Verification of energy efficiency of a low-thrust liquid-propellant engine with the deflector-centrifugal injecting pattern

Abstract

The article gives information about developed in Design Bureau Chemical Machinery behalf A.M. Isaev deflector centrifugal pattern mixing of propellants nitrogen tetroxide and unsymmetrical dimethylhydrazine, in which established liquid rocket engines (LREST) in a wide range of rods from 25 to 400 N. Design Bureau Chemical Machinery behalf A.M. Isaev on the basis of joint with KUAI (now SSAU named after Korolev, Samara) and studies on the characterization of the primary oxidant film on the deflector, the parameters of the secondary oxidant film on the inner wall of the combustion chamber, the parameters of the film cone spray nozzle centrifugal fuel in a venue with a secondary film oxidant parameters of the layer of liquid-phase mixing the oxidizer and fuel components on the inner wall of the combustion chamber was established mathematical model calculations of liquid-phase mixing of the components in the mixing element LREST with centrifugal deflection circuit mixing the components on the wall of the combustion chamber. Based on this Design Bureau Chemical Machinery behalf A.M. Isaev developed technique of calculations and design of LREST with centrifugal deflection circuit mixing fuel. Using this method in Design Bureau Chemical Machinery behalf A.M. Isaev designed iPart LREST 25, 50, 100, 200, 400N, with deflector centrifugal mixing scheme. Parametric studies were conducted LREST of 25, 50, 100, 200, 400 N to determine the degree of influence of various design and operational parameters of the element, such as the angle of leakage jets on the deflector angle leakage of primary films on the wall of the combustion chamber, the mean free path of the secondary oxidant film the wall of the chamber performance-liquid phase mixing of the fuel components. The results of experimental studies have confirmed the increased energy efficiency of small thrust jet engine thrust of 25, 50, 100, 200, 400 N with deflection centrifugal mixing scheme, expressed in a high specific impulse of more than 3000 m / s at the same time a large margin the temperature of engine components. Maximum temperature of the wall of the combustion chamber is at 1200 °С that is provided by a large margin – 600 °С (permissible material temperature chamber - niobium alloy with molybdenum coating bi-silicified MoSi2 – 1800 °С).

About the authors

Y. I. Ageenko

Isaev Chemical Machinery Design Bureau – Branch of Federal State Unitary Enterprise «Khrunichev State Research and Production Space Center»

Author for correspondence.
Email: kbhimmash@korolev-net.ru

Candidate of Science (Engineering)

Chief designer lines, chief designer, renowned designer

Russian Federation

I. V. Pegin

Isaev Chemical Machinery Design Bureau – Branch of Federal State Unitary Enterprise «Khrunichev State Research and Production Space Center»

Email: kbhimmash@korolev-net.ru

Deputy of the chief of the department liquid rocket engines of the small thrust

Russian Federation

References

  1. Ageenko Y.I. Мixing parameters investigations and methods of approach to calculations and development of the thrusters with a spray-centrifugal scheme of NT and NDMH mixing on the confusion chamber wall in considered // Vestnik of the Samara State Aerospace University. 2009. No. 3(19), part 2. P. 171-177. (In Russ.)
  2. Ageenko Y.I., Ilin I.V., Pegin I.V., Shalamov E.A. Investigation of the possibility of the creation lrest by thrust 400 n with a baffle-centrifugal scheme of NT and NDMG mixing // Vestnik of the Samara State Aerospace University. 2012. No. 3(34), part 1. P. 71-76. (In Russ.)
  3. Kozlov A.A., Vorobiev A.G., Borovik I.N. Zhidkostnye raketnye dvigateli maloi tyagi [Liquid propellant rocket engine of small thrust]. Moscow: MAI Publ., 2013 208 p.
  4. Dvukhkomponentnyy raketnyy dvigatel' maloy tyagi 11D428A-16. Ofitsial'nyy sayt FGUP «NIIMASh» [Two component thruster 11D428A-16. Official site of FSUE R&DIME]. Available at: http://niimashspace.ru/index.php/produce/rkt/33-rdmt/7-11428-16
  5. (accessed 06.2014).
  6. Dvukhkomponentnyy raketnyy dvigatel' maloy tyagi 11D458M. Ofitsial'nyy sayt FGUP «NIIMASh». [Two component thruster 11Д458М. Official site of FSUE R&DIME]. Available at: http://niimashspace.ru/index.php/produce/rkt/33-rdmt/12-114582
  7. (accessed 06.2014).
  8. N Bipropellant Apogee Motors. The official website for Airbus Defence & Space. Available at: http://cs.astrium.eads.net/sp/spacecraft-propulsion/apogee- motors/ 400n-apogee-motor.html (accessed: 03.06.2014).
  9. N Bipropellant Thruster. The official website for Airbus Defence & Space. Avail able at: http:// cs.astrium.eads.net/sp/spacecraft-propulsion/ bipropellant-thrusters/22n-thruster.html (accessed: 03.06.2014)
  10. N Bipropellant Thrusters for ESA`s ATV. The official website for Airbus Defence & Space. Available at: http://cs.astrium.eads.net/sp/spacecraftpropulsion/bipropellant-thrusters/220n-atvthrusters.html
  11. (accessed: 03.06.2014).
  12. Liquid rocket systems. Official site of Delft University of Technology. Available at: http://www.lr.tudelft.nl/ index. pdf?id=26229&L=1
  13. (accessed: 03.06.2014).

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