Academic Journal
Research on Automatic Attitude Control Technology of Six-Degree-of-Freedom Displacement Compensation for Full-Scale Aircraft Static Test.
| Τίτλος: | Research on Automatic Attitude Control Technology of Six-Degree-of-Freedom Displacement Compensation for Full-Scale Aircraft Static Test. |
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| Συγγραφείς: | Zheng, J., Jin, F., Wang, B., Mu, B., Liu, W. |
| Πηγή: | Experimental Techniques; Dec2025, Vol. 49 Issue 6, p1089-1106, 18p |
| Θεματικοί όροι: | Airplane testing, Posture, Deformations (Mechanics), Closed loop systems, Real-time computing, Automatic control systems, Hydraulic machinery |
| Περίληψη: | A novel closed-loop control principle was proposed for precisely controlling the attitude of full-scale aircraft during static test under large deformation. The test system was developed by integrating a displacement acquisition system, an industrial computer platform, a coordinated control system and hydraulic actuators. The displacement acquisition system was employed to facilitate the real-time sensing of the aircraft attitude changes. This was subsequently analyzed by computers to calculate attitude errors, based on which the compensation values were calculated for attitude correction. The correction was converted into voltage signals through an in-house program pre-integrated into the industrial computer platform. Finally, the MTS coordinated control system generates new control parameters based on the voltage signals, enabling a real-time adjustment on the movement of hydraulic actuators, which modifies the aircraft attitude. A device was developed for simulating the deformation characteristics of aircrafts under large deformation. A six-degree-of-freedom restraint system has been installed on the device according to the principle. Experiments were conducted to verify the capability of the approach for precisely controlling the aircraft attitude under various deformation states. Results showed that the aircraft attitudes were all restored to a value close to the theoretical attitude via displacement compensation scheme proposed, with the translational error less than ± 2 mm and the rotational error less than ± 0.02°. Whilst these errors were successfully reduced by applying the compensation algorithm during loading, they cannot be completely eliminated due to the influence of measurement and control errors. [ABSTRACT FROM AUTHOR] |
| Copyright of Experimental Techniques is the property of Springer Nature and its content may not be copied or emailed to multiple sites without the copyright holder's express written permission. Additionally, content may not be used with any artificial intelligence tools or machine learning technologies. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract. (Copyright applies to all Abstracts.) | |
| Βάση Δεδομένων: | Complementary Index |
| FullText | Links: – Type: other Text: Availability: 0 CustomLinks: – Url: https://dx.doi.org/doi:10.1007/s40799-025-00800-w Name: EDS - Springer Nature Journals (s7799221) Category: fullText Text: View record at Springer |
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| Items | – Name: Title Label: Title Group: Ti Data: Research on Automatic Attitude Control Technology of Six-Degree-of-Freedom Displacement Compensation for Full-Scale Aircraft Static Test. – Name: Author Label: Authors Group: Au Data: <searchLink fieldCode="AR" term="%22Zheng%2C+J%2E%22">Zheng, J.</searchLink><br /><searchLink fieldCode="AR" term="%22Jin%2C+F%2E%22">Jin, F.</searchLink><br /><searchLink fieldCode="AR" term="%22Wang%2C+B%2E%22">Wang, B.</searchLink><br /><searchLink fieldCode="AR" term="%22Mu%2C+B%2E%22">Mu, B.</searchLink><br /><searchLink fieldCode="AR" term="%22Liu%2C+W%2E%22">Liu, W.</searchLink> – Name: TitleSource Label: Source Group: Src Data: Experimental Techniques; Dec2025, Vol. 49 Issue 6, p1089-1106, 18p – Name: Subject Label: Subject Terms Group: Su Data: <searchLink fieldCode="DE" term="%22Airplane+testing%22">Airplane testing</searchLink><br /><searchLink fieldCode="DE" term="%22Posture%22">Posture</searchLink><br /><searchLink fieldCode="DE" term="%22Deformations+%28Mechanics%29%22">Deformations (Mechanics)</searchLink><br /><searchLink fieldCode="DE" term="%22Closed+loop+systems%22">Closed loop systems</searchLink><br /><searchLink fieldCode="DE" term="%22Real-time+computing%22">Real-time computing</searchLink><br /><searchLink fieldCode="DE" term="%22Automatic+control+systems%22">Automatic control systems</searchLink><br /><searchLink fieldCode="DE" term="%22Hydraulic+machinery%22">Hydraulic machinery</searchLink> – Name: Abstract Label: Abstract Group: Ab Data: A novel closed-loop control principle was proposed for precisely controlling the attitude of full-scale aircraft during static test under large deformation. The test system was developed by integrating a displacement acquisition system, an industrial computer platform, a coordinated control system and hydraulic actuators. The displacement acquisition system was employed to facilitate the real-time sensing of the aircraft attitude changes. This was subsequently analyzed by computers to calculate attitude errors, based on which the compensation values were calculated for attitude correction. The correction was converted into voltage signals through an in-house program pre-integrated into the industrial computer platform. Finally, the MTS coordinated control system generates new control parameters based on the voltage signals, enabling a real-time adjustment on the movement of hydraulic actuators, which modifies the aircraft attitude. A device was developed for simulating the deformation characteristics of aircrafts under large deformation. A six-degree-of-freedom restraint system has been installed on the device according to the principle. Experiments were conducted to verify the capability of the approach for precisely controlling the aircraft attitude under various deformation states. Results showed that the aircraft attitudes were all restored to a value close to the theoretical attitude via displacement compensation scheme proposed, with the translational error less than ± 2 mm and the rotational error less than ± 0.02°. Whilst these errors were successfully reduced by applying the compensation algorithm during loading, they cannot be completely eliminated due to the influence of measurement and control errors. [ABSTRACT FROM AUTHOR] – Name: Abstract Label: Group: Ab Data: <i>Copyright of Experimental Techniques is the property of Springer Nature and its content may not be copied or emailed to multiple sites without the copyright holder's express written permission. Additionally, content may not be used with any artificial intelligence tools or machine learning technologies. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract.</i> (Copyright applies to all Abstracts.) |
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| RecordInfo | BibRecord: BibEntity: Identifiers: – Type: doi Value: 10.1007/s40799-025-00800-w Languages: – Code: eng Text: English PhysicalDescription: Pagination: PageCount: 18 StartPage: 1089 Subjects: – SubjectFull: Airplane testing Type: general – SubjectFull: Posture Type: general – SubjectFull: Deformations (Mechanics) Type: general – SubjectFull: Closed loop systems Type: general – SubjectFull: Real-time computing Type: general – SubjectFull: Automatic control systems Type: general – SubjectFull: Hydraulic machinery Type: general Titles: – TitleFull: Research on Automatic Attitude Control Technology of Six-Degree-of-Freedom Displacement Compensation for Full-Scale Aircraft Static Test. Type: main BibRelationships: HasContributorRelationships: – PersonEntity: Name: NameFull: Zheng, J. – PersonEntity: Name: NameFull: Jin, F. – PersonEntity: Name: NameFull: Wang, B. – PersonEntity: Name: NameFull: Mu, B. – PersonEntity: Name: NameFull: Liu, W. IsPartOfRelationships: – BibEntity: Dates: – D: 01 M: 12 Text: Dec2025 Type: published Y: 2025 Identifiers: – Type: issn-print Value: 07328818 Numbering: – Type: volume Value: 49 – Type: issue Value: 6 Titles: – TitleFull: Experimental Techniques Type: main |
| ResultId | 1 |