Effect of Inspection Strategies on the Weight and Lifecycle Cost of Airplanes

Pattabhiraman, Sriram; Haftka, Raphael T.; Kim, Nam Hoon

doi:10.2514/6.2011-1763

Cited by 5 publications

(6 citation statements)

References 16 publications

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“…The values used for C Total in Figure 9B led to an estimated cost of £1440 per kg added. Although this value is close to similar estimations in the literature ( [25,26]), changes in the operation of the aircraft will affect the balance between C OTC and W AW . Using the Wired-Manual case as a benchmark, the years in operation required to compensate for the increased C OTC with the reduction in W AW are plotted in Figure 11.…”

Section: Discussionsupporting

confidence: 89%

“…Of paramount importance for the integration of a SHM system is the total added weight to the structure as it can influence the operational costs. Based on estimations of fuel consumption increase, the cost of weight (CoW) over the lifecycle of an aircraft is reported in the literature between 1500 − 2000 $/kg [25,26]. Even in the scenario of a 10% fuselage mass increase due to the integration of SHM, it is estimated in [20] that integrating a SHM system is still beneficial.…”

Section: Introductionmentioning

confidence: 99%

“…The structural weight savings can offset the SHM added weight and lead to an estimated 1.8% fuel reduction. Sizing reduction was also considered in [26], where fuselage weight savings up to 15% are reported; however, the SHM added weight was not considered. In [24], on the other hand, it was argued that for existing aircraft, the added weight on the structure might have to be compensated by an equivalent reduction in the maximum allowable payload (i.e., fewer passenger seats for a commercial airliner).…”

Section: Introductionmentioning

confidence: 99%

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Structural Health Monitoring Cost Estimation of a Piezosensorized Aircraft Fuselage

Giannakeas

Khodaei

2022

Sensors

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Guided waves-based SHM systems are of interest in the aeronautic sector due to their lightweight, long interrogation distances, and low power consumption. In this study, a bottom-up framework for the estimation of the initial investment cost (COTC) and the added weight (WAW) associated with the integration of a SHM system to an aircraft is presented. The framework provides a detailed breakdown of the activities and their costs for the sensorization of a structure using a fully wired approach or the adoption of the printed diagnostic film. Additionally, the framework considers the difference between configuring the system for Manual or Remote data acquisition. Based on the case study presented on the sensorization of a regional aircraft composite fuselage, there is a trade-off between COTC and WAW for the SHM options considered. The Wired–Manual case leads to the lowest COTC with the highest WAW, while the combination of diagnostic film with a Remote system leads to the highest COTC and the lowest WAW. These estimations capture the characteristics of each system and can be integrated into cost–benefit analyses for the final selection of a particular configuration.

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Section: Discussionsupporting

confidence: 89%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Structural Health Monitoring Cost Estimation of a Piezosensorized Aircraft Fuselage

Giannakeas

Khodaei

2022

Sensors

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“…Unfortunately, this issue has been either ignored or inappropriately estimated. For example, the cost due to the extra weight of the SHM system was calculated based on extra fuel cost [57]. Indeed, weight change directly leads to the change in fuel consumption and many airlines benefit from it.…”

Section: Added Cost Due To Shm Systemsmentioning

confidence: 99%

Cost-Effectiveness of Structural Health Monitoring in Fuselage Maintenance of the Civil Aviation Industry †

Dong

Kim

2018

Aerospace

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Abstract:Although structural health monitoring (SHM) technologies using sensors have dramatically been developed recently, their capability should be evaluated from the perspective of the maintenance industry. As a first step toward utilizing sensors, the objective of the paper is to investigate the possibility of using sensors for inspecting the entire fuselage during C-check. First, we reviewed various sensors for their detection range, detectable damage size, and installed weight, which revealed that the piezoelectric wafer active sensor (PWAS) is the most promising sensor for aircraft SHM. Second, we performed a case study of inspecting the fuselage of Boeing-737NG using PWAS. To maintain the same detecting capability of manual inspection in C-check, we estimated the total number of sensors required. It turned out that utilizing sensors can reduce the maintenance downtime and thus, maintenance cost. However, even with a very conservative estimate, the lifetime cost was significantly increased due to the weight of sensor systems. The cost due to the weight increase was an order of magnitude higher than the cost saved by using SHM. We found that a large number of sensors were required to detect damage at unknown locations, which was the main cause of the weight increase. We concluded that to make SHM cost-effective, it would be necessary either to improve the current sensor technologies so that a less number of sensors are used or to modify the aircraft design concept for SHM.

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“…These challenges can be traced back to the geometrical complexity of aircraft structures, plethora of damage scenarios in composites, cost-benefit limitations, and the wide range of the aircraft environmental and operational conditions (EOC). 6–8…”

Section: Introductionmentioning

confidence: 99%

An up-scaling temperature compensation framework for guided wave–based structural health monitoring in large composite structures

Giannakeas

Khodaei

Aliabadi

2022

Structural Health Monitoring

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Variations in environmental conditions can significantly impair the accuracy and reliability of guided wave structural health monitoring systems. Acquisition of baseline signals over a wide temperature range for the purposes of damage detection and localization is impractical for large composite structures. A novel framework for compensating the effect of temperature at a post-processing stage is presented in this paper to allow updating the compensation factors using observations obtained at different scales. The proposed methodology utilizes observations collected at the lower scales, where a large amount of data under controlled environment is available. Subsequently, the estimated compensation factors are propagated to the higher scales as priors within a Bayesian framework. This way, the measurements required from the high levels are reduced while making it possible to also update the estimated factors during the operation of the structure. The performance of the methodology is evaluated at different scales and compared with the direct use of compensation factors obtained from coupon studies only. It is demonstrated that the proposed methodology improves the fidelity of the compensation algorithm leading to a reduction in the uncertainty of the temperature-compensated signals. Based on the findings of the present study, the reduction in the uncertainty of the compensation improves the performance of both damage detection as well as damage localization in a large composite panel.

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Effect of Inspection Strategies on the Weight and Lifecycle Cost of Airplanes

Cited by 5 publications

References 16 publications

Structural Health Monitoring Cost Estimation of a Piezosensorized Aircraft Fuselage

Structural Health Monitoring Cost Estimation of a Piezosensorized Aircraft Fuselage

Cost-Effectiveness of Structural Health Monitoring in Fuselage Maintenance of the Civil Aviation Industry †

An up-scaling temperature compensation framework for guided wave–based structural health monitoring in large composite structures

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