«Актуальные вопросы в сфере социально-экономических, технических и естественных наук и информационных технологий» (3-4 апреля 2014г.)

Gryshyn M. V., Prykhodko O. A., Tymoshenko Zh. I.

Oles Honchar Dnipropetrovsk National University

NUMERICAL SIMULATION IN DEVELOPMENT OF NEW LAUNCH VEHICLE LAYOUT DIAGRAM

Today, one of the most perspective tendencies of the space transportation system (STS) design is a synthesis of aviation and space-rocket hardware. Study of influence and effect on a launch vehicle design and characteristics from each side and search of their optimal combination can be done with mathematical simulation.

The modern approach of launch vehicle (LV) design supposes the problem solution which is going to design rocket space complex (RSC) in order that applied technical decisions may help to reduce costs of production, testing and service of RSC. One of the ways to reduce cost of RSC service can be the implementation of reusable or partly-reusable LV. According to space-rocket hardware development, it was analyzed evolution scheme of LV constructive perfection that is shown in Table 1.

Table 1. Launch vehicle constructive perfection evolution

 Conception Example Full reusable LV X-33, Skylone, Venture Star Full reusable one stage and partial reusable another stage Space Shuttle, Buran-Energia Full reusable one stage and expendable another stage Pegasus XL Partial reusable first stage and expendable second stage Reusable engine Full expendable LV Proton and Taurus LV

The research of space launch service market shows us that with up-to-day development of satellite system the most necessary STS is a launch vehicle with a low-price launch. That launch vehicle should inject into the sun-synchronous orbit with height from 200 up to 400 km a payload in the range from 100 up to 500 kg. Therefore the task of numerical simulation in aeroballistics design should be solved for a small launch vehicle. As an idea of decreasing a launch price a reusable stage such as an aircraft can be considered.

The aerodynamic features of small launch vehicle can be defined with the help of numerical simulation based on Navier- Stokes’ equations.

The using of numerical simulation is conducting with mathematical description of physical processes such as flow, turbulence, flow separation, low-pressure zone that appear in LV external environment in a range from subsonic to hypersonic speed. These processes exert influences on a launch vehicle such as aerodynamic loads, acoustic waves and construction heating.

The solution of this task can allow us to define optimal design parameters of launch vehicle. Using these parameters can minimize influences from external environmental that can result reduction of construction «dry» mass and increasing launch vehicle energy. Used method of analysis can allow estimating qualitative LV geometry shape and flight scheme dependence on gained loads from external environmental. These dependences can be used on preliminary design phase in future.