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Multiple-input, multiple-output modal testing of a Hawk T1A aircraft: A new full-scale dataset for structural health monitoring

James Wilson, Max D. Champneys, Matt Tipuric, Robin Mills, David J. Wagg, Timothy J. Rogers

TL;DR

This work addresses the shortage of realistic, full-scale benchmark data for vibration-based SHM by delivering a complete MIMO modal testing dataset on a decommissioned Hawk T1A. The authors conduct a five-phase, multi-site testing campaign with over 200 test conditions, 140 sensors, and pseudo-damage and actual panel-removal scenarios to capture linear and nonlinear dynamics. The dataset is distributed in HFDF5 format, partitioned into per-test units and complemented by a Python interface that handles downloads and metadata, enabling broad accessibility and reproducibility. The work highlights practical challenges in large-scale SHM, such as data management, nonlinear effects, and the integration of strain sensing, and positions the dataset as a bridge between laboratory models and in-service structural health monitoring.

Abstract

The use of measured vibration data from structures has a long history of enabling the development of methods for inference and monitoring. In particular, applications based on system identification and structural health monitoring have risen to prominence over recent decades and promise significant benefits when implemented in practice. However, significant challenges remain in the development of these methods. The introduction of realistic, full-scale datasets will be an important contribution to overcoming these challenges. This paper presents a new benchmark dataset capturing the dynamic response of a decommissioned BAE Systems Hawk T1A. The dataset reflects the behaviour of a complex structure with a history of service that can still be tested in controlled laboratory conditions, using a variety of known loading and damage simulation conditions. As such, it provides a key stepping stone between simple laboratory test structures and in-service structures. In this paper, the Hawk structure is described in detail, alongside a comprehensive summary of the experimental work undertaken. Following this, key descriptive highlights of the dataset are presented, before a discussion of the research challenges that the data present. Using the dataset, non-linearity in the structure is demonstrated, as well as the sensitivity of the structure to damage of different types. The dataset is highly applicable to many academic enquiries and additional analysis techniques which will enable further advancement of vibration-based engineering techniques.

Multiple-input, multiple-output modal testing of a Hawk T1A aircraft: A new full-scale dataset for structural health monitoring

TL;DR

This work addresses the shortage of realistic, full-scale benchmark data for vibration-based SHM by delivering a complete MIMO modal testing dataset on a decommissioned Hawk T1A. The authors conduct a five-phase, multi-site testing campaign with over 200 test conditions, 140 sensors, and pseudo-damage and actual panel-removal scenarios to capture linear and nonlinear dynamics. The dataset is distributed in HFDF5 format, partitioned into per-test units and complemented by a Python interface that handles downloads and metadata, enabling broad accessibility and reproducibility. The work highlights practical challenges in large-scale SHM, such as data management, nonlinear effects, and the integration of strain sensing, and positions the dataset as a bridge between laboratory models and in-service structural health monitoring.

Abstract

The use of measured vibration data from structures has a long history of enabling the development of methods for inference and monitoring. In particular, applications based on system identification and structural health monitoring have risen to prominence over recent decades and promise significant benefits when implemented in practice. However, significant challenges remain in the development of these methods. The introduction of realistic, full-scale datasets will be an important contribution to overcoming these challenges. This paper presents a new benchmark dataset capturing the dynamic response of a decommissioned BAE Systems Hawk T1A. The dataset reflects the behaviour of a complex structure with a history of service that can still be tested in controlled laboratory conditions, using a variety of known loading and damage simulation conditions. As such, it provides a key stepping stone between simple laboratory test structures and in-service structures. In this paper, the Hawk structure is described in detail, alongside a comprehensive summary of the experimental work undertaken. Following this, key descriptive highlights of the dataset are presented, before a discussion of the research challenges that the data present. Using the dataset, non-linearity in the structure is demonstrated, as well as the sensitivity of the structure to damage of different types. The dataset is highly applicable to many academic enquiries and additional analysis techniques which will enable further advancement of vibration-based engineering techniques.
Paper Structure (12 sections, 2 equations, 13 figures, 3 tables)

This paper contains 12 sections, 2 equations, 13 figures, 3 tables.

Table of Contents

  1. Introduction
  2. Structure
  3. Experimental work
  4. Setup and hardware
  5. Testing regime
  6. Acquisition and control
  7. Dataset
  8. Dataset challenges
  9. Large datasets
  10. stid
  11. shm
  12. Conclusions

Figures (13)

  • Figure 1: The Hawk at the lvv.
  • Figure 2: The port wing of the Hawk during instrumentation.
  • Figure 3: Summary sensor placement sketch for the Hawk, showing the locations of the nearside (), farside () and triaxial () accelerometers on the main chassis. Also shown are the locations of the datums (SW, SS, PS, and PW) relative to the global datum, A. The substructures highlighted in magenta are detailed in Figures \ref{['fig:schematic_swing']}-\ref{['fig:schematic_rudder']}. The diagram is not shown to scale -- for precise locations, refer to the data set data:Wil:2024.
  • Figure 4: Schematic diagram for the starboard wing, showing the location of the accelerometers (), fbg (), shakers (), and pseudo-damage (). Not to scale.
  • Figure 5: Schematic diagram for the port wing, showing the location of the accelerometers (), fbg (), shakers (), pseudo-damage (), and removed panels (). Not to scale.
  • ...and 8 more figures