Design and Hardware-in-the-Loop Integration of a UAV Microavionics System in a Manned–Unmanned Joint Airspace Flight Network Simulator

Ates, Serdar; Bayezit, İsmail; Tsourdos, Antonios

doi:10.1007/s10846-008-9270-1

Cited by 13 publications

(4 citation statements)

References 16 publications

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“…ITU-BYU tailsitter UAV will be operated autonomously with the micro-avionics system [16], which is originally developed by ITU Control and Avionics Laboratory (CAL). Optimization of transition maneuvers, basic throttle management and propulsion system switching logic is still under development.…”

Section: Control Logic For Switching Propulsion Systemmentioning

confidence: 99%

“…As a result of several accidents mainly due to the high workload over the pilots, the development of the manned tailsitter projects were ceased. However, as unmanned systems developed, the distinct tailsitter concept is realized again by using recent autopilot technology [1,15,16]. As a matter of fact, many unmanned VTOL aircraft in addition to micro-helicopters are already under development.…”

Section: Introductionmentioning

confidence: 99%

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Hybrid Propulsion System Design of a VTOL Tailsitter UAV

Aksugur¹,

Tsourdos²,

Beard³

2008

SAE Technical Paper Series

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Tailsitter UAVs with their combined vertical take off and landing (VTOL) and fixed-wing aircraft with full flightspeed regime capability provides a distinct alternative to rotary-wing and ducted fan UAVs (OAVs). ITU-BYU Tailsitter concept aims to obtain the energy efficient regimes across the VTOL and the cruising flight regimes. This paper describes the hybrid propulsion system design approach to attain this. The preliminary design and the analysis indicate advantageous performance over other mini-class unmanned air vehicles.

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Section: Control Logic For Switching Propulsion Systemmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Hybrid Propulsion System Design of a VTOL Tailsitter UAV

Aksugur¹,

Tsourdos²,

Beard³

2008

SAE Technical Paper Series

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“…In the reported test, electrical and mechanical loads, in various flight conditions, are simulated and used as engine inputs. Ates et al 15 have presented an HIL integration of an unmanned air vehicle (UAV) micro-avionics system in a manned–unmanned joint airspace flight network simulator. In the study by Gans et al, 16 HIL simulation platform was done for vision-based control of UAVs.…”

Section: Introductionmentioning

confidence: 99%

Hardware-in-the-loop simulation of two-shaft gas turbine engine’s electronic control unit

Montazeri-Gh

Abyaneh

Kazemnejad

2016

Proceedings of the Institution of Mechanical Engineers, Part I:

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An electronic control unit for a fuel control system of two-shaft gas turbine engines plays an undisputable role in providing the required fuel flow to the engine as well as satisfying engine’s operational characteristics. One of the main challenges in designing such unit is the accuracy of its performance and the control strategy implementation on an electronic hardware via repeatable and comprehensive tests. In this article, a hardware-in-the-loop simulation is presented for testing of the electronic control unit for a two-shaft gas turbine engine. For this purpose, the engine is first presented and modeled by the use of Wiener block structure method. The fuel controller with Min–Max structure is then explained. Finally, the controller is implemented on a PC/104 hardware and tested in an hardware-in-the-loop simulation in order to verify its correct performance. The results show that the fuel controller satisfies all of the engine’s physical constraints, confirming the controller competence and successful implementation of the engine control algorithm on the PC/104 hardware.

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“…Similarly, authors in ref. [9], propose an HILS testbed by using a lowpower consumption PC/104+ computer as the flight management computer. In the above-mentioned works, only sensors or actuators are embedded as actual objects in the simulation loops, and the flight performance are mainly verified by the numerical results.…”

Section: Introductionmentioning

confidence: 99%

A low-cost hardware-in-the-loop-simulation testbed of quadrotor UAV and implementation of nonlinear control schemes

et al. 2015

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SUMMARYDesigning and testing flight control algorithms for quadrotor UAVs (unmanned aerial vehicles) is not an easy task due to the risk of possible danger and damage during the practical flight. In order to improve the safety and efficiency of the flight control implementation, a low-cost real-time HILS (hardware-in-the-loop simulation) testbed for quadrotor UAVs is developed in this paper. To realize the HILS testbed, a miniature quadrotor is used as the main body, equipped with a micro AHRS (attitude heading reference system) unit and a self-build DSP (digital signal processor) board. The HILS is implemented by using xPC target. A compact PC/104 computer is utilized as the target computer, and a laptop PC is employed as the host computer. A desktop PC is used as flight visualization computer which runs FlightGear and Google Earth to show visual data, such as orientation and flight path of the quadrotor UAV. This testbed can be utilized for simulating various flight control algorithms, without losing safeness and reliableness. To demonstrate the effectiveness of the proposed testbed, a new nonlinear adaptive sliding mode based stabilization control algorithm is developed and verified on the HILS testbed.

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Design and Hardware-in-the-Loop Integration of a UAV Microavionics System in a Manned–Unmanned Joint Airspace Flight Network Simulator

Cited by 13 publications

References 16 publications

Hybrid Propulsion System Design of a VTOL Tailsitter UAV

Hybrid Propulsion System Design of a VTOL Tailsitter UAV

Hardware-in-the-loop simulation of two-shaft gas turbine engine’s electronic control unit

A low-cost hardware-in-the-loop-simulation testbed of quadrotor UAV and implementation of nonlinear control schemes

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