In an embodiment, a method for aircraft weight estimation is provided that includes determining a weight signal based on a dynamic pressure signal, a calibrated angle of attack signal, a lift coefficient signal, a load factor signal, and a wing surface area. In another embodiment, a method to estima
In an embodiment, a method for aircraft weight estimation is provided that includes determining a weight signal based on a dynamic pressure signal, a calibrated angle of attack signal, a lift coefficient signal, a load factor signal, and a wing surface area. In another embodiment, a method to estimate aircraft weight is provided that includes determining a weight based on historical flight data relating horizontal control surface position to dynamic pressure. In another embodiment, a system for continuously estimating aircraft weight during flight is provided that includes a pitot-static subsystem, an angle of attack indicator, an accelerometer, a controller configured to provide a weight signal, and a signal filter for filtering the weight signal to determine a stable aircraft weight.
대표청구항▼
1. A method for aircraft weight estimation, comprising: providing a dynamic pressure signal from a pitot-static subsystem;determining a calibrated angle of attack signal from an angle of attack indicator;determining a lift coefficient signal based on the calibrated angle of attack signal and a Mach
1. A method for aircraft weight estimation, comprising: providing a dynamic pressure signal from a pitot-static subsystem;determining a calibrated angle of attack signal from an angle of attack indicator;determining a lift coefficient signal based on the calibrated angle of attack signal and a Mach number;providing a load factor signal from an accelerometer; anddetermining a weight signal based on the dynamic pressure signal, the calibrated angle of attack signal, the lift coefficient signal, the load factor signal, and a wing surface area. 2. The method of claim 1, wherein determining the lift coefficient is further based on a flap position. 3. The method of claim 1, further comprising determining a time-averaged weight signal by averaging the weight signal over time. 4. The method of claim 1, further comprising updating the lift coefficient based on one or more lookup tables. 5. A method for aircraft weight estimation, comprising: measuring a horizontal control surface position with a sensor;providing a dynamic pressure from a pitot-static subsystem;determining a weight using historical flight data relating the horizontal control surface position to the dynamic pressure based on aircraft weight; andrepeating continuously during flight the steps of measuring the horizontal control surface position, providing the dynamic pressure, and determining the weight to provide a weight signal. 6. The method of claim 5, further comprising filtering the weight signal by averaging the weight over time. 7. The method of claim 5, further comprising determining an airspeed based on the dynamic pressure signal. 8. The method of claim 7, further comprising determining a Mach number based on the airspeed and a temperature measured with a temperature sensing device. 9. The method of claim 8, further comprising updating the weight based on the Mach number and an air density measured using the pitot-static subsystem. 10. The method of claim 9, further comprising determining a center of gravity based on the weight signal and an amount of fuel onboard the aircraft. 11. The method of claim 10, further comprising updating the weight signal based on the center of gravity. 12. A system for continuously estimating aircraft weight during flight, comprising: a pitot-static subsystem for providing a dynamic pressure signal;an angle of attack indicator for providing a calibrated angle of attack signal;an accelerometer for providing a load factor signal;a controller configured to provide a weight signal based on an initial weight, the dynamic pressure signal, the calibrated angle of attack signal, and the load factor signal; anda signal filter for filtering the weight signal to determine a stable aircraft weight. 13. The system of claim 12, further comprising a flap indicator to sense a flap position for updating the lift coefficient. 14. The system of claim 12, further comprising a lift-coefficient-slope lookup table for determining the lift coefficient based on the calibrated angle of attack signal. 15. The system of claim 12, further comprising an airspeed indicator for providing airspeed based on the dynamic pressure signal. 16. The system of claim 15, further comprising a zero-degree angle-of-attack lift coefficient lookup table for determining the lift coefficient based on airspeed. 17. The system of claim 12, further comprising a control surface sensor for sensing a control surface position and a trim table based on historical flight data relating the control surface position to the dynamic pressure signal for a range of weights.
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이 특허에 인용된 특허 (7)
McIntyre Melville D. W. (Bellevue WA) Sebring David L. (Snohomish WA), Integrated fault-tolerant air data inertial reference system.
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