陈广强, 刘吴月, 豆修鑫, 周伟江, 杨云军, 豆国辉. 超声速飞行器FADS系统实时解算设计与验证[J]. 空气动力学学报, 2018, 36(4): 561-570. DOI: 10.7638/kqdlxxb-2016.0073
引用本文: 陈广强, 刘吴月, 豆修鑫, 周伟江, 杨云军, 豆国辉. 超声速飞行器FADS系统实时解算设计与验证[J]. 空气动力学学报, 2018, 36(4): 561-570. DOI: 10.7638/kqdlxxb-2016.0073
CHEN Guangqiang, LIU Wuyue, DOU Xiuxin, ZHOU Weijiang, YANG Yunjun, DOU Guohui. Flush air data sensing system real-time solving design and verification for supersonic vehicle[J]. ACTA AERODYNAMICA SINICA, 2018, 36(4): 561-570. DOI: 10.7638/kqdlxxb-2016.0073
Citation: CHEN Guangqiang, LIU Wuyue, DOU Xiuxin, ZHOU Weijiang, YANG Yunjun, DOU Guohui. Flush air data sensing system real-time solving design and verification for supersonic vehicle[J]. ACTA AERODYNAMICA SINICA, 2018, 36(4): 561-570. DOI: 10.7638/kqdlxxb-2016.0073

超声速飞行器FADS系统实时解算设计与验证

Flush air data sensing system real-time solving design and verification for supersonic vehicle

  • 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 < 1 ms,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1.2 m×1.2 m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。

     

    Abstract: 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 m supersonic 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.

     

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