Abstract: The ability to provide highly accurate and reliable relative navigation information in real time is a key enabling technology for autonomous operations between moving platforms in close proximity. Northrop Grummanpsilas Navigation Systems Sivision (NSD) has developed an innovative approach to relative navigation that fuses Global Positioning System (GPS) pseudorange and carrier phase measurements with Inertial Navigation System (INS) data and implements a innovative approach to resolving the GPS carrier phase integer ambiguity to satisfy accuracy, integrity, continuity, and availability requirements. This capability was recently demonstrated as part of the Air Force Research Laboratorypsilas Automated Aerial Refueling (AAR) program. During the final flight test phase, a Learjet-25 test aircraft autonomously performed station keeping and transitioning between various positions in close proximity to a KC-135R tanker, in a fashion typical of refueling maneuvers. The relative and absolute vehicle navigation data used by the autonomous flight control system were calculated using NSDpsilas relative navigation algorithm and sensor data from two LN-251 Embedded GPS/INS (EGI) systems with embedded 24-channel GPS receivers, one on each vehicle. This paper will present and discuss the flight test results and performance.

Abstract: An increasing number of applications require the provision of a relative navigation solution which exhibits both high accuracy and high integrity. Examples include air-to-air refuelling (AAR) of unmanned air vehicles (UAVs) and automated landing of aircraft on ships. In a previous paper, QinetiQ demonstrated that adding inertial navigation

Abstract: As stated in the roadmap for performance-based navigation, the Federal Aviation Administration (FAA) is committed to implementing area navigation (RNAV) and required navigation performance (RNP) procedures throughout the National Airspace System (NAS). RNAV and RNP procedures provide lateral guidance as well as vertical and speed restrictions at waypoints where necessary along arrival or departure procedures. As compared to conventional vectoring operations where the terminal controller issues heading, speed, and altitude clearances, RNAV procedures reduce the number of clearances issued by air traffic control (ATC). The MITRE Corporationpsilas Center for Advanced Aviation System Development (CAASD) in coordination with ATC subject matter experts from FAA operational facilities has conducted research to define automation needs for monitoring RNAV and RNP operations. The needs focus on ensuring controllers maintain situation awareness in environments with high RNAV and RNP participation and increasing traffic levels. One major function of the automation is to provide an alert to a radar controller when an aircraft is deviating from its assigned RNAV or RNP procedure. This paper presents the automation needs associated with monitoring RNAV and RNP operations, and the results from human-in-the-loop experiments that measured latency times in detecting deviation events in simulated RNAV and RNP environments with and without the alerting automation. Results indicate that latency times associated with detecting pilot deviations were reduced in conditions with the monitoring automation. Subjective workload measures were not different in any significant way.

Abstract: The application and development of CNS-INS integrated navigation system in high-altitude aircrafrt are overviewed.On the basis of the analysis of aviation aircraft load celetid navigation system(CNS)/inertial navigation system(INS)integrated navigation system at home and abroad,the technical performance of CNS/INS integrated navigation system from working environment,integrated patterns and navigation solution is analyzed and it is pointed out that CNS-INS integrated navigation system is more applicable to the aviation aircraft of implementation of the long voyage and high-flying,it can meet the needs of aviation aircraft to high-precision navigation system.The unique advantages of CNS/INS integrated navigation system is summarized.The necessity of development of CNS-INS integrated navigation system is proposed,and the future research development direction for CNS-INS navigation technology on aircraft is discussed.

Abstract: In applications employing multiple unmanned marine vehicles (MUMVs), the navigation has a very great importance to guarantee formation preservation and collision avoidance. While single vehicles usually base their navigation on absolute measurements (GPS, inertial navigation) to determine their position relative to the world, it may be reasonable to perform a relative navigation within vehicle teams. In this paper, we propose relative team navigation based on Kalman Filters to enable a velocity controller to establish a close formation under the typical marine constraints (narrow band width communication with low reliability). We will simulate a team of three marine vehicles and compare the results of different strategies for team navigation.

Abstract: PHOENIX is a downscaled experimental vehicle to demonstrate automatic landing capabilities of future Reusable Launch Vehicles (RLVs). PHOENIX has flown in May 2004 at NEAT (North European Aerospace Test range) in Vidsel, Sweden. As the shape of the vehicle has been designed for re-entry, the dynamics are very high and almost unstable. This requires a fast and precise GNC system. This paper describes the navigation system and the navigation filter of PHOENIX. The system is introduced and the high requirements are shown. The sensor configuration to fulfill the requirements is presented. Special focus is laid on the development and the structure of the navigation filter. The flight results of PHOENIX are shown and the performance of the navigation system is analyzed, which includes sensor failure scenarios.

Abstract: An aircraft navigation aid system comprises a flight management system (2), for example of the FMS type comprising flight management means (3) to provide the corresponding information, in particular for the navigation of the aircraft in flight. The device also comprises airport navigation aid means (4), integrated in said flight management system (2), and common interface means (5) comprising input means (7) and a display screen (8). Said device comprises navigation and guidance functions which are common to the flight management means (3) and the airport navigation aid means (4) and permit the generation of a complete course from a starting parking point to a destination parking point from one airport to another.

Abstract: GPS alone will be unable to meet emerging performance requirements for maritime applications with respect to service robustness, accuracy, integrity and availability. Even when Galileo (or indeed other nascent GNSS) eventually become operational there will be performance gaps. In particular, identified applications in port areas (for example automated docking) and in inland waterways, have very stringent performance requirements. EADS Astrium Ltd has developed a Test Environment for a Maritime Navigation System in order to perform demonstrations for the maritime community. This includes a number of Transmit Stations mounted on existing structures and terrain at accurately known locations overlooking a navigation zone (such as a maritime harbour). These continuously transmit replica GNSS signals. Another key component of the Navigation System is the single Monitoring and Control Station. This monitors each transmitter’s signal, calculates clock corrections and provides each Transmit Station with the contents of its navigation messages, emulating the function of the Galileo central control facility. It also controls and monitors any demonstration signal scenarios. This paper presents details of Astrium’s Pseudolite-based Navigation System that is the foundation of a Maritime Test Environment. As well as design details, the paper presents outcomes from a public demonstration undertaken in Oban, on the West Coast of Scotland in March 2008.

Abstract: Transportation systems able to support the future human exploration of the Moon are currently under investigation in Europe. These systems must ensure a safe return of the crew for a variety of contingency scenarios, including the loss of ground-based navigation. Optical measurements may be used to support on-board autonomous navigation for these cases. The paper describes the architecture and algorithms needed for candidate system concepts for optical autonomous navigation (including different sensors and types of processed measurements), and presents the expected performances of the proposed systems for a variety of contingency scenarios. I. Introduction dvanced space transportation systems will be needed to support the human exploration of the Moon in the coming decades. These systems are currently under investigation in Europe in the frame of the Crew Space Transportation System (CSTS) preparatory program. Several technology research projects are being conducted to develop the key technologies required for the CSTS. This paper summarizes the preliminary results of one of these projects, which is aimed at investigating optical autonomous navigation systems for manned lunar missions. Flight and crew safety considerations impose severe requirements on the design of manned missions. The system must be able to cope with potential off-nominal or emergency situations. For instance, a number of contingencies may lead to the loss of the ground trajectory navigation or of the ground-spacecraft communication link. In both cases, the required maneuvers cannot be uploaded to the spacecraft, risking mission success or even crew lives if the failure occurs at a critical phase or lasts long enough. Therefore, an autonomous GNC becomes mandatory to mitigate those risks to acceptable levels, and such a backup needs an autonomous navigation function. In a LEO mission, autonomous trajectory determination may be feasible with GNSS equipment, but the availability of GNSS signals cannot given for granted over a whole mission to the Moon. Hence, a different autonomous navigation means is needed for the cis- and circumlunar space. One of the potential techniques for providing the required autonomous navigation solution is optical navigation, which is based on the sighting of point targets (stars or far bodies) and/or extended targets (close bodies). Optical navigation has the advantage that it does not require the use of any external, pre-existing navigation infrastructure (such as beacons or other spacecraft). Additionally, the concept has been already demonstrated in-flight during the Apollo program. Candidate systems for optical autonomous navigation for manned lunar missions are described in terms of the type of processed measurements and the sensors required. The performances of one of these system concepts are presented.

Abstract: This paper discusses research being conducted in the United States to identify potential reduction in air traffic route and aircraft separation standards, using improved navigation and surveillance capabilities. Reduced separation would assist in addressing airspace and airport capacity issues caused by traffic growth and by adverse weather conditions.

Abstract: Forecasted traffic increases are driving demand for more efficient, predictable, and flexible ways of managing traffic in terminal environments. A key component to achieving those benefits is the increased availability of Area Navigation (RNAV) and Required Navigation Performance (RNP) procedures. RNAV and RNP procedures, where implemented today, provide benefits of efficiency and operational predictability. Achieving flexibility, while maintaining those benefits, is proposed by issuing RNAV procedure changes to the flight deck in lieu of radar vectoring. Understanding the human factors implications involved with this operational shift will be important to ensure workload is not substantially increased for either the pilot or the controller. This document describes an initial study of pilot task load and resulting workload and latency incurred when routing changes are issued in the flight critical phase of departure via a human-in-the-loop (HITL) simulation. Scenarios, conducted using pilots in a flight deck simulator, assessed the impact of modality (voice or text-issued) and of the aircraft’s altitude on processing two types of RNAV routing changes. Pilot workload, task success, task completion time, and errors incurred in performing the routing change task are presented. Results suggest the routing change task performed in the terminal environment may be more complex than expected. Although generally acceptable pilot workload levels were reported, the magnitude of latency for processing the routing change task was considerable. Additionally, FMS user interface issues emerged with the processing of routing changes in-flight. Pilot workload and latency issues related to the routing change task warrant further evaluation to ensure they are fully understood.

Abstract: For satisfing the high accuracy and reliability of carrier navigation performance requirements, a design project for fault-tolerant integrated navigation system according to inertial navigation system was proposed, which integrating classical fault detection and federated kalman filtering and adopting dasiafault diagnosis periodpsila approach to deal with system fault and outlier differently. With the carrier usage request and each navigation system usage scope and characteristics, the feasibility of the proposed project was analyzed by an actual INS/GPS/Doppler integrated navigation system example. The result shows that the project could effectively realize fault detection, isolation and reconfiguration, and the whole navigation computing process keeps good algorithm continuity, stability and system accuracy.

Abstract: This invention relates to domain of space activity and can be used for the Earth satellite aided radio navigation, particularly, for control (monitoring) the system integrity without attendance of means of the ground control complex and globally allocated reference stations. A technical result of the claimed technical solution is the responsiveness enhancement of a user's notification about navigation signal uncertainty; cutting-down of expenditures for solving the task of system's integrity control considering the lack of globally allocated ground-based control and monitoring complexes; elimination of additional radio links; increase of reliability of the system's integrity control, growth of reliability. The device for realizing the method of navigation satellite system's integrity control comprises a transmitter-receiver unit, a computer, a navigation signal generator, a navigation signal source, a range measuring instrument, an unit for computing the range to other reference satellites of the navigation satellite system, an unit for comparison of estimated range with the measured one, control unit and decision-making unit.

Abstract: Flight recoder is used to analyze the accident factors and prevent the accident. In the analysis of the flight recorder, the most important factor is how to estimate the precise location of the flight. Traditional aviation navigation is based on stable sensors such as DME and VOR. In order to enhance the precision of the location estimation, the integrated navigation algorithm is designed to incorporate DME, Air data sensors and INS(Inertial Navigation System). The results demonstrate that the proposed algorithm can achieve better accuracy, comparing with the traditional navigation schemes, in flight location estimation.ࠀȀ耀

Abstract: The European Geostationary Navigation Overlay Service (EGNOS) is Europe's first venture into satellite navigation. EGNOS augments the existing GPS satellite navigation service by providing additional information to enable it to be used to support safety critical applications. Before it can be used there are a number of steps to be performed in order to demonstrate that the system has been designed, deployed and is operated in a manner commensurate with its intended use in such safety critical applications. This demonstration has been developed in the form of a System Safety Case showing that the system is compliant to key safety requirements, resulting in a 'safe' navigation signal. This paper describes the challenges that must be faced to 'certify' satellite navigation systems providing safety-of-life services throughout large geographical areas encompassing many countries. In particular this paper focuses on the use of EGNOS to support aviation applications; it describes the current aviation regulatory mechanisms and looks into the future at how these mechanisms may evolve to support the certification of such complex systems such as Galileo, Europe's contribution to the second phase of Global Navigation Satellite Services (GNSS). (6 pages)

Abstract: In order to study the performance of satellite navigation system, such as satellite constellation coverage performance, signal links, time system and so on, it is necessary to build the mathematics simulation system for satellite navigation systems. The simulation system of the passive regional satellite navigation system (PRSNS) based on High Level Architecture (HLA) is introduced in this paper. An independent atomic clock federate is designed for solving the problem of consistency between the run-time infrastructure (RTI) simulation time system and the satellite navigation time system. Data Distribution Management services of RTI are used to improve the network communication speed. The three-level design pattern (TLDP) is proposed for the software design and development of the simulation system. The simulation system meets the requirements of the simulation and evaluation for the PRSNS. The research results are of great value to the realization of Chinese next generation of satellite navigation system.

Abstract: Method of operating a navigation system for a vehicle, comprising the steps of: - providing an initial route (300; 510) to a predetermined destination (D) comprising links associated with initial costs, - for at least one link of said initial route (300; 510), decreasing the cost associated with said link, and - providing the at least one link associated with a decreased cost for a further route calculation by the navigation system (100).

Abstract: A new intra-vehicular free-flyer location and navigation methodology is introduced which adopted the state of art radio location and navigation technology called Pseudolite (PL). Theoretical analysis demonstrates the efficiency of this method. It will greatly improve intra-vehicular free-flyer navigation accuracy to satisfy future needs in deep space exploration and space structure maintenance. PL system measurement model and navigation algorithm are given along with recommendations for future research.

Abstract: International Civil Aviation Organization(ICAO) adopted VOR(Very high frequency Omni-Range) as an international standard air navigation system in 1949 and recommended every country to make use of it in formulating air route and guiding take-off and landing of an aircraft. VOR is quite a useful navigation system so that more than 2,000 VORs have been installed all over the world including 39 in Korea: however, VOR signal could be easily affected by its circumstance like a mountainous area because it provides navigation information through AM and FM of VHF carrier. Therefore this study intends to investigate how much VOR performance is affected by its circumstances. For this purpose, the performance of the 10 VORs influenced by 24 obstacles are measured and analyzed by using an aircraft equipped with measuring instruments. This study may give us a feasible solution of problems related to the VOR siting in the future.