Patent US5167385A successfully refreshed from Google Patents.
US5167385A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Aircraft and system and method for operating thereof
Assignee: Pfister GmbH
•
Filing: 1989-01-30
•
Granted: 1992-12-01
•
Expires: 2009-01-30
Abstract
Abstract An aircraft and a method and system for operating thereof as force/moment sensors integrated in elastic connecting joints of parts and units of the aircraft. The various force/moment components determined by the sensors are processed in order to generate control signals for optimizing the operation of the aircraft.
Inventors
- 👤 Hans W. Hafner
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-31 12:30
CPC Classifications
G; G01; G01L; G01L1/00; G01L1/20; B; B60; B60G; B60G17/00; B60G17/015; B60G17/019; B60T; B60T8/00; B60T8/18; B60T8/1837; B60T8/1856; B60T8/32; B60T8/321; B60T8/325; B64; B64C; B64C19/00; B64C25/00; G05; G05D; G05D1/00; G05D1/0055; G05D1/0066; B60G2300/00; B60G2300/16; B60G2400/00; B60G2400/20; B60G2400/40; B60G2400/41; B60G2400/60; B60G2400/80; B60G2400/82; B60G2400/822; B60G2400/90; B60G2400/922; B60G2800/00; B60G2800/90; B60G2800/92
Claims Analysis
Total Claims: 11
Claim 1
Independent Claim
127 words
An aircraft having a plurality of essentially rigid parts elastically connected with each other, comprising: elastomeric material provided in connecting joints between said rigid parts; at least one sensor integrated in said connecting joints for determining forces and/or moments acting at said connecting joints and for generating signals representing said forces and/or moments, wherein said sensors are integrated in connecting joints between struts of a landing gear of said aircraft and a body of said aircraft, further wherein said sensors are integrated in connecting joints incorporated in said struts, and further wherein said sensors are integrated in connecting joints between support bars of said landing gear of said aircraft and said body of said aircraft, said support bars extending at an oblique angle relative to the horizontal.
Claim 2
Dependent Claim
127 words
An aircraft having a plurality of essentially rigid parts elastically connected with each other, comprising: elastomeric material provided in connecting joints between said rigid parts; at least one sensor integrated in said connecting joints for determining forces and/or moments acting at said connecting joints and for generating signals representing said forces and/or moments, wherein said sensors are integrated in connecting joints between struts of a landing gear of said aircraft and a body of said aircraft, further wherein said sensors are integrated in connecting joints incorporated in said struts, and further wherein said sensors are integrated in connecting joints between support bars of said landing gear of said aircraft and said body of said aircraft, said support bars extending at an oblique angle relative to the horizontal.
Claim 3
Dependent Claim
15 words
The aircraft of claim 1, wherein said connecting joint is incorporated in said support bar.
Claim 4
Dependent Claim
34 words
The aircraft of claim 1, wherein at least one of said sensors is integrated in connecting joints provided between struts of landing gear of said aircraft and wheel support means of said landing gear.
Claim 5
Dependent Claim
24 words
The aircraft of claim 1, wherein said sensors are positioned symmetrically relative to a vertical plane extending through a longitudinal axis of said aircraft.
Claim 6
Independent Claim
163 words
A system for controlling the operation of an aircraft having a plurality of essentially rigid parts elastically connected with each other, comprising: force/moment sensor means integrated in elastic connecting joints between said rigid parts for determining forces and/or moments, respectively, acting at said connecting joints and generating signals representing said forces and/or moments, wherein said force/moment sensors are embedded in elastomeric material in said elastic connecting joints, said elastic connecting joints being incorporated within support elements for supporting a body of said aircraft on landing gear means, wherein at least one of said support elements extends in a vertical direction and at least one of said other support elements extends at an oblique angle relative to said vertical direction; and a system control unit connected to said sensors for having signals of said sensors applied thereto, evaluating and processing said signals and providing output signals for controlling the operation of various units of said aircraft based on said forces/moment measured by said sensors.
Claim 7
Independent Claim
163 words
A system for controlling the operation of an aircraft having a plurality of essentially rigid parts elastically connected with each other, comprising: force/moment sensor means integrated in elastic connecting joints between said rigid parts for determining forces and/or moments, respectively, acting at said connecting joints and generating signals representing said forces and/or moments, wherein said force/moment sensors are embedded in elastomeric material in said elastic connecting joints, said elastic connecting joints being incorporated within support elements for supporting a body of said aircraft on landing gear means, wherein at least one of said support elements extends in a vertical direction and at least one of said other support elements extends at an oblique angle relative to said vertical direction; and a system control unit connected to said sensors for having signals of said sensors applied thereto, evaluating and processing said signals and providing output signals for controlling the operation of various units of said aircraft based on said forces/moment measured by said sensors.
Claim 8
Dependent Claim
33 words
The system of claim 5, wherein at least one of the sensors is integrated in elastic connecting joints between struts of landing gear of the said aircraft and wheel axles supporting said struts.
Claim 9
Dependent Claim
31 words
The system of claim 5, wherein said elastic connecting joints comprise coaxial tubes forming an annular gap therebetween filled with bubblefree elastomeric material in strongly adhesive contact with said force/moment sensors.
Claim 10
Dependent Claim
21 words
The system of claim 7, wherein at least one of said sensors is laterally attached to an exterior of said tubes.
Claim 11
Dependent Claim
16 words
The system of claim 7, wherein at least one sensor is embedded in said elastomeric material.
References Cited (Backward Citations)
US2722587A
Cited
US2992860A
Cited
US3205464A
Cited
US3625053A
Cited
US3805413A
Cited
US3800127A
Cited
US3881670A
Cited
US4004756A
Cited
US4175429A
Cited
US4394999A
Cited
US4312042A
Cited
US4725020A
Cited
US4706902A
Cited
US4536843A
Cited
US4644805A
Cited
US4739666A
Cited
US4703663A
Cited
WO1987002129A1
Cited
US4830399A
Cited
US4648569A
Cited
US4796192A
Cited
US4697768A
Cited
DE3620888A1
Cited
US4869444A
Cited
US4786009A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1995-12-01 | 1996-06-01 | 1996-12-01 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1999-12-01 | 2000-06-01 | 2000-12-01 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2003-12-01 | 2004-06-01 | 2004-12-01 | $7700.00 | Window Closed / Lapsed |