US4494210A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Enroute weight computer for aircraft
Assignee: Honeywell Inc
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Filing: 1981-12-21
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Granted: 1985-01-15
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Expires: 2001-12-21
Abstract
Abstract A measure of the enroute weight of an aircraft is continuously provided by determining the zero fuel weight during takeoff, adding the weight of total fuel as measured by fuel quantity sensors, interrupting the latter measure and holding its then current value whenever the fuel quantity sensors may be in error, such as when the aircraft is not level or during aircraft accelerations, and during this time computing the rate of change of aircraft weight as a function of aerodynamic and engine parameters and subtracting the time integral of this computed value from the held fuel quantity sensor value. Upon the aircraft resuming level, unaccelerated flight, the integrator is reset and the sensed fuel quantity measure restored.
Inventors
- 👤 Harry Miller
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-31 16:05
CPC Classifications
G; G01; G01G; G01G19/00; G01G19/02; G01G19/07
Claims Analysis
Total Claims: 8
Claim 1
Independent Claim
198 words
In an engine powered aircraft, an apparatus for providing a continuous measure of the total in-flight weight comprising: means for supplying a first total in-flight aircraft weight measure dependent upon the sum of zero fuel weight of the aircraft and weight of fuel in fuel tanks as derived from fuel level sensors disposed within said fuel tanks, and means independent of said fuel level sensors for computing and providing a measure of the weight of fuel supplied to the aircraft engines, wherein said independent fuel weight measure providing means comprises: computer means responsive to an engine operation parameter, aircraft speed and aircraft altitude for providing a measure of the rate of fuel flow to said engine, integrator means responsive to said fuel flow measure for providing a measure of the weight of fuel being consumed by said engine, means responsive to aircraft flight conditions, said flight conditions render said fuel level sensors inaccurate, and means responsive to said last-mentioned means for holding said fuel level sensor derived fuel weight measure and for subtracting from said sensor derived measure said computed fuel weight measure to thereby provide a second total in-flight aircraft weight measure during said aircraft flight conditions.
Claim 2
Dependent Claim
198 words
In an engine powered aircraft, an apparatus for providing a continuous measure of the total in-flight weight comprising: means for supplying a first total in-flight aircraft weight measure dependent upon the sum of zero fuel weight of the aircraft and weight of fuel in fuel tanks as derived from fuel level sensors disposed within said fuel tanks, and means independent of said fuel level sensors for computing and providing a measure of the weight of fuel supplied to the aircraft engines, wherein said independent fuel weight measure providing means comprises: computer means responsive to an engine operation parameter, aircraft speed and aircraft altitude for providing a measure of the rate of fuel flow to said engine, integrator means responsive to said fuel flow measure for providing a measure of the weight of fuel being consumed by said engine, means responsive to aircraft flight conditions, said flight conditions render said fuel level sensors inaccurate, and means responsive to said last-mentioned means for holding said fuel level sensor derived fuel weight measure and for subtracting from said sensor derived measure said computed fuel weight measure to thereby provide a second total in-flight aircraft weight measure during said aircraft flight conditions.
Claim 3
Dependent Claim
26 words
The apparatus as set forth in claim 1 wherein said engine operation parameter is the engine's pressure ratio and said aircraft speed is Mach number speed.
Claim 4
Dependent Claim
93 words
The apparatus as set forth in claim 2 wherein said computer means includes: data base means including numerical measures of the rate of fuel flow to the engines as a function of engine EPR, aircraft Mach number and altitude, means for providing a signal representative of engine pressure ratio, means for providing signals representative of aircraft speed and altitude, and means for deriving from said data base and from said signals representative of engine pressure ratio, aircraft speed and altitude, a further signal representative of the rate of fuel flow to said engine.
Claim 5
Dependent Claim
31 words
The apparatus as set forth in claim 1 wherein said aircraft flight condition responsive means includes: accelerometer means for sensing and providing an output measure of aircraft attitude and longitudinal accelerations.
Claim 6
Dependent Claim
17 words
The apparatus as set forth in claim 4 wherein said accelerometer means comprises a liquid level sensor.
Claim 7
Dependent Claim
112 words
The apparatus as set forth in claim 1 or 4 wherein said holding and subtracting means comprises: threshold detector means responsive to said accelerometer means for providing a logic signal having one state upon said accelerometer output measure exceeding a predetermined value, and another state upon said accelerometer output less than said predetermined value, measure holding means responsive to said one state of said logic signal for holding said total fuel weight measure provided by said fuel level sensor means, means also responsive to said one state of said logic signal for initiating the operation of said integrator means, and means for subtracting from said fuel level sensor measure said integrator measure.
Claim 8
Dependent Claim
38 words
The apparatus as set forth in claim 6 further including: further means responsive to the other state of said logic signal for deactivating said holding means and said integrator means and for resetting said integrator measure to zero.
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) | 1988-01-15 | 1988-07-16 | 1989-01-15 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1992-01-15 | 1992-07-16 | 1993-01-15 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1996-01-15 | 1996-07-16 | 1997-01-15 | $7700.00 | Window Closed / Lapsed |