Methods and systems for deploying adjacent trailing edge flaps
Systems and methods for deploying adjacent trailing edge flaps that are part of different flap assemblies of different stiffnesses are disclosed. An exemplary method comprises: deploying a first flap of a first flap assembly having a first stiffness by a first deployment amount and deploying a second flap adjacent the first flap by a second deployment amount where the deployment amount of the first flap part of the flap assembly of lower stiffness is greater than the second deployment amount of the second flap part of the flap assembly of higher stiffness. The difference in deployment amounts may be adapted to improve continuity between the first flap and the second flap when the first and second flaps are deployed and subjected to an aerodynamic load.
1 . A trailing edge flap system for an aircraft wing, the trailing edge flap system comprising:
a double-slotted flap movably coupled to a structure of the aircraft wing, the double-slotted flap having an outboard edge and a first stiffness;
a single-slotted flap movably coupled to the structure of the aircraft wing and having a second stiffness, the first stiffness being lower than the second stiffness, the single-slotted flap being disposed outboard of the double-slotted flap and adjacent the double-slotted flap, the single-slotted flap having an inboard edge, the inboard edge of the single-slotted flap being substantially parallel to the outboard edge of the double-slotted flap when the double-slotted flap and the single-slotted flap are retracted; and
one or more computers operatively coupled to an actuator of the double-slotted flap and to an actuator of the single-slotted flap, the one or more computers being configured to generate one or more outputs causing a commanded deployment of the double-slotted flap via the actuator of the double-slotted flap to a first deployment amount, and a commanded deployment of the single-slotted flap via the actuator of the single-slotted flap to a second deployment amount, where the first deployment amount is greater than the second deployment amount,
wherein a difference in commanded deployment between the commanded deployment of the double-slotted flap and the commanded deployment of the single-slotted flap at least partially compensates for the lower stiffness of the double-slotted flap and a greater deflection of the double-slotted flap to improve spanwise continuity between the double-slotted flap and the single-slotted flap when the double-slotted flap and the single-slotted flap are deployed and subjected to an aerodynamic load.
2 . The system as defined in claim 1 , wherein a first trailing edge portion of the aircraft wing defined by the double-slotted flap is non-parallel to a second trailing edge portion of the aircraft wing defined by the single-slotted flap.
3 . The system as defined in claim 1 , wherein the single-slotted flap is configured for generally streamwise deployment relative to the aircraft wing.
4 . The system as defined in claim 1 , comprising:
one or more first tracks for guiding a deployment of the double-slotted flap; and
one or more second tracks for guiding the deployment of the single-slotted flap, the one or more first tracks and the one or more second tracks being at least partially embedded in the double-slotted flap and in the single-slotted flap respectively.
5 . The system as defined in claim 1 , wherein the double-slotted flap is part of a first flap assembly having a first stiffness and the single-slotted flap is part of a second flap assembly having a second stiffness, the first stiffness of the first flap assembly being lower than the second stiffness of the second flap assembly.
6 . An aircraft comprising the system as defined in claim 1 .