Determination of the optimum design of the means to ensure the fuel continuity by the method of numerical simulation
Рубрика:
| 1Minai, OM, 1Kuzmich, IYu. 1Yangel Yuzhnoye State Design Office, Dnipro, Ukraine |
| Space Sci. & Technol. 2024, 30 ;(3):40-52 |
| https://doi.org/10.15407/knit2024.03.040 |
| Язык публикации: Ukrainian |
Аннотация: Residues of liquid propellant components in the power system of the propulsion system at the end of the operation of the launch vehicle stage significantly affect its energy characteristics. The fuel continuity features found in modern launch vehicle tanks ensure a continuous supply of propellant components from the tank to the propulsion system without disrupting flow and minimizing residues. In the fuel tank of launch vehicles, the presence of a tunnel pipeline complicates, and in certain cases excludes the possibility of taking fuel from the pole of the tank. Solving the problem of fuel intake, in this case, allows the use of means to ensure the continuity of fuel of the side type. However, the use of such a device, due to the displacement relative to the pole of the bottom of the tank by a certain angle of the sampling point, can lead to an uneven level of breakthrough and immersion of the boost gas at the inlet to the flow line and, as a result, a significant increase in the remainder of the fuel components.
The authors searched for and substantiated the optimal design of the means for ensuring fuel continuity on the example of the fuel tank of the first stage of the Cyclone-4 launch vehicle, which is equipped with a side-type fuel continuity means in the form of a profiled plate (plate). The designs of siphon and annular fuel continuity means are considered. An analytical calculation was carried out using empirical dependences, a physical experiment, and a numerical simulation of their main parameters. Based on the work performed, a comparative analysis of the change in the energy characteristics of the launch vehicle depending on the chosen design was carried out.
The efficiency of the operation of the considered means of ensuring the continuity of the fuel is determined in terms of the mass parameter of the remainder of the propellant components under static conditions. The result of the experimental and computational-analytical work was to obtain the most optimal variant of the fuel continuity means, which turned out to be a siphon according to several parameters. The introduction of a siphon means of ensuring continuity, as more optimal, into the design of the fuel tank of the «Cyclone-4» launch vehicle will improve its energy characteristics by increasing the mass of the output payload by 5.4 kg. Also, using the numerical modeling methods (CFD methods) for design work on development, optimization, and improvement, instead of empirical and semi-empirical dependencies, allows you to: obtain more accurate results; reduce the number of experimental designs; reduce the required number of tests; reduce the duration of examinations; reduce the total duration of computational and design and experimental work; reduce the overall material and technical costs and, as a result, reduce the final cost of the development product, which will increase its competitiveness.
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| Ключевые слова: residues of fuel components; fuel continuity means; propulsion system; fuel tank; fuel components |
References:
1. Baranov D. A., Elenev V. D. (2020). Typical solutions in the design and construction of elements of launch vehicles. Textbook. Samara: Samara Univ. Press, 112 p. [in Russian].
2. Belyaev N. M. (1983). Calculation of pneumohydraulic systems of a rocket. M.: Mashinostroenie, 223 p. [in Russian].
3. Bliznichenko V. V., Jur E. O, Krasnikova R. D. et al. (2007). Design and construction of launch vehicles. Ed. acad. S. M. Konyukhova. D.: Type of DNU, 504 p. [in Ukrainian].
4. Ziganshin A. M. (2013). Computational fluid dynamics. Setting and solving problems in the Fluent processor. Kazan: Kazansk Publishing House. state architect. builds. un-ta, 79 p. [in Russian].
5. Krivtsov A. V. (2013). Studying the influence of mesh quality and turbulence models on the results of CFD calculation in ANSYS Fluent. Samar: Publishing House of the State. aerospace. un-t them. S. P. Koroleva, 47 p. [in Russian]
6. Kuzmich I. Yu., Minai O. M. (2022). Selection of the optimal design of the intake device in the fuel tank of the first stage of the launch vehicle "Cyclone-4". Aerospace Engineering and Technology, № 1, 25-33.
7. Kuzmich I. Yu., Minai O. M. (2021). The influence of digitalization on the processes of design and experimental development in the rocket and space industry on the example of a capillary intake device. Materials of the XVI scientific readings "Dnieper Orbit - 2021". Dnepr, 162-169 [in Ukrainian].
8. Mikishev G. N. (1978). Experimental methods in spacecraft dynamics. M.: Mashinostroenie, 248 p. [in Russian].
9. Minai O. M., Sedykh I. V., Kuzmich I. Yu. (2019). Application of Numerical Simulation Methods in Experimental Development of Central Type Intake Devices. Aerospace engineering and technology, № 6 (158), 33-41.
https://doi.org/10.32620/aktt.2019.6.05
10. Tokarev V. E. (1967). Fluid outflow from a container with the formation of a funnel. News of higher educational institutions. Ser. Aviation technology, № 3, 92-94 [in Russian].
11. Shevchenko B. A. (1990). Calculation and experimental method for the development of means for the intake of fuel components from the tanks of aircraft with a liquid-propellant rocket engine. PhD (Tech.). Dnepropetrovsk.
12. Chen Lei, Liu Jintao, Li Wen, Yao Can, Zhu Honglai. (2019). Numerical simulation and microgravity experiment of fluid flow in the vane type. IOP Conf. Ser.: Materials Science and Engineering, 542, 8.
https://doi.org/10.1088/1757-899X/542/1/012012
13. Chen Shangtong, Duan Li, Kang Qi. (2021). Study on propellant management device in plate surface tension tanks. Research paper: Acta Mechanica Sinica, 11.
https://doi.org/10.1007/s10409-021-01121-y
14. Hartwig J. W. (2017). Propellant Management Devices for Low-Gravity Fluid Management: Past, Present, and Future Applications. J. Spacecraft and Rockets, 54, № 4, 808-824.
https://doi.org/10.2514/1.A33750
15. Hartwig J. W. (2016). Liquid Acquisition Devices for Advanced In-Space Cryogenic Propulsion Systems. Elsevier Inc, 469 p. .
16. Liu Jintao, Li Yong, Li Wen, Chen Lei, Guo Chongwu. (2019). Experimental study on liquid distribution in a vane type propellant tank. J. Phys.: Conf. Ser., 1314, 8.
https://doi.org/10.1088/1742-6596/1314/1/012097
17. Manning R. E., Ballinger Ian, Bhatia Manoj, Dowdy M. (2019). Design of the Europa Clipper Propellant Management Device. American Institute of Aeronautics and Astronautics AIAA Propulsion and Energy Forum, 19.
https://doi.org/10.2514/6.2019-3858
18. Minai O. (2020). Influence of long-term stay elements of capillary intake devices in liquid propellant components on their parameters. Aerospace Res. in Bulgaria, 32, 175-192.
https://doi.org/10.3897/arb.v32.e15
19. Walter T., Philipp B., Jaekle D., Netter G. (2016). The Evolutionary forces and the design and development of propellant management devices for space flight in Europe and the United States. Space Propulsion, 25
20. Walter T., Jaekle D. (2018). Review and history of ATK space systems surface tension PMD tanks. Space Propulsion, 24 .
21. Yusuf Aamir, Gopinathanb P. K., Kamatchi K., Jose Paul, Nageswaran G., Narayanan V. (2020). Design & Development of Propellant Intake Device for Cryo Upper Stage LOX Tank. 71st International Astronautical Congress (IAC): The CyberSpace Edition, Virtual. P. 12. Paper code: IAC-20,C4,2,2,x57098