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

Abstract

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.

Перспективи Застосування Поліолефінів В Якості Альтернативних Конструкційних Матеріалів Для Надлегких Ракет Носіїв

“…На сьогодні існує достатньо широкий спектр як металевих, так і неметалевих КМ. У зв'язку з пошуком КМ для РН з автофажними двигунними установками виникає потреба в полімерних конструкційних матеріалах, що одночасно є елементами ракети та її паливом [8].…”

Numerical Study of Aerodynamic Characteristics of a Pointed Plate of Variable Elongation in Subsonic and Supersonic Gas Flow

“…It should be noted that modern aircraft and structural elements can change its aerodynamic configuration in flight due construction features, or physical phenomena, that results in changes in aerodynamic characteristics [9][10][11]. Likewise, a number of tasks have recently emerged, in which the aircraft change the elongation, that must be taken into account when designing a flight program [12,13]. Similar problems arise when estimating aerodynamic and thermal loads on fragments of space debris discharged from low Earth orbits into the Earth's atmosphere [14,15].…”

Experimental studies of thermodynamic combustion processes of combustible demonstrators

“…Creation of in-flight burned structures will make it possible to solve the problems of selecting drop zones for the separating parts of the launch vehicles, utilization of rocket armament samples after exercises, de-alerting, etc. In [3], a new approach to the design of an ultralight missile made of plastic, the body of which is a solid propellant charge and burns up in the process of launching the missile was proposed.…”