Abstract: A method for guiding the approach and landing of an aircraft is provided. The method involves receiving navigation information from the aircraft, receiving navigation information from an aircraft carrier, integrating the navigation information from the aircraft with the navigation information from the aircraft carrier to determine a relative velocity and a relative position between the aircraft and the aircraft carrier, and propagating the relative velocity and the relative position forward in time for navigation purposes.

Abstract: Recently an unmanned aerial vehicle (UAV) has been widely used for military and civil applications. The role of a navigation system in the UAV is to provide navigation data to the flight control computer (FCC) for guidance and control. Since performance of the FCC is highly reliant on the navigation data, a fault in the navigation system may lead to a disastrous failure of the whole UAV. Therefore, the navigation system should possess a fault detection and isolation (FDI) algorithm. This paper proposes an attitude determination GPS/INS integrated navigation system with an FDI algorithm for a UAV. Hardware for the proposed navigation system has been developed. The developed hardware comprises a commercial inertial measurement unit (IMU) and the integrated navigation package (INP) which includes an attitude determination GPS (ADGPS) receiver and a navigation computer unit (NCU). The navigation algorithm was implemented in a real-time operating system with a multi-tasking structure. To evaluate performance of the proposed navigation system, a flight test has been performed using a small aircraft. The test results show that the proposed navigation system can give accurate navigation results even in a high dynamic environment.

Abstract: Methods and apparatus are provided for airspace navigation. Airspace navigation information for an aircraft is displayed in a first mode, such as, in a horizontal mode. One or more navigation events may then be detected, such as, proximity to a terrain feature, weather, traffic etc. The airspace navigation information for the aircraft is then displayed using dual modes, e.g., a horizontal mode and a vertical mode. Display parameters, such as colors, resolution, distance, scale, etc. may be set automatically or by a user. The display may also include information, such as avionics systems information, and communications information.

Abstract: Future Global Navigation Satellite Systems (GNSS) will significantly improve the performance of current navigation systems, providing new and enhanced capabilities. This will enable the implementation of innovative and advanced services and applications closer to the user's needs. In this framework, the road sector is one of the major potential markets for GNSS applications and, therefore, it is very promising for future EGNOS and GALILEO related applications. Satellite navigation receivers are now commonly installed in cars as a key tool for proving new services to people on the move such as electronic charging, real-time traffic information, emergency calls, route guidance, fleet management, or advance driving assistance systems. Specifically, a very important commercial opportunity is represented by the tolling-related applications. This paper describes the Vehicular Remote Tolling (VeRT) Project sponsored by Galileo Joint Undertaking (GJU) and performed in the frame of the first GJU Call under the EC VI Framework Programme. The overall design of the service provision architecture is also presented in this paper, together with the main topics related to the following activities focused on the service prototype demonstrator development.

Abstract: This paper presents a proposal for transitioning from terrestrial based navigation aids to implementing satellite and airborne surveillance as the primary navigation means. The transition occurs through several steps. First the installation and use of modern navigation and surveillance equipment is mandated by the regulatory organizations. The installations should take place in a sequenced fashion to allow time for companies to absorb the initial cost. Next the existing network of terrestrial navigation aids is down sized leaving only the areas of heaviest use in service. At this point, the Global Positioning System (GPS) is deemed the primary method of terrestrial and oceanic travel. Finally, terrestrial navigation stations are available around airports and the remaining stations are put in a standby condition for use the in the event of a national emergency. This paper also discusses the security benefits and examples of cost savings through implementation of these steps.

Abstract: The Federal Aviation Administration (FAA) and general aviation (GA) industry are working collaboratively to publish lower minimum en route altitudes (MEAs) for Global Positioning System (GPS)-equipped aircraft operating at low altitudes, and more direct transition routes through Class B airspace based on area navigation (RNAV) (commonly achieved in GA aircraft with GPS). These efforts are intended to improve access to airspace, safety of flight, and seamless RNAV operations in the NAS - in accordance with the FAA's roadmap to performance-based navigation published in July 2003. The roadmap initiatives were developed jointly by FAA and industry under the sponsorship of the Performance-Based Operations Aviation Rulemaking Committee (PARC). The GA representation on that committee was provided by Aircraft Owner's and Pilot's Association (AOPA), who was spearheading the movement toward achieving benefits with GPS and spurring a growth rate in aircraft equipage. This paper presents the concepts of use for lower MEAs based on GPS and RNAV transition routes through Class B airspace. The paper also provides a description of the benefits and an outline of the implementation strategy.

Abstract: An unmanned aerial vehicle (UAV) is an aircraft controlled by .emote commands from ground station and/o. pre-programmed onboard autopilot system. A navigation system in the UAV provides a navigation data for a flight control computer(FCC). The FCC requires accurate and reliable position, velocity and attitude information for guidance and control. This paper proposes an ADGPS/INS integrated navigation system for a UAV. The proposed navigation system comprises an attitude determination GPS (ADGPS) receive., a navigation computer unit, and a low-cost commercial MEMS inertial measurement unit(IMU). The navigation algorithm contains a fault detection and isolation (FDI) function fur integrity. In order to evaluate the performance of the proposed navigation system, two flight tests were preformed using a small aircraft. The first flight test was carried out to confirm fundamental operation of the proposed navigation system and to check the effectiveness of the FDI algorithm. In the second flight test, the navigation performance and the benefit of the GPS attitude information were checked in a high dynamic environment. The flight test results show that the proposed ADGPS/INS integrated navigation system gives a reliable performance even when anomalous GPS data is provided and better navigation performance than a conventional GPS/INS integration unit.

Abstract: Integrity of a GNSS (Global Navigation Satellite System) is one of the most important performance parameter for safety applications like air navigation. For Oceanic, En route or Non Precision Approach (NPA) phases, the integrity requirements as defined by the ICAO (International Civil Aviation Organisation) should be fulfilled by the future Galileo Safety of Life Service. One of the techniques that provide integrity check at receiver level is the so called Receiver Autonomous Integrity Monitoring (RAIM), which uses an over-determined navigation solution in order to make a consistency check. For that technique, numerous RAIM algorithms are available which have each advantages and drawbacks depending on the specific use. The aim of this work is to investigate the RAIM performances that can be expected using a combined Galileo/GPS navigation system for a defined scenario, and to compare these results with requirements.

Abstract: The National Airspace System (NAS) is a large and complex system encompassing a wide-range of resources to enable safe and efficient air transportation. To effectively manage the NAS, it is very important to be able to reliably assess current and future demand for communications, navigation, and surveillance (CNS) resources as they are triggered by air traffic control (ATC) events. The authors present an integrated model that is capable of relating NAS ATC events to NAS CNS demand. Model validation with a subset of recorded ETMS CNS statistics will be presented. Combining such a model with NAS future demand predictors such as Terminal Area Forecasts (TAF) and Future Aviation Timetable Estimator (FATE), it becomes possible to estimate the increase in CNS demand and future requirements for CNS capacity, for resource planning purposes. The model presented in this paper includes tracking of radar-related messages and sector workload.

Abstract: *This paper discusses the design of a navigation system for aircraft approach and landing. This navigation system consists of a strapdown inertial navigation system, a radio altimeter, and a vision system using landmarks image processing. Performance requirements of the navigation system for the realization of approach and landing are introduced. The information obtained from the vision system is used for estimating aircraft position and attitude with the inertial navigation system and radio altimeter in the Kalman filter. In this paper the research about the vision system, such as matching algorithms and their minimum size determinations, is used to satisfy the given navigation requirements. And the efficiency of the vision system is verified with processing of sample images. Lastly, an application procedure of the designed navigation system to landing is introduced, and simulation results indicate that it is possible to use it for aircraft approach and landing with the satisfaction of the application procedure.