Fixed Wing Research Articles

Lightweight aircraft design: Integrating biomechanics and algorithm optimization for drone construction using paper materials

Lightweight aircraft design emphasizes materials like composites, alloys, and advanced polymers to reduce weight while ensuring structural integrity. Streamlined aerodynamics, efficient propulsion systems, and optimized component layout further enhance performance. The purpose of this research is to develop an innovative aircraft design model for drones, integrating algorithm optimization techniques and lightweight materials to enhance the performance and efficiency of drones with the utilization of open-source software. We apply this structure to the construction of drones with fixed-wing (FW) and vertical take-off and landing (VTOL) configurations. The aircraft’s body is constructed using lightweight materials such as glass fiber fabric (Gff) and extruded polystyrene foam (XPS), employing a vacuum-assisted wet layup technique for fabrication. Multi-objective Co-evolving Ant Colony Optimization (MC-ACO) was used to improve the construction of drones with VTOL and FW capabilities. This strategy enabled it to be easier to achieve the trade-offs required for a generalist drone design, such as range, payload capabilities, and swarm operations, which were then evaluated against commercially available software to evaluate the effectiveness. Incorporating biomechanics into the design method permits higher consideration of user interaction with drones. The findings indicate that low-fidelity architecture is a suitable starting point for prototyping under limited time frames. The paper concludes with a discussion of the technical constraints of employing free software, as well as some practical concerns for flight testing drones with hybrid configurations.

The Effect of Air Density and Density Altitude on Landing Distance for Fixed Wing Aircraft

Abstract This thesis is concerned with studying the factors that effect on landing distance for fixed wing span aircrafts. These factors are divided related to types and characteristics of aircrafts, pilot’s technique, runway surface conditions, weathering conditions, and other environmental factors. Among these factors that were analysed in details both Air Density and Density Altitude to determine the effect of each factor on landing distance for fixed wing span aircrafts, what is the impact’s percentage of factor? Also, to determine the extent impact of each on the other, and the factors that affect them.

A Cost-Effective Solution for Measuring Vibration and Impact on Small Twin Engine Electric Fixed Wing UAV

A Cost-Effective Solution for Measuring Vibration and Impact on Small Twin Engine Electric Fixed Wing UAV

Motion Equations and Attitude Control in the Vertical Flight of a VTOL Bi-Rotor UAV: Part 2

This paper gathers the dynamical modeling of an unmanned aircraft and the design and simulation of the control system, allowing it to perform a Vertical Take-Off (VTOL) maneuver, a fixed-wing (FW) flight and a transition between the two configurations using two tilting rotors (Bi-Tilt). These Unmanned Aerial Vehicles (UAVs) operating in this configuration are categorized as Hybrid UAVs, for their capability of having a dual flight envelope: flying like a multi-rotor and navigating like a traditional fixed-wing aircraft, allowing the drone to perform complex missions where these two flight configurations are essential. This work exhibits the Bi-Rotor non-linear dynamics, valid for both flight configurations, the design of the control algorithm for stability and navigation, and a simulation of a complete flight mission.

HILS based Waypoint Simulation for Fixed Wing Unmanned Aerial Vehicle (UAV)

Hardware in loop simulation HILS-based waypoint simulation for fixed wing unmanned aerial vehicles is proposed in this paper. It uses an open-source arducopter as a flight controller, mission planner, and X-plane simulator. Waypoint simulation is carried out in the flight controller and executed in an X-plane simulator through a mission planner. A fixed wing unmanned aerial vehicle with an inverted T tail configuration has been chosen to study and validate waypoint flight control algorithms. The data transmission between mission planner and flight controller is done by serial protocol, whereas data exchange between X-plane and mission planner is done by User Datagram Protocol (UDP). APM mission planner is used as a machine interface to exchange data between the flight controller and the user. User inputs and flight gain parameters, both inner loop and outer loop, can be modified with the help of a mission planner. In addition to that, the mission planner provides a visual output representation of flight data and navigation algorithm.

Robust horizontal-plane formation control for small fixed-wing UAVs

The formation control problems of small fixed-wing(FW) unmanned aerial vehicles (UAVs) are investigated in this paper. By adopting a simplified aerodynamic force model and a cascade control structure, the horizontal motion of a FW UAV can be described as a linear system with uncertainties based on the feedback linearization technique. Thereafter, a novel robust formation protocol is proposed, which incorporates two components: the nominal controller and the robust filter-based compensator to restrain the influences of equivalent uncertainties. It turns out the formation error can converge to a sufficiently small neighborhood of the origin. The stability of the closed-loop system is proved in combination with classic Lyapunov-based arguments. Finally, field formation flight experiments on four small FW UAVs are carried out to demonstrate the effectiveness of the theoretical results.

Modelling and Attitude Control of an Agile Fixed Wing UAV based on Nonlinear Dynamic Inversion

An estimation model is key in the design and development of an unmanned aerial vehicle's control system. This work presents a complete methodology for modelling the dynamics of a fixed-wing UAV for aerobatic maneuvers. The UAV dynamic non-linear model considered uses total variables instead of a nominal values and perturbation values about certain trimmed conditions for conventional flight envelopes. Such modelling allows the expansion of the flight envelope of an unmanned aerial vehicle to cover the full range of the angle of attack. The quaternion formulation is used since it eliminates the nonlinearity of the aerodynamics due to Euler angles for high angle of attacks. The objective is to have a complete and accurate representation of a highly dynamic fixed wing UAV capable of making aerobatic maneuvers without encountering singularities. A set of controllers are then designed for the inner and outer loops for attitude control using nonlinear dynamic inversion in cascade with a PI controller. Simulations carried out show robust tracking of reference attitude angles.

COMPARISON OF SANDWICH COMPOSITE WING STRUCTURE WITH BALSA WOOD (CASE STUDY OF UAV AIRCRAFT FIXED WING VTOL VX-2)

UAV aircraft with a fixed wing configuration with multi-rotor are aircraft capable of vertical take-off and landing (VTOL). In designing the wing structure of aircraft, the weight factor and the strength of the wing structure are factors that need to be considered. The use of sandwich composite materials on UAV wings is expected to be able to meet the requirements of UAV aircraft, namely having a light weight, having high rigidity and strength. In this study, a comparative analysis the strength of the sandwich composite wing structure with the balsa wood wing of the UAV VTOL VX-2 aircraft was carried out. The steps taken are to model the composite wing structure of sandwiches and balsa wood using CATIA. Performing the process of structural analysis using ANSYS software. Both half-span models are subjected to lift and vertical take-off loads. From the analysis results, the sandwich composite wing (glass fiber skin with styrofoam core) is stronger than the balsa wood wing structure under vertical take off loads. While the VTOL rods, upper and lower spars of the balsa wood wing model are stronger than the sandwich structure under lift loads, but overall the sandwich wing structure is stronger than the balsa wood wing

Low-fidelity design optimization and development of a VTOL swarm UAV with an open-source framework

Hybrid configurations in aircraft design are highly favorable as they can achieve the appropriate trade-offs required to develop a generalized unmanned aerial system (UAS). Rapid prototyping of such systems at the student level is challenging because commercial software is expensive and difficult to interlink with other tools for creating a multi-disciplinary design. We address this challenge by conceptualizing an aircraft design framework made entirely of open-source software, libraries, and in-house code. We then use this framework to design an all-electric unmanned aerial system with transitioning Vertical Take-off and Landing (VTOL) and Fixed-Wing (FW) modes. The UAV is capable of long-range surveillance up to 100 Kilometers and carrying a maximum relief payload of 1 kg while operating in an ad-hoc wi-fi network with a swarm of similar UAVs. A low fidelity particle swarm optimization algorithm (PSO) and a comprehensive propulsion architecture is also incorporated and validated against commercial software. To validate the design, a prototype is fabricated from glass-fiber and XPS foam, integrated with appropriate sensors and tuned using ArduPilot software. The results show that low-fidelity design is a safe starting point for prototyping under constrained timelines. The study is concluded by discussing the technical challenges of using free software, and some practical considerations while flight testing a UAV with a hybrid configuration.

Nonlinear model predictive control and guidance for a propeller-tilting hybrid unmanned air vehicle

Hybrid unmanned aerial vehicles (UAVs) provide an interesting combination of the vertical takeoff and landing (VTOL) capabilities of rotary-wing (RW) and of the efficient forward flight of fixed-wing (FW) vehicles. The employed controllers must be able to handle the highly nonlinear dynamics and changing control authorities resulting from this combination, especially during the transition between the two flight modes. In this paper, a nonlinear model predictive control (MPC) structure is designed and applied to a tiltrotor convertible UAV. Full-flight envelope trajectory tracking and optimal exploitation of the aircraft’s VTOL and FW properties is achieved. A common approach is to design a set of stable controllers for various trim-points in the flight envelope and make use of Gain Scheduling (GS) or controller mixing, in order to select the appropriate control law for a given flight configuration. In this paper, a unified control approach is developed. A nonlinear MPC structure is designed and applied to a tiltrotor convertible UAV whose nonlinear model is derived and presented. Thus, full-flight envelope trajectory tracking and optimal exploitation of the aircraft’s VTOL and FW properties are achieved, without the need for controller switching or scheduling policies. The proposed multi-stage control allocation handles the changing control authorities of the actuators in a continuous manner and efficiently distributes the required control actions between propellers, tilt servos and control-surfaces. The feasibility and performance of this novel control approach are successfully evaluated in real-world flight experiments. Simulation results for comparison with state-of-the-art approaches are presented.

Software in Loop Simulation based Waypoint Navigation for Fixed Wing UAV

Software in loop simulation (SILS) based waypoint navigation test platform being presented in this paper for fixed wing unmanned aerial vehicle. The proposed platform helps to test waypoint navigation algorithm before implementing into real time environment. Matlab/Simulink and X-plane flight simulator are chosen for the proposed platform. The interface between these two platforms are done by using user datagram protocol (UDP). The waypoint navigation which is to be tested is run in Matlab/Simulink environment where as fixed wing model runs in X-plane simulator. Inverted T tail fixed wing unmanned aerial vehicle configuration is chosen for this research work to verify both its inner loop (attitude control) and outer loop (navigation control). Navigation algorithm executed in Matlab/Simulink compares difference between current and desired latitude longitude position to command flight simulator to reach its desired waypoint. Navigation towards a desired waypoint will be achieved by varying inner loop attitude command of an unmanned aerial vehicle. Finally results are observed and performances are verified in X-plane simulator.

Flight Test Evaluation for Tilt Rotor Unmanned Aerial Vehicle Development

Tiltrotor Unmanned Aerial Vehicle (UAV) is type of UAV that combine fixed wing (FW) and multirotor (VTOL) configuration in order to be able to perform instant transition from one configuration to another. Tiltrotor UAV has advantage to perform takeoff and landing from limited space such as plantation farm, forest, and residential area. Tiltrotor also can carry various mission since it has 2 configuration such as cargo drone, safer payload dropping, and mapping. In this research tiltrotor UAV designed with ruddervator (V-Tail) configuration with 3 motors in total, 2 motors placed on main wing with tilting capability and 1 motor placed at the end of fuselage as pitch controller in VTOL mode. Test flight will be conducted and evaluated to test UAV capability in hovering and transition from one mode to another

DESIGN, PERFORMANCE ANALYSIS OF WING, AND MANUFACTURING OF FIXED WING HAND LAUNCH UNMANNED AERIAL VEHICLE

This paper concentrates on the design, analysis, and development of fixed-wing hand launch unmanned aerial vehicle (UAV). This flight can able to carry the payloads of 0.8. The design process involves the conceptual, preliminary, and detailed design. This paper involves the investigation of the aerodynamic characteristics over the wing to enhance the aerodynamic design of the UAV. This analysis includes estimating the best gliding ratio to increase the flight mission and attain the maximum altitude. This simulation will be performed for subsonic flow with Mach number 0.04202(14.3m/s). The manufacturing of the UAV is done using composite materials like glass fiber of both (1mm and 2 mm) thickness, carbon fiber of 2mm, and carbon rod is used for connecting the empennage to the fuselage. The detailed design has been done in CATIA V5 and the analysis of the wing has been done using XFLR, ANSYS (fluent).

DESIGN AND EXPERIMENT OF A HIGH PAYLOAD FIXED WING VTOL UAV SYSTEM FOR EMERGENCY RESPONSE

Abstract. With the development of UAV technologies, the advantages of hybrid VTOL UAV have been realized and taken in emergency response. But, former hybrid VTOL UAV is lack of capacities on payload and endurance, which restrict the integration of multiple sensors. In this paper, a high payload fixed wing VTOL UAV, which has 20 kg payload and more than 3 hours endurance, is used to design a UAV system for emergency response. Multiple sensors including an optronics pod, PhaseOne IXM-100 camera, high accuracy inertial navigation system and three-axis stable head are integrated with it. Based on this, specific processing software is developed to process the video data and image which could meet the requirements of emergency response in different stages. Experiment results shown that the precision of mosaic image is about 10m and the precision of orthoimage is about 1m. This work could be reference for the design and practice of UAV system with multiple sensors.

OBLIQUE IMAGES AND DIRECT PHOTOGRAMMETRY WITH A FIXED WING PLATFORM: FIRST TEST AND RESULTS IN HIERAPOLIS OF PHRYGIA (TK)

Abstract. The complex archaeological site documentation benefits for a long time now from the aerial point of view and remote sensing methods. Moreover, the recent research on UAV photogrammetry platform equipment and flight planning actively contribute in this sense for a scaling improvement and cost-benefits balance. Frequently, the experiences on articulated topographic profiles in archaeological excavations require not only a multi-sensor approach but also and above all a multiscale one. According to this line, in a general time-cost ration framework, the geometric content of the generated DSMs should be complete of nadir and oblique point of view for the accurate 3D reconstruction of both upstanding buildings and excavations. In the same way, also the radiometric content closely depends on sensor payload quality and is strictly affected by excavation site condition, related to the site material and light. In this research, carried out in the impressive archaeological site of the ancient city of Hierapolis in Phrygia (Turkey) in the autumn 2019 campaign, the main goal was to evaluate and validate the overall performance of a novel UAV fix-wing ultralight platform with onboard GNSS receiver for RTK/PPK processing of cameras positioning and with the possibility of oblique images capturing. The expected contribute in terms of the acquisition, processing time, radiometric enhancement and geometry 3D reconstruction will be explored with preliminary test and outcomes, and with the results of the high-scale DSM and orthoimage generation of the complete Hierapolis site.

Design and performance analyses of a fixed wing battery VTOL UAV

The objective of this paper is to explain the design steps and performance analyses including energy consumption of a fixed-wing (FW) vertical take-off and landing (VTOL) unmanned air vehicle (UAV). The vehicle is designed from the beginning with the goal for low take-off 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 take-off, 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 take-off 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 three-dimensional printers and flight tests of VTOL-FW UAV will be performed as a future work.

Optimal design of Vertical-Taking-Off-and-Landing UAV wing using multilevel approach

In order to overcome the propre disadvantages of FW(Fixed-Wing) and VTOL(Vertical-Taking-Off-and-Landing) UAV (Unmanned Aerial Vehicle) and extend its application, the hybrid drone is invested more in recent years by researchers and several classifications are developed on the part of dual system. In this article, an innovative hybrid UAV is raised and studied by introducing the canard configuration that is coupled with conventional delta wing as well as winglet structure. Profited by Computational Fluid Dynamics (CFD) and Response Surface Method (RSM), a multilevel optimization approach is practically presented and concerned in terms of cruise flight mode: adopted by an experienced-based distribution strategy, the total lift object is respectively assigned into the delta wing (90–95%) and canard wing(5–10%) which is applied into a two-step optimization: the first optimization problem is solved only with the parameters concerned with delta wing afterwards the second optimization is successively concluded to develop the canard configuration considering the optimized delta wing conception. Above all, the optimal conceptual design of the delta and canard wing is realized by achieving the lift goal with less drag performance in cruise mode.

Editorial for the CEAS Aeronautical Journal special edition on Smart Fixed Wing Aircraft, WP 1.2 “Load Control”

This special issue of the CEAS Aeronautical Journal summarizes articles describing results of the work package “Load Control”, which was part of the Smart Fixed Wing Aircraft (SFWA) project, taking place in the framework of the European Clean Sky research programme. The editorial first gives a short overview over the Clean Sky framework and the SFWA project. Second, the articles of the special issue are shortly introduced.

Investigation of a Cruising Fixed Wing Mini Unmanned Aerial Vehicle Performance Optimization

The applications of unmanned aerial vehicles have been extended through the recent decades and they are utilized for both civil and military applications. The urge to utilize unmanned aerial vehicles for civil purposes has elevated researchers and industries interest towards the mini unmanned aerial vehicle (MUAV) category due to its suitable configurations and capabilities for multidisciplinary civil purposes. This study is an effort to further enhance the aerodynamic efficiency of MUAVs through a parametric study of the wing and proposing an innovative bioinspired wing design. The research is conducted utilizing numerical simulation and experimental validation. This research provides a better understanding of different wing parameter(s) effect on the aerodynamic performance of the wing and mini unmanned aerial vehicles. A new wing configuration is designed, implemented and evaluated. The wing is named as Alpine since it is inspired by biomimicry of alpine swift bird. Evaluation of the new wing geometry shows that the Alpine wing geometry performs 35.9% more efficient compared to an existing wing with similar wing area. Hence, the aerodynamic efficiency optimization is achieved for the Alpine wing which helps to enhance the performance of MUAVs.

UAVs for Wilderness Search and Rescue: Real-World Considerations and Technology Roadmap for Fixed Wing UAVs

Wilderness search and rescue is predominantly conducted by ground based teams, however its limitations have encouraged the use of alternative approaches. Aerial search and rescue provides complementary capabilities as it has a higher areal coverage rate and can survey challenging terrain that is not easily accessible. Helicopters and other manned aerial vehicles dominate aerial search, but disadvantages, such as the need for highly trained personnel, slow response time, and high capital requirements, limit their use. Unmanned aerial vehicles (UAVs) capture the benefits of helicopters while overcoming many of the associated drawbacks that limit their use for wilderness search and rescue. Here we demonstrate the need for UAVs in wilderness search and rescue. We compare the two main types of UAVs—fixed wing and rotary—along three performance factors, including flight range, image quality, and degree of control over the flight path. Theoretical and practical considerations for fixed wing UAVs are explored. Finally, we present practical technology ideas to improve the utility of both fixed wing and rotary UAVs. This work offers an introduction to aerial search and rescue with UAVs, assesses real-world tradeoffs between fixed wing and rotary UAVs, and presents a roadmap for further technology development to advance this technology into the field. KEYWORDS: UAVs, fixed wing UAVs, rotary UAVs, wilderness search and rescue, aerial search and rescue