Showing papers on "Guidance system published in 1980"

The "Magnetic wheel" in the suspension of high-speed ground transportation vehicles

Abstract: The electromagnetic support and guidance system for magnetic levitation railways consists of electromagnets on the vehicle and an armature rail on the track. The experience gained in the operation of the experimental vehicles built so far have lead to the development of a modular structure of the support and guidance system which uses the "magnetic wheel" as a self-contained functional unit. This concept, which is characterized by modular mechanical and electrical structures in connection with decentralized control systems, has made possible a higher reliability by functional redundancy and an improvement of the dynamic characteristics of the vehicle track systems. The results show that such a system is economically feasible within the constraints of existing technology and that it provides a very promising approach for future tracked high-speed ground transportation systems.

Sequential time discrimination system for sub-delivery systems

Abstract: A delivery system for multiple sub-missiles including in the sub-missiles a marking system, a detection system, a diverter for elimination of targets identified by the detector system, a scanner for initial determination of multiple targets, a logic circuit utilizing input from both the diverter and the scanner to eliminate targets and a sub-missile guidance system.

Track guidance system for tram - includes automatic retraction of mirrors to fit inside compact tunnels, triggered by guideway

Abstract: The track guided bus (1) fitted with retracting driving mirrors (9) to enable it to operate in narrow tunnels when guided, and with the mirrors extended for normal road travel. The retraction is powered by servo motors linked to an automatic control on the guidance sensors. The support arms for the mirrors are mounted on the roof of the bus or at the front. The mirror support combines the good visibility of the open road travel with the guidance in compact tunnels.

Missile guidance system - using laser beams for scanning, correlating reflected rays and sequentially scanning terrain elements

Abstract: The guidance system uses a series of laser beams (V, R, L) directed downwards in varying directions from the missile (300), with the reflected radiation correlated to obtain missile guidance signals. At least two laser rays(1, 2) within one of the beams (V) scan the same adjacent terrain elements(101, 102) one after the other, with the correlation obtained between the subsequent time modulations of each two such reflected rays(11, 12). The latter laser beam (V) is directed in front of the missile(300) with two additional beams (R, L) directed to either side of it, with the difference in the obtained correlation times for the latter two beams (R, L) used to provide the rotation of the missile about its vertical axis. The beams (V, R, L) may be modulated to allow the missile altitude to be determined by comparing the transmitted and reflected beams.

Cruise-missile-carrier navigation requirements

Abstract: This paper addresses the modeling, simulation, and performance predictions used in determining aircraft avionics and transfer-alignment requirements for a generic aircraft that would launch cruise missiles over water, a considerable distance from a first TERCOM (terrain comparison) update area. Such would be the case for an undefended wide-body aircraft that must remain far away from an opponent's air defense system. This long standoff range presents some unique requirements that are not present in a mission where cruise missiles are launched "close" to the first fix point, as from a penetrating bomber. The methodology used and the system requirements' results are described. I. Introduction T HIS paper describes the methodology and results of a parametric study conducted to determine the navigation requirements for cruise missile (CM) carrier aircraft (CMCA) candidates.1 Section II of this paper describes the methodology used in allocating the allowable navigation errors between the CM guidance system and the CMCA avionics system. From this baseline error allocation, avionics and transfer-alignment tradeoff studies were conducted. These tradeoff studies are described in Sees. Ill and IV, respectively. In Sec. V, a total weapon-system evaluation from aircraft takeoff to CM impact is presented which validates the error allocation of Sec. II for the models assumed in the study.

SLBM Fire Control Computational Algorithms in Support of Stellar Inertial Guidance

Abstract: : The addition of stellar guidance to a submarine launched ballistic missile (SLBM) system imposes special computational requirements on the fire control system. In general, the stellar guidance algorithms use the observable misorientations of the guidance inertial platform derived from an inflight star sighting and a statistical representation of the weapon system errors to obtain an estimate of the errors in guidance computed state vector (i.e., position, velocity, and inertial platform misorientation). In practice, these errors are estimated by the application of a precomputed gain matrix to the sighting information. The computation of this gain is a fire control responsibility. The improvement in weapon system accuracy achievable through incorporation of this stellar inertial guidance scheme is dependent on the orientation of the guidance inertial platform, i.e., the star to be sighted. An additional fire control task, therefore, is the selection of a star (from a catalog of stars) which enhances the observability of system errors and restricts the propagation of non-observable system errors. The implementation of algorithms to perform these tasks in a time constrained environment is the subject of this paper.

The Range Only Correlation System

Abstract: Developed specifically as a position updating guidance system for missile applications, the feasibility of the Range Only Correlation System (ROCS) was established by computer simulation in 1969-1970 and flight testing in 1975-1977. ROCS consists of a conventional radar sensor and a digital processor; it establishes the actual location of a vehicle flying at either high or low altitude extremes and over a wide variety of terrain characteristics. For high altitude applications this system derives position information by sequentially comparing three or more independent radar range returns with prestored range references. For low altitude applications vertical position information is obtained with the system operating in an altimeter mode, while horizontal position information is derived by comparing two independent radar range returns with references. The general features of this position updating system are presented. This includes a description of the radar sensor, the digital processor, the reference data, the performance characteristics, and lastly, the objectives of the current flight test program.

Missile guidance system

Abstract: PURPOSE:To make it possible to simplify the structure of an automatic trancking system and also to reduce the agitation of a beam due to a scan, by taking the scan with an electric seeker axis agreeing with a missile axis. CONSTITUTION:As for the homing guidance system for a missile, error angle detector 1 of K1 in gain detects error angle vector epsilon between visual-line unit vector T indicating the direction of a target and unit vector S indicating the direction of the electric seeker axis having been scanned agreeing with the axis of the missile, and controller 2 composed of steering unit 4 and rate detector 5 guides the missile by turning around to eliminate epsilon. If an error angle exists between missile axis vectors KB and SS', the output of rate detector 5 is fed back to the electric seeker axis by electric seeker axis scan control part 3 in proportion to the error angle, thereby controlling the guidance with the electric seeker axis agreeing with the missile axis angle.