scholarly journals Regressor time-shifting to identify longitudinal stability and control derivatives of the Jetstream 3102

2017 ◽  
Vol 69 ◽  
pp. 218-225 ◽  
Author(s):  
Sezsy Yusuf ◽  
Mudassir Lone ◽  
Alastair Cooke ◽  
Nicholas Lawson
Keyword(s):  
Longitudinal Stability ◽  
Stability And Control ◽  
Control Derivatives ◽  
And Control ◽  
Derivatives Of

Aircraft longitudinal stability and control derivatives identification by using life cycle and Levenberg–Marquardt optimization algorithms

2009 ◽  
Vol 17 (1) ◽  
pp. 17-34 ◽  
Author(s):  
Felipe Antonio Chegury Viana ◽  
Benedito Carlos de Oliveira Maciel ◽  
Nei Salis Brasil Neto ◽  
Marcelo Fernandes de Oliveira ◽  
Valder Steffen ◽  
...  
Keyword(s):  
Life Cycle ◽  
Optimization Algorithms ◽  
Longitudinal Stability ◽  
Stability And Control ◽  
Levenberg Marquardt ◽  
Control Derivatives ◽  
And Control

A Robust Longitudinal Stability Augmentation System for Small Aircraft Under Parametric Uncertainty

2020 ◽  
Author(s):  
Guilherme N. Barufaldi ◽  
Marcus H. Victor Jr. ◽  
Henrique W. R. Pereira ◽  
Roberto G. A. da Silva
Keyword(s):  
Parametric Uncertainty ◽  
Longitudinal Stability ◽  
H Infinity ◽  
Stability And Control ◽  
Handling Characteristics ◽  
Aerodynamic Properties ◽  
Stability Augmentation ◽  
Control Derivatives ◽  
And Control ◽  
Poor Stability

Small unmanned aerial vehicles (UAVs) face flying quality problems different from those encountered by larger aircraft. The lower airspeeds and small dimensions make these vehicles more susceptible to gusts and stability and control issues, which may render the aircraft difficult to fly. Moreover, due to many factors, UAVs are often built with a considerable degree of uncertainty regarding their aerodynamic properties and flying quality. The resulting aircraft may present poor stability and handling characteristics. This work presents the conceptual design of a robust stability augmentation system (SAS), aimed at increasing stability characteristics and protecting aircraft prone to flying quality problems. In order to deal with parametric uncertainties, the controller was designed with the robust H-infinity technique. The design process is presented, and a parametric aircraft model is provided, together with longitudinal stability and control derivatives. Simulations are presented to show the effects of the controller on the aircraft behavior.

Identification of Aircraft Longitudinal Stability and Control Derivatives Combining Global Search Natural Algorithms and a Gradient Based Algorithm

2009 ◽  
Vol 42 (10) ◽  
pp. 1217-1222
Author(s):  
Benedito Carlos de Oliveira Maciel ◽  
Luiz Carlos Sandoval Góes ◽  
Felipe A. Chegury Viana ◽  
Valder Steffen
Keyword(s):  
Global Search ◽  
Longitudinal Stability ◽  
Stability And Control ◽  
Control Derivatives ◽  
Gradient Based ◽  
And Control

Rotorcraft Lateral-Directional Oscillations: The Anatomy of a Nuisance Mode

2021 ◽  
Author(s):  
Dheeraj Agarwal ◽  
Linghai Lu ◽  
Gareth D. Padfield ◽  
Mark D. White ◽  
Neil Cameron
Keyword(s):  
Simulation Model ◽  
Simulation Models ◽  
Flight Test ◽  
Flight Simulation ◽  
Stability And Control ◽  
Systems Research ◽  
Control Derivatives ◽  
Research Aircraft ◽  
Level Of Understanding ◽  
And Control

High-fidelity rotorcraft flight simulation relies on the availability of a quality flight model that further demands a good level of understanding of the complexities arising from aerodynamic couplings and interference effects. One such example is the difficulty in the prediction of the characteristics of the rotorcraft lateral-directional oscillation (LDO) mode in simulation. Achieving an acceptable level of the damping of this mode is a design challenge requiring simulation models with sufficient fidelity that reveal sources of destabilizing effects. This paper is focused on using System Identification to highlight such fidelity issues using Liverpool's FLIGHTLAB Bell 412 simulation model and in-flight LDO measurements from the bare airframe National Research Council's (Canada) Advanced Systems Research Aircraft. The simulation model was renovated to improve the fidelity of the model. The results show a close match between the identified models and flight test for the LDO mode frequency and damping. Comparison of identified stability and control derivatives with those predicted by the simulation model highlight areas of good and poor fidelity.

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