Mathematical simulation of dynamic processes in the propellant feed system of launch vehicle space stages in microgravity
Journal Title: Технічна механіка, Техническая механика, Technical Mechanics - Year 2018, Vol 4, Issue 4
Abstract
The steady trend towards the development of space stages capable of putting into orbit several spacecraft with a single launch vehicle (LV) by multiple restarts of the stage sustainer engine in microgravity calls for the solution of a complex of problems aimed at assuring the continuity of the liquid propellant components in the propulsion system feed lines. The aim of this paper is mathematical simulation of dynamic processes in the pro-pellant feed system of LV space stages to assess its operability in microgravity in passive flight segments with an operating attitude control and stabilization system and at sustainer engine starts in periods with minimum tank filling levels. To solve these problems, the authors developed a methodology based on the finite-element method, the volume of fluid method, 3D CAE technologies, and the impedance method. The paper presents mathematical models of dynamic processes in a liquid-propellant LV space stage pro-pulsion feed system that has a capillary propellant management system. The mathematical models of spatial oscillations of a LV space stage with a spacecraft developed with account for the design features of the in-tank devices and propellant feed systems made it possible to determine the mode shapes and the motion parameters of the free surfaces of the propellant components in the tanks (the oxidizer tank and the fuel tank) of the stage and identify flight regimes potentially dangerous in terms of the possibility of the pressurization gas or the substituent gas dissolved in the propellant components penetrating into the engine propellant lines. Quantitative estimates of the propellant management device operability in these regimes were obtained. The mathematical models of hydrodynamic processes in a space stage liquid propellant propulsion system presented in this paper allow one to identify sustainer engine start conditions in which the pressurization gas may penetrate in the engine propellant lines and determine the parameters of dynamic processes in a space stage feed system at sustainer engine starts and cutoffs. The mathematical model of low-frequency hydrodynamic processes in a space stage feed system at sustainer engine starts and cutoffs was tested using the results of experimental studies (on water) of space stage sustainer engine cutoffs, and the calculated oscillation frequencies and amplitudes were shown to be in satisfactory agreement with the experimental ones.
Authors and Affiliations
O. Pylypenko, I. Bashliy, S. Dolhopolov
Keywords
Related Articles
- EP ID EP466740
- DOI -
- Views 70
- Downloads 0
Results of studies of kinematic and power parameters of transmission for mine diesel locomotive with differential at output
The work is devoted to the problem of a complex study of variations in the power, kinematic and energy parameters of a hydrostatic mechanical transmission "with a differential at output" during its operation in traction...
Effect of strip inserts on the stress and strain field in a plate with an elongated rectangular opening
This paper considers the stress and strain field in an elastic square plate with an elongated rectangular opening whose sides are reinforced with rectangular inserts. The aim of this work is to study the effect of the in...
Measurement of strains of soil base under short-time loads
Measurements of soil strains under loads are of importance in resolving various problems pertaining to na-tional economy. Until the present time the solution of the problem on measurements of complete and elastic settlem...
Physical simulation of the interaction of spacecraft with plasma flows and electromagnetic radiation fluxes in the Earth’s ionosphere
This paper briefly overviews the results of the investigations into problems of physical simulation of space-craft – ionospheric plasma interaction and spacecraft exposure to a complex of space factors conducted at the D...
Combined use of random search methods and gradient methods in the optimization of rocket design parameters and control programs
The aim of this paper is to develop a methodology for optimizing, at the initial design stage, the key charac-teristics of a rocket with a solid-propellant sustainer engine which can follow a ballistic, an aeroballistic,...