Morphing Wing-Tip Open Loop Controller and its Validation During Wind Tunnel Tests at the IAR-NRC
Journal Title: INCAS BULLETIN - Year 2016, Vol 8, Issue 3
Abstract
In this project, a wing tip of a real aircraft was designed and manufactured. This wing tip was composed of a wing and an aileron. The wing was equipped with a composite skin on its upper surface. This skin changed its shape (morphed) by use of 4 electrical in-house developed actuators and 32 pressure sensors. These pressure sensors measure the pressures, and further the loads on the wing upper surface. Thus, the upper surface of the wing was morphed using these actuators with the aim to improve the aerodynamic performances of the wing-tip. Two types of ailerons were designed and manufactured: one aileron is rigid (non-morphed) and one morphing aileron. This morphing aileron can change its shape also for the aerodynamic performances improvement. The morphing wing-tip internal structure is designed and manufactured, and is presented firstly in the paper. Then, the modern communication and control hardware are presented for the entire morphing wing tip equipped with actuators and sensors having the aim to morph the wing. The calibration procedure of the wing tip is further presented, followed by the open loop controller results obtained during wind tunnel tests. Various methodologies of open loop control are presented in this paper, and results obtained were obtained and validated experimentally through wind tunnel tests.
Authors and Affiliations
Mohamed Sadok GUEZGUEZ, Ruxandra Mihaela BOTEZ, Mahmoud MAMOU, Youssef MEBARKI
Keywords
Related Articles
- EP ID EP118142
- DOI 10.13111/2066-8201.2016.8.3.4
- Views 98
- Downloads 0
Concept Study of Radio Frequency (RF) Plasma Thruster for Space Propulsion
Electric thrusters are capable of accelerating ions to speeds that are impossible to reach using chemical reaction. Recent advances in plasma-based concepts have led to the identification of electromagnetic (RF) generati...
Experimental Methods for UAV Aerodynamic and Propulsion Performance Assessment
This paper presents an experimental method for assessing the performances and the propulsion power of a UAV in several points based on telemetry. The points in which we make the estimations are chosen based on several cr...
Subsonic aerodynamics experimental research on gas-dynamic parameters of the flow
Subsonic wind tunnels are generally aerodynamic equipment allowing to obtain in one of their elements, namely in the experimental area where the model is placed, a uniform and stable airflow of determined speed. Wind tu...
Comparative study between 2D and 3D FEM techniques in single bolt, single lap, composite bolted joints for space structures
Two-dimensional and three-dimensional finite element models have been developed to study the effects of bolt-hole clearance on the mechanical behavior of bolted composites (graphite/epoxy) joints in space structures. The...
Sensors of a Beechcraft C90 Aircraft for Extension of Data Acquisition System
In-flight data acquisition is a key point in the aircraft design process. For the control of a simulated prototype using the control surfaces, state variables such as acceleration, pitch rate for longitudinal motion, and...