Structure health inspection for aging transport aircraft

Jiang, Wei; Chang, Ray C.; Zhang, Shuqin; Zang, Shixin

doi:10.1108/aeat-02-2022-0046

Cited by 4 publications

(4 citation statements)

References 21 publications

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“…Database developments include data manipulation, compatibility check, input information of aircraft main geometry and moment of inertia data, equations of motion and unsteady thrust model. In references of Chang et al (2022), Jiang et al (2023) have detail descriptions of data manipulation, compatibility check, equations of motion and unsteady thrust model.…”

Section: Numerical Methods Developmentmentioning

confidence: 99%

Severity assessment of sudden plunging motion for jet transport aircraft in response to severe atmospheric turbulence

Jiang,

Chang,

Yang

et al. 2023

AEAT

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Purpose The purpose of this paper is to present a comparative study of flight circumstances, dynamic stability characteristics and controllability for two transport aircraft in severe atmospheric turbulence at transonic cruise flight for the purpose to obtain the prevention concepts of injuries to passengers and crew members for pilot training in International Air Transport Association (IATA) – Loss of Control In-flight (LOC-I) program. Design/methodology/approach A twin-jet and a four-jet transport aircraft encountering severe atmospheric turbulence are the study cases for this paper. The nonlinear unsteady aerodynamic models are established through flight data mining and the fuzzy-logic modeling technique based on the flight data of flight data recorder. This method can be adopted to examine the influence of horizontal wind shear and crosswind on loss of control, dynamic stability characteristics and controllability for transport aircraft in different weights and different sizes in tracking aviation safety of existing different types of aircraft. Findings The horizontal wind shear or crosswind before the turbulence encounter will easily induce rolling motion and then initiate the sudden plunging motion during the turbulence encounter. The roll rate will increase the oscillatory rolling motion during plunging motion, if the rolling damping is insufficient. The drop-off altitude will be enlarged by the oscillatory rolling motion during the sudden plunging motion. Research limitations/implications A lack of the measurement data of vertical wind speed sensor on board to verify the estimated values of damping term is one of the research limitations for this study. The fact or condition of being severe in sudden plunging motion can be judged through the analysis of oscillatory derivatives with both dynamic stability and damping terms. Practical implications The roll rate will increase the oscillatory rolling motion during plunging motion, if the rolling damping is insufficient. The drop-off altitude will be enlarged by the oscillatory rolling motion during the sudden plunging motion. The horizontal wind shear or crosswind before the turbulence encounter will easily induce rolling motion and then initiated the sudden plunging motion during the turbulence encounter. If the drift angle is large, to turn off the autopilot of yaw control first and stabilize the rudder by the pedal. When passing through the atmosphere turbulence area, the pilots do not need to amend the heading angle urgently. Social implications The flight safety prevention in avoidance of injuries for passengers and cabin crews is essential for the airlines. The horizontal wind shear or crosswind before the turbulence encounter will easily induce rolling motion and then initiated the sudden plunging motion during the turbulence encounter. Originality/value The flight safety prevention in avoidance of injuries for passengers and cabin crews is essential. The present assessment method is an innovation to examine the loss of control problems of aviation safety and promote the understanding of aerodynamic responses of the jet transport aircraft. It is expected to provide a valuable lecture for the international training courses for IATA – LOC-I program after this paper is being published.

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Section: Numerical Methods Developmentmentioning

confidence: 99%

Severity assessment of sudden plunging motion for jet transport aircraft in response to severe atmospheric turbulence

Jiang,

Chang,

Yang

et al. 2023

AEAT

Self Cite

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“…The flowchart for development is presented in Figure 1. In references of Chang et al (2022aChang et al ( , 2022b and Jiang et al (2023) have detail descriptions of data manipulation, compatibility check, equations of motion and unsteady thrust model.…”

Section: Aerodynamic Database Developmentmentioning

confidence: 99%

“…It has six applications of model-based derivative analysis for transport aircraft in the current state of the art. The published papers in recent five years with the applications in accident investigation (Lan and Chang, 2018), structure health inspection (Wang et al, 2021 andJiang et al, 2023), fuel saving analysis (Chang et al, 2022a(Chang et al, , 2022b and flight operations (Chang et al, 2022a(Chang et al, , 2022b.…”

Section: Introductionmentioning

confidence: 99%

Optimization of flight conditions based on performance sensitivity analysis for jet transport aircraft

Jiang,

Guo,

Zhu

et al. 2024

AEAT

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Purpose This study aims to enhance the fuel efficiency of jet transport aircraft based on mathematical models and flight crew operating manual (FCOM) for the purpose to assist the civil aviation industry in improving flight safety and operational efficiency. Design/methodology/approach The research applies flight data mining and fuzzy logic modeling technologies to set up lift-to-drag ratio (L/D) models and nine models of thrust, Mach number, engine pressure ratio and fuel flow rate to estimate the deviation of each flight parameter. All performance deviations are calculated based on the values of flight data recorded in the quick access recorder and FCOM at the observed flight conditions. The L/D model can obtain the influence of each flight parameter and estimate the insufficient amount of each parameter by averaging it with the least square method. In the estimation of optimal altitude, nine models are built based on data from FCOM to estimate the optimal altitude and complete comparative analysis of the airspeed, Mach number and fuel flow rate at the optimal altitude. Findings Analyze 11 relevant parameters from the sensitivity derivative of L/D model to obtain how each parameter affected fuel consumption and explore the causes of additional fuel consumption. Complete the estimation of the optimal cruise altitude of the aircraft, and calculate the comparative analysis of the altitude, speed, Mach number and other parameters with the sensitivity derivative of the L/D. The estimation of the optimal cruise altitude of the aircraft can meet the analysis of the sensitivity derivative. Research limitations/implications This study is to enhance the fuel efficiency of jet commercial transport based on mathematical model and FCOM. FCOM is required to conduct this study. The estimation of the optimal cruise altitude through the nine models of the aircraft could meet the analysis of the sensitivity derivative. Practical implications The object of present research is to demonstrate the effectiveness of optimization of flight conditions through model analysis to get knowledge of the effects of each influencing flight variable to L/D for future flight operations’ reference. Social implications The model-based derivative analysis had the ability to perform derivative prediction analysis on any input parameters, more flight parameters could be optimized in future research to help airlines improve flight safety and operational efficiency. Originality/value The present enhancement method of fuel efficiency is an innovation to examine the abnormal aircraft performance and its flight operations, thereby to explore the causes of additional fuel consumption. The present method can become an auxiliary tool for flight operations quality assurance to improve fuel efficiency for the airlines.

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“…However, as with other metallic materials, Ti-alloy airframes are prone to cracking under the extreme loading spectrum during their years of service life [3]. The crack damage in Ti-alloy structures is a critical problem to be solved for the structural integrity and performance recovery in the maintenance of aged aircrafts [4]. The adhesively bonded repair of cracked Ti-alloy structures with a composite patch, an important means of repair, has many advantages over traditional methods such as minimal additional weight, alleviated stress concentration around cracks, and efficient load transfer without inducing new stress defects [5].…”

Section: Introductionmentioning

confidence: 99%

Comparison of Repair Methods for Cracked Titanium Alloy Aircraft Structures with Single-Sided Adhesively Bonded Composite Patches

Hu,

Li,

Fang

et al. 2023

Materials

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Composite patches are widely accepted as a useful practice for the repair of cracked aircraft components and the repair method is of vital importance to the final performance of the repaired structures. The present research experimentally studied the repair efficiency and processing stability of pre-cured, prepreg (including unidirectional and plain weave prepregs) and wet-layup methods for use on cracked Ti-alloy panels through the configuration of a butt joint bonded with a one-sided composite patch. The efficiency and stability of these repair methods were elaborately evaluated and compared via the load bearing behavior, the microstructure of the bonding interface, and the structural failure morphology through two batches of testing specimens. Typical patterns were found in load-displacement curves where the initial damage and ultimate bearing load points divided them into elastic-linear, damage propagation and complete fracture phases. Although the co-cure process of both unidirectional prepreg and wet-layup methods can form a jigsaw-like demarcation interface between the adhesive layer and the composite patch to achieve a good bonding force and a high recovery of loading performance, the latter presents porous patches with a high coefficient of variation in load-carrying capacity. Conversely, the pre-cured laminate and the plain weave prepreg patches failed to restore the mechanical properties owing to the weak bonding interface and the low axial patch strength, respectively. The unidirectional prepreg patch was proven to be the optimal repair method for the cracked metallic structures when balancing repair efficiency and processing stability.

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Structure health inspection for aging transport aircraft

Cited by 4 publications

References 21 publications

Severity assessment of sudden plunging motion for jet transport aircraft in response to severe atmospheric turbulence

Severity assessment of sudden plunging motion for jet transport aircraft in response to severe atmospheric turbulence

Optimization of flight conditions based on performance sensitivity analysis for jet transport aircraft

Comparison of Repair Methods for Cracked Titanium Alloy Aircraft Structures with Single-Sided Adhesively Bonded Composite Patches

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