Patent US5299759A successfully refreshed from Google Patents.
US5299759A
Expired / Lapsed
US
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Helicopter turn coordination and heading hold mode control
Assignee: RTX Corp
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Filing: 1992-06-01
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Granted: 1994-04-05
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Expires: 2012-06-01
Abstract
Abstract A mode control (25) controls a helicopter flight control system (21) between a heading hold mode and a turn coordination mode according to switching patterns resembling the natural response of an expert pilot to flight conditions. Helicopter operating parameters (31,30) are detected (31,29) and each parameter's detected value is converted from a crisp value to a fuzzy input (100). A new mode fuzzy output is provided by applying a compositional rule of inference (105) across each fuzzy input and a composite mode selection rule base (110). The new mode fuzzy output is converted into a crisp value (112) which is used to determine whether the flight control system operates in the heading hold mode or the turn coordination mode.
Inventors
- 👤 Porter D. Sherman
- 👤 David H. Hetzler
- 👤 Paul Weisser, Jr.
- 👤 Stuart C. Wright
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-28 07:23
CPC Classifications
G; G05; G05D; G05D1/00; G05D1/08; G05D1/0808; G05D1/0858
Claims Analysis
Total Claims: 16
Claim 1
Independent Claim
208 words
Apparatus for controlling an aircraft flight control system between a turn coordination mode and a heading hold mode, wherein the flight control system provides control surface command signal to the aircraft control surfaces to control the yaw, pitch, roll and lift axes of the aircraft in flight, the apparatus comprising: control means operable by a pilot to provide axis command signals for controlling a given axis of the aircraft; sensing means for sensing a plurality of aircraft operating parameters and for providing operating parameter signals indicative thereof; fuzzification means responsive to some of said axis command signals and some of said operating parameter signals for providing fuzzy input signals indicative thereof; composite mode selection rule base means for providing a composite mode selection signal for each possible combination of said fuzzy input signals; processing means responsive to said composite mode selection rule base means and said fuzzy input signals for providing a new mode fuzzy output signal; defuzzification means responsive to said new mode fuzzy output signal for providing a crisp output signal indicative thereof; and mode selection means responsive to said crisp output signal for selecting either the turn coordination mode or the heading hold mode and for placing the flight control system in said selected mode.
Claim 2
Dependent Claim
208 words
Apparatus for controlling an aircraft flight control system between a turn coordination mode and a heading hold mode, wherein the flight control system provides control surface command signal to the aircraft control surfaces to control the yaw, pitch, roll and lift axes of the aircraft in flight, the apparatus comprising: control means operable by a pilot to provide axis command signals for controlling a given axis of the aircraft; sensing means for sensing a plurality of aircraft operating parameters and for providing operating parameter signals indicative thereof; fuzzification means responsive to some of said axis command signals and some of said operating parameter signals for providing fuzzy input signals indicative thereof; composite mode selection rule base means for providing a composite mode selection signal for each possible combination of said fuzzy input signals; processing means responsive to said composite mode selection rule base means and said fuzzy input signals for providing a new mode fuzzy output signal; defuzzification means responsive to said new mode fuzzy output signal for providing a crisp output signal indicative thereof; and mode selection means responsive to said crisp output signal for selecting either the turn coordination mode or the heading hold mode and for placing the flight control system in said selected mode.
Claim 3
Dependent Claim
17 words
Apparatus according to claim 1 further comprising memory means for storing said composite mode selection rule base.
Claim 4
Dependent Claim
113 words
Apparatus according to claim 2 wherein said fuzzification means comprises: scaling means for applying a scale factor to each of said axis command signals and said operating parameter signals to thereby provide corresponding scaled value signals in relation to discrete segments (u i ) on a normalized scale; membership weight assignment means responsive to said scaled value signals for providing a membership weight (l i ) value at each discrete segment (u i ) on said normalized scale for each of said scaled value signals; and each of said fuzzy input signals thereby being represented as a set of ordered pairs of discrete segments and corresponding membership weights (u i ,l i ).
Claim 5
Dependent Claim
38 words
Apparatus according to claim 3 wherein said defuzzification means comprises means for providing said crisp output signals as the weighted sum of each of said membership weights in excess of a threshold value for each of said segments.
Claim 6
Dependent Claim
33 words
Apparatus according to claim 4 wherein said composite mode selection rule base is generated as a composition of a plurality of mode selection rules each of which represents a suitable mode selection decision.
Claim 7
Dependent Claim
205 words
Apparatus for controlling an aircraft flight control system between a turn coordination mode and a heading hold mode, wherein the flight control system provides control surface command signal to the aircraft control surfaces to control the yaw, pitch, roll and lift axes of the aircraft in flight, the apparatus comprising: control means operable by a pilot to provide axis command signals for controlling a given axis of the aircraft; sensing means for sensing aircraft operating parameters and for providing operating parameter signals indicative thereof; microprocessor means responsive to some of said axis command signals and some of said operating parameter signals, said microprocessor means being operative according to fuzzy logic and including: means for providing fuzzy input signals indicative of fuzzy input values corresponding to said axis command signals and said operating parameter signals; means for providing a composite mode selection signal for each possible combination of said fuzzy input signals; means responsive to said composite mode selection signals and said fuzzy input signals for providing a new mode output signal; and mode selection means responsive to said new mode output signal for selecting either the turn coordination mode or the heading hold mode and for placing the flight control system in said selected mode.
Claim 8
Dependent Claim
205 words
Apparatus for controlling an aircraft flight control system between a turn coordination mode and a heading hold mode, wherein the flight control system provides control surface command signal to the aircraft control surfaces to control the yaw, pitch, roll and lift axes of the aircraft in flight, the apparatus comprising: control means operable by a pilot to provide axis command signals for controlling a given axis of the aircraft; sensing means for sensing aircraft operating parameters and for providing operating parameter signals indicative thereof; microprocessor means responsive to some of said axis command signals and some of said operating parameter signals, said microprocessor means being operative according to fuzzy logic and including: means for providing fuzzy input signals indicative of fuzzy input values corresponding to said axis command signals and said operating parameter signals; means for providing a composite mode selection signal for each possible combination of said fuzzy input signals; means responsive to said composite mode selection signals and said fuzzy input signals for providing a new mode output signal; and mode selection means responsive to said new mode output signal for selecting either the turn coordination mode or the heading hold mode and for placing the flight control system in said selected mode.
Claim 9
Dependent Claim
16 words
Apparatus according to claim 6 further comprising memory means for storing said composite mode selection signals.
Claim 10
Dependent Claim
32 words
Apparatus according to claim 7 wherein said composite mode selection signals are generated as a composition of a plurality of mode selection rules each of which represents a suitable mode selection decision.
Claim 11
Independent Claim
204 words
A method of controlling an aircraft flight control system between a turn coordination mode and a heading hold mode, wherein the flight control system provides control surface command signal to the aircraft control surfaces to control the yaw, pitch, roll and lift axes of the aircraft in flight, the method comprising the steps of: providing axis command signals in response to the operation of pilot operable controls, said axis command signal controlling a given axis of said aircraft; sensing a plurality of aircraft operating parameters and providing operating parameter signals indicative thereof; fuzzifying some of said axis command signals and some of said operating parameter signals for providing fuzzy input signals indicative thereof; providing a composite mode selection signal for each possible combination of said fuzzy input signals; applying a compositional rule of inference to said composite mode selection signals and said fuzzy input signals for providing a new mode fuzzy output signal; defuzzifying said new mode fuzzy output signal for providing a crisp output signal indicative thereof; selecting either the turn coordination mode or the heading hold mode as a flight control system new mode in response to said crisp output signal; and placing the flight control system in said selected new mode.
Claim 12
Independent Claim
204 words
A method of controlling an aircraft flight control system between a turn coordination mode and a heading hold mode, wherein the flight control system provides control surface command signal to the aircraft control surfaces to control the yaw, pitch, roll and lift axes of the aircraft in flight, the method comprising the steps of: providing axis command signals in response to the operation of pilot operable controls, said axis command signal controlling a given axis of said aircraft; sensing a plurality of aircraft operating parameters and providing operating parameter signals indicative thereof; fuzzifying some of said axis command signals and some of said operating parameter signals for providing fuzzy input signals indicative thereof; providing a composite mode selection signal for each possible combination of said fuzzy input signals; applying a compositional rule of inference to said composite mode selection signals and said fuzzy input signals for providing a new mode fuzzy output signal; defuzzifying said new mode fuzzy output signal for providing a crisp output signal indicative thereof; selecting either the turn coordination mode or the heading hold mode as a flight control system new mode in response to said crisp output signal; and placing the flight control system in said selected new mode.
Claim 13
Dependent Claim
53 words
The method of claim 9 wherein said step of providing a composite mode selection signal further comprises the steps of: providing a plurality of mode selection rules each of which represents a suitable mode selection decision; and generating said composite mode selection signals as a composition of said plurality of mode selection rules.
Claim 14
Dependent Claim
29 words
The method of claim 10 further comprising the step of providing a memory means for storing said mode selections signals for each possible combination of said fuzzy input signals.
Claim 15
Dependent Claim
116 words
The method according to claim 11 wherein said step of fuzzifying some of said axis command signals and some of said operating parameter signals further comprises the steps of: applying a scale factor to each of said axis command signals and said operating parameter signals to thereby provide corresponding scaled value signals in relation to discrete segments (u i ) on a normalized scale; assigning a membership weight (l i ) value at each discrete segment (u i ) on said normalized scale for each of said scaled value signals; and representing each of said fuzzy input signals as a set of ordered pairs of discrete segments and corresponding membership weights (u i ,l i ).
Claim 16
Dependent Claim
47 words
The method according to claim 12 wherein said step of defuzzifying said new mode fuzzy output signal comprises the step of providing said crisp output signals as the weighted sum of each of said membership weights in excess of a threshold value for each of said segments.
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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) | 1997-04-04 | 1997-10-04 | 1998-04-05 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 2001-04-04 | 2001-10-04 | 2002-04-05 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2005-04-04 | 2005-10-04 | 2006-04-05 | $7700.00 | Window Closed / Lapsed |