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US4814993A
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US
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Method and apparatus for the control of fuel consumption in an airplane
Assignee: CENTRALINA LABORATORIA PO SISTEMI ZA UPRAVLENIE
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Filing: 1986-11-26
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Granted: 1989-03-21
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Expires: 2006-11-26
Abstract
Abstract A method for the automatic control of fuel consumption in an airplane, comprises the determination and indication in real time of the specific range of the airplane as a ratio of the ground speed and the fuel flow rate. A maximum specific range is searched and maintained by producing, in the intervals between two subsequent searches of the maximum, control actions for maintaining an angle of attack, which corresponds to the last maximum of the specific range. When the conditions under which the maximum has been found to change, a new maximum is searched. An apparatus for performing the method, comprises transducers of ground speed and fuel flow rate, and a computing microprocessor connected via an output and an interface to a digital indicator as well as to a device for controlling the thrust of the airplane engines.
Inventors
- 👤 Yordan D. Zapryanov
- 👤 Dimcho I. Boyadjiev
- 👤 Desho I. Mladenov
- 👤 Lyudmil K. Mihailov
- 👤 Kiril H. Kolchakov
- 👤 Kostadin B. Botev
- 👤 Anton D. Tzekov
- 👤 Kostadin J. Dinev
- 👤 Michail P. Andronov
- 👤 Kolyo E. Kolev
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-24 04:42
CPC Classifications
G; G05; G05D; G05D1/00; G05D1/0005
Claims Analysis
Total Claims: 9
Claim 1
Independent Claim
115 words
A method for the automatic control of fuel consumption of an airplane during cruise flight, comprising the following steps: measuring ground speed, fuel flow rate, fuel density, air speed, altitude and angle of attack; determining the start of cruise flight using real flight data; interatively incrementing fuel rate and calculating specific range unitl maximum value of specific range is found; storing values of ground speed, altitude and angle of attack at which maximum specific range is found; iteratively measuring ground speed, altitude and angle of attack and maintaining a constant angle of attack by incrementing fuel flow rate; calculating a new maximum specific range only when a change is noted in ground speed or altitude.
Claim 2
Independent Claim
115 words
A method for the automatic control of fuel consumption of an airplane during cruise flight, comprising the following steps: measuring ground speed, fuel flow rate, fuel density, air speed, altitude and angle of attack; determining the start of cruise flight using real flight data; interatively incrementing fuel rate and calculating specific range unitl maximum value of specific range is found; storing values of ground speed, altitude and angle of attack at which maximum specific range is found; iteratively measuring ground speed, altitude and angle of attack and maintaining a constant angle of attack by incrementing fuel flow rate; calculating a new maximum specific range only when a change is noted in ground speed or altitude.
Claim 3
Dependent Claim
20 words
A method as claimed in claim 1 wherein said claculation of maximum specific range is computed by a gradient procedure.
Claim 4
Independent Claim
119 words
An apparatus for the control of fuel consumption in an airplane, comprising a transducer for determining ground speed, a transducer for determining fuel flow rate, a transducer for determining altitude, and a transducer for determining angle of attack; a computing microprocessor and a measuring microprocessor, each connected parallelly with the other and each being connected to an output interface; said transducers providing input for sai dmeasuring microprocessor; and thrust control means for varying fuel flow rate, said output interface being connected to said thrust control means; whereby saic omputing microprocessor computes specific range interatively unitl a maximum specific range is found; and said maximum specific range is recomputed only when a change is noted in ground speed or altitude.
Claim 5
Independent Claim
119 words
An apparatus for the control of fuel consumption in an airplane, comprising a transducer for determining ground speed, a transducer for determining fuel flow rate, a transducer for determining altitude, and a transducer for determining angle of attack; a computing microprocessor and a measuring microprocessor, each connected parallelly with the other and each being connected to an output interface; said transducers providing input for sai dmeasuring microprocessor; and thrust control means for varying fuel flow rate, said output interface being connected to said thrust control means; whereby saic omputing microprocessor computes specific range interatively unitl a maximum specific range is found; and said maximum specific range is recomputed only when a change is noted in ground speed or altitude.
Claim 6
Dependent Claim
43 words
An apparatus as claimed in claim 3, further comprising additional transducers for determining air speed, Mach number, and fuel density, said additional transducers providing additional input for said measuring microprocessor; and a mnemonic indicator and a digital indicator connected to said output interface.
Claim 7
Independent Claim
140 words
An apparatus for the control of fuel consumption in an airplane, comprising means for iteratively measuring ground speed, fuel flow rate, altitude, and angle of attack; means for computing maximum specific range based on ground speed, fuel flow rate, altitude, and angle of attack; said computing means being connected to said measuring means whereby said measuring means provides input for said computing means; means for varying fuel flow rate; said means for varying fuel flow rate being connected to said computing means whereby said means for varying fuel flow rate is controlled by an output of said computing means; whereby said angle of attack is maintained at a constant value by varying fuel flow rate in order to achieve maximum specific range and said maximum specific range is recomputed only when a change is noted in ground speed or altitude.
Claim 8
Independent Claim
140 words
An apparatus for the control of fuel consumption in an airplane, comprising means for iteratively measuring ground speed, fuel flow rate, altitude, and angle of attack; means for computing maximum specific range based on ground speed, fuel flow rate, altitude, and angle of attack; said computing means being connected to said measuring means whereby said measuring means provides input for said computing means; means for varying fuel flow rate; said means for varying fuel flow rate being connected to said computing means whereby said means for varying fuel flow rate is controlled by an output of said computing means; whereby said angle of attack is maintained at a constant value by varying fuel flow rate in order to achieve maximum specific range and said maximum specific range is recomputed only when a change is noted in ground speed or altitude.
Claim 9
Dependent Claim
97 words
An apparatus as claimed in claim 5, further comprising said measuring means further comprising means for measuring air speed, mach number, and fuel density; said measuring means having a memory for storing measured values and said computing means having a memory for storing computed values; a common memory, said measuring means and said computing means being connected to said common memory for exchanging information; whereby said computing means recomputes maximum specific range whenever the difference between values of ground speed or altitude in memory and values measured by said measuring means is greater than a predetermined amount.
References Cited (Backward Citations)
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1992-03-20 | 1992-09-19 | 1993-03-21 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1996-03-20 | 1996-09-19 | 1997-03-21 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2000-03-20 | 2000-09-19 | 2001-03-21 | $7700.00 | Window Closed / Lapsed |