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弹箭与制导学报 >

2017 , Vol. 37 >Issue 5: 30 - 34

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2017.05.007

导弹与制导技术

变刚度电动负载力矩模拟系统的刚度解算

  • 冀哲 ,
  • 姚晓先 ,
  • 梁作宝
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  • 北京理工大学宇航学院,北京 100081

冀哲(1987-),男,河北石家庄人,博士研究生,研究方向:机电伺服系统与检测技术。

收稿日期: 2016-10-25

  网络出版日期: 2025-05-22

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The Stiffness Calculating of the Variable Stiffness Electric Loading Simulator

  • JI Zhe ,
  • YAO Xiaoxian ,
  • LIANG Zuobao
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  • School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China

Received date: 2016-10-25

  Online published: 2025-05-22

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摘要

针对导弹半实物仿真闭环试验中,需要解决实时对舵机加载的问题,文中提出了一种变刚度加载方式。通过实时调整扭杆弹簧的加载长度实现变刚度加载,并给出了适用于此加载系统的刚度解算方案。由对地面风洞实验数据解算及插值,得到任意飞行状态下的负载刚度及等效攻角,作为变刚度加载系统的输入参数。并以某型号舵机的风洞实验数据,通过该方法进行刚度解算,所得到的实际加载力矩与加载力矩指令较为接近,证明了该解算方案的合理性。

关键词： 变刚度加载; 加载力矩; 等效攻角; 负载刚度; 刚度解算

本文引用格式

冀哲 , 姚晓先 , 梁作宝 . 变刚度电动负载力矩模拟系统的刚度解算[J]. 弹箭与制导学报, 2017 , 37(5) : 30 -34 . DOI: 10.15892/j.cnki.djzdxb.2017.05.007

Abstract

This paper adopts the loading torque simulator with variable stiffness to test the performance of rudders in a missile's Hardware-in-the-Loop Simulation (HILS). The variable stiffness loading is achieved by adjusting the loading length of the torsion bar spring in real time, and a solving method for variable stiffness is given. Based on the experimental data obtained from the wind tunnel test through calculation and interpolation, the load stiffness and the equivalent angle of attack are obtained in any flying state as the input parameters of the variable stiffness loading system. With a certain type of rudder's wind tunnel test data, using this solving method to calculate stiffness, the obtained actual load torque and load torque command is approximate, thereby testing the feasibility of the proposed method.

Key words： variable stiffness load; load torque; equivalent angle of attack; load stiffness; stiffness calculation

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参考文献

[1]
LEONDES C T, PEARSON J L. Missile autopilot adaption using control-surface hinge-moment feedback[J]. Journal of Spacecraft and Rockets, 1968. 5 (2): 154- 459.
[2]
ANTONELLI M G, BUCCI G, CIANCETTA F, et al. Automatic test equipment for avionics Electro-Mechanical Actuators (EMAS)[J]. Measurement, 2014. 57: 71- 84.
[3]
YALLA S K, KAREEM A, KABAT S, et al. Dynamic load simulator: development of a prototype[J]. Journal of Engineering Mechanics, 2001, 127(12): 1310-1315.
[4]
SHANG Yaoxing, YUAN Hang, JIAO Zongxia, et al. Matching design of hydraulic load simulator with aerocraft actuator[J]. Chinese Journal of Aeronautics, 2013, 26 (2): 470-480.
[5]
NAM Yoonsu. QFT force loop design for the aerodynamic load simulator[J]. IEEE Transactions on Aerospace and Electronic Systems, 2001, 37(4): 1384-1392.
[6]
ULLAH N, KHATTAK M I, KHAN W. Fractional order fuzzy terminal sliding mode control of aerodynamics load simulator[C]//SAGE. Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering.[S. l.: s. n.], 2015.
[7]
WANG Xingjian, WANG Shaoping, WANG Xiaodong. Electrical load simulator based on velocity-loop compensation and improved fuzzy-PID[C]//IEEE. 2009 ISIE 2009 IEEE International Symposium on Industrial Electronics.[S.l.]: IEEE, 2009: 238-243.
[8]
WANG X, WANG S, YAO B. Adaptive robust torque control of electric load simulator with strong position coupling disturbance[J]. International Journal of Control, Automation and Systems, 2013, 11(2): 325-332.
[9]
ULLAH N, WANG S. Improved torque control of electrical load simulator with parameters and state estimation[J]. International Science Index, Electrical and Computer Engineerings, 2011, 5(2): 1647-1653.
[10]
姚晓先, 宋晓东, 梁作宝, 等. 闭环负载刚度变化装置: CN102122135A[P]. 2011-07-13.
[11]
钱杏芳, 林瑞雄, 赵亚男. 导弹飞行力学[M]. 北京: 北京理工大学出版社, 2011: 22-23.
[12]
SACHS H K. Criteria of design for progressive torsion-bar springs[J]. Experimental Mechanics, 1967, 7 (3): 105-109.
[13]
LIN W F, CLARKE M D. Factors influencing the accuracy of aerodynamic hinge-moment prediction: ADA 066 606[R].[S. l.: s. n.], 1978.
[14]
SCHROCDER M. Synthesis of low-peak-factor signals and binary sequences with low autocorrelation (Corresp.)[J]. IEEE Transactions on Information Theory, 1970, 16 (1): 85-89.
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