ILR-33 „Amber” Rocket - a Platform For Microlauncher System Technology Development

Paper number

IAC-18,D2,9-D6.2,11,x45735

Author

Mr. Dawid Cieslinski, Poland, Institute of Aviation

Coauthor

Mr. Adam Okninski, Poland, Institute of Aviation

Coauthor

Mr. Michal Pakosz, Poland, Institute of Aviation

Coauthor

Mr. Tomasz Noga, Poland, Institute of Aviation

Coauthor

Mr. Tobiasz Mayer, Poland, Institute of Aviation

Coauthor

Mr. Damian Kaniewski, Poland, Institute of Aviation

Coauthor

Mr. Wojciech Florczuk, Poland, Institute of Aviation

Coauthor

Prof. Piotr Wolanski, Poland, Polish Academy of Sciences

Coauthor

Mr. Bartosz Bartkowiak, Poland, Institute of Aviation

Coauthor

Dr. Pawel Surmacz, Poland, Institute of Aviation

Year

2018

Abstract

With the increasing need for individual launch services for small satellites, plenty of microlauncher concepts are being elaborated within the space sector worldwide. As it is an early phase of the process and only a few offers are available, there is still an opportunity for newcomers to participate in the emerging microlauncher market. 

ILR-33 “Amber” rocket is  the latest  achievement of Warsaw Institute of Aviation. The main goal of the “Amber” rocket project was to develop a highly scalable, cost-effective platform for in-flight validation of microlauncher technologies. Efficient green propellant hybrid rocket technology is to enable conducting suborbital missions for altitudes up to 100 km. ILR-33 provides up to two minutes of microgravity conditions ($10^{-3}$ to $10^{-6}$ g). All subsystems including launch support ground facilities have been developed in-house. The first flight, being a successful demonstration, was held in October 2017. Due to the test range restrictions and safety constraints, a flight with a 15 km ceiling was performed. Limited performance was achieved by reducing the mass of the oxidiser in the tank. The main hybrid motor utilises 98\% hydrogen peroxide (High Test Peroxide) as oxidizer and polyethylene as  fuel, with burn time of 40 s. The 2017 flight was the first in-flight demonstration of a vehicle using such high concentrations of hydrogen peroxide as oxidiser worldwide. Telemetry data is discussed.

This paper is to present the results from the first flight test and to focus on practical possibilities of up-scaling technologies with focus on vehicle propulsion. The paper discusses a concept of a microsatellite launch vehicle enabling delivering small payloads to 700 km Sun-Synchronous Orbits. Various technology trade-offs are presented with focus on decreasing non-recurring and recurring costs. Analyses of  current TRLs and national development capabilities are provided. The paper contains comparisons between various system architectures with Rough Order of Magnitude cost estimation. The technology development roadmap is shown and the proposed consumer-orientated service is described.

Abstract document

IAC-18,D2,9-D6.2,11,x45735.brief.pdf

Manuscript document

IAC-18,D2,9-D6.2,11,x45735.pdf (🔒 authorized access only).

To get the manuscript, please contact IAF Secretariat.