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... A metalized fuel was used and its grain included the addition of solid oxidizer particles to increase the grain regression rate. Further attention was given to using hydrogen peroxide as an oxidizer, and concepts of satellite propulsion systems were proposed [98]. Propellant-grade hydrogen peroxide was desired. ...
This paper presents the development of indigenous hybrid rocket technology, using 98% hydrogen peroxide as an oxidizer. Consecutive steps are presented, which started with interest in hydrogen peroxide and the development of technology to obtain High Test Peroxide, finally allowing concentrations of up to 99.99% to be obtained in-house. Hydrogen peroxide of 98% concentration (mass-wise) was selected as the workhorse for further space propulsion and space transportation developments. Over the course nearly 10 years of the technology’s evolution, the Lukasiewicz Research Network—Institute of Aviation completed hundreds of subscale hybrid rocket motor and component tests. In 2017, the Institute presented the first vehicle in the world to have demonstrated in-flight utilization for 98% hydrogen peroxide. This was achieved by the ILR-33 AMBER suborbital rocket, which utilizes a hybrid rocket propulsion as the main stage. Since then, three successful consecutive flights of the vehicle have been performed, and flights to the Von Karman Line are planned. The hybrid rocket technology developments are described. Advances in hybrid fuel technology are shown, including the testing of fuel grains. Theoretical studies and sizing of hybrid propulsion systems for spacecraft, sounding rockets and small launch vehicles have been performed, and planned further developments are discussed.
... During the early phase of the design two propulsion systems were taken into consideration: a liquid rocket engine and a hybrid rocket motor. Experience with High Test Peroxide combined with Jet-A (liquid rocket engine) [26,27] and HTPB (hybrid rocket motor) [28,29] already existed at IoA. Theoretical performance obtained for hybrid rocket motors using storable propellants is nearly identical to that of liquid rocket engines using non-cryogenic propellants. While combustion efficiency is lower for hybrid rocket motors than for the bipropellants, additives such as aluminium powder or aluminium hydrate can increase performance beyond the one obtained from typical bipropellant engines while using the same oxidizer. ...
This paper gives an overview of the development of the ILR-33 ”Amber” sounding rocket designated for microgravity experiments, that is under development at Institute of Aviation in Warsaw, Poland. The lack of an easily accessible and affordable platform for this kind of research was one of the key reasons for this work. The proposed design enables performing experiments in microgravity for almost 150 seconds with an apogee over 100 km. Combining these results with a relatively low price per launch and short deployment time gives a possibility to establish a firm position on the dynamic market. This article describes also the rocket structure and the vehicle's capabilities. The proposed design utilizes a hybrid rocket motor with High Test Peroxide as an oxidizer along with two reusable solid rocket boosters. The early phase analysis of the rocket configuration and propellant considerations are also presented in the paper. Furthermore, there have been already several on-ground test performed such as: wind tunnel research and motor firings. The proposed design is considered as an introduction to small launch vehicle technology.
... In the Institute of Aviation, Space Technology Centre, a spacecraft propulsion module for maneuvering and orbit transfer have been designed. It consists of a hybrid rocket engine, that is used for delta-V, and small 2N thrusters for attitude control [8]. It seems to be quite similar to the existing device -MoTV, developed by Sierra Nevada Corporation, USA. ...
Nowadays the technology level of such domains, like: electronics, optics, power sources etc. makes possible to build satellite components and subsystems, which are small in size as well as light-weight. The current trend is to launch small (about 100 - 200 kg) satellites into LEO. Such satellites can be used for many different proposes, but due to relatively low altitude, most application can be for securities mission such as remote sensing, telecommunications and other. In order to keep a spacecraft on the defined LEO, in which the atmospheric influence cannot be neglected, delta-V for satellite maneuver is required. This kind of velocity change can be provided by the integrated rocket propulsion system. Such propulsion system can provides also attitude control, and in combination with main rocket engine, even makes possible to realize flexible missions, such as these, which demand not only orbit correction but also orbit transfer.
Rocket engines for the on-orbit propulsion system should meet special requirements. Apart from high
performance and reliability, they should be restartable as well as throttle-able. Propellants must be long-term
storable. Current trends in space propulsion development, especially in Europe, suggest to focus on green
propellants, which are regarded to replace hydrazine and its derivatives in the near future. Moreover, the use of nontoxic and easy-to-handle chemicals, such as hydrogen peroxide, makes possible to extend the sphere of entities, working on the research and development of space propulsion. Since the propellant is “green”, it does not require special, expensive infrastructure. The only limitation might be legal restrictions for individual countries, concerning possession and trading of high-energy chemicals. Green propellants are nevertheless the driving force for low-cost space propulsion.
Due to the fact, that hydrogen peroxide can be used both as oxidizer and mono-propellant, it seems to be the
perfect solution for a small propulsion system, which uses mono-propellant thrusters for ACS and a bi-propellant engine for delta-V. This kind of space propulsion module have been designed in the Institute of Aviation (IoA) in Poland and is presented in the paper. A hybrid rocket engine (HRE) have been chosen for the bi-propellant application. Currently this technology is under development. IoA have designed, built and is still testing a 100 N HRE. This hybrid uses 98% hydrogen peroxide (HTP-class) as oxidizer and Hydroxyl-Terminated Poly-Butadiene (HTPB) as solid fuel. It is self-ignitable and restartable.
The own, advanced technology for preparation of ultra-pure, highly concentrated (regularly 98%, possible up to 99,9%) hydrogen peroxide have been already developed in IoA. In the laboratory environment this technology easily covers the own needs for R&D activities. It might be also simply scaled-up , in case the demand increases.
Nearly ten years after joining the European Space Agency (ESA), Poland is continuing to make larger steps to increase its role in the European R&D market. While the Polish contribution to ESA is not large in terms of budget, Space Propulsion has been one of the areas of interest of Polish entities. The ESA Polish Industry Incentive Scheme (PLIIS) roadmap presented Chemical Propulsion as one of the directions for follow-on developments and an area, where potential European and global leadership could be achieved in specific narrow niches. Lukasiewicz Research Network – Institute of Aviation (IoA) is the national leader, so far taking part in 23 out of 29 ESA contracts, which have been given to Polish entities in this field. The Institute’s Chemical Propulsion team grew from 5 to 90 people and Lukasiewicz Research Network - Institute of Aviation is now one of the main actors in green propulsion research in the region.
