1887
banner image
No data available.
Please log in to see this content.
You have no subscription access to this content.
No metrics data to plot.
The attempt to load metrics for this article has failed.
The attempt to plot a graph for these metrics has failed.
Aircraft instrument for simultaneous, in situ measurement of and via pulsed cavity ring-down spectroscopy
Rent:
Rent this article for
USD
10.1063/1.2176058
/content/aip/journal/rsi/77/3/10.1063/1.2176058
http://aip.metastore.ingenta.com/content/aip/journal/rsi/77/3/10.1063/1.2176058
View: Figures

Figures

Image of FIG. 1.
FIG. 1.

(Color online) Layout of the optical and inlet systems.

Image of FIG. 2.
FIG. 2.

Ring-down trace with single exponential fit.

Image of FIG. 3.
FIG. 3.

(a) Schematic of the instrument frame and optical table mounted in the P-3 fuselage. (b) Inlet fast flow system and winglet.

Image of FIG. 4.
FIG. 4.

Schematic of the sealed, automated filter changer.

Image of FIG. 5.
FIG. 5.

Measurement of the wall loss rate (upper trace, solid points) through PFA tubing from exponential fit to the ratio of the concentration measured in two channels against the mean residence time between them. Repeated measurements gave a net loss rate of . The lower trace (open circles) shows the additional loss due to insertion of the machined, PFA pistons that hold the filter in place. The loss rate is similar in this trace, but there is a constant offset indicating a point source loss for in the flow system.

Image of FIG. 6.
FIG. 6.

(a) Measurement of the wall loss rate in the heated system at typical flows, converter, and measurement cell temperatures. (b, c) Measurement of the conversion efficiency as a function of heated channel flow rate and preconverter temperature in the field using two different CaRDS instruments sampling from the same manifold. The reference instrument had a flow of and a preconverter temperature of . Variation of the flow and temperature on the second instrument showed that the conversion is not a strong function of the conditions over a flow range of and preconverter temperature of .

Image of FIG. 7.
FIG. 7.

Allan variance plots of the instrument baseline in the laboratory (plot A) and from the aircraft during a daylight flight on July 27, 2004 (plot B). The laboratory data have a sensitivity of at but average to a detection limit below at . The aircraft data are considerably noisier, with a sensitivity of and a detection limit at of averaging of .

Image of FIG. 8.
FIG. 8.

Results from the test flight of the CaRDS instrument on the NOAA P-3 in March, 2004. Upper left: flight track. Lower: time series of , , and altitude. Upper right: variation of the instrument detection sensitivity (lower axis) and ring-down time constant (top axis) with altitude. The increase in sensitivity due to the increasing ring-down time constant and reduced turbulent flow noise approximately cancels the decrease in ambient number density, leading to a nearly altitude independent sensitivity.

Loading

Article metrics loading...

/content/aip/journal/rsi/77/3/10.1063/1.2176058
2006-03-23
2014-04-23
Loading

Full text loading...

This is a required field
Please enter a valid email address
752b84549af89a08dbdd7fdb8b9568b5 journal.articlezxybnytfddd
Scitation: Aircraft instrument for simultaneous, in situ measurement of NO3 and N2O5 via pulsed cavity ring-down spectroscopy
http://aip.metastore.ingenta.com/content/aip/journal/rsi/77/3/10.1063/1.2176058
10.1063/1.2176058
SEARCH_EXPAND_ITEM