UVC Airborne Holographic Lidar Transceiver Marc Hammond, David Huish, Tom Wilkerson, Scott Cornelsen Space Dynamics Laboratory Utah State University presentation for the Wind Lidar Working Group Sedona, AZ January 27-29, 2004 Research supported by NPOESS/IPO, NASA, and SDL © 2004

Outline High altitude aircraft : ER-2, Proteus Technology fusion basis (DLTA-M) HARLIE (Schwemmer), GLOW (Gentry) Performance UV– Cornerstone (UVC) transceiver UVC design progress at SDL Conclusion

Fusion of Two NASA Lidar Technologies HARLIE Holographic scan Lidar 1064 nm (present) Aerosol / cloud returns as function of azimuth and time “Cross beam” winds GLOW Doppler interferometer (“double-edge” etalon) 355 nm / 1064 nm Lidar Line-of-sight winds from aerosol returns LOS winds (molecular) from clear air DLTA Holographic 355 nm Multi-channel transceiver LOS winds / Cross beam winds Aerosol / Cloud morphology Airborne and ruggedized Platforms: ER-2 / Proteus Cal / Val for space-borne wind lidar Doppler Lidar Technology Accelerator

DLTA Direct Detection Doppler Lidar Instrument Layout Doppler Detector Non-Doppler Detector Laser Rotating hologram Laser Transmission

Conical scans for high altitude HOE lidar Nadir-45° sweep (  transonic) Tip-tilt mode horizon nadir

Expected performance-DLTA (nadir) Altitude 20 km

UVC-16: folded path, 16 in. hologram, 355 nm Length, diam. 30 in. Weight 187 lbs. Optical eff. 6 % 30 RPM Pacific Scientific motor Contitech timing belt ASRC data system Hamamatsu PMT SDL Transceiver Design

Pulse energy 1 mJ 355 nm Telescope diam cm Obstruction diam 4.6 cm Optical efficiency 6 % Horizontal path Clear air Density 2.5  cm -3 Range gate : UVC-16 Performance Photon returns per pulse

Weight 107 lbs. Length, diam. 24“ 3-Rod truss Convex secondary External detector Optical eff. 5% Other details similar to UVC-16 UVC – 12 Compact Transceiver

UVC - 12 Optical Return Path View from Detector End

Finite Element Analysis for UVC-12 Displacement Stress

Conclusion UVC is a compact, rugged transceiver for fusion of Holographic and Direct Detcction Doppler Lidar Thermal and Finite Element Analysis validate the design for flight in high altitude aircraft environment Next step: Vibration Analysis of UVC-16 and UVC-12 Design and fabrication of optical instrumentation for aircraft and satellites a major activity at Space Dynamics Laboratory Next design direction: Composite construction for greater strength and savings in weight. Composite technology is a focus area for SDL and Utah State University