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Guidance system
About: Guidance system is a research topic. Over the lifetime, 4282 publications have been published within this topic receiving 45964 citations.
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TL;DR: In this paper, a new guidance technique, referred to as 4-D guidance, is developed to improve the operation of future STOL aircraft transportation systems, which is a technique of synthesizing a complex three-dimensional flight path from simple pilot inputs and flying the aircraft along the path according to an ATC specified time schedule.
Abstract: A new guidance technique, referred to as 4-D guidance, is being developed to improve the operation of future STOL aircraft transportation systems. 4-D guidance refers to a technique of synthesizing a complex three-dimensional flight path from simple pilot inputs and flying the aircraft along the path according to an ATC specified time schedule. The two major elements of a 4-D guidance system are the trajectory synthesizer and the control law for flying the aircraft along the synthesized trajectory using the aircraft's autopilot and autothrottle. Inputs to the trajectory synthesizer are the three-dimensional coordinates of waypoints, the turning radius, the speed range, the acceleration limits and the arrival time at time control waypoints. First the three-dimensional trajectory is computed using circular arcs and straight lines. Then the airspeed profile, compensated for wind, is calculated to achieve the desired arrival times. The pilot is informed if the arrival times cannot be achieved. The synthesized trajectory is stored as a time sequence of reference states and controls which the aircraft is forced to track using a linear feedback law.
13 citations
Patent•
22 Sep 1982TL;DR: In this article, a method for augmenting the value of range uplink information in a predictive proportional navigation terminal guidance scheme is proposed, which results in acceptable miss distances, better than conventional proportional navigation, with sensitivity to unmodeled errors substantially less than that in modern guidance systems.
Abstract: A method for augmenting the value of range uplink information in a predictive proportional navigation terminal guidance scheme. A second order configuration, with noise adaptive varying gain parameters calculated as a function of time-to-go, is particularly useful for high altitude, minimally maneuvering targets. This configuration results in acceptable miss distances, better than conventional proportional navigation, with sensitivity to unmodeled errors being substantially less than that in modern guidance systems. A third order configuration makes enhanced use of range uplink information to provide improved terminal guidance against lower altitude maneuvering targets. The sensitivity of the third order configuration is similar to that of conventional proportional navigation but with better miss distance results.
13 citations
19 Jun 2012
TL;DR: The algorithm presented in the paper is designed to perform a fully adaptive autonomous landing starting from any point of the three dimensional space, based on the use of the DGPS/AHRS technology.
Abstract: This paper presents the flight test results of a fully adaptive algorithm for autonomous fixed wing aircrafts landing developed by CIRA, the Italian Aerospace Research Centre. The algorithm is designed and implemented in the framework of a complete autonomous guidance system, worked out by CIRA, able to allow autonomous way-points navigation, autonomous landing and autonomous collision avoidance for fixed wing aircrafts. The algorithm presented in the paper is designed to perform a fully adaptive autonomous landing starting from any point of the three dimensional space, based on the use of the DGPS/AHRS technology. Main features of the autolanding system based on the implementation of the proposed algorithm are: on line landing trajectory re-planning, fully autonomy from pilot inputs, weakly instrumented landing runway, ability to land starting from any point in the space and autonomous management of failures and/or adverse atmospheric conditions. The flight tests have been conducted at an airfield in Caserta, in the south of Italy, close the CIRA. The paper is structured into several paragraphs describing the algorithm designed for the autolanding maneuver, the control system architecture and the methodologies developed in order to safely manage the possible presence of failures and/or unfavorable weather conditions, the preliminary results of the real time validation with hardware in the loop simulation and, finally, the performances achieved by using the CIRA experimental flying platform, with reference to the real flight experiments.
13 citations
TL;DR: The proposed wearable guidance system is tested under various local pathway scenes, and the results confirm its efficiency in assisting blind people to attain autonomous mobility.
Abstract: A wearable guidance system is designed to provide context-dependent guidance messages to blind people while they traverse local pathways. The system is composed of three parts: moving scene analysis, walking context estimation and audio message delivery. The combination of a downward-pointing laser scanner and a camera is used to solve the challenging problem of moving scene analysis. By integrating laser data profiles and image edge profiles, a multimodal profile model is constructed to estimate jointly the ground plane, object locations and object types, by using a Bayesian network. The outputs of the moving scene analysis are further employed to estimate the walking context, which is defined as a fuzzy safety level that is inferred through a fuzzy logic model. Depending on the estimated walking context, the audio messages that best suit the current context are delivered to the user in a flexible manner. The proposed system is tested under various local pathway scenes, and the results confirm its efficiency in assisting blind people to attain autonomous mobility.
13 citations