Design study of the Small Rocket Launcher using an environmental-friendly propellant

Paper number

IAC-15,D2,7,10,x31089

Author

Mr. Kamil Sobczak, Institute of Aviation, Poland

Coauthor

Mr. Bartosz Bartkowiak, Warsaw University of Technology, Poland

Coauthor

Mr. Dawid Cieśliński, Warsaw University of Technology and Institute of Aviation, Poland

Coauthor

Mr. Wojciech Florczuk, Institute of Aviation, Poland

Coauthor

Mr. Dominik Kublik, Institute of Aviation, Poland

Coauthor

Mr. Blazej Marciniak, Institute of Aviation, Poland

Coauthor

Mr. Jan Matyszewski, Warsaw Institute of Aviation, Poland

Coauthor

Mr. Paweł Nowakowski, Warsaw University of Technology, Institute of Aviation, Poland

Coauthor

Mr. Adam Okninski, -, Poland

Coauthor

Mr. Michał Pakosz, Warsaw University of Technology and Institute of Aviation, Poland

Coauthor

Dr. Grzegorz Rarata, Institute of Aviation, Poland

Coauthor

Mrs. Karolina Rokicka, Institute of Aviation, Poland

Coauthor

Mr. Pawel Surmacz, Warsaw Institute of Aviation, Poland

Coauthor

Mr. Piotr Wolanski, Polish Academy of Sciences, Poland

Year

2015

Abstract

This paper gives an overview of the results of conceptual design study of a small rocket launcher that was performed at the Institute of Aviation in Warsaw, Poland. A launcher for small satellites needs to follow the design philosophy that should result in simplicity, reliability and cost efficiency to be able to compete successfully at a global commercial market level. The discussed issue will be the application of innovative and low-cost propulsion approach to various pressure-fed space transportation systems, including those for first and upper stages. 
The analysis of the rocket configuration, propellant considerations, existing tools for launcher design, manufacture and testing are presented shortly in the article. The development and operations costs along with payload market analysis are also included.
Two possible configurations of the rocket have been considered for evaluation it as a launcher capable of delivering a nano/small satellites to LEO orbit. The two stage rocket with the first stage propelled by a turbo-pump rocket engine has been considered. The second option that has also been investigated is the three stage rocket with all pressure fed liquid engines.
The results of propellants trade-off studies are presented as well. Their maturity status in space propulsion technologies, availability and advantages in comparison with the currently used propellants has been discussed. All considered propellants have been assumed with the use of the High Test Peroxide as an oxidizer.
A reasonably wide range of expertise gained, also at Space Technology Department during the development of various propulsion systems based on highly concentrated hydrogen peroxide – that is hybrid, mono- and bi-propellant rocket engines and sounding rockets – has been summarized and highlighted too. The importance of such experience and knowledge, especially in the context of small rocket launcher design, manufacture and exploitation has been encompassed.

Abstract document

IAC-15,D2,7,10,x31089.brief.pdf

Manuscript document

(absent)