The ILR-33 AMBER 2K ROCKET – dedicated access to suborbital experimentation

Paper number

IAC-19,D2,6,8,x50868

Author

Mr. Michal Pakosz, Poland, Institute of Aviation

Coauthor

Mr. Adam Okninski, Poland, Institute of Aviation

Coauthor

Mr. Bartosz Bartkowiak, Poland, Institute of Aviation

Coauthor

Mr. Pawel Nowakowski, Poland, Institute of Aviation

Coauthor

Mr. Tomasz Noga, Poland, Institute of Aviation

Coauthor

Mr. Jan Matyszewski, Poland, Institute of Aviation

Coauthor

Mr. Dawid Cieslinski, Poland, Institute of Aviation

Coauthor

Mr. Blazej Marciniak, Poland, Institute of Aviation

Coauthor

Mr. Damian Kaniewski, Poland, Institute of Aviation

Coauthor

Prof. Piotr Wolanski, Poland, Institute of Aviation

Year

2019

Abstract

ILR-33 AMBER rocket has been under development since late 2014 by Warsaw Institute of Aviation. The platform was verified in 2017 during a successful low-altitude flight and thus became the first rocket in the world that utilizes High Test Peroxide of 98% concentration. This test enabled the development of an improved version of AMBER – the „2K” version. ILR-33 AMBER 2K differs from its base configuration mainly by enlarged Solid Rocket Boosters, which enable to reach apogee over 100 km with increased payload mass. The rocket is also propelled by a hybrid motor using polyethylene as fuel.
The article presents the rocket’s performance as a microgravity platform and for suborbital testing of rocket-related technologies. AMBER 2K aims at relatively small experiments that require dedicated and quick access to space, what is in line with New Space trends. Due to the compact size of the rocket it is possible to provide services in Polish test ranges for limited apogees, exceeding stratospheric platforms’ capabilities, but still sufficient for specific payloads.
The article covers ground and in-flight test results. Consecutive flights of ILR-33 AMBER in 2019 are discussed. Test stand performance of the improved version of Solid Rocket Boosters is presented.
The AMBER rocket can also be treated as a technology demonstrator. Concepts of guidance and orientation control systems are shown. The guidance control is based on a canard subystem, which has been developed up to engineering model. The orientation control system concept is intended for microgravity flight phase and is based on Hydrogen Peroxide thrusters.

Abstract document

IAC-19,D2,6,8,x50868.brief.pdf

Manuscript document

IAC-19,D2,6,8,x50868.pdf (🔒 authorized access only).

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