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TsAGI Science Journal

ISSN Imprimir: 1948-2590
ISSN En Línea: 1948-2604

TsAGI Science Journal

DOI: 10.1615/TsAGISciJ.v40.i3.10
pages 279-298

DEVELOPMENT OF AEROSHAPE AND INVESTIGATION OF SMALL-SIZED WINGED RE-ENTRY VEHICLE AEROTHERMODYNAMIC CHARACTERISTICS

Anatoliy Vladimirovich Bobylev
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str., Zhukovsky, 140180, Moscow region, Russia
A. V. Vaganov
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str., Zhukovsky, 140180, Moscow region, Russia
Vladimir Grigor'evich Dmitriev
Central Aerohydrodynamic Institute (TsAGI), Zhukovsky, Moscow region, Russia
Sergey Mikhailovich Zadonsky
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str., Zhukovsky, 140180, Moscow region, Russia
Aleksandr Yuryevich Kireev
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str., Zhukovsky, 140180, Moscow region, Russia
Arkadii Sergeyevich Skuratov
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str., Zhukovsky, 140180, Moscow region, Russia
E. A. Stepanov
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str., Zhukovsky, 140180, Moscow region, Russia
Vasiliy Aleksandrovich Yaroshevsky
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str., Zhukovsky, 140180, Moscow region, Russia

SINOPSIS

The search for an efficient, small-sized winged re-entry vehicle aeroshape is considered. Problem solving involves an iteration process aimed at changing initial aerodynamic external aeroshape in order to realize given performance characteristics. The computation of aerodynamic characteristics at every iteration step is completed using software packages based on different engineering techniques. Estimation of descent trajectory parameters involves searching for the optimal trajectory, and realizing the maximum cross range at given equilibrium temperature limitations, for example, at stagnation points of aeroshape elements. For this reason the shape of perspective small-sized winged re-entry vehicle aeroshapes is worked out. The defining feature of the aeroshape is that its shape, size, and wing location provide not only balancing and stability, but also the necessary value of lift at all flight modes. The shape of the nose section, the airfoil, and the value of leading-edge sweep enabled realization of acceptable heat fluxes on the vehicle surface at hypersonic speeds.


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