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Mechatronic Systems

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♦ FACILITIES: infrastructure, designing tools, processing equipments

♦ TEST BENCHES FOR MECHATRONIC APPLICATIONS


1. WING FLIGHT CONTROLS TEST STAND


It is developed mainly by INCAS Mechatronics Unit, in a common location used by two Laboratories: Mechatronic System Laboratory and Mechano-Hydro-Pneumatic Laboratory.

The stand is conceived, among others, as a starting point of a wing load control ground demonstrator. The following flight controls of a specimen of naturally cantilevered wing are operated as a mechatronic system from a control room:

♥ aileron and flight spoilers

♥ speed brakes for flight ground aerodynamic braking

♥ high-lift devices:

♦ leading edge devices (slates)

♦ trailing-edge flaps

 

 

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VIEW ON WING FLIGHT CONTROLS TEST STAND
 
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CONTROL CONSOLE OF WING ACTUATION MECHATRONIC SYSTEM
 

2. SMART STRUCTURES STAND



♦ structures morphing
 
 
Smart structures have the ability to respond adaptively in a pre-designed useful and efficient manner to changes in environmental conditions, including any changes in its own condition
(V. K. Wadhawan)
 
Active techniques enhance dynamic behavior of the wing, without redesign and adding mass; nowadays, these are used both for flutter suppression and structural load alleviation
(I. Ursu)

Many aerospace and civil infrastructure systems are at or beyond their design life; however, it is envisioned
that they will remain in service for an extended period. SHM is one of the enabling technologies that will make this possible
(V. Giurgiutiu)

Morphing wing means that a hinged aileron and/or flap will be replaced by a structure that can transform its surface area and camber without opening gaps in and between itself and the main wing, or leading to sudden changes in cross-section which could result in significant aerodynamic losses, excessive noise and vibration in the airframe  (The Aeronautical Journal, 2008)

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SMART STRUCTURES TEST STAND
 

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RECENT LABORATORY TEAM ARTICLES IN RELATION TO
APPLICATIONS ON SMART STRUCTURES TEST STAND



 

3. DEVELOPING HYDRAULIC SERVOS FOR THE ACTUATION  OF FLIGHT CONTROLS

♦ PNCDI2 Project 81 036, “Designing of a hydrostatic servoactuator for aicrafts”, 2007-2010

Romanian Patent application number 2011 00751/28.07.2011:
„SERVOACTUATOR ELECTROHIDROSTATIC PENTRU AVIATIE, CU LEGE NECONVENTIONALA DE REGLARE IN POZITIE” (Electrohydrostatic actuator for aircraft, with nonconventional position tracking control law), authors: I. Ursu, M. Arghir,
A. Toader, G. Tecuceanu, C. Calinoiu
 

ISI Publications related to the hydraulic servos analysis and synthesis

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VIEW OF THE TEST RIG FOR THE HYDROSTATIC ACTUATOR

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NEW PROJECT IN INCAS MECHATRONIC SYSTEMS LABORATORY:
ADVANCED AEROSPACE TEST RIG WITH DYNAMIC LOADING OF THE ACTUATORS

 


 

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