WO2009093223A2 - Landing gear - Google Patents

Landing gear Download PDF

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Publication number
WO2009093223A2
WO2009093223A2 PCT/IB2009/050302 IB2009050302W WO2009093223A2 WO 2009093223 A2 WO2009093223 A2 WO 2009093223A2 IB 2009050302 W IB2009050302 W IB 2009050302W WO 2009093223 A2 WO2009093223 A2 WO 2009093223A2
Authority
WO
WIPO (PCT)
Prior art keywords
landing gear
articulated
lever element
wheels
shock absorbing
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/IB2009/050302
Other languages
French (fr)
Other versions
WO2009093223A3 (en
Inventor
Flora Nardone
Giuseppe Carreras
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.)
Magnaghi Aeronautica SpA
Original Assignee
Magnaghi Aeronautica SpA
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 Magnaghi Aeronautica SpA filed Critical Magnaghi Aeronautica SpA
Priority to CA2713135A priority Critical patent/CA2713135A1/en
Priority to US12/864,371 priority patent/US20110180662A1/en
Priority to AT09704550T priority patent/ATE549241T1/en
Priority to EP09704550A priority patent/EP2247499B1/en
Priority to BRPI0907616-6A priority patent/BRPI0907616A2/en
Publication of WO2009093223A2 publication Critical patent/WO2009093223A2/en
Publication of WO2009093223A3 publication Critical patent/WO2009093223A3/en
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/02—Undercarriages
    • B64C25/08—Undercarriages non-fixed, e.g. jettisonable
    • B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
    • B64C25/14—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like fore-and-aft
    • 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 
    • B64C25/34—Alighting gear characterised by elements which contact the ground or similar surface  wheeled type, e.g. multi-wheeled bogies
    • 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 
    • B64C25/58—Arrangements or adaptations of shock-absorbers or springs
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/02—Undercarriages
    • B64C25/08—Undercarriages non-fixed, e.g. jettisonable
    • B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
    • B64C25/12—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like sideways
    • B64C2025/125—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like sideways into the fuselage, e.g. main landing gear pivotally retracting into or extending out of the fuselage

Definitions

  • the present invention refers to an landing gear for aircrafts, of the "bogie” type, with double wheels in the front and in the back, in general comprising one or more front wheels and one or more rear wheels connected to a rocking beam, and at least a shock absorbing element.
  • This kind of landing gears is frequently used in medium or big aircrafts.
  • the technical problem underlying the present invention is to provide an aeronautical landing gear allowing to overcome the above-mentioned drawbacks with reference to the known art.
  • a landing gear as above specified, characterized in that the rocking arm ends of the shock absorbing element which are distal to the wheels are articulated on a lever element hinged on the aircraft frame, onto which means for rotating said lever element acts between a position wherein the wheels have an operative configuration and a position wherein the wheels are retracted within the landing gear bay.
  • figure 1 is a perspective view of a landing gear according to the invention.
  • figure 2 is a side view of the landing gear of figure 1 , showing both the operative configuration of the landing gear and its retracted position.
  • an aeronautical landing gear is overall shown with 1. It is of the so-called “bogie” type, and accordingly it has a pair of wheels, front 2 and i rear 3, connected by a beam 4.
  • the landing gear 1 has a single front wheel 2 and a single rear wheel 3, placed on the same side of the beam 4 and rotatably connected thereto at a respective hub 5.
  • each wheel 2, 3 will be provided with a suitable tire 6.
  • the wheels 2, 3 and the beam 4 are connected to the suspended masses of the aircraft by means of a rocking arm 7, which is rotatably connected to the beam 4 on a first hinge 8 substantially at the center of the beam 4.
  • the distal end 9 of the rocking arm 7 is instead articulated to a lever element 10, in turn hinged to the suspended mass with respect to the wheels 2, 3, i.e. the aircraft frame.
  • the linkage between the wheels 2, 3 and the suspended mass is also realized by a shock absorbing element 11 , of the oleo-pneumatic kind.
  • shock absorbing element 11 is connected to the rocking arm 7 on a second hinge 12 placed substantially next to said first hinge 8, in this example.
  • the other end 13 of the shock absorbing element 11 is instead articulated on said lever element 10.
  • said first hinge and the end of the lever element onto which the rocking arm 7 is articulated are oriented towards the front or the bow of the aircraft.
  • Non The lever element 10 is articulated with the aircraft frame at a front end thereof onto which urges the articulated joint of the rocking arm 7 on a single poking position 14.
  • the shock absorbing element 11 is then connected to the lever element 10 on the other opposed end.
  • the lever element 10, the shock absorbing element 11 and the rocking arm 7 realize an articulate triangle forming the linkage between the suspended masses, i.e. the aircraft, and the beam 4 with the wheels 2, 3.
  • the triangle Since such triangle would be undeformable if it were made of rigid elements, it comprises the shock absorbing element 11 which is capable of absorbing kinetic energy during landing, after contact between wheels 2, 3 and ground. Therefore, the triangle buckles by varying the length of the shock absorbing element 11.
  • lever element 10 means for rotating said lever element 10 acts between a position wherein the wheels 2, 3 are in an operative configuration and a position wherein the wheels 2, 3 are retracted in the landing gear bay, not shown.
  • the means for rotating is overall shown with 15.
  • the means 15 is articulated on the lever element 10 at an extension 16 thereof, placed next to the articulated joint of the shock absorbing element 11.
  • the means 15 is formed by an articulated arm 17 comprising a first portion 18 and a second portion 19 articulated by means of a cardanic element, said first portion 18 being connected to the lever element 10 and said second portion 19 being connected to the aircraft frame.
  • the retraction of the actuator 20 causes the rotation of the second portion 19, dragging up the first portion 18, the lever element 10 and the whole triangle to which it belongs.
  • the landing gear 1 is retracted, moving towards the front of the aircraft, lying on a vertical plane disposed along the aircraft advancing direction.
  • the dimensions of the landing gear depends principally on the dimensions of the shock absorbing element 11 and of the lever element 10, thus obtaining a considerable reduction of the overall dimensions inside the aircraft.
  • the wheels 2, 3 When the actuator 20 extends, the wheels 2, 3 are brought down until they reach an operative configuration. In this position, the shock absorbing element 11 is already placed in an optimal position in order to bear loads during landing, and no further supporting and strengthening elements are thus required, thus limiting the overall weight of the landing gear 1.
  • active and passive means for assuring the correct positioning and the locking of the landing gear 1 and the locking thereof in the landing configuration, as well as means for locking the landing gear when the aircraft is on the ground so as to avoid an erroneous retraction in the landing gear bay are provided.
  • the articulated arm 17 and the maneuver actuator 20 further extend frontally from the lever element, relative to the aircraft frame, thus without affecting the dimensions of the landing gear 1.
  • the landing gear 1 has a hydraulic control device of the pitch angle 22 (pitch trimmer) placed on the front portion of the beam 4 and connected to the aircraft frame.
  • the landing gear 1 has stopping means 23 of the landing gear of the aircraft, normally installed on the aircraft's fuselage, where the landing gear is retracted in the bay.
  • the rocking arm 7 is provided with a projecting pin 24 apt to cooperate with a hooking system 25, that could be hydraulically or mechanically unhooked by means of an apposite leverage.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Transmission Devices (AREA)
  • Braking Arrangements (AREA)
  • Valve Device For Special Equipments (AREA)
  • Valve-Gear Or Valve Arrangements (AREA)
  • Gear Transmission (AREA)
  • Handcart (AREA)
  • Stored Programmes (AREA)
  • Arrangement Or Mounting Of Propulsion Units For Vehicles (AREA)
  • Air Bags (AREA)

Abstract

A bogie-type landing gear (1) for aircrafts allows a remarkable weight and size reduction and comprises: one or more front wheels (2) and one or more rear wheels (3) connected to a beam (4), a rocking arm (7) centrally and rotatably connected to said beam (4), and a shock absorbing element (11), wherein the rocking arm ends (7) and of the shock absorbing element (11 ) which are distal to the wheels (2, 3) are articulated on a lever element (10) hinged on the aircraft frame, onto which means for rotating (15) said lever element (10) urges between a position wherein the wheels (2, 3) are in an operative configuration and a position wherein the wheels (2, 3) are retracted in the landing gear bay.

Description

LANDING GEAR
Description
The present invention refers to an landing gear for aircrafts, of the "bogie" type, with double wheels in the front and in the back, in general comprising one or more front wheels and one or more rear wheels connected to a rocking beam, and at least a shock absorbing element.
This kind of landing gears is frequently used in medium or big aircrafts.
Similar landing gears are known, but they are quite heavy and requires wide installation spaces for their structure and the system for retracting them in the nacelle.
Therefore, these two factors limits the use of this kind of landing gears, as these factors influence the vehicle performances.
The technical problem underlying the present invention is to provide an aeronautical landing gear allowing to overcome the above-mentioned drawbacks with reference to the known art.
Such problem is solved by a landing gear as above specified, characterized in that the rocking arm ends of the shock absorbing element which are distal to the wheels are articulated on a lever element hinged on the aircraft frame, onto which means for rotating said lever element acts between a position wherein the wheels have an operative configuration and a position wherein the wheels are retracted within the landing gear bay.
The use of the above-mentioned structure allows remarkable weight and dimensions reductions.
A preferred exemplificative embodiment of such landing gear will be hereby described, only as a non-limiting example, with reference to the annexed figures, wherein
* figure 1 is a perspective view of a landing gear according to the invention; and
* figure 2 is a side view of the landing gear of figure 1 , showing both the operative configuration of the landing gear and its retracted position.
With reference to figures 1 and 2, an aeronautical landing gear is overall shown with 1. It is of the so-called "bogie" type, and accordingly it has a pair of wheels, front 2 and i rear 3, connected by a beam 4.
In the present exemplificative embodiment, the landing gear 1 has a single front wheel 2 and a single rear wheel 3, placed on the same side of the beam 4 and rotatably connected thereto at a respective hub 5.
Moreover, it is intended that each wheel 2, 3 will be provided with a suitable tire 6.
The wheels 2, 3 and the beam 4 are connected to the suspended masses of the aircraft by means of a rocking arm 7, which is rotatably connected to the beam 4 on a first hinge 8 substantially at the center of the beam 4.
The distal end 9 of the rocking arm 7 is instead articulated to a lever element 10, in turn hinged to the suspended mass with respect to the wheels 2, 3, i.e. the aircraft frame.
The linkage between the wheels 2, 3 and the suspended mass is also realized by a shock absorbing element 11 , of the oleo-pneumatic kind.
In particular, the shock absorbing element 11 is connected to the rocking arm 7 on a second hinge 12 placed substantially next to said first hinge 8, in this example.
The other end 13 of the shock absorbing element 11 is instead articulated on said lever element 10.
The latter is placed according to the aircraft advancing direction during takeoff and landing. In particular, said first hinge and the end of the lever element onto which the rocking arm 7 is articulated are oriented towards the front or the bow of the aircraft.
Non The lever element 10 is articulated with the aircraft frame at a front end thereof onto which urges the articulated joint of the rocking arm 7 on a single poking position 14.
The shock absorbing element 11 is then connected to the lever element 10 on the other opposed end. The lever element 10, the shock absorbing element 11 and the rocking arm 7 realize an articulate triangle forming the linkage between the suspended masses, i.e. the aircraft, and the beam 4 with the wheels 2, 3.
Since such triangle would be undeformable if it were made of rigid elements, it comprises the shock absorbing element 11 which is capable of absorbing kinetic energy during landing, after contact between wheels 2, 3 and ground. Therefore, the triangle buckles by varying the length of the shock absorbing element 11.
On the lever element 10 means for rotating said lever element 10 acts between a position wherein the wheels 2, 3 are in an operative configuration and a position wherein the wheels 2, 3 are retracted in the landing gear bay, not shown. The means for rotating is overall shown with 15.
The means 15 is articulated on the lever element 10 at an extension 16 thereof, placed next to the articulated joint of the shock absorbing element 11. The means 15 is formed by an articulated arm 17 comprising a first portion 18 and a second portion 19 articulated by means of a cardanic element, said first portion 18 being connected to the lever element 10 and said second portion 19 being connected to the aircraft frame.
On the second portion 19 there is connected a maneuver hydraulic jack 20 at an intermediate articulated joint 21.
The retraction of the actuator 20 causes the rotation of the second portion 19, dragging up the first portion 18, the lever element 10 and the whole triangle to which it belongs.
In such way, the landing gear 1 is retracted, moving towards the front of the aircraft, lying on a vertical plane disposed along the aircraft advancing direction.
The dimensions of the landing gear depends principally on the dimensions of the shock absorbing element 11 and of the lever element 10, thus obtaining a considerable reduction of the overall dimensions inside the aircraft.
In figure 2, the retraction angle is highlighted and shown with α.
When the actuator 20 extends, the wheels 2, 3 are brought down until they reach an operative configuration. In this position, the shock absorbing element 11 is already placed in an optimal position in order to bear loads during landing, and no further supporting and strengthening elements are thus required, thus limiting the overall weight of the landing gear 1.
Anyhow, active and passive means for assuring the correct positioning and the locking of the landing gear 1 and the locking thereof in the landing configuration, as well as means for locking the landing gear when the aircraft is on the ground so as to avoid an erroneous retraction in the landing gear bay are provided. The articulated arm 17 and the maneuver actuator 20 further extend frontally from the lever element, relative to the aircraft frame, thus without affecting the dimensions of the landing gear 1.
Moreover, the landing gear 1 has a hydraulic control device of the pitch angle 22 (pitch trimmer) placed on the front portion of the beam 4 and connected to the aircraft frame.
Although per se known in the art, such device performs the function of maintaining in a substantially horizontal and parallel to the runway position the beam 4, even if during landing the aircraft has a positive pitch, which would raise the front wheel 2.
In turn, as the device 22 reaches its complete extension, it is not fed hydraulically anymore.
Moreover, the landing gear 1 has stopping means 23 of the landing gear of the aircraft, normally installed on the aircraft's fuselage, where the landing gear is retracted in the bay.
To this regard, the rocking arm 7 is provided with a projecting pin 24 apt to cooperate with a hooking system 25, that could be hydraulically or mechanically unhooked by means of an apposite leverage.
To the above-described aeronautical landing gear, a person skilled in the art, in order to satisfy further and contingent needs, could effect several further modifications and variants, all however encompassed in the protective scope of the present invention, as defined by the appended claims.

Claims

1. A bogie-type landing gear (1) for aircrafts, comprising: one or more front wheels (2) and one or more rear wheels (3) connected by a beam (4), a rocking arm (7) centrally and rotatably connected to said beam (4), and a shock absorbing element (11), characterized in that the ends (7) of the rocking arm and of the shock absorbing element (11) which are distal to the wheels (2, 3) are articulated on a lever element (10) hinged on the aircraft frame, on which means for rotating (15) said lever element
(10) acts between a position wherein the wheels (2, 3) are in an operative configuration and a position wherein the wheels (2, 3) are retracted in the landing gear bay.
2. Landing gear (1) according to claim 1 , wherein said lever element (10) is articulated to the aircraft frame at a first end thereof onto which the articulated joint of the rocking arm (7) urges on an poking position (14).
3. Landing gear (1) according to claim 2, wherein said lever element (10) is substantially placed along the aircraft advancing direction during landing, said first end being directed towards the bow and the landing gear (1) being of the front retraction type.
4. Landing gear (1) according to claim 3, wherein said shock absorbing element
(11) extends between an end of the lever element (10) opposed to said first end and a articulated joint on said rocking arm (7) next to his articulated joint on said beam (4).
5. Landing gear (1) according to any of the preceding claims, wherein said shock absorbing element (11) is of the cylinder-piston oleo-pneumatic kind.
6. Landing gear (1) according to claim 5, wherein the piston is articulated to the beam (4) and the cylinder is articulated to the lever element (10).
7. Landing gear according to any of the preceding claims, having a single front wheel (2) and a single rear wheel (3), placed on the same side of the beam (4).
8. Landing gear according to any of claims 3 to 7, having a pitch compensator (22) placed on the front portion of the beam (4).
9. Landing gear (1) according to any of claims 2 to 8, wherein the means for rotating (15) said lever element (10) is articulated on the lever element (10) at an extension (16) thereof next to the articulated joint of the shock absorbing element (11).
10. Landing gear (1) according to any of claims 2 to 9, wherein the means for rotating (15) said lever element (10) has an articulated arm (17) comprising a first portion (18) and a second portion (19) articulated head to head, said first portion (18) being connected to the lever element (10) and said second portion (19) being connected al aircraft frame.
11. Landing gear according to claim 10, wherein a retractile actuator (20) is rotatably connected to an intermediate articulated joint (21) on said second portion (19), for determining the rotation of the lever element (10).
PCT/IB2009/050302 2008-01-24 2009-01-26 Landing gear Ceased WO2009093223A2 (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
CA2713135A CA2713135A1 (en) 2008-01-24 2009-01-26 Landing gear
US12/864,371 US20110180662A1 (en) 2008-01-24 2009-01-26 Landing gear
AT09704550T ATE549241T1 (en) 2008-01-24 2009-01-26 LANDING GEAR
EP09704550A EP2247499B1 (en) 2008-01-24 2009-01-26 Landing gear
BRPI0907616-6A BRPI0907616A2 (en) 2008-01-24 2009-01-26 Landing gear gear

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
ITRM2008A000043 2008-01-24
IT000043A ITRM20080043A1 (en) 2008-01-24 2008-01-24 AIRCRAFT CART

Publications (2)

Publication Number Publication Date
WO2009093223A2 true WO2009093223A2 (en) 2009-07-30
WO2009093223A3 WO2009093223A3 (en) 2009-12-10

Family

ID=40290330

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/IB2009/050302 Ceased WO2009093223A2 (en) 2008-01-24 2009-01-26 Landing gear

Country Status (7)

Country Link
US (1) US20110180662A1 (en)
EP (1) EP2247499B1 (en)
AT (1) ATE549241T1 (en)
BR (1) BRPI0907616A2 (en)
CA (1) CA2713135A1 (en)
IT (1) ITRM20080043A1 (en)
WO (1) WO2009093223A2 (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3001708A1 (en) * 2013-02-06 2014-08-08 Eurocopter France Retractable landing gear for e.g. helicopter, has swinging device for angularly raising jack-shock absorber in order to place gear in retracted gear position when jack-shock absorber exceeds retraction threshold of extension stem
EP3375708A1 (en) * 2017-03-17 2018-09-19 Safran Landing Systems UK Limited Aircraft landing gear assembly

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2510412C (en) * 2013-02-04 2021-08-25 Messier Dowty Ltd Aircraft landing gear pitch trimmer actuator with variable damping
CN103523215A (en) * 2013-10-15 2014-01-22 江苏艾锐泰克无人飞行器科技有限公司 Landing assisting wheel of unmanned aerial vehicle
US9321524B2 (en) * 2014-04-22 2016-04-26 Goodrich Corporation Bogie beam articulation mechanism
ES2769269T3 (en) * 2017-03-17 2020-06-25 Safran Landing Systems Uk Ltd Airplane landing gear set
CN116022384A (en) * 2022-09-09 2023-04-28 中国空气动力研究与发展中心空天技术研究所 A retractable undercarriage driven by a worm gear
GB2636135A (en) * 2023-11-30 2025-06-11 Airbus Operations Ltd An aircraft landing gear
CN119527538B (en) * 2024-11-10 2025-11-11 四川沃飞长空科技发展有限公司 Landing gear and aircraft

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB820217A (en) * 1956-05-04 1959-09-16 Electro Hydraulics Ltd Retractable undercarriages for aircraft
FR1212900A (en) * 1958-10-09 1960-03-28 Rech Etudes Production Sarl Retractable landing gear
GB911121A (en) * 1959-02-05 1962-11-21 English Electric Co Ltd Improvements in and relating to aircraft undercarriages
GB1006522A (en) * 1963-10-08 1965-10-06 Electro Hydraulics Ltd Retractable undercarriages for aircraft
US3345019A (en) * 1965-12-30 1967-10-03 Bendix Corp Aircraft landing gear
FR2564418B1 (en) * 1984-05-15 1988-04-22 Messier Hispano Bugatti Sa LANDING GEAR WITH TANDEM WHEELS AND INDEPENDENT SHOCK ABSORBERS
RU2088478C1 (en) * 1995-02-28 1997-08-27 Акционерное общество открытого типа "ОКБ Сухого" Flying vehicle retractable landing gear
ITTO20011121A1 (en) * 2001-11-30 2003-05-30 Agusta Spa CART FOR A HELICOPTER.

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3001708A1 (en) * 2013-02-06 2014-08-08 Eurocopter France Retractable landing gear for e.g. helicopter, has swinging device for angularly raising jack-shock absorber in order to place gear in retracted gear position when jack-shock absorber exceeds retraction threshold of extension stem
EP3375708A1 (en) * 2017-03-17 2018-09-19 Safran Landing Systems UK Limited Aircraft landing gear assembly
US10946952B2 (en) 2017-03-17 2021-03-16 Safran Landing Systems Uk Ltd Aircraft landing gear assembly

Also Published As

Publication number Publication date
US20110180662A1 (en) 2011-07-28
EP2247499A2 (en) 2010-11-10
EP2247499B1 (en) 2012-03-14
WO2009093223A3 (en) 2009-12-10
ATE549241T1 (en) 2012-03-15
CA2713135A1 (en) 2009-07-30
BRPI0907616A2 (en) 2015-07-21
ITRM20080043A1 (en) 2009-07-25

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