Method and apparatus for aircraft sensor and actuator failure protection using reconfigurable flight control laws

Patent metadata

Field	Value
Publication number	US-9701404-B2
Application number	US-201414321443-A
Country	US
Kind code	B2
Filing date	Jul 1, 2014
Priority date	Oct 3, 2008
Publication date	Jul 11, 2017
Grant date	Jul 11, 2017

Abstract

A method and apparatus for reconfiguring flight control of an aircraft during a failure while the aircraft is flying. The method and apparatus provide a control law that is software-implemented and configured to automatically send flight control data to a mixing/mapping matrix. The method and apparatus also provide a reconfiguration management tool configured to communicate with the mixing/mapping matrix in order to safely transfer authority from a failed actuator to a back-up actuator. The method and apparatus also provide a sensor management tool for providing input to the reconfiguration management tool in order to smooth any transient conditions that may occur during reconfiguration. The method and apparatus provide for a way of smoothing any possible transient situation that might otherwise occur by employment of a fader, the fader being used to gradually convert positioning of failed actuators and positioning of reconfigured actuators. An exemplary aircraft for using the method and apparatus of a reconfigurable flight control system is a quad tilt rotor. The quad tilt rotor provides a variety of redundant and back-actuators, as such, having a robust and highly qualified reconfigurable flight control system is very desirable.

First claim

The invention claimed is:

1. A method of automatically reconfiguring flight control of an aircraft, comprising:
detecting a failure of a yaw control actuator;
calculating a risk factor;
determining whether reconfiguration is necessary based upon the risk factor;
transferring flight control authority from the yaw control actuator to a back-up actuator;
providing a sensor management tool;
generating differential thrust with the back-up actuator for yaw control; and
managing the transfer of flight control authority to the back-up actuators;
wherein the manacling the transfer of flight control authority to the back-up actuator step is accomplished by the sensor management tool.

2. The method according to claim 1 , further comprising:
mixing and mapping the use of the yaw control actuator and the back-up actuator by continuously changing the percentage usage of each actuator on the aircraft.

3. The method according to claim 1 , wherein the risk factor takes into consideration a control power level.

4. A method of automatically reconfiguring flight control of an aircraft, comprising:
detecting a failure of a first actuator;
calculating a risk factor;
seamlessly transferring flight control authority from a failed first actuator to a second actuator;
generating differential thrust with the second actuator for differential control; and
managing the transfer of flight control authority to the second actuators;
wherein the risk factor takes into consideration a control power level.

5. The method according to claim 4 , further comprising:
providing a sensor management tool;
wherein the managing the transfer of flight control authority to the second actuator step is accomplished by the sensor management tool.

6. The method according to claim 4 , further comprising:
mixing and mapping the use of the first actuator and the second actuator by continuously changing the percentage usage of each actuator on the aircraft.

7. The method according to claim 4 , wherein the differential control is utilized for yaw control.

8. The method according to claim 4 , further comprising:
determining whether reconfiguration is necessary based upon the risk factor;
wherein the risk factor is an empirical representation of a control authority of the aircraft, such that a degradation in the control authority effects the risk factor.

Assignees

• Bell Helicopter Textron Inc
• Textron Innovations Inc

Inventors

• Shue Shyhpyng Jack
• Corrigan John James
• Bird Eric Thomas
• Wood Tommie Lynn
• Ewing Alan Carl

Classifications

• G05B2219/24192

  Configurable redundancy · CPC title

• G05D1/0077 Primary

  using redundant signals or controls · CPC title

• B64C19/00

  Aircraft control not otherwise provided for · CPC title

• G05D1/0858

  specially adapted for vertical take-off of aircraft · CPC title

• B64C27/54 Primary

  Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement · CPC title