Zobrazeno 1 - 10
of 113
pro vyhledávání: '"Propellant mass fraction"'
Publikováno v:
Journal of Spacecraft and Rockets. 59:434-447
The physical basis and application of the fundamental relationship governing the balance and utilization of available energy for a chemical rocket operating within the atmosphere are described. The...
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::d3f2b923bd4093326ba7ca5969f20aac
https://doi.org/10.2514/1.a35100
https://doi.org/10.2514/1.a35100
Publikováno v:
Matthew T. Vernacchia
Small, low-thrust, long-burn-time solid propellant rocket motors could provide propulsion for a new class of kilogram-scale, transonic, uncrewed aerial vehicles (UAVs). This paper investigates technological challenges of small, low-thrust solid rocke
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::10f7abf4d6c70d8b850acede28e8cd02
https://doi.org/10.2514/1.b38104
https://doi.org/10.2514/1.b38104
Autor:
Toru Shimada, Kohei Ozawa
Publikováno v:
Journal of Propulsion and Power. 37:86-99
This paper evaluates various sources of oxidizer to fuel mass ratio (O/F) shifts in hybrid rockets and paths (physical phenomena) through which these O/F shifts affect flight performance. Moreover, the performance increase of O/F control in hybrid ro
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::176d9bc8dd800045edd6d38c9b90ff40
https://doi.org/10.2514/1.b37970
https://doi.org/10.2514/1.b37970
Akademický článek
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Autor:
Matthew A. Hitt
Publikováno v:
Journal of Spacecraft and Rockets. 57:1408-1413
Although several investigations have been performed regarding the fundamental physics of axial-injection, end-burning hybrid rocket motors, investigations into the mission performance of a propulsi...
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::cb7852db2cde4990f57a30be589828f1
https://doi.org/10.2514/1.a34767
https://doi.org/10.2514/1.a34767
Publikováno v:
Journal of Spacecraft and Rockets. 56:1689-1703
Small satellites may provide a low-cost platform for targeted science investigations in the Mars system. With current technology, small satellites require ride shares with larger orbiters to captur...
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::b19abf7a18a57625b48c5f4d675774d1
https://doi.org/10.2514/1.a34444
https://doi.org/10.2514/1.a34444
Publikováno v:
Journal of Propulsion and Power. 35:1073-1079
Properly determining the size and predicting the performance of a Hall-effect thruster (HET) is an essential process in the early phase of thruster design. In this paper, the scaling relations for ...
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::f4952433526a1b092654cdee19a57a68
https://doi.org/10.2514/1.b37424
https://doi.org/10.2514/1.b37424
Autor:
Ciara McGrath, Malcolm Macdonald
Publikováno v:
Mcgrath, C & Macdonald, M 2019, ' General perturbation method for satellite constellation reconfiguration using low-thrust maneuvers ', Journal of Guidance, Control, and Dynamics, vol. 42, no. 8, pp. 1676-1692 . https://doi.org/10.2514/1.G003739
A general perturbation solution to a restricted low-thrust Lambert rendezvous problem, considering circular-to-circular in-plane maneuvers using tangential thrust and including a coast arc, is developed. This provides a fully analytical solution to t
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::7fc451a92d78576d465a359db2a5c24d
https://doi.org/10.2514/1.g003739
https://doi.org/10.2514/1.g003739
Publikováno v:
Journal of Aerosol Science. 133:24-36
Aerosol sprays are used in many fields because they are easy to use and low in cost. Because flash-boiling has a great influence on atomization performance and spray characteristics such as droplet diameter and spray cone angle of aerosol spray, it i
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::8b1685b63b6cf1ba7c716853c7b42f5d
https://doi.org/10.1016/j.jaerosci.2019.04.008
https://doi.org/10.1016/j.jaerosci.2019.04.008
Publikováno v:
Journal of Spacecraft and Rockets. 56:887-898
A simplified theoretical treatment of rotating detonation engine (RDE) performance is developed for rocket applications with traceability to current combustion technology. In particular, the influe...
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::d07269074d0e0bd0d9b4fd42db79bc42
https://doi.org/10.2514/1.a34313
https://doi.org/10.2514/1.a34313