固旋翼垂直起降混电飞行器推进系统设计

doi:10.7527/S1000-6893.2021.25395

Abstract

Abstract: Through optimization of secondary energy systems, hybrid-electric systems can improve the efficiency of energy utilization, and gain a unique advantage of size independence of electric propulsion, which can distribute multiple propellers without significant changes in efficiency and weight, thereby having great potential in the development of general aviation technology. In this paper, based on the top-level design requirements and an estimated initial Maximum Takeoff Mass (MTOM) of a fixed-wing Vertical Takeoff and Landing (VTOL) aircraft, the design space of the hybrid-electric system is constructed by point performance constraints, through which the initial design parameters of horizontal and vertical propulsion systems are obtained. Combined with the specific mission, the weight of the battery and fuel is calculated. After several iterations and energy operations, the design parameters of the propulsion system are obtained, including the MTOM, the weight of each component of the hybrid-electric system, and the weight of battery and fuel. In the design space, taking the hybridization of power as a variable, we analyze the different design objectives between the minimum MTOM and the minimum fuel consumption, providing the design basis for the hybrid-electric aircraft in different scenarios. Finally, the effectiveness of the design method is verified through comparison analysis.

Key words: vertical takeoff and landing(VTOL), all-electric aircraft, hybrid-electric aircraft, hyrid-electric system design, hybrid-electric propulsion

CLC Number:

V272

ZONG Jian'an, ZHU Bingjie, HOU Zhongxi, YANG Xixiang. Design of hybrid-electric fixed-wing VTOL aircraft propulsion system[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(5): 225395-225395.

References

[1] PAPATHAKIS K V, KLOESEL K J, LIN Y, et al. NASA turbo-electric distributed propulsion bench[C]//52nd AIAA/SAE/ASEE Joint Propulsion Conference. Reston:AIAA, 2016.
[2] GLADIN J C, TRAWICK D, PERULLO C, et al. Modeling and design of a partially electric distributed aircraft propulsion system with GT-HEAT[C]//55th AIAA Aerospace Sciences Meeting. Reston:AIAA, 2017.
[3] ECONOMOU J T, TSOURDOS A, WANG S Q. Design of a Distributed Hybrid Electric Propulsion System for a Light Aircraft based on genetic algorithm[C]//AIAA Propulsion and Energy 2019 Forum. Reston:AIAA, 2019.
[4] FREDERICKS W J, MOORE M D, BUSAN R C. Benefits of hybrid-electric propulsion to achieve 4x cruise efficiency for a VTOL UAV[C]//2013 International Powered Lift Conference. Reston:AIAA, 2013.
[5] WROBLEWSKI G E, ANSELL P J. Mission analysis and emissions for conventional and hybrid-electric commercial transport aircraft[J]. Journal of Aircraft, 2019, 56(3):1200-1213.
[6] WALL T J, MEYER R. A survey of hybrid electric propulsion for aircraft[C]//53rd AIAA/SAE/ASEE Joint Propulsion Conference. Reston:AIAA, 2017.
[7] DE VRIES R, BROWN M, VOS R. Preliminary sizing method for hybrid-electric distributed-propulsion aircraft[J]. Journal of Aircraft, 2019, 56(6):2172-2188.
[8] BODSON M, SADEY D J, HUNKER K R, et al. Hybrid electric propulsion using doubly fed induction machines[J]. Journal of Propulsion and Power, 2019, 36(1):78-87.
[9] RIBOLDI C E D. Energy-optimal off-design power management for hybrid-electric aircraft[J]. Aerospace Science and Technology, 2019, 95:105507.
[10] LAMMEN W, VANKAN J. Energy optimization of single aisle aircraft with hybrid electric propulsion[C]//AIAA Scitech 2020 Forum. Reston:AIAA, 2020.
[11] FINGER D F, BRAUN C, BIL C. Comparative assessment of parallel-hybrid-electric propulsion systems for four different aircraft[J]. Journal of Aircraft, 2020, 57(5):843-853.
[12] FINGER D F, DE VRIES R, VOS R, et al. A comparison of hybrid-electric aircraft sizing methods[C]//AIAA Scitech 2020 Forum. Reston:AIAA, 2020.
[13] FINGER D F, BRAUN C, BIL C. Impact of engine failure constraints on the initial sizing of hybrid-electric GA aircraft[C]//AIAA Scitech 2019 Forum. Reston:AIAA, 2019.
[14] FINGER D F, BIL C, BRAUN C. Initial sizing methodology for hybrid-electric general aviation aircraft[J]. Journal of Aircraft, 2020, 57(2):245-255.
[15] TYAN M, NGUYEN N V, KIM S, et al. Comprehensive preliminary sizing/resizing method for a fixed wing-VTOL electric UAV[J]. Aerospace Science and Technology, 2017, 71:30-41.
[16] 唐伟, 宋笔锋, 曹煜, 等. 微小型电动垂直起降无人机总体设计方法及特殊参数影响[J]. 航空学报, 2017, 38(10):220972. TANG W, SONG B F, CAO Y, et al. Preliminary design method for miniature electric-powered vertical take-off and landing unmanned airial vehicle and effects of special parameters[J]. Acta Aeronautica et Astronautica Sinica, 2017, 38(10):220972(in Chinese).
[17] ECONOMOU J T, TSOURDOS A, WANG S Q. Design of a Distributed Hybrid Electric Propulsion System for a Light Aircraft based on genetic algorithm[C]//AIAA Propulsion and Energy 2019 Forum. Reston:AIAA, 2019.
[18] 张啸迟, 万志强, 章异嬴, 等. 旋翼固定翼复合式垂直起降飞行器概念设计研究[J]. 航空学报, 2016, 37(1):179-192. ZHANG X C, WAN Z Q, ZHANG Y Y, et al. Conceptual design of rotary wing and fixed wing compound VTOL aircraft[J]. Acta Aeronautica et Astronautica Sinica, 2016, 37(1):179-192(in Chinese).
[19] ZENG C, ABNOUS R, GABANI K, et al. A new tilt-arm transitioning unmanned aerial vehicle:introduction and conceptual design[J]. Aerospace Science and Technology, 2020, 99:105755.
[20] GU H W, LYU X M, LI Z X, et al. Development and experimental verification of a hybrid vertical take-off and landing (VTOL) unmanned aerial vehicle(UAV)[C]//2017 International Conference on Unmanned Aircraft Systems (ICUAS). Piscataway:IEEE Press, 2017:17060535.
[21] FRIEDRICH C, ROBERTSON P A. Hybrid-electric propulsion for aircraft[J]. Journal of Aircraft, 2015, 52(1):176-189.
[22] HARMON F G, FRANK A A, CHATTOT J J. Conceptual design and simulation of a small hybrid-electric unmanned aerial vehicle[J]. Journal of Aircraft, 2006, 43(5):1490-1498.
[23] 黄俊. 分布式电推进飞机设计技术综述[J]. 航空学报, 2021, 42(3):624037. HUANG J. Survey on design technology of distributed electric propulsion aircraft[J]. Acta Aeronautica et Astronautica Sinica, 2021, 42(3):624037(in Chinese).
[24] GUDMUNDSSON S. General aviation aircraft design:applied methods and procedures[M]. Oxford:Butterworth-Heinemann, 2014.
[25] LEISHMANN J G. Principles of helicopter aerodynamics[M]. 2nd ed. Cambridge:Cambridge University Press, 2006.
[26] GUNDLACH J. Designing unmanned aircraft systems:A comprehensive approach[M]. 2nd ed. Washington, D.C.:AIAA, Inc., 2014.
[27] SULLIVAN U V. Sullivan alternators[EB/OL].(2018-08-15)[2021-02-07]. https://www.sullivanuv.com/products/alternators/.
[28] ROSKAM J, LAN C. Airplane aerodynamics and performance[M]. Lawrence:DARcorporation, 1997:286-298.
[29] RAYMER D. Aircraft design:A conceptual approach[M]. 5th ed. Washington, D.C.:AIAA, Inc., 2012.
[30] GLADIN J C, TRAWICK D, PERULLO C, et al. Modeling and design of a partially electric distributed aircraft propulsion system with GT-HEAT[C]//55th AIAA Aerospace Sciences Meeting. Reston:AIAA, 2017.

Design of hybrid-electric fixed-wing VTOL aircraft propulsion system

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