Integrated Systems Architecture & Stability/Control Considerations in Early Vehicle Design

Transcription

1 Integrated Systems Architecture & Stability/Control Considerations in Early Vehicle Design POC: Dr. Imon Chakraborty Assistant Professor (New Hire, Fall 2018) 1

2 Research Engineer II Aerospace Systems Design Laboratory School of Aerospace Engineering Georgia Institute of Technology (Jan 2016 present) About the Speaker Associate Member AIAA Aircraft Design Technical Committee (Jun 2016 present) Private Pilot (ASEL) (Mar 2013 present) Ph.D., Aerospace Engineering (Dec 2015) Georgia Institute of Technology Advisor: Prof. Dimitri N. Mavris Research Focus M.S., Aerospace Engineering (Jul 2011) Georgia Institute of Technology Advisor: Prof. Panagiotis Tsiotras B.Tech., Mechanical Engineering (May 2009) National Institute of Technology Tiruchirappalli, Tamil Nadu, India Flight Mechanics & Controls Vehicle & Subsystems Sizing & Analysis 2

3 The Design and Control Challenges for Vehicles of the Future These vehicles tend to feature Unconventional configurations Distributed electric propulsion Novel systems architectures Aero/propulsive interactions By no means an exhaustive list! Sizing and design of these concepts is a major challenge The traditional vehicle design methodologies are of limited use Detailed stability and control considerations imperative even in early design stages Volocopter e-volo VC200 EHANG184 AAV Aurora Flight Sciences evtol Lilium Jet Enabling systems architectures need to be accounted for in the early design stages Airbus A 3 Vahana Carter/Mooney SR-C Air Taxi All image sources: LINK 3

4 (A Few) Things to be Done Differently We need a capability to rapidly size, analyze, simulate, and compare novel vehicle configurations and systems architectures in early design phases Can no longer defer certain analyses to later design stages Designing for and analyzing stability, controllability, and flight characteristics Acceptable static and dynamic stability characteristics? Trimmable with suitable control margin? Necessary control authority & maneuverability? Do control schemes provide desirable and easy-to-fly characteristics? Integrated conceptual design stage sizing and performance analysis Physics-based (rather than empirical) sizing of onboard systems (subsystems): estimation of weight, drag, power requirements, etc. More detailed mass properties analyses: center-of-gravity and inertia tensor in addition to mass breakdown to the level of major components Energy-based mission performance analysis: suitable for varying propulsion system architectures conventional, all-electric, or hybrid-electric 4

5 Flight Dynamics, Control, and Flight Simulation MATLAB/Simulink simulation model linked to FlightGear Flight Simulator Simulations can be either synced with clock time or run in batch mode An effective sandbox for testing flight control laws or schemes Model can be linked to a hardware setup for piloted simulations All numbercrunching Rendering & terrain elevation feedback 1.Duca, R., Sarojini, D., Chakraborty, I., Briceno, S., and Mavris, D., Effects of Epistemic Uncertainty on Structural Loads During Dynamic Maneuvers, AIAA SCITECH Forum and Exposition 2018, Kissimmee, FL, January 8-12, 2018, AIAA Chakraborty, I., Lozano, B.G., and Mavris, D.N., Pilot-Friendliness Considerations for Personal Air Vehicle Flight Control Systems, AIAA Aviation 2015 Conference, Dallas, TX, June 22-26, 2015, AIAA

6 Some Past Applications of Flight Simulation Framework Maneuver load analysis What structural loads arise during aircraft maneuvers (e.g., FAR-prescribed)? How sensitive are the predicted loads to sources of uncertainty? Pilot-friendly GA flight control design Analyze the effect of novel flight control laws on pilot workload 2. Chakraborty, I., Lozano, B.G., and Mavris, D.N., Pilot-Friendliness Considerations for Personal Air Vehicle Flight Control Systems, AIAA Aviation 2015 Conference, Dallas, TX, June 22-26, 2015, AIAA ? 1.Duca, R., Sarojini, D., Chakraborty, I., Briceno, S., and Mavris, D., Effects of Epistemic Uncertainty on Structural Loads During Dynamic Maneuvers, AIAA SCITECH Forum and Exposition 2018, Kissimmee, FL, January 8-12, 2018, AIAA Actuation power requirements for hybrid wing-body (HWB) aircraft Multiple large elevons large actuation power requirements How does this vary if the vehicle flies through turbulence? How does it vary with differing control allocation philosophy? 3. Garmendia, D.C., Chakraborty, I., and Mavris, D.N., A Multidisciplinary Approach to Assessing Actuation Power of a Hybrid Wing Body, AIAA Journal of Aircraft, Vol. 53, No. 4, July-August 2016, pp , 6

7 Hardware Setup Possibilities for Simulation Framework A spectrum of hardware setups can be used to complement the software setup Each has its own pros and cons (quality vs. complexity vs. cost) The combined software + hardware setup will yield a flexible simulation environment or framework with multiple research and educational applications Desktop simulation setup for testing Total Energy control for GA aircraft Multi-display simulation setup (proposed) Curved high FOV screen with projection system (proposed) Chakraborty, I., Lozano, B.G., and Mavris, D.N., Pilot-Friendliness Considerations for Personal Air Vehicle Flight Control Systems, AIAA Aviation 2015, Dallas, TX, June 22-26, 2015, AIAA Image: 2/projection-display-solutions/simpit-270-centurion 7

8 Progressive Electrification of Aircraft Subsystems Increasing use of electricity for secondary (non-propulsive) power Some examples of electricity for primary power (propulsive) Many proposed concept designs are enabled by distributed electric propulsion concepts Historical data and heuristics are either unavailable or not applicable in such cases Integrated Subsystems Sizing and Architecture Assessment Capability (ISSAAC) A framework aimed at integrating physics-based sizing and analysis of the aircraft* subsystems with traditional aircraft and engine sizing in early design phases * Generalizing aircraft to flight vehicle is one of the research goals 8

9 Integrated Subsystem Sizing & Architecture Assessment Capability (ISSAAC) Overview of Major Modules 1. Definition of 2. Traditional aircraft & engine sizing (FLOPS & NPSS) 6. Resizing Evaluate combinatorial space of architectures design requirements 3. Candidate subsystem architecture descriptor 4. Subsystem architecture sizing and evaluation (MATLAB) of aircraft & subsystems 5. Design mission performance analysis (FLOPS) 7. Off-design mission performance analysis (FLOPS) 8. Post-processing analysis (MATLAB, Excel, JMP) Decompose net impact into contributions from various systems Assess impact of sources of uncertainty ** Chakraborty, I., Subsystem Architecture Sizing and Analysis for Aircraft Conceptual Design, Ph.D. dissertation, Georgia Institute of Technology, December 2015, 9

10 Modeling & Propagating Impact of Subsystems Architecture Parametric definition of subsystem components if parent components move or re-size, so do associated subsystem components Impacts of subsystems architecture on missionlevel metric (e.g., fuel burn) through multiple causes can be traced ** Chakraborty, I., Subsystem Architecture Sizing and Analysis for Aircraft Conceptual Design, Ph.D. dissertation, Georgia Institute of Technology, December 2015, 10

11 Some Upcoming Tasks, Plans, and Goals Link latest FlightGear version Generalize features that are currently aircraft -specific Set-up hardware and equipment for immersive piloted flight simulation Exercise & test the developed capabilities Upgrade & generalize flight simulation framework Develop & refine energy-based mission performance analysis For conventional, electric, and hybrid propulsion systems, & accounting for secondary power usage Significant planned collaboration with other AU- AE faculty especially w.r.t. aerodynamic analysis Establish hardware setup for flight simulation framework Develop & improve mass properties estimation capabilities Focusing on novel vehicle configurations & subsystems architectures Mass properties, not just mass Application to design & dynamic simulation problem for a novel vehicle concept For example Design of an electric VTOL (e-vtol) or hybrid VTOL On-Demand Mobility (ODM) or Urban Air Mobility (UAM) vehicle concept 11

12 Summary and Future Outlook Advanced vehicle concepts of the future will feature novel configurations as well as novel onboard systems architecture This will necessitate a different approach to the way in which these vehicles are sized, designed, and analyzed Two areas in particular will require significant additional focus in early design More detailed consideration of stability & control and flight characteristics More attention to architecture of various onboard systems This is an exciting research area with wide-ranging collaboration opportunities across multiple domains and addressing society-relevant engineering challenges The capabilities developed will have significant research applications as well as general applicability to classroom instruction Point-of-Contact: Imon Chakraborty, Ph.D., imonchakraborty@gatech.edu 12