INVENT Overview Iden

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    Integrity Service Excellence

    Integrity Service Excellence

    Integrity Service Excellence

    Integrated Vehicle Energy

    Technology (INVENT) Overview

    Changing the Culture through

    Model Based Engineering

    4 May 2012

    IEEE 2012 Annual Meeting

    Cincinnati, Ohio

    STEVEN M. IDENINVENT Program Manager

    Energy / Power / Thermal Division

    Air Force Research Laboratory

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    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 aircraftLimited 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

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    Power & Thermal Management

    Requirements

    P

    ower&T

    hermalR

    equirements

    F-15C, D

    F-15E

    Active Denial

    Laser Fighter

    LRSII

    Time Today

    ~~

    F-16

    Heat Sink: Fuel, Lube, Ram Air,

    Fan Duct, Thermal Energy

    Storage, Expendable?

    Heat Sink: Fuel

    Heat Sink: Ram Air

    & Fuel

    F-22

    F-35 STOVL

    F-35 CTOL, CV

    LRSIII

    kW

    ELLA

    MEA I

    More Electric Aircraft Gen I

    Electric Engine Start

    Electric Primary Flight Control

    PTMS

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    Energy Optimized Aircraft (EOA)

    Energy Efficiency >>>

    Mission Capability >>>

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    AF INVENT Future Vision & GoalsSpirals 1,2, & 3 Capabilities Growth

    Providing Future Warfighter Capabilities

    10% Fuel Savings or Range for 5th

    Gen Tactical, Subsonic Strike, and

    Persistent/ISR (P/ISR)

    2X Ground Hold Time for 5thGen

    Tactical & Strike (120 min Goal)

    4X CAS Low Alt Ops Time for

    Tactical & Strike (120 min Goal)

    +15-20% Power and Thermal

    (P&T) Mission Capability

    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)

    Power & Thermal for High Mach to

    Hypersonic Vehicles

    10X Increased P&T for Hi Duty

    Cycle DEW

    10X P&T Systems Growth for LongEndurance ISR Missions

    INVENT Near-Term

    5thGEN More Electric Aircraft

    INVENT Mid-Term

    Next Gen. Energy Opt. Aircraft

    INVENT Far-Term

    Revolutionary Energy Opt. Aircraft

    F-35

    F-22

    UAV

    Supersonic LRS

    Persistent ISR

    Large Aircraft DEW

    Mobility

    Long Endurance UAV

    High Altitude Airship

    Hypersonic

    Subsonic LRS

    6thGen Fighter/DEW

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    Integrated Vehicle Energy Technology (INVENT)

    The Next System Revolution

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    Integrated Vehicle Energy Technology (INVENT)

    Rapid Model Based Design

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    INVENT Model Requirements

    and Implementation Plan (MRIP)

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    Heat Loads

    Mission Params

    Bay Temps

    Shaft Speed

    Shaft Power

    MachAltitude

    1x10-6 s1x10-7 s

    Simulation Time Step Domain

    Thrust

    Altitude

    Engine Transient Response

    1.0 sec0.1 s0.01 s0.001 s1x10-4 s1x10-5 s

    6-DOF Simulations

    Mission Profile

    HPEAS Transient Response

    Aircraft Maneuver

    Detailed Transient

    Analysis

    REPS

    HPEAS

    Vehicle ElectricalSimulation

    APTMS

    FTMS

    Propulsion

    Prop/Power/

    Thermal Analysis

    Propulsion/ThermalSimulation

    ElectricalDistributed

    HeterogeneousSimulation (DHS)

    VehicleDistributed

    HeterogeneousSimulation (DHS)

    Orders of magnitude differences in required simulations rates

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    Thermal Tip-to-Tail Model

    (Mission Level)

    FTMS

    Engine

    AVS

    PTMS

    Fuel

    Fuel

    Ram Air

    Bleed Air/

    Shaft Power

    Thrust

    FANQ

    LoadQ

    Fuel

    Thrust Command

    Drag

    Fuel Thermal Management

    System (FTMS)

    Fuel mass & temp

    Convection, conduction,

    radiation

    Ram air HX

    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

    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)

    Power Thermal

    Management

    System (PTMS)

    Air cycle or vapor cycle Cold air heat sink Heat sink for PAO loop

    Aircraft Heat Loads

    Actuators

    Cockpit Engine (pumps, bearings, and

    gearbox)

    Avionics (air cooled and liquidcooled)

    Electrical System

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    Electrical Tip-to-Tail Model(Segment Level)

    REPS

    Engine

    AVS

    HPEAS

    Voltage

    Actuation Command

    Thrust

    Shaft

    Speed Thrust Command

    Actuation Feedback

    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.

    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)

    High PerformanceElectrical Actuation

    System (HPEAS)

    (Transient)

    Actuators EMI Circuit

    Aerodynamic Loads

    Shaft

    Torque

    Current

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    Validation throughHardware in the Loop (HIL)

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    Torque

    Simulation

    Spee

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    Command

    Measured

    SpoolSpeed

    Thrust Achieved

    Fuel Burned

    Altitude

    Mach Number

    Thrust Request

    Gen

    Hardware

    Real-TimeSimulator

    6 DoF Airframe

    Dynamics and

    Autopilot Models

    Real-Time Simulator

    Real-Time Turbine

    Engine and FADECModels

    Turbine Emulator

    Drive Stand

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    INVENT Technology

    Demonstration & Validation Strategy

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    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)

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    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

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    Questions?

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