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US 7,010,399 B2Granted
Methods and apparatus for fuel control using inertial measurement data
AssigneeThe Boeing Company
InventorKurt A. Rupe
Life of this patent
Estimating the term…
Abstract
Methods and apparatus for fuel control systems using inertial measurement data are disclosed. In one embodiment, a method for controlling a fuel flow includes comparing an acceleration condition of the aircraft with a predetermined threshold at which normal fuel fluid characteristics begin to become unpredictable, and comparing the acceleration condition with a time-based acceleration profile for a given flight profile. Next, the method determines whether the aircraft is about to enter a prolonged negative acceleration regime. The method further includes maintaining normal fuel control and, after a predetermined amount of time has passed, initiating an alternate fuel source to the engine.
Claims31
A method for controlling a fuel flow to an engine of an aircraft, comprising:
- comparing an acceleration condition of the aircraft with a predetermined threshold at which normal fuel fluid characteristics begin to become unpredictable;
- comparing the acceleration condition with a time-based acceleration profile for a given flight profile;
- determining the aircraft is about to enter a prolonged negative acceleration regime;
- maintaining normal fuel control;
- and
- after a predetermined amount of time has passed, initiating an alternate fuel source to the engine.
3 more elements
A method for controlling a fuel flow to an engine of an aircraft, comprising:
- controlling fuel flow in a normal manner;
- determining an acceleration condition of the aircraft;
- comparing the acceleration condition with a predetermined threshold at which normal fuel fluid characteristics begin to become unpredictable;
- comparing the acceleration condition with a time-based acceleration profile for a given flight profile;
- determining the aircraft is about to enter a prolonged negative acceleration regime;
- initiating a counting period while maintaining normal fuel control;
- determining whether the counting period has exceeded a predetermined amount of time;
- and
- when the predetermined amount of time has passed, initiating an alternate fuel source to the engine.
6 more elements
A fuel system for delivering a fuel flow to an engine, comprising:
- a tank member having an interior region adapted to contain a quantity of fuel;
- a pump fluidly coupled to the interior region and adapted to provide a flow of fuel from the tank member through a feed conduit to the engine;
- a sump disposed within the interior region and adapted to provide a first quantity of fuel to the engine via the pump;
- a secondary fuel storage device operatively coupled to the feed conduit and adapted to provide a second quantity of fuel to the engine;
- a pressurized vessel operatively coupled to the tank member and to the secondary fuel storage device and adapted to pressurize each of the tank member and the secondary fuel storage device;
- and
- a control unit operatively coupled to the secondary fuel storage device and to at least one of the pump and the sump, the control unit being adapted to receive input signals from an acceleration measurement device indicative of an acceleration condition of the aircraft, and to output control signals to the secondary fuel storage device and to at least one of the pump and the sump, the control unit further being adapted to perform a method of controlling fuel flow, including:
- comparing the acceleration condition of the aircraft with a predetermined threshold at which normal fuel fluid characteristics begin to become unpredictable;
- comparing the acceleration condition with a time-based acceleration profile for a given flight profile;
- determining the aircraft is about to enter a prolonged negative acceleration regime;
- maintaining a first fuel flow to the engine from the sump using the pump;
- and
- after a predetermined amount of time has passed, initiating a secondary fuel flow from the secondary fuel storage device to the engine.
10 more elements
An aerospace vehicle, comprising:
- a fuselage;
- one or more lifting surfaces operatively coupled to the fuselage;
- at least one engine operatively coupled to the fuselage;
- and
- a fuel system operatively at least partially disposed within the fuselage and operatively coupled to the at least one engine, the fuel system including
- a tank member having an interior region adapted to contain a quantity of fuel;
- a pump fluidly coupled to the interior region and adapted to provide a flow of fuel from the tank member through a feed conduit to the engine;
- a sump disposed within the interior region and adapted to provide a first quantity of fuel to the engine via the pump;
- a secondary fuel storage device operatively coupled to the feed conduit and adapted to provide a second quantity of fuel to the engine;
- a pressurized vessel operatively coupled to the tank member and to the secondary fuel storage device and adapted to pressurize each of the tank member and the secondary fuel storage device;
- and
- a control unit operatively coupled to the secondary fuel storage device and to at least one of the pump and the sump, the control unit being adapted to receive input signals from an acceleration measurement device indicative of an acceleration condition of the aircraft, and to output control signals to the secondary fuel storage device and to at least one of the pump and the sump, the control unit further being adapted to perform a method of controlling fuel flow, including:
- comparing the acceleration condition of the aircraft with a predetermined threshold at which normal fuel fluid characteristics begin to become unpredictable;
- comparing the acceleration condition with a time-based acceleration profile for a given flight profile;
- determining the aircraft is about to enter a prolonged negative acceleration regime;
- maintaining a first fuel flow to the engine from the sump using the pump;
- and
- after a predetermined amount of time has passed, initiating a secondary fuel flow from the secondary fuel storage device to the engine.
15 more elements
Dependencies are inferred from the claim text.