Systems and methods for controlling a variable camber flight control system of an aircraft in a cruise flight phase
The disclosed systems and methods for controlling a variable camber (VC) flight control system of an aircraft in a cruise flight phase, comprising: i) in response to a first input from a user, operating the VC flight control system in a first mode, the first mode configured to operate the aircraft according to a passenger comfort goal, by maintaining a deck angle of the aircraft at a low and substantially constant value; and ii) in response to a second input from the user, operating the VC flight control system in a second mode, the second mode configured to operate the aircraft according to an efficiency goal.
1 . A method for controlling a variable camber (VC) flight control system of an aircraft in a cruise flight phase, comprising:
in response to a first input from a user, operating the VC flight control system in a first mode, the first mode configured to operate the aircraft according to a passenger comfort goal, by maintaining a deck angle of the aircraft at a low and substantially constant value; and
in response to a second input from the user, operating the VC flight control system in a second mode, the second mode configured to operate the aircraft according to an efficiency goal,
wherein the user is a passenger of the aircraft and the VC flight control system is accessible by the passenger through a display screen in a fuselage, and wherein a maximum remaining duration of the first mode adjusted depending on a fuel consumption of the aircraft is displayed to the passenger.
2 . The method of claim 1 , wherein in the first mode, the deck angle is selected by the VC flight control system based on predefined deflection values of flaps and ailerons associated with the aircraft.
3 . The method of claim 2 , wherein the predefined deflection values are stored in a look-up table.
4 . The method of claim 1 , wherein the low and substantially constant value of the deck angle is approximately equal to zero.
5 . The method of claim 1 , wherein in the second mode, an angle of attack is computed by the VC flight control system, such that the angle of attack reduces a drag felt by the aircraft, said deck angle being dependent on the angle of attack.
6 . The method of claim 1 , wherein the deck angle in the second mode is a maximum allowable deck angle.
7 . The method of claim 6 , wherein the maximum allowable deck angle is approximately 3°.
8 . The method of claim 1 , wherein the VC flight control system is switchable from the first mode to the second mode only after a predetermined duration.
9 . The method of claim 1 , wherein the VC flight control system is switchable from the second mode to the first mode only after a predetermined duration.
10 . A computer-implemented system configured to perform the method of claim 1 .
11 . A non-transitory computer-readable medium comprising computer-executable instructions that cause a system to execute the method according to claim 1 .