An autonomous system consisting of an unmanned aerial vehicle (UAV) in cooperation with an unmanned ground vehicle (UGV) is of interest in applications for military reconnaissance, surveillance and target acquisition (RSTA). The basic idea of such a system is to take advantage of the vehicles strengths and counteract their weaknesses. The cooperation aspect suggests that the UAV is capable of autonomously landing on the UGV. A fundamental part of the landing is to localise the UAV with respect to the UGV. Traditional navigation systems utilise global navigation satellite system (GNSS) receivers for localisation. GNSS receivers have many advantages, but they are sensitive to interference and spoofing. Therefore, this thesis investigates the feasibility of autonomous landing in a GNSS-denied scenario. The proposed landing system is divided into a control and an estimation system. The control system uses a proportional navigation (PN) control law to approach the UGV. When sufficiently close, a proportional-integral-derivative (PID) controller is used to match the movements of the UGV and perform a controlled descent and landing. The estimation system comprises an extended Kalman filter that utilises measurements from a camera, an imu and ultra-wide band (UWB) impulse radios. The landing system is composed of various results from previous research. First, the sensors used by the landing system are evaluated experimentally to get an understanding of their characteristics. The results are then used to determine the optimal sensor placements, in the design of the EKF, as well as, to shape the simulation environment and make it realistic. The simulation environment is used to evaluate the proposed landing system. The combined system is able to land the UAV safely on the moving UGV, confirming a fully-functional landing system. Additionally, the estimation system is evaluated experimentally, with results comparable to those obtained in simulation. The overall results are promising for the possibility of using the landing system with the presented hardware platform to perform a successful landing.

In this thesis two methods were developed for precise maritime landing of an autonomous multirotor aircraft based on real-time kinematic (RTK) Global Navigation Satellite System (GNSS). The first method called RTK-localized method (RLM) uses RTK GNSS measurements to localize a sea vessel and execute the landing. RLM was demonstrated outdoors in hardware and landed on a physically simulated boat called a mock-boat with an average landing error of 9.7 cm. The mock-boat was actuated to have boat-like motion and a forward velocity of ~2 m/s. This method showed that accurate landing is possible with RTK GNSS as the primary means of localizing a sea vessel. The localization was unaided by non-GNSS sensors or an estimator, but lacked full attitude estimation and measurement smoothing. The second method was called RTK-Estimation Method (REM) and provides a more complete and robust solution, particularly at sea. It includes a base (landing pad) estimator to fuse RTK GNSS measurements with a dynamic model of a sea vessel. In contrast to RLM, the estimator provides full attitude estimation and measurement smoothing. The base estimator consists of an EKF in conjunction with a complimentary filter and estimates the relative position, attitude, and velocity of a moving target using RTK GNSS and inertial measurements alone. REM was demonstrated outdoors in hardware for 18 flight tests. The same mock-boat from RLM was used as a substitute for a sea vessel, and the boat motion varied between tests. These dynamics were recorded and performances were compared. The rate of success was high given moderate mock-boat motion and degraded with more aggressive motion. Tests were conducted with forward velocities from 0 to 3 m/s and moderate to high wave like motion. Over all tests for REM, the multirotor landed with an average accuracy of 12.7 cm. The methods described depart from common methods given that the only sensors involved for tracking the sea vessel were RTK GNSS receivers and inertial measurement units. Most current methods rely on computer vision, and can fail in poor lighting conditions, in the presence of ocean spray, and other scenarios. The given solutions do not fail under such conditions. The multirotor was equipped with a standard off-the-shelf autopilot, PX4, and the methods function with common control and estimation schemes. The two methods are capable of landing on relatively small landing pads, on the order of 1 m by 1 m, at sea using measurements from satellites thousands of kilometers away.

Ce travail étudie certains des problèmes les plus pertinents dans le sens de la navigation et contrôle présentés dans une classe particulière de mini-véhicules aériens. L'un des principaux objectifs c'est à réaliser un véhicule léger et facile à déployer dans un court laps de temps, un véhicule sans pilote drone capable de suivre une mission complète, du décollage aux points de cheminement suivants et de terminer la mission avec un atterrissage autonome à l'intérieur d'une zone délimitée en utilisant une interface graphique dans un ordinateur ou une tablette. La génération de trajectoire II est la partie qui dit le drone où il doit voyager et sont générés par un algorithme intégré sur le drone. Le résultat classique de Dubins est utilisé comme base pour la génération de trajectoire en 2D et nous avons étendu à la génération de trajectoire 3D. Une stratégie de suivi de trajectoire développée en utilisant l'approche de Lyapunov, est présentée pour piloter un drone à voilure fixe à travers tout le chemin désiré. Le concept clé derrière le contrôleur de suivi de trajectoire s'appuie sur la réduction de la distance entre le centre de masse de l'avion p et le point sur la trajectoire q à zéro, ainsi que l'angle entre le vecteur vitesse et la tangente à la trajectoire. Afin de tester les techniques mises au point au cours de la thèse une application C# -Net personnalisée a été développé nommé MAV3DSim (Multi-Aerial Vehicle 3D Simulator). Le MAV3DSim permet une opération de lecture/écriture de/vers le moteur de simulation à partir de laquelle nous pourrions recevoir toutes les informations de capteurs émulés et envoyés par le simulateur. Le système complet est capable d'effectuer un décollage et d'atterrissage autonome, à travers des points de suivi. Ceci est accompli en utilisant chacune des stratégies développées au cours de la thèse. Nous avons une stratégie pour le décollage et l'atterrissage, ce qui est généré par la partie de navigation qui est le générateur de trajectoire. Une fois que nous avons généré le chemin, il est utilisé par la stratégie de suivi de trajectoire et avec ce que nous avons l'atterrissage et le décollage autonome. / This work studies some of the most relevant problems in the direction of navigation and control presented in a particular class of mini‐aircraft. One of the main objectives is to build a lightweight and easy to deploy vehicle in a short period of time, an unmanned aerial vehicle capable of following a complete mission from take‐o⁄ to the following waypoints and complete the mission with an autonomous landing within a delimitated area using a graphical interface in a computer. The Trajectory Generation It is the part that tells the drone where it must travel and are generated by an algorithm built into the drone. The classic result of Dubins is used as a basis for the trajectory generation in 2D and we have extended it to the 3D trajectory generation. A path following strategy developed using the Lyapunov approach is presented to pilot a fixed wing drone across the desired path. The key concept behind the tracking controller is the reduction of the distance between the center of mass of the aircraft p and the point q on the path to zero, as well as the angle between the velocity vector and the vector tangent to the path. In order to test the techniques developed during the thesis a customized C # .Net application was developed called MAV3DSim (Multi‐Aerial Vehicle 3D Simulator). The MAV3DSim allows a read / write operation from / to the simulation engine from which we could receive all emulated sensor information and sent to the simulator. The MAV3DSim consists of three main elements, the simulation engine, the computation of the control law and the visualization interface. The simulation engine is in charge of the numeric integration of the dynamic equations of the vehicle, we can choose between a quadrotor and a xed wing drone for use in simulation. The visualization interface resembles a ground station type of application, where all variables of the vehicle s state vector can be represented on the same screen. The experimental platform functions as a test bed for the control law prototyping. The platform consists of a xed wing aircraft with a PX4 which has the autopilot function as well as a Raspberry PI mini‐computer which to the implementation of the generation and trajectory tracking. The complete system is capable of performing an autonomous take‐o⁄and landing, through waypoints. This is accomplished by using each of the strategies developed during the thesis. We have a strategy for take‐o⁄ and landing, which is generated by the navigationon part that is the trajectory generator. Once we have generated the path, it is used by the trajectory tracking strategy and withthat we have landing and take‐o⁄ autonomously.

Precision landing capability is a necessary development that must take place before unmanned aircraft systems (UAS) can realize their full potential in today's modern society. Current multirotor UAS are heavily reliant on GPS data to provide positioning information for landing. While generally accurate to within several meters, much higher levels of accuracy are needed to ensure safe and trouble-free operations in several UAS applications that are currently being pursued. Examples of these applications include package delivery, automatic docking and recharging, and landing on moving vehicles. The specific problem we consider is that of precision landing of a multirotor unmanned aircraft on a small barge at sea---which presents several significant challenges. Not only must we land on a moving vehicle, but the vessel also experiences random rotational and translational motion as a result of waves and wind. Because maritime operations often span long periods of time, it is also desirable that precision landing can occur at any time---day or night.In this work we present a complete approach for precision shipboard landing and address each of the aforementioned challenges. Our method is enabled by leveraging an on-board camera and a specialized landing target which can be detected in light or dark conditions. Features belonging to the target are extracted from camera imagery and are used to compute image-based visual servoing velocity commands that lead to precise alignment between the multirotor and landing target. To enable the multirotor to match the horizontal velocities of the barge, an extended Kalman filter is used to generate feed-forward velocity reference commands. The complete landing procedure is guided by a state machine architecture that incorporates corrections to account for wind, and is also capable of quickly reacquiring the landing target in a loss event. Our approach is thoroughly validated through full-scale outdoor flight tests and is shown to be reliable, timely, and accurate to within 4 to 10 centimeters.

<p>Den senaste trenden inom flygvapenindustrin är utveckling av obemannade farkoster. Den svenska vapenindustrikoncernen Saab AB följer denna trend i och med den stundande introduktionen av företagets obemannade helikopter Skeldar V-150. Som ett led i vidareutvecklingen av detta system finns planer på att även lansera en marin variant, kallad Skeldar M. Tanken med denna marina variant är att möjliggöra fullständigt autonoma starter och landningar från fartyg. För att kunna genomföra detta på ett tryggt sätt även i hårt väder krävs att helikoptern hålls säkrad på fartygsdäcket såväl innan start som efter landning.</p><p>Uppgiften för detta arbete har varit att ta fram koncept för hur ett sådant säkringssystem skulle kunna se ut. För att ta fram idéer för dessa koncept har en flitigt brukad produktutvecklingsmetod använts. Metoden innebär att en kravspecifikation tas fram utifrån kundens behov. Med stöd av den genereras sedan ett antal produktkoncept genom kreativt tänkande och analyser av hur andra löser samma problem. Koncepten jämförs sedan utefter hur väl de uppfyller kundens behov och de bästa idéerna kan på så sätt väljas ut och vidareutvecklas.</p><p>De koncept som tagits fram i detta arbete har sträckt sig från enklare idéer där kardborrmaterial används för att säkra helikoptern, till system som mäter in helikopterns position relativt fartyget och justerar sitt eget läge därefter. Totalt framkom nio grundidéer och sammanlagt tolv varianter på antiglidsystem. I samråd med personer inblandade i Skeldar-projektet valdes sedermera tre av koncepten ut för att vidareutvecklas ytterligare, en lösning där helikoptern vinschas ner på däck, en annan där kardborrlås används för att säkra den och en tredje där sugkoppar håller Skeldar fast.</p><p>Med hänsyn tagen till bland annat svårigheter att implementera en vinschlösning ombord på såväl Skeldar som fartygen valdes denna lösning slutligen bort. Svårigheterna bottnar framför allt i utrymmesbrist och problem med automatisk sammankoppling av helikopter och fartyg. De koncept som rekommenderas i detta arbete blir därför ett av systemen med kardborrlås eller sugkoppar.</p> / <p>The latest trend within the air force industry is development of unmanned aerial vehicles. The Swedish defense industry group Saab AB is following this trend by means of the introduction of their unmanned helicopter Skeldar V-150. As part of the further development of this system Saab has plans on introducing a marine version of the system, called Skeldar M. One of the purposes of this version is to enable completely autonomous take-offs and landings from ships. To be able to complete this in a safe manner in harsh conditions the helicopter needs to be secured to the deck before take-off as well as after landing.</p><p>The purpose of this thesis has been to develop a concept for keeping Skeldar secured on deck. To establish ideas for these concepts a common method for product development has been used. The method involves acquiring customer needs and from these needs establish a list of demands on the product itself. A set of product concepts are then generated by means of creative thinking and competitor analysis. After that the concepts are compared based on how well they meet the demands put upon them and the best ideas get picked out and further developed.</p><p>The concepts developed in this thesis stretch from simple ideas where hook and loop fasteners are used to secure the helicopter to more advanced ones where the helicopter’s position relative to the ship is measured and the system adjust to this position. All in all nine basic ideas were developed and a total of twelve versions on securing systems. In consultation with people involved in the Skeldar project, three of the concepts were chosen for further development, one concept where the helicopter was winched to the deck, a second where hook and loop fasteners were used to secure it and finally one where vacuum grippers keeps Skeldar on deck.</p><p>With difficulties of implementing a winch system onboard Skeldar as well as on board the ships taken into account, this solution was dropped. This was primarly due to lack of space and difficulties solving an automatic connection between helicopter and ship. The concepts recommended in this thesis will therefore be one of the systems where hook and loop fasteners or vacuum grippers are used.</p>

Den senaste trenden inom flygvapenindustrin är utveckling av obemannade farkoster. Den svenska vapenindustrikoncernen Saab AB följer denna trend i och med den stundande introduktionen av företagets obemannade helikopter Skeldar V-150. Som ett led i vidareutvecklingen av detta system finns planer på att även lansera en marin variant, kallad Skeldar M. Tanken med denna marina variant är att möjliggöra fullständigt autonoma starter och landningar från fartyg. För att kunna genomföra detta på ett tryggt sätt även i hårt väder krävs att helikoptern hålls säkrad på fartygsdäcket såväl innan start som efter landning. Uppgiften för detta arbete har varit att ta fram koncept för hur ett sådant säkringssystem skulle kunna se ut. För att ta fram idéer för dessa koncept har en flitigt brukad produktutvecklingsmetod använts. Metoden innebär att en kravspecifikation tas fram utifrån kundens behov. Med stöd av den genereras sedan ett antal produktkoncept genom kreativt tänkande och analyser av hur andra löser samma problem. Koncepten jämförs sedan utefter hur väl de uppfyller kundens behov och de bästa idéerna kan på så sätt väljas ut och vidareutvecklas. De koncept som tagits fram i detta arbete har sträckt sig från enklare idéer där kardborrmaterial används för att säkra helikoptern, till system som mäter in helikopterns position relativt fartyget och justerar sitt eget läge därefter. Totalt framkom nio grundidéer och sammanlagt tolv varianter på antiglidsystem. I samråd med personer inblandade i Skeldar-projektet valdes sedermera tre av koncepten ut för att vidareutvecklas ytterligare, en lösning där helikoptern vinschas ner på däck, en annan där kardborrlås används för att säkra den och en tredje där sugkoppar håller Skeldar fast. Med hänsyn tagen till bland annat svårigheter att implementera en vinschlösning ombord på såväl Skeldar som fartygen valdes denna lösning slutligen bort. Svårigheterna bottnar framför allt i utrymmesbrist och problem med automatisk sammankoppling av helikopter och fartyg. De koncept som rekommenderas i detta arbete blir därför ett av systemen med kardborrlås eller sugkoppar. / The latest trend within the air force industry is development of unmanned aerial vehicles. The Swedish defense industry group Saab AB is following this trend by means of the introduction of their unmanned helicopter Skeldar V-150. As part of the further development of this system Saab has plans on introducing a marine version of the system, called Skeldar M. One of the purposes of this version is to enable completely autonomous take-offs and landings from ships. To be able to complete this in a safe manner in harsh conditions the helicopter needs to be secured to the deck before take-off as well as after landing. The purpose of this thesis has been to develop a concept for keeping Skeldar secured on deck. To establish ideas for these concepts a common method for product development has been used. The method involves acquiring customer needs and from these needs establish a list of demands on the product itself. A set of product concepts are then generated by means of creative thinking and competitor analysis. After that the concepts are compared based on how well they meet the demands put upon them and the best ideas get picked out and further developed. The concepts developed in this thesis stretch from simple ideas where hook and loop fasteners are used to secure the helicopter to more advanced ones where the helicopter’s position relative to the ship is measured and the system adjust to this position. All in all nine basic ideas were developed and a total of twelve versions on securing systems. In consultation with people involved in the Skeldar project, three of the concepts were chosen for further development, one concept where the helicopter was winched to the deck, a second where hook and loop fasteners were used to secure it and finally one where vacuum grippers keeps Skeldar on deck. With difficulties of implementing a winch system onboard Skeldar as well as on board the ships taken into account, this solution was dropped. This was primarly due to lack of space and difficulties solving an automatic connection between helicopter and ship. The concepts recommended in this thesis will therefore be one of the systems where hook and loop fasteners or vacuum grippers are used.

Thesis (MScEng)--Stellenbosch University, 2013. / ENGLISH ABSTRACT: The landing phase of any helicopter is the most critical part of the whole flight envelope, particularly on a moving flight deck. The flight deck is usually located at the stern of the ship, translating to large heave motions. This thesis focuses on the three fundamental components required for a successful landing: accurate, relative state-estimation between the helicopter and the flight deck; a prediction horizon to forecast suitable landing opportunities; and excellent control to safely unite the helicopter with the flight deck. A monocular-vision sensor node was developed to provide accurate, relative position and attitude information of the flight deck. The flight deck is identified by a distinct, geometric pattern. The relative states are combined with the onboard, kinematic state-estimates of the helicopter to provide an inertial estimate of the flight deck states. Onboard motion prediction is executed to forecast a possible safe landing time which is conveyed to the landing controller. Camera pose-estimation tests and hardware-in-the-loop simulations proved the system developed in this thesis viable for flight tests. The practical flight tests confirmed the success of the monocular-vision sensor node. / AFRIKAANSE OPSOMMING: Die mees kritiese deel van die hele vlug-duurte van ’n helikopter is die landings-fase, veral op ’n bewegende vlugdek. Die vlugdek is gewoonlik geleë aan die agterstewe-kant van die skip wat groot afgee bewegings mee bring. Hierdie tesis ondersoek die drie fundamentele komponente van ’n suksesvolle landing: akkurate, relatiewe toestand-beraming tussen die helikopter en die vlugdek; ’n vooruitskatting horison om geskikte landings geleenthede te voorspel; en uitstekended beheer om die helikopter en vlugdek veilig te verenig. ’n Monokulêre-visie sensor-nodus was ontwikkel om akkurate, relatiewe-posisie en oriëntasie informasie van die vlugdek te verwerf. Die vlugdek is geidentifiseer deur ’n kenmerkende, geometriese patroon. Die relatiewe toestande word met die aan-boord kinematiese toestandafskatter van die helikopter gekombineer, om ’n beraming van die inertiale vlugdek-toestande te verskaf. Aan-boord beweging-vooruitskatting is uitgevoer om moontlike, veilige landingstyd te voorspel en word teruggevoer na die landingsbeheerder. Kamera-orientasie afskat-toetse en hardeware-in-die-lus simulasies het die ontwikkelde sisteem van hierdie tesis lewensvatbaar vir vlug-toetse bewys. Praktiese vlug-toetse het die sukses van die monokulêre-visie sensor-nodus bevestig.

In the last years, the use of indoor drones has increased significantly in many different areas. However, one of the main limitations of the potential of these drones is the battery life. This is due to the fact that the battery size has to be limited since the drones have a maximum payload in order to be able to take-off and maintain the flight. Therefore, a recharging process need to be performed frequently, involving human intervention and thus limiting the drones applications. In order to solve this problem, this master thesis presents an autonomous recharging system for a nano drone, the Crazyflie 2.0 by Bitcraze AB. By automating the battery recharging process no human intervention will be needed, and thus overall mission time of the drone can be considerably increased, broadening the possible applications. The main goal of this thesis is the design and implementation of a control system for the indoor nano drone, in order to control it towards a landing platform and accurately land on it. The design and implementation of an actual recharging system is carried out too, so that in the end a complete full autonomous system exists. Before this controller and system are designed and presented, a research study is first carried out to obtain a background and analyze existing solutions for the autonomous landing problem. A camera is integrated together with the Crazyflie 2.0 to detect the landing station and control the drone with respect to this station position. A visual system is designed and implemented for detecting the landing station. For this purpose, a marker from the ArUco library is used to identify the station and estimate the distance to the marker and the camera orientation with respect to it. Finally, some tests are carried out to evaluate the system. The flight time obtained is 4.6 minutes and the landing performance (the rate of correct landings) is 80%. / Under de senaste åren har användningen av inomhusdrönare ökat betydligt på många olika områden. En av de största begränsningarna för dessa drönare är batteritiden. Detta beror på att batteristorleken måste begränsas eftersom drönarna har en väldigt begränsad maximal nyttolast för att kunna flyga. Därför måste de laddas ofta, vilket involverar mänskligt ingripande och därmed begränsar drönartillämpningarna. För att lösa detta problem presenterar detta examensarbete ett autonomt laddningssystem för en nanodrönare, Crazyflie 2.0. Genom att automatisera batteriladdningsprocessen behövs inget mänskligt ingrepp, och därigenom kan uppdragstiden för drönaren ökas avsevärt och bredda de möjliga tillämpningarna. Huvudmålet med denna avhandling är designen och implementationen av ett styrsystem för en inomhusdrönare, för att styra den mot en landningsplattform och landa korrekt på den. Arbetet inkluderar det faktiska laddningssystemet också, så att slutresultatet är ett fullständigt autonomt system. Innan regulatorn och systemet utformas och presenteras presenteras en genomgång av bakgrundsmaterial och analys av befintliga lösningar för problemet med autonom landning. En kamera monteras på Crazyflie 2.0 för att kunna detektera och positionera landningsstationen och styra drönaren med avseende på detta. För detektion används ArUcobibliotekets markörer vilka också gör det möjligt att räkna ut kamerans position och orientering med avseende på markören och därmed laddstationen. Slutligen utförs tester för att utvärdera systemet. Den erhållna flygtiden är 4,6 minuter och landningsprestandan (andel korrekta landningar på första försöket) är 80%.

The research on autonomous vehicles, and more specifically cooperation between autonomous vehicles, has become a prominent research field during the last cou- ple of decades. One example is the combination of an unmanned aerial vehicle (UAV) together with an unmanned ground vehicle (UGV). The benefits of this are that the two vehicles complement each other, where the UAV provides an aerial view and can reach areas where a ground vehicle can not. Furthermore, since the UAV has a limited range, the UGV can then serve as transport and recharge sta- tion for the UAV. This master thesis studies how model predictive control (MPC) can be used to land a UAV on a moving UGV.  A linear MPC is chosen, since previous work using this has shown promising results. The UAV is chosen to be controlled using commands in pitch, roll and climbing rate. The MPC is designed as a decoupled controller, with a separate horizontal and vertical controller. This allows for a spatial constraint to be im- plemented, which constrains the UAV from entering ground level before arriving above the UGV. It also constrains the UAV from potentially hitting protruding ob- jects on the UGV. The horizontal controller uses a simple planner, which guides the UAV to land on the UGV from behind.  The MPC is evaluated using a additive white Gaussian noise (AWGN) sen- sor error model with zero mean. The scenario used is that the UAV starts 50 m from the UGV, and the UGV starts driving in a given direction turning randomly. The MPC lands successfully in 100 % of the simulations for a wide range of tun- ings. The MPC maintains the same landing statistics with a delay in the sensor information of up to 500 ms. The AWGN could be increased while maintaining successful landings, however with significantly more retakes and longer landing times. Lower AWGN variance only slightly improves performance, suggesting that the MPC is quite robust towards high variance in the state estimation.  The MPC is also compared to a PID controller. The MPC has significantly shorter landing times. The PID has a more oscillatory control signal, however, the PID has a lower variance in landing positions, but a slightly less centered mean on the UGV. The overall results show that an MPC can be used to achieve a flexible controller that can be tuned and reformulated to fit the situation, and performs as good or better compared to a PID controller.  The hardware tests show promising results for the implementation of the MPC. The controller is not tuned and no system identification is done specifi- cally for the physical UAV, suggesting that the controller is robust for varying settings. Even though the UAV never lands on the UGV, the visual behavior and control signal plots suggest that it would be able to land. However, these tests are performed using global navigation satellite system state estimation on a sta- tionary UGV, therefore further tests need to be performed in more challenging scenarios.

A system of an unmanned aerial vehicle (UAV) collaborating with an unmanned ground vehicle (UGV) for use in for example surveillance, reconnaissance, transport and target acquisition is studied. The project investigates the problem of estimating the relative position, velocity and orientation between the UAV and the UGV required to autonomously land the UAV on the UGV during movement. The use of global navigation satellite system (GNSS) receivers are not considered since they are sensitive to interference and spoofing attacks.  The developed estimation system consists of an extended Kalman filter (EKF) using measurements from several sensors, including: a camera, barometers, inertial measurement units (IMUs) and impulse-radio ultra-wide bandwidth (IRUWB) transceivers. Primarily the use of near infrared (NIR) light emitting diodes (LEDs) attached to the UGV and a camera on the UAV is investigated. Several configurations of LED placements, and what errors to expect when measuring them with the camera, are evaluated. The performance is evaluated in both simulations and hardware sensor tests, but no live experiments that include any autonomous landing manoeuvre are conducted.  The results indicate that high estimation precision can be achieved, at close range the errors in position average below 2 cm and in orientation under 0.5 degrees. However, some problems arise from the detection and identification of the LEDs. Further, if measurements of the LEDs are completely missing, the estimation precision suffers due to error accumulation in the inertial navigation. These results indicate that autonomous landing is possible, since the amount of LED measurements and consequently also the estimation precision increases as the relative position decreases.