Guidance system

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

Ordnance delivery system and method including remotely piloted or programmable aircraft with yaw-to-turn guidance system

Abstract: A method and system for delivery ordnance to a target via a remotely piloted or programmable aircraft including a yaw-to-turn guidance system, a deployment and launching system and packaging for the aircraft are disclosed.

In-Flight Alignment and Calibration of Inertial Measurement Units - Part I: General Formulation

Abstract: This is the first part of a two-part paper which summarizes work pursued by the author in 1966 [1]. The paper describes the application of minimum-variance estimation techniques for in-flight alignment and calibration of an inertial measurement unit (IMU) relative to another IMU and/or some other reference. The first part formulates the problem, and the second part [2] reports numerical results and analyses. The approach taken is to cast the problem into the framework of Kalman-Bucy estimation theory, where velocity and position differences between the two IMU's are used as observations and the IMU parameters of interest become part of the state vector. Instrument quantization and computer roundoff errors are considered as measurement noise, and environmental induced random accelerations are considered as state noise. Typical applications of the technique presented might include the alignment and calibration of IMU's on aircraft carriers, the initialization of rockets or rocket airplanes which are launched from the wing of a mother ship, the alignment and calibration of IMU's which are only used in the latter phases of rocket flight, and for the initialization/updating of SST guidance systems.

Implementation and Flight Test Results of MILP-based UAV Guidance

Abstract: This paper discusses the implementation of a guidance system based on mixed integer linear programming (MILP) on a modified, autonomous T-33 aircraft equipped with Boeing's UCAV avionics package. A receding horizon MILP formulation is presented for safe, real-time trajectory generation in a partially-known, cluttered environment. Safety at all times is guaranteed by constraining the intermediate trajectories to terminate in a loiter pattern that does not intersect with any no-fly zones and can always be used as a safe backup plan. Details about the real-time software implementation using CPLEX and Boeing's OCP platform are given. A test scenario developed for the DARPA-sponsored software enabled control capstone demonstration is outlined, and simulation and flight test results are presented

Automated guidance system for a vehicle

Abstract: A system for automatically steering a vehicle through an irregular structure. A flexible lighting tube, in proximity to the back of the structure, communicates with at least one canted video camera. A processor takes the output of the camera, determines the position of the vehicle, and provides guidance to thevehicle's steering mechanism.

Mode confusion analysis of a flight guidance system using formal methods

Abstract: The paper discusses mode confusion analysis of a flight guidance system using formal methods. The paper describes the use of automated analysis tools, such as model-checkers and theorem provers, to search for potential sources of mode confusion in a representative specification of the mode logic of a Flight Guidance System.