Abstract:
The possibility of steady-state operation of small-size thrusters is discussed. A more detailed study of the known frequency equation makes it possible to compose a more detailed “chart of instability” for the physical formulation considered. It turns out that combustion in a certain range of parameters $v$ and $r$ (characterizing the dependence of the steady-state burning rate on pressure and the dependence of the surface temperature on initial temperature) is stable in a small-size thruster and unstable in a large-size motor.
Keywords:steady-state analysis, frequency equation, burning rate, boundary of the stability domain, solid-propellant rocket motor, microthruster.
