scholarly journals Comparative Analysis of the Selection of Lay-Up Stacking of Polymer Composite Load-Bearing Elements for the Tail Section of Fuselage Structure of the Light Aircraft

2021 ◽  
Vol 346 ◽  
pp. 03111
Author(s):  
Tun Lin Htet ◽  
P.V. Prosuntsov
Keyword(s):  
Composite Material ◽  
Comparative Analysis ◽  
Composite Materials ◽  
Design Optimization ◽  
Polymer Composite ◽  
Optimization Method ◽  
Load Bearing ◽  
Rear Part ◽  
Continuous Range ◽  
Selection Of

The problem of the selecting the optimal lay-up stacking of polymer composite materials for the load-bearing elements of the rear part of fuselage structure is considered. The comparison of two approaches to the design of the load-bearing elements is carried out. The first of them is the use of multilayered composite material for the load-bearing elements, the stacking angles of which is selected from a given discrete set, and the second is the use of composite material with a continuous range of variables in fabric lay-up angles. As a result design optimization, it is shown that using an optimization method with a continuous range of lay-angles allows reducing the weight of the load-bearing elements by 12.79%

scholarly journals Mechanical Properties of GFR & Graphite Epoxy Polymer Composites

2020 ◽  
Vol 5 (6) ◽  
pp. 560-565
Author(s):  
A. Aakash ◽  
S. Selvaraj
Keyword(s):  
Mechanical Properties ◽  
Composite Material ◽  
Composite Materials ◽  
Polymer Composite ◽  
Epoxy Polymer ◽  
Significant Degree ◽  
Polymer Composite Material ◽  
Water Ingestion ◽  
Selection Of

Composite materials have the great potential and widely used as building material in numerous applications. Polymer composite material obtains the necessary properties in a controlled significant degree by the selection of strands and lattice. The properties of the materials have been selected by choosing the correct proportion of matrix and reinforcements. To build the quality of the material by expanding the fiber substance of the material. In this current examination, the mechanical properties of the glass fiber and graphite is strengthened with epoxy polymer composite were considered. Here the open embellishment method was received for the manufacture of the polymer composite The mechanical properties, for example, rigidity, compression quality, sway quality and water ingestion test was resolved according to the ASTM norms. The mechanical properties were improved as the filaments support content expanded in the grid material.

Design Optimization of Shape and Layup Sequence of Polymer Composite Load Bearing Elements of Light Aircraft

2021 ◽  
pp. 97-107
Author(s):  
Lin Htet Tun ◽  
P.V. Prosuntsov
Keyword(s):  
Composite Material ◽  
Polymer Composite ◽  
Parametric Optimization ◽  
Minimum Weight ◽  
Optimization Method ◽  
Polymer Composite Material ◽  
Topological Optimization ◽  
Load Bearing ◽  
Structural Layout ◽  
Topology Optimization Method

The paper presents the methodology for designing the load bearing elements of tail section of a light aircraft through the sequential application of methods of parametric and topological optimization. First, we analyzed the loads acting on the aircraft at its maneuvering in the vertical and horizontal planes. Then, for these loads, by the parametric optimization method, we selected the locations of ribs of the tail section of the aircraft, which were subsequently used to develop individual forms of ribs based on the topology optimization method. Next, we carried out parametric optimization of layup angles of polymer composite material, intended for the production of ribs. Finally, we developed a structural layout for the load bearing elements of the fuselage, which meets the criteria of minimum weight when restrictions are imposed on the level of stresses in some layers of the composite material.

scholarly journals DETERMINATION OF DEFORMATION IN MESH COMPOSITE STRUCTURE UNDER THE ACTION OF COMPRESSIVE LOADS

2020 ◽  
Vol 17 (35) ◽  
pp. 599-608 ◽  
Author(s):  
Alexander A. OREKHOV ◽  
Yuri A. UTKIN ◽  
Polina F. PRONINA
Keyword(s):  
Composite Material ◽  
Carbon Fiber ◽  
Bearing Capacity ◽  
Polymer Composite ◽  
Experimental Studies ◽  
Polymer Composite Material ◽  
Lightweight Mesh ◽  
Carbon Filler ◽  
Selection Of

One of the significant innovative technologies is the creation of large-sized structures that work for a long time in space and meet stringent restrictions on overall mass characteristics. Among these structures, in the first place, is the section of bearing truss (BT). This article presents the results of experimental studies of sectors of load-bearing trusses of mesh design for compression. Recently, composite mesh cylindrical shells are used as spacecraft housings. The mesh shell is a supporting structure to which the instruments and mechanisms of the spacecraft are attached. The truss section is made of cross-linked polymer composite material with carbon fibers. The objective of the tests is to confirm the possibility of creating a lightweight mesh construction using a carbon fiber reinforced polymer composite material. To achieve this goal, the authors were assigned the following tasks: selection of carbon filler of polymer composite materials (PCM); selection of PCM binder; determination of the degree of carbon fiber reinforcement; choice of the number and orientation paths of spiral ribs, number of ring ribs and the sizes of individual ribs. As a result of the research, the calculated indicators for ensuring the bearing capacity and stiffness under the application of axial compressive load were obtained. At the same time, with the determination of bearing capacity, the deformation characteristics of the structure were twice determined in order to confirm their repeatability, as well as linear nature of the dependence of axial and radial deformations as a result of the applied load.

scholarly journals CONCEPTUAL DESIGN OF THE WING OR FUSELAGE STRUCTURE OF A MAINLINE AIRCRAFT MADE OF METAL-POLYMER COMPOSITE MATERIALS

2021 ◽  
pp. 74-82
Author(s):  
Valery Pechenyuk ◽  
◽  
Yuri Popov ◽  
Keyword(s):  
Composite Material ◽  
Composite Materials ◽  
Polymer Composite ◽  
Polymer Composite Material ◽  
Polymer Composite Materials ◽  
Design Stage ◽  
Aluminum Sheets ◽  
Preliminary Design Stage ◽  
Modified Formula ◽  
Metal Polymer

The analysis of existing aircraft structures made of metal-polymer composite materials is carried out, and a list of them with passport characteristics is compiled. The Fokker F-27 Friendship, Boeing-777 and Airbus A380, which use ARALL and GLARE materials, were selected as the aircraft under study. Formulas are determined and the distribution of normal force flows between metal and composite elements in the composition of MPCM based on aluminum sheets (aluminum-fiberglass – SIAL- 1-1, SIAL-3-1 and SIAL-1441 (9/8)) and titanium alloys (samples of titanium-carbon fiber from the patent-Example 1 and Example 3). To determine these parameters, the formulas used for a composite structure made of different materials are used. On the basis of the specification known MPCM the modified formula mixture rule for calculating the strength of new materials with a given set of orientation angles of PCM and the presence of layers of sheet metal, a comparison with standard mechanical characteristics and to show the efficiency of these formulas. Using these formulas, you can determine the strength characteristics for an arbitrary composition of the MPCM package. The features of the choice of design permissible stresses for the design of the airframe of a mainline aircraft made of metal-polymer composite material are highlighted. The concept of designing aircraft airframe elements using MPCM is considered. The results of this work will allow us to determine the rational components of the metal-polymer composite material and the structure of their distribution in the airframe design at the preliminary design stage.

Development of Forming Method of Deployable Boom from Thermoplastic Polymer Composite

2021 ◽  
Vol 887 ◽  
pp. 105-109
Author(s):  
A.M. Iuvshin ◽  
Y.S. Andreev ◽  
S.D. Tretyakov
Keyword(s):  
Composite Material ◽  
Composite Materials ◽  
Polymer Composite ◽  
Manufacturing Process ◽  
Polymer Composite Material ◽  
Polymer Composite Materials ◽  
Thermoplastic Polymer ◽  
Labour Intensity ◽  
Thermoset Polymer ◽  
Length Limitation

This paper studies deployable elements which are used in satellites and different terrestrial antenna devices. Many deployable elements are made from steel or thermoset polymer composite materials and have the following disadvantages like length limitation of deployable elements, labour intensity of manufacturing process of deployable elements etc. For this purpose a deployable tube boom element was chosen and a forming method for manufacturing deployable tube element from thermoplastic polymer composite material was developed.

Tailoring Composite Materials Through Optimal Selection of Their Constituents

1992 ◽  
Vol 114 (3) ◽  
pp. 451-458 ◽  
Author(s):  
H. M. Karandikar ◽  
F. Mistree
Keyword(s):  
Composite Material ◽  
Composite Materials ◽  
Multiobjective Optimization ◽  
Material Selection ◽  
The Other ◽  
Economic Factors ◽  
Optimal Selection ◽  
Structural Applications ◽  
Design Requirements ◽  
Selection Of

The use of composite materials has provided designers with increased opportunities for tailoring structures and materials to meet load requirements and changing and demanding environments. This has led to their increased use in structural applications. As with traditional materials the selection of an appropriate material for a design is important. In case of design using composite materials the selection of a material consists of selecting a fiber-resin combination which meets all design requirements. This involves choosing the fiber, the resin, and the proportion of these two constituents in the composite material. The phrase “material selection” refers to the problem of laminate selection. This corresponds to the task of choosing a fiber and resin combination based on technical and economic factors. Materials tailoring, on the other hand, involves manipulating the composition of the composite material to achieve desired properties and it is the selection of a fiber and resin simultaneously but separately. In this paper we present, through an example, a multiobjective optimization-based method for assisting a designer in tailoring composite materials for specific technical and economic objectives.

Molecular Mechanics of Organic Composite Materials: A Case Study of Cellulose-Adhesive System

2014 ◽  
Vol 1662 ◽  
Author(s):  
Lik-ho Tam ◽  
Denvid Lau
Keyword(s):  
Composite Material ◽  
Composite Materials ◽  
Interfacial Adhesion ◽  
Phenol Formaldehyde ◽  
Cellulose Fiber ◽  
Cellulose Fibers ◽  
Adhesive System ◽  
Dynamics Simulation ◽  
Load Bearing ◽  
Material Systems

ABSTRACTOrganic composite materials can be readily found in our daily life, such as plywood used in construction industry and bamboo composites as indoor and outdoor flooring materials. These organic composite material systems consist of cellulose fibers bonded with each other through adhesives, leading to a bonded system with a gradient structure that possesses a unique structural behavior which has a great potential to be used as load-bearing building materials. In view of the manufacturing process of such composite material systems and the structure in-between the cellulose fibers and the adhesives, the interfacial adhesion of such systems at multiscale would play a major role in determining their capability in load-bearing structural applications. In this research work, the interface between cellulose fiber and phenol-formaldehyde adhesive is chosen as a representative of the organic composite material system and molecular dynamics simulation is used for quantifying their mechanical properties and the corresponding interfacial adhesion. Here we demonstrate that cellulose fiber has a strong affinity to a phenol-formaldehyde adhesive with an adhesion energy of 151.3 mJ/m2. To the best of our knowledge, this is the first study that reports this material property for cellulose-adhesive system, which is three times larger than that between the gecko foot’s hair and the mineral surface. The mechanism of such strong adhesion is due to the possible hydrogen bonding between the cellulose and the adhesive.

Local Repair of Parts from Polymer Composite Material with the Use of Portable Hot Bonder Control Systems

2020 ◽  
Vol 992 ◽  
pp. 347-352
Author(s):  
V.V. Bazheryanu ◽  
I.V. Zaychenko ◽  
E.P. Zharikova
Keyword(s):  
Composite Materials ◽  
Control Systems ◽  
Polymer Composite ◽  
Local Heating ◽  
Polymer Composite Material ◽  
Heating Element ◽  
Polymer Composite Materials ◽  
Local Repair ◽  
Production Area ◽  
Selection Of

The object of research is the repair processes of parts made of polymer composite materials using a local heating element. The goal is the development of technology, the selection of equipment for repair of parts and assemblies from polymer composite materials using a local heating element and a vacuum source outside the production area, as part of the aircraft. In the process of performing the work, an analysis and review of the existing equipment for local repair of parts from polymer composite materials was carried out. Equipment for local repair of own and imported production was tested. Based on the results of testing and market analysis, equipment was selected that meets the requirements of ND for the manufacture of parts from polymer composite materials. A technical process for repairing parts using a local heating element and a device for hot gluing has been developed.

Sign in / Sign up

Export Citation Format

Share Document