Dissertations / Theses on the topic 'Helicopter transmissions'

The thesis presents a framework for integrating models, simulation, and experimental data to diagnose incipient failure modes and prognosticate the remaining useful life of critical components, with an application to the main transmission of a helicopter. Although the helicopter example is used to illustrate the methodology presented, by appropriately adapting modules, the architecture can be applied to a variety of similar engineering systems. Models of the kind referenced are commonly referred to in the literature as physical or physics-based models. Such models utilize a mathematical description of some of the natural laws that govern system behaviors. The methodology presented considers separately the aspects of diagnosis and prognosis of engineering systems, but a similar generic framework is proposed for both. The methodology is tested and validated through comparison of results to data from experiments carried out on helicopters in operation and a test cell employing a prototypical helicopter gearbox. Two kinds of experiments have been used. The first one retrieved vibration data from several healthy and faulted aircraft transmissions in operation. The second is a seeded-fault damage-progression test providing gearbox vibration data and ground truth data of increasing crack lengths. For both kinds of experiments, vibration data were collected through a number of accelerometers mounted on the frame of the transmission gearbox. The applied architecture consists of modules with such key elements as the modeling of vibration signatures, extraction of descriptive vibratory features, finite element analysis of a gearbox component, and characterization of fracture progression. Contributions of the thesis include: (1) generic model-based fault diagnosis and failure prognosis methodologies, readily applicable to a dynamic large-scale mechanical system; (2) the characterization of the vibration signals of a class of complex rotary systems through model-based techniques; (3) a reverse engineering approach for fault identification using simulated vibration data; (4) the utilization of models of a faulted planetary gear transmission to classify descriptive system parameters either as fault-sensitive or fault-insensitive; and (5) guidelines for the integration of the model-based diagnosis and prognosis architectures into prognostic algorithms aimed at determining the remaining useful life of failing components.

In the conventional helicopter, the transmission and powerplant systems are the major production and operator direct operating cost drivers. Additionally, they are related to helicopter safety and reliability concerns and impose performance boundaries. As a consequence, they need to be addressed. Adapting the transmission and powerplant systems with the introduction of more electric technologies, which are reported to be more reliable and cost friendly, involves a gross weight penalty, which cannot be accepted from a performance viewpoint. The implementation of liquid hydrogen, with the objective to introduce a sustainable energy carrier and free cold source for the high temperature superconductive devices driving the tail rotor, appears unattractive, from either a weight or a exploitation standpoint. Biodiesel could be an alternative to Avgas driven configurations, but at the moment, it has questionable chemical characteristics and is therefore discarded. Conceptual alternatives to the conventional helicopter explored in an attempt to verify their ability to overcome the stated performance, safety and cost aspects, are subjected to the same problems, the Turbine Driven Rotor (TDR) helicopter configuration excepted. The TDR helicopter drives a coaxial rotor configuration by means of a rotor embedded Ljungstr¨om turbine, omitting the need for a mechanical transmission system. Three TDR helicopter thermodynamic cycles are proposed. The piston engine powered TDR cycle shows to be of interest for the low weight class helicopters. The turbofan powered TDR cycle is preferred in the mid and high weight categories, benefitting from its configurational simplicity. The more complex turboshaft powered TDR cycle requires a heat exchanger, is heavier and thus not recommended. With respect to the Ljungstrom turbine, the loss models of Soderberg and Ainley and Mathieson used to establish its geometry and performance characteristics are generally acceptable and appear coherent, while a deviation angle correction is developed to cope with the radial outflow configuration of the turbine. Similarly, loss models for the internal leakage and disk friction are proposed. However, these models could not be substantiated by means of experiments. A design methodology to implement the Ljungstrom turbine in the helicopter rotor head is presented and allows adjusting the thermodynamic cycle characteristics such as to maximise the performance gain with respect to the conventional helicopter. For nominal operating conditions, ISA SLS, a VLR-class TDR helicopter shows to bear a performance gain of 10% over a conventional helicopter when equipped with an Avgas engine and 14% when a Diesel engine is used. Hereby, the cycle pressure ratio remained low, i.e. approximately 1.25, allowing a turbine polytropic effciency of 87%. An identical study with a NH-90-class TDR helicopter proved to offer a performance potential of 50% at a cycle pressure ratio around 1.6 and a turbine polytropic effciency of 90%. In all cases, the gas temperature at the inlet of Ljungstrom turbine remained below the rotor bearing temperature limit of 400 K.

Dissertation (Ph.D.)--University of Toledo, 2004.
Typescript. "A dissertation [submitted] as partial fulfillment of the requirements of the Doctor of Philosophy degree in Engineering." Bibliography: leaves 220-247.

La boîte de transmission principale (BTP) est une des principales sources dubruit perçu dans les cabines d’hélicoptères et pénalise fortement le confort acoustique deséquipages et passagers. Afin de réduire l’impact de cette source, les phénomènes acoustiqueset vibratoires mis en jeu par les boîtes de transmission à engrenages doivent être compris etsimulés durant les phases de développement. De cette façon, le comportementvibroacoustique des BTP pourra être amélioré dès la conception, réduisant ainsi le coût, lamasse et les difficultés d’intégration des solutions d’insonorisation. Ce travail présente lesBTP d’hélicoptères ainsi que le bruit qu’elles génèrent. Il présente également nosdéveloppements concernant la modélisation du comportement dynamique des BTP afin d’encalculer le bruit. Nous avons développé un code éléments finis permettant d’effectuer desétudes paramétriques afin d’ajuster le design des boîtes de transmission lors des phases dedéveloppement. Notre modèle est capable de calculer les efforts dynamiques aux paliers detransmissions composées de plusieurs engrenages cylindriques et spiro-coniques. Enfin, nousanalysons des mesures acoustiques et vibratoires effectuées autour de deux BTP pourplusieurs conditions de couple et vitesse. Ces mesures nous permettent de mieux comprendrele comportement vibroacoustique des BTP et de confirmer certaines tendances observées avecnotre modèle
Main gearbox (MGB) is one of the main noise sources in helicopter cabinsand it strongly penalizes acoustic comfort of crews and passengers. In order to reduce theimpact of this source, acoustic and vibration mechanisms of gearboxes have to be understoodand simulated during the development phases. By this way, MGB vibroacoustic behaviourcould be improved by design, thus reducing cost, additional weight and integration difficultiesof sound-proofing solutions. This work presents helicopters MGB and the noise they generate.It also presents our developments regarding the modelling of MGB dynamic behaviour fornoise computation. We have developed a finite elements code allowing to conduct parametricstudies to tune the gearboxes design in early development phases. Our model is able tocompute dynamic loads on bearings of any transmission composed of several cylindrical andspiral bevel gears. At last, we analyse acoustic and vibration measurements done around twoMGB for several conditions of torque and speed. These measurements allow to betterunderstand MGB vibroacoustic behaviour and to confirm some trends observed with ourmodel

Thesis (M.S. in Operations Research) Naval Postgraduate School, September 1997.
"September 1997." Thesis advisor(s): Robert R. Read. Includes bibliography references (p. 65). Also available online.

Approved for public release; distribution is unlimited
Health and Usage Monitoring Systems (HUMS) is an emerging technology in helicopter aviation. The United States Navy is evaluating its viability for use on its helicopter fleet. HUMS uses sensors placed throughout the helicopter to monitor and record vibration signals and numerous other aircraft operating parameters. This thesis evaluates the vibration signals recorded by a HUMS system using a statistical technique called tree structured classification. The goal of the analysis is to demonstrate the technique's ability to predict the presence of faulted components in the transmission of the SH-60B autonomously operated in a Helicopter Transmission Test Facility at Naval Air Warfare Center, Trenton, New Jersey. The analysis is implemented in the statistical software package S-plus (Mathsoft Inc., 1995)

It is important to ensure that Transpower is prepared to deliver upcoming transmission tower refurbishment projects that are located on sites with difficult access. This project reviews the availability, capability and cost of utilising alternative construction methods and any associated wider issues. The focus of this report is on how Transpower can more effectively utilise helicopters and gin poles for transmission tower erection and material delivery on remote sites.

The transformation of Joint forces to be lighter, more lethal, and capable of deploying from multiple dispersed locations free of prepared landing zones requires a dedicated heavy lift VTOL aircraft capable of rapidly delivering large payloads, such as the 20 to 26 ton Future Combat System, at extended ranges in demanding terrain and environmental conditions. Current estimates for a single main rotor configuration place the design weight over 130,000 pounds with an installed power of approximately 30,000 horsepower. Helicopter drive systems capable of delivering torque of this magnitude succeeded in the Russian Mi-26 helicopters split-torque design and the Boeing VERTOL Heavy Lift Helicopter (HLH) prototypes traditional multi-stage planetary design. The square-cube law and historical trends show that the transmission stage weight varies approximately as the two-thirds power of torque; hence, as the size and weight of the vehicle grows, the transmissions weight becomes an ever-increasing portion of total gross weight. At this scale, optimal gearbox configuration and component design holds great potential to save significant weight and reduce the required installed power. The drive system design methodology creates a set of integrated tools to estimate system weight and rapidly model the preliminary design of drives system components. Tools are provided for gearbox weight estimation and efficiency, gearing, shafting, and cooling. Within the same architecture, the designer may add similar tools to model subcomponents such as support bearings, gearbox housing, freewheeling units, and rotor brakes. Measuring the relationships between key design variables and system performance metrics reveals insight into the performance and behavior of a heavy lift drive system. A parametric study of select design variables is accomplished through an intelligent Design of Experiments that utilizes Response Surface Methodology to build a multivariate regression weight model. The model permits visualization of the design space and assists in optimization of the drive system preliminary design. This methodology is applied to both the Boeing HLH and the Russian Mi-26 main gearboxes. This study applies the drive system design methodology to compare the Mi-26 split-torque gearbox over the Boeing HLH multi-stage planetary gearbox in a single main rotor heavy lift helicopter.

L’une des principales sources d’inconfort dans un hélicoptère sont les vibrations transmises par le rotor à la structure de l’appareil. En vol d’avancement, des efforts aérodynamiques cycliques sont subis par l’ensemble des pales en tête rotor et génèrent de très fortes vibrations basse fréquence (aux alentours des 17Hz) transmises aux passagers via la boîte de transmission principale puis le fuselage lui-même. Afin de garantir le confort des membres d’équipage et des passagers, de nombreux systèmes antivibratoires ont été conçus. Ces systèmes sont généralement passifs car la majorité de l’énergie vibratoire transmise à la structure se situe à une fréquence unique ωc correspondant à bΩ avec b le nombre de pales et Ω la fréquence de rotation du rotor. Cependant, les appareils modernes évoluent et le régime rotor jusqu’alors fixe durant toutes les phases de vol varie à présent pour des préoccupations de performances et de consommation (variation de l’ordre de +/-10% autour de bΩ). Cette nouvelle contrainte dans la conception des hélicoptères rend pertinente la technologie des systèmes antivibratoires actifs, pouvant s’adapter à la sollicitation en termes d’amplitude et fréquence. Lors de ces travaux de thèse, la suspension passive SARIB de Airbus Helicopters basée sur le principe du DAVI (Dynamic Antiresonant Vibration Isolator) est modifiée afin d’être rendue active par ajout d’une partie actuation/commande. La théorie des lois et algorithmes de contrôle utilisés dans ces travaux, est présentée en détail afin de poser solidement les bases du contrôle actif du prototype de suspension conceptualisé ici à savoir le contrôle FXLMS (adaptatif) et le contrôle optimal LQG. Afin de simuler le fonctionnement du système, un modèle tridimensionnel de la suspension active est construit, couplé à la structure souple de l’hélicoptère (NH90). Sur ce modèle sont alors appliquées les différentes lois de commande introduites auparavant et leurs performances comparées dans différents cas de chargement en tête rotor et surtout pour différentes fréquences de sollicitation. De même, pour chaque algorithme, différentes localisations des capteurs d’erreur sont étudiées afin de converger vers une configuration optimale. Les simulations démontrent que l’algorithme FXLMS feedforward est très bien adapté au contrôle des perturbations harmoniques et permet de réduire très significativement le niveau vibratoire du plancher cabine, sans réinjection parasite dans le reste de la structure. Une comparaison de l’efficacité du SARIB actif avec les systèmes d’absorbeurs en cabine est ensuite effectuée pour démontrer la pertinence d’utiliser le principe du DAVI comme base d’un système actif. Les travaux de cette thèse traitent également des essais réalisés en laboratoire sur le prototype échelle 1 de la suspension SARIB active avec contrôle FXLMS
One of the main causes of discomfort in helicopters are the vibrations transmitted from the rotor to the structure. In forward flight, the blades are submitted to cyclic aerodynamic loads which generate low frequency (around 17Hz) but high energy mechanical vibrations. These vibrations are transmitted from the rotor to the main gearbox, then to the structure and finally to the crew and passengers. In order to maintain acceptable comfort for crew members and passengers, a lot of antivibration devices have been developed since the last 30 years. These systems are generally passive because most of the mechanical energy transmitted to the structure is at only one frequency ωc which is equal to the product bΩ with b the number of blades and Ω the rotor rotational speed. However, modern helicopters evolve and the rotor rpm, which has always been considered as fixed during flight is now a function of time, depending on the flight phases in order to increase performances and reduce energy consumption (variation bandwidth of Ω +/- 10%). This new constraint on the design of helicopters makes the active antivibration technology completely relevant with its capacity to adapt in terms of amplitude and frequency to the perturbation. During this thesis, the passive suspension called SARIB from Airbus Helicopters, based on the DAVI principle (Dynamic Antiresonant Vibration Isolator) is modified in order to implement active components and command (actuation). The theory of the control algorithms used in this thesis is presented in detail in order to define the theoretical tools of the active DAVI control which are : FXLMS control (adaptive control) and LQG (optimal control). To simulate the complete system, a 3D multibody model of the active suspension has been set up, coupled to a the flexible structure of a NH90 (Airbus Helicopters). On this model are applied the different control algorithms presented before and their performances are compared for different loads with variable frequency on the rotor hub. In the same way, different locations for the error sensors in the structure are studied to find the optimal control configuration. The simulations show that the FXLMS algorithm is well suited for the control of harmonic perturbations and reduce significantly the dynamic acceleration level on the cabin floor, without parasite reinjection on other parts of the structure. A comparison of the active SARIB with classical cabin vibration absorbers is also made in terms of efficiency in order to show the advantages of using the DAVI system as a base for an active antivibration device. Finally, this thesis also presents the experiments realized in the dynamics laboratory of Airbus Helicopters on a 1:1 scale prototype of the active SARIB suspension with FXLMS control. The results demonstrate the efficiency of the active suspension architecture and control algorithms

The primary objective of the research reported in this thesis was the improvement of safety in helicopters by identifying and, where necessary, developing vibration analysis techniques for the detection and diagnosis of safety critical faults in helicopter transmission systems. A review and, where necessary, expansion of past research is made into (a) the mechanisms involved in the production of vibrations in mechanical systems, (b) the failure modes experienced in geared transmission systems, (c) which failure modes are critical to the safety of helicopters, (d) how the safety critical failure modes affect the vibration signature, and e) the vibration analysis techniques currently used to detect safety critical failures. The effectiveness of the currently available vibration analysis techniques is investigated using in-flight vibration data from Royal Australian Navy helicopters and seeded fault data from a purpose built spur gear test rig. Detailed analysis of techniques for synchronous signal averaging of gear vibration data is undertaken, which includes the development of new methods of modelling and quantifying the effects of synchronous averaging on non-synchronous vibration. A study of digital resampling techniques is also made, including the development of two new methods which provide greater accuracy and/or efficiency (in computation) over previous methods. A new approach to fault diagnosis is proposed based on time-frequency signal analysis techniques. It is shown that these methods can provide significant improvement in diagnostic capabilities over existing vibration analysis techniques. Some limitations of general time-frequency analysis techniques are identified and a new technique is developed which overcomes these limitations. It is shown that the new technique provides a significant improvement in the concentration of energy about the instantaneous frequency of the individual components in the vibration signal, which allows the tracking of small short term amplitude and frequency modulations with a high degree of accuracy. The new technique has the capability of 'zooming' in on features which may span only a small frequency range, providing an enhanced visual representation of the underlying structure of the signal.

Ces travaux de thèse ont été réalisés grâce à une collaboration entre Safran Helicopter Engines (anciennement Turbomeca) et le Laboratoire de Mécanique des Contacts et des Structures (LaMCoS) de l’INSA de Lyon (UMR CNRS 5259). Les boîtes de transmission par engrenages des moteurs d’hélicoptères convoient la puissance mécanique du turbomoteur aux accessoires (pompes, démarreur) et au rotor. Leur conception dépend des nécessités des équipements embarqués, en particulier l’allègement pour réduire la consommation en carburant. Les engrenages haute vitesse de la transmission sont allégés grâce à des enlèvements de matière dans les corps sous la denture, les voiles-minces. Un modèle dynamique d’engrenages a été développé pendant ce projet de recherche. Son approche modulaire permet l’inclusion conjointe des sollicitations dues aux vibrations de l’engrenage et de la nouvelle flexibilité des voiles-minces. Il dérive d’un modèle à paramètres concentrés, comprenant des arbres en poutre, des paliers et carters sous forme de raideurs additionnelles et un élément d’engrenage rigide inclus par son nœud central. Hypothèse est faite que tous les contacts sont situés sur les lignes de contact du plan d’action. Ces lignes sont discrétisées selon des tranches-minces dans les dents et la déviation normale des cellules est recalculée à chaque pas de temps selon la déflexion de la denture. Le nouveau modèle remplace l’engrenage rigide par une modélisation EF du pignon et/ou de la roue condensée sur les nœuds de jante. Une interface lie les raideurs du plan d’action discrétisé aux éléments finis du corps d’engrenage. L’élément prend donc en compte à la fois les sollicitations de l’engrenage et le comportement statique et modal des corps flexibles en dynamique. Des comparaisons sont faites avec des données numériques et expérimentales. Elles attestent de la capacité du nouveau modèle à prédire le comportement dynamique des engrenages flexibles à hauts régimes de rotation. Ces résultats intègrent entre autres des données locales et globales en dynamique. Finalement, le modèle est utilisé sur les deux cas académiques validés pour visualiser les effets des corps flexibles plus en détails. Un premier focus sera fait sur la déflexion statique due aux charges d’engrènement et sur l’optimisation sur le fonctionnement dynamique possible. Puis, les impacts des sollicitations de l’engrènement sur le voile en rotation seront étudiés. Enfin, le pignon et la roue seront affinés, afin de visualiser l’optimisation massique possible et son impact sur la dynamique de l’engrenage
The research work presented in this manuscript was conducted in the Contact and Structural Mechanics Laboratory (LaMCoS) at INSA Lyon, in partnership with Safran Helicopter Engines (formerly-Turbomeca). In helicopters, the power from the turboshaft is transmitted to the rotor and the various accessories (pumps, starters etc…) via transmission gearboxes. In the context of high-speed, light-weight aeronautical applications, mechanical parts such as gears have to meet somehow contradictory design requirements in terms of reliability and mass reduction thus justifying precise dynamic simulations. The present work focuses on the definition of modular gear dynamic models, capable of integrating both the local phenomena associated with the instant contact conditions between the tooth flanks and the more global aspects related to shafts, bearings and particularly the contributions of light thin-rimmed /-webbed gear bodies. The proposed models rely on combinations of condensed sub-structures, lumped parameter and beam elements to simulate a pinion-gear pair, shafts, bearings and housing. Mesh elasticity is time-varying, possibly non-linear and is accounted for by Winkler foundations derived from a classic thin-slice model. The contact lines in the base plane are therefore discretised into elemental segments which are all attributed a mesh stiffness function and a normal deviation which are updated depending on the pinion and gear angular positions. The main originality in this PhD consists in inserting condensed finite elements models to simulate flexible gear bodies while keeping the simple and faster rigid-body approach for solid gears. To this end, a specific interface has been developed to connect the discretised tooth contact lines to the continuous finite element gear body models and avoid numerical spikes in the tooth load distributions for example. A number of comparisons with numerical and experimental results show that the proposed modelling is sound and can capture most of the quasi-static and dynamic behaviour of single stage reduction units with thin-webbed gears and/or pinions. The model is then applied to the analysis of academic and industrial gears with the objective of analysing the contributions of thin, flexible bodies. Results are presented which highlight the role of centrifugal effects and tooth shape modifications at high speeds. Finally, the possibility to further improve gear web design with regard to mass reduction is investigated and commented upon

Rotorcraft transmission design is limited by empirical weight trends that are proportional to the power/torque raised to the two-thirds coupled with the relative inexperience industry has with the employment of variable speed transmission to heavy lift helicopters of the order of 100,000 lbs gross weight and 30,000 installed horsepower. The advanced rotorcraft transmission program objectives are to reduce transmission weight by at least 25%, reduce sound pressure levels by at least 10 dB, have a 5000 hr mean time between removal, and also incorporate the use of split torque technology in rotorcraft drivetrains of the future. The major obstacle that challenges rotorcraft drivetrain design is the selection, design, and optimization of a variable speed transmission in the goal of achieving a 50% reduction in rotor speed and its ability to handle high torque with light weight gears, as opposed to using a two-speed transmission which has inherent structural problems and is highly unreliable due to the embodiment of the traction type transmission, complex clutch and brake system. This thesis selects a nontraction pericyclic continuously variable transmission (P-CVT) as the best approach for a single main rotor heavy lift helicopter to target the above mentioned obstacle for drivetrain design and provides advancement in the state of the art of drivetrain design over existing planetary and split torque transmissions currently used in helicopters. The goal of the optimization process was to decrease weight, decrease noise, increase efficiency, and increase safety and reliability. The objective function utilized the minimization of the weight and the constraint is the tooth bending stress of the facegears. The most important parameters of the optimization process are weight, maintainability, and reliability which are cross-functionally related to each other, and these parameters are related to the torques and operating speeds. The analysis of the split torque type P-CVT achieved a weight reduction of 42.5% and 40.7% over planetary and split torque transmissions respectively. In addition, a 19.5 dB sound pressure level reduction was achieved using active gear struts, and also the use of fabricated steel truss like housing provided a higher maintainability and reliability, low cost, and low weight over cast magnesium housing currently employed in helicopters. The static finite element analysis of the split torque type P-CVT, both 2-D and 3-D, yielded stresses below the allowable bending stress of the material. The goal of the finite element analysis is to see if the designed product has met its functional requirements. The safety assessment of the split torque type P-CVT yielded a 99% probability of mission success based on a Monte Carlo simulation using stochastic- petri net analysis and a failure hazard analysis. This was followed by an FTA/RBD analysis which yielded an overall system failure rate of 140.35 failures per million hours, and a preliminary certification and time line of certification was performed. The use of spherical facegears and pericyclic kinematics has advanced the state of the art in drivetrain design primarily in the reduction of weight and noise coupled with high safety, reliability, and efficiency.

Les travaux présentés à travers ce manuscrit s'inscrivent dans un contexte de recherches exploratoires sur l'optimisation des surfaces engrenantes. Après une étude approfondie de l'emploi des engrenages dans un environnement aéronautique, l'élaboration d'une nouvelle méthodologie de génération de profils de denture est proposée. Les travaux s'attachent à caractériser le comportement mécanique spécifique d'un montage d'engrenages dans les Boites de Transmission de Puissances (BTP) d'hélicoptère.Un outil informatique a été créé dans le module VBA (Visual Basic Application) d'Excel. Il permet de créer automatiquement des profils de denture conjugués et optimisés. Il a l'avantage de définir analytiquement plusieurs grandeurs physiques. L'outil a ainsi pour objectif de proposer des profils de denture optimisés selon plusieurs critères. Les « objectifs » retenus sont le rendement et la contrainte équivalente de Hertz au contact suivant le critère de Von Mises.Les travaux s'articulent autour de trois axes : - la reconstruction de profils conjugués de denture par une approche novatrice basée sur le « contact », - la construction de critères physiques (glissement, pression, contrainte, …), - la recherche de profils de denture optimaux en utilisant la simulation de Monte Carlo.Enfin, la perspective de rendre générique cette méthode afin qu'elle puisse générer n'importe quels types d'engrenage est envisagée en fin de manuscrit
The work described in the present manuscript is part of exploratory researches dealing with gears meshing surfaces optimization. After a short study of gears used in an aeronautical environment, the development of an innovative tool for tooth profile design is defined. Then, the specific behavior of a gear mesh within a helicopter main gearbox (MGB) is evaluated.A VBA software has been coded under MS Excel to generate conjugated and optimized gear tooth profiles. It advantageously defines and uses several physical parameters with their analytical formulation. The software provides at the user optimized tooth profiles according to a couple of criteria. The two “objective” functions evaluated are the efficiency and the Hertz equivalent stress within the contact using the Von Mises criterion.The work has been focused on three aspects:- The design of conjugated tooth profiles by contact sharing,- The definition of the relevant physical parameters,- The optimization of tooth profiles using Monte Carlo SimulationEventually, a generic method to design gear profiles, taking into account any physical parameters related to a gear mesh, could be expected as a future of this thesis work

碩士
國立成功大學
航空太空工程學系碩博士班
94
The digital multimedia grows vigorously in recent years and the digital image is so fascinating that we expect to be able to make the remote-control helicopter have digital-image communication ability. The thesis brings up an idea utilizing digital mobile communication module to develop an image transmission testing system which could be used on the remote-control helicopter. In addition to break the space limiting on its image transmission system and to remove the limit of distance between flight vehicle and ground server, the developed system also transmits flight information from GPS receiver via the communication module. We integrate this image system with the helicopter control system and test its feasibility. We hope that the integrated system can be improved gradually and become workable in the near future.