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Proprietary
BalloonWinds Update
Author: Ivan Dors – UNH([email protected])
Presented By: Michael Dehring -- MAC28 June 2006
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Overview
• Big Picture
• Mission Objectives
• Flight Objectives
• Instrument Status
• Summary
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Big Picture
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Big Picture
• Demonstrate direct-detection Doppler LIDAR technologies from 30 km above the Earth
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Flight Timeline
0
10
20
30
40
0 2 4 6 8 10 12 14
Time (Hr)
Altitude(km)
Mission Timeline
1. Liftoff - System Startup2. Emit Laser and Signal Fiber Alignment3. Flight Altitude Checkout4. Eight-Hour Data Collection5. Extended Data Collection (resources/weather)6. Descent
1. Liftoff - System Startup2. Emit Laser and Signal Fiber Alignment3. Flight Altitude Checkout4. Eight-Hour Data Collection5. Extended Data Collection (resources/weather)6. Descent
1 2 3 6
4 5
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Partial Inflation
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Ready For Launch
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Balloon Release
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Launch
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Balloon & Payload at Float Altitude
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Mission Objectives
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Mission Objectives
• Demonstrate direct-detection Doppler LIDAR fringe imaging from a high-altitude downward-looking platform
• Validate instrument performance models and atmospheric models @ 355 nm
• Assess the scalability of key subsystems to a space-borne Doppler LIDAR instrument
• Scale performance to a space-borne LIDAR
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Mission ObjectivesModel Validation
AtmosphereModel
Laser-TelescopeModel
Optics-CameraModel
Wind UncertaintyModel
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Flight Objectives
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Flight Objectives
Flight #
Objective Atm. Condition
Mission Date
1 Nighttime Concept
Demonstration
Night
Clear Air
09/06
2 Daytime Concept Demonstration
Day
Partly Cloudy
10/06
3 Full GTWS Demonstration
Day & Night Partly Cloudy
Autumn
05/07
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Flight I Objectives
Demonstrate the electrical, thermal, mechanical, and optical performance of the integrated instrument for nighttime flight conditions
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Flight II Objectives
Demonstrate the ability to operate during the daytime given the additional thermal load and the increased optical background
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Flight III Objectives
Demonstrate
Photometric measurement
Spectral measurement
Velocity measurement
Validate
Space instrument model
Subsystem scalability
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Flight I &II Priorities
•Engineering
•Optical Performance
•Photometric Return
•Aerosol-molecular ratio
•Velocity
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Instrument Status
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System Status
• Instrument is integrated to the gondola• Post-integration tests are being performed
– Thermal system– Pressure chambers & mechanical system– Power distribution system– Instrument health monitoring– Control system– Instrument & optical system– Data & communication system
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Ground Station
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Mass Budget
Budget [kg] As Built [kg]Laser Telescope Assembly 285 310Interferometer Enclosure 192 250Control Enclosure 302 333Cooling System 380 400Power Distribution 312 475AFRL Systems 90 90 (est)Ballast (10% of total mass) 200 231Gondola Structure 400 435
Total 2161 2542
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Power Budget
Budget [W] As Built [W]Laser Enclosure 492 271Interferometer Enclosure 80 80Control Enclosure 674 495Power System 10 9Coolant Pump 50 78
Total 1306 933
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Thermal System
• Additional heating pads added for ascent
• Excess heat dissipated with ~0.2 m3 ice
• Heat transferred with Propylene Glycol/DI Water 50%
• Temperature control loops operational
• System allows for 12+ hours of operation
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Telemetry Data
• 65 Temperature Sensors• 10 Pressure Sensors• 3 Fluid Flow Sensors• 46 Current Monitors• 2 Voltage Monitors• 11 Fan Speed Monitors• 2 GPS Sensors• 2 Attitude Sensors• 2 Decompression Sensors
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Telemetry Display
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Telemetry Graphs
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Laser Chamber Status
• Power steady at 3W (exiting chamber)
• Seeding stable
• Beam profile unchanged
• Beam steerer, shutters, attenuator, and reference injection are operational
• Heater pads added for thermal stability on ascent
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Laser-Telescope Status
TelescopeFocus
Laser Exit
70.6120
Y
X'
Y'
X
45
25
"Rotate" the Beam SteeringAxis by ~25deg CW to coincidewith the Laser /Telescope Axis
Y X
BeamSteering
Axis
Laser/Telescope Y
' Axis
Ch 5Ch1
Ch3
Ch 6
Ch0
Ch4 - aerooutput
Ch7
Ch2
aqua
blue
blue
blue
red redred
yellow
Purple
white
• Alignment routines are operational and are being refined– Beam finding
– Outer-fiber signal characterization
– Alignment maintaining
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Laser-Telescope Status
• Fixture used to test laser-telescope misalignments
• System aligned in up- and down-looking positions
• Misalignments <15% of steerer range– Fixture was the main
cause
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Interferometer Status
• Finesse– A-Channel: 5.6
– M-Channel: 6.3
• Recycling– A-Channel: 2.1
– M-Channel: 1.9
• Reference row– A-Channel: 10
– M-Channel: 12
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System MeasurementComparison
Pre-Ship Post-Ship
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Instrument StatusIntegrated Picture 1
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Instrument StatusIntegrated Picture 2
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Instrument StatusIntegrated Picture 3
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Scheduled Tests
• Mission Simulated Operations (July: UNH)– Dress rehearsal– Review complete flight timeline– Formally assign roles– Test operating procedures in real time– Test problem recovery procedures
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Scheduled Tests
• Lift Test (July: UNH)– Use a crane to lift the gondola– Test gondola structural integrity– Test opto-mechanics & alignment
• Laser-telescope system
• Interferometer
– Make measurements with swing and rotation
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Scheduled Tests
• Environmental Test (Aug: Kirtland AFB)– Flight profile in real time– No solar loading or radiation losses
• Effects have been calculated
• Radiation blankets will limit effects
– Make repairs and repeat if necessary
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Summary
• System is integrated to gondola
• Testing phase has begun
• Flights 1 & 2 will are scheduled for this fall
• Primary objectives for first two flights are engineering/system oriented