session IP

Title: Interactive Presentations
type: interactive
Description: Authors with an abstract accepted for an interactive presentation will be asked to prepare slides and display them for the duration of the congress on plasma screens. Authors will be assigned to interactive sessions in which they must be near the plasma screens to engage in interactive discussions with other congress attendees.
Date: 2016-09-28
Time: 13:15
Room: Jalisco Hall C - Exhibition Hall

IPC members

Coordinator: Mr. Giorgio Saccoccia, European Space Agency (ESA), France;
Coordinator: Dr. Toru Shimada, Institute of Space and Astronautical Science (ISAS), Japan Aerospace Exploration Agency, Japan;
Coordinator: Dr. Helen Webber, Reaction Engines Ltd., United Kingdom;
Coordinator: Mr. Christophe Bonhomme, Centre National d'Etudes Spatiales (CNES), France;
Coordinator: Prof. Riheng Zheng, Beihang University, China;

papers
Paper title	Presentation status	Speaker	Affiliation	Country
GAS-CORE NUCLEAR ROCKET ENGINES AND NOT STANDARD PROPULSIVE MASS FOR THEM	withdrawn	Mr. Oleg Aleksandrov	AVIASTAR Inc www.aviastar.us	United States
CFD Analysis of Combustion Instability in Axial-Injected Hybrid Rocket Engines during Throttling Transient	confirmed	Mr. Goutham Karthikeyan	Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency	Japan
Evaluation of Required Energies for Detonation of Chemical Rocket Propellants	confirmed	Ms. Akiyo Takahashi	Institute of Space and Astronautical Science (ISAS), Japan Aerospace Exploration Agency	Japan
Design, Study and Manufacturing of a Composite Solid Rocket Propellant	confirmed	Ms. Monika Johanna Pardo Spiess	Space Generation Advisory Council (SGAC)	Germany
improvement of nonlinear coefficient on combustion instability prediction in solid rocket motors		Ms. Shaojuan Wei	Northwestern Polytechnical University，NPU	China
Numerical modeling of large free-surface fluid flow in fuel tanks in flight		Mr. Oleksandr Brazaluk	Oles Honchar Dnipropetrovsk National University	Ukraine
effect of different thermal cure cycles on the propellant curing of solid rocket motor: a numerical study	confirmed	Mr. khadar voli	Indian Space Research Organization (ISRO)	India
Investigation of wagon-wheel fuel grain design of hybrid rocket motor	withdrawn	Dr. Xintian Li	China Academy of Launch Vehicle Technology (CALT)	China
Numerical Simulation of Inner Flow Field of a Pintle Injector Variable Thrust Hybrid Rocket Engine	confirmed	Mr. Bo Zhao	Beihang University	China
Size effect study of grain port on a long-time working hybrid rocket motor	withdrawn	Mr. xingliang sun	BUAA	China
development of three variants of reverse flow multiple nozzle solid rocket motor	withdrawn	Mr. SREEJITH K	Indian Space Research Organization (ISRO)	India
the glass-membrane MEMS igniter with improved performance for cube-sat application	confirmed	Dr. Daeban Seo	KARI	Korea, Republic of
Dr. V.A. Menshikov Association of participants of the Project "International Global Monitoring and forecasting AeroSpace System" (Association "IGMASS"), Russia.		Prof.Dr. Valery Menshikov		Russian Federation
Study on the Propellant Ablation Properties of Laser Ablation Propulsion	confirmed	Mr. Jian Li	College of Aerospace Science and Engineering, National University of Defense Technology	China
Numerical research on ablation of PTFE/Al propellant using continuous laser beam	withdrawn	Mr. Yu Zhang	College of Aerospace Science and Engineering, National University of Defense Technology	China
development and qualification of a high performance solid strapon motor	withdrawn	Mr. V MAHESH	Indian Space Research Organization (ISRO)	India
Influence of After-burning Chamber Dome Length on Secondary Combustion for Solid Ducted Rocket Motor	confirmed	Mr. bingle jin		China
cavity and jet injection effects on supersonic compressible ramp flow	withdrawn	Dr. Kangping Zhang	China Aerodynamics Research and Developement Center	China
The transient flow characteristics investigation of the wake behind a triangular flameholder in ramjet combustor	withdrawn	Dr. Yi Wang	Xi'an Aerospace Propulsion Institute	China
Research on the combination actuator system of adjustable nozzle in ramjet	withdrawn	Ms. Lili Fu	School of Astronautics,Northwestern Polytechnical University	China
5kW Class of Annular-Geometry Ion Thruster Development	withdrawn	Prof.Dr. tianping zhang	Lanzhou Institute of Physics	China
A Modular, Viable and Versatile System for Deployment of Solar Sail in a 3U Satellite	withdrawn	Ms. Tanvi Katke	College of Engineering, Pune	India
CIRA Liquid Propulsion Test Facilities: Vision and Roadmap		Dr. NUNZIA FAVALORO	CIRA Italian Aerospace Research Centre	Italy
CONCEPT AND DEVELOPMENT OF USING HYDROGEN PER OXIDE AS A PROPELLEANT	confirmed	Mr. Nadeem Alam	Department of Aeronautical Engineering, Babu Banarsi Das National Institute of Technology and Management, Lucknow,	India
Development of a Cryogenic Rocket Engine at Delft Aerospace Rocket Engineering	withdrawn	Mr. Mathijs Van de Poel	Delft University of Technology (TU Delft)	Belgium
Development of a Next-Generation Thrust Balance with Nano-Newton Resolution		Mr. Florian Nürmberger	TU Dresden	Germany
Development of Small Solid Rocket Boosters for the ILR-33 Sounding Rocket	confirmed	Mr. Pawel Nowakowski	Institute of Aviation	Poland
Dynamic load identification of a second stage liquid rocket engine based on Tikhonov regularization method	confirmed	Mr. song yan	Xi'an Aerospace Propulsion Institute	China
Electric Propulsion Anomalies and Failures: Analysis of On Orbit Track Record		Prof. Joseph Homer Saleh	Georgia Institute of Technology	United States
Experimental Investigation for Reliable Start-up of 5W Microwave Electrothermal Thruster as means of Primary Propulsion for Nano and Small Satellites in Realistic Space Condition		Mr. Rohan M Ganapathy	Bellatrix Aerospace Private Limited	India
Experimental Investigation of Combustion in MEMS based Microthrusters	confirmed	Mr. Aakash Patil	University of Pune	India
Experimental study on the current-sheet evolution for a pulsed inductive thruster	withdrawn	Dr. Xiaokang Li	National University of Defense Technology	China
Fast Transit Access to the Outer Solar System	confirmed	Prof.Dr. Edgar Bering	University of Houston	United States
Feasibility Study on Non-catalytic Ignitor for Hydrogen Peroxide/Polyethylene Hybrid Rocket	confirmed	Mr. Eunkwang Lee	Korea Advanced Institute of Science and Technology (KAIST)	Korea, Republic of
Impinging Injector Design for a Paraffin-Nitrous Oxide Hybrid Rocket Engine used in Sounding Rockets Part I: CFD Simulation of Candidate Designs	confirmed	Mr. Jeremy Chan-Hao Wang	University of Toronto Aerospace Team (UTAT)	Canada
Impinging Injector Design for a Paraffin-Nitrous Oxide Hybrid Rocket Engine used in Sounding Rockets Part II: Cold-Flow Testing of Candidate Designs	confirmed	Mr. Jeremy Chan-Hao Wang	University of Toronto Aerospace Team (UTAT)	Canada
investigations of real-fluid characteristics in high-pressure liquid rocket engines	confirmed	Mr. Li Pengfei	Xi'an Aerospace Propulsion Institute	China
Liquid-Propellant Rocket Engines Fault Diagnostic Based on Dynamic cloud BP networks		Dr. nie yao	College of Aerospace Science and Engineering, National University of Defense Technology	China
Low Cost Propulsion Technique to Transfer Satellite to Low Moon Orbit	withdrawn	Mr. Aman Singhal	University of Petroleum and Energy Studies	India
LV energetics increase by improvement of pneudraulic propellant feed systems characteristics of propulsion systems	confirmed	Mr. Anatolii Lohvynenko	Yuzhnoye State Design Office	Ukraine
Neuro-Fuzzy Model to Evaluate feed-back sensors of Mixture-Ratio Control System (MRCS) and control the performance of Rocket-Engine		Mr. elayaperumal ezhilrajan	Indian Space Research Organization (ISRO)	India
Numerical Study of LOX/Kerosene Combustion in a Single Element Coaxial Bi-Swirl Injector at Supercritical Conditions	withdrawn	Mr. Abhishek Sharma	Indian Space Research Organization (ISRO)	India
Progress in CIRA Development Plan on Electric Propulsion	confirmed	Dr. Francesco Battista	CIRA Italian Aerospace Research Centre	Italy
System & Magnetohydrodynamic Simulation Investigation on Pulsed Inductive Thrusters	confirmed	Dr. Xiaokang Li	National University of Defense Technology	China
The kinematics analysis on sway unit of LOX/Kerosene Rocket engine	confirmed	Dr. Jian ZHAO	Xi'an Aerospace Propulsion Institute	China
The LHT-100 Hall electric propulsion subsystem development for the XX-2 satellite		Mr. Li-Cheng Tian	Lanzhou Institute of Physics	China
Value analysis and value-informed tradeoffs for the adoption of electric propulsion onboard communication satellites		Prof. Joseph Homer Saleh	Georgia Institute of Technology	United States
Experimental Study on Combustion Characteristics of a Single Bi-Swirl Injector for Variable Thrust Lox/Kerosene Rocket Engine	confirmed	Mr. Yang Zhang	Beijing University of Aeronatics and Astronautics	China

session IP

Paper title

Mode

Presentation status

Speaker

Affiliation

Country