Slow-Burn Ammonium Perchlorate Propellants with Oxamide: Burn Rate Model, Testing, and Applications
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2020-05-B38106.R2.pdf
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529.03 KB
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Author(s)
Vernacchia, Matthew T.
Mathesius, Kelly J.
Hansman Jr, Robert J
Date Issued
June 2021
Journal
Journal or Propulsion and Power
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Citation
Vernacchia, Matthew T. et al. "Slow-Burn Ammonium Perchlorate Propellants with Oxamide: Burn Rate Model, Testing, and Applications." Journal or Propulsion and Power (June 2021): doi.org/10.2514/1.B38106. © 2021 The Authors
Version
Author's final manuscript
Abstract
Low-thrust long-burn-time solid rocket motors may be useful as propulsion for small, fast, uncrewed aerial vehicles. These motors require a slow-burning propellant that can operate at unusually low chamber pressures (0.3–2 MPa). Slow-burn propellants were developed using ammonium perchlorate oxidizer and the burn rate suppressant oxamide. By varying the amount of oxamide (from 0 to 20%), burn rates from 4 to 1 mm⋅s−1 (at 1 MPa) were achieved. The adjustable burn rate allows a set of similar propellants to serve many aircraft and mission concepts. This work presents burn rate measurements (from both a strand burner and a research motor), minimum burn pressure measurements, and combustion chemical equilibrium simulations. A novel model of oxamide’s effect on burn rate is also presented, and it fits well to the experimental data. Finally, these propellant data and models are applied to select the propellant and chamber pressure for an example low-thrust solid rocket motor.
MIT Department
Massachusetts Institute of Technology. Department of Aeronautics and Astronautics
Terms of Use
Creative Commons Attribution-Noncommercial-Share Alike
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DOI of Published Version
https://doi.org/10.2514/1.b38106
