三翼面验证机纯电方案设计

doi:10.7527/S1000-6893.2024.29618

Abstract

Abstract:

With the increasingly strict carbon emission policy， green air travel has become one of the new goals of civil aircraft design. The room of improvement of aerodynamic efficiency and structural efficiency of the civil aircraft with traditional layout is limited， so it is difficult to achieve greater drag reduction.The design scheme of new layout combined with new energy have become a research hotspot.This paper summarizes the research progress of new layout technologies of Blended Wing Body （BWB）， Truss-Braced Wing （TBW） and Three-Surface Aircraft （TSA）， as well as new energy technologies of electric vehicles. Based on the layout characteristics of the 200 kg UAV verification aircraft “Windrider 2.0”， the aerodynamic characteristics analysis and layout benefit evaluation of the three-surface layout are carried out by the Computational Fluid Dynamics （CFD） and engineering estimation method. The pitching moment characteristics of single deflection and combined deflection of canard and horizontal tail are analyzed. The canard has the ability to recover from high angle of attack and good high-a nose-down control capability. Compared with the non-canard wing layout， the complete three-surface layout of the verification aircraft can obtain about 7% trim lift increase at 4° of angle of attack. Considering the negative effects of zero-lift drag， downwash and weight increase of the canard， the drag can be reduced by about 19.7count， and the cruise lift-to-drag ratio is increased by 3%. The take-off weight gain caused by the canard + tail components is about 0.3%. The distributed electric propulsion architecture is designed， which can reduce the asymmetric thrust moment by 90%. The flight test of electric propulsion architecture and performance is carried out based on the UAV verification aircraft. When the cruise airspeed is 45 m/s， the power required by the verification aircraft is about 20 kW， and the cruise energy consumption is 0.126 kW·h/km. When the cruise airspeed is 35 m/s， the power required is 8 kW， and the cruise energy consumption is 0.065 kW·h/km. The maximum power is 45 kW in the take-off phase， which is twice the cruise power， and the take-off energy consumption accounts for about 2 % of the flight profile.

Key words: UAV verification aircraft, new layout, three-surface aircraft, electric aircraft, distributed electric propulsion

CLC Number:

V217.3

Chuihuan KONG, Dawei WU, Zhaoguang TAN, Lijun PAN, Rubing MA, Jiangtao SI. Design of fully electric scheme for three⁃surface verification aircraft[J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(6): 629618-629618.

Figures/Tables 24

Table 1

Fig.1

Fig.2

Fig.3

Table 2

Fig.4

Fig.5

Fig.6

Fig.7

Table 3

Table 4

Fig.8

Fig.9

Fig.10

Fig.11

Fig.12

Fig.13

Fig.14

Fig.15

Fig.16

Table 5

Fig.17

Fig.18

Fig.19

References 37

1	纪宇晗，孙侠生，俞笑，等. 双碳战略下的新能源航空发展展望［J］. 航空科学技术， 2022， 33（12）： 1-11.
	JI Y H， SUN X S， YU X， et al. Development prospect of new energy aviation under carbon peaking and carbon neutrality goals［J］. Aeronautical Science & Technology， 2022， 33（12）： 1-11 （in Chinese）.
2	BRAVO-MOSQUERA P D， CATALANO F M， ZINGG D W. Unconventional aircraft for civil aviation： A review of concepts and design methodologies［J］. Progress in Aerospace Sciences， 2022， 131： 100813.
3	夏明，巩文秀，郑建强，等. 欧美翼身融合大型民机方案综述［J］. 民用飞机设计与研究， 2021（3）： 123-134.
	XIA M， GONG W X， ZHENG J Q， et al. A review of blended-wing-body for large civil aircraft of Europe and America［J］. Civil Aircraft Design & Research， 2021（3）： 123-134 （in Chinese）.
4	邢宇. 桁架支撑机翼布局客机总体设计的综合分析与优化［D］. 南京：南京航空航天大学， 2018： 3-13.
	XING Y. Integrated analysis and optimization in conceptual design of airliners with truss-braced wing configuration［D］.Nanjing： Nanjing University of Aeronautics and Astronautics， 2018： 3-13. （in Chinese）.
5	QIN N， VAVALLE A， LE MOIGNE A， et al. Aerodynamic considerations of blended wing body aircraft［J］. Progress in Aerospace Sciences， 2004， 40（6）： 321-343.
6	DEHPANAH P， NEJAT A. The aerodynamic design evaluation of a blended-wing-body configuration［J］. Aerospace Science and Technology， 2015， 43： 96-110.
7	柴啸，陈迎春，谭兆光，等. 翼身融合布局客机总体参数分析与优化［J］. 航空学报， 2019， 40（9）： 623042.
	CHAI X， CHEN Y C， TAN Z G， et al. Analysis and optimization of overall parameters for blended-wing-body civil aircraft［J］. Acta Aeronautica et Astronautica Sinica， 2019， 40（9）： 623042 （in Chinese）.
8	蒋瑾，钟伯文，符松. 翼身融合布局飞机总体参数对气动性能的影响［J］. 航空学报， 2016， 37（1）： 278-289.
	JIANG J， ZHONG B W， FU S. Influence of overall configuration parameters on aerodynamic characteristics of a blended-wing-body aircraft［J］. Acta Aeronautica et Astronautica Sinica， 2016， 37（1）： 278-289 （in Chinese）.
9	潘立军，吴大卫，谭兆光，等. 基于适航符合性的翼身融合布局客机客舱布置设计［J］. 航空学报， 2019， 40（9）： 623044.
	PAN L J， WU D W， TAN Z G， et al. Cabin layout design for BWB civil aircraft based on airworthiness compliance［J］. Acta Aeronautica et Astronautica Sinica， 2019， 40（9）： 623044 （in Chinese）.
10	IATA. Aircraft technology net zero roadmap［EB/OL］. （2023-06-02）［2023-9-20］. .
11	REIST T A， ZINGG D W. Aerodynamic design of blended wing-body and lifting-fuselage aircraft［R］： AIAA-2016-3874. Reston： AIAA， 2016.
12	BRADLEY M K， DRONEY C K. Subsonic ultra green aircraft research phase I： Final report： NASA/CR-2011- 216847［R］. Washington， D.C.： NASA， 2011.
13	张新榃，张帅，王建礼，等. 支撑翼布局客机总体参数对结构重量的影响［J］. 航空学报， 2019， 40（2）： 522359.
	ZHANG X T， ZHANG S， WANG J L， et al. Effect of primary parameters on structure weight of civil aircraft with strut-braced wing［J］. Acta Aeronautica et Astronautica Sinica， 2019， 40（2）： 522359 （in Chinese）.
14	BRADLEY M， DRONEY C K. Subsonic ultra green aircraft research phase II： N+4 advanced concept development： NASA/CR-2012-217556［R］. Washington， D.C.： NASA， 2012.
15	CAVALLARO R， Challenges DEMASI L.， ideas， and innovations of joined-wing configurations ： A concept from the past， an opportunity for the future［J］. Progress in Aerospace Sciences， 2016， 87： 1-93.
16	DRONEY C K， HARRISON N， GATLIN G. Subsonic ultra-green aircraft research： Transonic truss-braced wing technical maturation［C］∥ Proceedings of the 31st Congress of the Internation-al Council of the Aeronautical Sciences. Bonn： ICAS， 2018： 9-14.
17	HARRISON N A， GATLIN G M， VIKEN S A， et al. Development of an efficient M=0.80 transonic truss-braced wing aircraft： AIAA-2020-0011［R］. Reston： AIAA， 2020.
18	XIONG J T， NGUYEN N T， BARTELS R E. Jig twist optimization of Mach 0.8 transonic truss-braced wing aircraft： AIAA-2023-1573［R］. Reston： AIAA， 2023.
19	STROHMEYER D， SEUBERT R， HEINZE W， et al. Three surface aircraft - A concept for future transport aircraft： AIAA-2000-0566［R］. Reston： AIAA， 2000.
20	NICOLOSI F， CORCIONE S， TRIFARI V， et al. Design and optimization of a large turboprop aircraft［J］. Aerospace， 2021， 8（5）： 132.
21	CACCIOLA S， RIBOLDI C， ARNOLDI M. Three-surface model with redundant longitudinal control： Modeling， trim optimization and control in a preliminary design perspective［J］. Aerospace， 2021， 8（5）： 139.
22	RIBOLDI C E D， CACCIOLA S， CEFFA L. Studying and optimizing the take-off performance of three-surface aircraft［J］. Aerospace， 2022， 9（3）： 139.
23	SOLLO A. P.180 avanti： an iconic airplane and the achievement of an historical milestone［J］. Aerotecnica Missili & Spazio， 2021， 100（1）： 69-78.
24	PIAGGIO AEROSPACE. Piaggio Aerospace Brochure Avanti Evo optimised［EB/OL］. （2018-02-28）［2023-09-20］. .
25	ALI J， SALEH M. Experimental and numerical study on the aerodynamics and stability characteristics of a canard aircraft［J］. Journal of Advanced Research in Fluid Mechanics and Thermal Sciences， 2020， 53（2）： 165-174.
26	AGNEW J W， HESS J R Jr. Benefits of aerodynamic interaction to the three-surface configuration［J］. Journal of Aircraft， 1980， 17（11）： 823-827.
27	FELDER J L. NASA electric propulsion system studies： GRC-E-DAA-TN28410［R］. Washington， D.C.： NASA， 2015.
28	王妙香. NASA亚声速大型飞机电推进技术研究综述［J］. 航空科学技术， 2019， 30（11）： 22-29.
	WANG M X. Overview of NASA electrified aircraft propulsion research for large subsonic transports［J］. Aeronautical Science & Technology， 2019， 30（11）： 22-29 （in Chinese）.
29	JANSEN R， BOWMAN C， JANKOVSKY A， et al. Overview of NASA electrified aircraft propulsion （EAP） research for large subsonic transports： AIAA-2017-4701［R］. Reston： AIAA， 2017.
30	WELSTEAD J， FELDER J L. Conceptual design of a single-aisle turboelectric commercial transport with fuselage boundary layer ingestion： AIAA-2016-1027［R］. Reston： AIAA， 2016.
31	STARKEY R， ARGROW B， KREVOR Z. Design and flight testing of a 15% dynamically scaled HL-20 vehicle model： AIAA-2012-1048［R］. Reston： AIAA， 2012.
32	何开锋，毛仲君，汪清，等. 缩比模型演示验证飞行试验及关键技术［J］. 空气动力学学报， 2017， 35（5）： 671-679， 670.
	HE K F， MAO Z J， WANG Q， et al. Demonstration and validation flight test of scaled aircraft model and its key technologies［J］. Acta Aerodynamica Sinica， 2017， 35（5）： 671-679， 670 （in Chinese）.
33	CHAMBERS J R. Modeling flight： The role of dynamically scaled free-flight models in support of NASA’s aerospace programs［M］. Washington， D.C.： NASA， 2010： 1-16.
34	JENKINSON L R， RHODES D， SIMPKIN P. Civil jet aircraft design［M］. Reston： AIAA， 1999.
35	陈迎春，宋文滨，刘洪. 民用飞机总体设计［M］. 上海：上海交通大学出版社， 2010： 29-195.
	CHEN Y C， SONG W B， LIU H. Civil aircraft design［M］. Shanghai： Shanghai Jiao Tong University Press， 2010： 29-195 （in Chinese）.
36	黄俊，杨凤田. 新能源电动飞机发展与挑战［J］. 航空学报， 2016， 37（1）： 57-68.
	HUANG J， YANG F T. Development and challenges of electric aircraft with new energies［J］. Acta Aeronautica et Astronautica Sinica， 2016， 37（1）： 57-68 （in Chinese）.
37	LEVY D. Prediction of average downwash gradient for canard configurations： AIAA-1992-284［R］. Reston： AIAA， 1992.

参数	数值
机身长度/m	5.7
机翼展长/m	7.6
飞机高度/m	1.8
最大起飞重量/kg	200
参考弦长/m	0.4
展弦比	19
机翼面积/m²	2.9
最大飞行速度/（km·h^-1）	200

分类	重量/kg	与起飞重量比值/%
最大滑行重量	200	100
最大起飞重量	200	100
最大着陆重量	200	100
空机重量	131	65.4
机体结构	107	53.7
电机	13	6.7
电调汇流	4	2.0
航电飞控系统	6	3.1
电池	44	22.1
商载	25	12.5

分类	面积/m²	巡航零升阻力/count	重量/kg
三翼面布局	1.00	39.9	2.67
前翼	0.35	13.5	1.07
平尾	0.65	26.4	1.60
无前翼布局平尾	1.00	38.5	2.42
变化量	0	1.4	0.25

分类	无人机（200 kg）	通航飞机（8 t）	支线飞机（40 t）
重量减小/%		0.3
航程增加/%		0.3
对应等效减重/kg	0.6	24.0	125
对应等效减阻/count	1.2	1.2	1
单位减阻等效减重/（kg·count^－1）	0.5	20.0	125

参数	数据
最大速度/（km·h^－1）	203
分布式最大空速/（km·h^－1）	162
最大过载/g	2.2
最大爬升率/（m·s^－1）	11
最大滚转速度/（（°）·s^－1）	43.3
尾翼前翼舵效比例	1.8~2.0
失速迎角/（°）	16~17
最大升力系数	2.3

Design of fully electric scheme for three⁃surface verification aircraft

RichHTML

PDF (PC)

Knowledge

Abstract

Cite this article

share this article

Figures/Tables 24

References 37

Related Articles 15

Recommended Articles

Metrics

Comments

[1]	Jinghui DENG. Technical status and development of electric vertical take⁃off and landing aircraft [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(5): 529937-529937.
[2]	ZHANG Xingyu, GAO Zhenghong, LEI Tao, MIN Zhihao, LI Weiling, ZHANG Xiaobin. Ground test on aerodynamic-propulsion coupling characteristics of distributed electric propulsion aircraft [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(8): 125389-125389.
[3]	SU Ning, HUANG Wenxin. Parallel power generation system based on dual-stator winding induction generator for electric propulsion aircraft [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(8): 325409-325409.
[4]	ZHANG Bendong, JIANG Jun, LI Zhi, LI Shimin, ZHANG Chaohai. Partial discharge characteristics of future more electric aircraft under low air pressure [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(7): 325374-325374.
[5]	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.
[6]	RAO Chong, ZHANG Tiejun, WEI Chuang, LIU Ying. Influence mechanism of propeller slipstream on wing of a distributed electric aircraft scheme [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2021, 42(S1): 726387-726387.
[7]	ZHANG Yang, ZHOU Zhou, GUO Jiahao. Effects of distributed electric propulsion jet on aerodynamic performance of rear wing [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2021, 42(9): 224977-224977.
[8]	LIU Haigang, LIU Liang, WANG Peng, ZHOU Wei. Model based simulation and analysis of energy optimization characteristics of more-electric aircraft [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2021, 42(8): 525801-525801.
[9]	ZHANG Zhuoran, XU Yanwu, YU Li, LI Jincai, XIA Yiwen. Parallel HVDC electric power system for more-electric-aircraft: State of the art and key technologies [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2021, 42(6): 624069-624069.
[10]	LEI Tao, KONG Delin, WANG Runlong, LI Weilin, ZHANG Xiaobin. Evaluation and optimization method for power systems of distributed electric propulsion aircraft [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2021, 42(6): 624047-624047.
[11]	FAN Zhenwei, YANG Fengtian, LI Yadong, XIANG Song, ZHAO Weiping. Design and test of two-seater electric aircraft [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2021, 42(3): 623972-623972.
[12]	LIU Yuanqiang, WANG Yanbing, XIANG Song, WANG Mengqi. Noise characteristics of propellers with different blade tips for electric aircraft [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2021, 42(3): 624567-624567.
[13]	YANG Fengtian, FAN Zhenwei, XIANG Song, LIU Yuanqiang, ZHAO Weiping. Technical innovation and practice of electric aircraft in China [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2021, 42(3): 624619-624619.
[14]	WANG Shuli, SUN Jinbo, KANG Guiwen, MA Shaohua. Energy efficiency optimization method for electric aircraft propulsion system [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2021, 42(3): 623942-623942.
[15]	HUANG Jun. Survey on design technology of distributed electric propulsion aircraft [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2021, 42(3): 624037-624037.