INTERNATIONAL JOURNAL OF LATEST TECHNOLOGY IN ENGINEERING,
MANAGEMENT & APPLIED SCIENCE (IJLTEMAS)
ISSN 2278-2540 | DOI: 10.51583/IJLTEMAS | Volume XIV, Issue X, October 2025
www.ijltemas.in Page 386
Design and Development of a Radio-Controlled Aircraft and
Concept of Electric Vertical Takeoff and Landing (eVTOL)
Gutti Siva Kumar¹, Jethwa Krushik Girish², Mr. Mayur Chavda³, Ms. Apexa Purohit⁴, Dr. Anil M. Bisen⁵, Dr. Mayank
Dev Singh⁶, Dr. Jai Bahadur Balwanshi⁷
¹²³⁴⁶ Mechatronics Engineering Department, ITM Vocational University, Vadodara, Gujarat, India
⁵⁷ Mechanical Engineering Department, ITM Vocational University, Vadodara, Gujarat, India
DOI:
https://doi.org/10.51583/IJLTEMAS.2025.1410000049
Abstract: This study presents the design, development, and preliminary testing of a radio-controlled (RC) aircraft and conceptual
work on its electric vertical take-off and landing
I. Introduction
(eVTOL) capabilities. The primary objective is to explore the feasibility of incorporating VTOL functionality into a lightweight
RC platform using accessible, low cost materials and components. The aircraft is constructed using foam board for its favorable
weight to strength ratio and employs a straightforward elevon- based control mechanism for pitch and roll modulation. A
brushless DC motor, electronic speed controller (ESC), and Li-Po battery constitute the propulsion system, while an Arduino
Nano and IMU (MPU6050) support the eVTOL’s stability and control. The system is manually operated via a Flysky FS-i6
transmitter and receiver. The prototype demonstrated stable flight in fixed wing mode and basic lift-off and hover capabilities in
VTOL mode; however, it encountered instability during mode transitions due to limitations in PID control tuning and power
demands. The outcomes suggest that hybrid flight systems are achievable on a small scale, albeit with significant challenges in
stability control and energy efficiency. This work lays a foundation for future investigations into hybrid UAV platforms and low-
cost autonomous aerial mobility solutions.
Index Terms: RC aircraft, eVTOL, PID control, brushless DC motor, elevon, UAV, Arduino, foam board, flight stability.
Advancements in electric propulsion and the increasing demand for urban air mobility have catalyzed the emergence of electric
vertical take-off and landing (eVTOL) aircraft. These vehicles combine the vertical lift capability of helicopters with the
aerodynamic efficiency of fixed wing aircraft, of- fering transformative potential for transportation, emergency response, and
surveillance in urban environments. eVTOL technology is integral to evolving concepts such as NASA’s Urban Air Mobility
(UAM) initiative, which envisions inte- grated air transport solutions in dense urban centers.
Parallel to this trend, the proliferation of unmanned aerial vehicles (UAVs) and hobby grade radio-controlled (RC) air- craft has
opened avenues for educational and experimental research. These platforms provide cost effective and man- ageable
environments to test complex flight concepts like VTOL on a smaller scale. This project takes advantage of these opportunities by
designing a lightweight RC aircraft with integrated eVTOL capabilities, emphasizing simplicity, modularity, and low-cost
construction.
Problem Statement
Traditional fixed-wing RC aircraft require runways or launch mechanisms for takeoff and landing, limiting their de- ployment in
constrained environments. In contrast, multirotor VTOL systems, while maneuverable, often necessitate com- plex control
algorithms and exhibit high power consumption. This project seeks to bridge the gap by developing a hybrid design that retains
the operational simplicity of fixed wing aircraft and enabling vertical take off and landing through integrated VTOL functionality.
Project Overview
The project encompasses the conceptualization, CAD de- sign, construction, and testing of a RC aircraft and its eVTOL
functionality. It features foam board construction for reduced weight, an elevon based control mechanism for maneuver- ability,
and a propulsion system centered around a brushless DC motor and electronic speed controller. The eVTOL func- tionality is
enabled through an Arduino Nano based control system incorporating an inertial measurement unit (IMU). The aircraft is
operated manually using a Flysky FS-i6 transmitter, supporting both horizontal and vertical flight testing.
Significance of the Study
This study holds educational and experimental significance by providing practical insights into UAV design, control sys- tems,
propulsion technology, and flight dynamics. It demon- strates how hybrid aircraft models can be constructed using accessible
tools and components, making the research rel- evant for academic institutions, UAV hobbyists, and early- stage prototyping in
aerospace engineering. Furthermore, the integration of CAD modeling and electronic control fosters a multidisciplinary approach
essential for next-generation aerial mobility solutions.
Objectives
This project aims to design, construct and evaluate a hybrid radio-controlled (RC) aircraft and conceptual work on its electric
INTERNATIONAL JOURNAL OF LATEST TECHNOLOGY IN ENGINEERING,
MANAGEMENT & APPLIED SCIENCE (IJLTEMAS)
ISSN 2278-2540 | DOI: 10.51583/IJLTEMAS | Volume XIV, Issue X, October 2025
www.ijltemas.in Page 387
vertical take off and landing (eVTOL) capabilities. It emphasizes a low cost, modular approach using accessible materials and
digital design techniques. The research focuses on achieving aerodynamic efficiency, functional control sys- tems, and structural
integrity suitable for experimental and educational purposes.
General Objective
To develop a functional prototype of a hybrid RC aircraft and conceptual work on its eVTOL features, leveraging com- puter
aided design (CAD) tools for precision modeling, and applying electronic control systems to achieve both horizontal and vertical
flight operations.
Specific Objectives
•
Structural Design: To model the RC aircraft and eVTOL configuration using CAD software to ensure dimensional
accuracy, component alignment, and weight distribution optimization.
•
Component Selection: To identify and integrate suitable propulsion and control components, including motors, electronic
speed controllers (ESCs), servos, batteries, and microcontrollers, based on thrust to weight ratios and system compatibility.
•
Airframe Construction: To fabricate a light weight, aerodynamically stable airframe using foam board and supporting
materials such as hot glue, 3D-printed parts, and control links.
•
Control Mechanism Implementation: To configure an elevon-based control system that combines pitch and roll control
via two SG90 servos, simplifying the mechanical design.
•
Manual Control Integration: To implement remote manual control using a Flysky FS-i6 transmitter and receiver system,
ensuring real-time response in both RC and VTOL modes.
•
Propulsion System Configuration: To assemble a propulsion system comprising a 2200KV brushless DC motor, a 30A
ESC, and an 11.1V 1500mAh 40C Li-Po battery to achieve sufficient lift and endurance.
•
Testing and Evaluation: To perform preliminary flight tests in controlled environments, assessing lift, maneuver- ability,
and stability during both vertical and horizontal flight phases.
•
Performance Assessment: To analyze flight performance data and propose iterative improvements for enhanced stability,
control, and energy efficiency.
II. Literature Review
This section reviews existing research and technological developments relevant to the design of electric vertical take- off and
landing (eVTOL) systems and radio-controlled (RC) aircraft. It examines key elements including flight configu- rations, control
mechanisms, material choices, and electronic components. The review highlights both academic studies and practical
implementations that have informed this project.
Evolution of eVTOL Technology
eVTOL aircraft are at the forefront of urban air mobility (UAM) initiatives aimed at addressing transportation ineffi- ciencies in
congested urban areas. They merge vertical lift capabilities with fixed-wing efficiency, thereby eliminating the dependency on
runways. NASA’s UAM initiative emphasizes the transformative potential of eVTOLs in urban transporta- tion systems [1]. The
integration of electric propulsion, au- tonomous control systems, and advanced materials is enabling rapid evolution in this field.
Fixed-Wing and Hybrid VTOL Systems
Hybrid VTOL aircraft combine characteristics of fixed-wing aircraft and multi rotors, facilitating efficient cruising and vertical
operations. Configurations such as tilt-rotor, tilt-wing, and tail-sitter are explored extensively in academia. Anderson et al. [2] at
Stanford University demonstrated the advantages of hybrid VTOL designs in achieving better range and efficiency compared to
pure multi rotor systems. However, these designs often require advanced control systems including GPS, IMU, and real-time
orientation feedback to handle flight transitions.
RC Aircraft Design Principles
RC aircraft serve as valuable tools for research and hobby applications due to their simplicity and adaptability. Stability in flight
is governed by key parameters such as thrust-to- weight ratio, center of gravity (CG), wing loading, and airfoil design. The
research by Rehan et al. [3] underscores the importance of balancing CG and minimizing wing loading for low-speed flight
stability. Foam board is a popular material for RC aircraft due to its low cost, ease of manipulation, and lightweight properties.
Elevon Control Mechanism
Elevons are a hybrid control surface that combines the functions of elevators and ailerons, commonly used in delta wing and
flying wing configurations. They provide pitch and roll control using only two servos, which reduces weight and mechanical
complexity. Beard and McLain [4] demonstrated the efficiency of elevons in minimalist UAV platforms, particu- larly when paired
with programmable transmitters that support mixing functions, such as the Flysky FS-i6 used in this study.
INTERNATIONAL JOURNAL OF LATEST TECHNOLOGY IN ENGINEERING,
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Precise Component Selection
The performance of RC and eVTOL systems is significantly influenced by component compatibility. High KV brushless motors
offer high rotational speeds ideal for lightweight plat- forms. ESCs should exceed expected current loads by at least 20 – 30%,
and Li-Po batteries must have high discharge rates to support peak loads during take-off. The SG90 micro servo is frequently
employed in educational UAVs for its cost effectiveness and adequate torque for foam-based applications. The MPU6050 IMU
and Arduino Nano are commonly used for basic flight stabilization in small UAVs [5].
Role of CAD in UAV Development
Computer-aided design (CAD) tools such as SolidWorks and Fusion 360 are instrumental in UAV prototyping. They allow
precise modeling of geometries, simulate weight dis- tribution, and ensure structural symmetry. CAD also supports the generation
of cutting templates and layout planning, which are vital for error-free assembly. As evidenced in student UAV competitions, CAD
contributes to improved build accuracy and facilitates early stage validation of design concepts.
III. Methodology
This section outlines the experimental and design method- ology employed in developing the RC aircraft and conceptual work on
its eVTOL functionality. The approach encompasses iterative design, component selection, CAD modeling, proto- typing, and
performance testing.
Design Approach
A prototyping methodology was adopted, combining theo- retical design with practical fabrication and iterative testing. Initial
design concepts were sketched, followed by precise modeling using CAD tools. The system design aimed to simplify mechanical
complexity while integrating both RC and eVTOL flight modes.
Materials Used
Two primary construction phases were implemented:
•
Prototype phase: Built using cardboard for concept validation.
•
Final build: Constructed with foam board for structural strength and minimal weight.
Additional materials included:
•
Hot glue for assembly
•
1.1 mm push rods for control linkages
•
Velcro straps for battery mounting
•
3D printed parts: motor mounts, tilt mechanisms, control horns
•
Spray paint for protective coating and visual differentia- tion
Electronic Components
Table I Electronic Components Used
Component
Specification
Motor
2200KV Brushless DC motor
ESC
30A Electronic Speed Controller
Battery
11.1V 3S 1500mAh 40C Li-Po
Transmitter/Receiver
Flysky FS-i6 with FS-iA6B receiver
Servos
SG90 micro servos
Propeller
5149N tri-blade
Microcontroller
Arduino Nano
IMU
MPU6050
CAD Modeling
SolidWorks was used for structural design, including:
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Fig. 1. Cad Model
•
Symmetric airframe modeling
•
Component layout (motor, battery, control surfaces)
•
Generating 2D templates for material cutting
•
Weight distribution and CG alignment estimation
Control System Configuration
For RC Plane:
•
Elevons controlled by two SG90 servos via Flysky FS-i6 transmitter
•
ESC powered by Li-Po battery with integrated BEC for servo supply
For eVTOL:
•
Arduino Nano interfaced with MPU6050 IMU for angle detection
•
Flysky receiver interfaced via iBus to read throttle, pitch, roll, and mode input
•
ESCs controlled via PWM signals from Arduino for dual- motor thrust
•
Elevon and tilt servos adjusted via PID-controlled feed- back from IMU
Software Implementation
Arduino IDE was used to implement a custom control program with the following features:
•
Sensor initialization and calibration
•
PID control for pitch and roll stabilization
•
iBus signal reading from FS-i6 for user commands
•
Smooth transition between hover (90° tilt) and forward flight (0° tilt)
•
Real-time computation loop for servo and motor control every 10 ms
Testing Procedure
Two modes of testing were conducted:
•
Fixed-wing RC testing: Evaluated in open ground with direct user input.
•
eVTOL testing: Conducted in a controlled indoor space for hover and lift validation.
Key metrics assessed:
•
Stability (during hover and cruise)
•
Lift-off capability and thrust adequacy
•
Response to control inputs
•
Transition reliability from vertical to horizontal mode
•
Battery consumption and flight duration
IV. Results and Discussion
This section presents and interprets the experimental find- ings from the RC aircraft and eVTOL prototype tests. It compares
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observed performance metrics with theoretical ex- pectations and evaluates the limitations and successes of each flight mode.
Observations
RC Plane Performance
•
Stability: The aircraft maintained consistent forward flight stability with responsive pitch and roll control via elevons. The
airframe showed minimal oscillations at lower speeds.
•
Speed and Efficiency: The plane achieved a ground- tested cruising speed of 5–8 m/s, with a theoretical capa- bility up to
10 m/s. Low aerodynamic drag contributed to efficient propulsion.
•
Flight Duration: The RC plane sustained a flight time of approximately 10–15 minutes per full battery charge, consistent
with comparable lightweight UAVs.
•
Control Response: Elevon-controlled maneuvering was adequate. However, at higher speeds, minor roll insta- bility was
detected, likely due to servo limitations or aerodynamic disturbances.
eVTOL Performance
•
Lift-Off and Hover: The vertical thrust was sufficient for lift-off, allowing for stable hovering at low altitudes for brief
periods (5–8 minutes).
•
Transition to Forward Flight: Attempts to transition from vertical to forward flight were unsuccessful due to
instability and control divergence during tilt-servo actuation.
•
Landing: The VTOL system allowed controlled vertical descent and landing with moderate stability.
•
Control Issues: The PID system exhibited tuning limita- tions, resulting in oscillatory behavior during hover and
transition attempts.
•
Power Consumption: Hover mode required both motors at high throttle, causing rapid battery depletion, thus limiting
flight time to 5–8 minutes.
Discussion
RC Plane Analysis
The RC configuration met expectations for forward flight stability and efficiency. The use of foam board and proper CG
positioning contributed to aerodynamic balance. SG90 servos provided effective elevon actuation, though some responsive- ness
degradation occurred at higher airspeeds. These findings are in alignment with other lightweight RC aircraft studies, validating
the design choices made.
eVTOL Analysis
The eVTOL mode revealed the inherent complexity of stable vertical flight and transition control. While hovering was achieved,
the system lacked the control precision required for smooth mode switching. Key limitations included:
•
Inadequate PID tuning for dynamic adjustments during flight transitions.
•
Sensor noise and delayed actuator response.
•
Software constraints related to the iBus library and low processing speed of the Arduino Nano.
Power consumption during VTOL operations further con- strained the aircraft’s usability, demonstrating the need for high-
efficiency propulsion and larger-capacity energy systems in future iterations.
Comparison with Literature
These results reflect common challenges in small-scale hy- brid UAV development as reported by Rehm [6] and Brooking [7],
including PID tuning, flight mode transitions, and battery limitations. The project confirms that while hybrid RC-eVTOL systems
are achievable at low cost, achieving full performance parity with commercial UAVs requires enhancements in con- trol
algorithms, power systems, and structural integration.
V. Conclusion
Summary
This study demonstrated the feasibility of building a low cost hybrid RC-eVTOL aircraft. The RC plane showed reliable
performance, while the eVTOL system revealed limitations in transition stability and power management.
Recommendations
•
Replace Arduino Nano with faster microcontrollers (e.g., ESP32).
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•
Apply advanced control algorithms and filters (e.g., Kalman).
•
Optimize aerodynamics and weight distribution.
•
Use higher capacity and energy-efficient batteries.
Limitations
Control instability during transitions, software constraints, and single prototype testing limited generalization.
Acknowledgment
The authors thank Mr. Mayur Chavda and Dr. Mayank Dev Singh for their support, and the Department of Mecha- tronics
Engineering, ITM Vocational University, for providing resources.
References
1. NASA, “Urban Air Mobility (UAM) Vision,” 2020. [Online]. Available: https://www.nasa.gov/uam
2. M. Anderson, J. Bowers, and S. Thomas, “Hybrid VTOL Aircraft: Efficiency in Urban Transport,” Stanford University,
2016.
3. M. Rehan, A. Saeed, and L. Khan, “Aerodynamic Optimization of Foam- Based RC Aircraft,” Journal of Aerospace
Research, vol. 8, no. 3, pp. 120–128, 2020.
4. R. Beard and T. McLain, Small Unmanned Aircraft: Theory and Practice. Princeton University Press, 2012.
5. K. Selvam, “Component-Level Integration for Small UAVs,” International Journal of Robotics and Mechatronics, vol.
11, no. 1, pp. 15–22, 2023.
6. T. Rehm, “Challenges in Small Hybrid VTOL UAVs: Design and Control Perspectives,” UAV Engineering Journal, vol.
9, no. 2, pp. 45–53, 2022.
7. D. Brooking, “Control and Stability Analysis of Low-Cost VTOL Drones,” in Proc. of the International Conf. on UAV
Systems, pp. 89– 96, 2017.
8. J. Anderson et al., “Hybrid VTOL Aircraft Research,” Stanford Univer- sity, 2016.
9. M. H. Rehan, A. Y. Qureshi, and Z. Shahid, “Design of RC Aircraft,” Feb. 2020.
10. R. Beard and T. McLain, Small Unmanned Aircraft: Theory and Prac- tice, 2012.
11. S. Selvam, “The Ultimate Guide to Building RC Vertical Takeoff Planes,” Sept. 2023.
12. N. Rehm, “dRehmFlight VTOL,” July 2022.
13. J. Brooking, “Project YMFC-AL: The Arduino Auto-Level Quadcopter,” Apr. 2017.
