Aerodynamic Modelling of a Wing-in-Slipstream Tail-Sitter UAV

Stone, R. Hugh

doi:10.2514/6.2002-5951

Cited by 32 publications

(16 citation statements)

References 5 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…A partial appreciation of the force and moment nonlinearities can be gained from a plot of the Z body-axis force, as shown in Fig. 3, taken from the aerodynamic database for the vehicle [21]. In this graph, the four stacked surfaces represent Z force values at different throttle settings plotted against angle of attack and velocity.…”

Section: T-wing Model and Aerodynamicsmentioning

confidence: 99%

“…Because of variations in density altitude and takeoff weight, some flight tests have taken place with thrust margins less than 20%. Figure 4 shows longitudinal trim characteristics for the vehicle, as predicted using the aerodynamic database [21] for three separate c.g. positions (nominal and one on either side).…”

Section: B Qualitative Description Of Vehicle Characteristicsmentioning

confidence: 99%

“…The database is constructed using an integrated propeller-blade element and panel-method model. This model uses corrections based on measured 2-D viscous data for those regions of the vehicle flowfield well outside the bounds of normal linear aerodynamic analysis [1,20,21]. This allows the vehicle to be modeled for angles of attack and sideslip between 90 deg and for velocities ranging from lowspeed vertical descent to high-speed forward flight.…”

Section: T-wing Model and Aerodynamicsmentioning

confidence: 99%

See 2 more Smart Citations

Flight Testing of the T-Wing Tail-Sitter Unmanned Air Vehicle

Stone

Anderson

Hutchison

et al. 2008

Journal of Aircraft

107

View full text Add to dashboard Cite

Since October 2005, the T-wing tail-sitter unmanned air vehicle has undergone an extensive program of flight tests, resulting in a total of more than 50 flights, many under autonomous control from takeoff to landing. Starting in August 2006, free flights with conversion between vertical and horizontal flight modes have also been undertaken. Although the latter flights have required some guidance-level ground-pilot input, significant portions of them were performed in autonomous mode, including the transitions between horizontal and vertical flight. This paper considers the overall control architecture of the vehicle, including the different control modes that the vehicle was flown under during the recent series of tests. Although the individual controllers for each flight mode are unremarkable in themselves, it is notable that the aggregate system allows the vehicle to fly throughout its entire flight envelope, which is considerably broader than that of conventional fixed-or rotary-wing vehicles. The performance of the controllers for the different flight modes will also be considered, with a particular focus on hover dispersion results, in differing wind conditions. The majority of these flights were performed on a tether test rig during autonomous control development, to ensure vehicle safety with minimal impact on vehicle dynamics. The demonstration of autonomous flight under the constraints imposed by the tether system in winds up to 18 kt is a significant achievement. Results from the more recent horizontal flight tests with conversions between vertical and horizontal flight are also presented. Most important, these results confirm the basic feasibility of tail-sitter vehicles that use control surfaces submerged in propeller wash for vertical flight control. The tether ropes weigh 0:108 oz=ft (10 g=m) and are 0.158 in. (4 mm) in diameter. STONE ET AL.Downloaded by UNIVERSITY OF ARIZONA on February 3, 2015 | http://arc.aiaa.org |

show abstract

Section: T-wing Model and Aerodynamicsmentioning

confidence: 99%

Section: B Qualitative Description Of Vehicle Characteristicsmentioning

confidence: 99%

Section: T-wing Model and Aerodynamicsmentioning

confidence: 99%

See 1 more Smart Citation

Flight Testing of the T-Wing Tail-Sitter Unmanned Air Vehicle

Stone

Anderson

Hutchison

et al. 2008

Journal of Aircraft

107

View full text Add to dashboard Cite

show abstract

“…In order to determine the dynamics equations for position coordinates it is enough to use the second Newton's dynamics principle [14], [15], [16] (12)…”

Section: Coordinates Of the Positionmentioning

confidence: 99%

Examination of the Unmanned Aerial Vehicle

Setlak

Kowalik

2019

ITM Web Conf.

View full text Add to dashboard Cite

The contemporary interdisciplinary field of knowledge, which is the robotics used in unmanned aerial vehicles, is developing very dynamically. In view of the above, the authors of this paper have set themselves the following thesis: it is possible to build a flying mobile robot based on a controller with low computing power and a simple PID controller, and in this respect they undertook to prove it. The examined object in real experiments was the Quadrocopter. The article discusses the tasks implemented during the design and practical implementation of a remotely controlled flying unit. First, a mathematical model describing the dynamics of the UAV movement was defined. Then, electronic components were selected to allow the quadrocopter to fly. The board has a central unit in the form of the ATmega644PA microcontroller. In the following, the process of programming subsequent elements that make up the quadrocopter control program was carried out. The control system for stabilizing the machine requires information about the location of the quadrocopter in space. This is accomplished by a measurement module containing an accelerometer and a gyroscope. In addition, the quadrocopter needs information about the potential operator's commands. In the final part of the article, based on the analysis of the research subject, the mathematical model created and the necessary simulation tests carried out in this area, practical conclusions were presented.

show abstract

“…These kinds of shortcomings are mainly due to the designed platform's inability to reconfigure its shape or wingspan area. The tail-sitter UAV on the other hand is optimal in its Cruise flight as it encompasses large airfoils while it sacrifices VTOL performance as these airfoils usually create disturbances in VTOL control when wind gusts are present [5]. Tail-sitter UAVs also require a diving maneuver for the UAV to transit from VTOL mode to Cruise mode [6].…”

Section: Introductionmentioning

confidence: 99%

Design and Implementation of a Thrust-Vectored Unmanned Tail-Sitter with Reconfigurable Wings

et al. 2015

View full text Add to dashboard Cite

In this paper, we present the development of a reconfigurable hybrid unmanned aerial vehicle (UAV): U-Lion [Ang et al., 11th IEEE Int. Conf. Control Automation (ICCA), pp. 750-755]. U-Lion is a small-scale UAV that is capable of vertical takeoff and landing (VTOL) and fixedwing Cruise modes through its unique mechanical design. Mainly built with carbon fiber and expanded polyolefin (EPO) foam, U-Lion is equipped with an array of avionic components which enable stable control of the UAV both in VTOL and Cruise modes. It was employed by the National University of Singapore (NUS) Unmanned System Research Group to participate in the 2013 UAV Grand Prix (UAVGP) competition held in Beijing, China. Its design adopts a reconfigurable wing and a tail-sitter structure, which combines the advantages of a fixed-wing plane and a rotor helicopter effectively. U-Lion could transit from vertical takeoff to a hovering stage before flying in Cruise mode to realize efficient long duration flight. The propulsion of U-Lion comes from a self-fabricated contra-rotating motor fixed on a gimbal mechanism which can change the direction of the motor for the required thrust. This thrust-vectored propulsion system primarily provides control in the VTOL mode but also enhances flight capabilities in Cruise mode. The maximum thrust provided by the motor can be as high as 40 N and it provides six degree of motion controls in VTOL mode. U-Lion has a few special internal designs to empower its capabilities: (1) Reconfigurable wings allow the U-Lion to adapt to different flying modes. (2) Adaptive center of gravity (CG) by adjusting the battery position to fulfill the different requirements of CG for VTOL mode and Cruise mode. (3) Unique contra-rotating thrust-vectored propulsion system. The detailed design and implementation procedure have been presented in this paper along with our computational fluid dynamics (CFD) simulation results, real flight tests and competition performance.

show abstract

Aerodynamic Modelling of a Wing-in-Slipstream Tail-Sitter UAV

Cited by 32 publications

References 5 publications

Flight Testing of the T-Wing Tail-Sitter Unmanned Air Vehicle

Flight Testing of the T-Wing Tail-Sitter Unmanned Air Vehicle

Examination of the Unmanned Aerial Vehicle

Design and Implementation of a Thrust-Vectored Unmanned Tail-Sitter with Reconfigurable Wings

Contact Info

Product

Resources

About