基于并联机构构型的新型CTS试验技术

董金刚; 魏忠武; 赵星宇; 谢峰; 秦永明; 马汉东

doi:10.7638/kqdlxxb-2019.0128

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基于并联机构构型的新型CTS试验技术

研究论文 | 更新时间：2026-05-28

- 基于并联机构构型的新型CTS试验技术
- A novel parallel mechanism-based CTS test technique for the wind tunnel
- 空气动力学学报 2020年38卷第5期页码：932-937
- 作者机构：
  
  中国航天空气动力技术研究院,北京,100074
- 作者简介：
  
  董金刚(1982-), 男, 河南周口市人, 高级工程师, 研究方向:实验流体力学.E-mail:djg0927@sina.com
- 基金信息：
  
  国家自然科学基金（11672283）
- DOI：10.7638/kqdlxxb-2019.0128
  中图分类号： V211.7
- 纸质出版：2020
- 稿件说明：
移动端阅览
董金刚, 魏忠武, 赵星宇, 谢峰, 秦永明, 马汉东. 基于并联机构构型的新型CTS试验技术[J]. 空气动力学学报, 2020, 38(5): 932-937.

DONG Jingang, WEI Zhongwu, ZHAO Xingyu, et al. A novel parallel mechanism-based CTS test technique for the wind tunnel[J]. 2020, 38(5): 932-937.
董金刚, 魏忠武, 赵星宇, 谢峰, 秦永明, 马汉东. 基于并联机构构型的新型CTS试验技术[J]. 空气动力学学报, 2020, 38(5): 932-937. DOI： 10.7638/kqdlxxb-2019.0128.

DONG Jingang, WEI Zhongwu, ZHAO Xingyu, et al. A novel parallel mechanism-based CTS test technique for the wind tunnel[J]. 2020, 38(5): 932-937. DOI： 10.7638/kqdlxxb-2019.0128.

摘要

捕获轨迹试验（CTS）技术是研究机弹分离安全性的有效手段，六自由度机构是CTS试验系统的核心组件。相比串联机构，并联六自由度机构具有定位精度高、机构刚度高以及承载能力强等优势。本文将并联机构应用到CTS风洞试验技术中，在风洞空间尺寸等条件约束下，对并联式六自由度机构构型以及结构参数进行设计，给出六自由度机构的位姿反解方程，评估了并联六自由度机构的运动空间，并对机构定位精准度进行了地面测试。CTS试验系统风洞试验验证结果表明：并联式CTS六自由度机构定位精准度高，CTS风洞试验数据重复性良好，试验系统运行稳定，不同马赫数下试验结果规律性良好。

Abstract

The capture trajectory test (CTS) technology is an effective method to study the safety of aircraft-to-machine separation. The six-degree-of-freedom mechanism is the core component of the CTS test system. Compared with a series mechanism

a parallel six-degree-of-freedom mechanism has the advantages of high positioning accuracy

high mechanism rigidity

and strong carrying capacity. In this paper

the parallel mechanism is applied to the CTS wind tunnel test technology. Under the constraints of the space size of the wind tunnel

the configuration and structural parameters of the parallel six-degree-of-freedom mechanism are designed. The motion space of the parallel 6-degree of freedom (DOF) mechanism is solved and evaluated

and ground testing of the positioning accuracy of the mechanism is conducted. The wind tunnel test verification of the CTS test system is performed. The results show that the parallel CTS 6-DOF mechanism has high positioning accuracy

and the wind tunnel test data have good repeatability. The test system operates stably

and the test results have good regularity under different Mach numbers.

关键词

Keywords

references

LI Z F. Special wind tunnel test technique[M]. Beijing:Aviation Industry Press, 2010:113-116. (in Chinese)

GARCON F, TARAVEL P, RAFFIN J C. Recent developments in captive trajectory systems of the ONERAModane wind tunnels[C ] //39th Aerospace Sciences Meeting and Exhibit, Reno, NV. Reston, Virginia: AIAA, 2001. doi: 10.2514/6.2001-579

ZILBERMAN M, SHAY M. The use of the Captive Trajectory system for computation of trajectories to the impact point[C ] //17th Aerospace Ground Testing Conference, Nashville, TN. Reston, Virginia: AIAA, 1992. doi: 10.2514/6.1992-4031

CARMAN J, HILL J B, D W, et al. Store separation testing techniques at the Arnold engineering development center. volume 2. description of captive trajectory store separation testing in the aerodynamic wind tunnel (4T)[R ] . Defense Technical Information Center, 1980. doi: 10.21236/ada087561

RAY E. Comparison of AEDC 4T and CALSPAN 8-ft wing tunnels for FA-18C/JDAM[R ] . Defense Technical Information Center, 2000. doi: 10.21236/ada376031

VEAZEY D, HOPF J. Comparison of aerodynamic data obtained in the Arnold Engineering Development Center wind tunnels 4T and 16T[C ] //20th AIAA Advanced Measurement and Ground Testing Technology Conference, Albuquerque, NM. Reston, Virginia: AIAA, 1998. doi: 10.2514/6.1998-2874

CENKO A, PHILLIPS K, M HOLMES I. Captive Trajectory System sting effects on store loads[C ] //32nd Aerospace Sciences Meeting and Exhibit, Reno, NV. Reston, Virginia: AIAA, 1994. doi: 10.2514/6.1994-195

CENKO A, PIRANIAN A, RAY E. Freestream data effects on trajectory predictions[C ] //AIAA Atmospheric Flight Mechanics Conference and Exhibit, Monterey, California. Reston, Virginia: AIAA, 2002. doi: 10.2514/6.2002-4417

YUZ S, WANG F X, LUO X F. Investigation of two special CTS test techniques[J]. Experiments and Measurements in Fluid Mechanics, 2004, 18(4):49-53.

HUANG X H, LUO X F, YU Z S. Design development of a new captive trajectory simulation system in FL-24 wind tunnel[J]. Acta Aerodynamica Sinica, 2008, 26(2):145-149.

HUANG X H, PANG X D, SONGBIN. Development of a new captive trajectory simulation system in the 1.2 m transonic wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2008, 22(2):95-98.

LI P, HUANG X H, ZHOU R, et al. Development of measurement and control system for CTS in 2 m×2 m supersonic wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2015, 29(4):95-100.

LOESER T, BERGMANN A. Development of the dynamic wind tunnel testing capabilities at DNW-NWB[C ] //41st Aerospace Sciences Meeting and Exhibit, Reno, Nevada. Reston, Virginia: AIAA, 2003. doi: 10.2514/6.2003-453

HVBNER A R. Experimental and numerical investigations of unsteady aerodynamic derivatives for transport aircraft configurations[C ] //45th AIAA Aerospace Sciences Meeting and Exhibit, Reno, Nevada. Reston, Virginia: AIAA, 2007. doi: 10.2514/6.2007-1076

LOESER T, BERGMANN A. Capabilities of deployment tests at DNW-NWB[M]. RTO-AVT-133, 2006: 13.

BERGMANN A, HUEBNER A, LOESER T. Experimental and numerical research on the aerodynamics of unsteady moving aircraft[J]. Progress in Aerospace Sciences, 2008, 44(2):121-137. doi:10.1016/j.paerosci.2007.10.006

XIE Z J, SUN X Y, SUN H S, et al.Mechanism design and dynamics analysis of high speed parallel robot for dynamic test in low speed wind tunnel[J]. Acta Aeronautica et Astronautica Sinica, 2013, 34(3):487-494.

GOU SS, JIAN K L. Kinematics analysis and simulation of a 6-DOF separation mechanism[J]. Journal of Chongqing University of Technology (Natural Science), 2017, 31(5):43-48.

CHEN X G. Analysis of the hexaglide parallel mechanism with double-end universal joints in kinematics chains[D]. Harbin: Harbin Institute of Technology, 2011: 30-36.

ZHANG X G, ZOU H W, CHEN W D.The Research of kinematic calibration method of parallel 6-DOF dock platform[J]. Journal of Astronautics, 2007, 28(2):273-277.

WANG H. Study on kinematic calibration of the 6-DOF parallel adjustment device[D]. Chengdu: University of Electronic Science and Technology of China, 2013.

YU D Y.Accuracy analysis and calibration of six-DOF motion simulator[D]. Harbin: Harbin Institute of Technology, 2006.

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