An aircraft morphable aerodynamic surface structure 110 comprises an elastomeric material 116 having a glass transition temperature, a temperature management system for changing a temperature of (heating or cooling) the elastomeric material, and a controller to control the temperature management system on the basis of a command received at the controller. A heatable material may be used to heat the elastomeric material. The heatable material may comprise particles, such as nanoparticles or carbon nanotubes, dispersed in the elastomeric material. An actuator 114 may actuate a shape change of the aircraft morphable aerodynamic surface structure under control of the controller. A temperature sensor may monitor a temperature of the elastomeric material, and the controller may control the temperature management system on the basis of an output of the temperature sensor. The temperature management system may change a temperature of respective portions of the elastomeric material independently of each other, and the controller may control the temperature management system to change the temperature of the respective portions of the elastomeric material independently of each other.
Aircraft surface structure
18.09.2024
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |
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