HR: 1330h
AN: C32A-0432    [PDF]
TI: Geoscience Laser Altimeter System - Characteristics and Performance of the Altimeter Receiver
AU: * Sun, X
EM: Xiaoli.Sun-1@nasa.gov
AF: NASA Goddard Space Flight Center, Code 924 B33, Room D424, Greenbelt, MD 20771 United States
AU: Abshire, J B
EM: James.B.Abshire@nasa.gov
AF: NASA Goddard Space Flight Center, Code 924 B33, Room D424, Greenbelt, MD 20771 United States
AU: Yi, D
EM: Donghui.Yi.1@gsfc.nasa.gov
AF: Raytheon ITSS/NASA GSFC, Code 971, Greenbelt, MD 20771 United States
AB: The Geoscience Laser Altimeter System (GLAS) on board ICESat spacecraft measures the surface height (altimetry) via the time of flight of its 1064 nm laser pulse. The GLAS laser transmitter produces 6 ns wide pulses with 70 mJ energy at 1064 nm at a 40 Hz rate. The altimeter receiver consists of a telescope, aft optics, a silicon avalanche photodiode, and electronic amplifiers. The transmitted and echo pulse waveforms are digitized at 1 GHz rate. The laser pulse time of flight is determined on the ground from the two digitized pulse waveforms and their positions in the full digital waveform record (about 5.4 ms long) by computing the pulse centroids or by curve fitting. The GLAS receiver algorithms in on board software selects the two waveform segments containing the transmitted and the echo pulses and sends them to ground. The probability of echo pulse detection and the accuracy of time of flight measurement depend on the received signal level, the background light within the receiver field of view, the inherent detector and amplifier noise, the quantization of the digitizer, and some times by cloud obscurations. A receiver model has been developed to calculate the probability of detection and accuracy of the altimeter measurements with these noise sources. From pre-launch testing, the minimum detectable echo pulse energy for 90% detection probability was about 0.1 fJ/pulse onto the detector. Such a receiver sensitivity allows GLAS to measure the surface height through clouds with optical density less than 2. The echo pulse energy required to achieve 10cm ranging accuracy was found to be about 3 times higher than the minimum detectable signal level. The smallest single shot range measurement error, which was determined by ranging to a fixed target with strong echo pulses and no background light, was 2 to 3cm. The maximum linear response echo pulse energy was 10 fJ/pulse for the strongest echo signals, assuming a Lambertian scattering snow surface, clear sky atmosphere transmission, and no pulse width spreading due to surface slopes. Results from the initial 38 days of GLAS operation on-orbit with Laser 1 showed the echo pulse energies varied, as expected, over a wide dynamic range due to the variability of atmosphere transmission and Earth surface characteristics. The receiver was able to reliably detect the ground surface echoes and measure time of flight under such dynamic conditions, except when there were dense clouds. When over Antarctica, the echo pulse energies were several times stronger than predicted. This suggests that the 1064 nm backscattering from the snow pack and ice-sheet surfaces are not completely Lambertian but is somewhat peaked at opposition. With Laser 1, the peak amplitude of the echo pulses from flat icesheets under clear sky conditions exceeded the linear response range of the receiver, causing some pulse waveform distortion due to saturation. We have characterized the effects of receiver saturation on the time of flight, pulse width, and pulse energy measurements for flat surfaces by testing a flight spare detector in the lab with simulated echo pulses. A data processing algorithm that minimizes the errors due to saturation for these measurements are described.
DE: 0933 Remote sensing
DE: 0994 Instruments and techniques
DE: 1640 Remote sensing
DE: 1863 Snow and ice (1827)
DE: 1894 Instruments and techniques
SC: Cryosphere [C]
MN: 2003 Fall Meeting