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.
This study evaluates the VTOL behaviour of a 4.18 m-span, 15.5 kg flying-wing UAV and proposes a simplified propulsion-layout redesign. Three flights of the original tri-rotor configuration were analysed using attitude, motor and servo PWM, altitude, and vibration data. Roll and pitch tracking errors averaged 0.54° and...
G. Badea, D. Crunteanu· INCAS Bulletin· 0 citations
This study examines the hovering and forward-flight stability of a heavy-lift coaxial unmanned helicopter with a suspended payload. A six-degree-of-freedom dynamics model is developed, coupling the rotor, fuselage, and a rigid-body sling via a universal joint, while neglecting rotor–payload aerodynamic interference for...
This study aims to investigate the flight stability, control robustness and trajectory tracking performance of a quadrotor unmanned aerial vehicle (UAV) equipped with a dual-axis tilt-rotor mechanism, and compares its performance against conventional quadrotor designs.
A Newton–Euler approach is used to deri...
Omer Bayraktar, A. Guldas· Aircraft Engineering and Aer...· 0 citations
Designing a statically stable flying-wing UAV glider is a highly nonlinear problem in which small geometric changes cause large shifts in stability and performance. While prior work has applied gradient-based and gradient-free methods to flying-wing aerodynamic optimization, most approaches lack direct parametric C...
Simon Grimm, E. Price, Aamir Ahmad· Aerospace Systems· 0 citations
This paper describes the first ever flight demonstration of a stability augmentation system using electromechanical inline actuators in a rotorcraft without hydraulic force amplification. A coaxial ultralight helicopter equipped with the stability augmentation system is used as a flight demonstrator. The paper covers...
B. Rothaupt, Walter Fichter, B. Grebing· CEAS Aeronautical Journal· 0 citations
The purpose of this study is to design, analyse, fabricate and validate a fixed-wing UAV for stable low-speed flight, payload carriage and controlled in-flight deployment. It aims to achieve aerodynamic efficiency, structural safety, stability and practical manufacturability for short-range logistics, surveillance...
Aditya Sivaraman, A. Ansari, Aqleem Siddiqui et al.· International Journal of Int...· 0 citations
We use cookies to run the site and, with your consent, for analytics and to show ads.
See our Cookie Policy.
