The SPARTAN research aims at developing a throttable propulsion technology, which is mandatorily needed for any planetary soft and precision landing. It relies on the hybrid engine technology, exploiting its capability of being throttled and its proper performances. This research is complementary to ESA TRP and Piedmont Regional development programs. It implements and strengthens the technological base in view of the future robotics and manned space exploration missions. The outcomes from the SPARTAN development can be reflected also in many other Earth/Space civilian applications, exploiting both the throttling capability of the propulsion system and the peculiar characteristics of the hybrid engine technology, like: safety, minimum environmental impact (green propellants), lower life cycle costs, responsiveness, competitive Performances, increased reliability, soft ignition and shutdown. The hybrid propulsion system is formed by two major constitutors: the engine itself, housing the fuel, and the oxidizer injection system. The research focuses on three major objectives, needed to achieve the soft and precision landing capabilities: - The engine design, specific for throttling functionality - The oxidizer throttable device development - The design of the landing case: test bench and testing procedures. Development will be supported by establishing an advanced coding, enabling the definition of the fuel and the throttling behavior of the hybrid engine. Engine definition will be supported by development tests: cold injection case, dedicated to the throttling device, and hot firing on subscale model, merging the throttling device and a subscale engine. In parallel a landing test and associated landing model (flying test bed) will be developed, providing for proven landing model and landing test capabilities. These capabilities will allow demonstrating the soft and precision landing features of a throttable hybrid propulsion technology

Description in English
The SPARTAN research aims at developing a throttable propulsion technology, which is mandatorily needed for any planetary soft and precision landing. It relies on the hybrid engine technology, exploiting its capability of being throttled and its proper performances. This research is complementary to ESA TRP and Piedmont Regional development programs. It implements and strengthens the technological base in view of the future robotics and manned space exploration missions. The outcomes from the SPARTAN development can be reflected also in many other Earth/Space civilian applications, exploiting both the throttling capability of the propulsion system and the peculiar characteristics of the hybrid engine technology, like: safety, minimum environmental impact (green propellants), lower life cycle costs, responsiveness, competitive Performances, increased reliability, soft ignition and shutdown. The hybrid propulsion system is formed by two major constitutors: the engine itself, housing the fuel, and the oxidizer injection system. The research focuses on three major objectives, needed to achieve the soft and precision landing capabilities: - The engine design, specific for throttling functionality - The oxidizer throttable device development - The design of the landing case: test bench and testing procedures. Development will be supported by establishing an advanced coding, enabling the definition of the fuel and the throttling behavior of the hybrid engine. Engine definition will be supported by development tests: cold injection case, dedicated to the throttling device, and hot firing on subscale model, merging the throttling device and a subscale engine. In parallel a landing test and associated landing model (flying test bed) will be developed, providing for proven landing model and landing test capabilities. These capabilities will allow demonstrating the soft and precision landing features of a throttable hybrid propulsion technology

Key words in English
Space exploration, Hybrid propulsion, Throttling capabilities, Planet access, Soft landing, Green Propellant

7E11027

Czech

Píštěk Antonín, prof. Ing., CSc. - principal person responsible

Institute of Aerospace Engineering
- responsible department (1.1.1989 - not assigned)
Institute of Aerospace Engineering
- beneficiary (1.1.2011 - 1.3.2014)

PEJCHAR, J.; KALNÝ, J.; POPELA, R.: Demonstrátor meziplanetární sondy pro pozemní zkoušky. (Funkční vzorek)
Detail

MARVAN, A.; PEJCHAR, J.; POPELA, R.; JEBÁČEK, I.: Automatické vystřelovací zařízení raketového záchranného systému. (Funkční vzorek)
Detail

DVOŘÁK, P.; HRADIL, J. Numerical simulation of cavitation valve flow. In ANSYS 2012 Setkání uživatelů a konference. Tesaříkova 1024/9 102 00 Praha 10: ARCADEA, 2012. p. 33-39. ISBN: 978-80-905040-1-1.
Detail

Responsibility: Píštěk Antonín, prof. Ing., CSc.