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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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Patent
03 Sep 1985
TL;DR: In this article, the camera detector raster is deliberately underscanning the camera and driving the camera's deflection coils with signals from pitch and yaw body rate sensors on the missile.
Abstract: In an optical guidance system, body fixed electronic image stabilization of television imaging is used to allow strapdown seeker guidance in a missile. Electronic image stabilization eliminates the need for a stabilized sensor or seeker platform while providing the same line-of-sight information that would have been obtained from the platform. Body fixed electronic image stabilization compensates for routine vibrational and rotational motion experienced by a missile airframe during flight. This compensation is accomplished by deliberately underscanning the camera and driving the camera's deflection coils with signals from pitch and yaw body rate sensors on the missile. The image developed on the camera detector raster is thereby moved in an equal and opposite direction to the sensed, experienced, motion during the same instant that the motion is occuring. Compensation thus stabilizes the resultant image, which would otherwise be a blur of motion on the display screen.

29 citations

Patent
01 Mar 1991
TL;DR: In this article, a "hardware-in-the-loop" simulator for training people in the use of a missile system to teach target acquisition, missile launch, and missile guidance under simulated battlefield conditions is presented.
Abstract: A "hardware-in-the-loop" simulator (10) for training people in the use of a missile system to teach target acquisition, missile launch, and missile guidance under simulated battlefield conditions. A battlefield environment (E) including at least one target (T) movable therewithin is created by a simulation module (12). Missile system hardware (H) including the missile acquisition, tracking, and guidance portions is provided. An interface module (20) converts signals produced by the simulating module to an infrared image acceptable by the hardware. The resultant image represents a field-of-view (FOV), including the target, within the battlefield environment. An image module (32) produces a dynamic image representative of the missile's position in the field-of-view. This image is observable by the hardware which utilizes it to determine the position of the missile relative to the target. The hardware also determines if a missile guidance signal is to be sent to the missile to guide it to the target. If so, the interface module is responsive to the guidance signal to simulate, in real-time, the response of the missile to the guidance signal.

29 citations

Journal ArticleDOI
TL;DR: In this paper, a simplified TBM guidance system is proposed based on integration of automated data collection with real-time computing, where the TBM's position in terms of point coordinates is continuously and automatically surveyed by a robotic total station, thus making it feasible to derive any line and level deviations from as-designed tunnel alignment in real time.
Abstract: This research aims to develop an automated and cost-effective solution to guide the advance of a tunnel-boring machine (TBM) during microtunneling and pipe jacking operations. Pros and cons of currently available TBM guidance systems are evaluated. A simplified TBM guidance system is proposed based on integration of automated data collection with real-time computing. The TBM's position in terms of point coordinates is continuously and automatically surveyed by a robotic total station, thus making it feasible to derive any line and level deviations from as-designed tunnel alignment in real time. Furthermore, given the coordinates of three observation points on the TBM, the attitudes of the TBM, which are described by three rotation angles of yaw, pitch, and roll, can be determined by a vector observation algorithm. Monte Carlo simulation was conducted to assess errors of point positioning and attitude determination by the proposed solution. For concept proving and application demonstration, a hardware-software integrated prototype system was developed in house and validation experiments were successfully conducted in terms of: (1) automated surveying of multiple targets; (2) attitude determination for a moving object that mimicked a working TBM; and (3) field installation and testing based on an ongoing project.

29 citations

Journal ArticleDOI
TL;DR: A new approach toward the automated solution of realistic near-optimal aircraft trajectories is introduced and implemented in a software package named Ace, where the optimal open-loop trajectory for a three-degree-of-freedom aircraft model is first solved by using direct multiple shooting and then inverse-simulated by using an integration inverse method based on Newton's iteration.
Abstract: A new approach toward the automated solution of realistic near-optimal aircraft trajectories is introduced and implemented in a software package named Ace. In the approach, the optimal open-loop trajectory for a three-degree-of-freedom aircraft model is first solved by using direct multiple shooting. Then the obtained trajectory is inverse-simulated with a more sophisticated five-degree-of-freedom performance model by using an integration inverse method based on Newton's iteration. The trajectories are evaluated visually and by analyzing errors between the trajectories. If the errors remain within a suitable application-specific tolerance, the inverse-simulated trajectory can be considered to be a realistic near-optimal trajectory that could be flown by a real aircraft. Otherwise, the parameters affecting the optimization and inverse simulation are altered and the computations are repeated. The example implementation of the approach, the Ace software, contains a graphical user interface that provides a user-oriented way to analyze aircraft minimum time and missile avoidance problems. In the software, the computation of the optimal and inverse-simulated trajectories is fully automated. The approach is demonstrated with numerical examples by using Ace.

29 citations

Proceedings ArticleDOI
27 Jun 2007
TL;DR: An efficient way to model no-fly zones, to generate a path in real-time to avoid known or "pop-up" obstacles, and to reconfigure the flight path in the event of reduced aircraft performance is presented.
Abstract: This paper presents a guidance algorithm for an unmanned aerial vehicle (UAV). It combines a nonlinear lateral guidance control law, originally designed for UAVs tracking circles for mid-air rendezvous, with a new simple adaptive path planning algorithm. Preflight path planning only consists of storing a few way points guiding the aircraft to its targets. The paper presents an efficient way to model no-fly zones, to generate a path in real-time to avoid known or "pop-up" obstacles, and to reconfigure the flight path in the event of reduced aircraft performance. Simulation results show the good performance of this reconfigurable guidance system which, moreover, is computationally efficient.

29 citations


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Performance
Metrics
No. of papers in the topic in previous years
YearPapers
202319
202252
202197
2020141
2019194
2018206