Enroute weight computer for aircraft

• US 4,494,210 A
• Filed: 12/21/1981
• Issued: 01/15/1985
• Est. Priority Date: 12/21/1981
• Status: Expired due to Term

• Current Assignee: Honeywell Incorporated (Honeywell International Inc.)
• Original Assignee: Sperry Corporation (Unisys Corporation)
• Inventors: Miller, Harry
• Primary Examiner(s): Krass, Errol A.
• Assistant Examiner(s): Teska, Kevin J.
• Application Number:
  US06/333,097
• Time in Patent Office: 1,121 Days
• Field of Search: 364/424, 364/442, 364/463, 364/567, 364/509, 364/560, 364/564, 364/510, 340/27 R, 340/945, 340/971, 340/973, 340/603, 340/612, 340/618, 340/620, 318/642, 244/194
• US Class Current: 702/175
• CPC Class Codes: G01G 19/07 for weighing aircraft

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.

Claims

1. 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.

2. 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.

3. 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.

4. 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.

5. The apparatus as set forth in claim 4 wherein said accelerometer means comprises a liquid level sensor.

6. 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.

7. 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.