VSP UAV Sector Overview
Presented at the
UAV Opportunities Workshop
University of Akron
April 2005
Jeff Yetter
Deputy UAV Sector Manager
Vehicle Systems Program
Aeronautics Research Mission Directorate
National Aeronautics & Space Administration
1
Briefing Roadmap
UAV Sector
•
•
•
•
Strategic
Capabilities
GOTChA’s
Roadmaps
Vehicle Systems
Program (VSP)
Future State
VSP Projects
Herb Schlickenmaier
•
•
•
•
•
Autonomy
Structures
Propulsion
Flight Demo’s
Planetary Flight
2
Vehicle Systems Program (VSP)
External/Independent
Review Groups
Vehicle Sectors
Efficient
Aerodynamic
Shapes and
Integration
- EASI (LaRC)
Vehicle Systems
(HQ)
Strategy Team
(One representative
per Aero Center)
Vehicle Integration,
Strategy & Technology
Assessment
- VISTA -
Integrated
Tailored
Aero-Structures
-ITAS (LaRC)
Ultra
Efficient
Engine
Technology
- UEET (GRC)
Quiet
Aircraft
Technology
-QAT (LaRC/GRC)
Autonomous
Robust
Avionics
- AuRA (LaRC/DFRC)
Low
Emissions
Alternative
Power
- LEAP (GRC)
Flight and System Demonstrations
- FS&D (DFRC)
3
Vehicle Sectors
UAV Sector
Subsonic Transports
Supersonic Aircraft
Personal Air
Vehicles
Uninhabited Air Vehicles
Hypersonic
Air Vehicles
Unmanned Aerial Vehicles (UAV)
Remotely Operated Aircraft (ROA)
High Altitude Long Endurance (HALE)
Rotorcraft
Extreme STOL
4
VSP’s UAV Focus is HALE
150
“Global Ranger”
Reference SOA
Capability
Altitude, 1000 ft
125
“SubOrbital
Long
Endurance
Observer”
“Global
Observer”
“Heavy Lifter”
(1st generation ROA)
100
50 kg
75
50
25
Piloted
Aircraft
Capability
1000 kg
Current
ROA
Capability
Extended HALE ROA
Requirements
1 kg
0
0.1
day
300 kg
0.2
day
0.5
day
1.0
day
2.0
day
5.0
day
Endurance, days
10
day
20
day
50
day
100
day
5
VSP’s Vision for HALE
• Low cost testbeds
• Solar/Battery power
• Validated design tools
• Helios MIB
Recommendations
LH2 propulsion
60 K ft @ 14 hrs, 100 kg
100 K ft @ 1 hrs, 50 kg
Solar cells; h=18%, 0.2 kw/kg
RFC: 0.25 kw-hr/kg
Technologies
al e
t
i
rb anc • Active shape control
O
ub ndur r” • Lt weight LH2 tanks
S
“
• Low SFC
E rve
g
e
n
Lo Obs OBJ #1
Solar/RFC propulsion
SOA (2003):
Technologies
al • Superconductor motors
b
lo r” • Multi-functional LH2 tanks
“G nge • Low SFC
Ra
OBJ #3
WL=15 lb/ft2
WL= 2.0 lb/ft2
Capabilities
• 7-14 days @ 60 K ft, 200 kg
• P/L fraction > 15%
• Robust turbulence performance
Capabilities
• Global diurnal range operations
• 10x payload increase @ 75 K ft
• Robust airframe/dispatch reliability
Technologies
• Inflatable/deployable aerostructures
• High power long endurance
electric propulsion
Technologies
• Light weight airframe
• Thin film solar cells
al r” • Long endurance energy storage
b
e
lo
“G serv
• Autonomous flt ops
b
O
OBJ #2
OBJ #4
WL = TBD lb/ft2
WL = 1.0 lb/ft2
Hybrid airframe
Capabilities
• 1-6 months @ 60 K ft
• P/L 150 kg, 2 kw
• +/- 40o latitude
Performance Objectives
FY03
FY05
FY07
FY09
y
av ” Capabilities
e
“H ifter • 100 days > 70 K ft
L
• 10,000 kg
• Global ops
FY11
FY13
FY15 6
HALE ROA Demonstrations
(Plan proposed to and accepted by OMB)
State of the Art
Helios, FY03
Altitude
Endurance
SubOrbital LE Global Observer,
Observer, FY08
FY10
Global Ranger
FY12
Heavy Lifter
FY16
60k / 100k ft
60k ft +
60k ft +
75k ft
60k ft +
1 Day / 1 Hour
14-day
60-day
2 Day
30-90 Day
200 X
Payload
50 kg
200 kg
150kg
20 X
Range
Local
Continental
Global
Global
Global
All Latitudes
+/- 45 deg Lat
All Latitudes
+/- 35 deg Lat
Active shape control
Lightweight airframe
Continuous aero-trim
optimization
Inflatable/deployable
aerostructures
Structures
Example
Technology
Hydrogen fueled,
Power
Lightweight LH2 tank,
Low SFC
Flight Control /
Autonomy
Turbulence resistant,
Highly Automated
Regenerative fuel cell, Superconductor motors
Thin film solar cells, Multi-function LH2 tanks High power electrical
propulsion
Light weight energy
Low SFC
storage
Fully Autonomous
Operations
Intelligent vehicle
systems management
7
HALE ROA Capabilities
Platform Capability
Mission Capability
Airspace Capability
Altitude
Endurance/Range
Payload
Autonomy
Propulsion
Structures
Communications
Sensors
Systems Integration
Precision trajectory
Multi-aircraft
Mission Demonstrations
Routine Access to NAS
Collision Avoidance
Equivalent Level of Safety
Contingency Management
Reliability
NAS Simulations
Planetary Exploration Capabilities
Autonomous, multi-vehicle, robotic operations
Intelligent Mission Management (IMM)
8
HALE ROA Capabilities - concluded
HALE ROA
Pseudogeosynchronous
Operations
Low cost - High Altitude
High
Bandwidth -
- Intelligent Mission
Management
Autonomous
Operations
- Integrated Vehicle
Systems Management
- Adaptive Flight Controls
- In-flight Retasking
Flight in
Global Airspace
Affordable Weather Operations -
Planetary
- Contingency Management
Readily
Deployable
Ease of Ground
Handling Remote Basing -
- Same Day File & Fly
- Sense & Avoid
OTH
Communications
Long Endurance Long Range -
Persistent
ocean and land
observation
- Mission Planning
Deployable Probes Formation Flight -
Multi-ship
Operations
Hydrogen
Fueled
- Consumable fueled
(Cryogenic H2)
- Regenerative Fuel Cell
& Solar Power (gaseous H2)
9
15-Year Technology Goal Set
UAV Sector Area Technology Targets
Goal
Lift-to-Drag Ratio
50
Empty Weight Fraction
25%
Thrust Power-to-Weight Ratio (watts/kg)
> 40
SFC: (lb fuel/lb thrust/hr)
< 0.2
Autonomous Mission Operations
Full Autonomy
Emissions (CO2, NOX)
0
O&M Cost ($ / flight hour)
400
Buoyancy Force
> Vehicle Wt
10
UAV Sector GOTChA Chart
Goals
Lift-to-Drag
Ratio = 50
1
Empty Weight 2
Fraction = 25%
SOA ~ 36
SOA = 45%
4
Specific Fuel
Consumption
(lb fuel/lb thrust/hr) < 0.2
SOA ~ 0.5
Propulsion System 3
Thrust Power-to-Weight
(w/kg) > 80
SOA ~ 40
Version 1
6
Mission
Operations Cost
(per flt hr) = $400
SOA ~ $2,000
100% Autonomous 5
Mission Operations
SOA ~ 90%
Autonomous
Objectives
L/D ~ 100 01
airfoils with
t/c > 15%,
Cm > 0, @
Re ~ 500,000
SOA:
L/D = 80
02
Reduce
airframe
structure
weight by 60%
03
Reduce
airframe
subsystem
weight by 60%
SOA:
Structure wt
fraction = 0.33
SOA:
Subsystem wt
fraction = 0.12
Energy
storage >
1kw-hr/kg
04
05
Energy
efficiency >
50%
SOA:
0.25 kw-hr/kg
SOA: 35%
Order of 08
magnitude
reduction in
human
involvement
07
Full
autonomy
during
emergencies
06
FAA
approved
same day
file & fly in
NAS
SOA: 10%
SOA: 60
Day COA
SOA:
2/Vehicle
Technical
Challenges
02
01
Prevent
laminar
separation
while
maintaining
high lift
Prevent thinwall buckling
without
weight
penalty
04
03
Reduce
subsystem wt
while
increasing
performance
and capability
Compensate
for nonuniform gust
loads without
weight
penalty
05
Reduce
weight &
volume of
energy &
power source
without
output
degradation
06
Develop realtime flight
planning,
health
monitoring
and reconfiguration
09
08
07
Develop long
endurance
unaided
autonomous
operations
and
navigation
Develop an
equivalent
level of safety
requirement
for detect
and avoid
systems
Develop realtime human
flight
management
interfaces
Approach
Implement 01
advanced
boundary
layer
control
techniques
such as
microadaptive
flow control
Develop 02
actively and
passively
tailored
flexible
aeroelastic
structures
responding
to in-situ
environment
Develop 03
competing
structural
concepts
with
optimized
geometries
and
material
properties
04
Develop
advanced
multifunctional
structures,
materials,
and
subsystems
05
Develop
regenerative
energy and
power
technology
06
Develop
lightweight,
long-life,
cryogenic
propellant
technology
07
Improve
efficiency of
electric-drive
propulsion &
power
technologies
08
Develop
lightweight,
miniature
robust
integrated
avionics &
sensors
09
Develop
artificial
intelligence
& integrated
vehicle
health mgmt
incl damage
tolerance
10
Develop
real-time
detect, and
avoid
techniques
11
Develop
real-time
systems
displays
for multiple
aircraft
operations
UAV Sector Roadmaps
Mission Operations Affordability
Mission Operations Technology
Propulsion & Power (Specific Fuel Consumption)
Propulsion & Power (Thrust-to-Weight Ratio)
Aerodynamics
Weight Management
Capability Development Timeline
High Altitude Long Endurance (HALE)
Required Technologies
@ TRL 6
SOA:
• 14 hrs @ 60K ft - 200-lb
• 1 hr @ 100K ft @ - 100-lb
• Pre-Programmed
FY14 Capability Set
• Global Range (2 days) @ 75K
• 4400 lb (2000 kg) Payload
• Autonomous Operations
FY08 Capability Set
• 14-days @ 60K ft
• 440 lb (200 kg) Payload
• Highly Automated Operations
FY04
FY08
FY11 Capability Set
• 60-days @ 60K ft
• 330 lb (150 kg) Payload
• Autonomous Operations
• Collaborative Engagement
FY12
FY16
13
Planetary Flight Vehicles (PFV)
VSP to develop technologies for autonomous
flight vehicles enabling planetary exploration
14
PFV Enabling Capabilities
Platform Delivery
“Transition to a Free-Flying Platform”
- Efficient platform packaging and delivery
- Robust Extraction, Deployment and Unfolding System and Pullout Technique
Extended Flight Duration
“Minutes to Hours”
- Improved aerodynamic efficiency
- Improved propulsion efficiency
- Increased energy density
- Increased overall robustness
Surface Interactions
“Science Driven”
- Enable payload delivery
- Enable landing and takeoff
– CTOL, VTOL, LTA
Flight Path Precision
“Feature Targeting”
- Improved state knowledge
- Improved platform stability
- Increased flight controls robustness
- Enhanced autonomy
Sub-System Enhancements
“Resource Reduction”
- Reduced avionics mass/power
- Integrated avionics/sensors
- Improved data return capabilities
15
Capability Development Timeline
Planetary Flight Vehicles (PFV)
Required Technologies
@ TRL 6
(Terrestrial Demo’s)
Surface Interactive
• Endurance: Reusable
• Fully autonomous, sentient ops
• Surface interaction via deployed
sensors and/or VTOL operations
Global Scale
• Endurance: 8-10 hours
• Payload: 50-100-lb
• Feature targeting via terrain
recognition
Regional Scale
• Endurance: 1-2 hours
• Payload: 20-lb
• Pre-Programmed Flight Path
Launch
Opportunity
Launch
Opportunity
FY04
FY09
FY14
FY19
16
Projects Supporting UAV Sector
External/Independent
Review Groups
Vehicle Sectors
Efficient
Aerodynamic
Shapes and
Integration
- EASI (LaRC)
Vehicle Systems
(HQ)
Strategy Team
(One representative
per Aero Center)
Vehicle Integration,
Strategy & Technology
Assessment
- VISTA -
Integrated
Tailored
Aero-Structures
-ITAS (LaRC)
Ultra
Efficient
Engine
Technology
- UEET (GRC)
Quiet
Aircraft
Technology
-QAT (LaRC/GRC)
Autonomous
Robust
Avionics
- AuRA (LaRC/DFRC)
Low
Emissions
Alternative
Power
- LEAP (GRC)
Flight and System Demonstrations
- FS&D (DFRC)
17
UAV Sector Technology Areas (1 of 2)
Autonomous Robust Avionics
Integrated Tailored AeroStructures
Integrated Vehicle System Management
Adaptive, Ultra-Lightweight Airframes
• On-Board Prognostics & Failure Mitigation
Systems
• Robust, Fault Tolerant Architectures
• Software Reliability
• Digital Systems Verification & Validation
methods
• Flexible Aeroelastic Structures
– Aeroservoelastic tools, Gust Load Alleviation
methods, Ground test methods
• HALE Wing Concepts
• Multi-functional Structures & Materials
Integrated Mission Management
• Architectures for autonomous/collaborative
decision environment for single UAV
• Architecture for unaided navigation via
payload-directed flight.
Adaptive Optimal Flight Controls
• Reconfigurable Control Technologies
Exploration Aerial Vehicles
Micro
Trailing-edge
Effectors
(MiTEs)
(Ilan Kroo)
• Planetary Aircraft Risk Reduction
– Aero-performance
– Extraction, Deployment, Unfolding, Pull-out
– Weight and volume reduction
18
UAV Sector Technology Areas (1 of 2)
Low Emissions Alternative Power
Flight & Systems Demonstrations
Aircraft Fuel Cell Power Systems
HALE ROA
• Regenerative Fuel Cell System Development
• Advanced Fuel Cell Technologies
• Proof-of-concept testing
• Pathfinder-Plus
• Sub-Orbital Long Endurance Observer
• Global Observer
Alternative Propulsion Systems
HALE ROA in the NAS (Access 5)
• H2 Propellant Feed Systems
– Requirements, tools, designs, operations
• Cryogenic Storage Technologies
• Policy & Regulations
• Enabling Technologies
• National Airspace Simulation
• Flight Demonstrations
– Materials, design, testing
Earth Sciences Capability Demos
• Civil ROA Roadmap
• Precision Navigation (absolute & relative)
• Over-the-Horizon Communications
• Annual Science Campaigns
19
HALE is a part of VSP Future
• Environment
• Noise Reduction Demonstrations
• Subsonic Noise Reduction
• Sonic Boom Mitigation
• Zero Emissions Aircraft Demonstration
• Science and Exploration
• HALE Demonstrations
20
HALE Demonstrations
State of the Art
Helios, FY03
Altitude
Endurance
SubOrbital LE Global Observer,
Observer, FY09
FY12
Global Ranger
Heavy Lifter
60k / 100k ft
60k ft +
60k ft +
75k ft
60k ft +
1 Day / 1 Hour
14-day
60-day
2 Day
30-90 Day
200 X
Payload
50 kg
200 kg
150kg
20 X
Range
Local
Continental
Global
Global
Global
All Latitudes
+/- 45 deg Lat
All Latitudes
+/- 35 deg Lat
Active shape control
Lightweight airframe
Continuous aero-trim
optimization
Inflatable/deployable
aerostructures
Structures
Example
Technology
Hydrogen fueled,
Power
Lightweight LH2 tank,
Low SFC
Flight Control /
Autonomy
Turbulence resistant,
Highly Automated
Regenerative fuel cell, Superconductor motors
Thin film solar cells, Multi-function LH2 tanks High power electrical
propulsion
Light weight energy
Low SFC
storage
Fully Autonomous
Operations
Intelligent vehicle
systems management
21
Sub-orbital Long Endurance Observer (notional)
(14-day Demonstrator)
• 60,000 Ft nominal operating altitude
• Up to 14-day endurance
• 2000 nm operating radius
Tradeoffs
• Hydrogen fueled; cryogenic storage
• 440 lb payload, 2 kW power available
• Loiter speed ~ 65 - 105 kTAS
• Cruise/Dash speed ~ 100 - 135 kTAS
– dash speed for re-visit
• Highly automated, retaskable
– reduced human involvement
• OTH communications
• Operations in moderate in-flight
turbulence, moderate winds, icing
• Vertical profiling (limited)
• Payload deployment (e.g., daughterships)
Twin Engine Variant
Reference Mission
OTH Comm
65,000 ft
Operating
Altitude
50,000 ft
•
•
•
•
• Equivalent Level of Safety (ELOS)
– Reliability & Safety
• Affordable (cost target tbd)
• Easy ground handling, quickly deployable
5 - 12 days
On Station
Airfield
Sampling Maneuvers
Feature Orbits
Vertical Profiling
Sensor Deployment
Ground
Station
2000 nm Operating Radius
22
14-day Reference Mission
OTH Communications
5 - 12 days
On Station
65,000 ft
Operating
Altitude
50,000 ft
•
•
•
•
Airfield
Sampling Maneuvers
Feature Orbits
Vertical Profiling
Sensor Deployment
Ground
Station
2000 nm Operating Radius
23
Global Observer (notional)
(60-day Demonstrator)
• 60,000 ft nominal operating altitude
• > 30 day endurance
• Operational latitudes of +/- 45°
• Solar powered electric propulsion
– regenerative H2 fuel cell for nighttime
operation
• 330 lb payload, 1 kW power available
• Loiter/Cruise speed ~ 50 kTAS
• Fully Autonomous, retaskable
– minimum human involvement
• OTH communications
• Operations in light in-flight turbulence,
light winds, no icing
• Near constant altitude loiter
• Equivalent Level of Safety (ELOS)
– Reliability & Safety
• Affordable (cost target tbd)
• Reduced ground handling support reqmts
General missions objectives:
• Long-dwell Earth and Atmospheric
Science Research
• Surveillance & Reconnaissance
(DHS/DOD)
• Commercial telecommunications
24
ARES - The 1st Mars Airplane (?)
Aerial Regional-scale Environmental Survey (ARES)
ARES Science Objectives
• Crustal Magnetism
• Near-Surface Atmospheric Chemistry
• Underlying Geology & Mineralogy
25
Concluding Remarks
• VSP focus is on High Altitude Long Endurance (HALE)
• Parallel efforts are focused on Planetary Flight Vehicles
• HALE has many Science and public benefit applications, but
capability gaps must be closed to meet Science and civil mission
requirements:
•
•
•
A/C Performance - broad operating envelope for Science applications
(propulsion, structures, aero and autonomy)
10X improvement in system reliability and operational costs
FAA “certification” for routine operations in the NAS
• VSP seeks opportunities to partner with OGA, industry and
academia in vehicle capability developments,
• Exploit synergy between NASA Aeronautics & Science Directorates
26
“Hale Yeah”
27