IEEE 2012 Annual Meeting Cincinnati, Ohio

Transcription

1 IEEE 2012 Annual Meeting Cincinnati, Ohio Integrated Vehicle Energy Technology (INVENT) Overview Changing the Culture through Model Based Engineering 4 May 2012 Integrity Service Excellence STEVEN M. IDEN INVENT Program Manager Energy / Power / Thermal Division Air Force Research Laboratory 1

2 Challenge In the Past Aircraft designed for peak power and peak thermal loads Over-design offered future growth potential Optimized based on mass and volume metrics Today 3 to 5 times heat load of legacy aircraft Limited ability to reject heat to environment Increasing secondary power demands On demand peak power for flight controls On demand peak power for engine thrust actuation devices Increased complexity Future Energy efficiency and optimization approaches Dynamic energy picture of the subsystems and vehicle airframe Stored energy converted energy distributed energy dissipated energy Requires new design processes 2

3 Power & Thermal Management Requirements LRSIII Power & Thermal Requirements kw ~ Heat Sink: Fuel, Lube, Ram Air, Fan Duct, Thermal Energy Storage, Expendable? Heat Sink: Fuel F-22 ELLA Active Denial LRSII MEA I F-35 STOVL F-35 CTOL, CV Laser Fighter F-16 F-15C, D F-15E Heat Sink: Ram Air & Fuel More Electric Aircraft Gen I Electric Engine Start Electric Primary Flight Control PTMS Time Today 3

4 Energy Optimized Aircraft (EOA) Energy Efficiency >>> Mission Capability >>> Reduce Demand Change Culture Reduced Fuel Burn Increased Range or Endurance Increased Performance No Thermal Management System Limits on Operations Mega-Watt Class Power & Cooling for Self-Defense Weapons Mission Capable Efficient Systems On-Demand Robust, Adaptive Variable Cycle Engines Advanced Aero Adaptive Versatile Turbine Engine (ADVENT) Highly Efficient Embedded Turbine Engine (HEETE) 4

5 AF INVENT Future Vision & Goals Spirals 1,2, & 3 Capabilities Growth Providing Future Warfighter Capabilities F-35 UAV Large Aircraft DEW Subsonic LRS Long Endurance UAV Mobility Hypersonic F-22 6 th Gen Fighter/DEW Persistent ISR Supersonic LRS High Altitude Airship 10% Fuel Savings or Range for 5 th Gen Tactical, Subsonic Strike, and Persistent/ISR (P/ISR) 2X Ground Hold Time for 5 th Gen Tactical & Strike (120 min Goal) 4X CAS Low Alt Ops Time for Tactical & Strike (120 min Goal) % Power and Thermal (P&T) Mission Capability INVENT Near-Term 5 th GEN More Electric Aircraft 50% Improved Range/Endurance Goal 10% On-Demand Integrated Systems 30% Advanced Engine Cycles (leveraged) 10% Aero Improvements (leveraged) No Thermal Management System (TMS) Restrictions 5X P&T Capacity (MW Class DEW) INVENT Mid-Term Next Gen. Energy Opt. Aircraft Power & Thermal for High Mach to Hypersonic Vehicles 10X Increased P&T for Hi Duty Cycle DEW 10X P&T Systems Growth for Long Endurance ISR Missions INVENT Far-Term Revolutionary Energy Opt. Aircraft 5

6 Integrated Vehicle Energy Technology (INVENT) The Next System Revolution Dynamic Energy Management System Adaptive P &T Management System High Performance Electromechanical Actuation Adaptive Cycle Engine MW-class Power Electrical Accumulator Unit Robust Electrical Power System Adaptive Smart Aircraft Power Systems Model Based Design 6

7 Integrated Vehicle Energy Technology (INVENT) Reduced Energy Demand For steady level flight: Lift=Weight and Thrust=Drag INVENT can reduce energy consumption in three ways: Reduce combined subsystem weight Currently 2x single engine weight Reduce bleed air Reduces the SFC and thrust penalties Reduce engine power extraction Reduces the SFC and thrust penalties 7

8 Integrated Vehicle Energy Technology (INVENT) Rapid Model Based Design The Need: Full Mission Capability Near Mid Far The Solution: Energy Optimized Aircraft Cockpit Simulation Full Mission Capability Verified and Validated Multifidelity Platform Based Toolsets Develop Integrated Subsystems & Models Develop Integrated System Models and Conduct Full System Optimization Iterative Virtual & Real Rapid Design Approach 8

9 INVENT Model Requirements and Implementation Plan (MRIP) Govt./Industry collaboration to establish modeling framework Mission & Segment Interface definitions Losses, heat Interactions Defines fidelity, data stream, and V&V requirements Software documentation requirements Standard for AF, industry and academia MRIP is open for public release Tip-to-Tail Diagram Government, Industry, Academia Collaboration for System-Level Development of Evolving MS&A Toolsets Capabilities 9

10 Need for Time-Accurate Mathematical Models Historically: S-S tabular-based look-up models Goal: Dynamic mathematical models s 1 Tabular data limits scope of possible investigations Steady-state information (neglects transient response between states) Data generated by resources not available to system integrator One architecture/mission/platform Cannot address dynamic controls interactions Develop time-accurate Math Layer mathematical models Improves: Model reusability Variable fidelity options Reconfigurable Multiple architectures/missions/platforms Address controls interactions / on-demand systems Move away from steady-state tabular data to time-accurate models to improve versatility and increase fidelity 10

11 M&S System Integration Challenge Orders of magnitude differences in required simulations rates Two different model fidelities defined (segment / mission) Vehicle Electrical Simulation Electrical Distributed Heterogeneous Simulation (DHS) REPS Heat Loads Mission Params Bay Temps Shaft Speed Shaft Power HPEAS HPEAS Transient Response Altitude Mission Profile Aircraft Maneuver Propulsion/Thermal Simulation Propulsion APTMS Mach Altitude Thrust Engine Transient Response Vehicle Distributed Heterogeneous Simulation (DHS) FTMS Detailed Transient Analysis 6-DOF Simulations Prop/Power/ Thermal Analysis 1x10-7 s 1x10-6 s 1x10-5 s 1x10-4 s s Simulation Time Step Domain 0.01 s 0.1 s 1.0 sec Segment Level Mission-Level 11

12 Fuel Thermal Management System (FTMS) Fuel mass & temp Convection, conduction, radiation Ram air HX Ram Air FTMS Thermal Tip-to-Tail Model (Mission Level) Engine (quasi-steady state) Controls return to tank flow Calculates engine heat loads Calculates net thrust Calculates fuel burn / SFC Interfaces with APTMS supplying bleed air & shaft power Fuel Engine Drag Thrust Command Thrust Aircraft Heat Loads Actuators Cockpit Engine (pumps, bearings, and gearbox) Avionics (air cooled and liquid cooled) Electrical System AVS Power Thermal Management System (PTMS) Air cycle or vapor cycle Cold air heat sink Heat sink for PAO loop Fuel PTMS Q FAN Fuel Bleed Air/ Shaft Power Q Load Air Vehicle System (AVS) 6-DoF to vehicle model Notional Long Range Strike Closed loop control over mission profile (speed, altitude, heading) Track metrics (range, endurance, fuel burn) 12

13 Electrical Tip-to-Tail Model (Segment Level) Robust Electrical Power System (REPS) (Transient) Generator Electrical Distribution Unit Electrical Accumulator Unit Engine (Transient) Calculates thrust Calculates fuel burn / SFC Interfaces with REPS System through shaft power. Shaft Speed Engine Thrust Command Air Vehicle System (AVS) (Transient) 6-DoF to vehicle model Notional Long Range Strike Closed loop control over mission profile (speed, altitude, heading) Track metrics (range, endurance, fuel burn) REPS Shaft Torque Thrust AVS High Performance Electrical Actuation System (HPEAS) (Transient) Actuators EMI Circuit Voltage Current HPEAS Actuation Feedback Actuation Command Aerodynamic Loads 13

14 Validation through Hardware in the Loop (HIL) Real-Time Turbine Engine and FADEC Models Thrust Achieved Fuel Burned 6 DoF Airframe Dynamics and Autopilot Models Actuation Feedback Actuator / Load Model Altitude Actuation Command Mach Number Thrust Request Aerodynamic Loads Real-Time Simulator Real-Time Simulator Real-Time Simulator Simulation Hardware Speed Command Measured Spool Speed Measured Generator Torque Drive Stand Turbine Emulator Gen Vdc ELECTRICAL ACCUMULATOR UNIT Converter Energy Storage Device Vdc Current Command ADVANCED LOAD EMULATOR Converter Measured Bus Voltage Average Power Dissipator Energy Storage Device Ultracapacitocapacitor Ultra- 14

15 2008 Component Dev. INVENT 6.2 INVENT Technology Demonstration & Validation Strategy Develop Models, Hardware, Integrate, Simulate, Test & Validate Subsystem & Dynamic Modeling INVENT 6.2, 6.3 INVENT Ground Demos INVENT 6.3 INVENT Flight Demo INVENT BATTERY ESG 270 VDC MAIN BUS Bi-Directional Converter EMA ACTUATOR P&CE EHA ACTUATOR P&CE IAP ACTUATOR P&CE Robust Electrical Power System ISIF F-35 Derivatives Battery Capacitor Possible solution Adaptive Power & Thermal Management System High Performance Electric Actuation System Integration of Adaptive Cycle Engine Capabilities VAATE Long Range Strike Persistent ISR Mobility Cleared for public For release, Official 88ABW , Use Only 26Aug11 15

16 Future MS&A Needs Desired Future Capabilities IP Protection Improve capability of RSTOOL to plot higher order response surfaces Integrated Configuration Management Physical Modeling Standard Toolboxes exs. 2 phase thermodynamic flow, hydraulic with thermal, others Data Management large data set logging, managing, consistent formats Automated simulation solver selection (speed / accuracy) Ability to capture model uncertainty associated with solver, parameters, and user input (physics modeled) Errors associated with launching Matlab engines Update Simulink Scope to measure point to point (cursor) 16

17 Future MS&A Needs (cont) Desired Future Capabilities (cont) Ability to read AMPL/GMPL files to create linear programs An GAMS format model interpreter is a workable solution Create a solver for mixed integer programs Ability to specify optimality gap for termination of the algorithm Future Modeling, Simulation, and Analysis Needs Distributed simulation capability for non-real time and real time Running segment level electrical models in real time make use of floating point FPGA or GPUs Availability of Jacobian for model reduction 17

18 INVENT is our Nation s Planning and Execution Construct for Energy Optimized Aircraft THE PARTNERSHIP THE MISSION Increase Capability, Performance Integrated Energy Management GE Rolls-Royce Fighter Engine Team Reduce Acquisition Time/Cost Government, Industry, Academia Collaborative Team 18

19 Questions? 19