Parametric Calculation of the Limiting Characteristics of Electrization of Structural Elements of the Solid Propellant Rocket Engine Exhaust Duct

Authors: Fedotova K.V., Yagodnikov D.A. Published: 17.04.2024
Published in issue: #1(148)/2024  


Category: Aviation and Rocket-Space Engineering | Chapter: Thermal, Electric Jet Engines, and Power Plants of Aircrafts  
Keywords: weakly ionized plasma, electrization, power condensed system, floating potential, double electric layer


The paper presents parametric study of the influence of the model power condensed system composition and the combustion products and pressure temperature in the combustion chamber (4--10 MPa) on the floating potential at the internal ideal wall of the solid propellant rocket engine tract and the potential alteration in the double layer. A metal-free model power condensed system was considered, as well as systems based on ammonium perchlorate and inert combustible binder with addition of the powdered aluminum and boron. A mathematical model of floating potential on the charged wall surface was used assuming Maxwellian distribution of electrons in the near-wall area and the collision-free plasma. Weak dependence of pressure in the combustion chamber on the wall floating potential was established; however, the floating potential modulus was decreasing due to a decrease in static pressure along the solid propellant rocket engine duct. It was revealed that the floating potential absolute value on the ideal inner wall of the solid propellant rocket engine duct was growing with the increased temperature of the combustion products of the power condensed system, which provided the greatest influence compared to the other parameters under consideration. The use of a more power-intensive power condensed system leads to an increase in the double electric layer extent, where quasineutrality of the weakly ionized combustion products is disrupted due to an increase in their temperature

This work was supported by the State Program for Fundamental Research of the Ministry of Education and Science of Russian Federation (no. 0705-2020-0044)

Please cite this article in English as:

Fedotova K.V., Yagodnikov D.A. Parametric calculation of the limiting characteristics of electrization of structural elements of the solid propellant rocket engine exhaust duct. Herald of the Bauman Moscow State Technical University, Series Mechanical Engineering, 2024, no. 1 (148), pp. 21--35 (in Russ.). EDN: CTTXTX


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