International Telemetering Conference Proceedings / October 25-28, 1993 / Riviera Hotel and Convention Center, Las Vegas, Nevada / This paper presents instrumentation and telemetry system techniques used in free-flight research drop model testing at the NASA Langley Research Center. The free-flight drop model test technique is used to conduct flight dynamics research of high performance aircraft using dynamically scaled models. The free-flight drop model flight testing supplements research using computer analysis and wind tunnel testing. The drop models are scaled to approximately 20% of the size of the actual aircraft. This paper presents an introduction to the Free-Flight Drop Model Program which will be followed by a description of the current instrumentation and telemetry systems used at the NASA Langley Research Center, Plum Tree Test Site. The paper describes three telemetry downlinks used to acquire the data, video, and radar tracking information from the model. Also described are two telemetry uplinks, one used to fly the model employing a ground based flight control computer and a second to activate commands for visual tracking and parachute recovery of the model. The paper concludes with a discussion of free-flight drop model instrumentation and telemetry system development currently in progress for future drop model projects at the NASA Langley Research Center.

The thesis traces the history of missile aerodynamic prediction methods and defines the aerodynamic requirements for the subsonic free-flight projectiles configurations under consideration. Different types of trajectory model are described with the aerodynamic input requirement being analysed. Methods of generating the required aerodynamic data for the trajectory models are discussed emphasising the aerodynamic models capabilities, weaknesses and ease of use. The method of masses aerodynamic prediction method is defined, highlighting the adaptations to the method that were carried out to generate the aerodynamic stability data required for subsequent projectile trajectory analysis. An assessment of the sensitivity and accuracy of the simulated data is carried out using experimental flight trial data on different projectile configurations. Finally, using the simulation models developed in previous chapters, a parametric analysis is carried out on different projectile configurations to optimise the trajectory performance.

This thesis deals with innovative concept of air traffic operations such as Free Flight. First, a baseline is established to determine how controllers operate under the current operation guidelines. Then flight trajectories are developed for different alternatives to the Free Flight operational concept. Finally, a comparison of these Free Flight alternatives with current operational concept is conducted to investigate an impact of Free Flight on Air Traffic Control. With the powerful features of optimization, graphics, and hierarchical modeling, the MATLAB toolboxes proved to be effective in the modeling process involved in this research. / Master of Science

No description available.

Present day air traffc control is reaching its operational limits and accommodating future traffic growth will be a challenging task for air traffic service providers and airline operators. Free Flight is a proposed transition from a highly-structured and centrally-controlled air traffic system to a self-optimized and highly-distributed system. In Free Flight, pilots will have the flexibility of real-time trajectory planning and dynamic route optimization given airspace constraints (traffic, weather etc.). A variety of advanced air traffc management (ATM) concepts are proposed as enabling technologies for the realization of Free Flight. Since these concepts can be exposed to unforeseen and challenging scenarios in Free Flight, they need to be validated and evaluated in order to implement the most effective systems in the field. Evaluation of advanced ATM concepts is a challenging task due to the limitations in the existing scenario generation methodologies and limited availability of a common platform (air traffic simulator) where diverse ATM concepts can be modeled and evaluated. Their rigorous evaluation on safety metrics, in a variety of complex scenarios, can provide an insight into their performance, which can help improve upon them while developing new ones. In this thesis, I propose a non-propriety, non-commercial air traffic simulation system, with a novel representation of airspace, which can prototype advanced ATM concepts such as conflict detection and resolution, airborne weather avoidance and cockpit display of traffic information. I then propose a novel evolutionary computation methodology to algorithmically generate a massive number of conflict scenarios of increasing complexity in order to evaluate conflict detection algorithms. I illustrate the methodology in detail by quantitative evaluation of three conflict detection algorithms, from the literature, on safety metrics. I then propose the use of data mining techniques for the discovery of interesting relationships, that may exist implicitly, in the algorithm's performance data. The data mining techniques formulate the conflict characteristics, which may lead to algorithm failure, using if-then rules. Using the rule sets for each algorithm, I propose an ensemble of conflict detection algorithms which uses a switch mechanism to direct the subsequent conflict probes to an algorithm which is less vulnerable to failure in a given conflict scenario. The objective is to form a predictive model for algorithm's vulnerability which can then be included in an ensemble that can minimize the overall vulnerability of the system. In summary, the contributions of this thesis are: 1. A non-propriety, non-commercial air traffic simulation system with a novel representation of airspace for efficient modeling of advanced ATM concepts. 2. An Ant-based dynamic weather avoidance algorithm for traffic-constrained enroute airspace. 3. A novel representation of 4D air traffic scenario that allows the use of an evolutionary computation methodology to evolve complex conflict scenarios for the evaluation of conflict detection algorithms. 4. An evaluation framework where scenario generation, scenario evaluation and scenario evolution processes can be carried out in an integrated manner for rigorous evaluation of advanced ATM concepts. 5. A methodology for forming an intelligent ensemble of conflict detection algorithms by data mining the scenario space.

L'utilisation des coefficients aérodynamiques pour caractériser le comportement d'un objet en vol libre demeure un sujet de recherche parmi les plus complexes et les plus étudiés dans le domaine de la balistique extérieure. La présente étude analyse l'identification des coefficients aérodynamiques à partir de données obtenues lors d'essais en vol libre. Elle vise à modéliser, définir ainsi que maîtriser les techniques d'identification de paramètres les plus adaptées au problème qu'est la détermination des coefficients aérodynamiques. Le travail de thèse a été dédié au développement d'une procédure d'identification pour la détermination des coefficients aérodynamiques à partir de mesures de vol libre et a été testée pour deux cas d'application : un corps de rentrée dans l'atmosphère et un projectile stabilisé par empennage. Cette procédure nécessite plusieurs étapes telles que la description du comportement d'un objet en vol libre sous la forme d'un modèle non linéaire en représentation d'état, la description polynomiale des coefficients aérodynamiques en fonction du nombre de Mach et de l'incidence, les analyses d'identifiabilité a priori et a posteriori suivies de l'estimation des paramètres. De plus, dans le but d'augmenter la probabilité que les coefficients caractérisent l'aérodynamique de l'objet pour l'ensemble des conditions d'essais et d'améliorer la précision des coefficients estimés, une stratégie "multiple fit" a été appliquée. Cette approche fournit une base de données de coefficients aérodynamiques, qui sont déterminés à partir de plusieurs séries de mesures analysées simultanément, afin de décrire le spectre le plus complet du mouvement de l'objet / The use of aerodynamic coefficients for the characterization of the behaviour of an object in flight remains one of the oldest and most emergent research project in the field of exterior ballistic. The present study investigates the identification of the aerodynamic coefficients based on measured data, gathered during free flight tests from different measurement techniques. This project deals with topics as modelling, defining and mastering parameter identification techniques best suited to the problem of the aerodynamic coefficients determination. In the frame of this study, an identification procedure was developed for the aerodynamic coefficients determination based on free flight measurements and was tested for two application cases: a re-entry space vehicle and a fin stabilized reference projectile. This procedure requires several steps such as the description of the behaviour of the vehicle in free flight as a nonlinear state-space model representation, the polynomial descriptions of the aerodynamic coefficients as function of Mach number and incidence, the a priori and a posteriori identifiability analyses, followed by the estimation of the parameters from free flight measurements. Moreover, to increase the probability that the coefficients define the vehicle’s aerodynamics over the entire range of test conditions and to improve the accuracy of the estimated coefficients, a multiple fit strategy was considered. This approach provides a common set of aerodynamic coefficients that are determined from multiple data series simultaneously analyzed, and gives a more complete spectrum of the vehicle’s motion

Afin d'atteindre leur cible, les projectiles guidés d'artillerie nécessitent d'être dotés d'un dispositif de pilotage. Des surfaces de contrôle déployables et orientables sont donc nécessaires. Toutefois, le montage de gouvernes ajustables sur une ogive est une tâche mécaniquement ardue. En effet, lors du tir effectué par canon, l'équipement de bord subit une accélération significative, ce qui implique que des liaisons mécaniques particulièrement robustes doivent être conçues entre les ailettes et le corps. Cette technologie est bien maîtrisée lorsqu'elle est employée sur des projectiles de gros calibre, mais devient bien plus compliquée quand elle doit être adaptée pour être intégrée dans des petits ou moyens calibres. Néanmoins, dans des conditions de vol supersonique, des ondes de choc qui interagissent avec des surfaces solides sont susceptibles de considérablement modifier la distribution de pression. Ce principe a permis d'imaginer une méthode alternative de pilotage de projectiles supersoniques en exploitant des ondes de choc générées au moyen de petites perturbations créées à partir d'un micro-actionneur de forme cylindrique, aussi appelé micro-plot. Comme les forces de portance exercée sur un corps sont essentiellement dues à une pression appliquée sur de grandes surfaces, il a été choisi de se baser sur une configuration stabilisée par empennage. En vue de simplifier l'étude, le travail a été effectué sur un projectile académique de référence bien connu appelé le Basic Finner.Des expériences ont tout d'abord été effectuées dans la soufflerie supersonique de l'ISL sur une plaque plane comportant un plot et deux ailettes verticales. Ces mesures ont permis de valider la capacité de simulations numériques stationnaires RANS à prédire à la fois la distribution pariétale de la pression que génère un tel actionneur et le champ de vitesse de l'écoulement dans son voisinage. Les distributions de pression et de vitesse ont été mesurées en utilisant des méthodes optiques appelés Pressure Sensitive Paints (PSP) et Particle Image Velocimetry (PIV) afin d'être comparés avec les résultats de la CFD. Une étude paramétrique a ensuite été menée en se basant exclusivement sur ces simulations RANS. Ces calculs ont permis de déterminer l'emplacement optimal pour lequel le plot est le plus efficace sur toute l'enveloppe de vol du projectile. A partir de cette position optimale, deux configurations spécifiques ne générant aucun moment de roulis ont été étudiées numériquement et comparés en termes d'efficacité. En utilisant les coefficients aérodynamiques résultants de ce travail, des simulations de trajectoires à 6 degrés de liberté (6-DOF) ont été réalisées avec le code de BALCO (OTAN). Celles-ci ont permis de déterminer la déviation potentielle qui peut être obtenue sur une des deux configurations retenues en employant un tel micro-actionneur. Ces simulations 6-DOF ainsi que l'effet de du plot sur le projectile ont enfin été validés lors d'une campagne d'essai en vol libre qui a eu lieu sur le champ de tir de l'ISL. / In order to reach their target, guided artillery projectiles need some steering capability. Folding and adjustable control surfaces are thus necessary. However, mounting adjustable rudders on a shell is a difficult task, mechanically speaking. Indeed, during the gun launch, the onboard equipment undergoes significant acceleration so that robust mechanical joints have to be designed between the rudders and the body. This technique performs very well on large-caliber projectiles, but becomes more complicated when it has to be embedded in small- or medium-caliber ones. Nevertheless, under supersonic flight conditions, shock waves interacting with solid surfaces are likely to strongly modify the pressure distribution. This principle made it possible to imagine a way of steering small-caliber vehicles using shock waves generated by means of small disturbances created by a cylindrical-shaped micro-actuator, also called micro-pin. As lift forces exerted on a body are mainly due to the pressure applied to large surfaces, a finned configuration has been chosen. To simplify the study, the work has been conducted on the Basic Finner, a well known academic reference projectile.Experiments were first performed in the ISL supersonic wind tunnel on a flat plate on which a pin and two vertical projectile-like fins were mounted in order to validate the capability of steady RANS numerical simulations to predict both the pressure footprint of such an actuator and the flow velocity in its vicinity. Pressure and velocity distributions have been measured by using optical methods called Pressure-Sensitive Paint (PSP) and Particle Image Velocimetry (PIV) in order to be compared with the calculation results. A parametric study was then conducted with these RANS simulations so that the optimum location for which the pin is the most effective over the complete flight envelope of the projectile could be determined. Using this optimum position two specific no-roll momentum configurations were studied numerically and compared in terms of effectiveness. By using the aerodynamic coefficients resulting from this work, 6-Degree-Of-Freedom (6-DOF) trajectory simulations were performed with the NATO BALCO code on one of these configurations in order to determine the potential deviation which can be obtained with such an actuator. These 6-DOF simulations as well as the pin effect on the projectile could finally be validated during a free-flight campaign that took place at the ISL open-range testing site.

Cette thèse explore des pistes d'amélioration du système de trafic aérien dans l'espace océanique de l'Atlantique Nord (NAT). D'abord, on considère le système actuel, où les avions suivent les rails prédefinis. On favorise les re-routages entre rails, diminuant la congestion dans l'espace continental. On applique des méthodes stochastiques d'optimisation pour trouver une configuration de vols sans conflits avec la séparation reduite entre aéronefs. Ensuite, on simule la planification des trajectoires avec le Wind Networking (WN). La source prinicipale des erreurs dans la prédiction de trajectoires étant l'incertitude dans la prévision du vent, le WN permet aux avions d'échanger leurs vents mesurés afin d'ajuster leurs prédictions. Enfin, on introduit le concept de free-flight dans NAT. Etant donné des trajectoires vent-optimales, on applique une méthode stochastique d'optimisation pour réduire le nombre de conflits au niveau stratégique, tout en conservant les trajectoires proches de leur optimum. Nos résultats numériques mettent en évidence plusieurs pistes pour améliorer le système de trafic aérien dans NAT, en considérant de nouvelles technologies et de nouveaux concepts. / This thesis investigates the ways to improve the air traffic system in the highly congested North Atlantic oceanic airspace (NAT). First, we consider the current system, where aircraft follow predefined NAT tracks. We favor the re-routings between tracks, decreasing congestion in pre-oceanic airspace, and apply stochastic methods of optimization to find a conflict-free flight configuration with reduced separation between aircraft. Second, we simulate trajectory prediction by Wind Networking (WN). While the main source of time prediction errors is the uncertainty in wind forecast, WN permits aircraft to exchange measured winds and adjust their predictions using this recent and accurate information. Third, we study the impact of introducing the free flight concept in NAT. We apply a stochastic method of optimization on data provided by NASA consisting of NAT flights with wind optimal trajectories. The aim is to reduce the number of conflicts on the strategic level, while keeping the trajectories close to the optimal routes. Our computational experiments show that the air traffic situation in NAT can be improved in several different ways, considering new technologies and new trajectory planning concepts.

The master thesis expresses the opinion on application of the Free Flight concept in European Airspace. In the beginning, the reason and the circumstances for concept application are characterized from both theoretical and practical approach. Afterwards, the key technology elements are defined as well as the ideal approach for developing them. Especially system ASAS was a subject of the deep investigation. Then the system ADS-B is introduced with all related issue from a performance point of view. Finally, the main factors affecting the capacity of the ASAS system in specific area of Airspace are investigated.

Thermals are regions of rising hot air formed on the ground through the warming of the surface by the sun. Thermals are commonly used by birds and glider pilots to extend flight duration, increase cross-country distance, and conserve energy. This kind of powerless flight using natural sources of lift is called soaring. Once a thermal is encountered, the pilot flies in circles to keep within the thermal, so gaining altitude before flying off to the next thermal and towards the destination. A single thermal can net a pilot thousands of feet of elevation gain, however estimating thermal locations is not an easy task. Pilots look for different indicators: color variation on the ground because the difference in the amount of heat absorbed by the ground varies based on the color/composition, birds circling in an area gaining lift, and certain types of cloud formations (cumulus clouds). The above methods are not always reliable enough and pilots study the weather for thermals by estimating solar heating of the ground using cloud cover and time of year and the lapse rate and dew point of the troposphere. In this paper, we present a Machine Learning based solution for assisting in forecasting thermals. We created a custom dataset using flight data recorded and uploaded to public databases by soaring pilots. We determine where and when the pilot encountered thermals to pull weather and satellite images corresponding to the location and time of the flight. Using this dataset we train an algorithm to automatically predict the location of thermals given as input the current weather conditions and terrain information obtained from Google Earth Engine and thermal regions encountered as truth labels. We were able to converge very well on the training and validation set, proving our method with around a 0.98 F1 score. These results indicate success in creating a custom dataset and a powerful neural network with the necessity of bolstering our custom dataset.