Transition flight simulation of a hybrid VTOL fixed-wing drone

Transstellar Journals, 2019

The transitional aircraft configuration is designed and developed, with a transitioning propulsion mounts from a hover mode to forward flight mode. Calculating the appropriate values of design parameters and performance characteristics was done initially keeping in mind, the takeoff weight, usability and the payload carried by the aircraft. Complete modelling of the wing using Catia V5 and designing it for flow and structural analysis using ANSYS. The NACA 4415 airfoil with optimal dimensions is considered for the wing. The laser cutting technique is used in the fabrication. The fabricated model has been precision machined with the lightest materials to reduce weight and increase the efficiency. The autonomy is achieved with required configuration and coding using the KK2 board with manual PID tuning, thus gave full control at hand. The VTOL mechanism was built from scratch and is wirelessly controlled for flight operations.

Journal of engineering, 2022

e Vertical Take-o and Landing (VTOL) unmanned aerial vehicles (UAVs) with the tilt-rotor mechanism also known as hybrid UAVs have a lot of challenges in designing and controlling concerning their use in harsh weather for surveillance and access to remote areas. is review paper presents a review of the preliminary design of hybrid aircraft and control systems. e tilt-rotor mechanism and tilt wings of a hybrid UAV are analyzed. e paper provides an outline of technical advances in UAVs in hybrid con guration concerning their constraint analysis, propulsion sizing, and design evaluation. Furthermore, the ight dynamics modeling is described with the control system and dynamics of the hybrid UAV. is paper lists various software for simulations and analysis such as SOLIDWORKS and CATIA for CAD modeling, MATLAB and SIMULINK for mathematical modeling and ight control, and XFLR5 for stability analysis of aerofoils, wings, and planes. In addition, certain control strategies are executed and scrutinized in terms of the theory, the linearity, and the implementation of the model.

International Journal for Research in Applied Science and Engineering Technology

Our study involves the implementation of a drone-based medicine delivery system utilizing the KK2.1.5 Flight Controller Board for Multirotor Drone. Our optimized drone is specifically designed to deliver medicine in rural areas, where transportation infrastructure may be lacking or geographical terrain may be difficult to traverse. Also, it can be used for contactless delivery of medicine in pandemic situation This innovative technology has the potential to be of great benefit in areas where traditional transportation services are inadequate or unavailable. I.

Engineering Science and Technology, an International Journal, 2020

The objective of this paper is to explain the design steps and performance analyses including energy consumption of a fixed-wing (FW) vertical takeoff and landing (VTOL) unmanned air vehicle (UAV). The vehicle is designed from the beginning with the goal for low takeoff weight and high aerodynamic performance. Aerodynamic design steps and sizing of both wing and control surfaces are demonstrated and static stability is fulfilled by evaluating the center of gravity location with respect to neutral point. In addition, power requirements and energy consumptions for takeoff , climbing, cruise and landing are evaluated in perspective of flight performances to find out the required endurance for each flight condition. In order to do that selected battery is modelled in Simulink and results are represented. In takeoff and landing flight conditions, momentum theory is implemented for vertical flight while the cruise flight is utilized to find out the maximum endurance. Drag calculations in level flight are performed in detail to experience the drawbacks of multi-rotor system including propellers providing vertical flight. Finally, VTOL-FW concept having multi-rotor system with four extra propellers and only fixed wing (FW) concept are compared in terms of endurance. It is found that FW concept without multi-rotor system with four propellers have much more endurance compared to VTOL-FW concept. Manufacturing with threedimensional printers and flight tests of VTOL-FW UAV will be performed as a future work.

IJRAME PUBLICATIONS, 2024

As we know that fixed wing unmanned aerial vehicle required long runways for takeoff and landing and also flight time then other. As it is difficult to have longer runway in city area, the need of vertical takeoff and landing (VTOL) arises. VTOL aircraft is the type of flight systems which have the ability to take off and land vertically, then transition to horizontal flight, and also allowing an aircraft to cover long distances at high speed and also have advantage to takeoff and land in vertical manner without the need of runway. There are various applications of VTOL such as it can be used as ondemand air mobility, for cargo and package delivery, in healthcare applications, and in emergency services. The new and emerging trends of VTOL are that it can be use as air ambulance. Air Ambulance service is a board term that combines two meaning i.e. air transport with basic emergency medical services which is able to transport injured patients or sick patients to the healthcare facilities and from healthcare facilities. So, in other terms, we can say that it is basically like airlifting patients in case of emergencies. Here, we are focused to develop advance VTOL air ambulance which can be use in any condition and which are capable to carry out its work more precisely and efficiently.

International Journal of Micro Air Vehicles, 2015

This paper considers the dynamic simulation of an Unmanned Hybrid Flying Robot (UHFR) with main fuel engine in the middle to carry most of the weight and promises long flights. This configuration will increase the flight time of the unmanned copter for a given payload size as opposed to the traditional quad-copters, where only DC motors are used. A parametric study to investigate the effect of the propellers ratio (main rotor propeller diameter to secondary rotor propeller diameter), the angle of incidence of the main rotor and the twist angle of the main rotor blades on selected performance criteria of the UHFR is presented.

In the interest of promoting the integration of hybrid-electric power train into the aviation industry, research is being conducted by North Carolina State University to establish the feasibility of electrified power train in a small scale unmanned aerial vehicle (UAV). To accomplish this, it is first necessary to understand dynamics of the system to calculate the required power associated with each portions of the aircraft’s mission. Though research that has been conducted in the past based power required on published governing equations. However, in the interest of understand the system at its most fundamental level, it was deemed prudent to derive the governing equations from Newton’s second law. Using analytical dynamics, a rotating coordinate system was applied to the craft and a rotation matrix was applied to establish the interaction of the aircraft’s external forces based on its Euler angles with respect to the inertial frame. The equations associated with the values and interactions of the aircraft’s external forces were combined and manipulated to develop three governing parameters of maintaining flight during a typical UAV mission. These parameters are minimum airspeed, minimum power applied to the propeller, and the minimum roll angle required to accomplish a loitering maneuver with set radius about a target. The next step of this research will be development of an optimization algorithm to match power train components to apply the necessary conditions derived in this paper. Keywords: Unmanned Ariel Vehicle; UAV; Flight Dynamics; Analytical Dynamics. Glossary of Variables: kT – Thrust coefficient of the propeller ρ – Air density n – Rotational speed of the propeller (rev/s) D – Propeller’s Diameter (in) AP – Wing planform area CL – Wing coefficient of lift J – Propeller advance ratio (u/nD) AF – Aircraft frontal area CD – Sum of the parasitic (CDo) and lift induced (CDi) drag coefficients AR – Wing aspect ratio e – Oswald efficiency factor

Drones

This article presents a preliminary study on the development of a new concept for an unmanned aerial vehicle (UAV) design that incorporates the use of four wings and attached systems to improve overall performance, it being classified as a hybrid quadcopter (a quad tilt wing, tiltrotor UAV). By simulation, it was determined that the developed concept has significant advantages compared with a conventional quadcopter. By implementing this concept, an increase in the maximum speed by 59.21% can be obtained; it reduces time to complete a 10 km route by 36.4%, decreases the energy consumption by 37%, and increases the maximum travel distance by 56.9% at 30% remaining battery capacity. Additionally, the concept improves maneuverability by allowing turning movements to be performed by changing the angle of incidence of the rear wings, resulting in less energy consumption compared to traditional turning methods applied in the case of a conventional quadcopter.

2018

Transportation plays vital roles in lives. Its connections are associated with almost everything, from postal deliveries to multi-million cargo shipments. Currently, transportation of medical goods during critical need is limited to wheeled motor vehicles and manned aircrafts, which can be costly, slow, and sometimes impossible when emergency site is out of reach. Nowadays, drones revolutionise healthcare by transporting lifesaving medical supplies such as medical aids and blood. Unfortunately, with current technology, drone’s battery lifespan is a limitation that can hinder the delivery process. This paper describes our study that concerns with design of mechanism that prolongs drone’s battery life and offers effective delivery of medical first aids. The mechanism is attached to the drone and carries medical aids safely while decreasing the number of take-off and landing by deploying the kits from air to land (using parachute method). The main objective of this study is to desi...

Transstellar Journals, 2019

The present works discuss the design of an Air Ambulance Drone (AAD), anuncrewed aerial vehicle or UAV has the ability to perform an operation to handle numerous activities like vigilance, saving people, any unpleasant circumstancesand evacuation of wounded. The computations of Preliminary design of the present AAD had been summarized in detail, which includes the structural, propulsive, aerodynamic and performance aspects. The innovative AAD employs the numerous techniques that identify the survivor, final design and so on, had been deliberated in these researches. The design has been made in Fusion 360 software and is presented. The peculiarities, significance and applications of present AAD have been discussed.