NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Collections About News Help Login
Back to Results
Rho-Isp Revisited and Basic Stage Mass Estimating for Launch Vehicle Conceptual Sizing StudiesA single metric for judging between two candidate propellant combinations for a given application is sought. By using the ideal rocket equation, the essential link between propellant density and specific impulse as the two primary performance drivers can be demonstrated.
Document ID
20150016477
Acquisition Source
Marshall Space Flight Center
Document Type
Conference Paper
Authors
Kibbey, Timothy P. (Jacobs Engineering and Science Services and Skills Augmentation Group (ESSSA) Huntsville, AL, United States)
Date Acquired
August 26, 2015
Publication Date
July 27, 2015
Subject Category
Numerical Analysis
Launch Vehicles And Launch Operations
Report/Patent Number
M15-4318
Meeting Information
Meeting: AIAA Propulsion and Energy Forum 2015
Location: Orlando, FL
Country: United States
Start Date: July 27, 2015
End Date: July 29, 2015
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
CONTRACT_GRANT: NNM12AA41C
Distribution Limits
Public
Copyright
Public Use Permitted.

Related Records

IDRelationTitle20150016561See AlsoRho-Isp Revisited and Basic Stage Mass Estimating for Launch Vehicle Conceptual Sizing Studies
No Preview Available