Abstract: A mobile station, and related methods, provide navigational assistance. The mobile station executes a local navigation application and can transition between network assisted navigation and stand-alone navigation that utilizes the local navigation application. Various events can cause the transition between the operational states.

Abstract: This paper presents a vision-based navigation algorithm for an autonomous helicopter landing in complex environment include appointed landing mark coupled with several similar targets. The vision navigation system is integrated with algorithms of vision detection, target recognition and navigation instruction calculation. The navigation is used for indicating the helicopter to land on the landing mark exactly. In our algorithm, we use international standard landing mark as helicopter landing signal. The experiments results demonstrate that the algorithm has feature of robustness, accuracy and real- time. It meets the actual flight requirements well.

Abstract: Real time traffic information is one of the most important features of Dynamic Vehicle Navigation Systems (DVNS). Research on improving the performance and accuracy of navigation systems has been focused on algorithm design and data modeling in navigation clients. However, traffic data organization, an important factor limiting system performance, has received little attention. This paper presents an analysis of traffic data structure and route process of DVNS and outlines the requirements for traffic database architectures. Based on the requirement analysis, a prototype of traffic management system is implemented and tested.

Abstract: Numerous studies emphasize the significant influence of air traffic complexity on controller's workload and consequently on the overall safety level. This paper describes a detailed investigation into these air traffic complexity metrics. The evaluated data originate from traffic samples of a recently conducted real-time simulation in air traffic control at EUROCONTROL CRDS Budapest. In these traffic samples both flight characteristics of individual aircraft and the interactions between pairs of aircraft were taken into consideration. With an attempt to quantify potential changes of the safety level, relevant indicators as the position, collision- respectively conflict probabilities were used. A traffic simulation environment was developed in order to determine these quantitative criteria more accurately. Additional emphasis was put onto the consideration of actual navigation performance of each aircraft to allow correlating air safety with performance based navigation (PBN) concepts. This paper deals exclusively with the endangering of the involved air traffic expressed through the factors defined in order to capture complexity of the traffic and as a specific level of risk or safety for an aircraft conflict or accident per period of time (4). Numerous studies investigate into safety through controller's workload, as prime factor driving safety, determined by both directly measurable air traffic factors (number of aircraft in the sector, speed, distance between aircraft, etc.) and controller's activity mediated by the controller's abilities, age, fatigue, level of experience, etc. (5). As the investigation into the correlation between subjective controller workload and safety level was previously conducted and strong connection was found (6) this paper focuses only on air traffic complexity as the objectively measurable prime driver of subjective controller workload and collision probabilities as an attempt to quantify the changes in air traffic safety level. Therefore, a detailed investigation into these air traffic complexity metrics and collision probability is described, followed by an analysis of their relationship. Moreover, the objective of the current study is to investigate into their interdependencies and examine whether they contribute to the overall safety as

Abstract: As fleet avionics continue to evolve, the use of the solutions provided by performance-based navigation (PBN) will continue to grow and provide benefits to the aircraft operators. Due to these potential benefits, several air carriers in the United States have announced plans to retro-fit their fleets with PBN capabilities. However, it is important to understand the current snapshot of avionics, as well as the historic growth before analyzing the future forward-fit scenarios. Since 2004, the MITRE Corporation's Center for Advanced Aviation System Development (CAASD) has monitored the navigational avionics for Part 121 United States airlines. In this time span, the number of Part 121 airframes has dropped by more than 400 aircraft while the number of Part 121 aircraft with a flight management computer (FMC) has grown at approximately the same rate. This has resulted in a fleet wide growth in the percent of aircraft operating with an FMC from 79% to 90%. Also, the number of aircraft operating with a Global Positioning System (GPS) (also known as Global Navigation Satellite System (GNSS) navigational sensor) has grown with 1,100 additional aircraft operating with a GNSS sensor today. This has resulted in a growth from 47% of the aircraft in 2004 to 66% of the aircraft. There have been three primary reasons for the growth of PBN operational capability: equipped aircraft delivered to the system, current fleet retro-fits, and new knowledge of the airline operators. This paper will discuss the current equipage trends, capability, and identify the evolutionary change in Part 121 PBN avionics from 2004 through 2008. Additionally, this paper will discuss the next generation of aircraft and potential future scenarios for fleet avionics.

Abstract: Applying low-cost sensors for the navigation of aircraft is an extremely challenging area. This paper presents an approach using dead reckoning by which aircrafts present position may be calculated from the knowledge of initial position and measurements of speed and acceleration. The main aim over here is to provide navigation information to the pilot on a cockpit display unit by using a standalone attitude and heading reference system and position estimation algorithm. This is helpful in navigation when GPS is non-operational or GPS drops out. The navigation loop provides continuous and reliable navigation solutions to the guidance and flight control loop for the flight. The whole navigation algorithm shall be implemented within an embedded display system that receives attitude information. This approach is also applicable for unmanned aerial vehicle and self-guided-rockets, where additional air-data and engine thrust data can be used for additional guidance and flight control.

Abstract: For the shortcomings existing in the current ship integrated navigation positioning methods of single ship such as depending on GPS overly,bade reliability and fault tolerance,and lacking of the concept of network system,a novel ship relative integrated navigation positioning method based on marine intelligent transport system,which is MITS,is proposed by introducing the wireless network system into ship integrated navigation in this paper.This proposed method doesn’t take the ship in MITS as lone node,so the target ship can use the navigation estimates from other ship nodes in MITS and adopt the optimal distributed weighted fusion in minimizing the trace of estimate error covariance matrix to improve the performance of its integrated navigation positioning estimate.Compared with the integrated navigation algorithm for single ship,the proposed relative navigation method has better navigation accuracy,stability and fault tolerance.

Abstract: The orientation error of Inertial Navigation System will be cumulated and sometimes even spread in the course of time because of the error from gyroscope and accelerometer. One effective way for resolving this problem is using the Integrated Navigation System. With the improvement of the performance of other navigation systems,the integrated navigation system which combines the inertial system as main part with other systems as assistant part is becoming a research hotspot. The paper gives a method for building a multi-sensor integrated navigation system formed by inertial navigation system,GPS and magnet sensor,and does some simulation for the integrated navigation system. The result shows that the integrated navigation system can meet the requirement of UAV's navigation and has fine stability.

Abstract: Atechnique for the on-line monitoring of the availability of navigation support of objects has been considered using the wide area differential subsystem of GPS/GLONASS satellite radio navigation systems. This technique is based on estimating the total probability of solving the problem of navigation determinations with the specified level of accuracy and continuity. The technique developed can be used for enhancing the efficiency of algorithms of monitoring the integrity of satellite radio navigation systems and their differential supplemen3ts under conditions of exposure to sudden unfavorable geophysical factors.