Modeling and Control for Turboelectric Aircraft

Transcription

1 Modeling and Control for Turboelectric Aircraft Aidan Dowdle NASA GRC AS&ASTAR Fellow 11/1/17 This material is based upon work supported by the National Aeronautics and Space Administration under Grant No. NNX17AB22H issued through the NASA Education through NASA Aeronautics Graduate Scholarship activity. Any opinions, findings, and conclusions or recommendations expressed in this thesis are those of the authors and do not necessarily reflect the views of the National Aeronautics and Space Administration.

2 Research Objective Many proposed conceptual designs (e.g. STARC-ABL) However, various electric propulsion architectures possible (1) All Electric (1) Turboelectric (1) Series Hybrid Electric (1) Objective: use modeling and systems-level analysis to study the capabilities of these architectures

3 Modeling Research Activities LEARN Project - Propulsion Architecture Assessment S.M. Thesis - Requirements Analysis via Dynamics and Control Center-Based Research Experience

4 Modeling Research Activities LEARN Project - Propulsion Architecture Assessment S.M. Thesis - Requirements Analysis via Dynamics and Control Center-Based Research Experience

5 LEARN Project Joint effort between MIT, USC, and Aurora Flight Sciences PI: Professor Edward Greitzer Assessing propulsion systems using Multi-Disciplinary Optimization (MDO) Airframe Electrical Mechanical Thermal Management System Specific type of MDO used is Geometric Programming (2)

6 Electrical Components Modeled Airframe Electrical Battery Power Cables PMBLDC Machines Power Electronics Circuit Protection Mechanical Thermal Management System

7 Ex.: Cable Model

8 Ex.: Integrated Electrical System 600 V vs. 7 kv system for 1 MW power delivery Battery Cable

9 Modeling Research Activities LEARN Project - Propulsion Architecture Assessment S.M. Thesis - Requirements Analysis via Dynamics and Control Center-Based Research Experience

10 Requirements Analysis Flight Path σ x, σ y, σ z Current location Velocity Angle-of-Attack Environment (e.g. wind gusts) Human Pilot

11 Requirements Analysis Prior analysis would not account for coupling Can take them into account using plant model & covariance analysis Thesis advised by Dr. Marija Ilic (3) Flight Path σ x, σ y, σ z Current location Velocity Angle-of-Attack Environment (e.g. wind gusts) Human Pilot

12 Aircraft Under Study Medium-sized (~150,000 lbs), tube-and-wing, turboelectric aircraft v Plane Trajectory Horizon State variables: v velocity α angle-of-attack θ pitch angle q pitch rate Control inputs: δ t throttle δ e elevator States evolve nonlinearly, e.g.

13 Incorporating Electric Components A turbine & generator powers the propulsor Parameters J motor inertia Ω nominal rotor speed δ ሶ rotor speed deviation f total motor damping P m - mechanical power P e - electrical power Fuel Fan Turbine Engine Generator AC/AC Converter Motor

14 Example Applications Disturbance response Sensor bandwidth requirements -3 db Bandwidth

15 Modeling Research Activities LEARN - Propulsion Architecture Assessment S.M. Thesis - Requirements Analysis via Dynamics and Control Center-Based Research Experience

16 Center-Based Research Experience NASA Glenn Research Center Aurora Flight Sciences (4) evtol (4) Solar (4)

17 Summary Research activities supported by NASA Glenn Research Center Geometric programming (LEARN) Electrical component modeling Sensitivity studies on propulsion architectures Requirements Analysis via Dynamics (S.M. Thesis (3) ) Take into account coupling between subsystems to perform a mission Created disturbance environment and tested control design Center-based research experience at NASA GRC & AFS

18 References [1] James L. Felder, NASA Glenn Research Center, NASA Hybrid Electric Propulsion Systems Structures, presentation to the Committee on Propulsion and Energy Systems to Reduce Commercial Aviation Carbon Emissions on September 1, 2015 [2] E. Burnell and W. Hoburg, GPKit software for geometric programming, , Version [3] A. Dowdle, A Requirements Analysis Methodology for Turboelectric Aircraft, S.M. dissertation, Dept. of Elec. Eng. and Comp. Sci., Massachusetts Institute of Technology, Cambridge, MA, [4] Aurora Flight Sciences Programs.