Proprietary BalloonWinds Update Author: Ivan Dors – UNH Presented By: Michael Dehring -- MAC 28 June 2006

Proprietary Overview Big Picture Mission Objectives Flight Objectives Instrument Status Summary

Proprietary Big Picture

Proprietary Big Picture Demonstrate direct-detection Doppler LIDAR technologies from 30 km above the Earth

Proprietary Mission Timeline 1.Liftoff - System Startup 2.Emit Laser and Signal Fiber Alignment 3.Flight Altitude Checkout 4.Eight-Hour Data Collection 5.Extended Data Collection (resources/weather) 6.Descent 1.Liftoff - System Startup 2.Emit Laser and Signal Fiber Alignment 3.Flight Altitude Checkout 4.Eight-Hour Data Collection 5.Extended Data Collection (resources/weather) 6.Descent

Proprietary Partial Inflation

Proprietary Ready For Launch

Proprietary Balloon Release

Proprietary Launch

Proprietary Balloon & Payload at Float Altitude

Proprietary Mission Objectives

Proprietary Mission Objectives Demonstrate direct-detection Doppler LIDAR fringe imaging from a high-altitude downward- looking platform Validate instrument performance models and atmospheric 355 nm Assess the scalability of key subsystems to a space-borne Doppler LIDAR instrument Scale performance to a space-borne LIDAR

Proprietary Mission Objectives Model Validation Atmosphere Model Laser-Telescope Model Optics-Camera Model Wind Uncertainty Model

Proprietary Flight Objectives

Proprietary Flight Objectives Flight # ObjectiveAtm. Condition Mission Date 1Nighttime Concept Demonstration Night Clear Air 09/06 2Daytime Concept Demonstration Day Partly Cloudy 10/06 3Full GTWS Demonstration Day & Night Partly Cloudy Autumn 05/07

Proprietary Flight I Objectives Demonstrate the electrical, thermal, mechanical, and optical performance of the integrated instrument for nighttime flight conditions

Proprietary Flight II Objectives Demonstrate the ability to operate during the daytime given the additional thermal load and the increased optical background

Proprietary Flight III Objectives Demonstrate Photometric measurement Spectral measurement Velocity measurement Validate Space instrument model Subsystem scalability

Proprietary Flight I &II Priorities Engineering Optical Performance Photometric Return Aerosol-molecular ratio Velocity

Proprietary Instrument Status

Proprietary 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

Proprietary Ground Station

Proprietary Mass Budget Budget [kg]As Built [kg] Laser Telescope Assembly Interferometer Enclosure Control Enclosure Cooling System Power Distribution AFRL Systems 9090 (est) Ballast (10% of total mass) Gondola Structure Total

Proprietary Power Budget Budget [W]As Built [W] Laser Enclosure Interferometer Enclosure 80 Control Enclosure Power System 109 Coolant Pump 5078 Total

Proprietary Thermal System Additional heating pads added for ascent Excess heat dissipated with ~0.2 m 3 ice Heat transferred with Propylene Glycol/DI Water 50% Temperature control loops operational System allows for 12+ hours of operation

Proprietary 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

Proprietary Telemetry Display

Proprietary Telemetry Graphs

Proprietary 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

Proprietary Laser-Telescope Status Alignment routines are operational and are being refined –Beam finding –Outer-fiber signal characterization –Alignment maintaining

Proprietary 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

Proprietary 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

Proprietary System Measurement Comparison Pre-Ship Post-Ship

Proprietary Instrument Status Integrated Picture 1

Proprietary Instrument Status Integrated Picture 2

Proprietary Instrument Status Integrated Picture 3

Proprietary 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

Proprietary 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

Proprietary 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

Proprietary 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