Zobrazeno 1 - 10
of 16
pro vyhledávání: '"Sunil Chintalapati"'
Publikováno v:
Marine Technology Society Journal. 52:32-41
Real-time data of storm surge are much needed for developing effective prediction models and nowcasting of impending hazard potential. The crucial aspect of monitoring and transmitting information for extreme weather conditions in near real time is v
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::090a188590cff35cc756cf043b08fb30
https://doi.org/10.4031/mtsj.52.4.8
https://doi.org/10.4031/mtsj.52.4.8
Autor:
Armando A. Rolins, Alexander Troshchenko, Kirill Martusevich, Isaac Spence, Sunil Chintalapati, Tiziano Bernard
Publikováno v:
2018 AIAA SPACE and Astronautics Forum and Exposition.
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::c236ce368bcf6fa92d1e36fafaa3ce8d
https://doi.org/10.2514/6.2018-5154
https://doi.org/10.2514/6.2018-5154
Effect of Isogrid-Type Obstructions on Thermal Stratification in Upper-Stage Rocket Propellant Tanks
Publikováno v:
Journal of Spacecraft and Rockets. 51:1587-1602
Analytical models for propellant thermal stratification are typically based on smooth wall flow correlations. However, many propellant tank walls have a mass-saving isogrid, which alters the boundary layer. This work investigates the boundary-layer b
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::f62b89be94f2bcceddb474355666e22c
https://doi.org/10.2514/1.a32699
https://doi.org/10.2514/1.a32699
Publikováno v:
Journal of Spacecraft and Rockets. 51:1377-1389
Orbital maneuvers of upper-stage rockets may generate propellant slosh waves and propellant breakup into droplets within the oxidizer and fuel tanks. When many droplets are created, increased propellant evaporation may occur and lead to a significant
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::82b7b2a86dca349ad02c75a273606ae8
https://doi.org/10.2514/1.a32308
https://doi.org/10.2514/1.a32308
Publikováno v:
Journal of Spacecraft and Rockets, 50(5), 992-1001. American Institute of Aeronautics and Astronautics Inc. (AIAA)
Communications to and from a launch vehicle during ascent are of critical importance to the success of rocket-launch operations. During ascent, the rocket's exhaust plume causes significant interference in the radio communications between the vehicle
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::594d063a26df60803b3e8f2fcd68a30e
https://doi.org/10.2514/1.a32358
https://doi.org/10.2514/1.a32358
Publikováno v:
Acta Astronautica. 86:188-200
Many launch support processes use helium gas to purge rocket propellant tanks and fill lines to rid them of hazardous contaminants. As an example, the purge of the Space Shuttle's External Tank used approximately 1,100 kg of helium. With the rising c
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::1f9c73bf2b29656c9d337f871c60c0fe
https://doi.org/10.1016/j.actaastro.2013.01.009
https://doi.org/10.1016/j.actaastro.2013.01.009
Publikováno v:
Journal of Spacecraft and Rockets. 49:1194-1204
Liquid-propellant slosh events occurring during orbital maneuvers of a rocket’s upper stage may adversely affect vehicle performance. Mission planners require accurate and validated simulation tools to understand and predict the effects of slosh on
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::a775dda74f94b2c19181dcf42cb391e4
https://doi.org/10.2514/1.a32052
https://doi.org/10.2514/1.a32052
Publikováno v:
51st AIAA/SAE/ASEE Joint Propulsion Conference.
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::8b7ab5f89769b43b49bac6bcf2e2adbb
https://doi.org/10.2514/6.2015-4249
https://doi.org/10.2514/6.2015-4249
Autor:
Charles A. Holicker, Gabriel Lapilli, Richard E. Schulman, Daniel Kirk, Sunil Chintalapati, Hector Gutierrez, Brian Wise
Publikováno v:
49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference.
A current problem that severely affects the performance of spacecraft is related to slosh dynamics in liquid propellant tanks under microgravity conditions. The confidence in computational fluid dynamics (CFD) predictions are low because of the lack
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::1356d54082ffb7fe8e3a0e6a8c073f9b
https://doi.org/10.2514/6.2013-3903
https://doi.org/10.2514/6.2013-3903
Autor:
Richard E. Schulman, Hector Gutierrez, Esteban Contreras, Daniel Kirk, Sunil Chintalapati, Charles A. Holicker
Publikováno v:
48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit.
Liquid propellant slosh occurring during orbital maneuvers of a rocket’s upper-stage may adversely affect vehicle performance. During orbital maneuvers the acceleration levels of an upper-stage vary substantially and significant liquid sloshing eve
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::4f2c21f489d464691ed1b2de6f9075c8
https://doi.org/10.2514/6.2012-4297
https://doi.org/10.2514/6.2012-4297