[go: up one dir, main page]

DE29900944U1 - Airplane landing gear protection system - Google Patents

Airplane landing gear protection system

Info

Publication number
DE29900944U1
DE29900944U1 DE29900944U DE29900944U DE29900944U1 DE 29900944 U1 DE29900944 U1 DE 29900944U1 DE 29900944 U DE29900944 U DE 29900944U DE 29900944 U DE29900944 U DE 29900944U DE 29900944 U1 DE29900944 U1 DE 29900944U1
Authority
DE
Germany
Prior art keywords
aircraft
protection system
landing gear
landing
wheels
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.)
Expired - Lifetime
Application number
DE29900944U
Other languages
German (de)
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.)
Merlaku Kastriot 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 DE29900944U priority Critical patent/DE29900944U1/en
Publication of DE29900944U1 publication Critical patent/DE29900944U1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface 
    • B64C25/405—Powered wheels, e.g. for taxing
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface 
    • B64C25/40—Alighting gear characterised by elements which contact the ground or similar surface  the elements being rotated before touch-down

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Alarm Systems (AREA)
  • Retarders (AREA)
  • General Details Of Gearings (AREA)

Description

BESCHREIBUNG Fiugzeug-Fahrwerk-Schutz-SystemDESCRIPTION Aircraft landing gear protection system

Fahrwerk-Systeme üblicher Art sind sehr kompliziert. Die modernen Flugzeuge fahren die Räder erst kurz vor der Landung aus. Jede Flugzeuglandung birgt auch Gefahren in sich. Da die Räder antriebslos sind, befinden sie sich ständig relativ in Ruhe, bis zu dem Zeitpunkt, wenn das Flugzeug die Piste (Landebahn) berührt. Zu diesem Zeitpunkt werden die Räder von Null auf mehrere Hundert km/h beschleunigt. Das belastet sehr die Räder bzw. das komplette Fahrwerk. Die Räder drehen sich nicht auf die Millisekunde mit voller Geschwindigkeit. Es dauert einen Moment, bis sie die Geschwindigkeit des Flugzeugs erreichen. Während dieser Verzögerung reiben sie kräftig auf der Piste. Es entsteht durch diese Reibung eine Hitze, welche die äusseren Schichten der Räder verbrennt. Dadurch entsteht eine kleine Rauchwolke hinter dem Flugzeug, während es landet. Um ein Feuer oder das Platzen der Räder zu verhindern, werden sie in der Regel mit nicht brennbaren Gasen gefüllt. Ausserdem werden die Räder ziemlich oft gewechselt. Es entstehen dadurch auch hohe kosten.Landing gear systems of the usual type are very complicated. Modern aircraft only extend the wheels shortly before landing. Every aircraft landing also involves dangers. Since the wheels are not powered, they are always relatively at rest until the aircraft touches the runway. At this point, the wheels are accelerated from zero to several hundred km/h. This puts a lot of strain on the wheels and the entire landing gear. The wheels do not rotate at full speed to the millisecond. It takes a moment until they reach the speed of the aircraft. During this deceleration, they rub vigorously on the runway. This friction creates heat that burns the outer layers of the wheels. This creates a small cloud of smoke behind the aircraft as it lands. To prevent fire or the wheels from bursting, they are usually filled with non-flammable gases. In addition, the wheels are changed quite often. This also results in high costs.

Der in den Schutzansprüchen 1 bis 8 angegebenen Erfindung liegt das Problem zugrunde ein System zu schaffen, das in der Lage ist, das Risiko, das die Räder während dem Landeanflug platzen oder brennen, fast auszuschliessen. Die Aufgabe der Erfindung ist auch die Lebensdauer des Flugzeugfahrwerks deutlich zu verlängern.The invention specified in claims 1 to 8 is based on the problem of creating a system that is able to almost eliminate the risk of the wheels bursting or burning during the landing approach. The aim of the invention is also to significantly extend the service life of the aircraft landing gear.

Dieses Problem wird mit den in den Schutzansprüchen 1 bis 8 aufgeführten Merkmalen gelöst.This problem is solved by the features set out in claims 1 to 8.

Vorteile der Erfindung sind:Advantages of the invention are:

- Der Landeanflug wird sicherer- The landing approach becomes safer

- Kein Reifenverschleiss,- No tire wear,

- Keine Destabilisierung des Flugzeugs, wenn zuerst nur eine Seite die Piste berührt,- No destabilization of the aircraft if only one side touches the runway first,

- Keine gefährliche Hitzeentwicklung, während die Räder die Landebahn berühren- No dangerous heat build-up while the wheels are touching the runway

- Keine Rauchwolke hinter dem Flugzeug (die in der Regel durch die Räder entsteht)- No cloud of smoke behind the aircraft (which is usually caused by the wheels)

- Keine Quietschgeräusche während dem Landeanflug.- No squeaking noises during landing approach.

Ausführungsbeispiele werden anhand der Figuren 1 bis 4 erläutert. Es zeigen;Embodiments are explained using figures 1 to 4. They show;

Die Fig. 1 zeigt eine Variante mit Elektromotoren Fig. 2 zeigt eine Variante mit "Windflügel" 1 Fig. 3 zeigt eine andere Variante mit Windkraft Fig. 4 zeigt ein Reifenprofil, das zusätzlich nutzvoll wäre.Fig. 1 shows a variant with electric motors Fig. 2 shows a variant with "wind blades" 1 Fig. 3 shows another variant with wind power Fig. 4 shows a tire profile that would also be useful.

Die Steuereinheit 2, die mit dem Computer 3 des Flugzeugs 10 verbunden ist, berechnet rechtzeitig die Landegeschwindigkeit des Flugzeugs. Mit dieser Geschwindigkeit fängt sie an die Räder 4 zu drehen. Da die Elektromotoren 5 ziemlich klein sind, werden sie eine Weile brauchen bis die notwendige Drehgeschwindigkeit erreicht wird. Wenn das Flugzeug keine eigenen Geschwindigkeitsmesser (bzw. Drehzahlmesser oder Drehzahl-Sensoren) für die Räder hat, werden Drehzahl-Sensoren 6 eingebaut, welche für jedes Rad separat die Drehzahl überwachen. Diese senden (z.B. per Funk) ihre Signale weiter an die Steuereinheit, welche die Kontrolle über jedes Rad hat.The control unit 2, which is connected to the computer 3 of the aircraft 10, calculates the landing speed of the aircraft in good time. At this speed, it starts to rotate the wheels 4. Since the electric motors 5 are quite small, they will take a while to reach the necessary rotation speed. If the aircraft does not have its own speedometers (or tachometers or speed sensors) for the wheels, speed sensors 6 are installed, which monitor the speed for each wheel separately. These send their signals (e.g. by radio) to the control unit, which has control over each wheel.

Die andere Variante ist rein mechanisch. Hier wird die Windkraft benutzt, um die Räder vor der Landung zu drehen. Seitlich an die Rad-Felgen sind kleine flügelartige Elemente 9 angebracht, welche das Rad zur Drehung zwingen.
Auch ein besonderes Rad-Profil 8 kann behilflich sein (Fig. 4).The other variant is purely mechanical. Here, wind power is used to turn the wheels before landing. Small wing-like elements 9 are attached to the sides of the wheel rims, which force the wheel to turn.
A special wheel profile 8 can also be helpful (Fig. 4).

Claims (8)

_ "I — SCHUTZANSPRÜCHE_ "I — PROTECTION CLAIMS 1. Flugzeug-Fahrwerk-Schutz-System, dadurch gekennzeichnet, dass kleine Elektromotoren die Räder des Flugzeugs vor der Landung annähernd mit derselben Geschwindigkeit vorwärts drehen, mit der sie sich drehen würden, wenn das Flugzeug landet bzw. die Landepiste berührt.1. Aircraft landing gear protection system, characterized in that small electric motors rotate the wheels of the aircraft forward before landing at approximately the same speed at which they would rotate when the aircraft lands or touches the runway. 2. Flugzeug-Fahrwerk-Schutz-System nach Anspruch 1, dadurch gekennzeichnet, dass die Elektromotoren kurz vor der Landung aktiviert werden können.2. Aircraft landing gear protection system according to claim 1, characterized in that the electric motors can be activated shortly before landing. 3. Flugzeug-Fahrwerk-Schutz-System, dadurch gekennzeichnet, dass kleine Wind-Elemente seitlich in die Räder eingebaut die Wind-Kraft nutzen, nachdem das Fahrwerk bei der Landung ausgefahren ist, um die Räder mit einer Geschwindigkeit vorwärts zu drehen, die annähernd der Geschwindigkeit des Flugzeugs bei der Landung entspricht.3. Aircraft landing gear protection system, characterized in that small wind elements built into the sides of the wheels use the wind force after the landing gear is extended during landing to rotate the wheels forward at a speed that approximately corresponds to the speed of the aircraft during landing. 4. Flugzeug-Fahrwerk-Schutz-System nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, dass eine Steuereinheit die Drehgeschwindigkeit der Räder vor der Landung überwacht.4. Aircraft landing gear protection system according to one of claims 1 to 3, characterized in that a control unit monitors the rotational speed of the wheels before landing. 5. Flugzeug-Fahrwerk-Schutz-System nach Anspruch 1 und / oder 3, dadurch gekennzeichnet, dass die Steuereinheit mit einem Computer des Flugzeugs verbunden ist, um die Daten der notwendigen Parameter auszutauschen und zu berechnen.5. Aircraft landing gear protection system according to claim 1 and/or 3, characterized in that the control unit is connected to a computer of the aircraft in order to exchange and calculate the data of the necessary parameters. 6. Flugzeug-Fahrwerk-Schutz-System nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet,6. Aircraft landing gear protection system according to one of claims 1 to 5, characterized in that dass die Steuereinheit die Drehgeschwindigkeit der Räder passend zu der Geschwindigkeit des Flugzeugs im Landezeitpunkt berechnet.that the control unit calculates the rotation speed of the wheels to match the speed of the aircraft at the time of landing. 7. Flugzeug-Fahrwerk-Schutz-System nach einem der Ansprüche 1 bis 6, dadurch gekennzeichnet,7. Aircraft landing gear protection system according to one of claims 1 to 6, characterized in that dass für jedes einzelne Rad Drehzahl-Sensoren ihre Signale an die Steuereinheit zur Bearbeitung weiterleiten.that for each individual wheel, speed sensors transmit their signals to the control unit for processing. 8. Flugzeug-Fahrwerk-Schutz-System,
dadurch gekennzeichnet,8. Aircraft landing gear protection system,
characterized, dass ein Spezial-Reifen-Profil die Luftstromverhältnisse über und unter dem Rad ändert, und so die Windkraft nutzt, um die Räder des Flugzeugs während dem Landeanflug schnell vorwärts zu drehen.that a special tire profile changes the airflow conditions above and below the wheel, thus using the wind power to quickly rotate the aircraft's wheels forward during the landing approach.
DE29900944U 1999-01-20 1999-01-20 Airplane landing gear protection system Expired - Lifetime DE29900944U1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
DE29900944U DE29900944U1 (en) 1999-01-20 1999-01-20 Airplane landing gear protection system

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE29900944U DE29900944U1 (en) 1999-01-20 1999-01-20 Airplane landing gear protection system

Publications (1)

Publication Number Publication Date
DE29900944U1 true DE29900944U1 (en) 1999-04-08

Family

ID=8068247

Family Applications (1)

Application Number Title Priority Date Filing Date
DE29900944U Expired - Lifetime DE29900944U1 (en) 1999-01-20 1999-01-20 Airplane landing gear protection system

Country Status (1)

Country Link
DE (1) DE29900944U1 (en)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102004028464A1 (en) * 2004-06-11 2005-12-29 Theodor Beck Drive for wheels of aircraft used during landing comprises system whereby wheels before touching down on runway are set into rotation by wind vanes on wheel rims
WO2007048164A1 (en) * 2004-12-09 2007-05-03 Soderberg Rod F Magnetically induced aircraft landing wheel rotation
US7594626B2 (en) 2006-06-08 2009-09-29 Rod F. Soderberg Magnetically induced aircraft landing wheel rotation
WO2009127885A2 (en) * 2008-04-17 2009-10-22 Darko Horvat Flexible crankshaft for software controllable aircraft wheel drive
US8684300B2 (en) 2009-08-28 2014-04-01 Airbus Operations Limited Aircraft landing gear
WO2014070033A3 (en) * 2012-05-31 2014-06-26 Costache Ovidiu Automated wheel turn speed adjustment system for aircraft landing aimed at reducing aircraft tire wear

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102004028464A1 (en) * 2004-06-11 2005-12-29 Theodor Beck Drive for wheels of aircraft used during landing comprises system whereby wheels before touching down on runway are set into rotation by wind vanes on wheel rims
WO2007048164A1 (en) * 2004-12-09 2007-05-03 Soderberg Rod F Magnetically induced aircraft landing wheel rotation
GB2436042A (en) * 2004-12-09 2007-09-12 Rod F Soderberg Magnetically induced aircraft landing wheel rotation
GB2436042B (en) * 2004-12-09 2009-11-04 Rod F Soderberg Improvements in aircraft landing wheel assembly
US7594626B2 (en) 2006-06-08 2009-09-29 Rod F. Soderberg Magnetically induced aircraft landing wheel rotation
WO2009127885A2 (en) * 2008-04-17 2009-10-22 Darko Horvat Flexible crankshaft for software controllable aircraft wheel drive
WO2009127885A3 (en) * 2008-04-17 2010-01-21 Darko Horvat Flexible crankshaft for software controllable aircraft wheel drive
US8684300B2 (en) 2009-08-28 2014-04-01 Airbus Operations Limited Aircraft landing gear
US9428266B2 (en) 2009-08-28 2016-08-30 Airbus Operations Limited Aircraft landing gear
US10562615B2 (en) 2009-08-28 2020-02-18 Airbus Operations Limited Aircraft landing gear
US11628931B2 (en) 2009-08-28 2023-04-18 Airbus Operations Limited Aircraft landing gear with pivoting drive transmission
WO2014070033A3 (en) * 2012-05-31 2014-06-26 Costache Ovidiu Automated wheel turn speed adjustment system for aircraft landing aimed at reducing aircraft tire wear

Similar Documents

Publication Publication Date Title
DE102008011791B4 (en) Integrated multifunctional wheel drive system for aircraft
EP2183136B1 (en) Brake system for a vehicle and a method for the operation of a brake system for a vehicle
DE60221949T2 (en) Electric steering for a vehicle with triple redundancy
DE102011085345A1 (en) Vehicle dynamics control platform between application and controlled object
DE102009032754A1 (en) Device for driving stabilization of trailer pulled by towing vehicle, has control unit electrically connected with stability sensor and drive unit, which is controllable by control unit depending on signals of stability sensor
US11332236B2 (en) Force limiting system and method for limiting loads in a powered aircraft landing gear drive wheel
DE102014006675A1 (en) Device and method for vehicle driving control
DE102017220797B4 (en) DEVICE AND METHOD FOR CONTROLLING POWER CONSUMPTION OF AN ELECTRONIC AUTOMOBILE SYSTEM
DE29900944U1 (en) Airplane landing gear protection system
EP3130798A1 (en) Method for controlling pitch drives of a wind turbine, control device and wind turbine
WO2019052807A1 (en) Method and device for determining wheel slip information of an electrically driven wheel of a motor vehicle
DE10235472B4 (en) Device for controlling the brakes of a commercial vehicle
DE102012107648B4 (en) Drive device for towed vehicles
DE102015110229B4 (en) Rail vehicle braking system and method for operating a rail vehicle braking system
DE3010903A1 (en) HELICOPTER
EP1746000B1 (en) Rail vehicle comprising means for monitoring the wheel-rail adhesion value
WO2019211087A1 (en) Control system for controlling a brake system of a rail vehicle
DE102010021352A1 (en) Driving apparatus for motor vehicle, has vehicle wheels propelling electrical machines and control device, in which moment calculation unit conducts appropriate control signal on rider-side default
DE102016012174A1 (en) Drive and / or braking device for a vehicle
EP3197734A1 (en) Method for controlling a braking device and braking device
DE102018215935A1 (en) Electrically driven axle
DE102017214583A1 (en) Method and device for increasing the stability of the driving state of a single-track motor vehicle
DE20302086U1 (en) Braking system for roller blades has signal operated electromechanical actuator
EP4069524A1 (en) Control of the dispensing of an adhesion-increasing agent for a rail vehicle
DE10201509A1 (en) Aircraft, in particular for transporting loads

Legal Events

Date Code Title Description
R086 Non-binding declaration of licensing interest
R207 Utility model specification

Effective date: 19990520

R081 Change of applicant/patentee

Owner name: MERLAKU, KASTRIOT, DE

Free format text: FORMER OWNER: MERLAKU, KASTRIOT, 84347 PFARRKIRCHEN, DE

Effective date: 20000816

R150 Utility model maintained after payment of first maintenance fee after three years

Effective date: 20020514

R157 Lapse of ip right after 6 years

Effective date: 20050802