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BalloonWinds Update

Author: Ivan Dors – UNH(Ivan.Dors@UNH.edu)

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