GB542817A - Improvements in aircraft alighting gear - Google Patents

Improvements in aircraft alighting gear

Info

Publication number
GB542817A
GB542817A GB12742/40A GB1274240A GB542817A GB 542817 A GB542817 A GB 542817A GB 12742/40 A GB12742/40 A GB 12742/40A GB 1274240 A GB1274240 A GB 1274240A GB 542817 A GB542817 A GB 542817A
Authority
GB
United Kingdom
Prior art keywords
lever
shock absorber
leg
landing element
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.)
Expired
Application number
GB12742/40A
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.)
Individual
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 GB12742/40A priority Critical patent/GB542817A/en
Publication of GB542817A publication Critical patent/GB542817A/en
Expired 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 
    • B64C25/50—Steerable undercarriages; Shimmy-damping
    • B64C25/505—Shimmy damping
    • 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
    • B64C25/60—Oleo legs

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Vehicle Body Suspensions (AREA)

Abstract

542,817. Aircraft undercarriages. DOWTY, G. H. Aug. 8, 1940, No. 12742. [Class 4] In a component of aircraft alighting gear wherein a landing element, such as a wheel 4, is mounted at the trailing end of a lever 7 pivoted at 6 to the lower end of a leg 1, a telescopic shock absorber 11, highly loadable in a short stroke is pivotally connected at 9 at the trailing end of the lever and similarly connected at its other end to the leg at a point 10 close enough to the pivot 6 of the lever thereon to constrain the shock absorber to swing bodily with a similar movement to that of the lever under landing and taxi-ing loads. The lever 7 carries a lug 8 for mounting the pivot 9 and is also provided with a tapered slot 15 for accommodating the landing element spindle 14 from which the latter can be readily removed on displacement of a closure plate 16 held in position by bolts 17. The downward swinging of the lever 7 may be limited by a stop 12 extending laterally of the lever. Liquid is preferably used as the resilient medium in the shock absorber, the latter being of a type in which the maximum intended loading is achieved within 3 or 4 inches of travel of the plunger with respect to its cylinder. The landing element may be bilaterally mounted by terminating the leg in a bifurcated fork, the lever 7 and shock absorber being duplicated. The component may be retractable and the landing element may comprise a ski, endless track, or a float. Specifications 473,768, 527,111, 533,076 and 537,541 are referred to.
GB12742/40A 1940-08-08 1940-08-08 Improvements in aircraft alighting gear Expired GB542817A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB12742/40A GB542817A (en) 1940-08-08 1940-08-08 Improvements in aircraft alighting gear

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB12742/40A GB542817A (en) 1940-08-08 1940-08-08 Improvements in aircraft alighting gear

Publications (1)

Publication Number Publication Date
GB542817A true GB542817A (en) 1942-01-28

Family

ID=10010270

Family Applications (1)

Application Number Title Priority Date Filing Date
GB12742/40A Expired GB542817A (en) 1940-08-08 1940-08-08 Improvements in aircraft alighting gear

Country Status (1)

Country Link
GB (1) GB542817A (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2416183A (en) * 1942-06-03 1947-02-18 Gen Tire & Rubber Co Aircraft landing gear
US2437219A (en) * 1944-08-05 1948-03-02 American Steel Foundries Shock strut
EP0262591A2 (en) * 1986-09-30 1988-04-06 The Boeing Company Two-stage aircraft landing gear
US4869444A (en) * 1986-09-30 1989-09-26 The Boeing Company Adjustable two-stage aircraft landing gear system

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2416183A (en) * 1942-06-03 1947-02-18 Gen Tire & Rubber Co Aircraft landing gear
US2437219A (en) * 1944-08-05 1948-03-02 American Steel Foundries Shock strut
EP0262591A2 (en) * 1986-09-30 1988-04-06 The Boeing Company Two-stage aircraft landing gear
EP0262591A3 (en) * 1986-09-30 1988-09-07 The Boeing Company Two-stage aircraft landing gear
US4869444A (en) * 1986-09-30 1989-09-26 The Boeing Company Adjustable two-stage aircraft landing gear system

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