session 7

Title: Space Vehicles – Mechanical/Thermal/Fluidic Systems
type: oral
Description: Discussed in this session are novel technical concepts for mechanical/thermal subsystems of launchers, manned and unmanned spacecraft, re-entry vehicles and small satellites. Also included in this session will be cost efficiency and reliability, material selection, new theoretical approaches, low cost manufacturing and test verification. Advanced subsystems and design for future exploration missions will also be included.
Date: 2008-10-02
Time: 15:00
Room: Dochart 1

IPC members

Chairman: Prof. Mario Marchetti, Sapienza University of Rome, Italy;
Chairman: Prof.Dr. Oleg Alifanov, MAI, Russian Federation;
Rapporteur: Prof. Guoliang Mao, Beijing Institute of Aerodynamics, China;

papers
Order	Paper title	Mode	Speaker	Affiliation	Country
1	SMART THERMAL PROTECTION SYSTEMS	presentation	Mr. Jesus Marcos	INASMET-TECNALIA	Spain
2	Numerical approach to control of infrared optical properties of conductive oxide by periodic microstrucured gratings	presentation	Dr. Kazunori Shimazaki	Japan Aerospace Exploration Agency (JAXA)	Japan
3	PDR-Level Structural Modeling and Analysis of the Mars Gravity Biosatellite	presentation	Mr. Joao Ricardo	Sonaca Space GmbH	Portugal
4	Calibration of Oxy-Acetylene torch for Ablative Liner Test for Rocket Motor casing and Nozzle.	presentation	Mr. B.Venkat Shivram Jadav	Vikram Sarabhai Space Centre, Thiruvananthapuram-695 022, INDIA	India
5	A Probabilistic Sizing Tool and Monte Carlo Analysis for Entry Vehicles Ablative Thermal Protection Systems	presentation	Dr. Antonio Mazzaracchio	Sapienza Università di Roma	Italy
6	thermal orbital heating rates lapan-tubsat analysis using software thermal desktop 5.0 and sinda/fluint 5.0		Mr. Ahmad Fauzi	Indonesian National Institute of Aeronautics and Space (LAPAN)	Indonesia
7	Space Launch Systems for Prevention of the Earth Collision with Asteroid		Dr. Stanislav Konyukhov	Yuzhnoye State Design Office	Ukraine
8	Effect of Weak Boundary on Thermal Stress of Throat Insert in SRM Nozzle		Mr. Shi Hongbin	Xi'an institute of aerospace propulsion technology	China
9	AERODYNAMIC CONFIGURATION ANALYSIS FOR A RETRIEVABLE ORBITAL VEHICLE		Mr. Col. Jose Duarte	Instituto de Aeronáutica e Espaço (IAE)	Brazil
10	study on control of residual stresses during manufacturing of flat al 7075-t7351 parts for use in space structures	presentation	Mr. Mirsaeid Abolghasemi	Iranian Space Agency (ISA)	Iran
11	Thermal distortion analysis of LEO earth observation satellite	presentation	Mr. Sun-Won Kim	Korea Aerospace Research Institute (KARI)	Korea, Republic of

session 7

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