Download Power and Propulsion Missions Details

Mission Session – Power &
Propulsion
April 26-28, 2005
Panel Discussion
Outline
• Review platform classes
– Use current examples
– Does not imply mission is done with these vehicles!
• Review missions
– Mission introduction
– Cycle through each mission, 20 minutes with Q & A
– Missions are conceptual in nature
• Inferences and assumptions may be required
• Document what is assumed
• Keep discussion flowing
• Sets the stage for technology session tomorrow
Daughter Ship Class
Length
Wingspan
Aspect Ratio
Weight
Endurance
Range
- w/ 2 hour loiter
Ceiling
Engine
Engine footprint
Engine Weight
Engine Power
5.25 feet (1.6 m)
8.6 feet
(2.62 m)
11.8
59 lbs
(27 kg)
10 hrs
403 miles / 350 nm / 648 km
50 mile / 43 nm / 80 km
15000 ft. (4.5 km)
---1.26 KW Electric
Propulsion
Engine SFC
Fuel Type
Fuel Capacity
Data Links
Speed
Electrical Power
Payload Wt.
(internal)
(volume)
--18. 2 lbs (8.3 kg)
-43.5 mph / 38 knots
70 kmh
180 Watts
13.5 lb (6.14 kg)
~ 0.482 ft3 or 0.0137 m3
Small UAV Class A
Length
Wingspan
Aspect Ratio
Weight (Empty)
(Launch)
Endurance
Range
Ceiling
Engine
Engine footprint
Engine Weight
6.2 feet
(1.9 m)
9.5 feet
(2.9 m)
15.3
18.1 lbs (8.2 kg)
33.1 lbs (15 kg)
30 hrs +
1800 miles /
1564 nm (2897 km)
up to 21,000 ft.
(med weight)
24cc Fuel Injected
Piston Powered
---
Engine Power
Engine SFC
Fuel Type
Fuel Capacity
Data Links
Speed
Electrical Power
Payload Wt.
(internal)
(volume)
1.2 KW
-Premium Unleaded
Gasoline
11 lbs / 5 kg (1.7 gallons)
UHF (uplink)
Sat (downlink)
47- 92 mph / 41- 80 kts /
76-148 kmh
50 Watts
5 lb (2.27 kg) w/ full fuel or
11 lb (5 kg) max
0.482 ft3 or 0.0137 m3
Small UAV Class B
Length
Wingspan
Aspect Ratio
Weight (Empty)
(Gross)
Endurance
Range
Ceiling
Engine
Engine footprint
Engine Weight
12 feet (3.66 m)
12 feet (3.66 m)
13
30 lbs (13.6 kg)
55 lbs (25 kg)
8 hours
~ 600 miles / 521 nm
(966 km)
9000 ft (2744 m)
Fuji BT- 86 Twin Cyl
(2 stroke)
0.368 ft3 (0.0104 m3)
6.2 lbs (2.8 kg)
Engine Power
Engine SFC
Fuel Type
Fuel Capacity
Data Links
Speed
Electrical Power
Payload Wt.
(Internal)
(volume)
7.5 hp @ max RPM
2 oz./min @ max RPM
40:1 Gasoline/Oil Mix
12 lbs
UHF (uplink/downlink)
45-90 mph / 39-78 knots /
145 kmh
N/A
22 lbs (10 kg)
1.01 ft3 (0.0286 m3)
Medium UAV Class
Length
Wingspan
Aspect Ratio
Weight (empty)
(max T/O)
Endurance
Range
Ceiling
Engine
Engine footprint
Engine Weight
Engine Power
36 feet (11 m)
66 feet (20.12 m)
16
3050 lb (1380 kg)
10000 lbs (4,536 kg)
32 hrs (clean)
24 hrs (w/ external stores)
2250 nm (4630 km)
50000 ft (15.2 km)
Honeywell TPE 331-10T
2.18 ft. DIA (0.66 m)
x 3.9 ft. (0.84 m) length
385 lbs (175 kg)
995 HP (746 KW) @ takeoff
Engine SFC
Fuel Type
Fuel Capacity
Data Links
Speed
Electrical Power
Payload Wt.
(Internal)
(External)
- 2 Inboard hardpts
- 2 center hardpts
- 2 outboard hardpts
(volume)
0.56 lb/h/shp @ takeoff
Jet A
3500 lbs (1588 kg)
Satcom: UHF/Ku-Band
LOS: C-Band
259 mph / 225 knots/ 416 kph
4.5 KW
800 lbs (363 kg)
3000 lbs (1364 kg)
1500 lbs (680 kg)
350 lbs (159 kg)
150 lbs (68 kg)
46 ft3 (1.3 m3)
Large UAV Class
Length
Wingspan
Aspect Ratio
Weight (empty)
(max T/O)
Endurance
Range
Ceiling
Engine
Engine footprint
Engine Weight
44.4 ft.
(13.53 m)
116 feet (34.8 m)
25
8940 lbs (4,055 kg)
25600 lbs (11,612 kg)
35 Hours
12000 nm (22224 km)
65000 ft. (19.5 km)
Rolls Royce-Allison
AE3007H turbofan
(5:1 bypass ratio)
3.21 ft. (0.98 m) DIA
x 8.9 ft. (2.7m) Length
1581 lbs (717.1 kg)
Engine Power
Engine SFC
Fuel Type
Fuel Capacity
Data Links
Speed
Electrical Power
Payload Wt.
(internal)
(external)
(volume)
33.8 KN, 7600 lb static
thrust at sea level
0.38 lb/s/lb @ takeoff
JP-8
14,700 lbs (6,668 kg)
Satcom: UHF/Ku-Band
LOS: UHF and CDL
391 mph (340 knots/630 kmh)
10 KVA
2000 lbs (909 kg) or
2000 lbs (909 kg)
2 (1000 lb) wing hard points
~ 150 ft3 (1.3 m3)
Very Long Endurance UAV Class
Length
Wingspan
Aspect Ratio
Weight (Gross)
(Empty)
Endurance
Range
Ceiling
Engine footprint
Engine Weight
Engine Power
Engine SFC
12 feet
(3.6 m)
250 feet (75.1 m)
25.75
1600 lbs (727.3 kg)
1322 lbs (601 kg)
168 hrs. (1 week)
-100 K ft. (30 km)
~ 3 ft3 (0.914 m3)
per engine
~ 12-13 lbs per motor
(182 lbs or 82.7 kg total)
2 hp or 1.5 KW per motor
N/A
Fuel Type
Fuel Capacity
Data Links
Speed
Electrical Power
Payload Wt.
(internal)
(external)
(volume)
Electric
N/A
S (Downlink) and L Band (Uplink)
19-27 mph / 17-23 knots / 43.5 kmh
- low altitude
170 mph / 148 knots / 274 kmh
- high altitude
1 KW @ 100 K ft. (30 km)
5 KW @ 60 K ft. (18 km)
100 lbs (45.5 kg) @ 100 K ft. (30 km)
600 lbs (272.7 kg) @ 70 K ft. (21 km)
5 pods additional space
~ 20 ft3 (0.567 m3)
Mission Characteristics
•
Six Mission descriptions provided:
–
–
–
–
–
–
•
Hurricane Genesis, Evolution, and Landfall
Cloud, Aerosol, Water Vapor, and Total Water Measurements
Active Fire, Emissions, and Plume Assessment
Southern Ocean Carbon Cycle
Antarctic Explorer (Cyrosphere)
Vegetation Structure, Composition, and Canopy Chemistry
Assumptions across all missions
–
–
–
–
OTH network centric communications
‘File and fly’ access to airspace
‘Plug and Play’ open architecture
Capable of 100% nominal autonomous sensor operation
Hurricane Genesis,
Evolution and Landfall
•
Science objective: Observation of hurricanes to improve predictions of
hurricane paths and landfall.
•
Remote, high altitude measurements:
- Electrical activity
- Precipitation
- Clouds
- Meteorological sounding
•
- Microphysics
- Dust
Tropospheric measurements:
- 4-D thermodynamics
- Winds
•
Boundary Layer:
- Sea surface temperature
- Surface winds
- Surface imaging
- Turbulent flux
- Surface state: wave spectra, sea
spume, etc
Hurricane Genesis,
Evolution and Landfall
•
High altitude, Mother Ship UAV: Very Long Endurance Platform
- GPS reflectance: surface wave spectra
- Optical Imager: lightning
- Meteorological sonde
- Lidar: surface wave spectra
- Daughter ships
- Sounder: water vapor and temperature
- Radar: cloud and precipitation - Radiometer: cloud and precipitation
– Payload: 1000 lbs, 100 – 200 ft3, 1 – 2 kW
•
Tropospheric UAV: Daughter Platform
- Microphysics (typical of drop-sondes, thermodynamics)
– Payload: ???
•
Boundary layer UAV: Small Platform
- Infrared pyrometer: SST
- Meteorological sonde: in-situ
- Winds
- XRBT thermocline
- Optical imager: surface imaging
- Turbulence flux
– Payload: ???
Hurricane
Hurricane Genesis,
Evolution and Landfall
• Key mission characteristics:
– High Altitude, Long Endurance
• Remote mother platform: 65K ft / 2-3 weeks
–
–
–
–
–
Daughter ships => deploy/retrieve
Formation (coordinated) flight
Multi-ship operation
Quick turn-around
Re-tasking mission during flight
• Satellite data
• Remote, mother platform observations
• Scientist
– Payload directed flight
– Terrain avoidance
• boundary layer platform
Cloud, Aerosol, Water Vapor,
and Total Water Measurements
• Science objective: study transformations of aerosols and gases in
following cloud systems
–
–
–
–
–
–
Convective systems
Sea breeze cloud formation
Marine stratiform
Contrails in the Central U.S. in air traffic regions
Synoptic scale systems & Fronts
Cirrus outflow
• Measurement
- Water vapor, total water, water isotopes - Lightning
- Temperature
- Aerosols and cloud particles
- Pressure
- Winds
- Ozone
- Source gases and tracers
- IR radiance
- Radicals
Cloud, Aerosol, Water Vapor
and Total Water Measurements
• Cloud and aerosol particles
–
–
–
–
Chemical composition
Number, size, volume
Habit
Extinction and absorption
• Source gases and tracers
– Hydrocarbons, Formaldehyde
- HN03, NOy, CO2, CO, HCl, CH3I, HCl
- Sulfur species (e.g. H2SO4, SO2)
• Radicals
– NO, NO2, OH
– HO2, RO2
Cloud, Aerosol, Water Vapor,
and Total Water Measurements
• In-flow & out-flow in-situ UAV: Medium platform
– Lidar, Microwave, Doppler Radar, FTIR, Ultra-violet spectrometer (UV-Vis),
atmospheric samplers
– Payload: 1600 lbs, 180 ft3, 10 kW
• Convective in-situ UAV: Medium platform
– Lidar, Microwave, Doppler Radar, FTIR, Ultra-violet spectrometer (UV-Vis),
Electrical Activity
– Payload: 1600 lbs, 180 ft3, 10 kW
• Remote UAV: Very Long Endurance platform
– Lidar, Microwave, Doppler Radar, Drop-sonde, FTIR , Optical Imager, UV-Vis, 95
GHz radar
– Payload: 1600 lbs, 180 ft3, 10 kW
Cloud, Aerosol, Water Vapor,
and Total Water Measurements
• Sensor Measurements
- Lidar #1 - water vapor
- Lidar #2 – temperature, ozone, aerosol and cloud particles
- Microwave – temperature
- Doppler radar – winds
- UV-Vis - ozone
- FTIR – ozone, IR radiance
- Optical imager – lightning
- 95 Ghz radar – aerosol and cloud particles (ice water
content)
- Atmospheric samplers – cloud and aerosol particles,
source gases and tracers, radicals
Cloud, Aerosol, Water Vapor, and Total Water
Measurements, cont’d
Cloud, Aerosol, Water Vapor,
and Total Water Measurements
• Key mission characteristics:
– High altitude, long endurance
• 3 – 5 days
– All weather
• Convective in-situ platform
– Range: 22,000 nmi
– Terrain avoidance
• In-flow in-situ platform
–
–
–
–
Formation (coordinated) flight
Multi-ship operations
Quick turn around
Re-tasking mission during flight
• Remote platform observations
• Weather, cloud, chemical forecasts
– Vertical profiling
– Payload directed flight
– 4 week campaign with 2 -3 flights
Active Fire, Emissions,
and Plume Assessment
• Science objective: understand the influence of an
active fire on carbon cycle dynamics
• Measurements:
–
–
–
–
Atmospheric chemistry
Thermal intensity time-series
Plume composition: volume, albedo, particle size distribution
Fuel type and quality
Active Fire, Emissions,
and Plume Assessment
• Remote UAV: Medium or Large platform
– Imaging Spectrometer [thermal, midwave, shortwave IR]
•
•
•
•
Hyperspectral (350 – 2500 nm)
Downword looking port
5 – 20m horizontal, 5 – 50 km swath
< 50 kg weight
– Lidar
•
•
•
•
•
Resolution: .05 – 20 micron
Downword looking port
1 m horizontal, 15 cm vertical
< 3 km swath
30 kg weight
- Payload: 130 lbs, 10 – 30 ft3, .8 kW
• In-situ UAV: Medium platform
– Isotope ratio mass spectrometers
– Gas chromatographer
– Non-dispersive infrared (IR) analyzer
– Payload: 200 lbs
Active Fire, Emissions, and Plume Assessment, cont’d
Active Fire, Emissions,
and Plume Assessment
• Key mission characteristics:
– Endurance: 24 – 72 hours
– All weather
• In-situ platform flies in plume of fire
–
–
–
–
–
–
Formation (coordinated) flying
Multi-ship operations
Quick deployment / Quick turn-around
Re-tasking mission during flight
Payload directed flight
Engine emissions can’t affect measurements
Southern Ocean Carbon Cycle
•
Science objective: local to regional sea-air flux
measurements that reduce uncertainty in
global measurements and models of
CO2 flux
•
Measurements
–
–
–
–
Measure winds
CO2
Sea state (obstacle avoidance)
Surface temperature
Southern Ocean Carbon Cycle
• UAV: small platform
- CO2 sensor (1 sample/m @ 150 m/sec)
- INU & GPS
- Hydrometer
- Radiometer
- Ocean optics spectrometer
- Hyper-spectral radiometer
- Interferometer
- Payload: 66 lbs, .7 ft3, .25 kW
Southern Ocean Carbon Cycle, cont’d
Southern Ocean Carbon Cycle
• Key mission characteristics:
–
–
–
–
–
Endurance: 48 hr
Low altitude flight: < 10K ft
Coordinated flight (swarm)
Multi-ship operations
Re-tasking mission during flight
• Sensor payload
• Satellite data
• Model forecasts
– Vertical profiling
– Remote base operation (potentially ships)
– Payload directed flight
Antarctic Explorer (Cryosphere)
• Science objective:
– Provide data for validating simulations of the dynamics
of ice and land topography, iceberg volume, glacier
profiles and glacier channel profiles
– Provide data on the effect on the ocean environment
• Measurements
- Time dependence of ice and land topography
- Coastal and open ocean salinity temperature, and currents, at
surface and beneath iceberg depths
- Time evolution of targeted iceberg freeboard volume, land glacier
profiles, and glacier channel profiles
- Atmospheric boundary layer observations at high space/time
resolution
Antarctic Explorer
• UAV: Medium or Large platform
- Optical imager
- Magnetometer
- Radar depth sounder: ice sheet thickness
- Drop-buoys: sea salinity, currents (at surface and beneath
iceberg depths), temperature
- Scanning Lidar: topographic mapping
- Payload: 1000 lbs, 10 – 20 ft3, .5 kW
Antarctic Explorer, cont’d
Antarctic Explorer
• Key mission characteristics:
–
–
–
–
–
–
–
Endurance: > 12 hr on-station (low altitude)
Range: Antarctic continent
All weather
Terrain avoidance
Quick deploy
Quick turn around
Re-tasking mission during flight
• Dynamic event, e.g. ice shelf break-up
– Remote base operations
– One mission every 3 days for 2 months, during ice
break-ups
Vegetation Structure, Composition,
and Canopy Chemistry
• Science objective: Provide 3-dimensional vegetation structure
and information on composition and
chemistry
• Measurements
– Terrestrial biomass
– Leaf-level chemistry (eg. lignin, xanthophylls, etc.)
– Water canopy content
Vegetation Structure, Composition,
and Canopy Chemistry
•
UAV 1: Medium Platform
–
Synthetic aperature radar (L=structure)
• 5-10m horizontal; 1m vertical
• 5-20km swath
• single pass interferometry
– Payload: 630 lbs, 30 ft3, 2 – 3 kW
•
UAV 2: Medium Platform
– Synthetic aperature radar
(p=ground return)
• 5-10m horizontal; 1m vertical
• 5-20km swath
• single pass interferometry
– Imaging spectrometer
• Hyperspectral (350nm-2500nm), 10nm
channels
• downward-looking port
• 5-20m horizontal
• 5-50km swath
– Payload: 760 lbs, 45 ft3, 2.2 – 3.7 kW
•
UAV 3: Medium Platform
– Synthetic aperature radar
(x=top of canopy)
– Lidar
• 2 frequency (525m, 1050nm),
waveform digitized
• downward-looking port
• 1m horizontal; 15cm vertical
– Payload: 700 lbs, 35 ft3, 2.6 – 3.6
kW
Vegetation Structure, Composition, and Canopy Chemistry, cont’d
Vegetation Structure, Composition,
and Canopy Chemistry
• Key mission characteristics:
–
–
–
–
Endurance: 12 – 24 hr
Formation (coordinated) flight
Multi-ship operations
Flights weekly during seasons of interest
Logistics
• Meet 8:00 am tomorrow at Ballroom A
• Shortly after will split:
– Sensor track: Room 335
– Power and Propulsion Track: Room 312