Query: uav  detail design

title: U Model Based Sliding Mode Controller Design for Quadrotor UAV Control Systems
abstract: This paper proposes a U model based fault tolerant controller design method in order to ensure the unmanned aerial vehicle (UAV) flight performance when subject to the actuator failures. Depending on the decoupled quadrotor model, this paper presents a sliding mode control method based on U model in detail and realizes fault tolerant control for the quadrotor UAV with the stability theory and simulation experiment verifications. The results show that the new controller designed by using the U model method can simplify the controller design process which has good fault tolerant characteristics when actuator faults occur compared with the traditional method.

title: Design of Multi platforms Sensor Management System for UAV Autonomous Detection and Perception
abstract: Aiming at the requirements of multiple UAVs self organizing management and cooperative detection in confrontation environment, an open multi platforms sensor management system is proposed. The implementation structure of the system is described in detail, and the design of functional modules, management strategies and implementation methods are given. The scheme can respond to various types and levels of avionics tasks, and can comprehensively consider and balance the system's many task requirements and various service requests, so that the overall performance of the system can be optimized. It is proved that the self organizing management and intelligent task assignment of multiple UAVs can be realized and the autonomous detection ability and task completion rate can be effectively improved in this scheme.

title: Design of a Specialized UAV Platform for the Discharge of a Fire Extinguishing Capsule Acronym
abstract: This thesis deals with the design of an unmanned multirotor aircraft system specialized for autonomous detection and localization of fires from onboard sensors, and the task of fast and effective fire extinguishment. The main part of this thesis focuses on the detection of fires in thermal images and their localization in the world using an onboard depth camera. The localized fires are used to optimally position the unmanned aircraft in order to effectively discharge an ampoule filled with a fire extinguishant from an onboard launcher. The developed methods are analyzed in detail and their performance is evaluated in simulation scenarios as well as in real world experiments. The included quantitative and qualitative analysis verifies the feasibility and robustness of the system.

title: Design and Development of a Fixed Wing Unmanned Aerial Vehicle (UAV) Prototype for Crop Spraying
abstract: The aim of this paper is to design and develop a fixed wing Unmanned Aerial Vehicle (UAV) prototype for crop spraying. The need to implement UAVs for crop spraying, literature review, design methodology, fabrication and testing of the prototype have been presented. Design methodologies of fixed wing UAVs, agricultural applications of UAVs as well as various methods of control of UAVs have been studied and presented in the literature review. The design methodology for this project has been elaborated in the third section. The mission requirements and the conceptual design have been elaborated first, followed by the preliminary design, which involves airfoil selection, aerodynamic design of wing and selection of the components of the propulsion system. Analysis in XFLR5 was performed for airfoil selection, wing design and tail design. The detail design expounds the structural design and analysis of wing and tail, the fuselage configuration and the spraying system to be implemented. The fabrication and testing of the prototype, its observations and results have been discussed in the last two sections.  UAV, fixed wing, crop spraying, design, analysis, fabrication, testing

title: Design of Lateral Flight Control Law for a Double Vertical Tail UAV
abstract: Flight control system plays a vital role in controlling the aircraft while flight control law is the core of the flight control system. In this paper, an efficient and reliable control law is proposed and introduced in detail for conventional aerodynamic layout UAVs with double vertical tail. A six degree freedom nonlinear model and linearization of the model are introduced firstly. On this basis, the control law is designed according to the root locus method. The simulation results are provided to demonstrate the effectiveness of the proposed scheme. Furthermore, in order to improve the control precision, robustness verification is described on the condition of gravity center shifting and parameter variation finally.

title: Aerodynamic and structural design for the development of a MALE UAV
abstract: The purpose of this paper is to present the preliminary design of a medium altitude long endurance (MALE) unmanned aerial vehicle (UAV) focusing on the interaction between the aerodynamic and the structural design studies.,The classic layout theory was used, adjusted for the needs of unmanned aircraft, including aerodynamic calculations, presizing methods and CFD, to estimate key aerodynamic and stability coefficients. Considering the structural aspects, a combination of layout, finite element methods and custom parameterized design tools were used, allowing automatic reshapes of the skin and the internal structural parts, which are mainly made of composite materials. Interaction loops were defined between the aforementioned studies to optimize the performance of the aerial vehicle, maximize the aerodynamic efficiency and reduce the structural weight.,The complete design procedure of a UAV is shown, starting from the final stages of conceptual design, up to the point where the detail design and mechanical drawings initiated.,This paper presents a complete view of a design study of a MALE UAV, which was successfully constructed and flight tested.,This study presents a complete, synergetic approach between the configuration layout, aerodynamic and structural aspects of a MALE UAV.

title: Design, detail analysis and performance testing of uav propulsion system
abstract: This project report is being conduct because the use of an Unmanned Aerial Vehicle (UAV) is getting popular among people either to have fun or study but the choices of powerplant are not fully deployed (in term of operational and performance sizing) and thus limiting the selection. The objective of this project is to propose a design, detail analysis and performance testing of an Unmanned Aerial Vehicle (UAV) propulsion system. In this study, the test bed model was designed to test the nitro engine Radio Control (RC) which is model of 46 LA OS Engine Series of aircraft performance which are four performance parameters that was studied such as thrust, available power and shaft brake power, propulsive efficiency and brake specific fuel consumption thus the performance parameters value can be calculated by measure the unknown value of parameters regarding to the equation involves within the range 2000 to 16000 RPM of engine speed by setting the test bed design with suitable apparatus. From this experiment, the result shows that the fabricated test bed can be use to study the engine performance and performance parameters are directly proportional to the engine speed which is mean the faster the speed of engine effected the increasing of performance parameters. As a conclusion, even without testing the engine to the real body of aircraft, all the engine performance parameter can be calculated from this experiment, and it will reduce the time and cost.

title: Conceptual Design of a Cargo UAV That Can Take off and Land Vertically
abstract: Fixed wing vertical take off and landing (VTOL) unmanned aerial vehicle (UAV)s are designed to combine the advantages of multi rotor UAVs and fixed wing UAVs in different flight phases in a single UAV. Fixed wing VTOL UAVs can achieve the mobility of multi rotor UAVs in hovering, vertical take off and landing flight phases. Since fixed wing UAVs are known for their efficiency in power consumption, fixed wing VTOL UAVs were created to efficiently perform the cruise phase of the flight for a similar reason. In this paper, we made the conceptual design of a fixed wing VTOL UAV which is called "DOGA" The mission of DOGA is to carry 0.5 kg. payload. Firstly, maximum take off weight was calculated, and then the airfoil profile, wings geometry, and the propulsion systems were determined. Also, design and performance parameters of DOGA were calculated. As a result, conceptual design of DOGA was completed and all the needed parameters for the detail design of the fixed wing VTOL UAV were derived.

title: Optimization for Conceptual Design of Reconfigurable UAV Family
abstract: The aircraft family is a set of aircraft products that share common components but vary in configurations based on different mission performance and requirements. The reconfigurable UAV family using modular design can improve the efficiency of executing multiple missions and enable the acquisition cost benefits, which is one of key competitive edges in military applications. This paper aims to study an effective optimization method for conceptual design of the reconfigurable UAV family with interchangeable components that can be reconfigured between missions. First, a Flying wing UAV family defined for combat and reconnaissance missions is used as an example for demonstration of the method, and an appropriate comprehensive analysis model is developed. Next, the optimization formulation for the conceptual design of UAV family is presented in detail, including design variables, design constraints, and objectives. A hybrid optimization strategy is then applied to solve the optimization problem of UAV family conceptual design. The results after optimization indicate that the mission performance and requirements for each configuration are satisfied, and costs are reasonably compromised for the UAV family.

title: Thrust Control Loop Design for Electric Powered UAV
abstract: This paper describes a process of designing a thrust control loop for an electric powered fixed wing unmanned aerial vehicle equipped with a propeller and a motor. In particular, the modeling method of the thrust system for thrust control is described in detail and the propeller thrust and torque force are modeled using blade element theory. A relation between current and torque of the motor is obtained using an experimental setup. Another relation between current, voltage and angular velocity is also obtained. The electric motor and the propeller dynamics are combined to model the thrust dynamics. The associated trim and linearization equations are derived. Then, the thrust dynamics are coupled with the flight dynamics to allow a proper design for the thrust loop in the flight control. The proposed method is validated by an application to a testbed UAV through simulations and flight test.