Uncertainty Quantification for the Actuation Power Requirements of a Hybrid Wing Body Configuration with Electrically Actuated Flight Control Surfaces

摘要

Hybrid Wing Body configurations, such as the N2A-EXTE, have the potential to meet NASA Environmentally Responsible Aviation N+2 goals. These configurations have redundant elevons typically spanning the entire trailing-edge of the wing, whose large areas result in the generation of large hinge moments. To ensure aircraft stability with a reduced static margin, high control surface deflection rates may also be required. The combination of large actuation loads and rates results in significant actuation power requirements, which affect both fuel burn and the sizing of the actuation subsystem. In the early design phases, there is significant uncertainty regarding the magnitude of the actuation power, which may depend on the vehicle's static margin, the design and designated roles of the redundant control surfaces, actuator design parameters, and additionally the intensity of encountered atmospheric turbulence. The objective of this paper is to present a methodical approach for assessing the magnitude of the uncertainty and relating it to aspects of the vehicle and actuation system design. Doing so will facilitate decision-making in early vehicle design. Following the sizing and optimization of electric actuators to meet the actuation requirements of the N2A-EXTE Hybrid Wing Body configuration's control surfaces, the power consumption of these actuators was evaluated under the following scenarios: (1) varying atmospheric turbulence, (2) varying vehicle center of gravity, (3) varying control surface utilization, and (4) varying actuator design parameters.