Development of ILR – 33 Amber sounding rocket for microgravity experiments

Paper number

IAC-16,A2,5,3,x35542

Coauthor

Mr. Blazej Marciniak, Institute of Aviation, Poland

Coauthor

Mr. Bartosz Bartkowiak, Institute of Aviation, Poland

Coauthor

Mr. Wojciech Florczuk, Institute of Aviation, Poland

Coauthor

Mr. Kamil Sobczak, Institute of Aviation, Poland

Coauthor

Mr. Damian Kaniewski, Institute of Aviation, Poland

Coauthor

Mr. Jan Matyszewski, Warsaw Institute of Aviation, Poland

Coauthor

Mr. Adam Okninski, Institute of Aviation, Poland

Coauthor

Mr. Pawel Nowakowski, Institute of Aviation, Poland

Coauthor

Mr. Michal Pakosz, Institute of Aviation, Poland

Coauthor

Mr. Dawid Cieslinski, Institute of Aviation, Poland

Coauthor

Dr. Grzegorz Rarata, Institute of Aviation, Poland

Coauthor

Mr. Pawel Surmacz, Warsaw Institute of Aviation, Poland

Coauthor

Mr. Dominik Kublik, Institute of Aviation, Poland

Coauthor

Mrs. Karolina Rokicka, Institute of Aviation, Poland

Coauthor

Mr. Jaromir Smetek, Institute of Aviation, Poland

Coauthor

Mr. Damian Rysak, Institute of Aviation, Poland

Coauthor

Prof. Piotr Wolanski, Polish Academy of Sciences, Poland

Year

2016

Abstract

Paper gives an overview of the development of ILR – 33 Amber sounding rocket designated for microgravity experiments, that was performed in Institute of Aviation in Warsaw, Poland. The lack of easy accessible and affordable platform for this kind of research was one of the key reasons for this work. Proposed design enables to perform experiments in microgravity for almost 150 seconds with apogee over 100 km. Combining this results with relatively low price per launch and short deployment time gives firm position on the market. The paper covers different type of payload considerations and cost analyses.
This article describes also rocket design and its capabilities. Proposed design utilizes hybrid type of rocket motor with High Test Peroxide as an oxidizer along with two reusable solid rocket boosters.  The early phase analysis of the rocket configuration and propellant considerations are also presented in the paper. Furthermore already performed testing phase including: wind tunnel research, motors design, manufacture and tests and drop down tests is also covered in this article. 
The proposed design is also considered as introduction phase for small rocket launcher that could deliver pico and nano satelites to LEO orbits. This solution is described by the possibility of rocket air-platform launch.

Abstract document

IAC-16,A2,5,3,x35542.brief.pdf

Manuscript document

IAC-16,A2,5,3,x35542.pdf (🔒 authorized access only).

To get the manuscript, please contact IAF Secretariat.