Guidance system

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

Stochastically Optimized Monocular Vision-Based Guidance Design

Abstract: This paper designs a relative navigation and guidance system for unmanned aerial vehicles for monocular vision-based control applications. Since 2-D vision-based measurement is nonlinear with respect to the 3-D relative state, an extended Kalman fllter (EKF) is applied in the navigation system design. It is well-known that the vision-based estimation performance highly depends on the relative motion of the vehicle to the target. Therefore, a main objective of this paper is to derive an optimal guidance law to achieve given missions under the condition that the EKF-based relative navigation outputs are fed back to the guidance system. This paper suggests a stochastic optimal guidance design that minimizes the expected value of a cost function of the guidance error and control efiort subject to the EKF prediction and update procedures. A one-step-ahead suboptimal optimization technique is implemented to avoid iterative computations. The approach is applied to vision-based target tracking and obstacle avoidance, and simulation results are illustrated.

Target locating system and approach guidance system

Abstract: The invention comprises a mulli-wave radar system for obtaining first target position information of a flying object by capturing and tracking the flying object from a maximum detection distance, a stereo-camera system for taking over the tracking of the flying object in the vicinity of a landing point by acquiring the first target position information of the flying object from the milli-wave radar system, and obtaining second target position information having higher precision than the first target position information, and a controller for managing the first target position information of the milli-wave radar system and the second target position information of the stereo-camera system, controlling the milli-wave radar system to capture and track the flying object to the vicinity of the landing point, and controlling the stereo-camera system to capture and track the flying object at the time of landing of the flying object.

Localization Framework for Real-Time UAV Autonomous Landing: An On-Ground Deployed Visual Approach.

Abstract: [-5]One of the greatest challenges for fixed-wing unmanned aircraft vehicles (UAVs) is safe landing. Hereafter, an on-ground deployed visual approach is developed in this paper. This approach is definitely suitable for landing within the global navigation satellite system (GNSS)-denied environments. As for applications, the deployed guidance system makes full use of the ground computing resource and feedbacks the aircraft's real-time localization to its on-board autopilot. Under such circumstances, a separate long baseline stereo architecture is proposed to possess an extendable baseline and wide-angle field of view (FOV) against the traditional fixed baseline schemes. Furthermore, accuracy evaluation of the new type of architecture is conducted by theoretical modeling and computational analysis. Dataset-driven experimental results demonstrate the feasibility and effectiveness of the developed approach.

Variable structure-based nonlinear missile guidance/autopilot design with highly maneuverable actuators

Abstract: In this brief, we propose a variable structure based nonlinear missile guidance/autopilot system with highly maneuverable actuators, mainly consisting of thrust vector control and divert control system, for the task of intercepting of a theater ballistic missile. The aim of the present work is to achieve bounded target interception under the mentioned 5 degree-of-freedom (DOF) control such that the distance between the missile and the target will enter the range of triggering the missile's explosion. First, a 3-DOF sliding-mode guidance law of the missile considering external disturbances and zero-effort-miss (ZEM) is designed to minimize the distance between the center of the missile and that of the target. Next, a quaternion-based sliding-mode attitude controller is developed to track the attitude command while coping with variation of missile's inertia and uncertain aerodynamic force/wind gusts. The stability of the overall system and ZEM-phase convergence are analyzed thoroughly via Lyapunov stability theory. Extensive simulation results are obtained to validate the effectiveness of the proposed integrated guidance/autopilot system by use of the 5-DOF inputs.