The blended-wing-body (BWB) configuration appears as a promising contender for the next generation of large transport aircraft. The idea of blending the wing with the fuselage and eliminating the tail is not new, it has long been known that tailless aircraft can suffer from stability and control problems that must be addressed early in the design. This thesis is concerned with identifying and then evaluating the flight dynamics, stability, flight controls and handling qualities of a generic BWB large transport aircraft concept. Longitudinal and lateral-directional static and dynamic stability analysis using aerodynamic data representative of different BWB configurations enabled a better understanding of the BWB aircraft characteristics and identification of the mechanisms that influence its behaviour. The static stability studies revealed that there is limited control power both for the longitudinal and lateral-directional motion. The solution for the longitudinal problem is to limit the static margins to small values around the neutral point, and even to use negative static margins. However, for the directional control problem the solution is to investigate alternative ways of generating directional control power. Additional investigation uncovered dynamic instability due to the low and negative longitudinal and directional static stability. Furthermore, adverse roll and yaw responses were found to aileron inputs. The implementation of a pitch rate command/attitude hold flight control system (FCS) improved the longitudinal basic BWB characteristics to satisfactory levels, or Level 1, flying and handling qualities (FHQ). Although the lateral-directional command and stability FCS also improved the BWB flying and handling qualities it was demonstrated that Level 1 was not achieved for all flight conditions due to limited directional control power. The possibility to use the conventional FHQs criteria and requirements for FCS design and FHQs assessment on BWB configurations was also investigated. Hence, a limited set of simulation trials were undertaken using an augmented BWB configuration. The longitudinal Bandwidth/Phase delay/Gibson dropback criteria, as suggested by the military standards, together with the Generic Control Anticipation Parameter (GCAP) proved possible to use to assess flying and handling qualities of BWB aircraft. For the lateral-directional motion the MIL-F-8785C criteria were used. Although it is possible to assess the FHQ of BWB configuartions using these criteria, more research is recommended specifically on the lateral-directional FHQs criteria and requirements of highly augmented large transport aircraft.

Thesis (Ph. D.)--West Virginia University, 2000. / Title from document title page. Document formatted into pages; contains ix, 185 p. : ill. Includes abstract. Includes bibliographical references (p. 87-91).

The blended-wing-body (BWB) configuration appears as a promising contender for the next generation of large transport aircraft. The idea of blending the wing with the fuselage and eliminating the tail is not new, it has long been known that tailless aircraft can suffer from stability and control problems that must be addressed early in the design. This thesis is concerned with identifying and then evaluating the flight dynamics, stability, flight controls and handling qualities of a generic BWB large transport aircraft concept. Longitudinal and lateral-directional static and dynamic stability analysis using aerodynamic data representative of different BWB configurations enabled a better understanding of the BWB aircraft characteristics and identification of the mechanisms that influence its behaviour. The static stability studies revealed that there is limited control power both for the longitudinal and lateral-directional motion. The solution for the longitudinal problem is to limit the static margins to small values around the neutral point, and even to use negative static margins. However, for the directional control problem the solution is to investigate alternative ways of generating directional control power. Additional investigation uncovered dynamic instability due to the low and negative longitudinal and directional static stability. Furthermore, adverse roll and yaw responses were found to aileron inputs. The implementation of a pitch rate command/attitude hold flight control system (FCS) improved the longitudinal basic BWB characteristics to satisfactory levels, or Level 1, flying and handling qualities (FHQ). Although the lateral-directional command and stability FCS also improved the BWB flying and handling qualities it was demonstrated that Level 1 was not achieved for all flight conditions due to limited directional control power. The possibility to use the conventional FHQs criteria and requirements for FCS design and FHQs assessment on BWB configurations was also investigated. Hence, a limited set of simulation trials were undertaken using an augmented BWB configuration. The longitudinal Bandwidth/Phase delay/Gibson dropback criteria, as suggested by the military standards, together with the Generic Control Anticipation Parameter (GCAP) proved possible to use to assess flying and handling qualities of BWB aircraft. For the lateral-directional motion the MIL-F-8785C criteria were used. Although it is possible to assess the FHQ of BWB configuartions using these criteria, more research is recommended specifically on the lateral-directional FHQs criteria and requirements of highly augmented large transport aircraft.

Software implementovaný v rámci Fly-by-Wire systému firmy Honeywell je složen z mnoha modelů implementovaných v systému Simulink. Tato práce se zabývá hledáním přímých a nepřímých spojitostí mezi jednotlivými signály v systému těchto modelů. Jako vhodný aparát je zvolena teorie grafů. Na základě modelů jsou vygenerovány grafy a úloha nalézt spojitost mezi signály je převedena na úlohu nalézt cestu mezi dvěma vrcholy grafu. Známé algoritmy k vyhledávání cest v grafech určují délku nebo váhu nalezené cesty. Pro tuto aplikaci je ale potřeba rozlišovat cesty primární a sekundární bez ohledu na jejich délku. Proto jsou tyto známé algoritmy upraveny.

Thesis (MScEng)--Stellenbosch University, 2012. / ENGLISH ABSTRACT: The air-to-air refuelling of large aircraft presents challenges such as a long fuel transfer time, slow aircraft responses and a large distance between the aircraft CG and the receptacle position. This project addresses some of these issues by adding a control system to keep the receiver aircraft in the correct position relative to the tanker to enable fuel transfer. This project investigates different control strategies which are designed to control the A330-300 during refuelling at one trim condition. The controllers are based on a mathematical aircraft model which was derived from a simulation model received from Airbus. The first set of controllers uses the aircraft actuators directly. Controllers that are based on the CG dynamics and the receptacle dynamics are compared. Due to the large distance between the CG and the receptacle it was found to be essential to control the receptacle position, and not only the CG position. Also, a controller that is based on a model of the receptacle dynamics performs better. The second set of controllers uses the aircraft manual control laws as an inner loop controller. This set of controllers and the last direct actuator controller use the same axial controller that uses the engine thrust to control axial position. It was found that both the direct actuator controller and the manual control laws controller are able to keep the receptacle within the disconnect envelope in moderate turbulence. In both sets of controllers the axial controller fails to keep the receptacle reliably within the disconnect envelope in light turbulence. From the results it is concluded that both the direct actuator control and manual control laws can be used to successfully control the receptacle position in the normal and lateral positions as long as the receptacle kinematics are included in the control design. Using only the engine thrust for axial control is insufficient. Several recommendations are made to improve the axial control and also how these results can be used in future work. / AFRIKAANSE OPSOMMING: Die lug-tot-lug brandstof hervulling van groot vliegtuie het uitdagings soos ’n lang hervullingstyd, stadige vliegtuig dinamika en ’n groot afstand tussen die hervullingspoort en die vliegtuig massamiddelpunt. Hierdie projek spreek sommige van hierdie uitdagings aan deur ’n beheerstelsel by te voeg wat die vliegtuig in die korrekte posisie relatief tot die tenker hou vir brandstofoordrag om plaas te vind. Hierdie projek ondersoek verskillende beheerstrategieë wat ontwerp is om die A330- 300 te beheer by ’n enkele gestadigde toestand. Die beheerders is gebaseer op ’n wiskundige vliegtuigmodel wat vanaf ’n simulasiemodel afgelei is. Die simulasiemodel is vanaf Airbus verkry. Die eerste stel beheerders beheer direk die vliegtuig se beheeroppervlakke. Beheerders wat onderskeidelik die massamiddelpunt en die hervullingspoort beheer word vergelyk. Daar is gevind dat dit essensieel is om die hervullingspoort te beheer en nie slegs die massamiddelpunt nie, as gevolg van die groot afstand tussen hierdie twee punte. Die tweede stel beheerders gebruik die vliegtuig se eie beheerwette as ’n binnelusbeheerder en vorm self die buitelus. Albei stelle beheerders gebruik dieselfde aksiale beheerder wat enjin stukrag gebruik om die aksiale posisie te beheer. Daar is gevind dat beide stelle beheerders die hervullingspoort binne die ontkoppelingsbestek kan hou in die normale en laterale rigtings tydens matige turbulensie. In beide stelle beheerders is dit die aksiale beheerder wat faal om die hervullingspoort betroubaar in posisie te hou, selfs in ligte turbulensie. Vanaf die resultate word afgelei dat beide die direkte beheerder en die buitelusbeheerder gepas is om die laterale en normale posisiebeheer toe te pas mits die dinamika van die hervullingspoort in ag geneem word. Om slegs stukrag te gebruik vir aksiale beheer is nie voldoende nie, en verskeie voorstelle word gemaak om die aksiale beheer te verbeter in toekomstige navorsing.

Techn. Universiẗat, Diss., 2003--Darmstadt.

Afin d’introduire de nouvelles fonctions dans les commandes de vol d’hélicoptère, il est nécessaire d’augmenter les bandes passantes de leurs actionneurs. La modélisation réaliste de l’ensemble du système d’actionnement, rendant compte de ses limitations de puissance et de sa consommation énergétique, ainsi que l’amélioration des technologies existantes des dispositifs d’étanchéité et de guidage sont les deux enjeux principaux permettant d’atteindre la durée de vie souhaitée à hautes fréquences. Pour supporter ce nouveau développement, ce travail s’organise en trois parties. Une première partie présente l’état de l’art des commandes de vol de l’hélicoptère. Une architecture générique d’actionneur est proposée ainsi que la terminologie associée. Une deuxième partie porte sur l’élaboration d’un modèle de connaissance détaillé à l’aide du formalisme Bond-graph pour le système d’actionnement. Un effort particulier est porté sur la standardisation des composants et de leurs interfaces dans une démarche orientée objet. La dernière partie traite concerne les dispositifs d’étanchéité et de guidage au niveau des vérins de commande de vol. Compte tenu de l’objectif d’utiliser des paliers fluides, les différentes manières de générer une force normale au sein d’un film fluide sont analysées. Puis, une étude plus approfondie des butées hydrostatiques et des paliers hybrides coniques est ensuite conduite en tenant compte des contraintes propres à l’aéronautique. L’ensemble des connaissances acquises sont appliquées à un cas concret de développement assisté par les modèles d’actionneur hautes fréquences pour le contrôle actif de rotor. / In order to introduce new functions in helicopter flight controls, it is necessary to increase the bandwidths of their actuators. A realistic modelling of the entire actuating system, taking into account its power limitations and its energy consumption, as well as the improvement of the existing sealing and guiding device technologies are the two main challenges to reach the desired high frequency without reducing dramatically the actuator lifespan. To support this new development, this work is organized in three parts. A first part presents the state of the art of the helicopter flight controls. A generic actuator architecture is proposed as well as the associated terminology. A second part deals with the development of a detailed knowledge-model using the Bond-graph formalism for the actuating system. A particular effort is made to standardize the components and their interfaces in an object-oriented approach. The last part deals with the sealing and guiding devices of flight control cylinders. Given the objective of using fluid bearings, the various ways of generating a normal force within a fluid film are analyzed. Then, a more detailed study of the hydrostatic thrust bearings and the conical hybrid bearings is then carried out taking into account the constraints specific to aeronautics. All the knowledge acquired is applied to a concrete case of development, aided by the models, of high frequency actuators for the active control of a rotor.

Le travail présenté dans cette thèse porte sur l’étude du pré-dimensionnement d’un actionneur électromécanique à entrainement direct dans une chaine de commande de vol électrique d’un hélicoptère.Le dimensionnement de cet actionneur répond à un brevet déposé par Airbus Helicopters et les éléments composant l’actionneur devront remplir les critères de sécurité des équipements embarqués des fonctions critiques. Dans un premier temps, une méthode de pré-dimensionnement d’actionneur électromécanique et plus particulièrement de machine électrique est décrite à l’aide d’un modèle analytique. Ce modèle est couplé à un algorithme d’optimisation afin de minimiser la masse tout en conservant les performances. Un prototype a fait l’objet d’une fabrication à l’échelle 1. Dans un second temps, une architecture et une méthode de calcul de l’asservissement sont définies afin d’obtenir les performances attendues par un cahier des charges en termes de précision, vitesse et stabilité. Dans le but d’améliorer le processus de dimensionnement et de prévoir le comportement dynamique de l’asservissement, des modèles multi-physiques sont développés et utilisés. Enfin, le prototype est mis en place sur un banc d’essai. Il a permis de valider le modèle de pré-dimensionnement et plus généralement de caractériser les machines électriques. Enfin, une campagne d’essai avec des cas de panne est réalisée pour mesurer et analyser les effets des pannes sur cet actionneur. / The thesis aim is the pre-design of a direct drive electromechanical actuator for Fly-By-Wire flight control of rotorcraft.The pre-design of this actuator answer to a Airbus Helicopters patent and all component must be compliant with the safety criteria of embedded system for critical function. Over a first phase, a method of electromechanical actuator’s pre-design and particularly of electrical machine is described with an analytical model. This model is linked with an optimization algorithm in order to minimize the actuator’s mass with the whole performances. A full scale prototype has been built.Over a second phase, architecture and methods for designing control are described in order to obtain the specification performances in term of precision, speed and stability. To improve the design process and the dynamic prediction of the control, multiphysics models have been developed and used.At last, the prototype is integrated on a test bench. This one allow to validate the electrical machines pre-design and more generally, to characterize the built electrical motors. A series of failure case’s tests takes place in order to analyze and measure all the actuator effect of the failure case.

Diplomová práce se zabývá představením, popisem a vytvořením modelu postranní řídicí páky pilota s aktivní silovou zpětnou vazbou firmy Honeywell International Inc. v prostředí MATLAB Simulink. Dále pak představením problému pilotem indukovaných oscilací a možnostmi jejich předcházení, detekce a potlačení. Model řídicí páky se silovou zpětnou vazbou je použit pro potlačení detekovaných oscilací v simulaci letounu.