Autonomous VTOL Joined Wing UAV

Zafirov, Dimo

doi:10.2514/6.2013-5087

Cited by 3 publications

(3 citation statements)

References 2 publications

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“…As a test case for the products AVL and Tornado we implemented the geometrical model of an experimental UAV -JoWi [9] developed at the Technical University Sofia -Plovdiv Branch (Figure 2, Figure 3) Aerodynamic tests were executed and the results for some of the stability derivatives are shown in Table 4: Table 4 6. CONCLUSION…”

Section: Resultsmentioning

confidence: 99%

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Comparative Investigation of VLM Codes for Joined-Wing Analysis

.¹

2013

IJRET

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The Vortex lattice method (VLM) is a popular aerodynamic analysis method used at the early stages of aircraft design. In this paper a comparative investigation of several computer programs applying the VLM is carried out and their ability to simulate non conventional wing configurations is evaluated. It was found that Athena Vortex Lattice (AVL) code calculated the most correct results, but other programs like Tornado provide useful supplemental information.

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Section: Resultsmentioning

confidence: 99%

“…Closed wing configurations of the boxwing type promise the biggest reduction in induced drag. They are able to provide a lot of other advantages as well, as pointed in [1]. However the closed wing system represents a much more complex subject for aerodynamic analysis and optimization than the conventional cantilever wing.…”

Section: Introductionmentioning

confidence: 99%

Comparative Investigation of VLM Codes for Joined-Wing Analysis

.¹

2013

IJRET

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“…Open-source commercially-produced autopilots examined include the Paparazzi Lisa/M, 12 3D Robotics APM 2.6, 13 and Pixhawk PX4 Autopilot; 14 these open-source autopilots are found in literature: Paparazzi Lisa/M, 15 and 3D Robotics APM 2.6. 16 The specifications for these units are given in Table 2.…”

Section: A Literature Review Of Data Acquisition Systems For Small Tmentioning

confidence: 99%

High-Frequency Sensor Data Acquisition System (SDAC) for Flight Control and Aerodynamic Data Collection

Dantsker

Mancuso

Selig

et al. 2014

32nd AIAA Applied Aerodynamics Conference

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This paper describes a high-frequency sensor data acquisition system (SDAC) for flight control and aerodynamic data collection research on small to mid-sized unmanned aerial vehicles (UAVs). The system is both low weight and low power, operates at 100 Hz and features: a high-frequency, high-resolution six degree-offreedom (6-DOF) inertial measurement unit (IMU) with a global positioning system (GPS) receiver, a 3-axis magnetometer, a pitot probe, seven 10-bit analog-to-digital converters (ADC), sixteen 12-bit analog-to-digital converters, a 14-bit analog-to-digital converter, twenty digital input/outputs (I/O), eight pulse width modulation (PWM) signal inputs, a 40 mile downlink transceiver, an open serial and an open CANbus port, and up to 64 GB of onboard storage. The data acquisition system was completely fabricated from commercial-off-theshelf (COTS) components, which reduced the system cost and implementation time. The SDAC combines the large variety of sensor streams into a unified high-fidelity state data stream that is recorded for later aerodynamics analysis and simultaneously forwarded to a separate processing unit, such as an autopilot.

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Flight Data Acquisition Platform Development, Integration, and Operation on Small- to Medium-Sized Unmanned Aircraft

Dantsker¹,

Mancuso

2019

AIAA Scitech 2019 Forum

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Unmanned aerial vehicles (UAVs) are rapidly increasing in popularity for civilian, military, and research applications, and as part of this uptrend, significant effort has been undertaken to integrate an increasing amount of sensing into these vehicles. This sensing, or in other words, acquisition of sensor data, is part of the core functionality of UAVs-without the ability to sense, an unmanned aircraft is unable to function. By intelligently integrating sensors into a vehicle and properly interfacing with them, one is able to derive streams of data from these sensors, which allow the aircraft to fly and the desired mission to occur. In just the past several years, along with the uptrend in UAV use, there has been an increase in the research to evaluate and improve aircraft performance and flight characteristics. All of these efforts depend on the ability to acquire and utilize high fidelity data from a large range of sensors and devices. This paper will first provide an overview for the development of a data acquisition system. It will then focus on the design aspects involved including system architecture, sensing interfaces, common sensors, and user interface. Next, the paper will present a study of data acquisition systems and flight control systems that have been used in UAV research, with their specifications. Finally, avionics integration examples will be provided to demonstrate application in an unmanned aircraft.

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Autonomous VTOL Joined Wing UAV

Cited by 3 publications

References 2 publications

Comparative Investigation of VLM Codes for Joined-Wing Analysis

Comparative Investigation of VLM Codes for Joined-Wing Analysis

High-Frequency Sensor Data Acquisition System (SDAC) for Flight Control and Aerodynamic Data Collection

Flight Data Acquisition Platform Development, Integration, and Operation on Small- to Medium-Sized Unmanned Aircraft

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