Affiliation:
1. Massachusetts Institute of Technology, Cambridge, Massachusetts 02139
2. BAE Systems, Merrimack, New Hampshire 03054
Abstract
Low-thrust, end-burning solid rocket motors have applications as propulsion systems for a class of small, transonic, uncrewed aerial vehicles. This paper provides new experimental measurements for characterizing small, low-thrust, end-burning motors. Four static fires measured the effects of motor chamber pressure and propellant oxamide content on exhaust plume radiant intensity, which could be important for vehicle visibility and tracking. Exhaust plume radiant intensity was found to be sensitive to a change in oxamide content and relatively insensitive to a change in chamber pressure for these motors. Thrust, chamber pressure, and burn rate were also measured for these motors, and a model for the minimum burn pressure of oxamide-doped propellants was improved.
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Reference15 articles.
1. SuttonG. P.BiblarzO., Rocket Propulsion Elements, 8th ed., Wiley, Hoboken, NJ, 2010, pp. 435–536, Chaps. 12–13.
2. Five-minute rocket motor
3. Survey of Low-Burn-Rate Solid Rocket Propellants
4. Low-Thrust Solid Rocket Motors for Small, Fast Aircraft Propulsion: Design and Development
5. Slow-Burn Ammonium Perchlorate Propellants with Oxamide: Burn Rate Model, Testing, and Applications