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Future capabilities of the Delta launch vehicleDesign features and payload delivery capabilities of the Delta 3920 launch vehicle are presented. The 3920 is the 14th iteration in a series that was first launched in 1960 and has in recent years surpassed a 97 percent success rate. Capacity is 2800 lb to GEO. The second stage has a propellant capacity of 13,244 lb and a specific impulse of 319.2 sec and produces 9443 lb thrust. The first mission is the Landsat-D satellite and 27 more launches are scheduled through 1985, some associated with different upper stage configurations. The 3924 configuration delivers payload to GEO at a cost of $7500/lb. A fairing has been designed to provide back-up for Shuttle payloads, although the larger size reduces the GEO payload to 2715 lb. Performance enhancements may, however, be gained through pneumatic thrusters for the Castor IV engine separation, higher Castor IV thrust levels, increased booster thrust, and a cryogenic second stage.
Document ID
19840055498
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Grimes, D. W.
(NASA Goddard Space Flight Center Greenbelt, MD, United States)
Kraft, J. D.
(NASA Goddard Space Flight Center Greenbelt, MD, United States)
Date Acquired
August 12, 2013
Publication Date
January 1, 1982
Subject Category
Launch Vehicles And Space Vehicles
Accession Number
84A38285
Distribution Limits
Public
Copyright
Other

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