scholarly journals Use of a composite repair patches to repair the upper air intake flap for the MiG-29 aircraft engine

2017 ◽  
Vol 40 (2) ◽  
pp. 101-127
Author(s):  
Michał Sałaciński ◽  
Michał Stefaniuk ◽  
Piotr Synaszko ◽  
Janusz Lisiecki
Keyword(s):  
Epoxy Composite ◽  
Aircraft Engine ◽  
Aircraft Structure ◽  
Composite Repair ◽  
Comparative Tests ◽  
Composite Patch ◽  
Bonded Repair ◽  
Air Intake ◽  
Welding Joints ◽  
Cost Efficient

AbstractThe Composite Patch Bonded Repair (CPBR) is one of the most cost-efficient types of aircraft structure repair. In the CPBR, the damaged structure is reinforced by applying a composite patch. The boron-epoxy composite (BFRP) is a popular choice for these types of repair. The BFRP was utilized to repair the cracked resistance welding joints in the upper flap of the MiG-29’s RD-33 engine intake. In the present paper, the numerical results are shown, along with the comparative tests of the undamaged inlet flap, the damaged inlet flap and of the CPBR repaired inlet flap.

scholarly journals ON EFFICIENCY OF SOME METHODS FOR DETERMINING THE AZIMUTHAL STRUCTURE OF NOISE IN CYLINDRICAL DUCT

Akustika ◽  
2019 ◽  
Vol 32 ◽  
pp. 130-134
Author(s):  
Vadim Palchikovskiy ◽  
Yuliy Bersenev ◽  
Ivan Korin
Keyword(s):  
Least Squares ◽  
Dynamic Range ◽  
Least Squares Method ◽  
Microphone Array ◽  
Aircraft Engine ◽  
Circular Array ◽  
Noise Measurements ◽  
Air Intake ◽  
Experimental Values ◽  
Cylindrical Duct

The determination of azimuthal sound modes propagating in a cylindrical duct is considered based on the results of noise measurements on experimental setup with a duct diameter of 1.8 m, which corresponds to the air intake of aircraft engine. The experiments were carried out in PNRPU anechoic chamber. Spinning modes were generated by a circular array of 40 acoustic drivers. Noise in duct was recorded with circular array of 100 microphones with optimized arrangement to reach maximum dynamic range. The following methods for determining the azimuthal structure of noise were compared: modal decomposition method, cross-correlation with a reference channel method; least-squares method. The mathematical foundations and specifics of these methods are briefly outlined. According to the results of the azimuthal structure extraction, it was found that the least-squares method provides the best agreement between the generated and extracted modes and the distribution of the computed and experimental values of acoustic pressures on microphone array.

Bonded boron-epoxy composite repair and reinforcement of cracked aluminium structures

1996 ◽  
Vol 34 (3) ◽  
pp. 339-347 ◽  
Author(s):  
T.E. Tay ◽  
F.S. Chau ◽  
C.J. Er
Keyword(s):  
Epoxy Composite ◽  
Composite Repair

Aircraft Engine Integration for the M88-RAFALE Couple

1992 ◽  
Author(s):  
Philippe Ramette ◽  
Jean Christophe Corde
Keyword(s):  
Air Force ◽  
Mechanical Behaviour ◽  
Aircraft Engine ◽  
Short Description ◽  
Weapon System ◽  
High Complexity ◽  
Key Factor ◽  
Air Intake

As all other comparable programs, the couple RAFALE-M88 has to be a fully optimized multirole weapon system with the highest level of integration; a key factor for that purpose is the very good prebuilt integration of the engine within the aircraft. After a short description of the main historical milestones of the aircraft and engine programs development and integration, the paper will first summarize the rigourous procedures which are used by aircraft and engine manufacturers, official services and future Air Force and Navy users. Then, the paper will detail the main points where aircraft engine integration as to be lead precisely and carefully; these points are: -at first, the electronical links which are establised between the aircraft and the engine, due to the high complexity of flight softwares who have to work and talk with each others; -secondly, the aerodynamical subjects, including air intake and exhaust nozzle installation; -thirdly, the mechanical integration (geometry, mechanical behaviour, …); -then all kinds of fluid circuits or equiments.

Experimental Research on the Mechanical Behavior of the Cracked Aluminum Plate Bonded by the Graphite/Epoxy Composite Patch

2013 ◽  
Vol 744 ◽  
pp. 432-435
Author(s):  
Yi Shan Zhang ◽  
Zun Wang ◽  
Zhi Wang
Keyword(s):  
Fatigue Strength ◽  
Mechanical Behavior ◽  
Experimental Research ◽  
Epoxy Composite ◽  
Aluminum Plate ◽  
Composite Patch

The effect of the graphite/epoxy composite patch parameters on the static and fatigue strength of the cracked aluminum plate was investigated experimentally. A series of specimens repaired by six types of composite patches including four different patch lengths and two different patch thicknesses were tested on the material tester. Specimens single-sided repaired and double-sided repaired by the same composite patches were also tested. The experiment results show that composite patches can provide an improvement in static and fatigue strength of the cracked aluminum plate, double-sided repair is more effective than single-sided repair, if the thickness and the length were selected properly, the composite patches can significantly enhance the strength of the repaired specimens.

Disbond effects on bonded boron/epoxy composite repair to aluminium plates

2008 ◽  
Vol 42 (2) ◽  
pp. 220-227 ◽  
Author(s):  
B. Bachir Bouiadjra ◽  
D. Ouinas ◽  
B. Serier ◽  
N. Benderdouche
Keyword(s):  
Epoxy Composite ◽  
Composite Repair

Performance assessment and optimization of hybrid composite patch repair of aircraft structure

2020 ◽  
Vol 16 (5) ◽  
pp. 887-913
Author(s):  
Alpesh H. Makwana ◽  
A.A. Shaikh
Keyword(s):  
Glass Fiber ◽  
Hybrid Composite ◽  
Volume Fraction ◽  
Patch Repair ◽  
Design Parameters ◽  
Aircraft Structure ◽  
Content Type ◽  
Composite Patch ◽  
Peel Stress ◽  
Selection Of

PurposeIn this article, a novel hybrid composite patch consisting of unidirectional carbon fiber and glass fiber is considered for repair of the aircraft structure. The purpose of this paper is to assess the performance of hybrid composite patch repair of cracked structure and propose an optimized solution to a designer for selection of the appropriate level of a parameter to ensure effective repair solution.Design/methodology/approachElastic properties of the hybrid composites are estimated by micromechanical modeling. Performance of hybrid composite patch repair is evaluated by numerical analysis of stress intensity factor (SIF), shear stress, and peel stress. Design of experiment is used to determine responses for a different combination of design parameters. The second-order mathematical model is suggested for SIF and peel stress. Adequacy of the model is checked by ANOVA and used as a fitness function. Multiobjective optimization is carried out with a genetic algorithm to arrive at the optimal solution.FindingsThe hybrid composite patch has maintained equilibrium between the SIF reduction and rise of the peel stress. The repair efficiency and repair durability can be ensured by selection of an optimum value of volume fraction of glass fiber, applied stress, and adhesive thickness.Originality/valueThe composite patch with varying stiffness is realized by hybridization with different volume fraction of fibers. Analysis and identification of optimum parameter to reduce the SIF and peel stress for hybrid composite patch repair are presented in this article.

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