Flight test and wind-tunnel study of a scaled unmanned air vehicle

1992 ◽  
Author(s):  
RICHARD HOWARD ◽  
ROBERT BRAY
Keyword(s):  
Wind Tunnel ◽  
Flight Test ◽  
Unmanned Air Vehicle ◽  
Air Vehicle ◽  
Wind Tunnel Study

scholarly journals Design and implementation of an unmanned aerial vehicle with self-propulsive wing

2019 ◽  
Vol 11 (6) ◽  
pp. 168781401985729 ◽  
Author(s):  
Abdelrahman Kasem ◽  
Ahmad Gamal ◽  
Amr Hany ◽  
Hesham Gaballa ◽  
Karim Ahmed ◽  
...  
Keyword(s):  
Fluid Dynamics ◽  
Computational Fluid Dynamics ◽  
Wind Tunnel ◽  
Rotational Speed ◽  
Lift Coefficient ◽  
Cross Flow ◽  
Unmanned Air Vehicle ◽  
Air Vehicle ◽  
Cross Flow Fan ◽  
High Angles Of Attack

The article aims to prove the effectiveness of the proposed unmanned air vehicle design (The Propulsive Wing) through numerical and experimental means. The propulsive wing unmanned air vehicle is a completely new class of unmanned air vehicle, making disruptive changes in the aircraft industry. It is based on a distributed cross-flow electric fan propulsion system. When the fan starts to operate, the flow is drawn from the suction surface, provided by energy through the fan and expelled out of the airfoil trailing edge (TE). This causes a significant lift increase and drag reduction with respect to ordinary aircrafts, making it perfect for applications requiring low cruise speed such as firefighting, agriculture, and aerial photography. In this early stage of the investigation, our main aim is to prove that this design is applicable and the expected aerodynamic and propulsion improvements are achievable. This is done through a two-dimensional computational fluid dynamics investigation of the flow around an airfoil with an embedded cross-flow fan near its TE. A scaled wind tunnel model of the same geometry used in the computational fluid dynamics investigation was manufactured and used to perform wind tunnel testing. The computational fluid dynamics and wind tunnel results are compared for validation. Furthermore, an unmanned air vehicle model was designed and manufactured to prove that the propulsive wing concept is flyable. The article shows that the aerodynamic forces developed on the cross-flow fan airfoil are not only functions of Reynolds number and angle of attack as for standard airfoils but also function of the fan rotational speed. The results show the great effect of the rotational speed of fan on lift augmentation and thrust generation through the high momentum flow getting out of the fan nozzle. Wind tunnel tests show that the suction effect of the fan provides stall free operation up to very high angles of attack (40 degrees) leading to unprecedented values of lift coefficient up to 5.8. The flight test conducted showed the great potential of the new aircraft to perform the expected low cruise speed and high angles of attack flight.

Trajectory Tracking Control for Micro Unmanned Aerial Vehicles

2013 ◽  
Vol 798-799 ◽  
pp. 448-451
Author(s):  
Rui Yong Zhai ◽  
Wen Dong Zhang ◽  
Zhao Ying Zhou ◽  
Sheng Bo Sang ◽  
Pei Wei Li
Keyword(s):  
Trajectory Tracking ◽  
Tracking Control ◽  
Kinematic Model ◽  
Flight Test ◽  
Guidance System ◽  
Test Results ◽  
Control Loop ◽  
Trajectory Tracking Control ◽  
Unmanned Air Vehicle ◽  
Air Vehicle

This article considers the problem of trajectory tracking control for a micro fixed-wing unmanned air vehicle (UAV). With Bank-to-Turn (BTT) method to manage lateral deviation control of UAV, this paper discusses the outer loop guidance system, which separates the vehicle guidance problems into lateral control loop and longitudinal control loop. Based on the kinematic model of the coordinated turning of UAV, the aircraft can track a pre-specified flight path with desired error range. Flight test results on a fixed-wing UAV have indicated that the trajectory tracking control law is quite effective.

scholarly journals Modeling the unstable DelftaCopter vertical take-off and landing tailsitter unmanned air vehicle in hover and forward flight from flight test data

2019 ◽  
Vol 11 ◽  
pp. 175682931988030 ◽  
Author(s):  
Christophe De Wagter ◽  
Joost Meulenbeld
Keyword(s):  
Test Data ◽  
Delta Wing ◽  
Flight Test ◽  
Model Parameters ◽  
Attitude Dynamics ◽  
Dynamics Model ◽  
Forward Flight ◽  
Plane Model ◽  
Unmanned Air Vehicle ◽  
Air Vehicle

The DelftaCopter is a tilt-body tailsitter unmanned air vehicle which combines a large swashplate controlled helicopter rotor with a biplane delta-wing. Previous research has shown that the large moment of inertia of the wing and fuselage significantly interacts with the dynamics of the rotor. While this rigid rotor cylinder dynamics model has allowed initial flight testing, part of the dynamics remains unexplained. In particular, higher frequency dynamics and the forward flight dynamics were not modeled. In this work, the cylinder dynamics model is compared with the tip-path plane model, which includes the steady-state flapping dynamics of the blades. The model is then extended to include the wing and elevon dynamics during forward flight. Flight test data consisting of excitations with a large frequency content are used to identify the model parameters using grey-box modeling. Since the DelftaCopter is unstable, flight tests can only be performed while at least a rate feedback controller is active. To reduce the influence of this active controller on the identification of the dynamics, one axis is identified at a time while white noise is introduced on all other axes. The tip-path plane model is shown to be much more accurate in reproducing the high-frequency attitude dynamics of the DelftaCopter. The significant rotor–wing interaction is shown to differ greatly from what is seen in traditional helicopter models. Finally, an Linear-Quadratic Regulator (LQR) controller based on the tip-path plane model is derived and tested to validate its applicability. Modeling the attitude dynamics of the unstable DelftaCopter from flight test data has been shown to be possible even in the presence of the unavoidable baseline controller.

Flight test of a half-scale unmanned air vehicle

1991 ◽  
Vol 28 (12) ◽  
pp. 843-848 ◽  
Author(s):  
R. M. Howard ◽  
J. C. Tanner ◽  
D. F. Lyons
Keyword(s):  
Flight Test ◽  
Unmanned Air Vehicle ◽  
Air Vehicle

scholarly journals Flight Test Result for the Ground-Based Radio Navigation System Sensor with an Unmanned Air Vehicle

Sensors ◽  
2015 ◽  
Vol 15 (11) ◽  
pp. 28472-28489 ◽  
Author(s):  
Jaegyu Jang ◽  
Woo-Guen Ahn ◽  
Seungwoo Seo ◽  
Jang Lee ◽  
Jun-Pyo Park
Keyword(s):  
Navigation System ◽  
Flight Test ◽  
Radio Navigation ◽  
Unmanned Air Vehicle ◽  
Air Vehicle ◽  
Radio Navigation System ◽  
Test Result

Unmanned Air Vehicle Flight Test using a Manned Surrogate Aircraft

2011 ◽  
Author(s):  
Timothy Jorris ◽  
Nathan Lehman ◽  
William Gray ◽  
Jay Kemper
Keyword(s):  
Flight Test ◽  
Unmanned Air Vehicle ◽  
Air Vehicle
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