Two automated laboratory stands for detonation tests of combustion chambers and small rocket engines

Main technical characteristics

Rocket propellants supply pressure: up to 20 [MPa]
Used oxidizers (gaseous, otherwise stated): air, oxygen, nitrous oxide (gaseous and liquid)
Used fuels (gaseous and liquid, otherwise stated): methane, propane, butane, kerosene, hydrogen (gaseous)
Thrust: up to 2 [kN]
Volume of air tank: 2 [m3] (6 [m3] is planned)

Operational Capacity

Rocket RDE Propulsion Test Bench has capability of testing small combustion chambers and engines geometries in various configurations run by numerous propellants and pressures. Gaseous hydrogen, numerous liquid and gaseous hydrocarbons (e.g. methane, propane, butane) so far were tested at pressure range of up to 200 bars. Also liquid and gaseous nitrous oxide is being highly exploited.
Ramjet RDE Propulsion Test Bench is focused on testing air – kerosene propellant mixtures by the mean of 2m3 air tank which provides supersonic air flow in the engine duct.
Laboratory has got heritage in research aimed at adopting RDE combustion chamber into turboshaft engine (GTD-350) as well.
Measurements in the laboratory cover temperature, pressure, very high frequency pressure measurement, flow rate, thrust. All means of security, quality control and standards of measurement reliability are being kept and constantly overseen.

Contact Information

Łukasiewicz Research Network – Institute of Aviation
al. Krakowska 110/114
02-256 Warsaw, Poland
central: (+48) 22 846 00 11
fax: (+48) 22 846 44 32
e-mail: ilot[at]

KRS 0000862006, NIP 1070046338, PL 1070046338, Regon: 387193275
90 1240 6247 1111 0000 4977 2760

Directions to the bus stop “Instytut Lotnictwa”
by tram: 7, 9, 15
by bus: 141, 154, 317, N38, N88

Warsaw (Poland)