The pulsed inductive thruster is characterized of no electrode corruption and wide propellant choice.To give insight into the propulsion mechanism of small scale thruster at different propellant mass(m)and energy(E)le...The pulsed inductive thruster is characterized of no electrode corruption and wide propellant choice.To give insight into the propulsion mechanism of small scale thruster at different propellant mass(m)and energy(E)levels,the transient Magneto Hydro Dynamics(MHD)method,completed by high temperature thermodynamic and transport,and plasma electrical models,is developed to study argon plasma response under the excitation of current of high rise rate.By calculating the two-dimensional expansion properties of the thruster with conical pylon,the simulations find that the main energy deposition occurs during the initial pulse rise stage,and the energy density of Joule heat is two magnitudes higher than the deposition in the down side.At propellant mass of 2 mg,average axial velocity of the current sheet increases from about 15 km/s at 750 J to about 21 km/s at 1470 J within the decoupling distance.The velocity variation synchronizes with the pulsed rise in the initial.The monotonically decrease of the temperature along axis results in the growth of low ionization level ions and reducing of high levels.The current sheet maintains the structure formed during the initial pulse rise when moving beyond the decoupling distance.Besides the change in forward velocity,the main difference is the dimension compared with that in the first half period,caused by thermal conduction and particle diffusion.The variations of total impulse It in the range of m from 2 mg to8 mg and E from 750 J to 1470 J show that It is proportional to m1/2 when E is determined.展开更多
The Pulsed Inductive Thruster(PIT)has the advantages of repeatable startup,no corruption and in-situ propellant feed.To study the flow expansion and circuit characteristics of PITs,the circuit-fluid model is developed...The Pulsed Inductive Thruster(PIT)has the advantages of repeatable startup,no corruption and in-situ propellant feed.To study the flow expansion and circuit characteristics of PITs,the circuit-fluid model is developed,and the high temperature thermodynamic and transport models are combined with the circuit-fluid model to predict the critical plasma parameters.The flow fields of initial mass of 2–8 mg and charge voltages of 10–14 k V are simulated.Comparison of the flow fields of argon and helium propellants suggests that,the flow field structures are similar.Slight differences exist on the magnitude of the density and magnetic field,caused by larger velocity in lighter atom case and difference on the ionization gap between adjacent ionization levels.Analysis of the circuit characteristics by the two-dimensional results indicates that the ratio of coil inductance to circuit inductance affects both the rise rate and phase of the plasma current,the larger the ratio,the greater the rise rate and the better the following characteristic.The calculations show that the magnetic energy obtained within the decoupling distance determines the overall performance the thruster can be obtained;self-induced field maintained by the thermal motion after the main pulse leads to the long attenuation process and difference on the total impulse when the angle of conical pylon is varied under constant coil dimension.展开更多
基金supported by the National Natural Science Foundation of China(Nos.11675040 and 11702319).
文摘The pulsed inductive thruster is characterized of no electrode corruption and wide propellant choice.To give insight into the propulsion mechanism of small scale thruster at different propellant mass(m)and energy(E)levels,the transient Magneto Hydro Dynamics(MHD)method,completed by high temperature thermodynamic and transport,and plasma electrical models,is developed to study argon plasma response under the excitation of current of high rise rate.By calculating the two-dimensional expansion properties of the thruster with conical pylon,the simulations find that the main energy deposition occurs during the initial pulse rise stage,and the energy density of Joule heat is two magnitudes higher than the deposition in the down side.At propellant mass of 2 mg,average axial velocity of the current sheet increases from about 15 km/s at 750 J to about 21 km/s at 1470 J within the decoupling distance.The velocity variation synchronizes with the pulsed rise in the initial.The monotonically decrease of the temperature along axis results in the growth of low ionization level ions and reducing of high levels.The current sheet maintains the structure formed during the initial pulse rise when moving beyond the decoupling distance.Besides the change in forward velocity,the main difference is the dimension compared with that in the first half period,caused by thermal conduction and particle diffusion.The variations of total impulse It in the range of m from 2 mg to8 mg and E from 750 J to 1470 J show that It is proportional to m1/2 when E is determined.
基金supported by the National Natural Science Foundation of China(Nos.11675040 and 11702319)。
文摘The Pulsed Inductive Thruster(PIT)has the advantages of repeatable startup,no corruption and in-situ propellant feed.To study the flow expansion and circuit characteristics of PITs,the circuit-fluid model is developed,and the high temperature thermodynamic and transport models are combined with the circuit-fluid model to predict the critical plasma parameters.The flow fields of initial mass of 2–8 mg and charge voltages of 10–14 k V are simulated.Comparison of the flow fields of argon and helium propellants suggests that,the flow field structures are similar.Slight differences exist on the magnitude of the density and magnetic field,caused by larger velocity in lighter atom case and difference on the ionization gap between adjacent ionization levels.Analysis of the circuit characteristics by the two-dimensional results indicates that the ratio of coil inductance to circuit inductance affects both the rise rate and phase of the plasma current,the larger the ratio,the greater the rise rate and the better the following characteristic.The calculations show that the magnetic energy obtained within the decoupling distance determines the overall performance the thruster can be obtained;self-induced field maintained by the thermal motion after the main pulse leads to the long attenuation process and difference on the total impulse when the angle of conical pylon is varied under constant coil dimension.
