An approach to estimate aircraft touchdown attitudes and control inputs

Wu, Po-Han; Voskuijl, Mark; Veldhuis, L.L.M.

doi:10.1016/j.ast.2017.09.023

Cited by 6 publications

(4 citation statements)

References 18 publications

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“…It has been used in a variety of research studies to investigate the flight mechanics of novel aircraft configurations such as a blended wing body [6,7,18], a box-wing aircraft [19,20] and a propulsive tail empennage concept [15]. Studies have been performed to assess the loads encountered during advanced take-off and landing procedures [21,22]. Finally, in case real-time simulations are required with a pilot in the loop, the simulation output can be cast to the Flight Gear open-source simulator † visual display system.…”

Section: Non-linear Flight Dynamics Analysis (Phalanx)mentioning

confidence: 99%

Assessment of Sub-scale Designs for Scaled Flight Testing

Kulkarni

Varriale

Voskuijl

et al. 2019

AIAA Aviation 2019 Forum

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Sub-scale Flight Testing (SFT) is potentially useful in predicting aircraft flight behaviour, especially in the case of unconventional designs for which legacy information is unavailable and wind tunnel tests are unable to predict aircraft dynamics. A necessary condition for SFT is the design of properly scaled models. However, even in case of perfect scaling, the sub-scale model needs adequate flight performance and handling qualities to enable the execution of flight tests. Thus, the (static and dynamic) stability and control (S&C) and handling qualities (HQ) of sub-scale designs should be evaluated accurately as well as quickly, to allow conceptual design iterations. To this purpose, we propose the use of a 3D panel method (3DPM) for the generation of the non-linear aerodynamic database, in combination with a non-linear flight dynamics analysis. Two main challenges affect the proposed approach. The first concerns the validity of the low-fidelity 3DPM data for the assessment of the sub-scale design S&C and HQ. The second is about the time consuming and error-prone pre/post-processing activity demanded by the hundreds of analysis cases for the aerodynamic database generation. The first issue is investigated by predicting the longitudinal S&C performance and HQ of a sub-scale design using 3DPM analysis and comparing them with the prediction from wind-tunnel test (static) data supplemented by (dynamic) data from 3DPM. Both models appear trimmable and stable and the difference in their HQ are quantified, thus verifying the suitability of 3DPM analysis for sub-scale design assessment. The pre/post-processing challenge is tackled by the development of a knowledge-based engineering application to automate the aerodynamics database generation, reducing the time needed for geometry modeling, discretization and postprocessing of hundreds of cases from weeks to hours. The proposed methodology and its flexibility are demonstrated in this paper, where a commercial 3DPM code and an in-house developed non-linear flight dynamics analysis tool have been used to assess two sub-scale designs, one conventional and one based on the box-wing configuration.

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Section: Non-linear Flight Dynamics Analysis (Phalanx)mentioning

confidence: 99%

Assessment of Sub-scale Designs for Scaled Flight Testing

Kulkarni

Varriale

Voskuijl

et al. 2019

AIAA Aviation 2019 Forum

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“…Silicone based fluids are high popular in the aerospace industry and used in the landing gear for aircrafts also known as the oleopneumatic shock absorbers. These shocks have a combination of air and fluid which is used to dissipate the landing energy quickly and prevent high amount of vibrations from travelling to the fuselage especially when landing can be a tedious job when there is a crosswind forcing the aircraft to go into unwanted positions [39], [40].…”

Section: Resultsmentioning

confidence: 99%

Shock Absorber Applications

Spiteri¹

2019

EJERS

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Shock Absorbers are a part of everyday life and have many different applications and uses. They are used for bridges, highways, buildings and cars to absorb the impact from the bumps, earthquakes and high winds. Different applications require different types of shocks and different materials. A rubber shock absorber cannot be used on a vehicle while a cylindrical shock absorber cannot be used on a highway. All the situations require a specific shape and type of shocks to be used for the required tasks.

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“…Several studies on modeling and simulation of flight control systems are included in the literature [18][19][20][21][22][23][24][25][26][27][28][29][30][31][32][33][34] . In the study by Góes et.al 18 , a comparison of two output-error methods to inverse modeling of an aircraft are presented by using the experimental flight data.…”

Section: Introductionmentioning

confidence: 99%

“…The study given by Goupil et.al 26 presents signal processing strategy based a data driven approach for the detection of failures impacting the flight control system. To estimate all possible aircraft touchdown attitudes and control inputs based on flight dynamics simulations and Monte Carlo evaluation, a solution is proposed by Wu et.al 27 . The other solution proposal of Alcalay et.al 28 for estimation of flight parameters in nominal and degraded flight conditions is based on virtual sensors which make use of an adaptive extended Kalman filter.…”

Section: Introductionmentioning

confidence: 99%

ABC and DE Algorithms based Fuzzy Modeling of Flight Data for Speed and Fuel Computation

Bağış¹,

Konar²

2018

IJCIS

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It is crucial to evaluate the information obtained from the sensors in a fast and accurate manner in air vehicles exposed to many internal and external influences during their flights. The effectiveness and flexibility of the reasoning method comes to the forefront when the pilot or flight control system makes the necessary decisions in critical situations. The method used should be able to provide the nearest response to the decision that the pilot has to give, even when working with complex, unclear or incomplete data. Thus, it is not the correct approach to think that sensorial measurements and methods that describe them through a model are separate from each other. In this study, a fuzzy rule based model is designed using some important measurement data belonging to a flight control system for simultaneously computation of speed and fuel parameters. The fuzzy model parameters are determined by using artificial bee colony (ABC) and differential evolution (DE) algorithms in the modeling process in which actual flight data of Boeing B-767-200ER type aircraft are used. To demonstrate the efficiency of the modeling approach and the algorithms, fuzzy model structures having 3 inputs-and-2 outputs for different rule numbers are tested. The inputs of the fuzzy models are considered as altitude, weight, and engine pressure ratio. On the other hand, parameters of the flight speed and fuel amount are used for outputs of the models. The results achieved from the models are comparatively presented with each other and actual values.

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An approach to estimate aircraft touchdown attitudes and control inputs

Cited by 6 publications

References 18 publications

Assessment of Sub-scale Designs for Scaled Flight Testing

Assessment of Sub-scale Designs for Scaled Flight Testing

Shock Absorber Applications

ABC and DE Algorithms based Fuzzy Modeling of Flight Data for Speed and Fuel Computation

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