Parametric Calculations of the Aerodynamics of a Descent Vehicle

We present the methodology and results of parametric aerodynamic studies of vehicles descending into the planet’s atmosphere. The proposed computational approach might serve as the basis for solving a number of problems such as predicting and optimizing the descent trajectory of the vehicle, the search for a rational aerodynamic layout of the vehicle, i.e., tasks requiring massive parametric calculations. The systematization of such calculations is the first step towards the creation of a specialized database that includes sets of input and output data (flight speed, angles of attack, drag and lift coefficients, aerodynamic pitching moment, etc.) and the corresponding three-dimensional fields of gas-dynamic quantities together with computational meshes of various granularity and parameters of the computational model. Additional information to each element of the database might be a set of variables, parameterizing the geometry of the vehicle, experimental data, etc. The probability of forming the information content of such a data-base using modern supercomputer systems is shown. The capabilities of the domestic supercomputer aerodynamic code NOISEtte are demonstrated in the field of multiparametric three-dimensional calculations of descent vehicles based on the numerical solution of the Navier --- Stokes equations on three-dimensional unstructured meshes

References

[1] Loytsyanskiy L.G. Mekhanika zhidkosti i gaza [Fluid mechanics]. Moscow, Drofa Publ., 2003.

[2] Landau L.D., Lifshits E.M. Teoreticheskaya fizika. T. 6. Gidrodinamika [Theoretical physics. Vol. 6. Thermodynamics]. Moscow, FIZMATLIT Publ., 2001.

[3] Tirskiy G.A., ed. Giperzvukovaya aerodinamika i teplomassoobmen spuskaemykh kosmicheskikh apparatov i planetnykh zondov [Hypersonic aerodynamics and heat exchange of descent spacecraft and planetary probes]. Moscow, FIZMATLIT Publ., 2011.

[4] Dmitrievskiy A.A., Lysenko L.N. Vneshnyaya ballistika [External ballistics]. Moscow, Mashinostroenie Publ., 2005.

[5] Golomazov M.M., Ivankov A.A. Examination of the aerodynamics of a prospective descent module descending in the atmosphere of Mars. Vestnik NPO im. S.A. Lavochkina, 2018, no. 2, pp. 56--61 (in Russ.).

[6] Golomazov M.M., Finchenko V.S., Shmatov S.I. Teoretiko-eksperimental’nye metody resheniya zadach aerodinamiki kosmicheskikh apparatov, spuskaemykh v atmosferakh planet. V kn.: Proektirovanie avtomaticheskikh spuskaemykh apparatov dlya fundamental’nykh nauchnykh issledovaniy [Theoretical experimental methods for solving aerodynamic problems of descent spacecraft in planetary atmospheres. In: Design of Automated Descent Spacecraft for Fundamental Scientific Research]. Moscow, MAI-Print Publ., 2014, pp. 962--1034 (in Russ.).

[7] Zheleznyakova A.L., Kuzenov V.V., Petrusev A.S., et al. The modelling of hydrodynamics for two different models of space vehicle. Fiziko-khimicheskaya kinetika v gazovoy dinamike [Physical-Chemical Kinetics in Gas Dynamics], 2010, vol. 9, no. 1 (in Russ.). Available at: http://chemphys.edu.ru/issues/2010-9/articles/144

[8] Andreev V.N., Borovkov A.I., Voynov I.B., et al. Aerogasdynamics behavior of the escape system separable nose assembly with operating propulsion system. Kosmicheskaya tekhnika i tekhnologii [Space Technique and Technologies], 2014, no. 4, pp. 10--20 (in Russ.).

[9] Matyushin M.M., Sokolov N.L., Ovechko V.M. Optimal control of a spacecraft during descent in Mars atmosphere. Vestnik NPO im. S.A. Lavochkina, 2016, no. 2, pp. 54--60 (in Russ.).

[10] Alabova N.P., Bryukhanov N.A., Dyad’kin A.A., et al. Role of computer simulation and physical experiment in investigations of space rocket system aerogasdynamics throughout the designing. Kosmicheskaya tekhnika i tekhnologii [Space Technique and Technologies], 2014, no. 3, pp. 14--21 (in Russ.).

[11] Aksenov A.A., Dyad’kin A.A., Moskalev I.V., et al. Computer simulation of the flow and the relative motion of the reentry vehicle and the parachute compartment hatch cover in the course of their separation during descent. Kosmicheskaya tekhnika i tekhnologii [Space Technique and Technologies], 2015, no. 2, pp. 39--50 (in Russ.).

[12] Lutsenko A.Yu., Nazarova D.K., Slobodyanyuk D.M. Computation of aerodynamic characteristics and parameters of flow around the launch vehicle nose fairing half in the ANSYS CFX package. Inzhenernyy zhurnal: nauka i innovatsii [Engineering Journal: Science and Innovation], 2018, no. 5 (in Russ.). DOI: http://dx.doi.org/10.18698/2308-6033-2018-5-1766

[13] Spalart P.R., Allmaras S.R. A one-equation turbulence model for aerodynamic flows. 30th Aerospace Sciences Meeting and Exhibit, 1992, no. 1992-0439. DOI: https://doi.org/10.2514/6.1992-439

[14] Garbaruk A.V. Sovremennye podkhody k modelirovaniyu turbulentnosti [Modern approaches to the modeling of turbulence]. St. Petersburg, St. Petersburg Univ. Publ., 2016.

[15] Abalakin I.V., Bakhvalov P.A., Gorobets A.V., et al. Parallel research code NOISEtte for large-scale CFD and CAA simulations. Vychislitel’nye metody i programmirovanie [Numerical Methods and Programming], 2012, vol. 13, no. 2, pp. 110--125 (in Russ.).

[16] Feoktistov K.P., ed. Kosmicheskie apparaty [Aircraft]. Moscow, Voenizdat Publ., 1983.