Low-Thrust Solid Rocket Motors for Small, Fast Aircraft Propulsion: Design and Development
| Autor: | R. John Hansman, Matthew T. Vernacchia, Kelly J. Mathesius |
|---|---|
| Přispěvatelé: | Massachusetts Institute of Technology. Department of Aeronautics and Astronautics |
| Rok vydání: | 2022 |
| Předmět: |
Propellant
business.product_category business.industry Mechanical Engineering Aerospace Engineering Thrust Propulsion Chamber pressure Fuel Technology Propellant mass fraction Rocket Space and Planetary Science Space Shuttle thermal protection system Environmental science Aerospace engineering Solid-fuel rocket business |
| Zdroj: | Matthew T. Vernacchia |
| ISSN: | 1533-3876 |
| DOI: | 10.2514/1.b38104 |
| Popis: | Small, low-thrust, long-burn-time solid propellant rocket motors could provide propulsion for a new class of kilogram-scale, transonic, uncrewed aerial vehicles (UAVs). This paper investigates technological challenges of small, low-thrust solid rocket motors: slow-burn solid propellants, motors that have low thrust relative to their size (and thus have low chamber pressure), thermal protection for the motor case, and small nozzles that can withstand long burn times. Slow-burn propellants were developed using ammonium perchlorate and 0–20% oxamide (burn-rate suppressant), with burn rates of 1–4 mm⋅s−1 at 1 MPa. Using these propellants, a low-thrust motor successfully operated at a thrust/burn area ratio 10 times less than that of typical solid rocket motors. This kilogram-scale motor can provide 5–10 N of thrust for 1–3 min. An ablative thermal protection liner was tested in these firings, and a new ceramic-insulated nozzle was demonstrated. This paper shows that small, low-thrust solid motors are feasible and presents a baseline design for the integration of such a motor into a small UAV. Department of Defense (DoD) MIT Lincoln Laboratories, BAE Systems, Inc. |
| Databáze: | OpenAIRE |
| Externí odkaz: |
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