Fig 1.
Examples of small monopropellant and bipropellant thrusters.
(A) Monopropellant thruster (Hydrazine propellant) [1]. (B) Bipropellant thruster (MMH-NTO propellant) [2].
Fig 2.
Fig 3.
Flow regimes and valid models at different Knudsen number [5,6].
Table 1.
Chemical equilibrium reaction result of hydrazine and MMH-NTO propellants.
Fig 4.
Configuration and calculation domain of thruster.
(A) Configuration of small thruster [11]. (B) Calculation domain of thrusters for N-S equations.
Fig 5.
Continuum flow results inside the thruster using N-S equations.
(A) Temperature [K]. (B) Axial velocity [m/s2]. (C) Density [kg/m3]. (D) Mach number.
Fig 6.
Exhaust plume flow properties at the thruster nozzle exit plane.
Fig 7.
Calculation domain of plume gas flow for DSMC method.
(A) Entire calculation domain. (B) Detailed domain adjacent to nozzle exit.
Fig 8.
Comparison of velocity streamlines of plume gas flows.
Fig 9.
Comparison of overall temperature distributions of plume gas flows [K].
(A) Overall temperature distributions over entire calculation domain. (B) Overall temperature distributions at z = +1 m and z = -0.5 m.
Fig 10.
Comparison of density distributions of plume gas flows [kg/m3].
(A) Density distributions over entire calculation domain. (B) Density distributions at z = +1 m and z = -0.5 m.
Fig 11.
Comparison of density distributions of H2 species [kg/m3].
(A) Density distributions over entire calculation domain. (B) Density distributions at z = +1 m and z = -0.5 m.
Fig 12.
Comparison of density distributions of N2 species [kg/m3].
(A) Density distributions over entire calculation domain. (B) Density distributions at z = +1 m and z = -0.5 m.