1 INVENT ―Tip-to-Tail‖ Energy/Engine/Power/Thermal Modeling, Simulation, & Analysis (MS&A) Capabilities and Vision Mitch Wolff, Ph.D. Scientific Advisor for INVENT AFRL/RZPE Wright Patterson Air Force Base 5 th Annual Research Consortium for Multidisciplinary System Design Workshop Boston, MA 29-30 June 2010
This document is posted to help you gain knowledge. Please leave a comment to let me know what you think about it! Share it to your friends and learn new things together.
Transcript
1
INVENT ―Tip-to-Tail‖
Energy/Engine/Power/Thermal
Modeling, Simulation, & Analysis (MS&A)Capabilities and Vision
Mitch Wolff, Ph.D.
Scientific Advisor for INVENT
AFRL/RZPE
Wright Patterson Air Force Base
5th Annual
Research Consortium for
Multidisciplinary System Design
Workshop
Boston, MA
29-30 June 2010
2
Introduction
Modern survivable military aircraft
• 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 (controls, # components, integration, power density, power transfer, …)
Cleared for Public Release , USAF AFRL/RZ, RZ09-0609, 8 Dec 09
Requires new design processes
3
Power & Thermal Management
RequirementsP
ow
er
& T
herm
al
Req
uir
em
en
ts
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
Cleared for Public Release , USAF AFRL/RZ, RZ09-0609, 8 Dec 09
4
Challenges
• Modern / future aircraft are designed for optimal
subsystem mass & volume
– Limited range & endurance
– Vehicle operations impact due to thermal limitations
– Power compatibility issues for actuation & sensors
• Vehicle level system assessment and optimization
requires complex highly integrated models at a
Vehicle System level to design & verify
– Conventional ―cut & try‖ approach can add significant costs
and delays
– System-level hardware ground and flight demonstrations
are required to validate integrated modeling approaches
Cleared for Public Release , USAF AFRL/RZ, RZ09-0609, 8 Dec 09
Vehicle Design
Challenges
Analysis and
Optimization
Challenges
5
Energy Optimized Aircraft
(EOA)
• Must account for ―entire‖ energy
picture
• Multi-role military aircraft must have
flexibility to support emerging
capabilities– Trade between energy consumption and
flexibility (minimum complexity)
– Must provide provisions for growth by
establishing near-, mid-, and far-term
aircraft-level goals
Cleared for Public Release , USAF AFRL/RZ, RZ09-0609, 8 Dec 09
Definition EOA: an aircraft that is optimized for broad capabilities
while maximizing energy utilization (aircraft and ground support)
with the minimum complexity system architecture.
6
What ―Challenge‖?
Energy
Utilization
It’s all just
crazy talk…It’s
an ELEPHANT!!It’s a solid
material
problem!!
It’s a fluid
problem!!It’s a system
problem!!
There is
no heat
sink…
It’s a
thermophysics
problem??!!
Cleared for Public Release , USAF AFRL/RZ, RZ09-0609, 8 Dec 09
7
Benefits:
• Improved Operability and Readiness
• Increased range or endurance
• 2X hot day ground operation
• 4X combat support altitude operations
• 5X electrical power and cooling
• 50% reduced weight and volume
High Performance
Electric Actuation
System (HPEAS)
Robust Electrical
Power System (REPS)
Adaptive Power & Thermal
Management System
(APTMS)
―Energy Optimized Aircraft‖ via
Integrated Vehicle Energy Technology (INVENT)
“Integrated" Advanced Hybrid Electric Vehicle Systems:
• Maximize Overall System Energy Efficiency
• Minimize Thermal Management Challenges
• Optimize ‗On-Demand‘ , Duty-Cycle Based-Systems
• Reduce Risk by Real-Time Simulation, “Fly it before we build it”
Integrated (static/dynamic)
M&S with Hardware-in-the-
Loop Demonstration
Advanced
Engine Technology
Integration
GE Rolls-RoyceFighter Engine Team
Cleared for Public Release , USAF AFRL/RZ, RZ09-0609, 8 Dec 09
8
HP
CompFan
Comb
TU
RB
INE
Comb
Pump
Hot Returned
Fuel to Feed
Tank
Aircraft Heat
Loads…
Generators
Hydraulics
ECS
Fuel Pumps
Avionics
Etc.
Aircraft
Return
Fuel Air
Cooled
Heat
Exchanger
Aircraft Fuel System Thermal Management
Fuel
from
other
tanks
Q = mcpΔT; or Tfinal= Q/mcp + Tinitial
Q is the amount of heat to be managed by fuel
m is the mass of the heated FUEL in feed tank
cp is the specific heat capacity of fuel
ΔT is the temperature difference;
Energy Balance Result is Tfinal considering
Tinitial to be 120 deg F
8
Generic Aircraft Mission ProfileTMS Limits to Mission Growth
Mission Time
TM
S F
uel Tem
pera
ture Fuel Temperature
Limit
End of
Mission
For Official Use Only
• Fuel temperature (mission) limited by fuel-cooled electronics
Ground Idle Low Altitude Cruise
Cleared for Public Release , USAF AFRL/RZ, RZ09-0609, 8 Dec 09
• Modern MEA architectures have drastically altered the dynamics of power flow on the electrical bus
• Peak-to-average power ratios may exceed 5-to-1 across 50 – 5000 ms
• Power electronic loads may produce regenerative power equal to peak power for durations of 20 – 200 ms
• Key loads with highly dynamic power requirements include radar and actuators
J. Wells, M. Amrhein, E. Walters, S. Iden, A. Page, P. Lamm, A. Matasso, ―Electrical Accumulator Unit for the Energy Optimized Aircraft,‖ SAE International Journal of Aerospace, 1(1):
pp. 1071-1077, 2008
Cleared for Public Release , USAF AFRL/RZ, RZ09-0609, 8 Dec 09
10
Energy Optimized Aircraft
M&S Vision
The
Need:
Near Mid Far
The
Solution:
Verified and ValidatedFull System,
Thermal Model
Cockpit Simulation –
Full Mission Capability
Advanced
Components
Integrated Vehicle Energy
Technology (INVENT) System
Integration Facility
M&S is Bridge from Science to FlightCleared for Public Release , USAF AFRL/RZ, RZ09-0609, 8 Dec 09
11
―Fly‖ Any Mission
+ MRIP (Modeling
Requirements &
Implementation
Plan)
―Mission‖ = 5 points
2007—after SAB Thermal Summer Study
• Only a few pre-defined missions are specified in requirements documents; used to design vehicle and all subsystems
• ―Design Point‖ and a few ―Off-Design Points‖ describe entire mission ( time-independent analysis)
• No impact on design/development/acquisition process—No cost or timeline reduction