TECHNICAL MECHANICS
ISSN (Print): 1561-9184, ISSN (Online): 2616-6380

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Home > Journal Issues > No 2 (2020) Technical mechanics > 3
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UDC 629.7.036

Technical mechanics, 2020, 2, 36 - 46

COMPUTER SIMULATION OF GAS-DYNAMIC PROCESSES FOR ROCKET FAIRING DESIGN OPTIMIZATION

DOI: https://doi.org/10.15407/itm2020.02.036

Vasyliv S. S., Pryadko N. S.

      ABOUT THE AUTHORS

Vasyliv S. S.
Institute of Technical Mechanics of the National Academy of Sciences of Ukraine and the State Space Agency of Ukraine

Pryadko N. S.
Institute of Technical Mechanics of the National Academy of Sciences of Ukraine and the State Space Agency of Ukraine

      ABSTRACT

      The fairing serves to protect the payload against exposure to external factors during the rocket flight. It must withstand considerable force and thermal loads and safely detach and move away from the rocket. This paper deals with the process of fairing flap separation from the rocket in the Earth’s dense atmosphere under conditions of considerable aerodynamic loads in the range of supersonic flight speeds. It is proposed that flap removal from the rocket structure be done using a detonation corded rocket engine, which develops a considerable thrust at a low mass and a short operation period. This significantly reduces the fairing mass. The forces arising in this process were determined by computer simulation. A technique for calculating the basic parameters of a detonation corded rocket engine for fairing flap removal is presented. The mathematical model of flap motion relative to the rocket during the process of detachment and removal consists of two parts: the calculation of the separation and acceleration of the flaps while in mechanical contact with the rocket and the calculation of the inertial motion of the flaps separated from the rocket. The computer simulation gives the projections of the aerodynamic forces and torque and the air pressure distribution for the most characteristic angles. Five protective partition shapes were simulated: conical, concave conical, spherical, concave spherical, and flat. The concave spherical shape was found to be optimal in terms of minimum energy consumption. The optimal shape, dimensions, and placement of the partition were calculated. The minimum thrust of the detonation corded engine required for flap removal from the rocket was determined, and effects that allow one to reduce this thrust were found. The calculated pressure distributions may be used in flap strength analysis.
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      KEYWORDS

detonation corded rocket engine, supersonic flow, fairing separation, simulation, pressure distribution

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      REFERENCES

1. Dotson K.W., Engblom W. A. Vortex-induced vibration of a heavy-lift launch vehicle during transon-ic flight. Journal of Fluids and Structures. 2004. V. 19. Iss. 5. Pp. 669 - 680. https://doi.org/10.1016/j.jfluidstructs.2004.04.009

2. Rogers S. E., Dalle D. J., Chan W. M. CFD Simulation of the Space Launch System Ascent Aerody-namics and Booster Separating. American Institute of Aeronautics and Astronautics. 2015. 33 pp. https://doi.org/10.2514/6.2015-0778

3. Groves C. E. Computational Fluid Dynamics Uncertainty Analysis for Payload Fairing Spacecraft Environmental Control. A dissertation submitted in partial fulfillment of the requirements for the PhD degree in the Department of Mechanical and Aerospace Engineering in the College of Engineer-ing and Computer Science at the University of Central Florida Orlando, Florida. 2014.164 pp. https://doi.org/10.2514/6.2014-0440

4. Murman S. M., Diosady L. T. Simulation of a hammerhead payload fairing in the transonic regime. American Institute of Aeronautics and Astronautics. 2008. Paper 2016-1548. 17 pp. https://doi.org/10.2514/6.2016-1548

5. Tsutsumi S., Takaki R., Takama Y., Imagawa K., Nakakita K., Kato H. Hybrid LES/RANS Simulations of Transonic Flowfield around a Rocket Fairing. American Institute of Aeronautics and Astronautics. 2012. https://doi.org/10.2514/6.2012-2900

6. Nallasamy R., Kandula M., Schallhorn P., Duncil L. Three-dimensional flowfield in the scaled pay-load. fairing model of an expendable launch vehicle. American Institute of Aeronautics and Astro-nautics. 2008. Paper 2008-4302. https://doi.org/10.2514/6.2008-4302

7. Frolov S. M. (Ed.). Pulsed Detonation Engines. Moscow: TORUS PRESS, 2006. 592 pp. (in Rus-sian).

8. Bykovsky F.A., Zhdan S. A. Continuous Spin Detonation. Novosibirsk: SORAN, 2013. 423 pp. (in Russian).

9. Shank Jason C. Development and Testing of a Rotating Detonation Engine Run on Hydrogen and Air. Thesis presented to the Faculty Department of Aeronautics and Astronautics Graduate School of En-gineering and Management Air Force Institute of Technology Air University Air Education and Training Command in partial fulfillment of the requirements for the degree of Master of Science in Aeronautical Engineering. USAF, 2012. 70 ðp.

10. Russo Rachel M.: Operational Characteristics of a Rotating Detonation Engine using Hydrogen and Air. Thesis presented to the Faculty Department of Aeronautics and Astronautics Graduate School of Engineering and Management Air Force Institute of Technology Air University Air Education and Training Command in partial fulfillment of the requirements for the degree of Master of Science in Aeronautical Engineering. USAF, 2011. 90 ðp.

11. International Organization for Standardization, Standard Atmosphere, ISO 2533:1975. 1975. 108 pp.

12. Vargaftik N. B. Handbook on Thermal Fluid Properties. Moscow: Nauka, 1972. 720 pp. (in Russian).





Copyright (©) 2020 Vasyliv S. S., Pryadko N. S.

Copyright © 2014-2020 Technical mechanics


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