Journal ArticleDOI
Comparative assessment of modified deconvolution and neuro-fuzzy technique for force prediction using an accelerometer balance system
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TLDR
A comparison of two force prediction techniques which are used in dynamic calibration has been studied and it has been observed that both modified deconvolution and ANFIS can be used for force prediction without intensive calculations, however the accuracy of ANF IS is slightly higher than that of modified deconVolution.About:
This article is published in Measurement.The article was published on 2021-02-01. It has received 3 citations till now. The article focuses on the topics: Deconvolution & Adaptive neuro fuzzy inference system.read more
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Transfer learning: A new aerodynamic force identification network based on adaptive EMD and soft thresholding in hypersonic wind tunnel
TL;DR: Li et al. as discussed by the authors designed residual attention block with soft threshold and dense block with adaptive EMD in TLN-AE&ST model, which can more effectively suppress the influence of instrument noise signal on model training effect.
References
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Journal ArticleDOI
Drag balance for hypervelocity impulse facilities
S. R. Sanderson,J. M. Simmons +1 more
TL;DR: In this paper, a finite element representation and spectral methods are used to obtain a mean square optimal estimate of the time history of the aerodynamic loading, and the effectiveness of the balance is demonstrated by measuring the drag on a cone with 15-deg semivertex angle in nominally Mach 5.6 flow.
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Dynamic calibration of force balances for impulse hypersonic facilities
TL;DR: In this article, deconvolution is used to infer aerodynamic forces on models in impulse hypersonic wind tunnels along with the theory behind the different calibration techniques applied to a single component stress-wave force balance.
Journal ArticleDOI
An accelerometer balance system for measurement of aerodynamic force coefficients over blunt bodies in a hypersonic shock tunnel
TL;DR: A miniature three-component accelerometer balance system for measuring the fundamental aerodynamic force coefficients over blunt bodies has been designed, fabricated and tested in the Indian Institute of Science hypersonic shock tunnel HST2 at a nominal Mach number of 5.75 as mentioned in this paper.
Journal ArticleDOI
Design and analysis of a flat accelerometer-based force balance system for shock tunnel testing
TL;DR: In this article, an accelerometer-based thin balance system for measuring aerodynamic forces on typical flight configurations in impulse facilities is described. But the model and the balance system are supported by rubber bushes, which leads to minimally restrained free cooling conditions of the model in the test section during the test duration.
Journal ArticleDOI
Dynamic force balances for short-duration hypersonic testing facilities
TL;DR: In this paper, two force balance techniques for use in hypersonic impulse facilities are compared by measuring the drag force on a 30D semi-apex-angle blunt cone model in a Hypersonic shock tunnel at a free stream Mach number of 5.75.