With the ILR-33 BURSZTYN 2K rocket, a cost-effective, scalable and environmentally friendly design, we have the ability to efficiently experiment in microgravity and probe the atmosphere. The ILR-33 BURSZTYN 2K rocket is used during flight as a suborbital test platform, capable of providing up to 150 seconds of microgravity conditions for a 10 kg payload. The payload compartment can be adapted to the Customer’s requirements, providing the best possible test conditions.

ILR-33 BURSZTYN 2K

The ILR-33 BURSZTYN 2K rocket is a flying suborbital platform designed at Łukasiewicz – Institute of Aviation. ILR-33 BURSZTYN 2K is offered as a standalone product, as well as a platform that enables research services. Powered by a hybrid rocket engine, supported by two auxiliary engines, it allows the mission to be tailored to the specific needs of the cargo being lifted.

ILR-33 BURSZTYN 2K – Main advantages

• the world’s first rocket using h2o2 with a concentration exceeding 98%
• innovative hybrid rocket engine
• low cost of suborbital flights
• scalability – the possibility of developing larger rocket systems

Technical data

ILR-33 BURSZTYN 2K
Length	4.6 m
Main stage diameter	230 mm
Flight ceiling	100 km
Maximum speed	1300 m/s
Payload weight	10 kg
Maximum gravity load	14 g
Duration of microgravity (10-3 g, 5 kg)	150 s

Auxiliary engines
Type	Solid propellant
Maximum thrust	2 x 16 000 N
Working time	6 s
Combustion chamber	Composite structure

Main engine
Type	Hybrid rocket engine
Oxidizer	Hydrogen peroxide (H2O2), concentration 98%+
Fuel.	Polyethylene
Maximum thrust	4,000 N
Working time	40 s
Combustion chamber	Composite structure

Examples of applications

• Tests in microgravity (200 s after 10-2 g);
• Validation of the avionic systems;
• Verification of the control systems;
• Qualification of the satellites;
• Tests of the separation mechanism of auxiliary engines;
• Atmospheric sounding;
• Imitator of ballistic air targets;
• Ground infrastructure tests.

Suborbital flights

The main objective of the ILR-33 BURSZTYN 2K rocket project is to validate key technologies developed for use in modern suborbital platforms, satellites and small carrier rockets. Bursztyn rocket is also a cost-effective, scalable and ecological construction, enabling efficient experimentation in microgravity and atmospheric probing. It can provide up to 150 seconds of microgravity conditions for a 10 kg payload. The basic version of the rocket has been successfully tested in flight. The payload compartment can be adapted to the Customer’s requirements, providing the best possible test conditions.

Rocket technologies – engineering services

Our portfolio includes satellite equipment used in orbit, as well as numerous suborbital rockets – military and civilian. Striving for engineering excellence and supporting global sustainable development, we are open to both domestic and international cooperation. Thanks to a wide range of services in the area of designing and optimizing solutions for aviation and space, the services we offer contribute to the development of new technologies.

• Designing vehicles and drives:
  • Solid, hybrid and liquid rocket propulsion,
  • Mechanisms, valves, bearings,
  • Composite structures,
  • Navigation and control systems,
  • On-board computers and other electronic systems,
  • Structural strength (finite element method),
  • Flow analysis, combustion modeling (finite element method),
  • Systems engineering

• Systems validation and testing:
  • Satellite and rocket propulsion systems,
  • Non-destructive tests,
  • Environmental tests,
  • Environmental tests,
  • Material tests – strength, fatigue, etc.,
  • Chemical tests.

Rocket subsystems and components

In addition to our commitment to propulsion, our engineers have developed key subsystems for rockets and satellites. The acquired knowledge enables the design of components in terms of even the most demanding assumptions.

Pyrotechnic devices

• Pyrotechnic cutters,
• linear hollow charges,
• pyrovalves,
• igniters,
• actuators,
• pushers,
• mortars.

Missile recovery systems

• Parachute systems,
• wind tunnel testing,
• use of the flat spin phenomenon,
• drop tests,
• simulations,
• sea surface recovery system.

Control systems and electronic systems for rockets

• On-board computers,
• launch management systems,
• data acquisition,
• control systems.

Separation mechanisms

• Separation systems for auxiliary engines, separation system for the main rocket member,
• Separation methods:
  • „Fire in the hole”,
  • pyrotechnic separation,
  • aerodynamic separation.

Avionic rocket control systems

We are working on avionic equipment for rockets in three areas:

• Measurements

We have extensive experience in integrating systems for measuring, among other things, basic flight parameters such as linear and angular velocities and the spatial position of the rocket. We have used proprietary inertial navigation algorithms, which enable short-term autonomous navigation calculations, in the on-board computers of the rockets we have developed.

• Control

We have developed flight control algorithms for rockets made at the Institute of Aviation.
In the ILR-33 AMBER 2K rocket, the on-board computer controls the rocket flight by means of coordinated inclination of the control surfaces – four canards placed symmetrically in the front part of the rocket. In other rockets – by means of control motors located around the rocket’s hull.

• Special features

We have also developed algorithms responsible for the implementation of the assumed flight plan and the electrical initiation of other rocket systems, such as the launch system, separation system or landing part recovery system. The rocket’s on-board computer, designed and built, is an example of this type of solution.

The developed algorithms and control methods are implemented by on-board computers designed, manufactured and tested in one of our certified laboratories.

• On-board computer for the ILR-33 BURSZTYN 2K rocket

As part of the ILR-33 BURSZTYN 2K program projects, our engineers have developed a mission control computer with the following functionalities:

• performing navigational calculations according to proprietary inertial navigation algorithms (INS);
• rocket flight control;
• ensuring telemetric and visual communication between the rocket and the ground control station at a distance of up to 100 km;
• activation of the rocket pyrotechnic initiators.