Approximate Methodology for Design Ballistic Calculations of the First Stage of Launch Vehicles

The initial stages of development of new types of launch vehicles involve performing the so-called design ballistic calculations. Currently, the relevance of design ballistics tasks is noticeably increasing in connection with the problems of deep space exploration and the creation of a new generation of space rocket systems, requiring significant financial investment. When developing design methods, motion models should not be inferior in accuracy to the uncertainties of the source data, and the algorithm of the technique should reflect the relationship of design parameters with the flight characteristics of the rocket. These principles formed the basis of the proposed methods for ballistic calculations of the active section of the trajectory of the first stages of heavy and super heavy launch vehicles. The technique is based on the results of the analysis of numerous trajectories corresponding to variations of various studied factors. The trajectory calculations were carried out using the method of numerical integration of differential equations of motion in a wide range of variation of design ballistic parameters and boundary conditions. The analysis made it possible to identify some general patterns of the controlled motion and to obtain the structure of the calculated dependencies in an analytical form.

References

[1] Mirkin E.A. Outlook for our country’s manned spaceflight development. Space technique and technologies, 2017, no. 1(16), pp. 5–10 (in Russ.).

[2] Bryukhanov N.A., Legostayev V.I., Lobykin A.A., Lopota V.A., Sizentsev G.A., Sinyavskiy V.V., Sotnikov B.I., Filippov I.M., Shevchenko V.V. Use of lunar resources for solar system exploration and exploitation in the 21st century. Space technique and technologies, 2014, no. 1(4), pp. 3–14 (in Russ.).

[3] Fortescue P., Swinerd G., Stark J. Spacecraft systems engineering. John Wiley & Sons, 2011. 691 p.

[4] Grigor’yev M.N., Okhochinskiy M.N., Vagner I.V. Logistical approach to the project of the Russian moon base. Innovations, 2016, no. 7, pp. 14–19 (in Russ.).

[5] Derechin A.G., Zharova L.N., Sinyavskiy V.V. International cooperation in the sphere of manned flights. Part 2. Development and operation of the International Space Station. Space technique and technologies, 2017, no. 2(17), pp. 5–28 (in Russ.).

[6] Sirota A.A. Stages of construction and construction features of the international lunar research station. Gagarinskiye chteniya — 2018. Sb. tez. dokl. XLIV Mezhdun. molodezh. nauch. konf [Gagarin Readings — 2018. Abstracts of the XLIV International Youth Scientific Conference]. Moscow, 2018, vol. 3, pp. 68–70.

[7] Schrunk D., Sharpe B., Cooper B., Thangavelu M. The Moon: Resources, Future Development and Settlement. Praxis Publishing Ltd., 2008. 560 p.

[8] Danilyuk A.Yu., Klyushnikov V.Yu., Kuznetsov I.I., Osadchenko A.S. Problems of design & development of perspective super-heavy launch vehicles. Vestnik NPO im. S.I. Lavochkina, 2015, no. 1(27), pp. 10–19 (in Russ.).

[9] Muzhikova M.N., Prusova O.L. Modern projects of superheavy rockets. Problemy razrabotki, izgotovleniya i ekspluatatsii raketno-kosmicheskoy tekhniki i podgotovki inzhenernykh kadrov dlya aviakosmicheskoy otrasli. Mater. XII Vseros. nauch. konf., posvyashchennoy pamyati glavnogo konstruktora PO “Polet” A.S. Klinyshkova [Problems of development, manufacture and operation of rocket and space technology and training of engineering personnel for the aerospace industry. Materials of the XII all-Russian scientific conference dedicated to the memory of the chief designer OF po Flight A.S. Klinyshkov]. Omsk, 2008, pp. 62–68.

[10] Evtif’yev M.D., Ostapenko A.V. Superheavy launcher based on “energy” launcher using modern achievements in the science and engineering. Reshetnevskiye chteniya. Mater. XIX Mezhdunar. nauch.-prakt. konf. [Reshetnev readings]. Krasnoyarsk, 2015, pt. 1, pp. 6–18.

[11] Feodos’yev V.I. Osnovy tekhniki raketnogo poleta [Rocket Flight Technology Basics]. Moscow, Nauka publ., 1979. 496 p.

[12] Appazov R.F., Lavrov S.S., Mishin V.P. Ballistika upravlyayemykh raket dal’nego deystviya [Ballistics of long-range guided missiles]. Moscow, Nauka publ., 1966. 305 p.

[13] Ballisticheskiye rakety i rakety-nositeli [Ballistic missiles and launch vehicles]. Ed. Alifanov O.M. Moscow, Drofa publ., 2004. 512 p.

[14] Osnovy proyektirovaniya letatel’nykh apparatov (transportnyye sistemy) [Fundamentals of aircraft design (transport systems)]. Ed. Matveyenko A.M., Alifanov O.A. Moscow, Mashinostroyeniye publ., 2005. 375 p.

[15] Sikharulidze Yu.G. Ballistika i navedeniye letatel’nykh apparatov [Ballistics and aircraft guidance]. Moscow, BINOM Laboratoriya znaniy publ., 2013. 417 p.

[16] Kovalev B.K. Razvitiye raketno-kosmicheskikh sistem vyvedeniya [The development of space rocket launch systems]. Moscow, Bauman Press, 2014. 398 p.

[17] Aerodinamika [Aerodynamics]. Ed. Kalugin V.T. Moscow, Bauman Press, 2017. 607 p.

[18] Petrov K.P. Aerodinamika transportnykh kosmicheskikh system [Aerodynamics of space transport systems]. Moscow, Editorial URSS publ., 2000. 368 p.

[19] Proyektirovaniye sredstv vyvedeniya kosmicheskikh apparatov [Design of spacecraft launch vehicles]. Ed. Serdyuk V.K., Medvedev A.A. Moscow, Mashinostroyeniye publ., 2009. 504 p.

[20] Klepikov I.A., Likhvantsev A.A., Prokof’yev V.G., Fatuyev I.Yu. The choice of the schematic diagram and parameters of the marching reusable oxygen-methane rocket engine for the returning first stage of a promising carrier. Trudy Energomash im. Akademika V.P. Glushko, 2012, no. 29, pp. 224–229 (in Russ.).

[21] Vasyanina A.Yu., Tonkikh A.A., Savchin D.A. Prospects of the methane-oxygen using. Reshetnevskiye chteniya. Mater. XIX Mezhdunar. nauch.-prakt. konf. [Reshetnev readings]. Krasnoyarsk, 2015, pp. 367–369.

[22] Mukhamedov L. P. Osnovy proyektirovaniya transportnykh kosmicheskikh system [Basics of the design of space transport systems]. Moscow, Bauman Press, 2019. 265 p.