钝头机体用嵌入式大气数据传感系统的改进三点式算法
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摘要
针对传统的用于钝头体飞行器的嵌入式大气数据传感系统的经典三点式算法对测压孔配置约束性严格的特点,对经典三点式算法进行了改进及验证。首先,对于经典三点式算法及改进算法进行了论述;其次,针对不同测压孔配置对算法精度的影响进行了系统的评估;最后,对于传统的经典三点式算法与改进三点式算法的优劣进行了比较。结论为:(1)改进的三点式算法对于测压孔的配置敏感性变差,即对测压孔约束很宽松,可用测压孔数增加,从而使得算法的适用性更强;(2)改进的三点式算法的精度与三点式算法相当,但是需要对测压孔进行系统选取及对比验证。
In view of the restrictive requirement of the pressure port configuration for the flush air data sensing(FADS) system based on the classical triple algorithm, a modified triple algorithm is developed and verified. Firstly, the classical triple algorithm and the modified triple algorithm are described. Secondly,the feasibility of the FADS system based on the modified triple algorithm including the pressure port configuration and the solving accuracy is evaluated. Finally, the advantages and the disadvantages of these two different methods are compared. The following results are obtained:(1) The solving accuracy becomes much less sensitive to the pressure port configuration for the FADS system based on the modified classical triple algorithm than that based on the classical triple algorithm. Therefore, much more pressure configurations can be used to predict the flight parameters and the restrictive requirement of the pressure port configuration is not necessary.(2) The solving accuracy differences between these two different methods is small, and the pressure port configuration still need to be verified.
In view of the restrictive requirement of the pressure port configuration for the flush air data sensing(FADS) system based on the classical triple algorithm, a modified triple algorithm is developed and verified. Firstly, the classical triple algorithm and the modified triple algorithm are described. Secondly,the feasibility of the FADS system based on the modified triple algorithm including the pressure port configuration and the solving accuracy is evaluated. Finally, the advantages and the disadvantages of these two different methods are compared. The following results are obtained:(1) The solving accuracy becomes much less sensitive to the pressure port configuration for the FADS system based on the modified classical triple algorithm than that based on the classical triple algorithm. Therefore, much more pressure configurations can be used to predict the flight parameters and the restrictive requirement of the pressure port configuration is not necessary.(2) The solving accuracy differences between these two different methods is small, and the pressure port configuration still need to be verified.
引文
1 Ellsworth JC,Whitmore SA.Simulation of a flush air-data system for trans-atmospheric vehicles.Journal of Spacecraft and Rockets,2008,45(4):716-732
2 Siemers PM,Wolf H.Shuttle entry air data system(SEADS)-flight verification of an advanced air data system concept.AIAA 88-2104,2014
3 Larson T,Siemers PM.Use of nose cap and fuselage pressure orifices for determination of air data for Space Shuttle Orbiter below supersonic speeds.NASA TR-1643,1980
4 Whitmore SA,Cobleigh BR,Hearing EA.Design and calibration of the X-33 Flush Air Data Sensing(FADS)System.NASATM-206540,1998
5 Terry LJ,Timothym R,Paul SM III.Wind-tunnel investigation of a flush air data system at mach numbers from 0.7to 1.4.NASA TM-101697,1990
6 Larson TJ,Siemers PM.Subsonic tests of an all-flushpressure-orifice air data system.NASA TR-1871,1981
7 Cobleigh BR,Whitmore SA,Haering Jr EA,et al.Flush air data sensing(FADS)system calibration procedures and results for blunt forebodies.NASA TP-209012,1999
8 Davis MC,Pahle JW,White JT,et al.Development of a flush airdata sensing system on a sharp-nosed vehicle for flight at Mach 3 to 8.NASA TM-2000-209017,2000
9 Wolf H,Henry MW,Siemers PM.Shuttle Entry Air Data System(SEADS):optimization of preflight algorithms based on flight results.AIAA-1988-2053,1998
10 Bibb KL,Cassidy LD,Schwing AM.Orion EFT-1 FADSbased trajectory reconstruction.AIAA-2016-3254,2016
11 Millman D R.A modified triples algorithm for flush air data systems that allows a variety of pressure port configurations.AIAA-2017-4211,2017
12王鹏,金鑫,张卫民.钝头机体用嵌入式大气数据传感系统的解算精度研究.力学与实践,2016,38(3):255-261Wang Peng,Jin Xin,Zhang Weimin.Research on the solving accuracy for the FADS system applied to the vehicle with blunt fore-bodies.Mechanics in Engineering,2016,38(3):255-261(in Chinese)
13王鹏,金鑫,张卫民等.钝头机体用FADS系统的校准.实验流体力学,2016,30(2):97-102Wang Peng,Jin Xin,Zhang Weimin,et al.Calibration for the FADS system applied to the vehicle with blunt forebodies.Journal of Experiments in fluid mechanics,2016,30(2):97-102(in Chinese)
14王鹏,胡远思,金鑫.尖楔前体飞行器FADS系统驻点压力对神经网络算法精度的影响.宇航学报,2016,37(9):1072-1079Wang Peng,Hu Yuansi,Jin Xin.Effect of stagnation pressure on the neural network algorithm accuracy for FADSsystem applied to the vehicle with sharp wedged fore-bodies.Journal of Astronautics,2016,37(9):1072-1079(in Chinese)
2 Siemers PM,Wolf H.Shuttle entry air data system(SEADS)-flight verification of an advanced air data system concept.AIAA 88-2104,2014
3 Larson T,Siemers PM.Use of nose cap and fuselage pressure orifices for determination of air data for Space Shuttle Orbiter below supersonic speeds.NASA TR-1643,1980
4 Whitmore SA,Cobleigh BR,Hearing EA.Design and calibration of the X-33 Flush Air Data Sensing(FADS)System.NASATM-206540,1998
5 Terry LJ,Timothym R,Paul SM III.Wind-tunnel investigation of a flush air data system at mach numbers from 0.7to 1.4.NASA TM-101697,1990
6 Larson TJ,Siemers PM.Subsonic tests of an all-flushpressure-orifice air data system.NASA TR-1871,1981
7 Cobleigh BR,Whitmore SA,Haering Jr EA,et al.Flush air data sensing(FADS)system calibration procedures and results for blunt forebodies.NASA TP-209012,1999
8 Davis MC,Pahle JW,White JT,et al.Development of a flush airdata sensing system on a sharp-nosed vehicle for flight at Mach 3 to 8.NASA TM-2000-209017,2000
9 Wolf H,Henry MW,Siemers PM.Shuttle Entry Air Data System(SEADS):optimization of preflight algorithms based on flight results.AIAA-1988-2053,1998
10 Bibb KL,Cassidy LD,Schwing AM.Orion EFT-1 FADSbased trajectory reconstruction.AIAA-2016-3254,2016
11 Millman D R.A modified triples algorithm for flush air data systems that allows a variety of pressure port configurations.AIAA-2017-4211,2017
12王鹏,金鑫,张卫民.钝头机体用嵌入式大气数据传感系统的解算精度研究.力学与实践,2016,38(3):255-261Wang Peng,Jin Xin,Zhang Weimin.Research on the solving accuracy for the FADS system applied to the vehicle with blunt fore-bodies.Mechanics in Engineering,2016,38(3):255-261(in Chinese)
13王鹏,金鑫,张卫民等.钝头机体用FADS系统的校准.实验流体力学,2016,30(2):97-102Wang Peng,Jin Xin,Zhang Weimin,et al.Calibration for the FADS system applied to the vehicle with blunt forebodies.Journal of Experiments in fluid mechanics,2016,30(2):97-102(in Chinese)
14王鹏,胡远思,金鑫.尖楔前体飞行器FADS系统驻点压力对神经网络算法精度的影响.宇航学报,2016,37(9):1072-1079Wang Peng,Hu Yuansi,Jin Xin.Effect of stagnation pressure on the neural network algorithm accuracy for FADSsystem applied to the vehicle with sharp wedged fore-bodies.Journal of Astronautics,2016,37(9):1072-1079(in Chinese)