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Dragonfly, a Pu-fueled drone heading to Titan, gets key NASA approval
Curiosity landed on Mars sporting a radioisotope thermoelectric generator (RTG) in 2012, and a second NASA rover, Perseverance, landed in 2021. Both are still rolling across the red planet in the name of science. Another exploratory craft with a similar plutonium-238–fueled RTG but a very different mission—to fly between multiple test sites on Titan, Saturn’s largest moon—recently got one step closer to deployment.
On April 25, NASA and the Johns Hopkins University Applied Physics Laboratory (APL) announced that the Dragonfly mission to Saturn’s icy moon passed its critical design review. “Passing this mission milestone means that Dragonfly’s mission design, fabrication, integration, and test plans are all approved, and the mission can now turn its attention to the construction of the spacecraft itself,” according to NASA.
Ronald D. Boyd, Sr.
Fusion Science and Technology | Volume 18 | Number 2 | September 1990 | Pages 317-324
Technical Paper | Blanket Engineering | doi.org/10.13182/FST90-A29303
Articles are hosted by Taylor and Francis Online.
Steady-State subcooled water flow boiling experiments were carried out in a uniformly heated horizontal circular channel with a 0.45-MPa exit pressure and with the mass velocity varying from 1.56 to 8.55 Mg/m2·s. Measurements of critical heat flux (CHF), local heat transfer, and pressure drop were made for a smooth-wall 1.02-cm-diam copper test section with a heated length-to-diameter (L/D) ratio of 49.0. For the same inlet temperature near 20.0°C, comparisons are made with previous data with L/D = 33.0, from 30.0 to 50.0, 96.6 (two cases), and 115.5. The exit pressures for the above data are 0.1, 0.45, 0.77, 1.59, and 1.67 MPa, respectively. When L/D is between 49.0 and 115.5, the L/D influence on CHF is found to be significant for a 1.02-cm channel diameter in subcooled flows for mass velocities above 4.0 Mg/m2·s. This finding is important since most researchers and designers assume minimal L/D influence when L/D is >30. Further, the present CHF and local heat transfer data extend the data base (CHF near 1000.0 W/cm2 and heat transfer coefficient near 70 000 W/m2·K) for large channel diameters near 1.0 cm and low exit pressures. These results will assist in preventing catastrophic conditions from occurring in future systems where the L/D influence might inappropriately be neglected. Finally, Gambill's correlation predicts CHF significantly above the present data for CHF below 500 W/cm2. Above 500 W/cm2, however, his correlation agreed well with both the present data and the data for L/D = 96.6.