二元激波矢量喷管矢量性能敏感性分析

doi:10.7527/S1000-6893.2022.27831

Abstract

Abstract:

Fluid thrust vectoring technology is regarded as a key technology for the development of very low detectable vehicles because of its advantages such as fast response， light weight and good stealth performance. The current research on the performance of fluid thrust vectoring nozzles is mainly focused on univariate studies. Multivariate sensitivity analysis of fluid thrust vectoring nozzles is carried out to help clarify the key parameters affecting the nozzle vectoring performance， and guide the design of fluid thrust vectoring nozzles. The sensitivity analysis method based on non-intrusive polynomial chaos was carried out to investigate the global sensitivity analysis of seven design variables such as Mach number of outflow， jet position， jet angle， Nozzle Pressure Ratio （NPR） and correlation analysis for different targets of the two-dimensional Shock Vector Control （SVC） nozzle. The results show that vector angle and vector efficiency are significantly sensitive to jet position； thrust coefficient is more sensitive to NPR， outflow Mach number， secondary flow pressure ratio （the ratio of total secondary flow pressure to ambient pressure SPR_t）. The results also show that secondary flow ratio is more sensitive to NPR， and the contribution of ratio of total mainstream and secondary flow temperature to ambient temperature to the vector performance is expressed mainly in the secondary flow ratio. The increase of both vector angle and secondary flow ratio leads to thrust loss， and the secondary flow ratio has the greatest impact. The increase in outflow Mach number changes the actual pressure ratio of the nozzle and reduces the nozzle vectoring performance. When the position of the secondary flow is close to the throat， the separation before the jet extends to the throat， and the separation after the jet reattaches under the large NPR. The change of the nozzle aerodynamic profile results in the decline of the vector performance， and in serious cases， the vector angle reversal occurs. The SVC nozzle should be designed so that the jet is positioned close to the nozzle outlet and the oblique shock wave in the nozzle is adjusted to develop near the nozzle outlet for a given NPR and SPR_t， thus improves the vector performance without increasing the secondary flow ratio. A reasonable combination of parameters can mitigate the negative impact of increasing outflow Mach number on nozzle vector performance， and can improve nozzle vector performance without increasing the secondary flow ratio.

Key words: fluidic vector thrust, two-dimensional nozzle, shock vector nozzle, global sensitivity analysis, non-intrusive polynomial chaos, transverse jet

CLC Number:

V231

Bowen SHU, Jiangtao HUANG, Zhenghong GAO, Gang LIU, Chengjun HE, Lu XIA. Sensitivity analysis of vector performance of two⁃dimensional shock vector control nozzle[J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(13): 127831-127831.

Figures/Tables 14

Fig.1

Fig.2

Fig.3

Table 1

Values of variables

变量序号	设计变量	取值范围
$v 1$	$M a ∞$	［0.05，1.3］
$v 2$	$θ / (°)$	［40，130］
$v 3$	$l / x t$	［1.211，1.904］
$v 4$	NPR	［3，10］
$v 5$	$S P R t$	［3，15］
$v 6$	$T m$	［1.0，5.0］
$v 7$	$T s$	［1.0，5.0］

Table 1

Fig.4

Fig.5

Fig.6

Fig.7

Table 2

Correlation coefficients for different targets

目标	$δ p$	$ω r$	$C f g$	$η p$
$δ p$		0.014	-0.20	0.84
$ω r$	0.014		-0.61	-0.23
$C f g$	-0.20	-0.61		-0.009 6
$η p$	0.84	-0.23	-0.009 6

Table 2

Fig.8

Table 3

Correlation coefficients between parameters and targets

目标	$δ p$	$C f g$	$ω r$	$η p$
$M a ∞$	-0.17	-0.35	-0.01	-0.1
$θ / (°)$	0.14	0.14	-0.01	0.10
$l / x t$	0.88	-0.24	-0.1	0.81
NPR	-0.10	0.56	-0.56	0.06
$S P R t$	-0.04	-0.40	0.63	-0.28
$T m$	0.021	-0.11	0.30	-0.07
$T s$	0.01	0.014	-0.31	0.09

Table 3

Table 4

Comparison for vector performance between samples

样本	$δ p$ /（°）	$C f g$	$ω r$ /%	$η p$ /（°）
Ori	7.3	0.97	4.0	1.83
1	8.86	0.93	4.6	1.94
2	10.57	0.96	4.7	2.44
3	-4.89	0.97	4.1	-1.19

Table 4

Table 5

Comparison for variables between samples

样本	$M a ∞$	$θ /$ （°）	$l / x t$	NPR	$S P R t$	$T m$	$T s$
Ori	0.05	101.01	1.80	4.60	3.22	1.00	1.00
1	0.84	49.93	1.73	5.58	4.61	2.90	4.60
2	0.32	85.45	1.83	6.32	6.09	1.96	4.72
3	0.53	96.89	1.27	8.29	9.06	1.29	4.53

Table 5

Fig.9

References 27

1	FRANCIS M S. Air vehicle management with integrated thrust-vector control［J］. AIAA Journal， 2018， 56（12）： 4741-4751.
2	王海峰. 战斗机推力矢量关键技术及应用展望［J］. 航空学报， 2020， 41（6）： 524057.
	WANG H F. Key technologies and future applications of thrust vectoring on fighter aircraft［J］. Acta Aeronautica et Astronautica Sinica， 2020， 41（6）： 524057 （in Chinese）.
3	程荣辉，张志舒，陈仲光. 第四代战斗机动力技术特征和实现途径［J］. 航空学报， 2019， 40（3）： 022698.
	CHENG R H， ZHANG Z S， CHEN Z G. Technical characteristics and implementation of the fourth-generation jet fighter engines［J］. Acta Aeronautica et Astronautica Sinica， 2019， 40（3）： 022698 （in Chinese）.
4	KOWAL H J. Advances in thrust vectoring and the application of flow-control technology［J］. Canadian Aeronautics and Space Journal， 2002， 48（2）： 145-151.
5	MARUYAMA Y， SAKATA M， TAKAHASHI Y. Performance analyses of fluidic thrust vector control system using dual throat nozzle［J］. AIAA Journal， 2021， 60（3）： 1730-1744.
6	史经纬. 固定几何气动矢量喷管流动机理及性能评估技术研究［D］. 西安：西北工业大学， 2015.
	SHI J W. Investigation on flow mechanism and performance estimation of fixed-geometric thrust vectoring nozzle［D］. Xi’an： Northwestern Polytechnical University， 2015 （in Chinese）.
7	DEERE K. Summary of fluidic thrust vectoring research at NASA langley research center［C］∥ 21st AIAA Applied Aerodynamics Conference. Reston： AIAA， 2003： 3800.
8	CHIARELLI C， JOHNSEN R， SHIEH C， et al. Fluidic scale model multi-plane thrust vector control test results［C］∥ 29th Joint Propulsion Conference and Exhibit. Reston： AIAA， 1993： 2433.
9	WING D J， GIULIANO V J. Fluidic thrust vectoring of an axisymmetric exhaust nozzle at static conditions［C］∥1997 ASME Fluids Engineering Division Summer Meeting. New York： ASME， 1997： DWSA M97-3228.
10	DEERE K. Computational investigation of the aerodynamic effects on fluidic thrust vectoring［C］∥ 36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. Reston： AIAA， 2000： 3598.
11	WAITHE K， DEERE K. An experimental and computational investigation of multiple injection ports in a convergent-divergent nozzle for fluidic thrust vectoring［C］∥ 21st AIAA Applied Aerodynamics Conference. Reston： AIAA， 2003： 3802.
12	FORGHANY F， TAEIBE-RAHNI M， ASADOLLAHI-GHOHIEH A. Numerical investigation of freestream flow effects on thrust vector control performance［J］. Ain Shams Engineering Journal， 2018， 9（4）： 3293-3303.
13	FORGHANY F， TAEIBE R M， ASADOLLAHI G， et al. Numerical investigation of injection angle effects on shock vector control performance［J］. Proceedings of the Institution of Mechanical Engineers， Part G： Journal of Aerospace Engineering， 2019， 233（2）： 405-417.
14	YOUNES K， HICKEY J P. Fluidic thrust shock-vectoring control： A sensitivity analysis［J］. AIAA Journal， 2020， 58（4）： 1887-1890.
15	王占学，李志杰. 喷管气动参数对推力矢量影响的数值模拟［J］. 推进技术， 2008， 29（2）： 187-193.
	WANG Z X， LI Z J. Effect of aerodynamic parameters of main and secondary flow path on thrust vectoring［J］. Journal of Propulsion Technology， 2008， 29（2）： 187-193 （in Chinese）.
16	张晓博，王占学，刘增文. 气动矢量喷管二次流对发动机性能的影响［J］. 推进技术， 2013， 34（1）： 3-7.
	ZHANG X B， WANG Z X， LIU Z W. Influence of secondary flow in fluidic thrust vector nozzle on aero-engine performance［J］. Journal of Propulsion Technology， 2013， 34（1）： 3-7 （in Chinese）.
17	史经纬，王占学，刘增文，等. 二次流喷口形状对激波矢量控制喷管推力矢量特性影响［J］. 航空动力学报， 2013， 28（12）： 2678-2684.
	SHI J W， WANG Z X， LIU Z W， et al. Effects of secondary injection forms on thrust vector performance of shock vector controlling nozzle［J］. Journal of Aerospace Power， 2013， 28（12）： 2678-2684 （in Chinese）.
18	王猛杰，额日其太，王强，等. 激波矢量控制喷管落压比影响矢量性能及分离区控制数值模拟［J］. 航空动力学报， 2015， 30（3）： 526-536.
	WANG M J， ERIQITAI， WANG Q， et al. Numerical simulaton of nozzle pressure ratio effect on vector performance and separation control for shock vector control nozzle［J］. Journal of Aerospace Power， 2015， 30（3）： 526-536 （in Chinese）.
19	王晓明，刘辉，韩龙柱，等. 激波诱导推力矢量喷管不同气体喷注时的性能分析［J］. 北京航空航天大学学报， 2018， 44（11）： 2267-2272.
	WANG X M， LIU H， HAN L Z， et al. Performance analysis of shock thrust vector nozzle under different gas injections［J］. Journal of Beijing University of Aeronautics and Astronautics， 2018， 44（11）： 2267-2272 （in Chinese）.
20	ZHAO H， GAO Z H， XU F， et al. Review of robust aerodynamic design optimization for air vehicles［J］. Archives of Computational Methods in Engineering， 2019， 26（3）： 685-732.
21	ZHAO H， GAO Z H， GAO Y， et al. Effective robust design of high lift NLF airfoil under multi-parameter uncertainty［J］. Aerospace Science and Technology， 2017， 68： 530-542.
22	SCHAEFER J A， WEST T， HOSDER S， et al. Uncertainty quantification of turbulence model closure coefficients for transonic wall-bounded flows［C］∥ 22nd AIAA Computational Fluid Dynamics Conference. Reston： AIAA， 2015： 2461.
23	陈宪，陈诚，黄江涛，等. 腹部襟翼对飞翼布局飞行器起降气动特性的影响［J］. 航空学报， 2022， 43（3）： 125028.
	CHEN X， CHEN C， HUANG J T， et al. Effects of belly flap on take-off and landing characteristics of a flying-wing vehicle［J］. Acta Aeronautica et Astronautica Sinica， 2022， 43（3）： 125028 （in Chinese）.
24	舒博文，杜一鸣，高正红，等. 典型航空分离流动的雷诺应力模型数值模拟［J］. 航空学报， 2022， 43（11）： 487-502.
	SHU B W， DU Y M， GAO Z H， et al. Numerical simulation of Reynolds stress model of typical aerospace separated flow［J］. Acta Aeronautica et Astronautica Sinica， 2022， 43（11）： 487-502 （in Chinese）.
25	HOSDER S， WALTERS R， BALCH M. Efficient sampling for non-intrusive polynomial chaos applications with multiple uncertain input variables［C］∥ 48th AIAA/ASME/ASCE/AHS/ASC Structures， Structural Dynamics， and Materials Conference. Reston： AIAA， 2007： 1939.
26	SOBOL′ I M. Global sensitivity indices for nonlinear mathematical models and their Monte Carlo estimates［J］. Mathematics and Computers in Simulation， 2001， 55（1-3）： 271-280.
27	SOBOL I M， KUCHERENKO S. Derivative based global sensitivity measures and their link with global sensitivity indices［J］. Mathematics and Computers in Simulation， 2016， 71（10）： 3009-3017.

[1]	Wanying YUN, Zhenzhou LYU. An efficient surrogate method for analyzing parameter global reliability sensitivity [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(12): 227670-227670.
[2]	DENG Tian, LI Jiazhou, CHEN Wei. Breakup mechanism of viscous liquid transverse jet [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(3): 125130-125130.
[3]	WU You, XU Xu, CHEN Bing, YANG Qingchun. Numerical study on transverse/opposing jet interaction flowfield under high Mach number [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2021, 42(S1): 726359-726359.
[4]	ZHANG Wei, GAO Zhenghong, ZHOU Lin, XIA Lu. Adaptive parameterization method for surrogate-based global optimization [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2020, 41(10): 123815-123815.
[5]	LAI Jiang, ZHAO Zhongliang, WANG Xiaobing, LI Hao, LI Yuping. Uniform pitching motion and angular rate effects on transverse jet interaction [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2019, 40(10): 122866-122866.
[6]	FENG Kaixuan, LYU Zhenzhou, JIANG Xian. Efficient algorithm for estimating derivative-based global sensitivity index [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2018, 39(3): 221699-221699.
[7]	SONG Fuqiang, YAN Chao, MA Baofeng, JU Shengjun. Uncertainty analysis of aerodynamic characteristics for cone-derived waverider configuration [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2018, 39(2): 121519-121519.
[8]	LIU Fuchao, WEI Pengfei, ZHOU Changcong, ZHANG Zheng, YUE Zhufeng. Time-dependent reliability and sensitivity analysis for planar motion mechanisms with revolution joint clearances [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2018, 39(11): 422133-422141.
[9]	GONG Xiangrui, LYU Zhenzhou, ZUO Jianwei. Two improved methods for variance-based global sensitivity analysis' W-indices [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2016, 37(6): 1888-1898.
[10]	RUAN Wenbin, LIU Yang, XIONG Lei. Influence of side aerodynamic derivative uncertainty on side flight load based on global sensitivity analysis [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2016, 37(6): 1827-1832.
[11]	ZHENG Li-bao. INFRARED EMISSIONS FROM TURBOJET WITH TWO-DIMENSIONAL NOZZLE [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2002, 23(2): 140-142.

Sensitivity analysis of vector performance of two⁃dimensional shock vector control nozzle

RichHTML

PDF (PC)

Knowledge

Abstract

Cite this article

share this article

Figures/Tables 14

References 27

Related Articles 11

Recommended Articles

Metrics

Comments