Correct-by-construction Control with Non-asymptotic Learning, Estimation and Detection in-the-Loop
Abstract
Future aircraft will use morphing structures not only to improve aerodynamic efficiency, but also for aircraft stability and control. In order to ensure superiority, maneuverability, and survivability of morphing, tailless aircraft, significant advancements in our fundamental understanding of morphing geometries and their associated effects on aerodynamic forces, moments, and control are needed. The overall hypothesis is that the fundamental relationships between aerodynamics and wing morphology can be exploited to produce adequate longitudinal and lateral control for tailless aircraft. The objectives are as follows: 1. Identify relationships between wing morphing and aerodynamics of tailless aircraft; 2. Characterize the morphing input parameters that produce desired control outputs; 3. Assess the accuracy of the predicted relations using canonical wind-tunnel cases; and 4. Evaluate the control relationships on a full free-body dynamic system. The technical approach will be delineated in four phases: 1) Aerodynamic Modeling: Employ multi-fidelity modeling techniques to predict resulting aerodynamic forces and moments due to wing morphology on tailless aircraft. 2) Control-Methodology Development: Develop a novel reverse-mapping technique to relate the geometric morphing parameters to desired aircraft control. This will produce a type of virtual elevator, aileron, and rudder that can be linked to a traditional autopilot or control system. 3) Model Assessment: Compare model predictions to canonical windtunnel tests to assess the accuracy of the aerodynamic model and controls mapping. 4) Flight Testing and Evaluation: Evaluate the full free-body dynamics and controllability of an aircraft using wing morphology for control through flight simulation and sub-scale airframe flight testing. Outcomes of this work include improved understanding of wing morphology and theassociated control laws for tailless aircraft. This approach will allow the control limits to be tested over a range of scenarios from basic flight to large disturbances and assess the full, free-body dynamics relating the aerodynamics to the aircraft response and controllability. Additional outcomes include improved aerodynamic modeling techniques for morphing aircraft, a novel reverse-mapping control methodology for morphing aircraft that will allow traditional autopilots to be used with future morphing airframes, and a set of canonical test cases that can be used to validate other modeling methods and experimental results. The proposed work will employ a continuous-skin morphing technology developed by an adaptive-structures team at the Air Force Research Lab. This technology has been tested for mechanical and structural performance, and further testing and evaluation is underway on traditional aircraft with straight wings and tails. The proposed work will leverage this morphing technology to identify, characterize, assess, and evaluate fundamental relations between wing morphology and the control of tailless aircraft. Project outcomes will support active and future programs in the Department of Defense, including air-based and submersible craft design, analysis, and control. Fundamental findings will be directly applicable to next-generation fighter aircraft, which will be tailless designs and may use morphing technology for improved efficiency and control with reduced noise and radar signature.
Document Details
- Document Type
- DoD Grant Award
- Publication Date
- Jul 26, 2018
- Source ID
- N000141812502
Entities
People
- Douglas F. Hunsaker
Organizations
- Office of Naval Research
- United States Navy
- Utah State University