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Solid-propellant rocket motor internal ballistics performance variation analysis, phase 5
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Sforzini, R. H. Murph, J. E. |
| Copyright Year | 1980 |
| Description | The results of research aimed at improving the predictability of internal ballistics performance of solid-propellant rocket motors (SRM's) including thrust imbalance between two SRM's firing in parallel are presented. Static test data from the first six Space Shuttle SRM's is analyzed using a computer program previously developed for this purpose. The program permits intentional minor design biases affecting the imbalance between any two SMR's to be removed. Results for the last four of the six SRM's, with only the propellant bulk temperature as a non-random variable, are generally within limits predicted by theory. Extended studies of internal ballistic performance of single SRM's are presented based on an earlier developed mathematical model which includes an assessment of grain deformation. The erosive burning rate law used in the model is upgraded and made more general. Excellent results are obtained in predictions of the performances of five different SRM's of quite different sizes and configurations. These SRM's all employ PBAN type propellants with ammonium perchlorate oxidizer and 16 to 20% aluminum except one which uses carboxyl terminated butadiene binder. The only non-calculated parameters in the burning rate equations that are changed for the different SRM's are the zero crossflow velocity burning rate coefficients and exponents. The results, in general, confirm the importance of grain deformation. The improved internal ballistic model makes practical development of an effective computer program for application of an optimization technique to SRM design which is also demonstrated. The program uses a pattern search technique to minimize the difference between a desired thrust-time trace and one calculated based on the internal ballistic model. |
| File Size | 2760331 |
| Page Count | 65 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19860021337 |
| Archival Resource Key | ark:/13960/t1mh2f22t |
| Language | English |
| Publisher Date | 1980-01-01 |
| Access Restriction | Open |
| Subject Keyword | Spacecraft Propulsion And Power Solid Propellant Ignition Interior Ballistics Solid Propellant Rocket Engines Space Shuttle Boosters Combustion Stability Rocket Thrust Thrust Distribution Solid Propellant Combustion Applications Programs Computers Booster Rocket Engines Rocket Engine Design Computer Aided Design 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 |
