Transcript UAVworkshop3_v3 - InnovationLabs — Innovation

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Civil UAV Capabilities Assessment
A Summary and Synthesis of the Akron Workshop
TABLE OF CONTENTS
Overview
Concept Cards
Missions Overview
Mission: Arctic Explorer (Cryosphere)
Mission: Carbon Cycle Southern Ocean
Mission: Vegetation Structure
Mission: Active Fire, Emissions
Mission: Hurricane Genesis Evolution
Page 22
Mission: Cloud, Aerosol, Water VaporPage 26
Additional Investment Opportunities
Civil UAV Capabilities Assessment
Workshop 3 • Akron, Ohio • April 26–28, 2004
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Page 3
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Page 9
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Page 17
Page 31
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Overview
The purpose of this workshop was to identify capabilities
needed in future civil UAV’s to enable informed funding
decisions on key technologies. This is focused to reveal
science sensor technology gap data in more details than just
miniaturization and will provide information for a section in our
assessment document. We also need to determine power and
propulsion technology shortfall data.
Our task is to develop a Civil UAV Capability Assessment for
a 2015 Time Frame. We are intending to serve the SubOrbital Science Program (Yuhas), the Vehicle Systems
Program (Camacho) and to complement the DOD roadmap.
We will consider Homeland Security, Commercial, Land
Management, and Earth Sciences in our assessment.
Our objectives are to document future missions of civil UAVs
based on user defined needs, the technologies necessary to
support those missions; to discuss SOA of those
technologies, identifying those in progress, those planned,
and those for which no current plans exist. We also intend to
provide the foundations for development of a comprehensive
civil UAV roadmap.
This document is a summary of the group’s work.
Civil UAV Capabilities Assessment
Workshop 3 • Akron, Ohio • April 26–28, 2004
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Concept Cards
During the
introductory
presentations on
Wednesday, April
27th, participants
were introduced to
the current state of
UAV capabilities,
platforms and
roadmaps. These
concept cards were
captured during
those
presentations.
Civil UAV Capabilities Assessment
Workshop 3 • Akron, Ohio • April 26–28, 2004
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Missions: Overview
Context
After completing the workshop in Boulder the
following 6 missions from the Sub-Orbital Science
Missions of the Future Workshop were defined as
suitable to be used as example of mission types.
1.
2.
3.
4.
5.
6.
Arctic Explorer (Cryosphere)
Carbon Cycle Southern Ocean
Vegetation Structure, Composition, and Canopy
Chemistry
Active Fire, Emissions, and Plume Assessment
Hurricane Genesis Evolution and Landfall
Cloud, Aerosol, Water Vapor, and Total Water
Measurements
These missions were used in this workshop to stimulate
the first set of conversations to assess the
capabilities and technology gaps for both
instrumentation/sensors as well as power and
propulsion.
Civil UAV Capabilities Assessment
Workshop 3 • Akron, Ohio • April 26–28, 2004
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Mission: Arctic Explorer (Cryosphere)
Brief Description: This mission supports measurements of the dynamics of the breakup of polar glacier and polar ice sheets.
The measurements enable direct observation of the evolution in time of ice and land topography, iceberg volume, glacier profiles,
and glacier channel profiles and provide data for validating simulations of these dynamics and their interaction with the ocean
environment.
Sensor Package
The breakout group working on this
mission identified the following
sensors required to complete this
mission:
1.
2.
3.
4.
5.
6.
7.
Active Microwave
Passive STAR (and salinity)
V/IR Imager / Spectrometer
Magnetometer
Topo Lidar (downsized)
Stereo Imager (miniaturized)
High Resolution Nav.
This suite of sensors solve a number of other
science challenges, not just the cryosphere. We
can look at volcanoes, solid earth and geology,
etc. Most of these sensors are pretty welldeveloped. The passive STAR is the least
developed - this is the biggest technology gap.
All of the others need to be repackaged and
miniaturized. For the spectrometer this could
actually allow improved performance.
Civil UAV Capabilities Assessment
Workshop 3 • Akron, Ohio • April 26–28, 2004
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Mission: Arctic Explorer (Cryosphere)
Sensors/Instrumentation
Sensor
Measurements
Notes
Weight/Power/
Active Microwave
Ice thickness, snow,
water
-Embedded antenna
(needs
miniaturization)
50kg, 2kw, BW - Low
Passive STAR
(and salinity)
Freeze, thawline,
water
-Conformed antenna
50kg, 150w, BW - Low
V/IR Imager /
Spectrometer
Lband, 1.4ghz, +
18.37ghz
-Needs
miniaturization
(pushbroom)
25kg, 500w, BW - 1mb
Magnetometer
SST, refectivity
-Mature technology
15kg, 10w, BW - Low
-Needs
miniaturization
50kg, 100w, BW - High
~10mb
Topo Lidar
(downsized)
Stereo Imager
(miniaturized)
-COTS
10kg, 10w, BW - High
~20mb
High Resolution
Nav.
-COTS
5kg, 5w, BW - Low
205kg, 2.8kw
Civil UAV Capabilities Assessment
Workshop 3 • Akron, Ohio • April 26–28, 2004
To do high-sensitivity
measurements, we need a
platform that can go very low and
slow, while maintaining a constant
land speed - this is critical for
these kinds of remote sensing
instruments. This gives us a much
better signal-to-noise ratio. We
would love to get a ground speed
of 5 knots, but this would require
some serious headwinds.
Operationally, cloud cover will be
an issue for some of our
objectives. We want to record data
on board, and we will need on/off
commands for some data sites.
We do not see any issues for
logistics and deployment. This is
pretty standard operationally.
The total payload will probably be
just under 200kg. It seems like a
good Predator package, but it
should all be measured under
12,000 feet.
We need to pay attention to any
extra power that might be required
to heat these instruments in
extremely cold conditions.
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Mission: Arctic Explorer (Cryosphere)
Power & Propulsion
Performance Specifications
Flight Characteristics
1. Altitude: 200’ AGL - terrain avoidance
to 12,000’
2. Range: long distance / arctic continent
3. Payload mass: 1000lbs
4. Payload power: 1/2kw
5. Propulsion power: rapid climb
capabilities (turbine/hydrocarbon)
6. Endurance: 36 hours
7. Sampling
8. Speed - >100 knots due to high winds
9. Temp: below -35° operating conditions
10. Quick deploy / quick turnaround
11. Frequency: 1 mission / 3 days during
ice breakup
12. Cost: less than $1000/hour
13. Terrain avoidance requirement
14. Mission available more than 50% of
deployment
•Low flight
•High wind conditions - 100 knots or better
•Map of base state; quick response to
events
•Map continent in 3 weeks every season
•Does wind affect lidar measurements?
–Need calm conditions
•Terrain following
•Summer or winter operations?
–Year round?
•Re-tasking during flight
On the Antarctic mission, we questioned when
we would be taking this data, such as in winter
when you're fighting a lot of winds. We
considered using a dirigible, but we weren't sure
if that would fit the requirements.
We were a little worried if it is really cold, there
is a lot of distortion, we have problems with the
turbine. If you're using light fuel, it's probably not
a problem.
The antarctic is colder than the arctic. We saw
minus 74 C. This impacts the type of fuel you
use. They used JP5 for that. We're at JP8 now.
We need to do a little more work on this.
Civil UAV Capabilities Assessment
Workshop 3 • Akron, Ohio • April 26–28, 2004
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Mission: Arctic Explorer (Cryosphere)
Technology Development Opportunities
Passive Microwave
1.
2.
3.
Scale from Satellite to
UAV
Salinity Sensor
Passive Microwave for
snow on land
1.
2.
3.
Light weight
Antenna integration
w/aircraft
Additional Cal. Issue for
UAV applications
Active Microwave
Radar (Ka or P)
Passive Optical
HyperSpectral Imager V/SWIR
Miniaturization, light weight
Hyper/Multi-spectral TIR
Stereo Camera
Coupled with Lidar
Stabilized mount
Light weight, generic; include
IMU
Civil UAV Capabilities Assessment
Workshop 3 • Akron, Ohio • April 26–28, 2004
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Mission: Carbon Cycle Southern Ocean
Brief Description: The primary goal of this mission would be a definitive measure of net annual CO2 uptake from the
atmosphere by the Southern Ocean, including its inter-annual variability, and relation to other known quantities. The mission would
also add greatly to knowledge of vertical mixing in the atmosphere over the Southern Ocean. The results would serve as inputs to,
or constraints on, models of the carbon cycle, improving understanding of many aspects.
Sensor Package
The breakout group working on this
mission identified the following sensors
(or capabilities) required to complete this
mission:
1. ICO2
2. H2O
3. Radiometer
4. Ocean color imager
5. Raman for CO2
6. Lidar (scatterometer optic/RF)
7. Turbulence probe
8. Surface temperature
9. FTIR
10. Deployable buoy
11. Boundary layer
12. L-band radiometer (1.4ghz)
In the near-term, we captured what is possible in
FY06. We used the instruments recommended in a
recent paper, and we added 2-channel GPS to
measure surface roughness. We did not include Seeand-Avoid. We have assumed that will always been an
operator in the loop ﾐ this does not have full autonomy.
Civil UAV Capabilities Assessment
Workshop 3 • Akron, Ohio • April 26–28, 2004
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Mission: Carbon Cycle Southern Ocean
Sensors/Instrumentation
Developing the lightweight antennae will be one of our biggest
challenges. We can increase our autonomy and our data
capacity. Our total mass is less than 200 pounds and just over
1000 watts. This depends on a 3000 mile range. The speed is
negotiable.Our CO2 measurements will require even more
resolution than a 10-pound LIDAR can provide. We also need
really good measurements of water vapor. You run the risk of a
false signature. We also need to talk to the wind LIDAR.
Once we get to 2010, we can develop a much better
solution. We could develop a CO2 LIDAR. We could add a
three-channel LIDAR to measure the winds. We will add a
hyperspectral camera. Infrared (for looking at the sea
surface) will be a challenge because of the cooling issues.
An FTIR has the same cooling issues. It will take until 2010
to develop and image analysis algorithm.
#s
W
Licor CO2 insitu & H2O
2#
5w
Radiometer (SSFR)
2#
5w
Ocean Optics Spectrometer
1#
5w
2-CH GPS (sea state/surface + Pos x, y, z +
winds)
1#
5w
Turb Probe
2#
Camera
FY 10
FY 06
Low & High Altitude Vehicles (10m,
3km)
For Improved Science Return
#s
W
Lidar: CO2
10#
200w
Lidar: winds/turbs
15#
300w
Optical absorption: CO2
10#
150w
Hyperspectral cameras: vis
2#
20w
IR (cooling for IR!)
10#
100w
1w
Raman Spectrometer (CO2)
10#
150w
1#
1w
FTIR (cooling for IR!)
45#
100w
KT - 11
1#
10w
Image Analysis
—
—
3-D: hotwire/flux gate
2#
5w
L-band radiometer (salinity)
20#
25w
Data system and control
5#
50w
Antennas
17#
87w
Autonomy: Control
5#
50w
127#
1095w
Totals
Totals
Buoys: TBD
Civil UAV Capabilities Assessment
Workshop 3 • Akron, Ohio • April 26–28, 2004
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Mission: Carbon Cycle Southern Ocean
Power & Propulsion
Performance Specifications
Flight Characteristics
1. 10-30m steady state - profiles to 3000’
2. Range: 8000km
3. Payload mass: 66lbs
4. Payload power: ?
5. Propulsion power: climbing requirement
(turbine/hydrocarbon)
6. Endurance: 48 hours
7. Sampling: 150 samples/second ?
8. Speed - >100 knots (more info needed)
9. Frequency:
•Land or sea-based platforms
•Swarm (5 vehicles) w/predefined flight
pattern
•Sensor adjustable flight pattern
•High wind
•Carbon sequestration
•Shipboard operations:
40° – 70° South Latitude
–Catapult
–Recovery - net?
•Parachute?
•Question on rate of climb for verticle
profiles
We believe that the current UAV can
handle the mission. Payload mass is
shown there at 66 lbs. This is low
weight. So these are mild and unless
there is some flight concern about
turbulence, what we have now would
work fine.
Between the small and medium
platforms you have a good jump in
power. There may be some
modification to a small UAV and have
what you need.
One thing is that in your power
requirements, you need to specify if
the requirements are simply for
payload or does it include the
communications package?
Civil UAV Capabilities Assessment
Workshop 3 • Akron, Ohio • April 26–28, 2004
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Mission: Carbon Cycle Southern Ocean
Technology Development Opportunities
Passive Microwave
Salinity -> L-band Passive
Passive Optical
HyperSpectral Imager V/SWIR
Miniaturization, light weight
Gas Filter Correlation
Radiometer
GFCR
Column abundance
Stabilized mount
Light weight, generic; include
IMU
Active Optical
CO2 lidar
Winds
Short range
In-Situ
CO2
High precision
Wind
Vertical
Civil UAV Capabilities Assessment
Workshop 3 • Akron, Ohio • April 26–28, 2004
Missions: Vegetation Structure, Composition, and
Canopy Chemistry
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Brief Description: This suborbital mission would help scientists improve the characterization of terrestrial biomass, leaf level
chemistry and canopy water content. The science data will provide 3-dimensional vegetation structure and information on composition
and chemistry. In addition, the observations will elucidate functional groups and physiological impacts on the carbon cycle.
Sensor Package
The breakout group working on this
mission identified the following sensors
(or capabilities) required to complete this
mission:
1.
2.
3.
4.
Radar (P, L, X band - polarimatric
Hyperspectral
Lidar
On-board recorder
For this particular application, we do not think
that there is any UAV-specific advantage.
These missions are short-duration, there are
no opportunistic measurement requirements
(vegetation tends to change quite slowly), and
alternative approaches exist. There are a lot of
technologies used for other applications,
however, that could be used for our purposes.
Civil UAV Capabilities Assessment
Workshop 3 • Akron, Ohio • April 26–28, 2004
Missions: Vegetation Structure, Composition, and
Canopy Chemistry
Sensors/Instrumentation
Sensor
Weight
Power
Radar
200kg
2kw
Hyperspectral
50kg
100w
Lidar
100kg
100w
Data rate
Volume
On-board recorder
80mb/sec
80x80x80cm
Flight
Duration
Altitude
12 hours
<40,000’ (15km)
Technology Specifications
Lightweigt antenna
Power supply provided by UAV
Large on-board data storage/downlink capability
Technology Challenges
Autonomous operations
Low mass & reconfigureable design
COTS digital system
Steerable antenna
Real time flight path control
High power L/X T/R Module / dual pol. Amt.
We want to use radar, hyperspectral radar,
LIDAR, and an on-board recorder. Some of
these technologies need to be adapted to the
UAV platform, but this is not a major hurdle.
There are some key components that will be
required for the antennae, telescope, and focal
point array.
There are some general technology challenges
for the UAV. It requires autonomous operations
because it uses different platforms. It requires
a steerable antenna. We need to be able to
correct the flight path in-flight. We need highpower modules.
A 12 hour mission could generate up to 7
terabytes of data, given the instruments
onboard. There are no real-time requirements
for this data, so we do not need instantaneous
access to it. We need to find the most costeffective means of transmitting and storing the
data. We need to coordinate the flight path, but
we do not need to coordinate the flight paths of
multiple aircraft in formation. One UAV will
have X-band and L-band, and a second UAV
will carry LIDAR and hyperspectral. They do
not need to fly at the same time.
Civil UAV Capabilities Assessment
Workshop 3 • Akron, Ohio • April 26–28, 2004
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Missions: Vegetation Structure, Composition, and
Canopy Chemistry
Power & Propulsion
Performance Specifications
Flight Characteristics
1. 40,000’
2. Range:
3. Payload mass: 760lbs
4. Payload power: turbine/hydrocarbon
5. Propulsion power: turbine/hydrocarbon
6. Endurance: 12-24 hours
•Formation flying: GPS
•Refly Formation: GPS
•Every Season
The way we figure the power and mass
for the state of the art UAV situation, we
need to reduce the power by half and the
weight by a quarter.
The weight of the antennae system is in
pretty good shape. The key thing is to
modularize these components. Reducing
the weight of the battery and the sensor
system. It will require interferometric
measurements and differential GPS. You
will need a flight controller as a critical
aspect. We will have a data rate transfer
of 1mb/sec. Having optical
communication is a good approach.
There should be a lot of trades in here.
We think this mission is doable with
current technology. The current assets
will work, We didn't see a real challenge
here at all.
Civil UAV Capabilities Assessment
Workshop 3 • Akron, Ohio • April 26–28, 2004
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Missions: Vegetation Structure, Composition, and
Canopy Chemistry
Technology Development Opportunities
Passive Microwave
Add L-band for SM -> moisture
(C&X-band)
Active Microwave
Radar (X & L)
Passive Optical
HyperSpectral Imager V/SWIR
Miniaturization, light weight
Stereo Camera
Coupled with Lidar
Stabilized mount
Light weight, generic; include IMU
Active Optical
Waveform lidar
Canopy top
Civil UAV Capabilities Assessment
Workshop 3 • Akron, Ohio • April 26–28, 2004
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Mission: Active Fire, Emissions, and Plume Assessment
Brief Description: This suborbital mission would help Earth Science scientists further understand the influence of disturbance
on carbon cycle dynamics by observing and measuring: the atmospheric chemistry; the thermal intensity time-series; the plume
composition, including the volume, albedo, particle size distribution; and, the fuel type and quality. The measurements would also
provide the atmospheric composition focus area a better understanding of fire plume chemical constituents resulting from different
fuels under different intensities of fire.
Instruments
Remote
1. Imaging Hyperspectral
2. Lidar
3. Gas Filter Correlation Radiometer
In-Situ
1. Mass Spec
2. CI Gas Chromatograph
3. NDIR
4. Spectral Radiometer
5. Chemical Microsensors
6. Particulate Sensors
7. Tunable Diode Laser
8. Gas Bottles
9. UV Absorption 03 Sensor
10. Aerosol Spectrometer
11. Condensation Neurli Counter
12. Metrology System
13. Flame Ionization
We have a long list of things we want to measure. We did not have any fire specialists on our team, but we think we did a good job. We need a long
list of equipment as well.
Civil UAV Capabilities Assessment
Workshop 3 • Akron, Ohio • April 26–28, 2004
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Mission: Active Fire, Emissions, and Plume Assessment
Sensors/Instrumentation
Measurement Objectives
CO
CO2
N2O
NOX
CHY
NMH CH2O
O2, O3 (evolution)
Aerosols / particulates / size dist.
Energy release rate
Albedo
Optical depth
H2O
Winds, Temperature, Pressure
This mission is perfect for UAVs. One UAV would be high up making
measurements of aerosols and humidity radiation and one UAV low enough to
capture measurements where you don't want a manned craft. The long
endurance for the upper one is also a challenge we have.
From this list of instruments (and what they could measure), we tried to
assemble a package of instruments that would measure the most important
items, including CO and CO2. With this list, we can now talk about
miniaturization to see if such an effort makes any sense. Many of the
instruments are so tiny that they are essentially free for the mission in terms of
size, weight and space.
We developed weight and power numbers for each item, but we have not yet
summed them up. We want to use LICOR to measure CO2. We want to use a
HSRL LIDAR ﾐ a very powerful instrument for this mission. Another requirement
for these instruments is onboard calibration gasses.
Finally, we wanted to talk about technology gaps. We feel that the multi-spectral
is pretty good for use today (not a hyper-spectral). Many of these instruments
are in pretty good shape. Some instruments need some help to run more
autonomously. There are some physical limits to how far we can miniaturize the
LIDAR.
We will need to package our instruments differently when we start packing them
into the tight spaces of UAVﾕs. This is in conflict with another teamﾕs report
which encourages plug-and-play. There will be data management problems
onboard the UAV.
Civil UAV Capabilities Assessment
Workshop 3 • Akron, Ohio • April 26–28, 2004
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Mission: Active Fire, Emissions, and Plume Assessment
Sensors/Instrumentation
Lidar (HSRL)
Req’d
LICOR
CO2
NDIR
Req’d
Multi-Sprectral
TIR Scanner
Chem/Micro
CO2
CO
Aerosol
(particulates)
SOA
TDL
Detection Limit
~.1μ
.05μ
350ppm
200ppb
50mk
200
1ppm
Low ppb
Dynamic Range
up
20
10000ppm
3ppm
1800c
3000
400ppm
To>1ppm
Time Response
~1hz
Vert
profile
1hz
20hz
~ seconds
~ seconds
1 sec
Specificity
Quantitative
Speed
Composition
good
NA
Good,
depends
Good,
depends
Excellent
Autonomy
possible
demonstrated
YES
Not req
(72 hrs
OK)
Not req (72
hrs OK)
Requires
setup
Cal Gas
(Stability)
NA
Yes
Built in cal
Size
1.5 M3
1ft3
1f3gas
.3 M3
30cc
30cc
<10cc
1M3
Weight
300kg
15# + gas
15#gas
50
100g
100g
<10g
100kg
Power
700w
100w
300
1w
1w
<10w
250w
Environmental
Exposure
Mod. Robust
(humidity, temp)
Robust
Good
Robust
Moderately
robust
Needs
miniaturization
Can do,
needs minor
work
Can do
Can do
Can do
needs work
Some limits to
aperture & laser
power
Yes
.3m
1watt
Civil UAV Capabilities Assessment
Workshop 3 • Akron, Ohio • April 26–28, 2004
20
Mission: Active Fire, Emissions, and Plume Assessment
Power & Propulsion
Performance Specifications
Flight Characteristics
1. Altitude: lower up to 20,000’ / upper above
20,000’
2. Range:
3. Payload mass: 130-200lbs
4. Payload power:
5. Propulsion power: heavy wind loads
6. Endurance: 24-72 hours
7. Speed:
8. Mission Frequency:
9: Trajectory requirements: position
knowledge required; trajectory requirement
requires additional propulsion power
10. All-weather flight - required for mapping
but not for other missions
•Multiple vehicles in coordinated flight,
but not in formation
•Fly in the plume - spiral
•Terrain avoidance
•Track chemistry changes
•Vehicle ingests smoke particles
•Reduction of O2 - is there enough O2 for
combustion?
•Engine emissions cannot affect
measurements
•Re-tasking during flight
•Payload directed flight
•Mountain fires require higher aircraft
performance = gas turbine
The remote UAV can handle this. It depends on
how many of these you want. Can you stage them
by regions? Then we could send one out as one
wears down.
The plume UAV is also possible. This speaks to the
dirty and dangerous and is probably not dull. This
may need a bit of work because of the temperature
and amount of soot. There is a story in which soot
was going into the engines and they would just shut
down. This could be a challenging environment to
work in. We need to find out more information about
the conditions.
If you have to keep temperatures constant for the
instruments, then you need a heating cooling
system either by payload bay or instrument by
instrument.
The current technology of UAVs is complete right
now for this mission than any of the others. You're
closer to a total application.
We haven't talked about airspace yet. We have to
partner with the forest service on this. But from an
operational standpoint, we're ready to do this.
Control burns are the place to do the science. The
authorization to have airspace for a control burn is
from the Forest Service. There are some places
that you can go to your restricted areas with UAVs
right now.
Civil UAV Capabilities Assessment
Workshop 3 • Akron, Ohio • April 26–28, 2004
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Mission: Active Fire, Emissions, and Plume Assessment
Technology Development Opportunities
Passive Microwave
In-Situ
L-band for S.M. -> fuel level
CO (TDL or UV) + μsensors
Weight & power reduction - open
path
THC (FID + μsensors) (total
hydrocarbons)
Available with some mods reduce extra gases, inlet
Black Carbon
Measurements needed
Particles
Inlet, external probes
10->37ghz
Passive Optical
HyperSpectral Imager V/SWIR
Miniaturization, light weight
Hyper/Multi-spectral TIR
Stabilized mount
Light weight, generic; include
IMU
Gas Filter Correlation
Radiometer
GFCR
Column abundance
Active Optical
High Spectral Resolution Lidar
Cloud/aerosol
Ozone lidar
This capability was missed in the
mission summary but was
required in the mission described
in the July 2004 workshop.
Civil UAV Capabilities Assessment
Workshop 3 • Akron, Ohio • April 26–28, 2004
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Mission: Hurricane Genesis Evolution, and Landfall
Brief Description: The purpose of this mission would be to accomplish observations of hurricanes to improve predictions of
hurricane paths and landfall. This approach would use high altitude remote sensing to gather data on precipitation, clouds, electrical
phenomenon, microphysics, and dust. Daughter ships or drop-sondes would gather data (four-dimensional cubes of thermodynamic
variables and winds) at lower altitudes. Additional data would be gathered in the boundary layer (sea surface temperature and surface
winds, surface imaging, turbulent fluxes, water surface state). Measurements of this type would improve hurricane modeling
capability to increase human safety.
Sensor Package
The breakout group identified the
following sensors (or capabilities)
required to complete this mission:
1. Optical imager
2. Sondes
3. uWave sounder
4. Radar
5. GPS Reflectance
6. Lidar
7. Infra-red pyrometer
8. Near surface sea temperature
9. IR Sounder
Our recommended solution is to deploy multiple high-altitude
platforms. We would instrument one UAV with microwave
and a few other sensors. We would take the adaptive high
altitude platform to the outer storm or the near-storm
environment - weﾕll put our LIDARs on that vehicle. We will
put our drop-sondes on another UAV to validate our remote
sensing instruments, but we do not want to use them
routinely because of the weight that they add to the mission.
This replaces high, middle, and low-altitude platforms.
Civil UAV Capabilities Assessment
Workshop 3 • Akron, Ohio • April 26–28, 2004
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Mission: Hurricane Genesis Evolution, and Landfall
Sensors/Instrumentation
Instrument
Data Rate
Measurement
Size
Weight
Power
Optical Imager
0kbps
K-H billows
6-7km
2kg
Sondes
50kbps
Soundings
16” length
1lb - 696lbs for
12 days
uWave Sounder
100kbps
Soundings (cloudy & clear)
.5x.5m
50lb
40w
Radar
2.4kbps
Clouds & Precipitation
C-band 5m;
x-band ~2m
450lbs
1800w
GPS Reflectance
4.8kbps
Surface & Spectral Cloud
Soundings
4kg
300w
Lidar
14.4kbps
H2O
525lbs
500w
Mid-IR Sounder
200kbps
H2O, T, P, CO, CO2, O3
200kg
500w
IR Sounder
Sea Surface temperature
20-40kg
20w
AXBT
Near surface sea temperature
Totals
171.6 kbps
Our Recommended Solution
1.
2.
3.
4.
1m each
Multiple high altitude platforms, instrumented appropriately, fex;
Inner core - u-wave sounder & radar (cloudy!)
Outer storm & storm environment - lidars & mid IR sounder (clear!)
Cal/Val - dropsondes
17lbs
866kg
(too heavy)
3.8kw
Our goal is to get data that we cannot get from a
satellite or manned mission. We want a
balanced, 4D ‘grid’ of sounding points.
We need a new technique for measuring
surface temperature (about 1m below the
surface) - we donﾕt know how to do that from a
UAV.
Civil UAV Capabilities Assessment
Workshop 3 • Akron, Ohio • April 26–28, 2004
24
Mission: Hurricane Genesis Evolution, and Landfall
Power & Propulsion
Performance Specifications
1. Altitude: 65,000’
2. Range: 200 nautical miles radius
3. Payload mass: 200kg min/ 1000lb desired
4. Payload power: 1 kw
5. Propulsion power: 150-300 hp
6. Endurance: 14 days
7. Time to destination: 24hrs max
8. Deploy from: Hispanola; Canary Islands
9: Mission Frequency:
Reusable dirigible - “grandmother”
Vehicle speed vs. wind speed?
This is a challenge from multiple directions from both an airframe and power and propulsion standpoint. We need to get there quick as well as
stay there for a long time as well as get to various points through the storm.
We need both convective levels to get data for both hurricane and cloud. We might be able to come up with something cheap and expendable. All
of these are challenging for us. Particularly the high and long endurance one. We had quite a bit of discussion. We wondered if we could get it out
there another way.
We keep coming up with the dirigible idea. Can you fly something out there that can keep it out there for awhile? There are multiple ways of
handling it.
Civil UAV Capabilities Assessment
Workshop 3 • Akron, Ohio • April 26–28, 2004
25
Mission: Hurricane Genesis Evolution, and Landfall
Technology Development Opportunities
Passive Microwave
1.
2.
Atmospheric Sounding? 183ghz
C-band (SFMR) -> surface wind
speed; rain rate; 4->8ghz
Active Microwave
Radar (X & L)
Passive Optical
Hyper/Multi-spectral TIR
Stabilized mount
Light weight, generic; include IMU
Active Optical
Water vapor lidar
High Spectral Resolution Lidar (HSRL)
For clouds and aerosol
Winds
Long range
In-Situ
Dropsondes
Double as a buoy?
Weight & size reduction
Communication (relay stations? UAV
pickup?); Target= 200g
Civil UAV Capabilities Assessment
Workshop 3 • Akron, Ohio • April 26–28, 2004
26
Mission: Cloud, Aerosol, Water Vapor, & Total Water
Brief Description: This suborbital mission would study transformations of aerosols and gases in cloud systems.
Convective systems, Sea breeze cloud formation, Marine stratiform, Contrails in the Central U.S. in air traffic regions and
ship tracks in oceans, Synoptic scale systems & Fronts, and Cirrus outflow.
Sensor Package
The breakout group identified the
following sensors (or capabilities)
required to complete this mission:
1.
2.
3.
4.
5.
6.
7.
8.
9.
10.
11.
12.
13.
Instrument/Measurement
Cloud and aerosol lidar
Doppler radar
Optical imager
95 GHz radar
Nav data (from the aircraft)
Temperature profiler
Water vapor lidar
Broadband UV-IR radiometer
FTIR radiometer
Microwave radiometer
Lightning detection
Temperature profiler
On our board, we indicated the priority for each of these
instruments. H means high, M is medium, and L is low. For
the three lower-flying platforms, we have extra space but we
are a little bit overweight (about 10-15%). Many of these
sensors will be smaller in five years. The real problem we
have is power, and there’s not much we can do about it in
the instruments. Many of the probes hang outside the UAV,
they need to be de-iced, and that required power. The
aircraft guys have to give us more power – up to 5.7 KW.
Civil UAV Capabilities Assessment
Workshop 3 • Akron, Ohio • April 26–28, 2004
27
Mission: Cloud, Aerosol, Water Vapor, & Total Water
Sensors/Instrumentation
Instrument/Measurement
Cloud and aerosol lidar
Doppler radar
Optical imager
95 GHz radar
Nav data (f rom the aircraf t)
Temperature prof iler
Water v apor lidar
Broadband UV-IR radiometer
FTIR radiometer
Microwav e radiometer
Lightning detection
Instrument/Measurement
CO
Ozone
CO2
Water v apor
Priority
H
M
H
H
L
M
M
M
M
M
Priority
H
H
H
H
Ice nuclei
H
CN
H
CCN
H
Aerosol size: 0.01-3 um; 3 um-1.5 mm
MMS
M
M
Aerosol composition
H
Notes
Heritage
CPL
GSFC EDOP
MODIS airborne simulator
GSFC CRS
JPL MTP
DLR solid state wv lidar
Notes
Liquid N2
Inlet
Inlet
External mirrors
Special inlet
requirements
Special inlet
requirements
Special inlet
requirements
Heritage
ARC Argus
NOAA O3
HU CO2
JPL JLH
Volume
(cu ft) Mass (lbs)
8
150
12
400
1
22
1.2
400
Power
Acceptable
(kW)
Autonomous
as is?
0.5
Y
N
1.5
0.1
1.5
0.7
40
35
1000
0.3
2
2
1
65.9
50
10
2067
0.5
0.1
6.5
N
3
150
1.5
n
Generic
1
15
0.1
y
3
100
0.25
y
3
0.5
200
20
0.75
0.25
y
y
0.5
16.5
20
755
0.1
4.35
y
DMT CCN
NMASS+PCASP
External probes +CAPS
External probes ARC MMS
Special inlet
requirements Generic
Power
(kW)
5
N
State of the Art
Volume
Power
Acceptable
(cu ft) Mass (lbs)
(kW)
Autonomous
as is?
2
80
0.3
y
1
25
0.3
y
1.5
125
0.5
y
1
20
0.3
y
CSU IN
Volume
(cu ft) Mass (lbs)
20
600
Target for Technology
Volume
Power
(cu ft) Mass (lbs)
(kW)
55
660
3
In the remote UAV, the numbers are huge. We need 16 cubic feet, 755 pounds, and 4.35KW. We hope that the next generation of
instruments will combine the functions of multiple instruments of today - this would save us on weight and power demands. Let’s combine
the LIDARs and the RADARs as much as possible. If we can do this, we get much closer on all of the parameters for today’s high flyer.
There are some integration issues that we need to consider. Some instruments need to be easily accessed after a flight. Some detectors
need to be cooled with liquid nitrogen. Many instruments have external parts (probes, optical windows, etc.), and these parts need to be
accommodated by the platform. The water vapor detection inside the convective system might be problematic.
Civil UAV Capabilities Assessment
Workshop 3 • Akron, Ohio • April 26–28, 2004
28
Mission: Cloud, Aerosol, Water Vapor, & Total Water
Sensors/Instrumentation
Instrument/Measurement
Water v apor
Priority
H
Notes
Heritage
External mirrors
JLH
Special inlet; large dry
gas f low
NCAR/OSU CVI
External probes
ARC MMS
NMASS+PCASP+
External probes
CAPS
External probe
SPEC, inc CPI
Liquid N2 and inlet
required
JPL ALIAS
External probe
Gerber/UU CIN
Optical windows
ARC/CU SSFR
External inlet
NOAA O3
Condensed water content
MMS
H
M
Aerosol size: 0.01um-1.5 mm
Particle habit
M
H
Water isotopes
Cloud extinction
Upward and downward radiativ e f luxes
O3
M
L
L
H
CO, CH4
CO2
Temperature prof iler
H
H
L
External inlet; Liquid N2ARC Argus
External inlet
HU CO2
JPL MTP
H
Coupled to condensed
water content
instrument (i.e.,
downstream pickof f )
Ice nuclei composition
Instrument/Measurement
Particle habit
Priority
H
Condensed water content
CN
CCN
H
M
M
Aerosol size: 0.01um-1.5 mm
Ice nuclei
Cloud extinction
MMS
M
M
L
H
Water v apor
O3
H
M
CO
CO2
M
M
Notes
Heritage
External probe
SPEC CPI
Special inlet; large dry
gas f low
NCAR/OSU CVI
Special inlet
Generic
Special inlet
DMT CCN
NMASS+PCASP
External probe
+CAPS
Special inlet
CSU IN
External probe
CIN
External probes
ARC MMS
cloud tolerant; external
mirrors required
LaRC
Inlet
NOAA
Inlet; Liquid N2 and cal
gas
ARC Argus
Inlet; cal gas
HU CO2
State of the Art
Volume
Power
Acceptable
(cu ft) Mass (lbs)
(kW)
Autonomous
as is?
1
20
0.3
10
0.5
183
20
1.1
0.25
3
1
200
25
0.75
0.1
2
1
1
1
120
22
20
25
0.5
0.2
0.5
0.3
2
1.5
0.7
80
125
35
0.3
0.5
0.3
0
24.7
10
885
0.05
5.15
State of the Art
Volume
Power
Acceptable
(cu ft) Mass (lbs)
(kW)
Autonomous
as is?
1
25
0.1
10
1
3
183
15
100
1.1
0.1
0.25
3
3
1
0.5
200
150
22
20
0.75
1.5
0.2
0.25
1
1
20
25
0.3
0.3
2
1.5
28
80
125
965
0.3
0.5
5.65
Civil UAV Capabilities Assessment
Workshop 3 • Akron, Ohio • April 26–28, 2004
Target for Technology
Volume
Power
(cu ft) Mass (lbs)
(kW)
55
660
3
Target for Technology
Volume
Power
(cu ft) Mass (lbs)
(kW)
55
660
3
29
Mission: Cloud, Aerosol, Water Vapor, & Total Water
Power & Propulsion
Performance Specifications
Flight Characteristics
1. Altitude: 20-40,000’ / 40-60,000’
2. Range: 22,000 Nautical miles
3. Payload mass: 1600lbs
4. Payload power: 10kw
5. Propulsion power: De-icing capability
(heators); defogging capability; low nox
propulsion
6. Endurance: 3-5 days
7. Speed: 165’/sec 50’/sec downdraft
8. Mission Frequency: Current frequencey 4
- 6 week observation periods / year
•Slower is better - loiter over 1 spot
•Convective flyer is more difficult
•Fly in formation over ocean at different
altitudes - long transits for profiling
•Mix of manned and unmanned vehicles
•Chemical measurements: clean, virgin
air
This is in a similar class as the mid-air
convective. The challenge here is not so much
in weight or power, it's more the gradient
updrafts and keeping the thing in control. It
might be similar to the hurricane mid-altitude
concerns too.
We have to make sure we don't get something
that sucks and wipes out the entire engine.
How much control authority are we going to
have in the engine face? Can we give you
enough power? We need to know more about
the power needs. It's tough to say how much of
a challenge this is.It could be that one of the
current UAVs with or without modifications
could handle this.
Civil UAV Capabilities Assessment
Workshop 3 • Akron, Ohio • April 26–28, 2004
30
Mission: Cloud, Aerosol, Water Vapor, & Total Water
Technology Development Opportunities
Active Microwave
95ghz Radar
Passive Radiometer
Passive Optical
Stereo Camera
Coupled with Lidar
Stabilized mount
Light weight, generic; include IMU
1. Lidars
(a) Combine water vapor and cloud/aerosol lidar and
(b) Add capability to cloud/aerosol lidar: make it a High Spectral Resolution Lidar
(HSRL) that measures
- extinction at 355 and 532 nm
- backscatter at 355, 532, and 1064 nm
This enables retrievals of aerosol effective radius, concentration, real and
imaginary refractive index, and single scatter albedo.
Optical window may be an integration/accommodation issue.
Active Optical
Target accommodations for combined instrument: 8 cf, 300 lbs, 1.5 kW
Water vapor lidar
2. Radars: Combine the two radars
High Spectral
Resolution Lidar
(HSRL)
for clouds and aerosol)
Ozone
This capability was missed in the
mission summary but was required
in the mission described in the July
2004 workshop
Target accommodations for combined instrument: 10 cf, 300 lbs, 1.5 kW
Windows/radomes may be an integration/accommodation issue.
3) On-board data analysis and interpretation
In-Situ
Total Water / condensed water
Optical detection, CVI weight & size reduction of on-board gas generation
Particle probe
Size & weight reduction
Particle
1-10μm resolution improvement; white light source, phase doppler
Condensed water phase discrimination
Civil UAV Capabilities Assessment
Workshop 3 • Akron, Ohio • April 26–28, 2004
31
Additional Investment Possibilities
Active Microwave Gap Filler
Vehicle Possibilities
Autonomous Flight Control <1m
Avionics (control, Active steering)
Autonomous Ops
Mission
Prop/power Generation
Key Challenge
HALE = HURR (remote) + cloud 14 days
Turbine
Batteries
IC engine
Fuel cell
Solar
Hybrids
Endurance
30 days
Lightweight antenna
- embedded T/R module
- material
- metrology (active)
- wavefront sensing
Solar Regeneration
Battery
Mid-altitude In-situ
Convective = cloud
1-2 days
Turbine? - distortion
IC engine
Environment
(gradient)
Antenna receivers < weight, metrology
0.5 m x 15m; 15m swath
Fire In-situ
Alt 10k ft. or lower
Turbine
IC engine
Environment
(T, gradient, soot)
Hurricane boundary layer
Alt = 300m (-20k ft?)
Turbine?
IC engine?
Need true
conditions
Options:
modularized
Factor of 2 reduction in power
Factor of 4 reduction in volume
Data storage and communication
Data Rate (1Gb/s, sampling rate; 180hz); ~3 TB;
OTH Communication)
In-Situ - other ideas
Engine-generated vacuum (ref to LaRC Tech report)
Engine heat for de-icing
Aerodynamically-efficient probes & inlets
Common calibration gases
Mission dependent power
Civil UAV Capabilities Assessment
Workshop 3 • Akron, Ohio • April 26–28, 2004
32
Additional Investment Possibilities
Active Optical
Ins trum e nt
WAG Cos t
Tim e
Tim e to De mo
(Le ss than full
capability)
O3+Aerosol (Backscatter)
$7M
4-5 years
2-3 years
HSRL
$5M
4 years
2-3 years
H2O
$7M
5 years
4 years
O3+HSRL
$8M
4-5 years
O3+HSRL+H2O
$9M
5 years
Winds (long range, pulsed,scanning) $10M
5 years
Winds (short range, CW)
$5M
3 years
CO2 (1%)
$10M
5 years
Very little water vapor lidar transmitter development ongoing at this time.
Funding needed in this area.
Inteferometric HSRL receiver technologies are not being developed in the US.
Work ongoing in Europe, but insight into progress and problems difficult to
obtain.
Civil UAV Capabilities Assessment
Workshop 3 • Akron, Ohio • April 26–28, 2004