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  • development of a low cost sounding rocket propelled by a hybrid motor

    Paper number

    IAC-17,A2,5,2,x40054

    Author

    Mr. Michal Pakosz, Institute of Aviation, Poland

    Coauthor

    Mr. Bartosz Bartkowiak, Institute of Aviation, Poland

    Coauthor

    Mr. Adam Okninski, Institute of Aviation, Poland

    Coauthor

    Mr. Kamil Sobczak, Institute of Aviation, Poland

    Coauthor

    Mr. Damian Kaniewski, Institute of Aviation, Poland

    Coauthor

    Mr. Jan Matyszewski, Institute of Aviation, Poland

    Coauthor

    Mr. Pawel Nowakowski, Institute of Aviation, Poland

    Coauthor

    Mr. Blazej Marciniak, Institute of Aviation, Poland

    Coauthor

    Mr. Dawid Cieslinski, Institute of Aviation, Poland

    Coauthor

    Mr. Damian Rysak, Institute of Aviation, Poland

    Coauthor

    Mr. Dominik Kublik, Institute of Aviation, Poland

    Coauthor

    Dr. Grzegorz Rarata, Institute of Aviation, Poland

    Coauthor

    Mr. Jaromir Smetek, Institute of Aviation, Poland

    Coauthor

    Dr. Pawel Surmacz, Institute of Aviation, Poland

    Coauthor

    Mr. Wojciech Florczuk, Institute of Aviation, Poland

    Coauthor

    Prof. Piotr Wolanski, Institute of Aviation, Poland

    Coauthor

    Ms. Anna Barbara Kasztankiewicz, Institute of Aviation, Poland

    Coauthor

    Mr. Maciej Skórski, Institute of Aviation, Poland

    Coauthor

    Mr. Jacek Mazurek, Institute of Aviation, Poland

    Coauthor

    Dr. Zbigniew Gut, Institute of Aviation, Poland

    Year

    2017

    Abstract
    This paper gives an overview of the next stage of development of the ILR-33 "Amber" sounding rocket. The main goal of this project is to design a highly scalable, cost effective and green platform for conducting experiments in microgravity. The article focuses on critical subsystems’ tests carried out during the development. Results of main motor firings are presented. The main engine is a hybrid motor using High Test Peroxide (98\%) as oxidizer and high-density polyethylene as fuel. Its mean thrust exceeds 4 000 N and the burn time is 40 s. The motor was designed and tested in the Institute of Aviation in Warsaw, Poland. Moreover, the paper shows the results of tests of the 6000 N class solid propellant boosters. Three parallel firings of two motors on the test stand were performed.  Attention was paid to the ignition delay time and its variation to ensure that unsymmetrical performance of two boosters will not affect the mission sequence. Furthermore, tests of the launch tower and rocket release system were carried out. The start sequence controlled by the computer was proven. Subsequent experiments concerned recovery system reliability and performance of the on-board computer. These were verified during a drop test campaign. The payload, avionics and recovery modules were dropped from a helicopter and obtained data was analysed. The first launch of the rocket is scheduled for October 2017. Follow-on actions and technology maturation plans are presented.
    Abstract document

    IAC-17,A2,5,2,x40054.brief.pdf

    Manuscript document

    IAC-17,A2,5,2,x40054.pdf (🔒 authorized access only).

    To get the manuscript, please contact IAF Secretariat.