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Space shuttle srm interim contract, part 2
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1974 |
| Description | The characteristics of the solid rocket propellant for use with the space shuttle rocket engine are discussed. Design ramifications have created different web thicknesses and motor operating pressures which have necessitated small changes in the required propellant burning rate at 1,000 psia. However, the SRM burning rate remains well within the range demonstrated in the Poseidon and Minuteman first stage motors. Any change in propellant burning rate can be accomplished readily by a slight modification in the oxidizer particle size distribution. The ballistic and mechanical properties of the propellant remain unchanged from the baseline (Configuration 0). |
| File Size | 2198164 |
| Page Count | 111 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19740024184 |
| Archival Resource Key | ark:/13960/t55f3ks91 |
| Language | English |
| Publisher Date | 1974-06-28 |
| Access Restriction | Open |
| Subject Keyword | Space Vehicles Solid Rocket Propellants Space Shuttles Propellant Properties Solid Propellant Rocket Engines Performance Prediction Propellant Chemistry Propellant Additives Burning Rate Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
