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
- Manuscript document
IAC-17,A2,5,2,x40054.pdf (🔒 authorized access only).
To get the manuscript, please contact IAF Secretariat.