• Home
  • IAC Papers Archive
  • Public Website
  • My papers
  • Home
  • event
  • IAC-20
  • C2
  • 7
  • session 7

    Title

    Space Vehicles – Mechanical/Robotic/Thermal/Fluidic Systems

    Description

    The topics to be addressed include novel technical concepts for mechanical/robotic/thermal/fluidic systems and subsystems of launchers, manned and unmanned spacecraft, re-entry vehicles and small satellites. Advanced subsystems and design of future exploration missions will be covered, considering issues arising from material selection, cost efficiency and reliability, and advancements in space vehicle development with respect to engineering analysis, manufacturing, and test verification. It is also planned to discuss the issues of experimental and computational simulation of functioning and full-scale tests of space vehicles and their systems/subsystems. Attention will be paid to the problem of verification and validation of mathematical models for the design and experimental development of these objects at various phases of their life cycle.

    IPC members
    • Co-Chair: Prof. Oleg Alifanov, Moscow Aviation Institute, Russian Federation;

    • Co-Chair: Dr. Brij Agrawal, Naval Postgraduate School, United States;

    • Rapporteur: Prof. Guoliang Mao, Beijing Institute of Aerodynamics, China;

    papers

    Order

    Time

    Paper title

    Mode

    Presentation status

    Speaker

    Affiliation

    Country

    1

    Thermal Design of the Emirates Mars Mission (Hope Probe)

    withdrawn

    Mr. Yousuf Alshehhi

    Mohammed Bin Rashid Space Centre (MBRSC)

    United Arab Emirates

    2

    Application of Magnetocaloric Cooling Components for Small Satellite Systems

    Mr. Benjamin Grzesik

    Technische Universität Braunschweig

    Germany

    3

    Hope Probe’s Mechanical System

    withdrawn

    Mr. Mahmood Alawadhi

    Mohammed Bin Rashid Space Centre (MBRSC)

    United Arab Emirates

    4

    Flexible and Scalable Thermal Design of Modular On-Orbit Assembly Microsatellite

    Mr. Weijian Pang

    Shaanxi Engineering Laboratory for Microsatellites, Northwestern Polytechnical University

    China

    5

    DIAGNOSTICS OF DEFECTS OF THERMAL PROTECTIONS INFLATABLE RE-ENTRY VEHICLES

    Dr. Alena V. Morzhukhina

    Moscow Aviation Institute (National Research University, MAI)

    Russian Federation

    6

    Generation of the reference map in design parameters for efficient thermal control of satellite components using PCM

    10

    confirmed

    Mr. Yeon Cho

    Korea Polytechnic University

    Korea, Republic of

    7

    Thermal Analysis and TVAC Testing of the Hope Probe (Emirates Mars Mission)

    Mr. Abdulla Alshehhi

    UAE Space Agency

    United Arab Emirates

    8

    Reentry Convective Heat Flux Estimation using CFD

    withdrawn

    Mr. Mayank Kumar

    Vikram Sarabhai Space Centre, Thiruvananthapuram-695 022, INDIA

    India

    9

    Attitude control system of a microsatellite based on the inverse problems technique and the Kalman filter

    10

    confirmed

    Mr. Evgeny Chebakov

    Moscow Aviation Institute (National Research Institute, MAI)

    Russian Federation

    10

    Reliability-based multi-objective design optimization of the satellite thermal control system using swarm-based optimization algorithms

    10

    confirmed

    Mr. Elyas Fadakar

    Beihang University (BUAA)

    China

    11

    A novel development of the PCM heat switch for future spacecraft missions

    withdrawn

    Mr. Jakub Mašek

    Brno University of Technology

    Czech Republic

    12

    Development of a thermal design model for a small spacecraft with integrated heat pipes

    10

    confirmed

    Mr. Nikolay Mullin

    Skolkovo Institute of Science and Technology

    Russian Federation

    13

    MONITORING AND ANALYSIS OF THE STRESSED-DEFORMED CONDITION OF THE SHELLS, IN THE PROCESS OF THEIR MANUFACTURE DURING 3D PRINTING AND WELDING WORKS

    10

    confirmed

    Mr. Valerii Satokin

    Ukraine

    14

    Design of the Structure and Propelling system of a Mars exploration and mapping drone

    withdrawn

    Mrs. Sofia Garaizar

    Spain

    15

    Cooling Channel at the Leading Edge of Supersonic Vehicle design based on Working fluid convection

    10

    confirmed

    Ms. Mochen Chang

    Northwestern Polytechnical University

    China

    16

    SharjahSat-1 Thermal Analysis for Orbit-Launch Selection

    10

    confirmed

    Mr. Ibrahim Alsabt

    Sharjah Academy for Astronomy, Space Sciences and Technology (SAASST)

    United Arab Emirates