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\title{Acceptance Testing of Electro Hydraulic based Aircraft Actuator using LabVIEW}
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\begin{document}

             \author[1]{Karthik  SP}

             \author[2]{Karthik  SP}

             \author[3]{Vijay  Desai}

             \affil[1]{  National Institute of Technology, Karnataka.}

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\date{\small \em Received: 16 December 2013 Accepted: 31 December 2013 Published: 15 January 2014}

\maketitle


\begin{abstract}
        


This paper presents an approach to perform aircraft actuator Acceptance Testing capability. Efforts include design and development of Test system for Electro Hydraulic aircraft actuator, in nominal condition that may be used along with measurement data to generate effective test results. LabVIEW platform is used for developing the test system.To develop communication between the LabVIEW based Test software and Actuator, Portable Test Controller (PTC), is used.

\end{abstract}


\keywords{LabVIEW, Portable Test Controller (PTC), Electro-Hydraulic (EH) and Smart Test Controller Unit (SCU).}

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\let\tabcellsep& 	 	 		 \par
Of the various kinds of actuators, EHAs were chosen for this study because of their growing role in the aerospace field. They are relatively compact and can offer high power-to-weight ratios and motion velocities.\par
[Andrew  {\ref Goldenberg \& Saeid Habibi, 1999]}.\par
Actuator Acceptance Testing at Assembly and Production Flooris to determine, if the requirements of a specification or contract are met. It may involve functional tests, physical tests, or performance tests. But for EH based actuator it's a performance testing, which included Testing the aircraft actuator for its basic functionality, including sensors functionality under the hydraulic pressure and real condition environment. [H. \hyperref[b3]{Moon and W. Knowles, 1970]} [G. \hyperref[b2]{McGrath, 1964]}.\par
Electrical actuation technologies have to comply with demanding aircraft requirements concerning reliability, performance, weight, and environmental conditions. Electro Hydraulic actuation use comes from customer and airworthiness requirements for clean and more environment friendly aircraft.\par
The use of Electro Hydraulic actuators helps in aircraft maintenance. Airlines across the globe are looking for more efficient aircraft that can increase their net profit. The increasing fuel price is a major driving factor, forcing the aircraft manufactures to opt for more fuel efficient actuation systems.\par
With the primary functions in the aircraft more powered by electrical and hydraulic system; rather than conventional Pneumatic system aircraft will be able to achieve reduced fuel burn, higher reliability, reduction in maintenance cost, and more dispatch availability. Many R\&D programs are going on in this industry for saving fuel and enhancing operational efficiency.\par
The instrumentation requirements in the area of automotive testing has increased many folds owing to the increasing and stringent demands imposed by several regulatory bodies such as the BIS, CMVR, EEC, etc. The type of tests to be carried out depends upon the purpose of evaluation such as for certification, design validation, etc. The parameters to be evaluated pertaining to the testing of vehicles are many. Presently, a number of dedicated instruments are being employed for the above purpose, each instrument meant to carry out evaluation of a specific parameter. However, one of the major disadvantages in such instruments is that their functionality is rigid and is difficult for reconfiguration. It I. 
\section[{INTRODUCTION}]{INTRODUCTION}\par
eing relatively new to the aerospace industry, Electro Hydraulic actuators are being used widely in aircraft. The quantum of knowledge as compared to ones accumulated for the other actuator types are much less and especially when it comes to Acceptance Testing. Lack of health monitoring data from the system installed in field and prohibitive costs of carrying out real flight tests push for the need of building system models and designing affordable but realistic experimental setups.\par
An electro-hydraulic system comprising an electromagnetic actuator and a hydraulic actuator relatively arranged such that the movement of the hydraulic actuator is controlled by the movement of the electromagnetic actuator.\par
The electromagnetic actuator is preferably a linear motor with a piston rod arranged to reciprocate in response to electric signal supplied to the electromagnetic actuator. A pump is preferably arranged between the electromagnetic actuator and the hydraulic actuator and causes movement of the hydraulic actuator as a result of the movement of the shaft of the linear motor. [J.  {\ref Edge, 1978]} [G. \hyperref[b1]{Daneker, 1973]}.\par
Electro-Hydraulic Actuators (EHA) are presently used in numerous aerospace applications, from robotic applications to thrust vector control of rocket engines, where they accomplish a range of rotational and translational functions ]. 
\section[{B Year 2014}]{B Year 2014}\par
requires the adjustments of many hardware components to achieve the desired functional behavior. It was, therefore intended to have an instrumentation system, which could be completely customized to the users requirements and at the same time be flexible enough to cater for the changing requirements of the test methodologies pertaining to the variation in the test standards.[S V Londhe et al, 1999]In view of this Moog Inc has developed test controller hardware for testing and validating the EH actuators.\par
A detailed description has been provided about the architecture of acceptance systems and how various cases for acceptance are tested in the test environment and corresponding data is collected to verify the physics based models.\par
A design and development of test system has been included to outline the details of experimental data collection and calculate the results depending upon the collected data and predetermined data. Furthermore, some idea about how actuator performs in real flight environments through actual flight tests and using real flight data have been presented. Finally, the roadmap leading from this effort towards developing successful Test System for aircraft electro-hydraulic actuators is discussed. 
\section[{II. OVERVIEW OF THE SYSTEM}]{II. OVERVIEW OF THE SYSTEM}\par
The Moog Portable Test Controller is made user friendly with only having a small amount of control keys available. The majority of the functions can be controlled through the push/turn knob that is located in the middle.\par
The test system uses PTC, a digital servo controller to command and control the load and position. It is a 1 to 4 channel digital servo controller with Liquid Crystal Display (LCD). This controller gives the flexibility to add additional hardware like the digital and analog inputs and outputs that includes vibration inputs, strain gauge amplifier inputs, remote control units etc.\par
The connection between the SCU's and the real-time front end is established by using a low-cost real-time Ethernet communication link, enabling the controller to be placed very close to the actuator. The analogue cabling, usually an expensive and noise prone part of a test system, can be kept as short as possible, introducing very high signal-to-noise ratios.\par
The Test System has capability to measure Linear Variable Differential Transformer (LVDT) sensor on UUT (Unit Under Test), to measure the position and communicate as a voltage signal back to the PTC for the position loop closure. The Acceptance Test Procedure (ATP) test setup is shown in Figure \hyperref[fig_0]{1}. Position Loop: PTC generally uses the FCSLoop to bind position loop with SCU1.The FCS loop is a Moog unique control loop with dual mode controller, which allows to switch between force and position control modes. The SCU has all necessary I/O hardware to connect a typical actuator. Usually this will be a hydraulic, servo-controlled actuator. Each SCU is connected to its own actuator. It's the job of the controller to modify the output connected to the actuator in such a way that the feedback is always as close as possible to the commanded value. Host Computer gives the input command to PTC low level Drivers which will interact with hardware system and hardware system gives the feedback command to Host Computer through PTC.  The functional logic of GUI for Air Purging Test is shown in Figure  {\ref 4}. Figure  {\ref 5} and Figure  {\ref 6} shows the LabVIEW code of the Air Purging Test for both the loops respectively. Channel1 is for Position Loop, which is bound with SCU1 and connected through FCS type Loop. 
\section[{Global Journal of Researches in Engineering}]{Global Journal of Researches in Engineering}\par
Channel2 is for Force Loop, which is bound with SCU2 and connected through FCS type Loop.\par
Figure \hyperref[fig_5]{7} shows the selected PTC channels and Figure \hyperref[fig_6]{8} shows how these channels bind with respective SCU's.   After binding the loop and LVDT calibration, Tuning has to be performed for better output following with respect to input commands. A Proportional-Integral-Derivative controller (PID controller) is uses to control the loop feedback mechanism. PID is the most commonly used feedback controller. A PID controller calculates an "error" value as the difference between a measured process variable and a desired setpoint. The controller attempts to minimize the error by adjusting the process control inputs. Figure \hyperref[fig_9]{12} shows the Position loop tuning. ? Now apply the null bias servo value offset current to the UUT.\par
? Now slightly increase and decrease the offset current to move the UUT in Extend and Retract direction respectively.\par
? Now Set the PID values in such a way that the system will not go in unstable mode. And set the optimum PID values so that output signal follows the input command exactly or nearly exact.    
\section[{CONCLUSION}]{CONCLUSION}\par
The intended test equipment has been built and system software for controlling the test equipment has been developed in LabVIEW. A new approach used in this paper to test the actuator using PTC hardware. The advantage of PTC used in Acceptance software is cost reduction of the Testing and the reduction in the development time. On the basis of this approach and its derivative system design, we can further make different test system with large scale testing, which is going to be applied widely in the automation and industrial field.\begin{figure}[htbp]
\noindent\textbf{1}\includegraphics[]{image-2.png}
\caption{\label{fig_0}Figure 1 :}\end{figure}
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\noindent\textbf{}\includegraphics[]{image-3.png}
\caption{\label{fig_1}}\end{figure}
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\noindent\textbf{2}\includegraphics[]{image-4.png}
\caption{\label{fig_2}Figure 2 :}\end{figure}
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\noindent\textbf{3}\includegraphics[]{image-5.png}
\caption{\label{fig_3}Figure 3 :}\end{figure}
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\noindent\textbf{456}\includegraphics[]{image-6.png}
\caption{\label{fig_4}Figure 4 :Figure 5 :Figure 6 :}\end{figure}
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\noindent\textbf{7}\includegraphics[]{image-7.png}
\caption{\label{fig_5}Figure 7 :}\end{figure}
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\noindent\textbf{8}\includegraphics[]{image-8.png}
\caption{\label{fig_6}Figure 8 :}\end{figure}
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\noindent\textbf{9}\includegraphics[]{image-9.png}
\caption{\label{fig_7}Figure 9 :}\end{figure}
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\noindent\textbf{}\includegraphics[]{image-10.png}
\caption{\label{fig_8}}\end{figure}
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\noindent\textbf{12}\includegraphics[]{image-11.png}
\caption{\label{fig_9}Figure 12 :}\end{figure}
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 			\footnote{© 2014 Global Journals Inc. (US)} 		 		\backmatter  			  				\begin{bibitemlist}{1}
\bibitem[Goldenberg and Habibi (1999)]{b0}\label{b0} 	 		‘A Mechatronics Approach for the Design of a New High Performance Electro Hydraulic Actuator’.  		 			A Goldenberg 		,  		 			S Habibi 		.  		 doi:10.4271/- 1999-01-2853.  	 	 		\textit{SAE Technical Paper},  				1999-01-2853, 1999.  	 
\bibitem[Moon and Knowles ()]{b3}\label{b3} 	 		‘Acceptance Criteria for Demonstrating System Safety Requirement’.  		 			H Moon 		,  		 			W Knowles 		.  		 doi:10.4271/- 700630.  	 	 		\textit{SAE Technical Paper}  		1970. 700630.  	 
\bibitem[Daneker ()]{b1}\label{b1} 	 		‘Army View of Acceptance Tests’.  		 			G Daneker 		.  		 doi:10.4271/- 730424.  	 	 		\textit{SAE Technical Paper}  		1973. 730424.  	 
\bibitem[Rzucidlo (2006)]{b4}\label{b4} 	 		\textit{Laboratory and Preliminary In-Flight Tests of Electromechanical Actuators},  		 			Pawel Rzucidlo 		.  		 doi:10.4271.  		2006-01-2414, 2006. 2006-01-2414.  	 	 (SAE Technical Paper) 
\bibitem[Rzucidlo (2006)]{b5}\label{b5} 	 		\textit{Laboratory and Preliminary In-Flight Tests of Electromechanical Actuators},  		 			Pawel Rzucidlo 		.  		 doi:10.4271.  		2006-01-2414, 2006. 2006-01-2414.  	 	 (SAE Technical Paper) 
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