US3652040A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Landing gear shock strut
Assignee: Cleveland Pneumatic Tool Co
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Filing: 1970-06-10
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Granted: 1972-03-28
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Expires: 1990-06-10
Abstract
Abstract The wheel-supporting piston of the strut is rotated relative to the cylinder by an adjustable torque arm interconnection of the two to eliminate vertical friction, the adjustment being made by a hydraulic actuator, and a pressure readout of the internal strut pressure provides indication of the vertical weight load on the gear after such friction elimination.
Inventors
- 👤 Erwin H Hartel
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-04 19:18
CPC Classifications
B; B64; B64C; B64C25/00; B64C25/32; B64C25/58; B64C25/60; B64C25/34; B64C2025/345
Claims Analysis
Total Claims: 11
Claim 1
Independent Claim
121 words
In an aircraft landing gear including a cylinder, a wheelsupporting piston movable in the cylinder, bearing means between the cylinder and piston for supporting and guiding the latter in its such movement, seal means sealing the cylinder and piston, and an air-oil spring in the cylinder, the improvement comprising power means for producing relative movement of the cylinder and piston with aircraft weight load imposed on the gear, thereby to eliminate frictional force developed by the bearing means and seal means, and pressure sensitive means for measuring and indicating fluid pressure within the air-oil spring after such relative movement of the cylinder and piston to provide an indication of the vertical weight load on the gear free of such frictional force.
Claim 2
Dependent Claim
121 words
In an aircraft landing gear including a cylinder, a wheelsupporting piston movable in the cylinder, bearing means between the cylinder and piston for supporting and guiding the latter in its such movement, seal means sealing the cylinder and piston, and an air-oil spring in the cylinder, the improvement comprising power means for producing relative movement of the cylinder and piston with aircraft weight load imposed on the gear, thereby to eliminate frictional force developed by the bearing means and seal means, and pressure sensitive means for measuring and indicating fluid pressure within the air-oil spring after such relative movement of the cylinder and piston to provide an indication of the vertical weight load on the gear free of such frictional force.
Claim 3
Dependent Claim
22 words
A landing gear as set forth in claim 1, wherein the power means produces oscillatory relative movement of the cylinder and piston.
Claim 4
Dependent Claim
21 words
A landing gear as set forth in claim 1, wherein the power means produces relative rotation of the cylinder and piston.
Claim 5
Dependent Claim
22 words
A landing gear as set forth in claim 1, wherein the power means produces oscillatory relative rotation of the cylinder and piston.
Claim 6
Dependent Claim
48 words
A landing gear as set forth in claim 1, wherein the power means includes first and second arms having corresponding ends respectively pivotally connected to the cylinder and piston, and means for causing relative angular displacement of said arms to produce relative rotation of the cylinder and piston.
Claim 7
Dependent Claim
47 words
A landing gear as set forth in claim 5, wherein the first and second arms are torque arms the free ends of which are interconnected by pivot means, and the thus interconnected ends are laterally displaced relatively to produce the relative rotation of the cylinder and piston.
Claim 8
Dependent Claim
36 words
A landing gear as set forth in claim 5, wherein the means for causing relative angular displacement of said arms includes a double-acting hydraulic actuator, the relative rotation of the cylinder and piston thereby being oscillatory.
Claim 9
Independent Claim
79 words
The method of weighing an aircraft by measuring vertical load on its landing gear, each including a cylinder and piston and an air-oil spring therebetween, which comprises the steps of causing short stroke relative movement of each cylinder and piston with the aircraft on the ground in the loaded condition to be weighed, with such relative movement effectivE to substantially eliminate vertical friction in the gear, and measuring the spring fluid pressure in the gear after such relative movement.
Claim 10
Independent Claim
79 words
The method of weighing an aircraft by measuring vertical load on its landing gear, each including a cylinder and piston and an air-oil spring therebetween, which comprises the steps of causing short stroke relative movement of each cylinder and piston with the aircraft on the ground in the loaded condition to be weighed, with such relative movement effectivE to substantially eliminate vertical friction in the gear, and measuring the spring fluid pressure in the gear after such relative movement.
Claim 11
Dependent Claim
15 words
The method set forth in claim 8, wherein the relative movement is rotary and oscillatory.
References Cited (Backward Citations)
US2687857A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1975-03-28 | 1975-09-27 | 1976-03-28 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1979-03-28 | 1979-09-27 | 1980-03-28 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1983-03-28 | 1983-09-27 | 1984-03-28 | $7700.00 | Window Closed / Lapsed |