This thesis presents the development and implementation of a software framework for estimating the position of a drone during flight. This framework is based on an algorithm known as the Unscented Kalman Filter (UKF), a recursive method of estimating the state of a highly nonlinear system, such as an aircraft. In this thesis, we present a UKF formulation specially designed for a quadcopter carrying an Inertial Measurement Unit (IMU) and a downward-facing camera. The UKF fuses data from each of these sensors to track the position of the quadcopter over time. This work supports a number of similar efforts in the robotics and aerospace communities to navigate in GPS-denied environments with minimal hardware and minimal computational complexity. The software framework explored in this thesis provides a means for roboticists to easily implement similar UKF-based state estimators for a wide variety of systems, including surface vessels, undersea vehicles, and automobiles. We test the system's effectiveness by comparing its position estimates to those of a commercial motion capture system and then discuss possible applications. / Master of Science

No description available.

Nous présentons le développement d'un prototype de gravimètre atomique compact reposant sur l'interférométrie atomique avec des transitions Raman stimulées. Nous démontrons une amélioration importante de la compacité et de la simplicité de chaque élément du dispositif expérimental (tête de senseur, source laser, référence de fréquence micro-onde, système de filtrage des vibrations). Ce travail s'appuie sur l'utilisation d'une pyramide creuse comme miroir de rétro-réflexion, ce qui permet de réaliser toutes les fonctions d'un interféromètre atomique (piégeage et refroidissement des atomes, interféromètre, détection) avec un unique faisceau laser. Nous avons donc développé une tête de senseur très compacte, dont les fonctions clés ont toutes été simplifiées. La source laser met en jeu un unique laser émettant à 1560 nm pour interroger des atomes de Rubidium 87. Elle bénéficie de l'utilisation de composants optiques télécoms fibrés, qui ont déjà démontré leur performance et leur robustesse aux conditions environnementales. Tous les éléments du prototype sont assemblés pour permettre la mise en place de l'interféromètre. Ce type de gravimètre compact est très intéressant pour la gravimétrie de terrain. En parallèle, nous avons développé un système de réjection du bruit de vibration, basé sur l'électronique numérique. La contribution des vibrations sur la phase atomique est pré-compensée avant la fermeture de l'interféromètre, directement sur la phase optique des lasers. Ceci garantit que chaque point de mesure a une sensibilité maximum, malgré un bruit de d'accélération important. Ainsi, pour un gravimètre posé au sol en environnement urbain, nous avons démontré une sensibilité à l’accélération de l’ordre de à 1 seconde, qui atteint après 300 secondes d’intégration. Notre dispositif nous a finalement conduit à l’hybridation complète du gravimètre atomique avec un accéléromètre classique, conduisant à un accéléromètre exact très large bande [DC , 430 Hz]. Ce résultat est très prometteur, notamment pour la navigation inertielle. / We present the development of a compact atomic gravimeter, relying on atom interferometry using stimulated Raman transitions. We demonstrate a significant improvement in terms of compactness and simplicity for each element of the device (sensor head, laser source, micro-wave frequency reference, vibration rejection system). This work relies on the use of a hollow-pyramid in place of the usual retro-reflecting mirror. This component allows realizing each step of measurement (trapping and cooling of the atoms, interferometer, detection) with a single laser beam. We developed a very compact sensor head, for which we have simplified every key element. The laser source features only one single laser diode, emitting at 1560 nm to interrogate Rubidium 87 atoms. It benefits from the use of fibered optical telecom components, which have already demonstrated to be performing and robust to environmental conditions. All the elements of the accelerometer prototype are now gathered to allow for the operation of the interferometer. On-field gravimetry will greatly benefit from such compact absolute gravimeter. In parallel, we have developed a novel vibration rejection method, based on digital electronics. The atomic phase shift induced by vibrations is pre-compensated before the recombination of the wave-packets, directly on the optical phase on the Raman lasers. This ensures that each measurement point stays at maximum sensitivity, even in the presence of great acceleration noise. As a result, for a gravimeter operating directly on the ground in an urban environment, we have reached sensitivity to acceleration at a level of at 1 s, which improves down to after 300 s. Finally, our method lead us to fully hybridize the atom gravimeter with a classical accelerometer, which results in an accurate very large-band accelerometer [DC , 430 Hz]. This demonstration is very promising for applications in inertial navigation.

Ces travaux de thèse s'inscrivent à la frontière entre l'utilisation de l'interférométrie atomique pour tester un principe fondamental de physique, le principe d'équivalence faible, et le transfert des technologies développées dans ce but vers des applications industrielles, en particulier la navigation inertielle, à travers une collaboration avec l'entreprise iXBlue au sein d'un laboratoire commun (iXAtom) où nous avons travaillé à l'hybridation d'une centrale inertielle avec un accéléromètre atomique afin de corriger la dérive temporelle de la centrale.Afin de tester le prince d'équivalence faible, nous utilisons un interféromètre atomique double espèce (87Rb et 39K). Cette expérience est réalisée en laboratoire mais également en micropesanteur à bord de l'avion ZERO-G de Novespace. Cette particularité pose des contraintes sur les choix technologiques puisque le montage doit être robuste, compact et transportable. Notre système laser en est un bon exemple puisqu'il est basé des technologies télécom (1560 et 1534 nm) doublées en fréquence. Nous avons réalisé le premier test du principe d'équivalence en micropesanteur avec des atomes froids en 2015, ce qui représente une étape majeure vers la réalisation d'un instrument embarquable à bord d'un satellite.Le 39K est une espèce difficile à refroidir et à manipuler à cause de sa structure hyperfine étroite. Nous avons mis en place un refroidissement par mélasse grise pour cette espèce en ajoutant un laser résonnant avec la transition D1 du potassium. Nous avons également mis en place une préparation des atomes dans l'état non magnétique mF=0 efficace à 95%. Ces techniques ont amélioré le contraste de nos franges d'interférences d'un facteur 4 et nous a permis d'obtenir une sensibilité sur le paramètre d’Eötvös en laboratoire de 5.2x10-8 après 11500 s d'intégration. / This thesis is at the boundary of the fundamental physics with the test of the weak equivalence principle (WEP) and the transfer of the technologies developed to industrial applications such inertial navigation. We began collaboration in a joint laboratory (iXAtom) with the iXBlue company where we worked on the hybridization of an inertial unit with a cold atom accelerometer.In order to test the WEP, we use a dual-species atom interferometer (87Rb and 39K). This experiment works in the laboratory but it is designed to perform onboard the Novespace ZERO-G plane. This specificity puts constraints on the design of the setup because it needs to be robust, compact and transportable. Our laser system is a good example because it is based on Telecom technologies (1560 and 1534 nm) frequency doubled. We realized the first test of the weak equivalence principle on microgravity with cold atoms in 2015, which is a major step toward a future spatial mission.The 39K is an atomic species hard to cool and manipulate because of its narrow hyperfine structure. We implemented an other cooling method, the gray molasses, by using a laser resonant to the potassium D1 transition. We built a new sequence to prepare the atoms in the mF= 0 state. This sequence is effective at 95%. These techniques improved the contrast of our interference fringes by a factor 4 which led to the obtention of a sensitivity on the Eötvös parameter in the laboratory of 5.2x10-8 after 11500 s of integration.

A 6-Degree Of Freedom (DOF) numeric model and computer simulation along with the 1/10th scale physical model of the Rapidly Deployable Stable Platform (RDSP) are being developed at Florida Atlantic University in response to military needs for ocean platforms with improved sea keeping characteristics. The RDSP is a self deployable spar platform with two distinct modes of operation enabling long distance transit and superior seakeeping. The focus of this research is the development of a Dynamic Position (DP) and motion mitigation system for the RDSP. This will be accomplished though the validation of the mathematical simulation, development of a novel propulsion system, and implementation of a PID controller. The result of this research is an assessment of the response characteristics of the RDSP that quantifies the performance of the propulsion system coupled with active control providing a solid basis for further controller development and operational testing. / by Sean P. Marikle. / Thesis (M.S.C.S.)--Florida Atlantic University, 2009. / Includes bibliography. / Electronic reproduction. Boca Raton, Fla., 2009. Mode of access: World Wide Web.

Thesis. 1978. M.S.--Massachusetts Institute of Technology. Dept. of Aeronautics and Astronautics. / MICROFICHE COPY AVAILABLE IN ARCHIVES AND AERONAUTICS. / Includes bibliographical references. / M.S.

Despite significant progress in GPS/INS integration-based direct geo-referencing (DGR) technology over the past decade, its performance still needs to be improved in terms of accuracy and tolerance to GPS outages. This is mainly due to the limited geometric strength of the GPS satellite constellation, the quality of INS and the system integration technology. This research is focused on pseudolite (PL) augmentation to enhance the geometric strength of the GPS satellite constellation, and the Neural Network (NN) aided Kalman filter (KF) system integration algorithm to improve the geo-referencing system's performance during GPS outages. The main research contributions are summarized as below: a) Systematic errors introduced by pseudolites have been investigated. Theoretical and numerical analyses reveal that errors of troposphere delay modelling, differential nonlinearity and pseudolite location are sensitive to pseudolite receiver geometry. Their effect on final positioning solutions can be minimised by selecting optimal pseudolite and receiver locations, which is referred to as geometry design. Optimal geometry design for pseudolite augmented systems has been proposed based on simulation results in airborne surveying scenarios. b) Nonlinear geometry bias, or nonlinearity, exists in single difference processes when the unit vectors from the reference and user receivers to a satellite or pseudolite are non-parallel. Similar to long baseline differential GPS (DGPS), nonlinearity is a serious issue in pseudolite augmentation. A Projected Single Difference (PSD) method has been introduced to eliminate nonlinear geometry bias. An optimized expression has been derived to calculate the direction of project vectors, and the advantages of applying PSD in pseudolite augmented airborne DGPS have been demonstrated. c) A new method for pseudolite tropospheric delay modelling has been proposed, which is based on single-differenced GPS tropospheric delay models. The performance of different models has been investigated through simulations and field testing. The advantages and limitations of each method have been analysed. It is determined that the Bouska model performs relatively well in all ranges and elevations if the meteorological parameters in the models can be accurately collected. d) An adaptive pseudolite tropospheric delay modelling method has been developed to reduce modelling error by estimating meteorological parameters in real-time, using GPS and pseudolite measurements. Test results show that pseudolite tropospheric delay modelling errors can be effectively mitigated by the proposed method. e) A novel geo-referencing system based on GPS/PL/INS integration has been developed as an alternative to existing GPS/INS systems. With the inclusion of pseudolite signals to enhance availability and geometry strength of GPS signals, the continuity and precision of the GPS/INS system can be significantly improved. Flight trials have been conducted to evaluate the system performance for airborne mapping. The results show that the accuracy and reliability of the geo-referenced solution can be improved with the deployment of one or more pseudolites. f) Two KF and NN hybrid methods have been proposed to improve geo-referenced results during GPS outages. As the KF prediction diverges without measurement update, the performance of a GPS/INS integrated system degrades rapidly during GPS outages. Neural networks can overcome this limitation of KF. The first method uses NN to map vehicle manoeuvres with KF measurement in a loosely coupled GPS/INS system. In the second method, an NN is trained to map INS measurements with selected KF error states in a tightly coupled GPS/INS system when GPS signals are available. These training results can be used to modify KF time updates. Optimal input/output and NN structure have been investigated. Field tests show that the proposed hybrid methods can dramatically improve geo-referenced solutions during GPS outages.

The objective of the thesis is concerned on the problem of detecting superpositional signals in a wireless channel. In many wireless systems, an observed signal is commonly represented as a linear combination of the transmitted signal with the interfering signals dispersed in space and time. These systems are generally known as the interference-limited systems. The mathematical model of these systems is generally referred as a superpositional model. A distinguished characteristic of signal transmission in a time-varying wireless channel is that the channel process is not known a priori. Reliable signal reception inherently requires exploiting the structure of the interfering signals under channel uncertainty. Our goal is to design computational efficient receivers for various interference-limited systems by using advanced statistical signal processing techniques. The thesis consists of four main parts. Firstly, we have proposed a novel Multi-Input Multi-Output (MIMO) signal detector, known as the neighbourhood exploring detector (NED). According to the maximum likelihood principle, the space time MIMO detection problem is equivalent to a NP-hard combinatorial optimization problem. The proposed detector is a sub-optimal maximum likelihood detector which eliminates exhaustive multidimensional searches. Secondly, we address the problem of signal synchronization for Global Positioning System (GPS) in a multipath environment. The problem of multipath mitigation constitutes a joint estimation of the unknown amplitudes, phases and time delays of the linearly combined signals. The complexity of the nonlinear joint estimation problem increases exponentially with the number of signals. We have proposed two robust GPS code acquisition systems with low complexities. Thirdly, we deal with the problem of multipath mitigation in the spatial domain. A GPS receiver integrated with the Inertial Navigation System (INS) and a multiple antenna array is considered. We have designed a software based GPS receiver which effectively estimates the directions of arrival and the time of arrival of the linearly combined signals. Finally, the problem of communications with unknown channel state information is investigated. Conventionally, the information theoretical communication problem and the channel estimation problem are decoupled. However the training sequence, which facilitates the estimation of the channel, reduces the throughput of the channel. We have analytically derived the optimal length of the training sequence which maximizes the mutual information in a block fading channel.

<p>Navigation is about knowing your own position, orientation and velocity relative to some geographic entities. The sensor fusion considered in this thesis combines data from a dead reckoning system, inertial navigation system (INS), and measurements of the ground elevation. The very fast dynamics of aircraft navigation makes it difficult to estimate the true states. Instead the algorithm studied will estimate the errors of the INS and compensate for them. A height database is used along with the measurements. The height database is highly non-linear why a Rao-Blackwellized particle filter is used for the sensor fusion. This integrated navigation system only uses data from its own sensors and from the height database, which means that it is independent of information from outside the aircraft. </p><p>This report will describe the algorithm and illustrate the theory used. The main purpose is to evaluate the algorithm using real flight data, why the result chapter is the most important.</p>

One of Saab Space’s products is the S19 guidance system for sounding rockets.Today this system is based on an inertial navigation system that blindly calculatesthe position of the rocket by integrating sensor readings with unknown bias. Thepurpose of this thesis is to integrate a Global Positioning System (GPS) receiverinto the guidance system to increase precision and robustness. There are mainlytwo problems involved in this integration. One is to integrate the GPS with sensorfusion into the existing guidance system. The seconds is to get the GPS satellitetracking to work under extremely high dynamics. The first of the two problems issolved by using an Extended Kalman filter (EKF) with two different linearizations.One of them is uses Euler angles and the other is done with quaternions. Theintegration technique implemented in this thesis is a loose integration between theGPS receiver and the inertial navigation system. The main task of the EKF isto estimate the bias of the inertial navigation system sensors and correct it toeliminate drift in the position. The solution is verified by computing the positionof a car using a GPS and an inertial measurement unit. Different solutions to theGPS tracking problem are proposed in a pre-study. / En av Saab Space produkter är navigationssystemet S19 som styr sondraketer.Fram till idag har systemet varit baserat på ett tröghetsnavigeringssystem somblint räknar ut position genom att integrera tröghetsnavigerinssystemets sensorermed okända biaser. Syftet med detta exjobb är att integrera en GPS med tröghetsnavigeringsystemetför att öka robusthet och precision. Det kan i huvudsak delasupp i två problem; att integrera en GPS-mottagare med det befintliga navigationsystemetmed användning utav sensorfusion, och att få satellitföljningen attfungera under extremt höga dynamiska förhållanden. Det första av de två problemenlöses genom ett Extended Kalman filter (EKF) med två olika linjäriseringar.Den första linjäriseringen är med Eulervinklar och är välbeprövad. Den andra ärmed kvaternioner. Integrationstekniken som implementeras i detta Examensarbeteär en lös integration mellan GPS-mottagaren och tröghetsnavigeringssystemet. Huvudsyftetmed EKF:en är att estimera bias i tröghetsnavigeringsystemets sensoreroch korrigera dem för att eliminera drifter i position. Lösningen verifieras genomatt räkna ut positionen för en bil med GPS och en inertiell mätenhet. Olika lösningartill satellitföljningen föreslås i en förstudie.