session IP

Title: Interactive Presentations
type: interactive
Description: This session offers a unique opportunity to deliver your key messages in an interactive presentation on any of the subjects of Space Propulsion addressed in the classic Sessions. The presentation will be displayed on a digital screen in a dedicated location and available for view by all Congress attendees for the entire Congress week. In addition, one afternoon is dedicated exclusively for the attendees to view the Interactive Presentations, and the author will be assigned a specific eight minute slot to personally present the topic and interact with the attendees present. The Interactive Presentation may take advantage of all electronic display capabilities, such as: PowerPoint charts, embedded hot links, pictures, audio and video clips etc. An award will also be presented to the author of the best Interactive Presentation in the C Category at a special ceremony. An Abstract that follows the standard format must be submitted by the deadline for standard IAC abstracts.
Date: 2017-09-28
Time: 12:45
Room: Hall J&K2

IPC members

Co-Chair: Dr. Elizabeth Jens, Jet Propulsion Laboratory - California Institute of Technology, United States;
Co-Chair: Ms. Elizabeth Driscoll, Spaceflight, United States;
Co-Chair: Dr. Jerrol Littles, Aerojet Rocketdyne, United States;
Co-Chair: Mr. Christophe Bonhomme, Centre National d'Etudes Spatiales (CNES), France;
Co-Chair: Dr. Yen-Sen Chen, American Institute of Aeronautics and Astronautics (AIAA), United States;

papers
Paper title	Presentation status	Speaker	Affiliation	Country
Spacecraft-plasma interactions of a cubesat equipped with miniaturized feep thrusters	confirmed	Mr. Amenosis Lopez	TU Braunschweig	Germany
Advanced Propulsion Control System(APCS) Model using Intelligent Techniques	confirmed	Mr. elayaperumal ezhilrajan	Indian Space Research Organization (ISRO)	India
Transient Responses of Turbulent Heat Transfer of N-Decane at Supercritical Pressure and Temperature below 800 K	confirmed	Dr. Bo Ruan	School of Aeronautics and Astronautics, Dalian University of Technology	China
design, manufacture and testing of a 20 cm electron cyclotron resonance gridded ion thruster and neutraliser using additive manufacturing	withdrawn	Mr. Jacob Verlander	University of Southampton	United Kingdom
wavelet packet analysis of time-frequency characteristic of the LOX/Kerosene rocket engine due to heavy impact	confirmed	Dr. Feiping Du	Xi'an Aerospace Propulsion Institute	China
Application of Particle-In-Cell Simulation Techniques in the Analysis and Optimisation of Magnetic Nozzle Geometries	confirmed	Mr. Alexander Ryan	University of New South Wales	Australia
Multi-objective Design Optimization of the Cusped Field Thruster for Micro-Satellite Platforms	confirmed	Mr. Thomas Logan Fahey	RMIT University (Royal Melbourne Institute of Technology)	Australia
Study of Effect of Neutral Flow and Electron Transport in Wall Less Hall Thruster Concept	confirmed	Mr. Rohan M Ganapathy	Bellatrix Aerospace Private Limited	India
Control of Miniaturized Electrospray Ion Thrusters for CubeSat Designs	confirmed	Mr. Samuel Laprise	Ecole Polytechnique de Montreal	Canada
Coilgun Acceleration Model Containing Interactions Between Multiple Coils	withdrawn	Ms. Connie Liu	School of Aerospace Engineering, Georgia Institute of Technology	United States
Overview of Electric Propulsion Developments at TU Dresden for Micro and Small-Satellites	confirmed	Prof. Martin Tajmar	TU Dresden	Germany
investigation of selective laser melting (slm) for production of microwave ion thruster accelerator grids	withdrawn	Mr. David Hoffman	University of Southampton	United Kingdom
Evaluation of Quasi-Steady Operation of MPD Thruster using Electric Double-Layer Capacitors	withdrawn	Mr. Shunichiro Ide	The University of TOKYO, Graduate school	Japan
Closed-loop Thrust Control for Micropropulsion Systems	confirmed	Mr. Stefano Silvestrini	Delft University of Technology (TU Delft)	The Netherlands
choi-williams ditribution analysis for fault detection of the liquid propellant rocket engine	confirmed	Dr. Feiping Du	Xi'an Aerospace Propulsion Institute	China
Numerical Simulation of Flow Characteristics in Methane Transverse Jet	confirmed	Mr. zengkai shi		China
Two Dimensional Axisymmetric Navier-Stokes Analysis of Hybrid Rocket Intrinsic Instability	withdrawn	Mr. Goutham Karthikeyan	Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency	Japan
Study of Ignition Transient in 2m Diameter Segmented SRM	confirmed	Dr. Jian-ru Wang	The 41st Institute of the Fourth Academy, China Aerospace Science and Technology Corporation (CASC)	China
An additively-manufactured CNG/GOX aerospike rocket engine: Test results, performance and analysis	confirmed	Mr. Nicholas Mason-Smith	Monash University	Australia
Study on auto-ignited hybrid rocket based on n2o oxidizer using catalytic ignition system	confirmed	Mr. Jincheol Kim	Chosun University	Korea, Republic of
Early Studies and Fire Tests of a Green Liquid Apogee Engine Based on Decomposition of 98% Hydrogen Peroxide	confirmed	Dr. Pawel Surmacz	Institute of Aviation	Poland
Applications for 3D printing in the Design of Hall Effect Thrusters	withdrawn	Mr. Ethan Hopping	University of Alabama in Huntsville	United States
Effect of Prestrain on Dynamic Mechanical Properties of HTPB propellant	confirmed	Prof. Jinxian Li	Science and Technology on Combustion, Internal Flow and Thermal-structure Laboratory,Northwestern Polytechnical University	China
numerical investigation on detonation process of pulse detonation engine with hypergolic propellants	withdrawn	Dr. Hongbo HU	Xian Aerospace Propulsion Institute	China
investigation of catalytic re-ignition process in hydrogen peroxide hybrid rocket motors	confirmed	Dr. Sheng Zhao	China Academy of Launch Vehicle Technology (CALT)	China
numerical simulation of catalytic decomposition and combustion process in an hydroxylammonium nitrate (han)-based monopropellant thruster	confirmed	Ms. Xiqiao Yu	Shanghai Insitute of Space Propulsion	China
Assessment of combustion instability mechanisms based on an energy balance analysis	confirmed	Mr. Arnau Pons Lorente	Purdue University	United States
Investigation on the Near-nozzle Field Flow of Liquid Jet in a Supersonic Crossflow	confirmed	Mr. Liyin Wu	China Aerodynamics Research and Development Center (CARDC)	China
A Theoretical Study on Throttle Ranges of O/F Controllable Hybrid Rocket Propulsion Systems	withdrawn	Dr. Kohei Ozawa	Kyushu Institute of Technology	Japan
Numerical simulation of the start process of a han-based mono-propellant rocket thruster	confirmed	Prof.Dr. Dechuan Sun	School of Aeronautics and Astronautics, Dalian University of Technology	China
Systematic performance analysis of cubesat propulsion systems using the high performance satellite dynamics simulator HPS	confirmed	Dr. Benny Rievers	ZARM University of Bremen	Germany
Development of 2,500 N class hydrogen peroxide/polyethylene hybrid rocket for lab-scale sounding rocket application	confirmed	Mr. Yongtae Yun	Korea Advanced Institute of Science and Technology (KAIST)	Korea, Republic of
Numerical Simulation of Influence of Injector Parameters on Combustion in LOX/Methane Engine	confirmed	Prof. Ping Jin	School of Astronautics, Beihang University	China
Material Compatibility of Six Metal Alloys with HAN based Green Monopropellant Fuel Blend	confirmed	Mr. Rohan M Ganapathy	Bellatrix Aerospace Private Limited	India
particle damping characteristics of low and medium frequency oscillation in solid rocket motor	confirmed	Ms. Shaojuan Wei	Northwestern Polytechnical University，NPU	China
Feasibility of FDM Ablative Ceramic Materials for Low-Cost Propulsive Systems	withdrawn	Mr. Adam Bower	University of Alabama in Huntsville	United States
Optimization of catalytic bed geometry for 98% hydrogen peroxide monopropellant thruster	withdrawn	Mr. Przemyslaw Paszkiewicz	Warsaw University of Technology (WUT)	Poland
Shallow Water Tests of Seconary Injection Thrust Vector Control of Aerospike Nozzles	confirmed	Mr. Christian Bach	Technische Universität Dresden (DTU)	Germany
Numerical and experimental study of supersonic film cooling with cracking hydrocarbon fuel as coolant	withdrawn	Mr. Kunlin Cheng	Harbin Institute of Technology	China
Design and Experimental Characterization of a Hydrogen Peroxide-Ethanol based Combustor for Space Propulsion	confirmed	Mr. Disip Chaturvedi	Indian Institute of Technology, Bombay	India
Primary In-Space Experimental results of the HEP-100MF Electrical Propulsion System	confirmed	Prof.Dr. Yan Shen	Beijing Insitude of Control Engineering	China
Reusable TSTO Conceptual Vehicle Designs using the TRRE Engine	withdrawn	Dr. Peiran Su	Science and Technology on Scramjet Laboratory, Beijing Power Machinery Research Institute	China
Turbine reheater: a new paradigm for hypersonic flight propulsion	withdrawn	Prof. Sterian Danaila	University POLITEHNICA of Bucharest - Research Center for Aeronautics and Space	Romania
LES of Streamwise Vortex on Supersonic Mixing employing Hypermixer	withdrawn	Mr. Sheng Guo	Science and Technology on Scramjet Laboratory,Beijing Power Machinery Research Inst	China
Experimental and Computational Studies of Supersonic Combustion Characteristics of HyperMixer in Mach 8 Flight Condition		Dr. Yang Fujiang	Science and Technology on Scramjet Laboratory, The 31st Research Institute of CASIC	China
Preliminary studies on physical definition and discrimination of rocket-ejector mode of RBCC Engine	withdrawn	Dr. Feiteng Luo	Science and Technology on Scramjet Laboratory, Beijing Power Machinery Research Institute	China
The preliminary study of severity level of structural discontinuities in paraffin grain of hybrid propellant rocket		Dr. Artem Andrianov	University of Brasilia	Brazil
Analysis of cavitation characteristics of pumps used in liquid rocket engines by using multihole orifice plate		Mr. RAHUL KUMAR CHAURASIA	Indian Space Research Organization (ISRO)	India
On the Electrical Propulsion of a Solar Sail	confirmed	Ms. Elena Ancona	Telespazio VEGA Deutschland GmbH	Germany
Physical grounds and control optimization of ultralow-orbit spacecraft with electric ramjet	confirmed	Dr. Olga Yanova	TsAGI	Russian Federation

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