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 a wing of an aircraft, the system comprising:
a first flap assembly including a first flap movably coupled to a structure of the aircraft wing, the first flap assembly having a first stiffness, the first flap assembly being configured to guide the first flap to a first deployed position based on a flap deployment command; and
a second flap assembly including a second flap movably coupled to the structure of the aircraft wing, the second flap being disposed adjacent the first flap, the 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, the second flap assembly being configured to guide the second flap to a second deployed position based on the flap deployment command, the first deployed position of the first flap being adapted to compensate for an expected deflection of the first flap assembly under an aerodynamic load to improve continuity between the first flap and the second flap when the first flap and the second flap are deployed based on the flap deployment command.
2. The system as defined in claim 1 , wherein the first deployment position of the first flap is adapted to compensate for different expected deflections of the first flap assembly and of the second flap assembly.
3. The system as defined in claim 1 , wherein the first flap is double-slotted and second flap is single-slotted.
4. The system as defined in claim 1 , wherein the first flap is disposed inboard of the second flap relative to the aircraft wing.
5. The system as defined in claim 4 , wherein an outboard edge of the first flap and an inboard edge of the second flap are substantially parallel when the first flap and the second flap are substantially retracted.
6. The system as defined in claim 1 , wherein a first trailing edge portion of the aircraft wing defined by the first flap is non-parallel to a second trailing edge portion of the aircraft wing defined by the second flap.
7. The system as defined in claim 1 , wherein the second flap is configured for generally streamwise deployment relative to the aircraft wing.
8. The system as defined in claim 1 , wherein:
the first flap assembly comprises one or more first tracks for guiding the deployment of the first flap; and
the second flap assembly comprises one or more second tracks for guiding the deployment of the second flap, the one or more first tracks and the one or more second tracks being at least partially embedded in the first flap and second flap respectively.
9. An aircraft comprising the system as defined in claim 1 .
10. A method for deploying adjacent trailing edge flaps movably coupled to an aircraft wing during flight where the adjacent trailing edge flaps are part of different flap assemblies having different stiffnesses, the method comprising:
deploying a first flap of a first flap assembly having a first stiffness to a first deployed position in response to a flap deployment command; and
deploying a second flap adjacent the first flap to a second deployed position in response to the flap deployment command, the second flap being 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 and the first deployed position of the first flap being adapted to compensate for an expected deflection of the first flap assembly under an aerodynamic load to improve continuity between the first flap and the second flap when the first flap and the second flap are deployed in response to the flap deployment command.
11. The method as defined in claim 10 , wherein the first deployment position of the first flap is adapted to compensate for different expected deflections of the first flap assembly and of the second flap assembly.
12. The method as defined in claim 10 , wherein the first flap is double-slotted and second flap is single-slotted.
13. The method as defined in claim 10 , wherein the first flap is disposed inboard of the second flap relative to the aircraft wing.
14. The method as defined in claim 13 , wherein an outboard edge of the first flap and an inboard edge of the second flap are substantially parallel when the first flap and the second flap are substantially retracted.
15. The method as defined in claim 10 , wherein a first trailing edge portion of the aircraft wing defined by the first flap is non-parallel to a second trailing edge portion of the aircraft wing defined by the second flap.
16. The method as defined in claim 10 , comprising deploying the second flap in a generally streamwise direction relative to the aircraft wing.
17. The method as defined in claim 10 , comprising determining the first deployment position of the first flap based on an operating parameter of the aircraft.
18. The method as defined in claim 10 , comprising determining the first deployment position of the first flap based on an airspeed of the aircraft.