Guidance system

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

Nonlinear Guidance and Navigation of a Tactical Missile with High Heading Error

Abstract: This study examines the guidance and navigation problem of an acceleration constrained tactical missile for any initial missile and target orientation. A nonlinear guidance law (NGL) based on the theory of nonlinear differential geometric methods is presented, and an extended Kalman filter (EKF) in modified spherical coordinate (MSC) has been invoked for the third party (tracking radar) to estimate the missile-to-target position, velocity, and acceleration before handing over. After locking on the target, the RF seeker of the missile is used to estimate the required guidance information using active seeker measurements. It can be shown that the design of the guidance algorithm valid for arbitrary initial missile and target orientation in three dimension (3-D) has to null not only the line of sight (LOS) rate but also the relative heading error (RHE). The performance of a tactical missile with an active RF seeker in high relative heading error (RHE) is evaluated using the combination of an EKF and the NGL in two dimension (2-D) space. In particular, a comparison is made between two guidance schemes using estimated states from an EKF. The two guidance schemes are 1) a composite NGL coupled with a terminal side jet control (TSJC), and 2) a traditional extended proportional navigation (EPN) guidance law also coupled with the TSJC. The results show that the composite NGL coupled with a TSJC provides a significant improvement in high RHE engagements over the traditional PN type guidance law.

Monitoring of a free space for motor vehicles

Abstract: The maneuvering of a road vehicle so as to avoid collision with objects, eg reversing into a garage [13] uses processed images from a digital camera. The guidance system generates virtual corridor surfaces [16] that ensure that the vehicle avoids contact with real surfaces as the doorway [14] is approached. The walls are updated as the vehicle moves.

Flat guidance schemes for magnetically levitated high‐speed guided ground transport

Abstract: A magnetically levitated high‐speed vehicle requires a noncontact guidance system. Guideway configurations are discussed, and the possibility of achieving guidance from a flat surface is investigated. A vehicle with electrodynamic suspension and linear synchronous motor propulsion carries superconducting magnets which may be used for guidance purposes. Eight possible ``flat'' guidance mechanisms are examined. It is shown that the interaction between vehicle‐borne magnets and levitation strips or linear synchronous motor (LSM) windings cannot provide adequate restoring forces. Additional conductors are therefore required for guidance. The use of either vertically mounted rectangular loops or horizontally mounted null‐flux (NF) loops under either the levitation magnets or propulsion magnets is therefore examined. The most promising system involves the interaction between propulsion magnets and horizontal NF loops, with the interaction between propulsion magnets and the edges of the levitation strips providing backup guidance. The guidance characteristics are analyzed and checked by model impedance measurements, and it is shown that, for this system a lateral stiffness of 106 N/m can be achieved.

Infrared vision based automatic landing guidance method and system applied to fixed-wing UAV (unmanned aerial vehicle)

Abstract: The invention discloses an infrared vision based automatic landing guidance method and system applied to a fixed-wing UAV (unmanned aerial vehicle). The system comprises two identical image tracking modules, an image processing module, a control module and a wireless transmission module, wherein each image tracking module comprises a camera and biaxial pan-tilt units. According to the method, the UAV is detected, identified and tracked in images with an image tracking technology, and deflecting angles of the pan-tilt units are accurately recorded; the relative space position of the UAV can be determined through geometric relationship analysis and trigonometric calculation of pitch heading angles of the two pan-tilt units and the distance between the pan-tilt units, and position information of the UAV is sent to the UAV through the wireless transmission module, so that the UAV is guided to accurately land. The infrared vision based automatic landing guidance system is constructed on two sides of a landing runway of the UAV, complicated image processing is performed based on powerful computing capacity of a ground-based computer, each guidance device is utilized to the greatest extent, the accuracy of the system is improved, the control is simple, and real-time performance and stability are good.