Sukanya Puthalapattu is a mechanical engineer whose academic and professional work reflects disciplined analytical thinking and advanced design capability. With a Master of Science in Mechanical Engineering from Texas A&M University–Kingsville, her technical foundation spans advanced dynamics, control systems, fluid mechanics, and computational design. Her proficiency in SolidWorks, CATIA V5, ANSYS, MATLAB, and geometric dimensioning and tolerancing is complemented by hands-on experience in 3D modeling, structural validation, and engineering analysis. Her graduate research project, ‘Design and Analysis of Double-Propeller Hexacopter’, represents a focused exploration into UAV system design, motion simulation, and dynamic modeling. Rather than treating drone development as a surface-level design task, Sukanya approached it as a multi-variable mechanical system requiring mathematical rigor, aerodynamic reasoning, and structural feasibility. The project reflects her ability to translate theoretical mechanics into simulation-validated design. By integrating Newton–Euler dynamic modeling with SolidWorks motion analysis, she developed a framework to enhance thrust distribution, stability control, and hovering efficiency. The result is not merely a drone configuration, but a carefully engineered dynamic system grounded in mechanical principles.
Redefining Multicopter Architecture: Why a Double-Propeller Hexacopter?
The central objective of Sukanya’s graduate research was to design and analyze a double-propeller hexacopter using computational modeling and motion simulation. Traditional multicopter research frequently focuses on quadcopters due to structural simplicity and cost efficiency. However, quadcopters exhibit limitations in redundancy, payload capacity, and stability under component failure.
Hexacopters offer improved fault tolerance and lifting capacity, but Sukanya’s work moves a step further by implementing a twelve-rotor system configured as six pairs of counter-rotating propellers. The rationale behind this configuration is performance enhancement through distributed thrust. By increasing the number of propulsion units, upward force is divided across multiple rotors, reducing per-motor load while improving overall system stability.
The design also improves redundancy; in the event of rotor failure, the system can maintain controlled flight and execute a safe landing. This characteristic is critical for UAV applications involving surveillance, mapping, or transportation of valuable equipment. However, increasing the number of rotors introduces control complexity.
The hexacopter’s stabilization requires coordinated management of yaw, roll, and pitch motions. Each rotor contributes weight, and total system mass directly influences battery life and flight duration. Thus, the design challenge lies in balancing thrust generation with energy efficiency.
The use of counter-rotating propellers further enhances torque management. Opposing rotational directions reduce net reaction torque and improve stability during hover. Additionally, airflow interaction between propeller pairs allows partial recovery of energy from slipstream motion, contributing to improved thrust efficiency. Sukanya’s architectural decision reflects a systems-level understanding of mechanical trade-offs. The design does not merely increase propulsion units; it strategically redistributes aerodynamic forces to enhance stability, safety, and load-carrying capability. In doing so, the project demonstrates an advanced grasp of multicopter configuration beyond standard UAV frameworks.
Mathematical Modeling and Dynamic Control Framework
At the core of the project lies a comprehensive mathematical model developed using the Newton–Euler technique. This model represents the dynamic behavior of the twelve-rotor system by relating motor angular velocities to generated thrust forces and reaction torques. Establishing accurate coordinate systems was essential for describing translational and rotational motion.
Thrust and torque constants were defined as proportional relationships between aerodynamic forces and the square of angular velocity. This allowed Sukanya to construct a matrix representation linking motor speeds to resultant body forces. Because the configuration involves twelve independent rotors controlling four primary outputs, total thrust and three torque components, the matrix is non-square. To resolve this, a pseudo-inverse approach was applied to determine the required motor speeds for specific force and torque demands.
Euler angles were used to parameterize orientation. Roll motion results from asymmetric speed variations across lateral rotor pairs, pitch motion from front-rear speed differentials, and yaw motion from alternating clockwise and counterclockwise rotor velocities. These relationships were mathematically expressed to calculate angular accelerations and body movements.
The model also incorporates gravitational force, thrust force, drag effects, and gyroscopic movements. Although gyroscopic contributions are relatively small, their inclusion strengthens the physical accuracy of the system representation. Tilt limits were analytically defined to prevent instability during aggressive maneuvers.
This modeling framework transforms the hexacopter from a conceptual drone into a quantifiable dynamic system. The derived equations allow prediction of translational acceleration, angular response, and stability margins under varying operational conditions. Such analytical rigor ensures that performance optimization is not based on trial and error, but on mathematically grounded control logic.
CAD Design and Motion Simulation in SolidWorks
The theoretical model was translated into a detailed physical design using SolidWorks. The geometrical dimensions of the lower frame, upper frame, and arms were defined with reference-based measurements and refined to meet regulatory constraints and practical feasibility. The result was a structurally coherent UAV platform designed for balanced load distribution.
The chassis was conceptualized as the structural backbone requiring both rigidity and weight efficiency . Motor housings, rotor assemblies, landing gear, hub connections, and propeller dimensions were modeled individually and then assembled into a complete system. Each motor was selected to maintain uniform kV ratings to ensure balanced performance across all propulsion units.
Motion simulation played a critical role in validating the design. By simulating takeoff, hover, forward flight from point A to point B, and landing phases, Sukanya evaluated altitude maintenance and system responsiveness. Angular velocity and angular acceleration plots were analyzed to understand system behavior under varying input conditions
The simulation environment enabled assessment of dynamic constraints without physical prototyping. Structural alignment, rotor interference clearance, and frame symmetry were verified in the CAD environment. This digital validation approach reduced uncertainty and ensured that the mathematical model translated accurately into mechanical geometry.
The integration of 3D modeling and motion analysis reflects Sukanya’s broader expertise in CAD-driven engineering design. The project demonstrates a seamless transition from equation-based modeling to parametric digital construction, reinforcing the feasibility of the double-propeller architecture.
Performance Optimization and Stability Enhancement
Performance optimization in the double-propeller hexacopter centers on achieving stable hovering, controlled maneuverability, and efficient thrust distribution within a twelve-rotor configuration. In multicopter systems, hovering represents a dynamic equilibrium condition where total generated thrust must precisely counteract gravitational force. In this design, that equilibrium is achieved through synchronized control of angular velocities across all rotor pairs.
The counter-rotating propeller arrangement plays a critical role in managing torque effects. By configuring paired propellers to rotate in opposite directions, the system reduces net reaction torque and improves yaw stability. This mechanical balance minimizes unwanted rotational drift during hover and ensures directional corrections can be made without destabilizing the vehicle. The distribution of thrust across six arms further enhances lateral stability by maintaining symmetry around the center of gravity.
Roll and pitch motions are governed by controlled speed variations in defined rotor groups. Increasing rotor speed on one side while proportionally reducing it on the opposite side generates the necessary torque for angular displacement. These torque relationships were mathematically derived within the dynamic model, ensuring that maneuvering inputs are not empirical but analytically determined. This structured control logic improves predictability during transitional movements such as forward acceleration or lateral correction.
Energy efficiency is equally central to system performance. While a twelve-rotor configuration increases total mass and power demand, thrust is distributed evenly across motors, preventing excessive load concentration. By avoiding over-reliance on individual motors, the design supports balanced energy consumption and contributes to sustained flight performance. Maximum tilt angle calculations were incorporated into the control framework to preserve stability margins. Limiting excessive angular displacement prevents loss of control during aggressive maneuvering and maintains safe operational boundaries.
The result is a UAV system engineered for controlled stability rather than raw thrust amplification. Through coordinated torque management, distributed propulsion, and analytical control modeling, the double-propeller hexacopter achieves reliable hovering and directional precision under realistic operating conditions.
A Structured Contribution to Multicopter Engineering
The Design and Analysis of Double-Propeller Hexacopter represents a structured and analytically grounded contribution to multicopter engineering. Sukanya Puthalapattu approached UAV development as a dynamic systems problem requiring integration of mechanical theory, mathematical modeling, and computational validation. Rather than focusing solely on hardware configuration, the project emphasizes equilibrium between aerodynamic forces, torque management, and structural feasibility.
By employing Newton–Euler dynamics, pseudo-inverse matrix control logic, and SolidWorks-based motion simulation, the research establishes a coherent link between theoretical derivation and practical implementation.
The double-propeller configuration enhances thrust distribution and redundancy while maintaining analytical consistency and mechanical symmetry. Each design decision is supported by mathematical relationships governing rotor speeds, torque generation, and translational response.
Importantly, the project demonstrates that UAV performance optimization is most effective when grounded in first-principles mechanics. The integration of control modeling, CAD validation, and dynamic simulation ensures that the system is not merely conceptual but functionally reasoned. Stability, efficiency, and redundancy are treated as interconnected variables rather than isolated features.
As a graduate-level research undertaking, the work reflects technical rigor, disciplined modeling methodology, and design precision. It positions the double-propeller hexacopter not simply as a variation of existing multicopter platforms, but as a systematically engineered aerial system shaped by analytical clarity and structured optimization.
