Evaluation of a Three Degree of Freedom Test Rig for Stability Derivative Estimation

A Gatto; MH Lowenberg

doi:10.2514/1.19821

Evaluation of a Three Degree of Freedom Test Rig for Stability Derivative Estimation

A Gatto, MH Lowenberg

Department of Aerospace Engineering

Research output: Contribution to journal › Article (Academic Journal) › peer-review

26 Citations (Scopus)

Abstract

This paper details a quantitative investigation into a cost-effective, three degree-of-freedom test rig to determine aircraft static and dynamic stability derivatives. The technique used a speciï¬�cally designed three degree-of-freedom gimbaled mechanism to connect an actively controlled model to a vertical support strut. The support strut was also mounted on a six-component piezoelectric balance to obtain aerodynamic force and moment data simultaneously with the model motion. With only minor modiï¬�cations to the overall setup, a comprehensive set of static and dynamic stability derivatives were obtained which showed reasonable to good agreement with other, independently obtained, data.

Translated title of the contribution	Evaluation of a Three Degree of Freedom Test Rig for Stability Derivative Estimation
Original language	English
Pages (from-to)	1747 - 1762
Number of pages	16
Journal	Journal of Aircraft
Volume	43 (6)
DOIs	https://doi.org/10.2514/1.19821
Publication status	Published - Nov 2006

Bibliographical note

Publisher: American Institute of Aeronautics and Astronautics

Access to Document

10.2514/1.19821

http://www.aiaa.org/content.cfm?pageid=406&gTable=jaPaper&gid=19821

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title = "Evaluation of a Three Degree of Freedom Test Rig for Stability Derivative Estimation",

abstract = "This paper details a quantitative investigation into a cost-effective, three degree-of-freedom test rig to determine aircraft static and dynamic stability derivatives. The technique used a speci{\"i}¬�cally designed three degree-of-freedom gimbaled mechanism to connect an actively controlled model to a vertical support strut. The support strut was also mounted on a six-component piezoelectric balance to obtain aerodynamic force and moment data simultaneously with the model motion. With only minor modi{\"i}¬�cations to the overall setup, a comprehensive set of static and dynamic stability derivatives were obtained which showed reasonable to good agreement with other, independently obtained, data.",

author = "A Gatto and MH Lowenberg",

note = "Publisher: American Institute of Aeronautics and Astronautics",

year = "2006",

month = nov,

doi = "10.2514/1.19821",

language = "English",

volume = "43 (6)",

pages = "1747 -- 1762",

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issn = "0021-8669",

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T1 - Evaluation of a Three Degree of Freedom Test Rig for Stability Derivative Estimation

AU - Gatto, A

AU - Lowenberg, MH

N1 - Publisher: American Institute of Aeronautics and Astronautics

PY - 2006/11

Y1 - 2006/11

N2 - This paper details a quantitative investigation into a cost-effective, three degree-of-freedom test rig to determine aircraft static and dynamic stability derivatives. The technique used a speciï¬�cally designed three degree-of-freedom gimbaled mechanism to connect an actively controlled model to a vertical support strut. The support strut was also mounted on a six-component piezoelectric balance to obtain aerodynamic force and moment data simultaneously with the model motion. With only minor modiï¬�cations to the overall setup, a comprehensive set of static and dynamic stability derivatives were obtained which showed reasonable to good agreement with other, independently obtained, data.

AB - This paper details a quantitative investigation into a cost-effective, three degree-of-freedom test rig to determine aircraft static and dynamic stability derivatives. The technique used a speciï¬�cally designed three degree-of-freedom gimbaled mechanism to connect an actively controlled model to a vertical support strut. The support strut was also mounted on a six-component piezoelectric balance to obtain aerodynamic force and moment data simultaneously with the model motion. With only minor modiï¬�cations to the overall setup, a comprehensive set of static and dynamic stability derivatives were obtained which showed reasonable to good agreement with other, independently obtained, data.

U2 - 10.2514/1.19821

DO - 10.2514/1.19821

M3 - Article (Academic Journal)

VL - 43 (6)

SP - 1747

EP - 1762

JO - Journal of Aircraft

JF - Journal of Aircraft

SN - 0021-8669

ER -