Showing papers on "Guidance system published in 1979"

Drone-type missile

Abstract: The invention relates to a drone-type missile for combatting ground targets from the ground, particularly for the use against targets which emit electromagnetic rays, such as radar stations; with built-in target-seeking head, guidance system, self-propulsion and take-off assist, preferably a booster rocket.

Digital flight guidance system

Abstract: A digital flight guidance system includes a pair of processors, each with its own memory means and arranged with common input and output means for providing monitored guidance of an aircraft when the craft is in cruise modes or when the craft is performing a critical maneuver such as landing, terrain following, or the like

Trajectory shaping of anti-armor missiles via tri-mode guidance

Abstract: In a missile system, a simple way to guide a missile in a predetermined tectory from launch to the impacting with a target for optimum warhead penetration of armor by a guided missile. Initially, the missile is guided in yaw by proportional navigation. Subsequently it is guided in pitch first by a pitch programmer until the missile reaches a predetermined gimbal angle between a line of sight of a seeker of the missile and a centerline of the missile, then in pitch by a pseudo-time-optimal closed loop controller to direct the missile pitch attitude at a predetermined rate toward a target until said missile reaches another predetermined gimbal angle, and finally by proportional navigation in pitch of the missile to the target.

Feasibility study of route guidance system

Abstract: The Comprehensive Automobile Traffic Control (CAC) Project was started in 1973 as a six-year project sponsored by the Agency of Industrial Science and Technology, Ministry of International Trade and Industry. The aim of this major project is to develop a comprehensive system for controlling the flow of vehicular traffic through the use of the most up-to-date computer and other technology for monitoring and controlling traffic in order to improve overall traffic conditions by reducing accidents, congestion, and air pollution and to relieve drivers of unnecessary mental stress. This paper presents some results of the feasibility study of this CAC system. Since route guidance plays the most important role in the CAC system, a detailed explanation is given of the route guidance subsystem and its guidance algorithm, which is based on the results of computer simulation. This report also discusses the effects that might be expected from introducing the CAC system in an area of Tokyo that contains 1500 intersections. In particular, this report closely scrutinizes the important route guidance subsystem, providing a quantitative analysis of the possibilities for easing congestion and achieving various other effects. A general review is made of the cost and benefits of such a system. (Author)

An Automatic Guidance System for Tractors

Abstract: A digital controller is described which is used in a guidance system for automatic steering of an agri-cultural tractor. This controller is constructed from digital logic elements. Field performance experience with the controller is also described.

Echo exhancing decoy

Abstract: A method of interdicting a guided missile equipped with an active radar-controlled guidance system is shown to include generating decoy signals in a transponder on an decoy launched from a ship being attacked, such decoy signals being formed by amplifying echo signals from the ship to cause the apparent position of the ship (as measured by the active radar-controlled guidance system) to differ from the actual position of the ship so that the guided missile ultimately is caused to miss the ship.

Fuel-conservative guidance system for powered-lift aircraft

Abstract: A concept for automatic terminal area guidance, comprising two modes of operation, was developed and evaluated in flight tests. In the predictive mode, fuel efficient approach trajectories are synthesized in fast time. In the tracking mode, the synthesized trajectories are reconstructed and tracked automatically. An energy rate performance model derived from the lift, drag, and propulsion system characteristics of the aircraft is used in the synthesis algorithm. The method optimizes the trajectory for the initial aircraft position and wind and temperature profiles encountered during each landing approach. The design theory and the results of simulations and flight tests using the Augmentor Wing Jet STOL Research Aircraft are described.

Guidance system for a roving vehicle

Abstract: Computer controlled guidance system for semiautonomous robot guides robot in incompletely defined environment. System operates in real time avoiding obstacles detected by "stereo television and laser range finder eyes."

Armed expendable decoy

Abstract: A method of interdicting a guided missile equipped with an active radar-controlled guidance system is shown to include generating decoy signals in a transponder on an armed decoy launched from a ship being attacked toward such missile, such decoy signals initially obscuring echo signals from the ship to cause the apparent position of the ship (as measured by the active radar-controlled guidance system) to differ from the actual position of the ship, and, when the decoy and guided missile are in proximity with one another, exploding a warhead on the decoy to destroy the guided missile.

Independent landing monitor

Abstract: This invention comprises means for monitoring the operation of an aircraft landing guidance system which functions independently of the landing guidance system. The means include a radio altimeter aboard the aircraft, a reflector positioned on the ground at a predetermined location along the prescribed approach path to provide enhanced return of the altimeter signal and means for comparing the actual radio altitude with a predetermined altitude value to provide an indication of the location of the aircraft within a tolerable distance from a prescribed point on the approach path.

Evaluation of the navigation performance of shipboard-VTOL-landing guidance systems

Abstract: The objective of this study was to explore the performance of a VTOL aircraft landing approach navigation system that receives data (1) from either a microwave scanning beam (MSB) or a radar-transponder (R-T) landing guidance system, and (2) information data-linked from an aviation facility ship. State-of-the-art low-cost-aided inertial techniques and variable gain filters were used in the assumed navigation system. Compensation for ship motion was accomplished by a landing pad deviation vector concept that is a measure of the landing pad's deviation from its calm sea location. The results show that the landing guidance concepts were successful in meeting all of the current Navy navigation error specifications, provided that vector magnitude of the allowable error, rather than the error in each axis, is a permissible interpretation of acceptable performance. The success of these concepts, however, is strongly dependent on the distance measuring equipment bias. In addition, the 'best possible' closed-loop tracking performance achievable with the assumed point-mass VTOL aircraft guidance concept is demonstrated.

Minicomputer Applications In Automated Testing Of Electro-Optical Guidance Systems

Abstract: An Automated Laser Seeker Performance Evaluation System (ALSPES) has been developed at the US Army Missile Research and Development Command (USAMIRADCOM) which utilizes a minicomputer to implement the control functions required to test electro-optical (E /0) guidance systems. Software programs have been written for a series of tests which fully evaluate E /0 seeker performance. Test conditions are fed into a CRT terminal and the minicomputer conducts a fully automated, "hands-off" test by varying such parameters as laser energy, target position and velocity, seeker position and angular rate, and time separation between targets. This paper discusses the types of automated tests performed, the electro-optical test equipment utilized and the layout of the test facility, the minicomputer to test equipment interface, and the cost savings resulting from the development of this automated test facility.

Classical versus modern homing missile guidance

Abstract: Modern guidance systems are generally accepted to yield better performance than classical proporticmal navigation systems However, it is not always recognized that this better performance carries with it certain costs in inproved components or additional instruments This paper compares a modern guiasnce system, MGS, to a classical proportional navigationai, PIV , homing misslle guidance system in terms of perforuance, robustness, and ease of implementation Q aan titative first order miss distances are compared to show that MGS has the smallest miss if component tolerances can be met, but as component tolerances or measurement errors degrade, MGS degrades faster than PN until, at relatively large component or measurement erl-ors, PN has less miss distance than MGS

Digital adaptive controllers for VTOL vehicles. Volume 1: Concept evaluation

Abstract: A digital self-adaptive flight control system was developed for flight test in the VTOL approach and landing technology (VALT) research aircraft (a modified CH-47 helicopter). The control laws accept commands from an automatic on-board guidance system. The primary objective of the control laws is to provide good command-following with a minimum cross-axis response. Three attitudes and vertical velocity are separately commanded. Adaptation of the control laws is based on information from rate and attitude gyros and a vertical velocity measurement. The final design resulted from a comparison of two different adaptive concepts--one based on explicit parameter estimates from a real-time maximum-likelihood estimation algorithm, the other based on an implicit model reference adaptive system. The two designs were compared on the basis of performance and complexity.

Guidance System Application to Missile‐X Basing Alternatives

Abstract: The Missile-X concept is based on the achievement of post-attack survivability. This is accomplished by preservation of missile location uncertainty through continuous or random missile/launcher movement which obscures observation by hostile forces. Three basing concepts have been developed to accommodate this periodic movement: (1) shuffling missile/launcher and missile/launcher simulators among a number of vertical shelters; (2) random movement of missile/launcher along a covered trench to presurveyed launch sites (Ground Mobile); (3) moving missiles via aircraft to random remote bases with the capability of air launch (Air Mobile). The first two modes are land launch, the missile guidance being achieved through use of a self-contained inertial guidance system. The Air Mobile guidance is accomplished with the same inertial system, however, augmentation is needed to obtain an acceptable accuracy. The guidance problem in the Air Mobile case is the determination of initial conditions at launch—estimation of position, velocity and alignment to tens of meters, several centimeters per second, and a few arc seconds, respectively, after up to 6 hours of cruise. The problem is made difficult by the uncertainty of the local gravity field. Several schemes have been investigated as a means to solve this problem; the basic Missile-X inertial guidance aided by: (1) doppler/altimeter radars with and without improved gravity data during cruise; (2) radio ground beacons during cruise; and (3) radio ground beacons during the missile boost phase. The use of Star Trackers is also considered. Results show that a combination of all these (except the Star Tracker) would provide a reliable system with a reasonable missile accuracy from an ensemble point of view. The study describes a specific configuration for such a system—for both land launch and air launch.

Time response simulation of the guidance and control system of an automatically steered wire-following vehicle

Abstract: Time-response simulation studies carried out in support of the development and validation of the guidance/steering subsystem of a wire-following-vehicle (WFV) are described. A lateral guidance system is outlined, field testing and simulation validation are covered, and time response simulation results are discussed.

Performance and Cost Analysis of a Command-Guided Ballistic Missile Radar

Abstract: : This report addresses many of the technical questions associated with developing and implementing a command-guided ballistic rocket using a microwave or millimeter radar to provide position and roll information for the rocket. The basic feasibility of an X-band radar for providing the rocket position and roll data was established in the first phase of this design study. The second phase of the investigation concentrated on providing additional depth in the treatment of the missile retroreflector configurations, more detailed performance and cost trade-offs among the beacon and passive reflector-equipped missile concepts, missile beacon transponder design tradeoffs and a recommended design configuration, and an analytical examination of multiple rocket tracking system concepts and tracking radar requirements.