Computational Study of the Flight Dynamics, Stability and Control of an Unmanned Aerial Vehicle in an Integrated Simulation Framework

2008 ◽  
Author(s):  
Leon CS Tan ◽  
M. Damodaran
Keyword(s):  
Unmanned Aerial Vehicle ◽  
Computational Study ◽  
Flight Dynamics ◽  
Simulation Framework ◽  
Integrated Simulation ◽  
Stability And Control ◽  
Aerial Vehicle ◽  
And Control ◽  
Dynamics Stability

scholarly journals Design and Analysis of a Rocket-Deployed Flying-Wing UAV

2021 ◽  
Author(s):  
Yukei Oyama
Keyword(s):  
Additive Manufacturing ◽  
Aspect Ratio ◽  
Unmanned Aerial Vehicle ◽  
Wing Loading ◽  
Wing Area ◽  
Power Requirement ◽  
Stability And Control ◽  
Power Loading ◽  
Aerial Vehicle ◽  
And Control

This undergraduate paper demonstrates the design, analysis, and manufacturing of a rocket deployable electric powered experimental unmanned aerial vehicle. The design process begins with defining the volume and dimensions of the allocated payload space for the UAV in the rocket. These dimensions are given by the aerostructures sub team in the Ryerson Rocketry Club. The dimensions given were used to determine the best configuration for the mission. The wing loading, power loading and endurance of the UAV are obtained from the constrained payload volume in the rocket and the avionics system of the of the UAV. The wing area, UAV weight and power requirements were calculated based on the previously determined values. The power requirement determines the motor size and propeller configuration. Aerodynamics, stability, and control were based the selected airfoil and obtained wing area. After completing the design, foam, additive manufacturing, and composite layups were used to create prototypes of the UAV. These prototypes were used to iterate the aircraft and address any immediate changes. The chosen design is a foldable flying wing, once deployed from the rocket has a wingspan of 70 inches, an aspect ratio of 13.35 and a surface area of 367 in2 . A prototype was created to prove the design feasibility of the UAV. The prototype proved to function as planned, capable of gliding, powered flight, and takeoff.

scholarly journals Design and Analysis of a Rocket-Deployed Flying-Wing UAV

2021 ◽  
Author(s):  
Yukei Oyama
Keyword(s):  
Additive Manufacturing ◽  
Aspect Ratio ◽  
Unmanned Aerial Vehicle ◽  
Wing Loading ◽  
Wing Area ◽  
Power Requirement ◽  
Stability And Control ◽  
Power Loading ◽  
Aerial Vehicle ◽  
And Control

This undergraduate paper demonstrates the design, analysis, and manufacturing of a rocket deployable electric powered experimental unmanned aerial vehicle. The design process begins with defining the volume and dimensions of the allocated payload space for the UAV in the rocket. These dimensions are given by the aerostructures sub team in the Ryerson Rocketry Club. The dimensions given were used to determine the best configuration for the mission. The wing loading, power loading and endurance of the UAV are obtained from the constrained payload volume in the rocket and the avionics system of the of the UAV. The wing area, UAV weight and power requirements were calculated based on the previously determined values. The power requirement determines the motor size and propeller configuration. Aerodynamics, stability, and control were based the selected airfoil and obtained wing area. After completing the design, foam, additive manufacturing, and composite layups were used to create prototypes of the UAV. These prototypes were used to iterate the aircraft and address any immediate changes. The chosen design is a foldable flying wing, once deployed from the rocket has a wingspan of 70 inches, an aspect ratio of 13.35 and a surface area of 367 in2 . A prototype was created to prove the design feasibility of the UAV. The prototype proved to function as planned, capable of gliding, powered flight, and takeoff.

scholarly journals Flight Dynamics, Stability and Control of a Flexible Airplane

2013 ◽  
Vol 15 (AEROSPACE SCIENCES) ◽  
pp. 1-17
Author(s):  
A. Khalil ◽  
M. ElNomrossy ◽  
G. Elbayoumi ◽  
M. Bayoumi
Keyword(s):  
Flight Dynamics ◽  
Stability And Control ◽  
And Control ◽  
Dynamics Stability

Modeling and control of a quadrotor tail-sitter unmanned aerial vehicles

2021 ◽  
pp. 095965182110504
Author(s):  
Hongbo Xin ◽  
Yujie Wang ◽  
Xianzhong Gao ◽  
Qingyang Chen ◽  
Bingjie Zhu ◽  
...  
Keyword(s):  
Control System ◽  
Unmanned Aerial Vehicles ◽  
Unmanned Aerial Vehicle ◽  
Euler Angle ◽  
Level Flight ◽  
Aerial Vehicles ◽  
Flight Mode ◽  
Aerial Vehicle ◽  
Hover Flight ◽  
And Control

The tail-sitter unmanned aerial vehicles have the advantages of multi-rotors and fixed-wing aircrafts, such as vertical takeoff and landing, long endurance and high-speed cruise. These make the tail-sitter unmanned aerial vehicle capable for special tasks in complex environments. In this article, we present the modeling and the control system design for a quadrotor tail-sitter unmanned aerial vehicle whose main structure consists of a traditional quadrotor with four wings fixed on the four rotor arms. The key point of the control system is the transition process between hover flight mode and level flight mode. However, the normal Euler angle representation cannot tackle both of the hover and level flight modes because of the singularity when pitch angle tends to [Formula: see text]. The dual-Euler method using two Euler-angle representations in two body-fixed coordinate frames is presented to couple with this problem, which gives continuous attitude representation throughout the whole flight envelope. The control system is divided into hover and level controllers to adapt to the two different flight modes. The nonlinear dynamic inverse method is employed to realize fuselage rotation and attitude stabilization. In guidance control, the vector field method is used in level flight guidance logic, and the quadrotor guidance method is used in hover flight mode. The framework of the whole system is established by MATLAB and Simulink, and the effectiveness of the guidance and control algorithms are verified by simulation. Finally, the flight test of the prototype shows the feasibility of the whole system.

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