Design Of Unmanned Aerial Vehicle Research Articles

Nonlinear Lifting-Line Model using a Vector Formulation of the Unsteady Kutta-Joukowski Theorem

In this paper, a vector form of the unsteady Kutta-Joukowski theorem is derived and then used in the formulation of a general Lifting-Line Model capable of analysing a wide range of engineering problems of interest. The model is applicable to investigating lifting surfaces having low to moderate sweep, dihedral, out-of-plane features such as winglets, in both steady-state and unsteady cases. It features corrections of the span-wise circulation distribution based on available two-dimensional aerofoil experimental data, and stable wake relaxation through fictitious time marching. Potential applications include the conceptual and initial design of low-speed Unmanned Aerial Vehicles, the study of flapping flight or Wind Turbine blade design and analysis. Several verification and validation cases are presented, showing good agreement with experimental data and widely-used computational methods.

Optimized Trajectory Design in UAV Based Cellular Networks for 3D Users: A Double Q-Learning Approach

In this paper, the problem of trajectory design of unmanned aerial vehicles (UAVs) for maximizing the number of satisfied users is studied in a UAV based cellular network where the UAV works as a flying base station that serves users, and the user indicates its satisfaction in terms of completion of its data request within an allowable maximum waiting time. The trajectory design is formulated as an optimization problem whose goal is to maximize the number of satisfied users. To solve this problem, a machine learning framework based on double Q-learning algorithm is proposed. The algorithm enables the UAV to find the optimal trajectory that maximizes the number of satisfied users. Compared to the traditional learning algorithms, such as Q-learning that selects and evaluates the action using the same Q-table, the proposed algorithm can decouple the selection from the evaluation, therefore avoid overestimation which leads to sub-optimal policies. Simulation results show that the proposed algorithm can achieve up to 19.4% and 14.1% gains in terms of the number of satisfied users compared to random algorithm and Q-learning algorithm.

UAV-Assisted Emergency Networks in Disasters

Reliable and flexible emergency communication is a key challenge for search and rescue in the event of disasters, especially for the case when base stations are no longer functioning. Unmanned aerial vehicle (UAV)-assisted networking is emerging as a promising method to establish emergency networks. In this article, a unified framework for a UAV-assisted emergency network is established in disasters. First, the trajectory and scheduling of UAVs are jointly optimized to provide wireless service to ground devices with surviving BSs. Then the transceiver design of UAV and establishment of multihop ground device-to-device communication are studied to extend the wireless coverage of UAV. In addition, multihop UAV relaying is added to realize information exchange between the disaster areas and outside through optimizing the hovering positions of UAVs. Simulation results are presented to show the effectiveness of these three schemes. Finally, open research issues and challenges are discussed.

LQG controller design for a quadrotor UAV based on particle swarm optimisation

This paper deals with the modelling and the linear quadratic Gaussian (LQG) control design of a quadrotor unmanned aerial vehicle (UAV) using different particle swarm optimisation (PSO) variants. Such a PSO-designed LQG controller is optimised in order to stabilise the position and the heading of the studied vertical take-off and landing (VTOL) quadrotor. Both canonical and recent variants of PSO algorithm, with linearly decreasing of inertia weight (PSO-In) and perturbed updating strategy (PSO-gbest), are considered for the systematically design and tuning of the LQG weighting matrices. These effective control parameters of the LQG approach represent the decision variables of the PSO-based LQG optimisation problem. Such an optimisation problem is formulated to minimise various performance time-domain criteria, like the integral of absolute error (IAE) and the maximum overshoot (MO) index, under nonlinear constraints related to the step responses of the closed-loop quadrotor dynamics. All proposed PSO algorithms are compared with each other and with the well known harmony search algorithm (HSA) and water cycle algorithm (WCA) metaheuristics for the stabilisation problem of the position and heading dynamics of the VTOL drone. Demonstrative simulation results are carried out in order to show the effectiveness of the proposed PSO variants-tuned LQG control approach.

LQG controller design for a quadrotor UAV based on particle swarm optimisation

This paper deals with the modelling and the linear quadratic Gaussian (LQG) control design of a quadrotor unmanned aerial vehicle (UAV) using different particle swarm optimisation (PSO) variants. Such a PSO-designed LQG controller is optimised in order to stabilise the position and the heading of the studied vertical take-off and landing (VTOL) quadrotor. Both canonical and recent variants of PSO algorithm, with linearly decreasing of inertia weight (PSO-In) and perturbed updating strategy (PSO-gbest), are considered for the systematically design and tuning of the LQG weighting matrices. These effective control parameters of the LQG approach represent the decision variables of the PSO-based LQG optimisation problem. Such an optimisation problem is formulated to minimise various performance time-domain criteria, like the integral of absolute error (IAE) and the maximum overshoot (MO) index, under nonlinear constraints related to the step responses of the closed-loop quadrotor dynamics. All proposed PSO algorithms are compared with each other and with the well known harmony search algorithm (HSA) and water cycle algorithm (WCA) metaheuristics for the stabilisation problem of the position and heading dynamics of the VTOL drone. Demonstrative simulation results are carried out in order to show the effectiveness of the proposed PSO variants-tuned LQG control approach.

Analysis and Optimization of Unmanned Aerial Vehicle Swarms in Logistics: An Intelligent Delivery Platform

Deploying unmanned aerial vehicle (UAV) swarms in delivery systems are still in its infancy with regard to the technology, safety, and aviation rules and regulations. Optimal use of UAVs in dynamic environments is important in many aspects, e.g., increasing efficacy and reducing the air traffic, resulting in a safer environment, and it requires new techniques and robust approaches based on the capabilities of UAVs and constraints. This paper analyzes several delivery schemes within a platform, such as delivery with and without using air highways and delivery using a hybrid scheme along with several delivery methods (i.e., optimal, premium, and first-in first-out) to explore the use of UAV swarms as part of the logistics operations. In this platform, a dimension reduction technique, “dynamic multiple assignments in multi-dimensional space,” and several other new techniques along with Hungarian and cross-entropy Monte Carlo techniques are forged together to assign tasks and plan 3D routes dynamically. This particular approach is performed in such a way that UAV swarms in several warehouses are deployed optimally given the delivery scheme, method, and constraints. Several scenarios are tested on the simulator using small and big data sets. The results show that the distribution and the characteristics of data sets and constraints affect the decision on choosing the optimal delivery scheme and the method. The findings are expected to guide the aviation authorities in their decisions before dictating rules and regulations regarding effective, efficient, and safe use of UAVs. Furthermore, the companies that produce UAVs are going to take the demonstrated results into account for their functional design of UAVs along with other companies that aim to deliver their products using UAVs. Additionally, private industries, logistics operators, and municipalities are expected to benefit from the potential adoption of the simulator in strategic decisions before embarking on the practical implementation of UAV delivery systems.

Подход к формированию технического облика беспилотного воздушного судна

The article focuses upon the substantiation of efficiency criterion at formation of technical shape of an unmanned aerial vehicles. The authors analyze the criteria of efficiency of applying unmanned aerial vehicles, such as relative weight, flight time, unit cost of flight and life cycle cost and provide reasoning for the necessity of using the combined criterion considering economic and functional efficiency. Variable, non-variable and uncertain parameters characterizing an unmanned aerial vehicles are formulated. The optimization problem of determining the technical appearance is considered. The process of technical appearance formation is based on three interrelated processes: aerodynamic arrangement; volume-mass arrangement and structural-force arrangement. The purpose of the technical appearance is to find such interrelated values of the parameters of an unmanned aerial vehicle (UAV), which ensure the achievement of a compromise between the requirements while ensuring the extreme of any selected generalized criterion of optimality, for example, the minimum cost of the life cycle of the finished product - the aircraft. This criterion is one of the most general criteria for aircraft efficiency, but it is difficult to calculate it at an early stage of development. Therefore, in practice, it uses other criteria that are close to the cost of the life cycle stages. The specific feature of the process of UAV glare formation, as well as any complex technical system, is a large number of unknown and high degree of uncertainty, especially at the early stages of development. To overcome this uncertainty, the design process is divided into a series of successive iterative stages. The task of searching for the most advantageous combination of UAV design parameters depending on its purpose can be considered as the task of searching for the extremum of some target function – optimization task. Based on the conducted substantiation the authors propose the technique of defining the rational appearance of an unmanned aerial vehicles, considering the accepted restrictions.

Simultaneous Design of a Small UAV (Unmanned Aerial Vehicle) Flight Control System and Lateral State Space Model

In this study, the design of a small unmanned aerial vehicle (UAV) and the real-time application of the flight control system and lateral state-space model were investigated. For this purpose, an UAV production was carried out, which was assembled from different locations at certain intervals to the wing and tail set body and moved back and forth before the flight. An autopilot was then used which allowed the change of P, I, D values ​​between 1 and 100. First of all, we obtained a lateral state space model of the UAV and obtained a simulation model of Unmanned Aerial Vehicle. At the same time, the block diagram of the autopilot system was extracted and modeled in MATLAB / Simulink environment. Afterwards, SPSA developed a cost function consisting of ascent, seating time and maximum overrun, and the Unmanned Aircraft and autopilot system were redesigned simultaneously to minimize this cost function. High performance is easily observed in simulation responses and real flights.

Design and Simulation of Eight-Rotor Unmanned Aerial Vehicle Based on Hybrid Control System

In order to control the position and attitude of unmanned aerial vehicle (UAV) better in different environments, this study proposed a hybrid control system with backstepping and PID method for eight-rotor UAV in different flight conditions and designed a switching method based on altitude and attitude angle of UAV. The switched process of hybrid controller while UAV taking off, landing, and disturbance under the gust is verified in MATLAB/Simulink. A set of appropriate controllers always matches to the flight of UAV in different circumstances, which can speed up the system response and reduce the steady-state error to improve stability. The simulation results show that the hybrid control system can suppress the drift efficiently under gusts, enhance the dynamic performance and stability of the system, and meet the position and attitude of flight control requirements.

Challenge and Advantage of Materials in Design and Fabrication of Composite UAV

Unmanned Aerial Vehicles (UAVs) is constructed with composite materials, including its aerodynamic surfaces wings, horizontal stabilizer, and rudder. Three main constituents of our model is Kevlar 49, carbon fibre, glass fibre. KALPANA-1 is a pusher type, tail dragger, fixed wing radio controlled medium range remotely operated composite aircraft. This is designed for Aerial surveillance & reconnaissance. It is a kind of drone which has capability of carrying 2kg of operational payload as surveillance camera and its gimbal mount unit. It can be equipped with on-board sensors for weather monitoring as civilian use of UAV. It has a carbon frame body which makes it hassle to work in all-weather environment, protecting its electronics and payload from external entities. KEVLAR-49 is reinforced at the bottom part of the fuselage to overcome hard landing & impacts. The main disadvantage of using carbon fibre is that it partially shelled the RC signals so we fixed our receiver outside of the fuselage. For camera mounting purpose a duct made in front side of fuselage. It can use as other diplomatic mission as mounting camera and robotic arm for weight lifting mechanism. Some further upgrading two semi ducts at two side of the front face of the fuselage for steerable camera mounting. Aircraft using single electrical propulsive system and large wings which helps it for a long range, good endurance and smooth steady flight. Composite materials don’t break easily, but that makes it hard to analyses if the interior structure has been damaged at all. In contrast, aluminum bends and dents easily, making it easy to detect structural damage; the same damage is much harder to detect with composite structures. Repairs can also be more difficult when a composite surface is damaged. Finally, composite materials can be expensive, but the high initial costs are typically offset by long-term cost savings and life cycle more compare to cost of material.

A Design of Rapid Deployment Small Unmanned Aerial Vehicles

In view of the problems of slow deployment and high rescue costs when encountering sudden emergencies, a kind of rapid deployment small unmanned aerial vehicles was proposed. According to existing unmanned aerial vehicles technology, the principle of the unmanned aerial vehicles structure was analyzed and designed. Moreover, the launching device and the body protection cover were designed for the launching process. This unmanned aerial vehicle will play an important role in rapid disaster relief, exploration and large-scale data collection.

VTOL UAV Transition Maneuver Using Incremental Nonlinear Dynamic Inversion

The paper seeks to study the control system design of a novel unmanned aerial vehicle (UAV). The UAV is capable of vertical takeoff and landing (VTOL), transition flight and cruising via the technique of direct force control. The incremental nonlinear dynamic inversion (INDI) approach is adopted for the 6-DOF nonlinear and nonaffine control of the UAV. Based on the INDI control law, a method of two-layer cascaded optimal control allocation is proposed to handle the redundant and coupled control variables. For the weight selection in optimal control allocation, a dynamic weight strategy is proposed. This strategy can adjust the weight of the objective function according to the flight states and mission requirements, thus determining the optimizing direction and ensuring the rationality of the allocation results. Simulation results indicate that the UAV can track the target trajectory accurately and exhibit continuous maneuverability in transition flight.

UAV aerodynamic design involving genetic algorithm and artificial neural network for wing preliminary computation

In this paper, the aerodynamic design procedure of a mini unmanned aerial vehicle, intended to perform aerial reconnaissance at low altitude and low Reynolds number, was summarized. Design process was divided into two major parts: conceptual design phase and preliminary design phase. During the conceptual design, classical procedures and data from similar unmanned aerial vehicles already designed were employed to define the requirements related to unmanned aerial vehicle design. The preliminary design was performed using panel method where the emphasis was given on the design of the UAV wing, fuselage design and empennage. The wing planform parameters were determined through an aerodynamic optimization process using both genetic algorithms and artificial neural networks. Finally an aerodynamic analysis using panel method, Computational Fluid Dynamic simulations and wind tunnel testing was carried out. Unmanned aerial vehicle full configuration design process was consistent, where a comparison between the final obtained results was carried out and showed an agreement in terms of lift, drag and pitch moment coefficients.

A numerical study into the longitudinal dynamic stability of the tailless aircraft

PurposeThe purpose of this research is a study into a mathematical approach of a tailless aircraft dynamic stability analysis. This research is focused on investigation of influence of elevons (elevator) on stability derivatives and consequently on the aircraft longitudinal dynamic stability. The main research question is to determine whether this impact should be taken into account on the conceptual and preliminary stage of the analysis of the longitudinal dynamic stability.Design/methodology/approachAerodynamic coefficients and longitudinal stability derivatives were computed by Panukl (panel methods). The analysis of the dynamic stability of the tailless aircraft was made by the Matlab code and SDSA package.FindingsThe main result of the research is a comparison of the dynamic stability of the tailless aircraft for different approaches, with and without the impact of elevator deflection on the trim drag and stability derivatives.Research limitations/implicationsThis paper presents research that mostly should be considered on the preliminary stage of aircraft design and dynamic stability analysis. The impact of elevons deflection on the aircraft moment of inertia has been omitted.Practical implicationsThe results of this research will be useful for the further design of small tailless unmanned aerial vehicles (UAVs).Originality/valueThis research reveals that in case of the analysis of small tailless UAVs, the impact of elevons deflection on stability derivatives is bigger than the impact of a Mach number. This impact should be taken into consideration, especially for a phugoid mode.

Conceptual design of small unmanned aerial vehicle with proton exchange membrane fuel cell system for long endurance mission

Energy is the most important factor determining the performance of a small unmanned aerial vehicle (UAV) with a proton exchange membrane fuel cell (PEMFC) system because the mission capability of a small UAV is determined by the energy of its power source. For this reason, in this study, a new conceptual design process for a small UAV with a PEMFC system was investigated with respect to energy. The mission profile and requirements for the small UAV were first determined. Five reference aircrafts were selected based on mission requirements, and some input parameters were assumed for conducting analyses based on these reference aircrafts. A constraint analysis was conducted to determine wing loading and power-to-weight ratios. The wing loading and power-to-weight ratios were used for mission analysis to determine the design specifications of the small UAV. The effect of gravimetric power and energy densities of the PEMFC system on the designed UAV endurance was also investigated. Finally, performance targets of the PEMFC system were suggested for a long endurance mission of the small UAV. This study investigated a conceptual design process that can be widely used for the conceptual design of small UAVs with PEMFC systems.

Mission Analysis and Operational Optimization of Adaptive Cycle Microturbofan Engine in Surveillance and Firefighting Scenarios

The current work focuses on mission-based evaluation of a novel engine architecture arising from the conversion of a microturbojet to a microturbofan via introduction of a variable speed fan and bypass nozzle. The solution significantly improves maximum thrust by 260%, reduces fuel consumption by as much as 60% through maintaining the core independently running at its optimum, and enables a wider operational range, all the meanwhile preserving a simple single spool configuration. Particularly, the introduction of a variable-speed fan enables real-time optimization for both high-speed cruise and low-speed loitering. In order to characterize the performance of the adaptive cycle engine with increased number of controls (engine speed, gear ratio, bypass opening), a component map-based thermodynamic study is used to contrast it against other similar propulsion systems with incrementally reduced input variables. In the following, a shortest path-based optimization is conducted over the locally minimum fuel consumption operating points, based on a set of gradient driven connectivity constraints for changes in gear ratio and bypass nozzle area. The resultant state transition graphs provide global optimum for fuel consumption at a thrust range in a given altitude and Mach flight envelope. Then, the engine model is coupled to a flight mechanics solver supplied with a conceptual design for a representative multipurpose unmanned aerial vehicle (UAV). Finally, the associated mission benefits are demonstrated in surveillance and firefighting scenarios.

Systematic design methodology for development and flight testing of a variable pitch quadrotor biplane VTOL UAV for payload delivery

This paper discusses the conceptual design and proof-of-concept flight demonstration of a novel variable pitch quadrotor biplane Unmanned Aerial Vehicle concept for payload delivery. The proposed design combines vertical take-off and landing (VTOL), precise hover capabilities of a quadrotor helicopter and high range, endurance and high forward cruise speed characteristics of a fixed wing aircraft. The proposed methodology is described by taking an example of a VTOL Unmanned Aerial Vehicle (UAV) for a mission requirement of carrying and delivering 6 kg payload to a destination at 16 km from the point of origin. First, the design of proprotors is carried out using a physics based modified Blade Element Momentum Theory (BEMT) analysis, which is validated using experimental data generated for the purpose. Proprotors have conflicting requirement for optimal hover and forward flight performance and a compromise solution has to be chosen. Next, the biplane wings are designed using simple lifting line theory. The airframe design is followed by power plant selection and transmission design. Finally, weight estimation is carried out to complete the design process. The proprotor design with 24° preset angle and −24∘ twist is found to be suitable for the current mission profile, based on 70% weightage to forward flight and 30% weightage to hovering flight conditions. A reduction in operating RPM of the proprotors from 3200 during hover to 2000 during forward flight results in 27% increase in proprotor efficiency. The VTOL UAV design proposed in this paper is also predicted to consume 64% less power in airplane mode compared to the quadrotor mode, thereby establishing the benefit of this hybrid concept. A proof-of-concept scaled prototype is fabricated using commercial-off-the-shelf parts and a Proportional Integral Derivative (PID) controller is developed and implemented on open source PixHawk autopilot board to enable stable hovering flight and attitude tracking during hover flight tests.

RESEARCH FEATURES OF AEROELASTIC OSCILLATIONS OF UNMANNED AERIAL VEHICLES WITH ELECTRIC ACTUATOR OF RUDDERS

Designing a modern flight vehicle is associated with the need to solve many scientific and technical problems. These tasks include the prevention of insecure self-oscillations in flight, taking into account the elasticity of the structure. These problems relate to dynamic aeroelasticity, a science that examines the interaction of an elastic structure (at its oscillation) with an air flow. Maneuverable unmanned aerial vehicles (UAVs) are considered. Since UAVs are essentially not used without an automatic control system (ACS), its presence must be taken into account when considering the vibrations of an elastic structure in flight. The influence of the elasticity of UAV design on the operation of ACS in flight is manifested in the possibility of self-oscillations in the loop "elastic UAV – ACS". Self-oscillations lead to disruption of normal operation of the onboard equipment or its failure. The complexity of the problem requires its consideration at almost all stages of UAV’s development, including the creation of a prototype and testing. The computational and experimental studies of the characteristics of elastic oscillations in the UAV flight of the cross-shaped scheme are considered. The features of these UAVs (options with a modular design, the nonlinearity of the airframe, rudders, ACS, and others) due to a significant amount of testing that is the basis for the calculations. Electric actuators have a small continuous operation time, and resource use, there are gearboxes with a large gear ratio and backlashes. This determines the dependence of the rotation rigidity of the rudders on the amplitude and frequency, as well as a significant increase in the total moments of inertia. The technique of bench experiment with obtaining data to assess the boundaries of the flutter and the boundaries of the stability of the loop "elastic UAV – ACS" is given. The questions of improvement of the stabilization system of UAV required for the study of its stability at frequencies of elastic oscillations are considered, as well as the evaluation of the limiting cycles of self-oscillations is given.

Wireless sensor network development: Targeting and control system for semi-ballistic vehicle for rapid and precise search and rescue applications

This paper considers the vast development in the technology of sensor such as embedded system, Global Position- ing System (GPS) wireless communications and wireless sensor applications. In recent years an efsicient design of a Wireless Sensor Network has become a leading area of research for semi-ballistic unmanned Aerial Vehicle (UAV). A network of sensor is a device that responds and detects some type of input from both the physical or environmental conditions, such as pressure, heat, light, etc. The output of the sensor is generally an electrical con- ditions that is transmitted to controller for further processing. Wireless sensor network has been widely used and its design has become an important sield of control engineering in addition to providing real-time communication system in surveillance, tracking, and monitoring applications. In this paper, development of wireless sensor net- work for targeting and control system of a semi-ballistic UAV for rapid and precise search and rescue operations is being presented and discussed. The developed system is composed of two sections: Air Section and Ground Section. The Air Section consists of Magnetic Compass Sensor, Micro-Electro-Mechanical Sensors (MEMs), GPS, Camera, Servo Motor and Parachute Controllers and the latter is consist of Video Recording, Receiver and Moni- toring. The system will helps in locating the exact location at centralized level. In effect, it increases the response efsiciency. Furthermore, this system helps in controlling and protecting naval, ground and arm forces in any lo- cation for the search and rescue operations. The wireless sensor network system is capable of collecting, storing and analyzing data from several devices embedded in the vehicle. Results show that the multi-sensor fusion and integration plays a critical role in the overall design and performance enhancement of the semi-ballistic unmanned aerial vehicle being developed.

An anti-collision four-axis UAV design based on PID fuzzy controller

The hardware of the four-axis unmanned aerial vehicle (UAV) is based on ARM SCM32f103, and the hardware is designed and manufactured independently. The UAV has the characteristics of high reliability, good stability and strong resistance to damage. The circuit of the UAV includes a gyroscope accelerometer module, an infrared module, a Bluetooth serial port module, a barometer module, and a PWM output module. In terms of control algorithms, a four- axis motion model was established using MATLAB/SIMULINK, and an optimal algorithm was derived for model simulation calculations. That is, the PID fuzzy controller is designed and the fuzzy controller is used to precisely control the speed of the motor. The four-axle UAV judges the damaged propeller through the abrupt change of attitude of the four-axle UAV and enters the fault handling mode. For different destruction situations, the four-axle UAV use the existing undamaged paddles to make the UAV still stable in the sky and landing slowly to protect the UAV, even if one paddle, two paddles, or three paddles are damaged.