HIIPER Space Propulsion Simulation Using Plasma Module Z. Chen1, E. Ziehm1, G. H. Miley1 1University of Illinois at Urbana-Champaign, Urbana, IL, USA Abstract The Helicon Injected Inertial Plasma Electrostatic Rocket (HIIPER) is an electric space
IMPACT OF EXPERIMENTAL CONDITIONS ON AUTOCORRELATION BUNCHLENGTH MEASUREMENTS C. Settakorn, ChiangMai University, ChiangMai, 50200, Thailand H. Wiedemann, Stanford
Attach this sheet when submitting your result repot. 1. Experimental Conditions Values Description d Separation of Capacitor Plates (Thickness of Spacer)
Experimental Design in the Cultural ... be used only to confirm the technical ... in the Cultural Space Interior Design Studio: Linear Programmatic
Collection of physical photons? ... Simulating the Appearance of Nature Author: Henrik Wann Jensen Subject: Subsurface Scattering, BSSRDF, Hair Keywords:
“Difﬁculties in Simulating the Internet ... A Simple Model and its Empirical Validation, ... user/application adaptation
Semiconductor Thin-Film Transistors ... that surface states at the top of the AlGaN bar- ... In order to grasp the fundamentals needed to describe
of thermoplastic, fibre reinforced plastics - demonstrated for a side impact protection beam ... of effective strains. ... distribution and formation of
Simulating the Power Consumption of Large-Scale Sensor Network Applications ... personal or classroom use is granted without fee provided that copies are
ABSTRACT: Original ray tracing method can be used to create picture of objects that are very similar to photographic. However for simplicity,
Simulating Experimental Conditions of the HIIPER Space Propulsion Device D.
1 Ahern ,
2 Chen ,
1 Krishnamurthy ,
2 Ulmen ,
1. University of Illinois at Urbana-Champaign, Aerospace Engineering, IL 61801 2. University of Illinois at Urbana-Champaign, Nuclear, Plasma, and Radiological Engineering, Urbana, IL 61801
Introduction: The Helicon-Injected Inertial Plasma Electrostatic Rocket (HIIPER) is a two-stage electric propulsion system comprising of a helicon plasma source and an inertial electrostatic confinement (IEC) device. COMSOL has been used to predict results and simulate experimental diagnostics.
Results: 1. Potential profiles were generated for experiment and GEA
Figure 5. COMSOL potential profile.
IEC Chamber Wall
Figure 1. IEC in jet mode.
Computational Methods: Three COMSOL studies have been performed: 1. Gridded energy analyzer (GEA) potential profile 2. Helicon potential profile generated by spherical Langmuir probe 3. Cooling and heating curves of Faraday cup diagnostic
Figure 2. COMSOL model of the GEA inside the IEC chamber.
Figure 3. COMSOL model of the helicon dielectric tube attached to IEC.
Electron Repeller Grid
Ion Sweep Grid
2. Langmuir probe simulation showed a 25 V drop in helicon tube 3. Faraday cup cooling curve and heating calibration curve were generated
Figure 6. Cooling curve and heating calibration curve.
Conclusions: COMSOL numerical analysis on potential profiles has allowed for predicting experimental results. For Faraday cup, preliminary simulation results indicate a correlation with experimental results and allow for the extraction of thermal power values. References: 1. B. A. Ulmen, et al, "Investigation of Plasma Properties in a Helicon-Injected Inertial Plasma Electrostatic Rocket (HIIPER)," in 48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, Atlanta, 2012. 2. G. H. Miley, et al, "HIIPER Space Propulsion for Future Space Missions," in COMSOL Conference 2011, Boston, 2011.
Figure 4. Faraday cup diagnostic and COMSOL model.
3. P. Keutelian, et al, "Progress in Numerical Simulation of HIIPER Space Propulsion Device," in COMSOL Conference 2012, Boston, 2012.