MEMS smart variable-geometry flexible flight control surfaces: distributed control and high-fidelity modeling

2004 ◽  
Author(s):  
S.E. Lyshevski
Keyword(s):  
Distributed Control ◽  
Flight Control ◽  
High Fidelity ◽  
Variable Geometry ◽  
Control Surfaces

scholarly journals Validation of Aero-Load Estimator for Convair 880 Aircraft Flight Simulator Benchmark with Electro-Hydrostatic Actuators

2021 ◽  
Vol 13 (3) ◽  
pp. 13-27
Author(s):  
Yamina BOUGHARI ◽  
Ruxandra Mihaela BOTEZ ◽  
Amir BANIAMERIAN ◽  
Ehsan SOBHANI TEHRANI ◽  
Armineh GARABEDIAN
Keyword(s):  
Flight Control ◽  
Flight Test ◽  
Flight Simulation ◽  
High Fidelity ◽  
Aerodynamic Coefficient ◽  
Lookup Tables ◽  
Calculation Methodology ◽  
Geometrical Data ◽  
And Control ◽  
Control Surfaces

Simulating an aircraft model using of high fidelity models of subsystems for its primary and secondary flight control actuators requires measuring or estimating aero-load data acting on flight control surfaces. One solution would be to incorporate the data recorded from flight tests, which is a time-consuming and costly process. This paper proposes another solution based on the validation of an aero-loads estimator or on the hinge moments predictor for fully electrical aircraft simulator benchmark. This estimator is based on an aerodynamic coefficient calculation methodology, inspired by Roskam’s method that uses the geometrical data of the wing and control surfaces airfoils. The hinge moment values are found from two-dimensional lookup tables where the deflections of the control surfaces, aircraft altitude, and aircraft angles of attack are the input vectors of the tables; and the resulting hinge moment coefficients are the output vectors. The resulting hinge moment coefficients of the Convair 880 primary flight control surfaces are compared to those of its recorded flight test data; the results from the new software solution were found to be very accurate. Hinge moment lookup tables are integrated in the Convair 880 high fidelity flight simulation benchmark using mathematical models of energy-efficient Electro-Hydrostatic Actuators (EHA). Autopilot controls are designed for the roll, pitch, attitude and yaw damper motions using Proportional Integral (PI) controller scheduled for different flight conditions. Several different aircraft simulation scenarios are evaluated to demonstrate the efficacy and accuracy of the predicted hinge moment results.

Research on the ELAC Systems of A320 Family Aircrafts

2012 ◽  
Vol 546-547 ◽  
pp. 1562-1567
Author(s):  
Kai Yin ◽  
Gang Yin ◽  
Qin Zhen Li
Keyword(s):  
Computer System ◽  
Basic Principle ◽  
Flight Control ◽  
On Line ◽  
Control Surfaces ◽  
Driving Circuit

This document introduces the basic principle of the ELAC System (Elevator Aileron Computer System) working of A320 aircrafts, and mainly, analyzes the driving circuit of the ELAC computer for the flight control surfaces. Furthermore, introduces a real fault on line maintenance, analyze it and find out the reason, give some useful advice on A320 aircraft line maintenance.

Modeling and Analysis of a Digital Hydraulic Actuator for Flight Control Surfaces

2021 ◽  
Author(s):  
R. S. Lopes ◽  
M. P. Nostrani ◽  
L. A. Carvalho ◽  
A. Dell’Amico ◽  
P. Krus ◽  
...  
Keyword(s):  
Performance Analysis ◽  
Flight Control ◽  
Data Model ◽  
Flight Performance ◽  
Hydraulic Actuator ◽  
Hydraulic Power ◽  
Fighter Aircraft ◽  
Modeling And Analysis ◽  
Modeling Process ◽  
Control Surfaces

Abstract This paper presents the design and modeling process of a flight control actuator using digital hydraulics and a performance analysis that compares the proposed solution and the Servo Hydraulic Actuator (SHA) on a fighter aircraft model. The proposed solution is named Digital Hydraulic Actuator (DHA) and comprises the use of a multi-chamber cylinder controlled by on/off valves and different pressures sources provided by a centralized hydraulic power unit, as proposed in the Fly-by-Wire (FbW) concept. The analyses were carried out using the Aero-Data Model in a Research Environment (ADMIRE), which was developed for flight performance analysis. The actuators were modeled using the software Matlab/Simulink® and Hopsan. They were applied to control the aircraft elevons in a flight mission close to the aircraft limits, to evaluate the actuator’s behavior and energy efficiency. The results show a reduction in energy dissipation up to 22.3 times when comparing the DHA with the SHA, and despite the overshooting and oscillations presented, the aircraft flight stability was not affected.

NDE of Damage in Aircraft Flight Control Surfaces

2007 ◽  
Author(s):  
David K. Hsu ◽  
Daniel J. Barnard ◽  
Vinay Dayal
Keyword(s):  
Flight Control ◽  
Aircraft Flight ◽  
Aircraft Flight Control ◽  
Control Surfaces

Longitudinal Flight Control for a Novel Airborne Wind Energy System: Robust MIMO Control Design Techniques

2011 ◽  
Author(s):  
Nicholas Tierno ◽  
Nicholas White ◽  
Mario Garcia-Sanz
Keyword(s):  
Wind Energy ◽  
Wind Turbine ◽  
Flight Control ◽  
Synchronous Generator ◽  
Energy System ◽  
Polar Coordinate System ◽  
Additional Information ◽  
Wind Energy System ◽  
Aerodynamic Control ◽  
Control Surfaces

This paper deals with the longitudinal flight control for a novel Airborne Wind Energy (AWE) system: the EAGLE System. It is a tethered lighter-than-air flyer wind turbine composed of a blimp, several aerodynamic airfoils (wings) with specific aerodynamic control surfaces (ailerons, elevator, rudder), a counter-rotating aerodynamic rotor for the wind turbine (four identical sections, symmetrically arranged, with three blades each), an electrical synchronous generator attached to the counter-rotating rotors, and a tether to secure the airship and to transmit the generated power. Additional information can be found in US Patent, Provisional Application No. 61/387,432 developed by the authors. The designed system proposed here supports a 2.5 kW generator and flies at approximately 100 meters. The mathematical model developed for the AWE system incorporates a hybrid blimp-airfoil design, modeled using a hybrid Cartesian-polar coordinate system to capture the dynamics of both the airship and the tether, and includes the effect of the counter-rotating aerodynamic rotor of the wind turbine, as well as the aerodynamic control surfaces. This paper presents the design of a robust Multi-Input Multi-Output (MIMO) controller for the 3×3 longitudinal flight dynamics of the tethered airborne wind energy system. The control system is designed by applying sequential MIMO robust Quantitative Feedback Theory (QFT) techniques.

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