GB191500568A - Improvements in or relating to the Landing Devices of Aeroplanes and Hydro-Aeroplanes. - Google Patents

Improvements in or relating to the Landing Devices of Aeroplanes and Hydro-Aeroplanes.

Info

Publication number
GB191500568A
GB191500568A GB191500568DA GB191500568A GB 191500568 A GB191500568 A GB 191500568A GB 191500568D A GB191500568D A GB 191500568DA GB 191500568 A GB191500568 A GB 191500568A
Authority
GB
United Kingdom
Prior art keywords
cylinder
plunger
oil
piston
air
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
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.)
Vickers Ltd
Original Assignee
Vickers Ltd
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 Vickers Ltd filed Critical Vickers Ltd
Publication of GB191500568A publication Critical patent/GB191500568A/en
Expired legal-status Critical Current

Links

Classifications

    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C25/00Alighting gear
    • B64C25/32Alighting gear characterised by elements which contact the ground or similar surface 
    • B64C25/58Arrangements or adaptations of shock-absorbers or springs
    • B64C25/60Oleo legs

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Actuator (AREA)

Abstract

568. Vickers, Ltd., and Duncan, T. S. Jan. 13. [Cognate Application, 11,664/15.] Pneumatic and hydraulic springs; dashpots.-A device fitted between the wheels, skids, or floats and the framework of an aeroplane in order to absorb the shock of landing comprises two telescopic members enclosing compressed air and oil, the shock being dissipated by further compressing the air and by causing the oil to be forced from one part of the apparatus to the other through gradually diminishing passages. The recoil is also damped and the parts brought gently to rest by fluid friction. Fig. 1 shows one form of the device laid on its side, the left-hand end being normally the lower end. A lower cylinder A containing oil works in an upper compressed-air cylinder C having a plunger B adapted to displace oil from the lower cylinder. The plunger B is tapered so that the annular space through which the oil flows diminishes as the cylinder A rises. An inner casing A<1>, perforated for the passage of oil through it into the cylinder C, guides the cylinder A. The plunger B is hollow and in communication through a hole B<1> with the air space, and a piston D carried by a rod D<1> in the cylinder A works within the plunger B. The rod D<1> is a loose fit in the hole in the plunger, or the plunger may have separate perforations, so that there is always some oil at its lower end which retards the descent of the piston D. Fig. 3 shows a modification in which the plunger B acts as a guide for the upper end of the cylinder A. The plunger is square in crosssection, parallel-sided, and fits a hole in the end of the cylinder A, but tapered flats b<x>, Fig. 5, are cut at the corners so as to leave ports a<x> in the top of the cylinder A. Inclined slots b<1> forming continuations of the flats b<x> are cut in the plunger to allow free flow of the oil at the beginning of the stroke. The piston D, in this case, is formed as an enlargement of the head of the cylinder A and works in a reduced part of the cylinder C. One or more passages d<1> in the piston D ensure a supply of oil beneath the piston. A tube b<2> communicating with the air cylinder through a chamber b<4> and passage B<1> ensures that any oil in the plunger will be blown out on the return stroke. The plunger may be triangular or polygonal, or it may be cylindrical with tapered flats or keyways formed upon it. Instead of forming the fluid passages on the outside of the plunger, they may be formed on a rod projecting into the open lower end of the ram from the base of the cylinder A.
GB191500568D 1915-01-13 1915-01-13 Improvements in or relating to the Landing Devices of Aeroplanes and Hydro-Aeroplanes. Expired GB191500568A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB191500568T 1915-01-13

Publications (1)

Publication Number Publication Date
GB191500568A true GB191500568A (en) 1916-04-13

Family

ID=32648589

Family Applications (1)

Application Number Title Priority Date Filing Date
GB191500568D Expired GB191500568A (en) 1915-01-13 1915-01-13 Improvements in or relating to the Landing Devices of Aeroplanes and Hydro-Aeroplanes.

Country Status (1)

Country Link
GB (1) GB191500568A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4630788A (en) * 1983-11-09 1986-12-23 Messier-Hispano-Bugatti (S.A.) Aircraft landing gear, in particular for helicopters

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4630788A (en) * 1983-11-09 1986-12-23 Messier-Hispano-Bugatti (S.A.) Aircraft landing gear, in particular for helicopters

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