored in the retracted state, the heavy main engine safely. Especially in aircraft landings occur large vertical accelerations, which lead to damage to the engine mount, when long leverage forces act on the engine mount.

Dieses Problem wird durch die im Patenanspruch 1 aufgeführten Merkmale gelöst.This problem is solved by the features listed in claim 1.

Die mit der Erfindung erzielten Vorteile bestehen insbesondere darin, dass der Motorträger auf einer Kreisbahn geführt wird, die eine minimale Rumpföffnung ermöglicht und dass der Motorträger im eingefahrenen Zustand durch die Führungselemente an der Rumpföffnung sicher gelagert ist. Lange Hebelkräfte können auf den Motorträger auf diese Weise nicht wirken, da die Führungselemente an der Unterkante des Motorträgers die Kräfte nahe am Motor aufnehmen.The advantages achieved by the invention are in particular that the motor carrier is guided on a circular path, which allows a minimum hull opening and that the motor carrier is securely stored in the retracted state by the guide elements on the hull opening. Long leverage forces can not act on the engine mount in this manner as the guideways on the bottom edge of the engine mount absorb forces near the engine.

Ein Ausführungsbeispiel der Erfindung ist in den Zeichnungen dargestellt und wird im Folgenden näher beschrieben.An embodiment of the invention is illustrated in the drawings and will be described in more detail below.

Es zeigenShow it

1 das eingefahrene Klapptriebwerk 1 the retracted folding engine

2 das halb ausgefahrene Klapptriebwerk 2 the half-extended retractable engine

3 das voll ausgefahrene Klapptriebwerk mit stehendem Motor 3 the fully extended retractable engine with stationary engine

4 das voll ausgefahrene Klapptriebwerk mit laufendem Motor 4 the fully extended retractable engine with running engine

BezugszeichenlisteLIST OF REFERENCE NUMBERS

11
Rumpfklappen/RumpföffnungBody flap / trunk opening
22
Drehachse für den HauptmotorRotary axis for the main engine
33
Führungselementeguide elements
44
Motorträgerengine support
55
Kulissenführunglink guide
66
Kulissenbausteinbackdrop block
77
Spindelmotorspindle motor
88th
Haltegestellholding frame

Die Erfindung beruht im Wesentlichen darauf, dass ein kreisförmiger Motorträger (4) durch Führungselemente (3) an dem Haltegestell (8) geleitet wird. Diese Führungselemente sind vorzugsweise kugelgelagerte Rollen, damit der Motorträger an der Ober- und Unterkante leichtgängig durchgeführt werden kann. Diese Führungselemente sind möglichst nah an der Rumpföffnung (1) angebracht, damit im eingefahrenen Zustand der Hauptmotor sicher gelagert ist. Die Vertikalkräfte bei einer Flugzeuglandung könnten sonst den Motorträgerarm durch die auftretenden Hebelkräfte beschädigen, wenn der Motorträgerarm nur im unteren Bereich des Trägers gelagert ist. Ein einziger Kulissenbaustein (6) ist am untersten Ende des kreisförmigen Motorträgers (4) befestigt, der in einer kreisförmigen Kulissenführung (5) geführt wird. Nur die kreisförmige Geometrie der Motorträger (4) ermöglicht diese Art der Führung entlang der Trägerform für den Ein- und Ausfahrvorgang. Das Ein- und Ausfahren des Motorträgers wird vorzugsweise durch einen Spindelmotor (7) bewirkt.The invention is essentially based on the fact that a circular motor mount ( 4 ) by guide elements ( 3 ) on the holding frame ( 8th ). These guide elements are preferably ball-bearing rollers, so that the engine mount can be performed easily on the top and bottom edges. These guide elements are as close as possible to the hull opening ( 1 ) is mounted so that when retracted the main engine is stored safely. The vertical forces in an aircraft landing could otherwise damage the engine mount arm by the lever forces that occur when the engine mount arm is only supported at the bottom of the carrier. One single building block ( 6 ) is at the lowermost end of the circular engine mount ( 4 ), which in a circular slotted guide ( 5 ) to be led. Only the circular geometry of the engine mounts ( 4 ) allows this type of guidance along the carrier shape for the extension and retraction process. The retraction and extension of the motor carrier is preferably by a spindle motor ( 7 ) causes.

Der kreisförmige Motorträgerarm (4) hat eine gleichmäßige Breite und ermöglicht dadurch eine Führung entlang der Ober- und Unterkante des Motorträgerarms (4) in den Führungselementen (3).The circular motor arm ( 4 ) has a uniform width and thereby allows a guide along the top and bottom edges of the motor support arm ( 4 ) in the guiding elements ( 3 ).

ZITATE ENTHALTEN IN DER BESCHREIBUNG QUOTES INCLUDE IN THE DESCRIPTION

Diese Liste der vom Anmelder aufgeführten Dokumente wurde automatisiert erzeugt und ist ausschließlich zur besseren Information des Lesers aufgenommen. Die Liste ist nicht Bestandteil der deutschen Patent- bzw. Gebrauchsmusteranmeldung. Das DPMA übernimmt keinerlei Haftung für etwaige Fehler oder Auslassungen.This list of the documents listed by the applicant has been generated automatically and is included solely for the better information of the reader. The list is not part of the German patent or utility model application. The DPMA assumes no liability for any errors or omissions.

Zitierte PatentliteraturCited patent literature

  • DE 10152447 A1 [0002] DE 10152447 A1 [0002]
  • DE 102004008073 A1 [0002] DE 102004008073 A1 [0002]

Claims (1)

Klapptriebwerk für Flugzeuge, dadurch gekennzeichnet, dass ein kreisförmiger, gleichmäßig breiter Motorträger an der Ober- und Unterkante durch Führungselemente in einem Haltegestell nahe der Flugzeugrumpföffnung geleitet wird und ein einziger Kulissenbaustein am untersten Ende des kreisförmigen Motorträgers befestigt ist, der in einer kreisförmigen Kulissenführung geführt wird.A retractable aircraft engine, characterized in that a circular, uniformly wide engine mount at the top and bottom edge is guided by guide elements in a holding frame near the aircraft fuselage opening and a single link block is attached to the lowermost end of the circular engine mount, which is guided in a circular slotted guide ,
DE201010025488 2010-06-29 2010-06-29 Retractable engine for aircraft Active DE102010025488B4 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
DE201010025488 DE102010025488B4 (en) 2010-06-29 2010-06-29 Retractable engine for aircraft

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE201010025488 DE102010025488B4 (en) 2010-06-29 2010-06-29 Retractable engine for aircraft

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DE102010025488A1 true DE102010025488A1 (en) 2011-12-29
DE102010025488B4 DE102010025488B4 (en) 2012-10-25

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Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102013010084A1 (en) * 2013-06-14 2014-12-18 Christian Etter Single-extension mechanism with mechanical locking in the end positions for engines / drives in aircraft
FR3015434A1 (en) * 2013-12-23 2015-06-26 Snecma TURBOMACHINE SUSPENSION
DE102015121744A1 (en) * 2015-12-14 2017-06-14 Hans Ulrich Tobuschat Drive device for a missile
DE102018222543A1 (en) * 2018-12-20 2020-06-25 Rolls-Royce Deutschland Ltd & Co Kg Aircraft with a hybrid electric drive and method for operating such an aircraft
EP4186787A1 (en) * 2021-11-24 2023-05-31 Raytheon Technologies Corporation Aircraft propulsor and method for using said propulsor
DE102018118953B4 (en) 2017-08-09 2023-06-01 Deutsches Zentrum für Luft- und Raumfahrt e.V. Retractable auxiliary drive for gliders

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10152447A1 (en) 2001-10-26 2003-05-15 Pk Ohg Flap drive for glider has slideways on side wall and drive arm for slide blocks attached to drive arm and housing frame
DE102004008073A1 (en) 2004-02-19 2005-09-22 Florian Schambeck Telescopic driving mechanism for a model airplane comprises a support arm having a lower end which is guided by a connecting rail into a connecting link to provide a means for the movement of the support arm
DE202008006591U1 (en) * 2008-05-14 2008-08-21 Thoma, Martin, Dr. Retractable engine for aircraft

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10152447A1 (en) 2001-10-26 2003-05-15 Pk Ohg Flap drive for glider has slideways on side wall and drive arm for slide blocks attached to drive arm and housing frame
DE102004008073A1 (en) 2004-02-19 2005-09-22 Florian Schambeck Telescopic driving mechanism for a model airplane comprises a support arm having a lower end which is guided by a connecting rail into a connecting link to provide a means for the movement of the support arm
DE202008006591U1 (en) * 2008-05-14 2008-08-21 Thoma, Martin, Dr. Retractable engine for aircraft

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102013010084A1 (en) * 2013-06-14 2014-12-18 Christian Etter Single-extension mechanism with mechanical locking in the end positions for engines / drives in aircraft
FR3015434A1 (en) * 2013-12-23 2015-06-26 Snecma TURBOMACHINE SUSPENSION
US9394057B2 (en) 2013-12-23 2016-07-19 Snecma Suspension for a turbine engine
DE102015121744A1 (en) * 2015-12-14 2017-06-14 Hans Ulrich Tobuschat Drive device for a missile
DE102015121744B4 (en) 2015-12-14 2021-12-16 Hans Ulrich Tobuschat Propulsion device for a missile
DE102018118953B4 (en) 2017-08-09 2023-06-01 Deutsches Zentrum für Luft- und Raumfahrt e.V. Retractable auxiliary drive for gliders
DE102018222543A1 (en) * 2018-12-20 2020-06-25 Rolls-Royce Deutschland Ltd & Co Kg Aircraft with a hybrid electric drive and method for operating such an aircraft
EP4186787A1 (en) * 2021-11-24 2023-05-31 Raytheon Technologies Corporation Aircraft propulsor and method for using said propulsor

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