초록 ▼

A method for controlling an aircraft includes the steps of receiving acceleration data related to an acceleration of a front portion of the aircraft, and receiving pitch, roll, and/or yaw rate data related to a rate of a center portion of the aircraft. The method also includes a step of generating a

A method for controlling an aircraft includes the steps of receiving acceleration data related to an acceleration of a front portion of the aircraft, and receiving pitch, roll, and/or yaw rate data related to a rate of a center portion of the aircraft. The method also includes a step of generating a pitch, roll, and/or yaw command based on the acceleration data and on the rate data.

대표청구항 ▼

1. A method for controlling an aircraft, comprising the steps of:receiving first vertical acceleration data related to a vertical acceleration of a front vibration antinode of said aircraft;receiving second vertical acceleration data related to a vertical acceleration of a rear vibration antinode of

1. A method for controlling an aircraft, comprising the steps of:receiving first vertical acceleration data related to a vertical acceleration of a front vibration antinode of said aircraft;receiving second vertical acceleration data related to a vertical acceleration of a rear vibration antinode of said aircraft;receiving pitch rate data related to a pitch rate of a center vibration node of said aircraft; andcomputing a pitch command based on said first and second vertical acceleration data and on said pitch rate data.2. The method of claim 1, wherein said step of computing comprises:filtering signals carrying said first and second vertical acceleration data and said pitch rate data.3. The method of claim 2, wherein said step of filtering comprises filtering frequencies in excess of 10 Hz.4. The method of claim 1, further comprising the step of receiving pitch flight control data, and wherein said step of computing comprises computing said pitch command based on said pitch flight control data.5. A method for controlling an aircraft, comprising the steps of:receiving first horizontal acceleration data related to a horizontal acceleration of a front portion of said aircraft;receiving second horizontal acceleration data related to a horizontal acceleration of a rear portion of said aircraft;receiving roll rate data related to a roll rate of a center portion of said aircraft;receiving yaw rate data related to a yaw rate of a center portion of said aircraft; andcomputing both a roll command and a yaw command based on said first and second horizontal acceleration data, on said roll rate data, and on said yaw rate data.6. The method of claim 5, wherein said step of computing comprises:filtering signals carrying said first and second horizontal acceleration data, said roll rate data, and said yaw rate data.7. The method of claim 6, wherein said filtering comprises filtering frequencies in excess of 10 Hz.8. The method of claim 5, further comprising the step of receiving roll flight control data, and wherein said step of computing comprises computing said roll command based on said roll flight control data.9. The method of claim 5, further comprising the step of receiving yaw flight control data, and wherein said step of computing comprises computing said yaw command based on said yaw flight control data.10. The method of claim 5, further comprising the steps of:receiving first vertical acceleration data related to a vertical acceleration of said front portion of said aircraft;receiving second vertical acceleration data related to a vertical acceleration of said rear portion of said aircraft;receiving pitch rate data related to a pitch rate of said center portion of said aircraft; andcomputing a pitch command based on said first and second vertical acceleration data and on said pitch rate data.11. A method for controlling an aircraft, comprising the steps of:receiving roll, pitch, and yaw flight control data;receiving roll, pitch, and yaw rate data related to roll, pitch, and yaw rates of a center vibration node of said aircraft;receiving vertical acceleration data related to a vertical acceleration of a front vibration antinode of said aircraft and to a vertical acceleration of a rear vibration antinode of said aircraft;receiving horizontal acceleration data related to a horizontal acceleration of said front vibration antinode of said aircraft and to a horizontal acceleration of said rear vibration antinode of said aircraft;computing both a roll command and a yaw command based on said roll and yaw flight control data, on said roll and yaw rate data, on said vertical acceleration data, and on said horizontal acceleration data;computing a picth command based on said pitch flight control data, on said pitch rate data, and on said vertical acceleration data; andactuating control surfaces configured to control roll, pitch, and yaw of said aircraft based on said roll, pitch, and yaw commands.12. The method of claim 11, further comprising the step offiltering signals carrying said roll, pitch, and yaw rate data, said vertical acceleration data, and said horizontal acceleration data.13. The method of claim 11, further comprising the step ofweighing said roll, pitch, and yaw rate data, said vertical acceleration data, and said horizontal acceleration data.14. The method of claim 12, further comprising the step ofweighing said filtered roll, pitch, and yaw rate data, vertical acceleration data, and horizontal acceleration data.15. The method of claim 14, further comprising the step ofphase-controlling said filtered and weighed roll, pitch, and yaw rate data, vertical acceleration data, and horizontal acceleration data.16. The method of claim 15, further comprising the step ofsumming said phase-controlled, filtered, and weighed roll, pitch, and yaw rate data, vertical acceleration data, and horizontal acceleration data.17. The method of claim 11, further comprising the step ofintegrating said roll rate data to derive roll angle information.18. The method of claim 16, further comprising the steps of:integrating said roll rate data to derive roll angle information; andweighing said roll angle information.19. The method of claim 18, wherein the step of summing additionally sums said roll angle information.20. The method of claim 11, wherein said control surfaces include an elevator, ailerons, spoilers, and a rudder.