EP0403501A4 - Quick change wheel landing gear - Google Patents

Quick change wheel landing gear

Info

Publication number
EP0403501A4
EP0403501A4 EP19890902486 EP89902486A EP0403501A4 EP 0403501 A4 EP0403501 A4 EP 0403501A4 EP 19890902486 EP19890902486 EP 19890902486 EP 89902486 A EP89902486 A EP 89902486A EP 0403501 A4 EP0403501 A4 EP 0403501A4
Authority
EP
European Patent Office
Prior art keywords
aft
fore
tubes
gear
landing
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Withdrawn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
EP19890902486
Other languages
English (en)
Other versions
EP0403501A1 (de
Inventor
Charles E. Davis
J. Robert Duppstadt
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.)
Bell Helicopter Textron Inc
Original Assignee
Bell Helicopter Textron Inc
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 Bell Helicopter Textron Inc filed Critical Bell Helicopter Textron Inc
Publication of EP0403501A1 publication Critical patent/EP0403501A1/de
Publication of EP0403501A4 publication Critical patent/EP0403501A4/en
Withdrawn legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/02—Undercarriages
    • 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 
    • B64C2025/325—Alighting gear characterised by elements which contact the ground or similar surface  specially adapted for helicopters

Definitions

  • This invention relates to aircraft landing gear systems and, in particular, to a quick change wheel landing gear assembly provided as an alternate system for a helicopter having a skid landing gear assembly.
  • helicopter landing gear systems may comprise skids, skis, wheels, or floats.
  • the energy of the shock and stress encountered by the landing gear when it engages the surface may be absorbed by resilient springs, bending rods, torsion bars, air-filled bodies, or various combinations of these shock absorbing devices.
  • the present invention comprises a wheel landing gear assembly designed as a quick change replacement for a skid landing gear assembly on a helicopter.
  • the wheel landing gear assembly attaches to the helicopter at the same structural saddles used for the attaching skid landing gear to the aircraft. Therefore, the present invention provides an alternate wheel landing gear assembly for a helicopter without adding special landing gear support structure other than minor brace and brake fittings.
  • the quick change wheel landing gear assembly provides a ready means for back-fitting existing skid gear helicopters with a wheel landing gear system. Thus, new helicopters can be built without costly and heavy additional structures for mounting an alternate landing gear system.
  • the present invention is designed to preserve many desirable features of a skid landing gear system, including low cost and easy maintenance.
  • a pair of fore and aft longitudinal tubes are attached to a pair of short, spaced-apart cross tubes that are positioned to be mounted on the helicopter structural saddles used to mount the skid landing gear.
  • the longitudinal tubes act as energy absorbers for vertical loads during landing and also act to stabilize the landing gear in the presence of wheel drag loads during flight.
  • the longitudinal tubes are connected together at the forward end for mounting a nose gear thereto.
  • the nose gear is mounted so as to be fully swiveling and it may comprise dual wheels to reduce shimmy.
  • the aft main gear wheels are mounted on cantilever landing gear legs extending laterally from the longitudinal tubes at positions near the aft cross tube.
  • An alternate configuration includes shorter fore and aft tubes, not attached to the rear cross tube, but anchored at the back end to fittings on the main helicopter beams.
  • a full length aft cross tube is used and is stabilized with drag braces from the ends of the fore and aft tubes to near the rear wheels on the cross tube.
  • nose gear loads are absorbed by bending deflection of the fore and aft longitudinal tubes.
  • a resilient spring in the nose gear may be used to absorb energy in conjunction with the deflection of the longitudinal tubes.
  • Landing loads on the aft main gear may be absorbed by resilient springs, bending deflection of the gear legs and the aft cross tube, torsion of the fore and aft longitudinal tubes, or any combination of these actions.
  • the aft main gear springs may be replaced by two aft cross tubes or one cross tube and a drag brace used as a combined bending tube and truss configuration in some operational applications of the landing gear system.
  • FIGURE 1 illustrates the quick change wheel landing gear assembly of the present invention installed on a helicopter
  • FIGURE 2 is a perspective view of the quick change wheel landing gear assembly removed from the helicopter
  • FIGURE 3 is a perspective view of a portion of the present invention showing the elastomeric bearing and support assembly for the aft main landing gear.
  • quick change tricycle landing gear assembly 10 is shown mounted on a helicopter 11.
  • Landing gear assembly 10 is designed to replace a skid landing gear assembly by mounting directly to the structural saddles 12 and 14 used to mount the skid landing gear assembly to the underside of helicopter 11.
  • Landing gear assembly 10 comprises a pair of spaced-apart fore and aft tubes 16 and 18 that extend generally parallel to each other and the longitudinal axis of helicopter 11.
  • Fore and aft tubes 16 and 18 are attached to a pair of short, spaced-apart cross tubes 20 and 22.
  • Fore and aft tubes 16 and 18 and cross tubes 20 and 22 are rigidly connected by means of standard fittings that are well known in the art.
  • a pivot bearing assembly 24 having a generally vertical axis for nose gear 26 to swivel about.
  • Nose gear 26 may be mounted on a trailing arm connected to a spring assembly 25 mounted for rotation about the axis of pivot bearing 24.
  • Spring assembly 25 absorbs vibrations and small deflections of nose gear 26 during taxiing to reduce fatigue loads in the fore and aft tubes 16 and 18.
  • nose gear 26 may comprise dual nose wheels to reduce shimmy of nose gear 26.
  • the aft portion of landing gear assembly 10 comprises main gear wheels 30 and 32 mounted on cantilever landing gear legs 34 and 36.
  • Main gear legs 34 and 36 are mounted on fore and aft tubes 16 and 18, respectively, so as to extend laterally therefrom adjacent the aft cross tube 22.
  • Landing loads on the main gear wheels 30 and 32 may be absorbed by deflection of the gear legs 34 and 36, resilience of springs connecting the gear legs 34 and 36 to the longitudinal tubes 16 and 18, deflection of the aft cross tube 22, torsion of the fore and aft longitudinal tubes 16 and 18, or any combination of these actions.
  • connection bracket 38 is shown connecting fore and aft tube 18 to aft cross tube 22.
  • An elastomeric bearing 40 is mounted on tube 18 aft of cross tube 22 and bracket 38.
  • a cylindrical elastomeric spring 42 may be bonded to the inside surface of bearing 40 and to the outside surface of longitudinal tube 18 inserted into bearing 40.
  • Bearing 40 may include a pair of lugs 46 for mounting aft gear leg 36 thereto.
  • Longitudinal tube 16 includes a similar connection bracket and an elastomeric bearing with lugs for mounting aft gear leg 34 thereto.
  • Landing gear assembly 10 is designed as a quick change replacement for a skid landing gear system on helicopter 11.
  • the cross tubes 20 and 22 of gear assembly 10 are adapted to attach to the same structural saddles 12 and 14 used for attaching the skid landing gear to the underside of helicopter 11.
  • landing gear assembly 10 may include fore and aft longitudinal tubes 16 and 18 being connected at the aft end to the back end fittings on the main helicopter beam in which case, a full length aft cross tube is used and is stabilized with drag braces from the ends of fore and aft tubes 16 and 18.
  • Landing gear assembly 10 is a low cost system that incorporates many of the maintenance free features of a skid landing gear system.
  • landing gear assembly 10 provides a quick means for back-fitting existing skid gear helicopters with a wheel landing gear system without requiring major costly and heavy additional mounting structures, landing gear assembly 10 eliminates the previous weight and cost penalties incurred when providing wheels for helicopters equipped with skid landing systems.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • General Details Of Gearings (AREA)
  • Vibration Prevention Devices (AREA)
  • Tires In General (AREA)
  • Devices For Checking Fares Or Tickets At Control Points (AREA)
  • Arrangement Of Transmissions (AREA)
EP19890902486 1988-12-08 1988-12-08 Quick change wheel landing gear Withdrawn EP0403501A4 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/US1988/004319 WO1990006257A1 (en) 1988-12-08 1988-12-08 Quick change wheel landing gear

Publications (2)

Publication Number Publication Date
EP0403501A1 EP0403501A1 (de) 1990-12-27
EP0403501A4 true EP0403501A4 (en) 1991-05-08

Family

ID=22209028

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19890902486 Withdrawn EP0403501A4 (en) 1988-12-08 1988-12-08 Quick change wheel landing gear

Country Status (9)

Country Link
EP (1) EP0403501A4 (de)
JP (1) JP2767305B2 (de)
KR (1) KR0163950B1 (de)
AR (1) AR245664A1 (de)
BR (1) BR8807883A (de)
CA (1) CA2003186A1 (de)
IL (1) IL92594A (de)
MX (1) MX174284B (de)
WO (1) WO1990006257A1 (de)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19701404C1 (de) * 1997-01-17 1998-02-26 Eurocopter Deutschland Radlandewerk für Hubschrauber

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2108747A (en) * 1935-05-31 1938-02-15 Glover William Gordon Launching and beaching of aircraft
US2396189A (en) * 1943-05-03 1946-03-05 William N Millar Aircraft float
US2582426A (en) 1947-10-18 1952-01-15 Goodrich Co B F Variable rate spring suspension
US2909342A (en) 1954-06-04 1959-10-20 Menasco Mfg Company Landing gear for helicopters
US3144223A (en) * 1962-04-11 1964-08-11 Hiller Aircraft Company Inc Aircraft landing gear
US3520497A (en) 1968-06-05 1970-07-14 Rotorway Inc Framework for a helicopter

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
Conway H. G.: "Landing Gear Design" & Hall Ltd., London, U. K., 37 Essex street *

Also Published As

Publication number Publication date
KR0163950B1 (ko) 1998-12-01
JP2767305B2 (ja) 1998-06-18
EP0403501A1 (de) 1990-12-27
AR245664A1 (es) 1994-02-28
CA2003186A1 (en) 1990-06-08
IL92594A (en) 1992-08-18
KR900009392A (ko) 1990-07-04
IL92594A0 (en) 1990-08-31
MX174284B (es) 1994-05-03
BR8807883A (pt) 1990-11-27
WO1990006257A1 (en) 1990-06-14
JPH03503148A (ja) 1991-07-18

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