Patent US5374014A successfully refreshed from Google Patents.
US5374014A
Expired / Lapsed
US
⏱️ 0.0 years remaining
System for control of an aerodynamic surface of an aircraft
Assignee: Airbus Operations SAS
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Filing: 1992-12-22
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Granted: 1994-12-20
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Expires: 2012-12-22
Abstract
Abstract System for control of an aerodynamic surface (1) of an aircraft, comprising an intentional actuation member (5) and a hydraulic jack (2) intended to deflect said aerodynamic surface (1). According to the invention, the system comprises means (14) for detecting the difference in pressures prevailing in said jack (2), on either side of the piston (2C) of the latter, and calculation means (11) comprising: a computer delivering values of a coefficient which is a decreasing function of said difference in pressures; and a multiplier receiving an electrical signal (dp) representing a demanded deflection and said coefficient and addressing a first deflection command (C2) formed by the product of said signal and said coefficient to said servovalve.
Inventors
- 👤 Pascal Traverse
- 👤 Xavier Le Tron
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-04 02:26
CPC Classifications
B; B64; B64C; B64C13/00; B64C13/24; B64C13/38; B64C13/50; B64C13/503
Claims Analysis
Total Claims: 16
Claim 1
Independent Claim
203 words
A system for control of an aerodynamic surface (1) of an aircraft, comprising: (a) an intentional actuation member (5) associated with a transducer (6) for delivering an electrical signal (dp) representing a demanded deflection of said aerodynamic surface (1); (b) a hydraulic jack (2) intended to deflect said aerodynamic surface (1) under the control of a servovalve (3) and of a servocontroller (4); (c) means (14) for detecting the difference in pressures (ΔP) prevailing in said jack (2), on either side of the piston (2C) of the latter; and (d) first calculation means receiving said electrical signal (dp) representing a demanded deflection and deriving a deflection command addressed to said servovalve (3), said first calculation means (11) comprising: (i) a computer (18) delivering values of a coefficient (K) which is a decreasing function of said difference in pressures (ΔP); and (ii) a multiplier (19) receiving said electrical signal (dp) representing a demanded deflection and said coefficient (K) and addressing a first deflection command (C2) formed by the product of said signal and said coefficient to said servovalve, said computer (18) calculating the values of said coefficient (K) in real time, as a function of the instantaneous value of said difference in pressures (ΔP).
Claim 2
Independent Claim
203 words
A system for control of an aerodynamic surface (1) of an aircraft, comprising: (a) an intentional actuation member (5) associated with a transducer (6) for delivering an electrical signal (dp) representing a demanded deflection of said aerodynamic surface (1); (b) a hydraulic jack (2) intended to deflect said aerodynamic surface (1) under the control of a servovalve (3) and of a servocontroller (4); (c) means (14) for detecting the difference in pressures (ΔP) prevailing in said jack (2), on either side of the piston (2C) of the latter; and (d) first calculation means receiving said electrical signal (dp) representing a demanded deflection and deriving a deflection command addressed to said servovalve (3), said first calculation means (11) comprising: (i) a computer (18) delivering values of a coefficient (K) which is a decreasing function of said difference in pressures (ΔP); and (ii) a multiplier (19) receiving said electrical signal (dp) representing a demanded deflection and said coefficient (K) and addressing a first deflection command (C2) formed by the product of said signal and said coefficient to said servovalve, said computer (18) calculating the values of said coefficient (K) in real time, as a function of the instantaneous value of said difference in pressures (ΔP).
Claim 3
Dependent Claim
34 words
The system as claimed in claim 1 which also comprises a deflection detector (16) for said aerodynamic surface and deflection limiting means (20) receiving said deflection command and linked to said deflection detector (16).
Claim 4
Dependent Claim
31 words
The system as claimed in claim 1 wherein said first calculation means (11) also comprises a device (17) for averaging said difference in pressures which is addressed to said computer (18).
Claim 5
Dependent Claim
16 words
The system as claimed in claim 1 wherein said computer (18) is of the analog type.
Claim 6
Dependent Claim
16 words
The system as claimed in claim 1 wherein said computer (18) is of the digital type.
Claim 7
Dependent Claim
65 words
The system as claimed in claim 1 which also comprises: (e) second calculation means (8) also receiving said electrical signal (dp) representing a demanded deflection and deriving a second supplementary deflection command (C1) for said aerodynamic surface; and (f) a two-position changeover switch (10) capable of addressing one or the other of said first or second deflection commands (C1 or C2) to said servovalve (3).
Claim 8
Dependent Claim
61 words
The system as claimed in claim 6 wherein said changeover switch (10) addresses said second deflection command (C1) generated by said second calculation means (8) to said servovalve (3), said first deflection command (C2) generated by said first calculation means (11) being addressed to said servovalve by means of said changeover switch only when said second calculation means (8) are defective.
Claim 9
Independent Claim
212 words
A system for control of an aerodynamic surface (1) of an aircraft, comprising: (a) an intentional actuation member (5) associated with a transducer (6) for delivering an electrical signal (dp) representing a demanded deflection of said aerodynamic surface (1); (b) a hydraulic jack (2) intended to deflect said aerodynamic surface (1) under the control of a servovalve (3) and of a servocontroller (4); (c) means (14) for detecting the difference in pressures (ΔP) prevailing in said jack (2), on either side of the piston (2C) of the latter; and (d) first calculation means receiving said electrical signal (dp) representing a demanded deflection and deriving a deflection command addressed to said servovalve (3), said first calculation means (11) comprising: (i) a computer (18) delivering values of a coefficient (K) which is a decreasing function of said difference in pressures (ΔP); and (ii) a multiplier (19) receiving said electrical signal (dp) representing a demanded deflection and said coefficient (K) and addressing a first deflection command (C2) formed by the product of said signal and said coefficient to said servovalve, said computer (18) delivering a fixed value (K1, K2, . . . Kn+1) of said coefficient (K) for each of a few regions subdividing the range of possible variations in said difference in pressures (ΔP).
Claim 10
Independent Claim
212 words
A system for control of an aerodynamic surface (1) of an aircraft, comprising: (a) an intentional actuation member (5) associated with a transducer (6) for delivering an electrical signal (dp) representing a demanded deflection of said aerodynamic surface (1); (b) a hydraulic jack (2) intended to deflect said aerodynamic surface (1) under the control of a servovalve (3) and of a servocontroller (4); (c) means (14) for detecting the difference in pressures (ΔP) prevailing in said jack (2), on either side of the piston (2C) of the latter; and (d) first calculation means receiving said electrical signal (dp) representing a demanded deflection and deriving a deflection command addressed to said servovalve (3), said first calculation means (11) comprising: (i) a computer (18) delivering values of a coefficient (K) which is a decreasing function of said difference in pressures (ΔP); and (ii) a multiplier (19) receiving said electrical signal (dp) representing a demanded deflection and said coefficient (K) and addressing a first deflection command (C2) formed by the product of said signal and said coefficient to said servovalve, said computer (18) delivering a fixed value (K1, K2, . . . Kn+1) of said coefficient (K) for each of a few regions subdividing the range of possible variations in said difference in pressures (ΔP).
Claim 11
Dependent Claim
34 words
The system as claimed in claim 8 which also comprises a deflection detector (16) for said aerodynamic surface and deflection limiting means (20) receiving said deflection command and linked to said deflection detector (16).
Claim 12
Dependent Claim
31 words
The system as claimed in claim 8 wherein said first calculation means (11) also comprise a device (17) for averaging said difference in pressures which is addressed to said computer (18).
Claim 13
Dependent Claim
16 words
The system as claimed in claim 8 wherein said computer (18) is of the analog type.
Claim 14
Dependent Claim
16 words
The system as claimed in claim 8 wherein said computer (18) is of the digital type.
Claim 15
Dependent Claim
65 words
The system as claimed in claim 8 which also comprises: (e) second calculation means (8) also receiving said electrical signal (dp) representing a demanded deflection and deriving a second supplementary deflection command (C1) for said aerodynamic surface; and (f) a two-position changeover switch (10) capable of addressing one or the other of said first or second deflection commands (C1 or C2) to said servovalve (3).
Claim 16
Dependent Claim
61 words
The system as claimed in claim 13 wherein said changeover switch (10) addresses said second deflection command (C1) generated by said second calculation means (8) to said servovalve (3), said first deflection command (C2) generated by said first calculation means (11) being addressed to said servovalve by means of said changeover switch only when said second calculation means (8) are defective.
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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) | 1997-12-19 | 1998-06-20 | 1998-12-20 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 2001-12-19 | 2002-06-20 | 2002-12-20 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2005-12-19 | 2006-06-20 | 2006-12-20 | $7700.00 | Window Closed / Lapsed |