Aerospace Technic and Technology

The issues of choosing a composition, operating process parameters and operating modes of propulsion for supersonic cruising aircraft providing transoceanic flights are considered. A condition of maximum payload relative mass is used as a criterion for choosing the composition of the propulsion. This criterion can be transformed using the aircraft mass balance equation into a condition of the minimum relative mass of fuel and propulsion. A predictor-corrector method is used to solve the task. Choosing the composition, operating process parameters and operating modes of propulsion according to the cruising segment, taking into account the remaining flight segments takeoff, climb and descent by the empirical coefficients, is used as a predictor stage. Based on the solving results of this stage, the best competing variants of propulsions are selected for the purpose of subsequent more detailed analysis at a corrector stage by numerically solving the differential equations of the aircraft motion along an entire flight profile. At the same time, on each elementary section of the path, the control parameters of the propulsion are optimized according to the criterion of the minimum required fuel consumption to overcome this section. Propulsion with turbojet engine, turbofan and mixed flows turbofan engine, turbo-ramjet engine and turbofan engines that have ramjet modes are considered. Patterns of the change in the relative mass of the fuel and propulsion for the indicated compositions of the propulsions according to cruising segment of the flight for the cruising speeds corresponding to the M = 1.5...4 are established. These dependencies make it possible to select variants of propulsion competing in terms of payload for a cruising speed or select the most advantageous cruising speed for propulsion composition which is given. These dependencies were used to determine competing variants of the power plant, providing a minimum of the relative mass of fuel and propulsion for the airplane with a cruising speed corresponding to the M = 3. At the stage of the corrector, these variants of the propulsion were evaluated according to the criterion of the relative mass of fuel and propulsion by solving the equations of the aircraft motion along the entire flight profile with the optimization of the control parameters of the propulsion on each elementary segment of the profile according to the criterion of minimum fuel consumption to overcome it. In doing so, the operating process parameters of the propulsion were optimized near of those values that were obtained at the stage of the predictor. The analysis of the obtained results indicates that, in comparison with the predictor stage at the corrector stage, the parameters of the propulsion operating process that are optimal from the point of view of the relative mass of fuel and propulsion changed by about 12.5 %, and the relative mass of fuel and propulsion by about 3...4 %.

relative mass; payload; mass of fuel and propulsion; supersonic cruising speed; aircraft; propulsion; airbreathing jet engines; ramjet mode

Kislov, O. V., Shevchenko, M. A. Metod vybora sostava i rezhima raboty silovoi ustanovki, rezhima raboty dlya letatel'nogo apparata so sverkhzvukovoi kreiserskoi skorost'yu [Method of Choosing Composition and Operation Mode of Propulsion, Operation Mode of Aircraft at Supersonic Cruising Speed]. Otkrytye informatsionnye i komp'yuternye integrirovannye tekhnologii – Open Information and Computer Integrated Technologies, 2020, no. 88, pp. 51-61. DOI: 10.32620/oikit.2020.88.04.

Dugan, F. J., Koenig, R. W., Whitlow, J. B., McAuliffe, T. B. Turbojet and turbofan engines for a Mach 3supersonic transport. NASA Report, 1964, no. CR-64-21540. 12 р.

Berton, J. J., Haller, W. J., Senick, P. F., Jones, S. M., Seidel, J. A. A Comparative Propulsion System Analysis for the High-Speed Civil Transport. NASA Report, 2005, no. TM-2005-213414. 106 р.

Demenchenok, V. P., Druzhinin, L. N., Parkhomov, A. L., Sosunov, V. A., Tskhovrebov, M. M., Shlyakhtenko, S. M., El'perina, A. S. Teoriya dvukhkonturnykh turboreaktivnykh dvigatelei [Theory of turbofan engines]. Moscow, Mashinostroenie Publ., 1979. 432 p.

Jaminson, R. R. Power Units for Very High Speed Winged Vehicles. Aerospace Proceeding, Bristol, England, 1966, pp. 484-513.

Chen, M., Jia, Z., Tang, H., Xiao, Y., Yang, Y., Yin, F. Research on simulation and performance optimization of Mach 4 civil aircraft propulsion concept. International Journal of Aerospace Engineering, 2019, Vol. 2019. Article ID: 2918646. 19 p. DOI: 10.1155/2019/2918646.

Ulitenko, Yu. A. Analiz kharakteristik turboreaktivnogo dvukhkonturnogo dvigatelya s forsazhnoi kameroi sgoraniya s vpryskom vody za vkhodnym ustroistvom [Turbojet bypass engine with afterburner with water injection after input unit performance analysis]. Aviacijno-kosmicna tehnika i tehnologia – Aerospace technic and technology, 2019, no. 1 (153), pp. 29-38. DOI: 10.32620/aktt.2019.1.03.

Morgenstern, J. and other. Advanced Concept Studies for Supersonic Commercial Transports Entering Service in the 2018-2020 Period Phase 2. NASA Report, 2015, no. CR-2015-218719. 396 р. Available at: https://ntrs.nasa.gov/citations/20150015837 (аccessed 23.03.2021).

Kishalov, A. E., Markina, K. V. Issledovanie i prognozirovanie gazodinamicheskikh parametrov potoka kamer sgoraniya aviatsionnykh GTD [Research and prediction of thermal gas parameters flow combustion chambers of aviation GTE]. Vestnik UGATU, Ufa, USATU Publ., 2017, no. 13(1), pp. 60-68.

Nechaev, Yu. N., Fedorov, R. M., Kotovskii, V. N., Polev, A. S. Teoriya aviatsionnykh dvigatelei [Theory of Aviation Engines]. Moscow, VVIA im. prof. N. E. Zhukovskogo Publ., 2006. 448 p.

Kislov, O., Shevchenko, M. Osobennosti rascheta i regulirovaniya dvukhkonturnogo turboreaktivnogo dvigatelya s forsazhnoi kameroi sgoraniya v naruzhnom konture na pryamotochnykh rezhimakh raboty [Calculation and regulation features of duct-burning turbofan engine at ramjet modes]. Aviacijno-kosmicna tehnika i tehnologia – Aerospace technic and technology, no. 6(166), pp. 15-23. DOI: 10.32620/aktt.2020.6.02.

Druzhinin, L. N., Shvets, L. I., Malinina, N. S. (1983). Metod i podprogramma rascheta termodinamicheskih parametrov vozduha i produktov sgoraniya uglevodorodnyh topliv. Rukovodyaschiy tehn. material aviatsionnoy tehniki. RTM 1677–83. Dvigateli aviatsionnye i gazoturbinnye. Moscow. 68 p.

Yankin, V. I. Sistema programm dlya rascheta kharakteristik VRD na ETsVM. [System of programs for calculating the characteristics of turbojet engine with a computer]. Moscow, Mashinostroenie Publ., 1976. 168 p.

Kislov, O, Ambrozhevich, M., Shevchenko, M. Development of a method to improve the calculation accuracy of specific fuel consumption for performance modeling of air-breathing engines. Eastern-European Journal of Enterprise Technologies, 2021,no. 2 (8 (110)), pp. 23–30. DOI: https://doi.org/10.15587/1729-4061.2021.229515

Idel'chik, I. E. Spravochnik po gidravlicheskim soprotivleniyam [Hydraulic resistance Handbook]. Moscow, MEI Publ., 1992. 672 p.

Optimizatsiya i vybor parametrov rabochego protsessa GTD po samoletnym kriteriyam effektivnosti s ispol'zovaniem ASTRA-OPT [Optimization and selection of parameters of the GTE working process according to aircraft efficiency criteria using ASTRA-OPT]. Samara, Samarskiy gosudarstveniy aerokosmicheskiy universitet Publ., 2007. 40 p.

Yicheng, S, Howard S. Review and prospect of supersonic business jet design. Progress in Aerospace Sciences, 2017, vol. 90, pp. 12-38. DOI: 10.1016/j.paerosci.2016.12.003.

Batyrov, T. Rossiya i OAE razrabotayut sverkhzvukovoi biznes-dzhet [Russia and the UAE will develop a supersonic business jet]. Available at: https://www.forbes.ru/newsroom/biznes/421741-rossiya-i-oae-razrabotayut-sverhzvukovoy-biznes-dzhet (аccessed 23.04.2021) (In Russian)

Kislov, O., Shevchenko, M. Development of a method for selecting a cruising mode and engine control program of a ramjet aircraft. Eastern-European Journal of Enterprise Technologies, 2021, vol. 3, no. 3 (111), pp. 6-14. DOI: 10.15587/1729-4061.2021.233850.