Mathematical modeling of acceleration dynamics of test object till 3-4 M number on installation «rocket rail track»

Аuthors

Biruykov V. I.^*, Pronin O. Y.^**

Scientifically-proving ground aviation systems, Beloozersky, Moscow region, 140250, Russia

*e-mail: aviatex@mail.ru
**e-mail: gknipas@transcom.ru

Abstract

For achievement of hypersonic speed of pilotless flying machines it is necessary to find the solution of some technical problems connected with processes of an aerodynamic flow of flying machine surface, as well as heating and strength of its structure elements. It should be also performed the works on creation of the athodyd engine (Ramjet) with wide range regulated speed air stream. With respect of perspective multimode supersonic Ramjet working process investigation the ballistic problem of the flying machine with Ramjet (object of test) test on experimental installation «Rocket rail track» is considered. The installation represents monorail track specially designed with a small gradient angle in length of 3,5 km (nowadays the works on its lengthening up to 5 km are conducted) on which the rail carriage set powered by solid fuel rocket engines with the thrust 450 кН is placed. The increase of installation thrust-to-weight ratio level is possible by increasing of engines quantity.
In the work it is created the mathematical model of object of the test acceleration dynamics, which takes into consideration the losses: of lifting force creation, overcoming of rail — carriage boots friction forces, aerodynamic drug, vortex formation, base drug and wave resistance. The algorithm is developed on the basis of Runge-Kutta method of 4th order. The simulation code is executed using the Fortran. It were carried out different simulations with various placing of object of test and engines using one, or two rail carriages. The analysis about influence on acceleration dynamics the engines thrust reserve and variation in weight object of test or engines was conducted. The model was verified by comparison of calculation results with the obtained earlier experimental data. The executed calculation research allows to optimize the thruster and of object of test cross-section and weight for achievement of necessary speed on the 3,5 km track length. It was shown that under high density of air at speed of 3-4 M the drug losses were dominated. The tests for «Rocket rail track» installation under the 3-4 M can model the processes at the investigated flight height with a speed multiple to the air density ratio.

Keywords:

flying machines, hypersonic, shock waves, rocket rail track, athodyd RamJet

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