The investigation of thermal and gas dynamic processes in the combustion chamber of the rocket engine using slurry fuel

Bondarenko, S.V.; Dreus, Andrii; Lysenko, K. V.

doi:10.1177/0954410017704216

Cited by 5 publications

(3 citation statements)

References 6 publications

(6 reference statements)

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“…A given method makes it possible to ensure the guaranteed removal of an object within a specified time both in dense layers of the Earth's atmosphere and in higher orbit, including deep space. To implement a given method, tugs and various rocket propulsion systems are employed [6,7], including thrusters [8,9]. The disadvantage of this method is significant energy costs related to the need for fuel components to operate the systems that enable the removal process, which leads to the high cost of a particular implementation.…”

Section: Literature Review and Problem Statementmentioning

confidence: 99%

Analysis of ballistic aspects in the combined method for removing space objects from the nearEarth orbits

Dron

Golubek

Dubovik

et al. 2019

EEJET

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Section: Literature Review and Problem Statementmentioning

confidence: 99%

Analysis of ballistic aspects in the combined method for removing space objects from the nearEarth orbits

Dron

Golubek

Dubovik

et al. 2019

EEJET

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“…Therefore, a clear demand for the development of light and ultralight launch vehicles has formed in the launch services market. In conditions of tough competition, developers are forced to look for new inexpensive and reliable technical solutions in this area, for example, the use of original propulsion systems (Bondarenko et al, 2018;Cappelletti et al, 2018;Schmierer et al, 2019) or original body structures (Bolonkin, 2006) and others solutions (Fedaravic ˇius et al, 2019).…”

Section: Introductionmentioning

confidence: 99%

A simulation of the thermal environment of a plastic body of a new type of launch vehicle at the atmospheric phase of the trajectory

Dreus

Yemets

Dron

et al. 2021

AEAT

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Purpose Leading developers and providers in the modern space launch market note a splash in the development of ultralight launch vehicle (LV), driven by the growing demand for small satellites for large constellations in low Earth orbits. One of the promising ways to solve the problem of the quick launch of such satellites is to use a new type of ultralight launch vehicle with a plastic body. The project of such a launch vehicle was proposed by Oles Honchar Dnipro National University (Ukraine). Along with that, there is a need for appropriate research studies on the thermal resistance of the plastic shell, as the physical, mechanical and thermophysical characteristics of polymers significantly differ from traditional aerospace materials. The purpose of this study is to validate the design and ballistic parameters of such a launch vehicle in terms of providing an acceptable thermal environment at the atmospheric phase of the trajectory. Design/methodology/approach The workability of a new type of propulsion system is being investigated experimentally in bench conditions. To study the process of aerodynamic heating of a plastic shell, numerical modeling based on the integration of the flight dynamics and heat transfer equations is used. Findings Brief information about the design of a new type of ultra-light autophage launch vehicle with a plastic body is presented. A mathematical model for the movement of the launch vehicle at the atmospheric phase of the trajectory, and for the heating of the polyethylene body of the launch vehicle, taking into account the dynamic change in the atmospheric parameters is proposed. The influence of the motion trajectory on the thermal environment of the rocket body is investigated, rational motion trajectories and corresponding permissible g-loads are determined. Originality/value The fundamental possibility of using plastic (polyethylene) as a structural material and fuel for bodies of a new type of ultralight launch vehicles has been substantiated. It is shown that to ensure acceptable thermal conditions of a plastic body, it is necessary to use thermal insulation. It is proposed to use a polymeric Teflon coating as such thermal insulation. The results are important for the development of technologies for launching small satellites into orbit, as the use of plastic as the main structural material of the rocket body will significantly reduce the launch cost.

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“…The effect of solid particle content and maximum size of particle on the smallest droplet diameter that allows secondary atomization were analyzed by using applying the established droplet shell-forming model. Bondarenko et al [16] have investigated the thermal and gas dynamics processes in the combustion chamber of prospective rocket engines using slurry fuel, and experimental and numerical results of pressure and temperature in the combustion chamber were presented. Rahimi et al [17] formulated and characterized a type of gel propellant, and a laboratory-scale rocket engine with selected hypergolic neat-liquid and gelled bipropellant combinations was examined successfully.…”

Section: Introductionmentioning

confidence: 99%

Investigations on Internal Ballistic Characteristics of Pasty Propellant Rocket Engine

Shan

Chen

et al. 2021

International Journal of Aerospace Engineering

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Pasty rocket engines have broad application prospects in the aerospace field. To study the internal ballistic characteristics of the pasty propellant rocket engine, the burning surface change model of pasty propellant was built. The calculation program was developed to calculate the pressure evolution in the combustion chamber, and the experiment was carried out based on a pasty propellant rocket test system. The data calculated by the program are in good agreement with the experiment, the error of the initial pressure peak is only 4.02%, and the internal ballistic characteristics of the rocket engine at each stage were analyzed detailly. The effects of ignition delay time, transport pipeline structure, free volume of the combustion chamber, mass flow rate, and flow velocity of the pasty propellant on internal ballistic characteristics of the pasty propellant rocket engine are investigated. The results indicate that when the ignition delay time increases, the pressure rises faster and the initial pressure peak increases obviously. The transport pipe diameter changes from 11.3 mm to 7.4 mm, and the initial combustion time and residual propellant combustion time decreased by 41.3% and 36.0%. The reduction of the free volume of the combustion chamber can reduce the initial pressure peak and the time to reach the equilibrium pressure. The initial pressure spike and equilibrium pressure rise with the increase of the pasty propellant flow velocity. While the ignition transient decreased with the increase of the pasty propellant flow velocity. The internal ballistic properties can be improved by reducing the ignition delay time, the diameter of the transport pipeline, and the free volume of the combustion chamber, or by increasing the mass flow rate of the pasty propellant rocket engine.

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The investigation of thermal and gas dynamic processes in the combustion chamber of the rocket engine using slurry fuel

Cited by 5 publications

References 6 publications

Analysis of ballistic aspects in the combined method for removing space objects from the nearEarth orbits

Analysis of ballistic aspects in the combined method for removing space objects from the nearEarth orbits

A simulation of the thermal environment of a plastic body of a new type of launch vehicle at the atmospheric phase of the trajectory

Investigations on Internal Ballistic Characteristics of Pasty Propellant Rocket Engine

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The investigation of thermal and gas dynamic processes in the combustion chamber of the rocket engine using slurry fuel

Cited by 5 publications

References 6 publications

Analysis of ballistic aspects in the combined method for removing space objects from the near­Earth orbits

Analysis of ballistic aspects in the combined method for removing space objects from the near­Earth orbits

A simulation of the thermal environment of a plastic body of a new type of launch vehicle at the atmospheric phase of the trajectory

Investigations on Internal Ballistic Characteristics of Pasty Propellant Rocket Engine

Contact Info

Product

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Analysis of ballistic aspects in the combined method for removing space objects from the nearEarth orbits

Analysis of ballistic aspects in the combined method for removing space objects from the nearEarth orbits