|Table of Contents|

Six-component Force Balance for Big Expansion Ratio Nozzle Test-bed

《南京理工大学学报》(自然科学版)[ISSN:1005-9830/CN:32-1397/N]

Issue:
2011年04期
Page:
547-551
Research Field:
Publishing date:

Info

Title:
Six-component Force Balance for Big Expansion Ratio Nozzle Test-bed
Author(s):
YAO Yu1WU Hong-tao2
1. College of Aerospace Engineering; 2. College of Mechanical and Electronic Engineering, Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China
Keywords:
big expansion ratios nozzle test-beds six-component balances static calibration finite element method
PACS:
V211. 752
DOI:
-
Abstract:
To study the dynamic performance of a big expansion ratio nozzle with asymmetric structure, a nd measure the six-component dynamic force accurately for the thrust vectoring,a novel integrated six-component force balance is introduced in the paper based on S-bend deformation of Tbeams. By analyzing the measuring microstrain and the assembled structure of the test-bed, the balance is designed and fabricated. The static calibration is employed to obtain the matrix of working coefficients for the balance and the finite element method is included to demonstrate the presented design method. Research result shows that the presented balance has a simple structure and high precision and accuracy,which can meet the demands of a six-component force measurement for the big expansion ratio nozzle test-beds.

References:

[1] Wilson J W, Johnson W O,Sottosanti P C. Dual flex— A low horsepower flexible seal nozzle[J]. Journal of Spacecraft and Rockets, 1972,9 ( 8) : 567-568.
[2] Chu C W,Der J J,Ortiz V M,et al. Effect of swirl on the potential core in two-dimensional ejector nozzle [J]. Journal of Aircraft, 1983, 20( 2) : 191-192.
[3] Deere K A,Flamm J D,Berrier B L,et al. Computational study of an axisymmetric dual throat fluidic thrust vectoring nozzle for a supersonic aircraft application [A]. 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference[C]. Reston,USA: American Institute of Aeronautics and Astronautics Inc, 2007: 918-940.
[4] Liu J S,Parks G T,Clarkson P J. Shape optimisation of axisymmetric cylindrical nozzles in spherical pressure vessels subject to stress constraints[J]. International Journal of Pressure Vessels and Piping, 2001, 78: 1-9.
[5] 张强,杨永,李喜乐. 双喉道射流推力矢量喷管的数 值模拟研究[J]. 西北工业大学学报,2009,26( 6) : 754-759.
[6] 金捷,赵景芸,张明恒,等. 轴对称矢量喷管内流特 性的模型试验[J]. 推进技术,2005,26 ( 2 ) : 144 -146.
[7] 付尧明,王强,额日其太,等. 矢量喷管六分量测力 试验台的研制[J]. 实验流体力学与测量,2002, 11( 1) : 87-93.
[8] 杨恩霞,刁彦飞,庞永刚. 多分量矢量喷管试验台的 开发设计和研究[J]. 哈尔滨工业大学学报,2001, 22( 4) : 84-86.
[9] Ramaswamy M A,Alvi F S,Krothapalli A. Special 6- component jet rig balance for studying new thrust vectoring concepts[A]. International Congress on Instrumentation in Aerospace Simulation Facilities [C]. Pacific Grove,CA,USA: IEEE Press, 1997: 202-213.
[10] 贺德馨. 风洞天平[M]. 北京: 国防工业出版社, 2001: 328-365.

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Last Update: 2012-10-23