Fabricated and tested CTP IPPTs at cone angles of 20deg, 38deg, and 60deg, and performed direct single-pulse impulse bit measurements with continuous gas flow. Single pulse performance highest for 38deg angle with impulse bit of approx.1 mN-s for both argon and xenon. Estimated efficiencies low, but not unexpectedly so based on historical data trends and the direction of the force vector in the CTP. Capacitor charging system assembled to provide rapid recharging of capacitor bank, permitting repetition-rate operation. IPPT operated at repetition-rate of 5 Hz, at maximum average power of 2.5 kW, representing to our knowledge the highest average power for a repetitively-pulsed thruster. Average thrust in repetition-rate mode (at 5 kV, 75 sccm...
We present a characterization of the performance of a recently developed gas-fed pulsed plasma thrus...
Pulsed inductive plasma thrusters [1-3] are spacecraft propulsion devices in which electrical energy...
A two-dimensional semi-empirical model of pulsed inductive thrust efficiency is developed to predict...
THE inductive pulsed plasma thruster (IPPT) is an electrodeless space propulsion device where a capa...
The inductive pulsed plasma thruster (IPPT) is an electromagnetic plasma accelerator that has been i...
Inductive Pulsed Plasma Thrusters (iPPT) spacecraft propulsion devices in which electrical energy is...
The inductive pulsed plasma thruster (IPPT) is an electromagnetic plasma accelerator that has been i...
Pulsed inductive plasma thrusters [1-3] are spacecraft propulsion devices in which electrical energy...
It is found that the impulse of a pulsed inductive plasma thruster utilizing preionization is maximi...
The pulsed inductive thruster (PIT) is an electrodeless, magnetic rocket engine that can operate wit...
The design and testing of a small inductive pulsed plasma thruster (IPPT), shown in Fig. 1 with all ...
Abstract: NASA Glenn Research Center (GRC) has evaluated the performance of a pulsed plasma thruster...
Pulsed inductive plasma thrusters [1-3] are spacecraft propulsion devices in which electrical energy...
A model of the maximum achievable exhaust velocity of a conical theta pinch pulsed inductive thruste...
Operational characteristics of two separate inductive thrusters with coils of different cone angles ...
We present a characterization of the performance of a recently developed gas-fed pulsed plasma thrus...
Pulsed inductive plasma thrusters [1-3] are spacecraft propulsion devices in which electrical energy...
A two-dimensional semi-empirical model of pulsed inductive thrust efficiency is developed to predict...
THE inductive pulsed plasma thruster (IPPT) is an electrodeless space propulsion device where a capa...
The inductive pulsed plasma thruster (IPPT) is an electromagnetic plasma accelerator that has been i...
Inductive Pulsed Plasma Thrusters (iPPT) spacecraft propulsion devices in which electrical energy is...
The inductive pulsed plasma thruster (IPPT) is an electromagnetic plasma accelerator that has been i...
Pulsed inductive plasma thrusters [1-3] are spacecraft propulsion devices in which electrical energy...
It is found that the impulse of a pulsed inductive plasma thruster utilizing preionization is maximi...
The pulsed inductive thruster (PIT) is an electrodeless, magnetic rocket engine that can operate wit...
The design and testing of a small inductive pulsed plasma thruster (IPPT), shown in Fig. 1 with all ...
Abstract: NASA Glenn Research Center (GRC) has evaluated the performance of a pulsed plasma thruster...
Pulsed inductive plasma thrusters [1-3] are spacecraft propulsion devices in which electrical energy...
A model of the maximum achievable exhaust velocity of a conical theta pinch pulsed inductive thruste...
Operational characteristics of two separate inductive thrusters with coils of different cone angles ...
We present a characterization of the performance of a recently developed gas-fed pulsed plasma thrus...
Pulsed inductive plasma thrusters [1-3] are spacecraft propulsion devices in which electrical energy...
A two-dimensional semi-empirical model of pulsed inductive thrust efficiency is developed to predict...