Guidance system

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

Travel guidance system, travel guidance apparatus, travel guidance method, and computer program

Abstract: A guidance prompt used for guidance for a guide branch point ahead of a movable object is selected from among a plurality of potential guidance prompts, based on whether a distance from a guidance starting point where guidance starts to a guidance ending point by which guidance is required to be finished is greater than a distance traveled by the movable object while guidance is being spoken. The selected guidance prompt is then set as the guidance prompt for the guide branch point, and guidance for the guide branch point by the set guidance prompt is performed when the movable object reaches the guidance starting point associated with the set guidance prompt.

Precision-guided hypersonic projectile weapon system

Abstract: A precision-guided hypersonic projectile weapon system. The inventive system includes a first subsystem for determining a target location and providing data with respect thereto. A second subsystem calculates trajectory to the target based on the data. The projectile is then launched and guided in flight along the trajectory to the target. In the Illustrative application, the projectile is a tungsten rod and the first subsystem includes a forward-looking infrared imaging system and a laser range finder. The second subsystem includes a fire control system. The fire control system includes an optional inertial measurement unit and predicts target location. The projectile is mounted in a missile launched from a platform such as a vehicle. After an initial burn, the missile launches the projectile while in flight to the target. The missile is implemented with a rocket with a guidance system and a propulsion system. In accordance with the present teachings, the guidance system includes a transceiver system mounted on the projectile. The transceiver system includes a low-power continuous wave, millimeter wavelength wave emitter. A system is included at the launch platform for communicating with the projectile. The platform system sends a blinking command to the projectile and measures the round trip delay thereof to ascertain the range of the projectile. Velocity is determined by conventional Doppler techniques or differentiation. Azimuth and elevation are then determined by a monopulse antenna on the launch platform. As a consequence, the platform ascertains the location of the projectile and the impact point thereof. The platform generates a command to the projectile which is received by the projectile and used to actuate control surfaces to adjust the trajectory and impact point thereof as necessary.

Method and system for augmenting a guidance system with a path sensor

Abstract: In an automatic vehicle position control system, such as a satellite-based agricultural implement steering system, the satellite-based steering information is adjusted with information obtained from one or more path sensors to facilitate the automatic nudging of the vehicle to take account of inaccurate tracking of the agricultural implement relative to its tractor, terrain variations, and inaccuracies in the satellite-based steering system.

Attitude Guidance for Spinning Vehicles with Independent Pitch and Yaw Control

Abstract: The design and simulation of an attitude guidance and control scheme for a spinning aerospace vehicle is detailed. The basis for the guidance law is the projection of the angular-velocity vector onto a plane normal to the desired heading. The result of the projection is an attitude error that can be converted to pitch-and yaw-rate commands for an autopilot. Two single-input/single-output controllers are used in this paper, which in turn issue flap defiection commands. An asymmetrical vehicle spinning at 1.5 Hz with independent pitch-and yaw-flap sets is simulated in a six-degree-of-freedom simulation. It is shown to perform successful attitude maneuvers for two different cases. In one case, the basic guidance law is used. This results in a settling time of approximately 1.0 s. The next case performs the maneuver with a modified guidance law that includes decoupling terms. This case results in a settling time of 0.6 s. The guidance law has a number of possible applications. These include stability augmentation and redundancy, alternatives in fin Configurations for vehicles, and reduction in number of necessary control surfaces. Copyright © 2009.

Navigation and Guidance System Architectures for Small Unmanned Aircraft Applications

Abstract: Two multisensor system architectures for navigation and guidance of small Unmanned Aircraft (UA) are presented and compared. The main objective of our research is to design a compact, light and relatively inexpensive system capable of providing the required navigation performance in all phases of flight of small UA, with a special focus on precision approach and landing, where Vision Based Navigation (VBN) techniques can be fully exploited in a multisensor integrated architecture. Various existing techniques for VBN are compared and the Appearance-Based Navigation (ABN) approach is selected for implementation. Feature extraction and optical flow techniques are employed to estimate flight parameters such as roll angle, pitch angle, deviation from the runway centreline and body rates.