US4488235A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Speed control system for aircraft
Assignee: Honeywell Inc
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Filing: 1981-11-03
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Granted: 1984-12-11
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Expires: 2001-11-03
Abstract
Abstract Speed control apparatus for use in an aircraft performance management system of the type wherein a target Mach number command is supplied to the aircraft pitch controls to attain the target Mach and is simultaneously supplied to the aircraft throttles to capture a computed engine pressure ratio (EPR) or fan speed (N 1 ), said apparatus being operative during maximum thrust climbs and minimum thrust descents upon an abrupt step function target Mach number command wherein said step function command is converted to a ramp command, the slope of which is directly proportional to the existing thrust-minus-drag conditions of the aircraft and inversely proportional to its existing weight, thus ensuring a proper division between aircraft acceleration and rate of climb or aircraft deceleration and rate of descent.
Inventors
- 👤 Harry Miller
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-01 00:24
CPC Classifications
G; G05; G05D; G05D1/00; G05D1/04; G05D1/06; G05D1/0607; G05D1/0615; G05D1/0638; G05D1/0653
Claims Analysis
Total Claims: 15
Claim 1
Independent Claim
115 words
Speed command apparatus for aircraft having an automatic throttle control system for controlling the thrust imparted to said aircraft by the aircraft engines and an automatic flight control system for controlling the aircraft pitch attitude, said apparatus comprising: (a) means for providing a command signal corresponding to an aircraft speed change from an existing value to a commanded value, (b) means responsive to said command signal for providing a ramp signal (c) means for supplying said ramp signal to said automatic flight control system for changing the aircraft pitch attitude in accordance therewith, and (d) means for controlling the slope of said ramp signal in accordance with the potential flight path angle of said aircraft.
Claim 2
Dependent Claim
115 words
Speed command apparatus for aircraft having an automatic throttle control system for controlling the thrust imparted to said aircraft by the aircraft engines and an automatic flight control system for controlling the aircraft pitch attitude, said apparatus comprising: (a) means for providing a command signal corresponding to an aircraft speed change from an existing value to a commanded value, (b) means responsive to said command signal for providing a ramp signal (c) means for supplying said ramp signal to said automatic flight control system for changing the aircraft pitch attitude in accordance therewith, and (d) means for controlling the slope of said ramp signal in accordance with the potential flight path angle of said aircraft.
Claim 3
Dependent Claim
18 words
The apparatus as set forth in claim 1 wherein said command signal is sustantially a step function command.
Claim 4
Dependent Claim
33 words
The apparatus as set forth in claim 1 further including: means for controlling said automatic throttle control system in accordance with a signal corresponding to a limit thrust condition of the aircraft engines.
Claim 5
Dependent Claim
33 words
The apparatus as set forth in claim 3 wherein said limit thrust signal corresponds to a maximum thrust limit for said engines and wherein said speed command signal requires an increase in speed.
Claim 6
Dependent Claim
33 words
The apparatus as set forth in claim 3 wherein said limit thrust signal corresponds to a minimum thrust limit for said engines and wherein said speed command signal requires a decrease in speed.
Claim 7
Independent Claim
64 words
The apparatus as set forth in any one of said claims 1 through 5 further including: (a) means for providing a signal corresponding to the actual speed of the aircraft, (b) means responsive to said actual speed signal and said ramp signal for providing a resultant speed error signal, and (c) means for supplying said speed error signal to said automatic flight control system.
Claim 8
Dependent Claim
52 words
The apparatus as set forth in claim 6 further including: (a) means responsive to said actual speed signal for supplying a signal corresponding to the rate of change thereof, and (b) means for supplying said speed error and said rate of change of actual speed signal to said automatic flight control system.
Claim 9
Dependent Claim
87 words
The apparatus as set forth in claim 1 wherein said ramp slope controlling means comprises: (a) means for providing a signal corresponding to the longitudinal acceleration of said aircraft, (b) means for providing a signal corresponding to the vertical acceleration of the aircraft, (c) means for providing a signal corresponding to the angle of attack of the aircraft, and (d) means responsive to said last mentioned signals for providing a signal corresponding to the difference between the thrust minus drag divided by the weight of said aircraft.
Claim 10
Dependent Claim
184 words
Speed command apparatus for aircraft having an automatic throttle control system for controlling the thrust imparted to said aircraft by the aircraft engines and an automatic flight control system for controlling the aircraft pitch attitude, said apparatus comprising: means for providing a command signal corresponding to an aircraft speed change from an existing value to a commanded value, means responsive to said command signal for providing a ramp signal, means for supplying to said automatic flight control system for changing the aircraft pitch attitude in accordance therewith, and means for controlling the slope of said ramp signal in accordance with the potential flight path angle of said aircraft, said ramp slope controlling means further comprising: (a) means for providing a signal corresponding to the thrust imparted to said aircraft by said engines, (b) means for providing a signal corresponding to the drag of the aircraft, (c) means for providing a signal corresponding to the weight of the aircraft, and (d) means for providing a ramp slope control signal corresponding to the difference between said thrust and the drag signals divided by said weight signal.
Claim 11
Dependent Claim
184 words
Speed command apparatus for aircraft having an automatic throttle control system for controlling the thrust imparted to said aircraft by the aircraft engines and an automatic flight control system for controlling the aircraft pitch attitude, said apparatus comprising: means for providing a command signal corresponding to an aircraft speed change from an existing value to a commanded value, means responsive to said command signal for providing a ramp signal, means for supplying to said automatic flight control system for changing the aircraft pitch attitude in accordance therewith, and means for controlling the slope of said ramp signal in accordance with the potential flight path angle of said aircraft, said ramp slope controlling means further comprising: (a) means for providing a signal corresponding to the thrust imparted to said aircraft by said engines, (b) means for providing a signal corresponding to the drag of the aircraft, (c) means for providing a signal corresponding to the weight of the aircraft, and (d) means for providing a ramp slope control signal corresponding to the difference between said thrust and the drag signals divided by said weight signal.
Claim 12
Dependent Claim
143 words
Speed command apparatus for aircraft having an automatic throttle control system for controlling the thrust imparted to the aircraft by the aircraft engines and an automatic flight control system for controlling the aircraft pitch attitude, said apparatus comprising: (a) means for providing a substantially step function speed command signal corresponding to an aircraft speed change from an existing speed value to a commanded value, and (b) means for supplying said command signal speed to said automatic flight control system for changing the aircraft pitch attitude in accordance therewith to thereby change the aircraft speed, said command signal speed supplying means comprising (i) means for converting said substantially step function speed command signal to a ramp function having a slope proportional to the potential flight path angle of said aircraft whereby to control the acceleration of said aircraft in capturing said commanded speed value.
Claim 13
Dependent Claim
143 words
Speed command apparatus for aircraft having an automatic throttle control system for controlling the thrust imparted to the aircraft by the aircraft engines and an automatic flight control system for controlling the aircraft pitch attitude, said apparatus comprising: (a) means for providing a substantially step function speed command signal corresponding to an aircraft speed change from an existing speed value to a commanded value, and (b) means for supplying said command signal speed to said automatic flight control system for changing the aircraft pitch attitude in accordance therewith to thereby change the aircraft speed, said command signal speed supplying means comprising (i) means for converting said substantially step function speed command signal to a ramp function having a slope proportional to the potential flight path angle of said aircraft whereby to control the acceleration of said aircraft in capturing said commanded speed value.
Claim 14
Dependent Claim
82 words
The apparatus as set forth in claim 10 wherein said converting means includes: (a) means for providing a signal corresponding to the thrust imparted to said aircraft by said engines, (b) means for providing a signal corresponding to the drag of the aircraft, (c) means for providing a signal corresponding to the weight of the aircraft, and (d) means for providing a ramp slope control signal corresponding to the difference between said thrust and the drag signals divided by said weight signal.
Claim 15
Dependent Claim
87 words
The apparatus as set forth in claim 10 wherein said ramp slope controlling means comprises: (a) means for providing a signal corresponding to the longitudinal acceleration of said aircraft, (b) means for providing a signal corresponding to the vertical acceleration of the aircraft, (c) means for providing a signal corresponding to the angle of attack of the aircraft, and (d) means responsive to said last mentioned signals for providing a signal corresponding to the difference between the thrust minus drag divided by the weight of said aircraft.
References Cited (Backward Citations)
US3752967A
Cited
US3860800A
Cited
US3967799A
Cited
US4019702A
Cited
US4093158A
Cited
US4357663A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1987-12-11 | 1988-06-11 | 1988-12-11 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1991-12-11 | 1992-06-11 | 1992-12-11 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1995-12-11 | 1996-06-11 | 1996-12-11 | $7700.00 | Window Closed / Lapsed |