Atmospheric Sampling with UAS for Storm Research · 2018. 11. 15. · Atmospheric Sampling with UAS...
Transcript of Atmospheric Sampling with UAS for Storm Research · 2018. 11. 15. · Atmospheric Sampling with UAS...
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Atmospheric Sampling with UAS for Storm Research
Alyssa Avery, Nick Foster, and Dr. Jamey Jacob
Oklahoma State University
ISARRA 2016May 24, 2016
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SUAS In Boundary Layer Meteorology
• Lowest part of the atmosphere (boundary layer) is directly influenced by terrain and diurnal cycle; includes heat transfer, pollution dispersion and advection, turbulence, agricultural, and urban meteorology
• Difficult to measure with radar, balloons, and towers
Accessible using SUAS
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System Concepts
Routine ProfilingLimited areaSlow responseSwarms
Event PatrolWide areaFaster responseDropsondes
Targeted ProfilesHigh altitudeRapid responseGlidersondes
Multi-Rotors
Fixed Wing
Rockets
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Profiling Prototypes
• GPS/IMU• Pressure,
Temp., Humidity• Winds aloft
(direction, magnitude)
• Turbulence
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Vertical Profiling
Bailey
• Development of automated profiling capabilities – short mission duration results in hot-swapping of platforms
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Autopilot Development
• Adaptive control algorithm to enable a “plug and play” type autopilot to minimize tuning and maximize stability – Bayesian non-parametric approach
• Organically accommodate advances in software, hardware, and communication system
A Multi-platform Plug and Adapt Autopilot System
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Glidersonde Concept
Atmospheric Sensor
Performance• Altitude : 5000 ft (1500 m)• Cruise Speed : 39 kias (20 m/s)• Stall Speed : 19 kias (9.8 m/s)• Endurance : 12 min
Glider• Weight : 0.5 lb (0.23 kg)• Length : 19.5in (50 cm)• Width : 3 in (7.6 cm)• Span : 24 in (61 cm)• Wing Area : 66 in2 (440 sq. cm)
Measurements• Velocity• Pressure• Relative Humidity• Temperature• Wind Speed• Wind Direction
GPS Antenna
Swing Wing
Folding Tail
*sample Windsonde data
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Rocket Deployment ConceptCO2 and piston assemblydischarge at max altitude
Rocketsonde & Gliderassembly launch to alt.
Gliders deploy with CO2 & piston and emerge from rocket airframe
Glider wing deploys and Windsonde probe emerges,
gliders return to launch
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MARIAMesocyclone Analysis Research Investigation Aircraft
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Mission ScenariosSupercell average size and structure
1. -Initiate flight hours prior to storm formation-Survey stationary grid prescribed by radar prediction, specifically around LCL- Land upon tornado formation of supercell dissipation
1. - Initiate flight hours prior to storm formation- Survey mobile boundary layer- Follow supercell or tornado outside downdraft sections- Land upon tornado or supercell dissipation
1. -Initiate flight upon supercell formation- Circle storm outside downdraft sections surveying at variable altitudes- Continue to survey after storm ends- Land when necessary
Range 500 miles (800 km) : Allows for approx. 6 laps around
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Mission Requirements
Aim: maximize the amount of information that can be gathered by a storm chasing• System should fit in a van or
truck and be able to deploy without a runway,
• The aircraft should fly from six to eight hours to gather a relatively well populated meteorological grid from the start of storm formation
• The vehicle should able to carry both meteorological sensors and EO/IR cameras.
• Deployable sensor packages• Boom mountable sensors out
of flow
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CONOPS
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Aircraft Layout
Fuel
Autopilot Dropsondes TAMDAR IR Camer
Hot wire, pitot, or 5 hole probe
GTOW: 35 lb (15 kg)Wing Area: 6.125 sqft (0.57 m^2)
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Onboard Sensors, Hot Wire
• Hot wire sensors• Measures turbulence with high
resolution• Inexpensive options currently being
explored
• Testing at OSU’s wind tunnel• Cylinder inserted into steady flow
Modern Device Wind Sensor Hot-wire Anemometer
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Onboard Sensors, TAMDAR
• Panasonic’s TAMDAR Edge• Small version UAS version of
Panasonic’s TAMDAR flown on many commercial aircraft
• Collects high resolution temperature, pressure, winds aloft, humidity, icing, and turbulence data
• All information used as part of a larger set of data for weather prediction and modeling
• Forecasting model: Real Time Four Dimensional Data Assimilation
• Requires clean flow out of prop wash
TAMDAR
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Onboard Sensors, Multi-hole Probe
• Manufactured five hole probe• Air speed, heading, alpha, beta
• Currently being developed at OSU
• 3D printed to reduce cost and improve robustness
• Testing • Calibration at AoA ±45 in wind
tunnel
• Further wind tunnel testing and aircraft integrated required
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Onboard Sensors, IR Camera
• IR Camera, DRS long wave IR camera• Requires gimbal and IR
transparent screen• Thermal imaging
• Testing• IR Cameras have been used in
UAS at OSU for precision agriculture
• Characterized using MATLAB software
• Provides distortion focal length, field of view, etc.
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Dropsondes
• Sensor packages will consist of pressure, temperature, humidity, wind sensor, and GPS
• Sensors are small inexpensive breakout boards that will send data through an Arduino board
• Data will be recorded onboard and send a radio signal to ground station
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Dropsonde Deployment
• Dropsondes are stored in the belly of the aircraft
• Rotating dispenser will drop them one at a time
• Parachute will be pulled from the dropsonde and allow the sensor package to be carried by weather formations
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Summary
• AV Sensors• TAMDAR Edge• Multi-hole Probe• Pitot Probe• Wind Sensor/Hot Wire • IR Camera
• Dropsonde Sensors• Barometric
Pressure/Temperature Sensor
• Humidity/Temperature Sensor
• Wind Sensor• GPS
COSTSTAMDAR GiftMulti-hole Probe In-houseIR Camera $2200Wind Sensor $24Dropsonde $110
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Flight Tests
• Flight tests gathered data with, Pitot, IMU, and GPS
• Test bed aircraftuses electric engines and landing gear
• Flights done at OSU’s flight field
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05.17.2016
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Cloudmap Flight Campaign
• June 27- July 1• OSU will be gathering data with
– MARIA
– Rocket launched glidersonde
– Quadcopter swarms
– Ground based sensors
• Testing Locations– OSU Flight Field
– Marina Site
– ARM Site
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Future Work
Immediate • Complete fully
operational MARIA• Complete sensor
integration on MARIA test airframe and operational airframe
• Rocket launched glidersonde system testing
Broad
• Optimize flight campaigns to collect the most pertinent data – Define most usual metrics for
successful data collection (data volume, length of time, magnitude of distance, etc.)
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Aircraft Specifications
Performance Predictions and Airframe Characteristics, Operational System
Stall speed 36 kts (67 kph)Maximum Speed 110kts (203 kph)
Cruise Speed 55 kts (102 kph)Endurance 8 hrs.
Service Ceiling 30,000 ft. (9100 m)Weight 35 lbs. (15 kg)
Span 7 ft. (2.1m) 0
5000
10000
15000
20000
25000
30000
35000
40000
0 25 50 75 100 125 150 175
Alti
tude
, ft
Velocity, knots
VstallVmax ReciprocatingCeiling ReciprocatingCeiling ElectricVmax Electric
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