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Manufacture and static firing of x259-e6 rocket motor serial number xj04/0001
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Robertson, D. R. |
| Copyright Year | 1975 |
| Description | A single motor was cast and static fired to demonstrate the performance of high energy crosslinked double base (XLDB) propellant in standard X259 rocket motor hardware. Prior to motor fabrication, the motor was analyzed to predict the results of static firing the X259 motor loaded with XLDB propellant. As a result of the analyses, a forward dome shrinkage liner was added to the design. With this design change it was determined that adequate margins of safety existed. The motor, designated the X259-E6 model with serial number XJ04/0001, was fabricated using a slurry-casting technique and was assembled with a standard X259-B4 nozzle which had the nozzle throat machined to a smaller inside diameter than the B4 model and the exit cone cut short for Bacchus Works altitude expansion. The motor was static fired on 20 February 1974 with the nozzle failing during motor operation. Nozzle failure was attributed to spalling of the throat material leading to complete nozzle break-up. However, the propellant functioned as predicted in the motor chamber, ignition was normal, and char and erosion of the internal insulator were as expected. |
| File Size | 6304035 |
| Page Count | 69 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19750006755 |
| Archival Resource Key | ark:/13960/t8rc1tn2d |
| Language | English |
| Publisher Date | 1975-01-28 |
| Access Restriction | Open |
| Subject Keyword | Spacecraft Propulsion And Power Rocket Nozzles Propellant Tests Static Firing Engine Design Rocket Engines Double Base Propellants Engine Tests Failure 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 |
