mission session – power & propulsion april 26-28, 2005 panel discussion

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 5.25 feet (1.6 m)Wingspan 8.6 feet (2.62 m)Aspect Ratio 11.8Weight 59 lbs (27 kg)Endurance 10 hrsRange 403 miles / 350 nm / 648 km- w/ 2 hour loiter 50 mile / 43 nm / 80 kmCeiling 15000 ft. (4.5 km)Engine -- Engine footprint --Engine Weight --Engine Power 1.26 KW Electric

Propulsion

Engine SFC --Fuel Type --Fuel Capacity 18. 2 lbs (8.3 kg)Data Links --Speed 43.5 mph / 38 knots

70 kmhElectrical Power 180 Watts Payload Wt. (internal) 13.5 lb (6.14 kg)

(volume) ~ 0.482 ft3 or 0.0137 m3

Small UAV Class A

Length 6.2 feet (1.9 m)Wingspan 9.5 feet (2.9 m)Aspect Ratio 15.3Weight (Empty) 18.1 lbs (8.2 kg) (Launch) 33.1 lbs (15 kg)Endurance 30 hrs +Range 1800 miles /

1564 nm (2897 km)Ceiling up to 21,000 ft.

(med weight)Engine 24cc Fuel Injected

Piston PoweredEngine footprint --Engine Weight --

Engine Power 1.2 KWEngine SFC --Fuel Type Premium Unleaded

GasolineFuel Capacity 11 lbs / 5 kg (1.7 gallons)Data Links UHF (uplink)

Sat (downlink)Speed 47- 92 mph / 41- 80 kts /

76-148 kmh

Electrical Power 50 WattsPayload Wt. (internal) 5 lb (2.27 kg) w/ full fuel or

11 lb (5 kg) max(volume) 0.482 ft3 or 0.0137 m3

Small UAV Class B

Length 12 feet (3.66 m)Wingspan 12 feet (3.66 m)Aspect Ratio 13Weight (Empty) 30 lbs (13.6 kg) (Gross) 55 lbs (25 kg)Endurance 8 hoursRange ~ 600 miles / 521 nm

(966 km)Ceiling 9000 ft (2744 m)Engine Fuji BT- 86 Twin Cyl

(2 stroke)Engine footprint 0.368 ft3 (0.0104 m3)Engine Weight 6.2 lbs (2.8 kg)

Engine Power 7.5 hp @ max RPMEngine SFC 2 oz./min @ max RPMFuel Type 40:1 Gasoline/Oil MixFuel Capacity 12 lbsData Links UHF (uplink/downlink)Speed 45-90 mph / 39-78 knots /

145 kmh Electrical Power N/APayload Wt.(Internal) 22 lbs (10 kg)(volume) 1.01 ft3 (0.0286 m3)

Medium UAV Class

Length 36 feet (11 m)Wingspan 66 feet (20.12 m)Aspect Ratio 16

Weight (empty) 3050 lb (1380 kg) (max T/O) 10000 lbs (4,536 kg)Endurance 32 hrs (clean)

24 hrs (w/ external stores)Range 2250 nm (4630 km) Ceiling 50000 ft (15.2 km)Engine Honeywell TPE 331-10T Engine footprint 2.18 ft. DIA (0.66 m)

x 3.9 ft. (0.84 m) lengthEngine Weight 385 lbs (175 kg)Engine Power 995 HP (746 KW) @ takeoff

Engine SFC 0.56 lb/h/shp @ takeoffFuel Type Jet AFuel Capacity 3500 lbs (1588 kg)Data Links Satcom: UHF/Ku-Band

LOS: C-Band Speed 259 mph / 225 knots/ 416 kphElectrical Power 4.5 KWPayload Wt.(Internal) 800 lbs (363 kg)(External) 3000 lbs (1364 kg)- 2 Inboard hardpts 1500 lbs (680 kg)- 2 center hardpts 350 lbs (159 kg)- 2 outboard hardpts 150 lbs (68 kg)(volume) 46 ft3 (1.3 m3)

Large UAV Class

Length 44.4 ft. (13.53 m)Wingspan 116 feet (34.8 m)Aspect Ratio 25Weight (empty) 8940 lbs (4,055 kg) (max T/O) 25600 lbs (11,612 kg)Endurance 35 HoursRange 12000 nm (22224 km)Ceiling 65000 ft. (19.5 km)Engine Rolls Royce-Allison

AE3007H turbofan (5:1 bypass ratio)

Engine footprint 3.21 ft. (0.98 m) DIA x 8.9 ft. (2.7m) Length

Engine Weight 1581 lbs (717.1 kg)

Engine Power 33.8 KN, 7600 lb staticthrust at sea level

Engine SFC 0.38 lb/s/lb @ takeoffFuel Type JP-8Fuel Capacity 14,700 lbs (6,668 kg)Data Links Satcom: UHF/Ku-Band

LOS: UHF and CDLSpeed 391 mph (340 knots/630 kmh) Electrical Power 10 KVAPayload Wt. (internal) 2000 lbs (909 kg) or (external) 2000 lbs (909 kg)

2 (1000 lb) wing hard points(volume) ~ 150 ft3 (1.3 m3)

Very Long Endurance UAV Class

Length 12 feet (3.6 m)Wingspan 250 feet (75.1 m)Aspect Ratio 25.75Weight (Gross) 1600 lbs (727.3 kg) (Empty) 1322 lbs (601 kg) Endurance 168 hrs. (1 week)Range --Ceiling 100 K ft. (30 km)Engine footprint ~ 3 ft3 (0.914 m3)

per engineEngine Weight ~ 12-13 lbs per motor

(182 lbs or 82.7 kg total)Engine Power 2 hp or 1.5 KW per motorEngine SFC N/A

Fuel Type ElectricFuel Capacity N/AData Links S (Downlink) and L Band (Uplink)Speed 19-27 mph / 17-23 knots / 43.5 kmh

- low altitude170 mph / 148 knots / 274 kmh- high altitude

Electrical Power 1 KW @ 100 K ft. (30 km)5 KW @ 60 K ft. (18 km)

Payload Wt. (internal) 100 lbs (45.5 kg) @ 100 K ft. (30 km)

600 lbs (272.7 kg) @ 70 K ft. (21 km)(external) 5 pods additional space (volume) ~ 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:

• Tropospheric measurements:

• Boundary Layer:

- Precipitation- Clouds- Meteorological sounding

- Electrical activity- Microphysics- Dust

- 4-D thermodynamics

- Winds

- Sea surface temperature

- Surface winds

- Surface imaging

- Turbulent flux

- Surface state: wave spectra, sea spume, etc


• High altitude, Mother Ship UAV: Very Long Endurance Platform

– 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

– Payload: ???

- Optical Imager: lightning

- Meteorological sonde

- Daughter ships

- Radar: cloud and precipitation

- GPS reflectance: surface wave spectra

- Lidar: surface wave spectra

- Sounder: water vapor and temperature

- Radiometer: cloud and precipitation

- Infrared pyrometer: SST

- Winds

- Optical imager: surface imaging

- Meteorological sonde: in-situ

- XRBT thermocline

- Turbulence flux

Hurricane


• 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

- Temperature

- Pressure

- Winds

- Ozone

- Lightning

- Aerosols and cloud particles

- 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


• 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

- 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


• Sensor Measurements

Cloud, Aerosol, Water Vapor, and Total Water Measurements, cont’d


• 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

• 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


• 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

• 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


• 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


• 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

• 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

mission session – power & propulsion april 26-28, 2005 panel discussion

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