飞机飞行载荷校准试验约束补偿技术

doi:10.7527/S1000-6893.2023.27500

Abstract

Abstract:

To solve the problem that the loads on the aircraft restraint device go beyond its limit of the landing gear under the serious load conditions in a particular aircraft loads calibration test， the design theory of constraint compensation is studied. A longitudinal and lateral-directional balance engineering model for aircraft is established based on mechanical analysis， and the relationship function between the constraint compensation and the calibration loads is derived. According to the structural characteristics of the aircraft， a constraint compensation scheme which can realize the dynamic balance of the whole aircraft during the test， and implementation control techniques are proposed， which can effectively correct the nonlinear errors in dynamic loading， component deformation and loading equipment installation deviation during loads calibration tests. By the implementation of aircraft loads calibration test， the scientific nature of the constraint compensation is verified. The results show that the constraint compensation can be used to realize the dynamic balance of the aircraft during loads calibration test and keep the variations of the 3-way loads on the passive restraint device of the landing gear within 5%， thus effectively reducing the risks of the calibration test.

Key words: flight loads, load calibration test, aircraft constraint, constraint compensation, aircraft balance

CLC Number:

V217⁺.32

Jianhu YU. Constraint compensation technology on aircraft loads calibration test[J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(19): 227500-227500.

Figures/Tables 8

Fig.1

Fig.2

Fig.3

Fig.4

Fig.5

Table 1

Fig.6

Fig.7

References 21

1	总装备部. 军用飞机强度和刚度规范第二部分：飞行载荷：［S］. 北京：总装备部军标出版发行部， 2008.
	General Equipment Department. Military airplane structure strength specification Part 2： Flight loads：［S］. Beijing： General Equipment Department Military Standard Press， 2008 （in Chinese）.
2	总装备部. 军用飞机强度和刚度规范第十部分：飞行试验：［S］. 北京：总装备部军标出版发行部， 2008.
	General Equipment Department. Military airplane structure strength specification Part 10： Flight test：［S］. Beijing： General Equipment Department Military Standard Press， 2008 （in Chinese）.
3	LOMAX T. Structural loads analysis for commercial transport aircraft： Theory and practice［M］. Reston： American Institute of Aeronautics and Astronautics， 1996.
4	SKOPINSKI T， AIKEN W S， HUSTON W B. Calibration of strain-gage installations in aircraft structures for the measurement of flight loads： NACA-Report-1178［R］. Washington D. C. ： NASA， 1954.
5	克利亚奇科 M P. 飞机强度飞行试验（静载荷）［M］. 汤吉晨，译. 西安：航空航天部《ASST》系统工程办公室， 1992： 21-23.
	KLIQKO M P. Aircraft strength test （static load）［M］. TANG J C， translated. Xi’an： ASST Engineering Office of Ministry of Aeronautics and Astronautics， 1992： 21-23 （in Chinese）.
6	JENKINS J M， DEANGELIS V M. A summary of numerous strain-gage load Calibration on Aircraft Wings and Tails in a Technology Format： NASA Technical Memorandum 4804［R］. Washington， D. C. ：NASA， 1997.
7	NELSON S A. Strain gage selection in loads equations using a genetic algorithm［R］. Washington D. C. ： NASA， 1994.
8	蒋祖国，田丁栓，周占廷. 飞机结构载荷/环境谱［M］. 北京：电子工业出版社， 2012： 260-267.
	JIANG Z G， TIAN D S， ZHOU Z T. Aircraft structural load/environment spectrum［M］. Beijing： Publishing House of Electronics Industry， 2012： 260-267 （in Chinese）.
9	汤吉晨. 飞机尾翼载荷飞行测量研究［J］. 航空学报， 1989， 10（10）： 474-478.
	TANG J C. Investigation on the determination of airplane tail loads by flight tests［J］. Acta Aeronautica et Astronautica Sinica， 1989， 10（10）： 474-478 （in Chinese）.
10	张海涛，余建虎，李志蕊，等. T型尾翼布局的垂尾载荷测量技术［J］. 航空学报， 2019， 40（3）： 122074.
	ZHANG H T， YU J H， LI Z R， et al. Measuring technology for vertical fin load of T-shaped empennage layout［J］. Acta Aeronautica et Astronautica Sinica， 2019， 40（3）： 122074 （in Chinese）.
11	李志蕊，范华飞，谢帅，等. 机翼载荷脱机校准技术研究与应用［J］. 航空科学技术， 2018， 29（10）： 38-42.
	LI Z R， FAN H F， XIE S， et al. Research and application on the technology of wing loading off-aircraft calibration［J］. Aeronautical Science & Technology， 2018， 29（10）： 38-42 （in Chinese）.
12	WILLIAM A L， RICK S. Strain-gage loads calibration parametric study： NASA/TM-20040212853［R］. Washington D. C. ：NASA， 20044.
13	李昭广，郭正旺，赵华. 小子样飞机载荷谱测量飞行试验研究技术［C］∥全国飞行力学与飞行试验年会论文集. 西安：中国航空学会飞行力学与飞行试验分会， 2005： 282-286.
	LI Z G， GUO Z W， ZHAO H. flight test research technology of small sample aircraft load spectrum measurement［C］∥ Proceedings of the National Annual Conference on Flight Mechanics and Flight Tests. Xi’an： Chinese Society of Aeronautics and Astronautics Flight Mechanics and Flight test sub-society， 2005： 282-286 （in Chinese）.
14	梁相文. 未来试飞新技术挑战［M］. 北京：航空工业出版社， 2014.
	LIANG X W. Challenge of future new flight test technology［M］. Beijing： Aviation Industry Press， 2014 （in Chinese）.
15	LAWRENCE F R. Evaluation of a strain-gage load calibration on a low-aspect-ratio wing structure at elevated temperature ［R］. Washington D. C.： NASA， 1989.
16	洪嘉振，杨长俊. 理论力学［M］. 2版. 北京：高等教育出版社， 2002.
	HONG J Z， YANG C J. Theoretical mechanics［M］. 2nd ed. Beijing： Higher Education Press， 2002 （in Chinese）.
17	LOKOS W， OLNEY C， CHEN T， et al. Strain-gage loads calibration testing of the active aeroelastic wing F/A-18 Aircraft［C］∥ Proceedings of the 22nd AIAA Aerodynamic Measurement Technology and Ground Testing Conference. Reston： AIAA， 2002.
18	LABELLE R J. E2-C loads calibration preliminary design review［R］. Washington D. C.： NASA， 2004.
19	刘冰. 大型飞机全机静力试验静定支持与约束技术及其应用［J］. 科学技术与工程， 2019， 19（11）： 286-291.
	LIU B. Research and azpplication of statically determinate support and restraint technology for static test on large aircraft［J］. Science Technology and Engineering， 2019， 19（11）： 286-291 （in Chinese）.
20	夏峰，穆家琛. 全机静力试验多轮多支柱起落架支持与加载技术［J］. 科学技术与工程， 2018， 18（30）： 238-244.
	XIA F， MU J C. The support and loading technology of landing gear with multi-wheels and multi-struts for full-scale aircraft static test［J］. Science Technology and Engineering， 2018， 18（30）： 238-244 （in Chinese）.
21	曹景涛. 六自由度静定支持与约束技术在飞机载荷校准试验中的应用［J］. 应用力学学报， 2014， 31（3）： 317-321， 484.
	CAO J T. The application of six degree of freedom statically determinate support and restraint technology in aircraft load calibration test［J］. Chinese Journal of Applied Mechanics， 2014， 31（3）： 317-321， 484 （in Chinese）.

部件	加载方式	作用点	方向	大小/%DLL
平尾	两侧对称	16点组合	向下	41
垂尾	单侧加载	8点组合	向左	37

[1]	CUI Ming, FENG Jianmin, MI Zheng, GUO Junhao. Loading technology for main structure of large UAV durability test [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(6): 525887-525887.
[2]	MENG Min, JIANG Xian, JIA Tianjiao. A flap crank load measurement method based on virtual load calibration test [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2020, 41(2): 223408-223408.
[3]	JING Zhiwei, HOU Zongtuan, GUO Zhaodian. Flight Loads Design Technique for Flexible Aircraft Airdrop [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2014, 35(11): 3037-3045.
[4]	YANG Chao;XIAO Zhipeng;WAN Zhiqiang. A Robust Aeroelastic Optimization Method of Structure and Trim for Air Vehicle with Multiple Control Surfaces [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2011, 32(1): 75-82.
[5]	Yuan Zhengting . IN FLIGHT MEASUREMENT OF STATIC PRESSURE ON A SUBSONIC TRANSPORT AIRCRAFT [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 1998, 19(4): 486-488.

Constraint compensation technology on aircraft loads calibration test

RichHTML

PDF (PC)

Knowledge

Abstract

Cite this article

share this article

Figures/Tables 8

References 21

Related Articles 5

Recommended Articles

Metrics

Comments