超声速飞行器FADS系统实时解算设计与验证
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摘要
针对典型超声速飞行器的头部外形,采用CFD数值模拟方法计算获得超声速飞行器头部测压点阵列的压力数据,设计了基于BP神经网络技术的求解算法和基于FPGA+DSP构架数字信号处理的解算机、飞行马赫数2.0~4.5的嵌入式大气数据传感系统实时解算方案。应用蒙特卡罗法分析测量总误差对算法模型的影响,并获得满足嵌入式大气数据传感系统设计目标要求的测量系统总误差。算法在解算机上完成1次计算所需时间<1ms,完全可以满足嵌入式大气数据传感系统算法实时解算设计的要求。在1.2m×1.2m超声速风洞完成求解算法的实时解算试验,试验结果与风洞系统的测量结果基本吻合,系统在实时解算过程中未出现异常、能灵敏反映出来流参数变化、具有很好的鲁棒性和敏捷性。静压测量相对误差≤6.9%,马赫数测量误差<0.1,迎角和侧滑角的测量误差均<1°。最后还分析了试验误差影响因素,提出了试验改进的方法。
In view of the head shape of a typical supersonic aircraft,the array pressure data of supersonic aircrafts is calculated by computational fluid dynamics method.The real-time solution scheme for algorithm model of the flush air data sensing system is designed for the flight Mach umber range 2.0~4.5 based on BP neural network technique and FPGA+DSP architecture digital signal processing.The design results of the algorithm model are analyzed.The influence of the total error on the algorithm model is investigated by the Monte Carlo method,and the total error of the measurement system is obtained.The algorithm needs no more than 1 millisecond for one time solution in solving machine,which can meet the requirements of the flush air data sensing system for algorithm real-time solving.The test of real-time calculation of the principled sample machine is in 1.2 m×1.2 msupersonic wind tunnel.Test results are in good agreement with the measurement results of the wind tunnel system.The system is working without any fatal error in the whole test.It can reflect the variations of the flow parameters,and has good robustness and agility.The relative error of static pressure measurement is≤ 6.9%,the Mach number measurement< 0.1,the angle of attack and the side slip angle measurement<1°.The influence factors of measurement error are analyzed,and improvement method of the experiment is presented at last.
In view of the head shape of a typical supersonic aircraft,the array pressure data of supersonic aircrafts is calculated by computational fluid dynamics method.The real-time solution scheme for algorithm model of the flush air data sensing system is designed for the flight Mach umber range 2.0~4.5 based on BP neural network technique and FPGA+DSP architecture digital signal processing.The design results of the algorithm model are analyzed.The influence of the total error on the algorithm model is investigated by the Monte Carlo method,and the total error of the measurement system is obtained.The algorithm needs no more than 1 millisecond for one time solution in solving machine,which can meet the requirements of the flush air data sensing system for algorithm real-time solving.The test of real-time calculation of the principled sample machine is in 1.2 m×1.2 msupersonic wind tunnel.Test results are in good agreement with the measurement results of the wind tunnel system.The system is working without any fatal error in the whole test.It can reflect the variations of the flow parameters,and has good robustness and agility.The relative error of static pressure measurement is≤ 6.9%,the Mach number measurement< 0.1,the angle of attack and the side slip angle measurement<1°.The influence factors of measurement error are analyzed,and improvement method of the experiment is presented at last.
引文
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[12]Li Q D,Chen L L,Zhang X G,et al.FADS fast intelligent fault detection and diagnosis technology[J].Journal of System Engineering and Electronic Technology,2009,31(10):2544-2546.(in Chinese)李清东,陈璐璐,张孝功,等.FADS快速智能故障检测和诊断技术[J].系统工程与电子技术,2009,31(10):2544-2546.
[13]Chen G Q,Wang G D,Chen B Y,et al.Study of flush air data system technology for low cost flight test platform[J].Journal of Astronautics,2015,36(10):1195-1202.(in Chinese)陈广强,王贵东,陈冰雁,等.低成本飞行试验平台FADS技术研究[J].宇航学报,2015,36(10):1195-1202.
[14] Wang P,Jin X,Zhang W M.Application of FADS system in hypersonic flight vehicles with sharp wedged fore-bodies[J].Sci Sin-Phys MechAstron,2013,43(9):1105-1110.(in Chinese)王鹏,金鑫,张卫民.FADS系统在尖楔前体高超声速飞行器中的应用[J].中国科学:物理学力学天文学,2013,43(9):1105-1110.
[15]Qin Y M,Zhang C,Dong J G.Experimental study on flush air data sensing system calibration in wind tunnel[J].Acta Aerodynamica Sinica,2015,33(4):488-492.(in Chinese)秦永明,张春,董金刚.嵌入式大气数据传感系统风洞标定试验研究[J].空气动力学学报,2015,33(4):488-492.
[2] JoelC Ellsworth,Stephen A Whitmore.Reentry airdata system for a sub-orbital spacecraft based on X-34design[R].AIAA-2007-1200.
[3] Jost M,Schwegmann F,Dr T Kohler.Flush air data system and advanced airdata system for the aerospace industry[R].AIAA-2004-5028.
[4] Ethan Baumann,Joseph W Pahle,Mark C Davis.X-43Aflush airdata sensing system flight test results[R].AIAA-2008-657.
[5] Joel C Ellsworth,Stephen A Whitmore.Simulation of a flush air-data system for transatmospheric vehicles[J].Journal of Spacecraft and Rocket,2008,45(4):716-73.
[6] Zheng C J,Lu Y P,Gao L.Application of BP network in flush air data sensing system[J].Journal of Measurement and Control Technology,2006,25(6):9-12.(in Chinese)郑成军,陆宇平,高璐.BP网络在嵌入式大气数据传感系统中的应用[J].测控技术,2006,25(6):9-12.
[7] Feng J C,Zheng C J,Chen feng.Flush air data sensing system and BP network correction algorithm[J].Journal of Computer Measurement and Control,2006,14(4):541-544.(in Chinese)冯建超,郑成军,陈峰.嵌入式大气数据传感系统及其BP网络校正算法[J].计算机测量与控制,2006,14(4):541-544.
[8] Zheng S D,Lu Y P,Ye W.Study on FADS system fault detection and management technology based onχ2 test[J].Journal of Computer Measurement and Control,2007,15(11):1449-1454.(in Chinese)郑守铎,陆宇平,叶玮.基于χ2检验的FADS系统故障检测与管理技术研究[J].计算机测量与控制,2007,15(11):1449-1454.
[9] Zhao L,Lu Y P.FADS system and its algorithm based on RBF neural network[J].Journal of Air Craft Design,2012,32(1):43-47.(in Chinese)赵磊,陆宇平.基于RBF神经网络的FADS系统及其算法研究[J].飞机设计,2012,32(1):43-47.
[10] Wen R X,Zheng S Z,Ye W.The development status of flush air data sensing technology[J].Journal of Electro-Optic and Control,2008(8):101-106.(in Chinese)温瑞珩,郑守铎,叶玮.嵌入式大气数据传感技术的发展现状[J].电光与控制,2008(8):101-106.
[11]Li Q C.Flushing air data three preliminary study on the method of solution[J].Journal of Aerodynamics,2014,32(03):360-363.(in Chinese)李其畅.嵌入式大气数据三点解算方法初步研究[J].空气动力学学报,2014,32(03):360-363.
[12]Li Q D,Chen L L,Zhang X G,et al.FADS fast intelligent fault detection and diagnosis technology[J].Journal of System Engineering and Electronic Technology,2009,31(10):2544-2546.(in Chinese)李清东,陈璐璐,张孝功,等.FADS快速智能故障检测和诊断技术[J].系统工程与电子技术,2009,31(10):2544-2546.
[13]Chen G Q,Wang G D,Chen B Y,et al.Study of flush air data system technology for low cost flight test platform[J].Journal of Astronautics,2015,36(10):1195-1202.(in Chinese)陈广强,王贵东,陈冰雁,等.低成本飞行试验平台FADS技术研究[J].宇航学报,2015,36(10):1195-1202.
[14] Wang P,Jin X,Zhang W M.Application of FADS system in hypersonic flight vehicles with sharp wedged fore-bodies[J].Sci Sin-Phys MechAstron,2013,43(9):1105-1110.(in Chinese)王鹏,金鑫,张卫民.FADS系统在尖楔前体高超声速飞行器中的应用[J].中国科学:物理学力学天文学,2013,43(9):1105-1110.
[15]Qin Y M,Zhang C,Dong J G.Experimental study on flush air data sensing system calibration in wind tunnel[J].Acta Aerodynamica Sinica,2015,33(4):488-492.(in Chinese)秦永明,张春,董金刚.嵌入式大气数据传感系统风洞标定试验研究[J].空气动力学学报,2015,33(4):488-492.