Patent US4597548A successfully refreshed from Google Patents.
US4597548A
Expired / Lapsed
US
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Shock absorbing struts for aircraft landing gear
Assignee: Woodward HRT Inc
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Filing: 1983-06-17
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Granted: 1986-07-01
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Expires: 2003-06-17
Abstract
Abstract Shock absorbing struts for use on aircraft landing gear which include a pair of fluid containing chambers defined by a pair of telescoping cylinders. Fluid flows from one of the chambers to another through a metering orifice proportional to the differential in pressure generated by impact loads created upon landing or taxiing of the aircraft. Upon the differential pressure exceeding a predetermined threshold level an additional flow path positioned in parallel to the metering orifice is opened by an amount proportional to the amount of differential pressure in excess of the threshold to thereby maintain a substantially constant load on the landing gear irrespective of impact loads imparted thereto.
Inventors
- 👤 Raymond A. Bergloff
- 👤 James T. Hollis
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-08 16:42
CPC Classifications
B; B64; B64C; B64C25/00; B64C25/32; B64C25/58; B64C25/60
Claims Analysis
Total Claims: 6
Claim 1
Independent Claim
193 words
A shock absorbing airplane landing gear strut comprising: a first fluid containing chamber; a second fluid containing chamber; a ground contacting member; means for connecting said first and second chambers between the body of said airplane and said ground contacting member; means for varying the volume of at least one of said chambers responsive to loads applied to said ground contacting member on landing or taxiing of said airplane; first fluid flow path means connected between said chambers including a first orifice therein, second fluid flow path means connected between said chambers in parallel with said first path and including a second orifice therein; means for varying the area of at least one said orifices including a spool valve normally blocking said at least one orifice, responsive to the magnitude of said load exceeding a predetermined threshold; means for sensing the pressure in one of said chambers; and means connected to said pressure sensing means for producing a signal responsive to said load exceeding said threshold for moving said spool valve to open said orifice, the area of the other of said orifices being independently varied responsive to loads applied to said strut.
Claim 2
Dependent Claim
193 words
A shock absorbing airplane landing gear strut comprising: a first fluid containing chamber; a second fluid containing chamber; a ground contacting member; means for connecting said first and second chambers between the body of said airplane and said ground contacting member; means for varying the volume of at least one of said chambers responsive to loads applied to said ground contacting member on landing or taxiing of said airplane; first fluid flow path means connected between said chambers including a first orifice therein, second fluid flow path means connected between said chambers in parallel with said first path and including a second orifice therein; means for varying the area of at least one said orifices including a spool valve normally blocking said at least one orifice, responsive to the magnitude of said load exceeding a predetermined threshold; means for sensing the pressure in one of said chambers; and means connected to said pressure sensing means for producing a signal responsive to said load exceeding said threshold for moving said spool valve to open said orifice, the area of the other of said orifices being independently varied responsive to loads applied to said strut.
Claim 3
Dependent Claim
205 words
A shock absorbing airplane landing gear strut comprising: a first fluid containing chamber; a second fluid containing chamber; a ground contacting member; means for connecting said first and second chambers between the body of said airplane and said ground contacting member; means for varying the volume of at least one of said chambers responsive to loads applied to said ground contacting member on landing or taxiing of said airplane; first fluid flow path means connected between said chambers including a first orifice therein; second fluid flow path means connected between said chambers in parallel with said first path and including a second orifice therein; and spool valve means for varying the area of at least one of said orifices including means for producing an electrical signal responsive to the magnitude of said load exceeding a predetermined threshold; an electrohydraulic servovalve; a separate source of input signals for said electrohydraulic servovalve; means for applying said separate source of signals to said electrohydraulic servovalve, said input signals in combination with said electrical signal positioning said electrohydraulic servovalve to in turn position said spool valve to open said at least one orifice by an amount proportional to the amount said pressure in said one chamber exceeds said threshold.
Claim 4
Dependent Claim
205 words
A shock absorbing airplane landing gear strut comprising: a first fluid containing chamber; a second fluid containing chamber; a ground contacting member; means for connecting said first and second chambers between the body of said airplane and said ground contacting member; means for varying the volume of at least one of said chambers responsive to loads applied to said ground contacting member on landing or taxiing of said airplane; first fluid flow path means connected between said chambers including a first orifice therein; second fluid flow path means connected between said chambers in parallel with said first path and including a second orifice therein; and spool valve means for varying the area of at least one of said orifices including means for producing an electrical signal responsive to the magnitude of said load exceeding a predetermined threshold; an electrohydraulic servovalve; a separate source of input signals for said electrohydraulic servovalve; means for applying said separate source of signals to said electrohydraulic servovalve, said input signals in combination with said electrical signal positioning said electrohydraulic servovalve to in turn position said spool valve to open said at least one orifice by an amount proportional to the amount said pressure in said one chamber exceeds said threshold.
Claim 5
Dependent Claim
51 words
The strut as defined in claim 2 wherein said electrohydraulic servovalve is inactive in the absence of said electrical signal from said pressure sensing means and said spool valve includes spring means biasing said spool valve to a position to close said one orifice in the absence of said electrical signal.
Claim 6
Dependent Claim
41 words
The strut as defined in claim 3 wherein said spool valve is disposed to be insensitive to inertial forces generated by said load and thereby remaining in a position to close said one orifice except when said electrical signal is generated.
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USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1989-06-30 | 1989-12-30 | 1990-07-01 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1993-06-30 | 1993-12-30 | 1994-07-01 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1997-06-30 | 1997-12-30 | 1998-07-01 | $7700.00 | Window Closed / Lapsed |