Abstract
Applications to spin stabilized vehicles and motor instability are sketched and models for acceleration augmented burning of non-metallized composite propellants are briefly critiqued. A detailed aerothermochemical model for steady-state, 2-D planar deflagration of an HTPB, AP sandwich in an acceleration field is described. Computed results are displayed for operational pressure and acceleration levels. Results show trend agreement in both magnitude and direction with experimental results and illuminate the gas phase mechanism - flow/combustion interactions driven by AP deflagration products/HTPB pyrolysis products density differences. The results invalidate opinions that gas phase effects are inadequate and imply that structural/deflagration coupling can be a significant aspect of real solid rocket instability.
Original language | English (US) |
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State | Published - 2001 |
Event | 39th Aerospace Sciences Meeting and Exhibit 2001 - Reno, NV, United States Duration: Jan 8 2001 → Jan 11 2001 |
Other
Other | 39th Aerospace Sciences Meeting and Exhibit 2001 |
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Country/Territory | United States |
City | Reno, NV |
Period | 1/8/01 → 1/11/01 |
ASJC Scopus subject areas
- Space and Planetary Science
- Aerospace Engineering