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Defense and Security Studies  Original Research 
Vol. 3, January 2022, pp.106-112 
https://doi.org/10.37868/dss.v3.id211 

This work is licensed under a Creative Commons Attribution License (https://creativecommons.org/licenses/by/4.0/) that allows others 
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 106 

 
 
Laminar Composite Materials for Unmanned Aircraft Wings 
 
Mala Utami1*, Jonathan Ernest Sirait2, Beny Budhi Septyanto3, Aries Sudiarso4, I Nengah Putra 
Apriyanto5 
1,2,3 Faculty of Defense Technology, Indonesian Defense University, Indonesia 
 
 

*Corresponding author E-mail: mala.utami@tp.idu.ac.id

Received Nov. 15, 2022 
Revised Dec. 2, 2022 
Accepted Dec. 21, 2022 

Abstract 

Unmanned Aerial Vehicles (UAVs) have high popularity, especially in the 
military field, but are now also being applied to the private and public sectors. 
One of the UAV components that require high material technology is the wing. 
The latest material technology developed as a material for unmanned aircraft 
wings is a composite material that has high strength and lightweight. This 
research aims to identify composite materials that can be used for unmanned 
aircraft wing structures. The method used in this research is a qualitative method 
with a literature study approach. The results of this theoretical study show that 
some of the latest composite materials that have been developed into materials for 
unmanned aircraft wings are Laminar Composites with a sandwich structure. 
Laminar and sandwich composites consist of various constituent materials such as 
Balsa wood fiber-glass and polyester resin, microparticles, Carbon Fibre 
Reinforced Polymer, polymer matrix composites reinforced with continuous 
fibers, Polymer matrix composites, E-glass/Epoxy, Kevlar/Epoxy, Carbon/Epoxy, 
woven fabrics, acrylonitrile butadiene styrenecarbon (ABS) laminated with 
carbon fiber reinforced polymer (CFRP) and uniaxial prepreg fabrics. Laminar 
and sandwich composite materials are a reference for developing unmanned 
aircraft wing structures that have resistant strength and lightweight.   

© The Author 2022. 
Published by ARDA. 

Keywords: UAV Wings, Composite Materials, Laminar Composites, Sandwich 
Composites 

1. Introduction  

An unmanned aerial vehicle (UAV) can be defined as a type of aircraft that is not controlled by a pilot, but 
uses aerodynamic forces with a lift so that it can fly autonomously or be remotely controlled, can be recovered 
or disposed of, and can carry payloads that can be tailored to the desired task and operation [1]. UAVs are 
increasing in use for both civilian and military use and are preferred because they are more cost-effective and 
more versatile. So in the last few decades UAVs have become very popular due to their versatility [6]. 

Currently, Unmanned Aerial Vehicles (UAVs), or in Indonesia known as unmanned aircraft (Drones) have 
high popularity so the development of good materials at a low price becomes a goal. Not only that but 
designing UAVs also requires engineers to design and produce on a large scale with limited time [3]. The 
development of UAVs in the aviation industry is to find materials or materials that have high speed. The 
advancement of UAVs is highly dependent on innovations in various technologies such as control systems, 
computer technology, and communication integration. Innovations in manufacturing techniques and materials 
are also important to develop and improve UAVs’performances by producing durable and lightweight 



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structures. This can be achieved by applying innovative composite materials with high strength, ballistic and 
rigid properties. Advanced composite materials are made of fibrous materials embedded in a resin matrix, 
generally laminated with fibers oriented in alternating directions to form the strength and stiffness of the 
combined material [3]. 

Wing development for unmanned aerial vehicles (UAVs) is a multi-stage work such as airfoil selection, 
geometric calculation, structural design, material selection, numerical analysis, and manufacturing. The main 
objective in wing development is to design a structure characterized by high strength and low weight. The 
wing should have a high strength ratio and be supported by lightweight. There will be loads and moments 
acting on the wing so to overcome the stress due to these loads the wing must have high strength. The weight 
or weight of the wing must be low because the heavyweight will reduce unwanted efficiency in the engine [3]. 

With the development of material technology, it is easy to access and purchase composite materials. With the 
advancement of composite manufacturing technology, to make even complex shaped parts can be made easily 
in a few days. The use of UAV composite materials is different from that of general aviation vehicles, where 
most of the structures are made of aluminum and titanium in addition to carbon fiber composites. Whereas 
almost all UAV structures are made of carbon fiber composites [2], it becomes possible to manufacture a 
UAV in a laboratory or workshop for 4 or 5 people in a few weeks.  

In addition, maintenance and repair of UAVs can also be done quickly and easily because they are assembled 
from small, cheap, and easy-to-manufacture composite components. Composite materials offer an excellent 
strength-to-weight ratio with greater manufacturability of complex parts, unique contours, and special 
features, especially in aircraft applications. One of the basic aircraft components of concern in the application 
of composite material structures is the wing profile [6].   

 

Figure 1. Comparison of stiffness and strength with a weight between composite materials [4] 



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In the selection of composite materials for UAVs that have high criteria, it means that the selected material 
must have resistant strength and be lightweight. For example, polymer matrix composites reinforced with 
continuous fibers are a good choice. These materials are characterized by Young's Modulus values twice as 
high as those of aluminum alloys and twice as lightweight [5]. The difficulty of using composite materials lies 
in the structure, the use of composite materials requires knowledge of material constants and mechanical 
properties. Correctly defining the characteristics of the composite material will guarantee that the material can 
be a good structure and have the desired reliability of results. The use of composites in aircraft is increasing 
day by day, especially in military aircraft. Composite materials have the advantages of high strength and 
lightweight which are very well applied to complex parts, unique contours, and special features, especially as 
aircraft materials. One aircraft component that is very suitable for using composite materials is the wing 
profile. Therefore, this paper raises the issue of the use of composite materials in unmanned aerial vehicles 
(UAVs), especially on the wings. This paper is a theoretical study that aims to increase the knowledge of 
authors and readers in material engineering technology and its application in the military. 

2. Research method  

This research uses a qualitative method with a literature review approach. The discussion or analysis is carried 
out based on the works of research results related to the topic and the results of thoughts that have been 
produced by researchers and practitioners. The literature review is one of the techniques that can be used in 
research. A literature review has its own difficulties when compared to other research techniques. As it 
requires a high understanding of the researchers in conducting a study of a problem to be solved related to the 
theory to be used, and the model or method to be carried out. The stages in this literature review research are 
as follows. 

a. Finding and determining relevant literature, this activity requires high focus and shrewdness in finding 
data sources, especially secondary data. Journals, articles, and books are the main sources in this research, the 
more sources used, the better the results obtained. 

b. Conducting literature screening, at this second stage, the researcher must be able to filter the selection 
of sources that have been obtained to be used in problem-solving. Of the many sources obtained, they are 
evaluated to adjust to the objectives of the research to be achieved.  

c. Strengthening the topic with the sources that have been obtained, at this stage, this is the level of 
difficulty in the literature review because it must be able to strengthen existing theories with sources and 
discuss gaps in the form of advantages or disadvantages of each source.  

d. Conclude based on the outcome of the discussion so as to reach a solution to the problem raised. 

3. Results and discussion 

The definition of composite material is a material consisting of two or more phases with significantly different 
properties (physical and chemical). Combined together to form a new material with different characteristics 
from its components. The resulting composite material properties are beneficial properties that cannot be 
achieved with one phase/component alone.  And what is unique is that each component remains separate in 
the finished structure [3]. One of the most common examples of composites is fiber-reinforced composite 
materials that consist of high-strength and modulus fibers in a matrix material. Reinforced steel bars 
embedded in concrete provide an example of fiber-reinforced composites. In a composite, the function of the 
fiber is to carry the load exerted on the composite structure and provide stiffness, strength, thermal stability, 
and other structural properties. While the matrix material serves as a component that binds the fibers together, 
transfers fiber loads, and provides protection to reinforce the fibers against chemical attack, mechanical 
damage, and other environmental effects such as moisture and others [6]. 

The composite industry has grown rapidly with the advent of better plastic resins and good reinforcing fibers. 
As DuPont developed the aramid fiber known as Kevlar, it has become a standard in armor due to its high 
ductility. In addition, carbon fibers were also developed so since this time composites have become a 



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substitute for metals as a new material.  At present, of course, the composite industry continues and is still 
growing, its growth as a metal replacement material as an aircraft material, especially in unmanned aircraft 
[7].  Composites have unique advantages over other monolithic materials such as high strength properties, 
high stiffness, durable life, low density, and adaptability to the structure being created. In addition, recent 
composite materials are exploring improvements such as corrosion resistance, wear resistance, appearance, 
temperature-dependent properties, thermal stability, thermal insulation, thermal conductivity, and acoustic 
insulation. The basis that makes composite materials have superior structural performance lies in the high 
specific strength (strength to density ratio) and high specific stiffness (modulus to density ratio) and the 
anisotropic and heterogeneous character of the material. The anisotropic and heterogeneous character also 
provides the freedom to design structures with optimal configurations to obtain certain functions [8].   

Composite materials can be classified into several types, namely [9]: 

a. First classification, based on matrix constituents. Organic Matrix Composites (OMCs), Metal Matrix 
Composites (MMCs), and Ceramic Matrix Composites (CMCs). The term organic matrix composites are 
generally assumed to cover two classes of composites, namely Polymer Matrix Composites (PMCs) and 
carbon matrix composites commonly referred to as carbon-carbon composites. 

b. The second classification refers to reinforcement. Fiber reinforced composites, laminar composites, 
and Particulate Composites. 

c. Fiber Reinforced Composites, are composites in which fibers as reinforcement are embedded in the 
matrix material. These composites are called discontinuous fiber composites or short fiber composites with 
properties that vary depending on the length of the fiber. 

d. Laminar Composites, composites consisting of material held together by a matrix. Sandwich 
structures fall under this category. 

e. Particulate Composites, composites consisting of particles distributed or embedded in the matrix 
body. The particles are in the form of flakes or powders. Article board, concrete, and wood are examples. 

In its application as a leading material in UAVs, especially wings, ceramic materials used are various as 
described above.  

Based on research conducted by Lamaini et al., [10] the sandwich structure made consists of Balsa wood, 
fiberglass, polyester resin, and microparticles used to close the pores of the Balsa wood surface. The results of 
the mechanical properties analysis of the UAV wing structure can be seen in that the sandwich structure can 
be used in UAV applications. The developed UAV wing weighs 800 grams, 20 mm camber thickness with a 
length of 20 mm and a span of 70 mm. Tensile, compressive, and flexural tests have been carried out on the 
sandwich structure. The results of the average tensile and compressive properties of the composite can 
compete with existing composite materials. The lay-up method can cost production and can also be used in 
large-scale production.  So it can be concluded that Balsa wood-based sandwich composites can be used as 
UAV wing structures. 

All main components in the aircraft are made of CFRP (Carbon Fibre Reinforced Polymer) composite 
material consisting of woven and uniaxial prepreg fabrics. Uniaxial prepreg fabrics aim to ensure volume 
consistency and will provide a smooth overlap. A low-cost manufacturing process can be achieved by 
reducing the number of parts and a fabrication process that does not require costly autoclaving. The 
characteristics obtained from the test results of the UAV wing structure with composite materials are the 
shaker-table approach to simulate the wing on the UAV. The shaker-table method produces a signal of greater 
magnitude with less noise when compared to data obtained from a full aircraft configuration [11]. 

Table 1 shows previous research on material utilization for UAV wings, with authors, titles, methods and type 
of composite materials given. 



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Table 1. Previous research on material utilization for UAV wings 

Author (year) Title Methods Composite Material 

Lamani, Shivaji., Stanvil 
Dsouza, Dane Hubert 
Saldanha, Granvil 
Dsouza and Madhurima 
R Londhe. (2020) [10] 

Analysis, Fabrication and 
Testing of a Sandwich 
Composite for an UAV 
Wing 

Hand lay-up 
technique 

Sandwich Composite (fiber-
glass and polyester resin and 
microparticles) 

J. Simsiriwong & R. 
Warsi Sullivan. (2012) 
[11] 

Experimental Vibration 
Analysis of a Composite 
UAV Wing 

The form of woven 
and uniaxial 
prepreg fabrics 

Carbon-fiber reinforced 
polymer (CFRP) composite 

Basri, E. I., Sultan, M. 
T. H., M., F., Basri, A. 
A., Abas, M. F., Majid, 
M. S. A., Ahmad, K. A. 
(2019) [12] 

Performance analysis of 
composite ply orientation 
in aeronautical application 
of unmanned aerial 
vehicle (UAV) 
NACA4415 wing 

Ply combinations 
Carbon Fiber Reinforced 
Polymer (CFRP) laminated 
composite 

Grodzki, W., & 
Łukaszewicz, A. (2015) 
[3] 

Design and manufacture 
of unmanned aerial 
vehicles (UAV) wing 
structure using composite 
materials. 

- 

Polymer matrix composites 
reinforced with continues 
fibers, 
Polymer matrix composites 
(Laminates and sandwich 
structures) 

Tah’ir Turgut (2007) [6] 

Manufacturing And 
Structural Analysis Of a 
Lightweight Sandwich 
Composite UAV Wing 

Vacuum Bagging 
Method with curing 
at room temperature

Laminated composite and 
sandwich structure (E-
glass/Epoxy, Kevlar/Epoxy, 
Carbon/Epoxy) 

Sasi Kirono (2015) [13] 
Mechanical Properties of 
Unmanned Aircraft 
Composite Materials 

A comparison of 
the mechanical 
properties of 
composite materials 
is carried out by 
tensile strength 
testing. 

Front Fuselage Components 
Upper skin with three layers 
of carbon fiber, honeycomb, 
and glass fiber 
 

Vasić, Zoran, Stevan 
Maksimović, and 
Dragutin Georgijević 
(2018) [15] 

Applied Integrated Design 
in Composite UAV 
Development 

Pyrolysis of an 
organic precursor 
such as rayon or 
Poly-acrylonitrile, 
or petroleum pitch 

Graphite fibers, glass, carbon 
and graphite, Kevlar, boron 
and Carbon fibers 

 



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According to research conducted by Basri et al., [12], the ACP (ANSYS Composite Preppost) module is used 
to apply composite materials with various thicknesses and angles. Which is applied to wing skins, spars, and 
ribs. Laminate Composite is prepared according to the Classical Laminate Theory (CLT) to investigate the 
behavior of composite sandwich structures subjected to internal influences from applied loads. In ANSYS, the 
model of a wing structure is interpreted in the form of shell elements (lamina). The effect of ply orientation on 
the NACA 4415 UAV wing composite laminate was evaluated. Analytical predictions show that the stress 
state developed in the variation of fiber orientation with ply-angle has a significant influence on the strength. 
Finite element analysis studies show the total displacement values obtained are within the acceptable range.  

Unmanned aerial vehicle (UAV) wings according to their purpose vary in airfoil shape, thickness, chord 
dimension, span, surface area, and geometry. Despite the differences, the design concept is similar to all types 
of structures. Due to the high requirements of modern UAV (high-strength-low-weight) composite materials, 
especially polymer matrix composites reinforced with continuous fibers are the most appropriate choice. To 
transfer such loads, composite structures have been designed. The first proposed structure is a laminated 
composite consisting of glass cloth (outer) and unidirectional carbon cloth (inner) reinforced with balsa wood 
ribs for proper shape. The construction made is a type of sandwich structure, since the upper and lower layers 
of fabric are separated with balsa wood ribs. The second analysis structure is characterized by an additional 
foam core separating the glass-carbon fabric layers. 

Numerical analysis of composite structures based on the same boundary conditions showed that the sandwich 
structure is characterized by the deflection of the foam core layer under the load of 11.34 mm - 3 times 
smaller than the carbon fiber laminate deflecting 32.16 mm considering the same weight. Lightweight 
composite structures based on carbon, glass fibers produced by the vacuum bag technique minimize the 
creation of voids (bubbles and wrinkles) and allow to obtain of high fiber content which translates into higher 
strength of the created structures [3]. According to research by Vasić et al [15] composites with graphite fiber 
materials are the strongest and stiffest materials widely used in unmanned aircraft structural systems. Placing 
fibers in graphite composites, it will increase the strength and stiffness of the composite material.  

Tensile testing of coupon specimens was conducted to obtain the modulus of elasticity of the composites used 
in the UAV. The elastic properties obtained from the mechanical tests were used in the elemental analysis of 
the UAV wing. The woven fabric was modeled as a 2-D orthotropic layer in the analysis. In addition to 
mechanical testing, elastic properties were also obtained by two other methods. One method is the composite 
micromechanics approach. In this approach, the properties are obtained based on the volume fraction of the 
constituents and their respective mechanical properties. The woven fabric is modeled as a biaxial cross-ply 
laminate in the analysis. Another method used to derive elastic properties is the approximate approach. This 
approach is based solely on the rule of mixtures. In this case, the woven fabric is also modeled as a 2-D 
orthotropic layer. It can be concluded from the results of the full-wing analysis that the three material 
definitions used to give consistent and acceptable results. Moreover, if the displacement results are observed, 
it is clear that they are almost the same [10]. 

Research has been conducted by Galatas et al [16] using the latest sandwich composite structure consisting of 
acrylonitrile butadiene styrenecarbon (ABS) laminated with carbon fiber reinforced polymer (CFRP) layer 
with ABS/CFRP/ABS arrangement. A series of tests were conducted with tensile measurements for 3D 
printed samples with varying filler densities and CFRP layers. The results showed that the ABS/CFRP/ABS 
sandwich structure during the tensile tests exhibited brittle properties while it was ductile for the monolithic 
ABS samples.    

4. Conclusions 

Laminar Composites type composite material with sandwich structure is the latest composite material and is 
widely applied as a UAV wing structure. Laminar composites and sandwiches consisting of various materials 
such as Balsa wood fiberglass and polyester resin, microparticles, Carbon Fiber Reinforced Polymer, polymer 



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112 

matrix composites reinforced with continuing fibers, Polymer matrix composites, E-glass/Epoxy, 
Kevlar/Epoxy, Carbon/Epoxy, woven fabrics, acrylonitrile butadiene styrenecarbon (ABS) laminated with 
carbon fiber reinforced polymer (CFRP)and uniaxial prepreg fabrics. This laminar-type composite material 
with a sandwich structure has good test values and can be used as a UAV wing structure material.  

Declaration of competing interest 

The authors declare that they have no any known financial or non-financial competing interests in any 
material discussed in this paper. 

Funding information 

No funding was received from any financial organization to conduct this research. 

 

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