Test Engineer

2015

The aim of this paper is to highlight some significant aspects related to the dynamic simulation and virtual fatigue behavior evaluation of actuators for aeronautical use (ball screws), subjected to vibration actions, defined by specific instruction and simulating real operating conditions. In particular, it relates to the ability to run (in frequency domain) sine sweep tests simulations by avoiding classical harmonic analyses, in order to reduce the calculation time. This is possible by using a suitable transformation of the input spectra into the corresponding power spectral density (PSD) functions, to perform a faster PSD spectrum analysis and, then, reconverting the output PSD functions into simple frequency spectra, in order to accurately evaluate fatigue behavior

Technical Sciences, 2021

The paper present the results of work on measurement system dedicated to hardware used during wind tunnel tests, especially to servomechanisms. These devices could be applied to set specific position of control surface. Proposed system would ensure continuous monitoring of servo-rotor position and servo-motor temperature and would avoid uncontrolled change of control surface position. The application designed to monitor the operating status of the servomechanism was prepared in the LabVIEW software and was implemented on the myRIO platform. Developed test rig allow to register time histories of servo-rotor position and temperature during for different values of applied load. In the paper, test methodology were also presented. Experimental studies show that before wind tunnel tests, selected servomechanism should be tested in terms of maintaining the parameters declared by the manufacturer, especially during continuous operation. Developed measurement system can be used during wind t...

Proceedings of the 2nd International Conference on Computer Application and System Modeling, 2012

The design and installation of control force measurement device for quick evaluation flight test was difficult due to not enough time and fund available. Three control force indication devices were assembled and tested. They were spring balance, control force indication glove and FlexiForce indicator. The flight test results showed that all the three devices could be used for quick control force measurement. The principle of control force indication glove was innovative. However, for the spring balance, the undirected control of the aircraft was abnormal and it might influence the quality opinion of the pilot on the handling quality of the aircraft. The load sensor on the control force indication glove must be improved. The reliability of the FlexiForce indicator also should be improved.

Global Journal of Research In Engineering, 2014

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.

… 프로시딩즈| 기술보고서| 해외연구 …, 2005

In the last decades the use of flight tests in the aeronautical industries have been increasing, mainly because the parameters identification technics have been used in the flight mechanics field, including control systems and flight simulation as well.

This paper presents realized station for testing of electrical motors. Station has two main parts: Emulator of load and part for control and monitoring of the whole system. Emulator is a calibrated electromagnetic brake. Emulator can emulate different types of load, like gravitational, linear, fan and compound load, which is combination of first three. Control of emulator and monitoring of motor parameters during testing is realized with Compact RIO controller. Graphical user interface is realized in LabVIEW. Results obtained during motor testing, are shown at the end, and compared with the MATLAB simulated results.

Energies

In this paper, the static and dynamic simulations, and mechanical-level Hardware-In-the-Loop (MHIL) laboratory testing methodology of prototype drive systems with energy-saving permanent-magnet electric motors, intended for use in modern construction cranes is proposed and described. This research was aimed at designing and constructing a new type of tower crane by Krupiński Cranes Company. The described research stage was necessary for validation of the selection of the drive system elements and confirmation of its compliance with applicable standards. The mechanical construction of the crane was not completed and unavailable at the time of testing. A verification of drive system parameters had to be performed in MHIL laboratory testing, in which it would be possible to simulate torque acting on the motor shaft. It was shown that the HIL simulation for a crane may be accurate and an effective approach in the development phase. The experimental tests of selected operating cycles of ...

Noise Vibration and Hardness are some of the most common problems and quality criteria in mobile automotive parts. This is the case of constant velocity joint of drive shaft. The test rig presented was develop to evaluate and characterize the drive shaft for vehicle front traction. It reproduce parameters as speed, angle and torque similar to those presented in normal operation. In the output it allows measurement of axial force and vibration. The design criteria and outline of system are presented. Then the development of the load cell for axial force and torque using strain gages. The design was based on flexion and torsion theories for stress analysis and deformations. The strain gages arrangement with the instrumentation are presented with de calibration procedure and its results. Design and instrumentation were verified at every stage of the process to achieve the required accuracy. Finally static and dynamic test was carried out and the theorical and experimental results consistent with 1.022\% for axial force and 1.72\% for torque of deviation.

Komunikácie, 2022

This paper presents an analysis of the strength of a prototype test rig for testing rotors of unmanned aerial vehicles. Digital design software was used for the design work that covered the creation of a virtual model of the test rig and strength analysis of its key elements. The paper discusses the test rig solutions, applied to date, of the small main rotor research. From the assumed operational parameters and structural parameters of the rotor, the main forces acting on the designed structure were determined: lifting force, reaction torque and empty mass of the test rig. Suitable actuators of the control system enabling the regulation of the total pitch and periodic pitch of the rotor, within the full range of the angle of attack, were selected for the rotor under test. The FEM (Finite Element Method) strength analysis was carried out for the proposed support structure and the correctness of the design was verified.

Aviation, 2010

The development of computer techniques and computational systems based on the finite element method allows one to conduct a free vibration analysis of large systems like an aviation gearbox test rig. The object of this paper is to present a free vibration analysis of a gear fatigue test rig working in a closed loop configuration. A numerical model of the test rig based on the finite element method is presented in this paper. The base model contains all the essential structures of the real system. After the numerical results of the natural frequencies of the rig were obtained, they were then verified by the experimental results on a real object. Numerical analysis was performed using the ANSYS code.