Guidance system

About: Guidance system is a research topic. Over the lifetime, 4282 publications have been published within this topic receiving 45964 citations.

Guidance law design based on non-smooth control

Abstract: The guidance law design for the missile–target interception problem in the presence of system uncertainty is investigated in this paper. To improve the disturbance rejection property, two kinds of non-smooth guidance laws based on a finite-time control technique are developed. The first is a high-gain finite-time guidance law, which can be derived by assuming that the system uncertainty is bounded by a constant. The second one is a composite guidance law including a disturbance observer and a finite-time state feedback, where the disturbance observer is introduced to estimate the system uncertainty and the finite-time state feedback is to stabilize the guidance system. Under both of the proposed guidance laws, it can be proved that the line-of-sight angle rate will converge to the origin or a small region of the origin in a finite time. Simulation comparisons show the effectiveness of the proposed method.

Real-time pilot guidance system for improved flight-test maneuvers

Abstract: The Dryden Flight Research Facility of the NASA Ames Research Center has developed a pilot trajectory guidance system that increases the accuracy of flight-test data and decreases the time required to achieve and maintain desired test conditions. The system usually presented to the pilot computed differences between reference or desired and actual flight state conditions. The pilot then used a cockpit display as an aid to acquire and hold desired test conditions. This paper discusses various flight-test maneuvers and the quality of data obtained using the guidance system. Some comparisons are made between the quality of maneuvers obtained with and without the system. Limited details of the guidance system and algorithms used are included. In general, the guidance system improved the quality of the maneuvers and trajectories flown, as well as allowing trajectories to be flown that would not have been possible without the system. This system has moved from the developmental stage to full operational use in various Dryden research and test aircraft.

Method and apparatus for directing a pursuing vehicle to a target with evasion capabilities

Abstract: A method and apparatus for directing a pursuing vehicle, such as a torpedo,n an intercept trajectory from a launching vehicle to a target vehicle with evasion capabilities Models of the pursuing vehicle and evading target provide proposed trajectories based upon various environmental considerations A guidance system uses estimates of initial operating parameter solutions, such as gyro angle, alertment time and intercept time, to begin a convergent, iterative process that defines final operating parameter solutions from which the guidance parameters are determined and transferred to the pursuing vehicle at launch These parameters take into account various evasive strategies that a target vehicle might use to avoid being intercepted by the pursuing vehicle

A Vision-Based Gestural Guidance Interface for Mobile Robotic Platforms

Abstract: This paper describes a gestural guidance interface that controls the motion of a mobile platform using a set of predefined static and dynamic hand gestures inspired by the marshalling code. Images captured by an onboard color camera are processed at video rate in order to track the operator’s head and hands. The camera pan, tilt and zoom are adjusted by a fuzzy-logic controller so as to track the operator’s head and maintain it centered and properly sized within the image plane. Gestural commands are defined as two-hand motion patterns, whose features are provided, at video rate, to a trained neural network. A command is considered recognized once the classifier has produced a series of consistent interpretations. A motion-modifying command is then issued in a way that ensures motion coherence and smoothness. The guidance system can be trained online.