Low-Thrust Solid Rocket Motors for Small, Fast Aircraft Propulsion: Design and Development

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 small, low-thrust motors: slow-burn propellants, that have low thrust relative to their size (and thus chamber pressure), thermal protection the motor case, and small nozzles can withstand long burn times. Slow-burn propellants were developed using ammonium perchlorate 0–20% oxamide (burn-rate suppressant), with rates at 1 MPa. Using these successfully operated thrust/burn area ratio 10 times less than typical motors. kilogram-scale 5–10 N 1–3 min. An ablative liner was tested in firings, ceramic-insulated nozzle demonstrated. shows are feasible presents baseline design integration such into UAV.