Structural Design and Optimization of Heavy-Duty

Design of an Unmanned Aerial Vehicle for Logistics Applications in the Low-Altitude Economy

Optimized Modular Design and Development of a Tilt-Rotor Bicopter Drone

Hybrid systems like tilt-rotor bicopter drones combine the beneficial characteristics of both fixed-wing and rotary-wing technology, enabling long endurance and VTOL capability. However, such drones also require an optimum design to ensure both static and dynamic stability. The modular design of a traditional bicopter is developed in this paper based on extensive analysis and in-depth structural and aerodynamic simulations. The structural analysis has been performed to ensure that the aircraft's structure withstands the stresses encountered during different flight modes. Controlling the relative positions of the Center of Gravity (CG) and Neutral Point (NP) is an essential aspect of the design, ensuring stability during hover and positive stability during forward flight. The thrust and power analyses have been conducted to assess the flight performance and endurance. After analysis, the drone has been developed, and flight tests with a basic flight controller were conducted to validate the performance metrics obtained in the simulation.

Load Analysis of Flap and Slat Actuators in Aircraft High-Lift Systems

This study develops an end-to-end load analysis scheme for flap and slat actuators, which comprise the aircraft’s high-lift system, and the analysis results are directly integrated into hardware optimization. Because they shoulder heavy responsibilities during the takeoff and landing phases, whether they can remain rock-solid under complex aerodynamic conditions or even remain unmoved in emergencies is directly related to their overall safety performance. This work process is closely linked and includes three major links. First of all, according to the CCAR-25.301 standard, the load envelope under normal working conditions is sorted out, and the limit cases of abnormal faults are exhausted. Subsequently, ANSYS Workbench pulled silk and peeled off the cocoons to capture the peak stress at the engagement between the output shaft and the gear. In the end, the closed-loop verification of the customized test bench made the theoretical calculations and the hardware-measured data exactly the same. The entire package provides designers with hardcore data support, and always uses airworthiness, not convenience, as the criterion when improving actuator performance.

Design of AUV launch and recovery system based on multi-degree-of-freedom manipulator

Aiming at the problems of high sea condition susceptibility, low automation level, and high operational risks in the storage, transportation, launching, and recovery of shipborne Autonomous Underwater Vehicles (AUVs) under complex marine wind and wave environments, this paper designs an AUV launching and recovery device with a wheeled mobile chassis. The device integrates three core modules: a wheeled transfer platform, a multi-degree-of-freedom telescopic manipulator, and a modular open-close net cage. The wheeled chassis enables flexible deck transportation and rapid positioning of the AUV; the 360° rotatable and telescopic manipulator adapts to multiple operation positions for flexible launching and precise deployment; the open-close net cage significantly improves AUV recovery efficiency and operational safety. Structural strength analysis via SolidWorks plug-in verifies the device’s mechanical performance and reliability under rated load. Experimental and analytical results show the device has good stability and sea condition adaptability, with prominent advantages in deck transportation, operation accuracy, and complex environment adaptability, providing technical schemes and design references for efficient and safe launching and recovery of shipborne AUVs.

Design of The VTOL Jet Engine for Energy Efficiency and Lightweight Flying Vehicle Analysis in Malaysia

Driven by the growing demand for efficient emergency Vertical Takeoff and Landing (VTOL) transportation and advanced air mobility, the development of lightweight flying vehicles has become increasingly critical. This research presents an innovative flap design integrated with a jet engine system to optimize the aerodynamic efficiency and flight endurance of a lightweight aircraft. Characterized by a 770 kg payload capacity and a maximum speed of 425 km/h, the proposed vehicle underwent a rigorous development process involving aerodynamic analysis, structural configuration design, Computational Fluid Dynamics (CFD) simulations, and validation. The airframe leverages high-strength, lightweight materials specifically carbon fiber and aluminum integrated with a jet propulsion layout to reduce energy consumption. Numerical simulations demonstrate that the proposed flap configuration enhances flight endurance by approximately 36% over conventional designs. This framework exhibits strong potential for emergency response applications, including ambulatory and rescue operations, by mitigating traffic-induced delays. This study contributes directly to the advancement of energy-efficient jet engine technology and next-generation aerospace transportation systems in Malaysia.

Research on Structural Improvements of UAVs under Extreme Weather Conditions