Showing papers on "Guidance system published in 1969"

Electronic celestial navigation means

Abstract: An automatic navigation and guidance system for use in moving vehicles such as air or sea craft, and more particularly a navigation system utilizing a single automatic star or satellite tracker through which a continuous indication of the longitude and latitude of the moving vehicle may be provided to an automatic guidance system, automatic star selection being provided, the described celestial navigation device providing continuous, accurate monitoring of a further inertial navigation device during normal operation, the further inertial navigation device providing continuous navigation and orientation during interruptions of the celestial navigation device.

Far field approximation for a nozzle exhausting into a vacuum.

Abstract: a perfect update of velocity, position, and attitude occurs prior to the burn from the parking orbit. The system parameters used in the evaluation technique can be estimated using techniques that are relatively unsophisticated but are of sufficient accuracy to accomplish the desired result. These techniques were implemented in computer programs now in use at NASA/ERG. The computer programs were exercised on a Jupiter flyby mission. For this mission and the assumptions made, it can be concluded that the accuracy of the strapdown guidance systems evaluated is adequate to accomplish the guidance and navigation of a Jupiter flyby mission. If the first midcourse correction is made 10 days after launch and the required probability of mission failure attributable to guidance is 0.05, the reliability (mean time to failure) of the pure inertial strapdown guidance systems considered is such that no system examined would succeed if operated continuously from launch to midcourse. If the probability of mission failure attributable to guidance is relaxed to 0.1, the two specified systems still fail if midcourse correction is made 10 days after launch. An optimum system which will succeed is found. Concentrated attention to reduction of system power requirements would yield a significant reduction in the weight attributable to guidance for this specific mission. This might be achieved by development of a lightweight variable thermal impedance for the ISU.

Method and apparatus for vehicle control and guidance

Abstract: A vehicle guidance and control system for providing information concerning the speed and direction of movement of a vehicle along a predetermined path on a roadway. The path is defined by a plurality of spaced, permanently magnetized elements located along the roadway. Vehicle mounted sensors respond to the magnetic fields of the elements and produce electrical signals representing the speed and direction of movement of the vehicle with respect to the path. In one embodiment, the electrical signals are employed as control signals in a closed loop electromechanical guidance system for the vehicle. By varying the pattern of magnetic polarization of the elements, binary information can be transferred from the roadway to the vehicle. With suitable data processing equipment in the vehicle, traffic information, such as, speed limits, directions, accident information, exit directions and the like can be visually presented to the vehicle operator.

System for the optical automatic and autonomous guiding of self-rotating missiles

Abstract: An automatic and autonomous optical guidance system for an autorotative missile to be directed towards a target emitting radiations, the missile having a single flight-control rudder operable at each revolution of the missile about its axis of rotation; comprising an optical target position detecting means for producing, at each revolution of the missile, signals which are a function of the deviation between the autorotational axis of the missile and the missile-target direction; control signal producing means connected to the optical detecting means for generating, at each revolution of the missile, a control energy; and motor means connected to the control signal producing means in order to be supplied thereby and positively coupled with the single flight-control rudder in order to guide the missile, at each revolution thereof, as a function of the deviation between its autorotational axis and the missile-target direction; the optical target position detecting means comprising an optical modulator formed of a plane support provided, radially from a point of origin, with a succession of opaque sectors and transparent sectors arranged in alternate sequence, the optical modulator being disposed in the image plane of an objective lens which projects the target image on to the image plane, and, a photoelectric cell located downstream of the optical modulator for receiving light pulses generated by a relative displacement between the target and the optical modulator, the photoelectric cell converting the light pulses into electric signals which are transmitted to a frequency discriminator producing an output voltage which is a function of the frequency of the pulses, thereby a function of the angular deviation of the target with respect to a reference direction constituted by the optical axis of the optical target position detecting means, the voltage actuating, the control signal producing means; the relative displacement between the optical modulator and the target image being produced by the autorotational movement of the missile.

Automatic missile guidance system

Abstract: The automatic missile guidance system comprises a sight with which a gunner establishes a line-of-sight from the gun position to the target. When the missile is launched, a source of pulsating, radiant energy on the rear of the missile is detected by a guidance unit at the sight. The guidance unit produces steering commands related to the deviation of the missile from the line-of-sight. Means interconnecting the guidance unit and the missile transmits the guidance signals to the missile to direct it along the line-of-sight. This guidance unit to missile connection may be wires which unreel from the missile as it proceeds towards its target.

A design for an experimental route guidance system

Abstract: THIS PAPER DESCRIBES AN EXPERIMENTAL ROUTE GUIDANCE SYSTEM (ERGS) DESIGNED BY GENERAL MOTORS CORPORATION UNDER CONTRACT TO THE FEDERAL HIGHWAY ADMINISTRATION, BUREAU OF PUBLIC ROADS. AN ELECTRONIC SYSTEM WHICH WOULD AUTOMATICALLY PROVIDE DRIVERS WITH ROUTING INSTRUCTIONS AT DECISION POINTS IN THE ROAD NETWORK ALONG THE WAY TO THEIR RESPECTIVE DESTINATIONS WAS DEVELOPED. SYSTEM HARDWARE CONSISTS OF BOTH MOBILE AND FIXED ELEMENTS, WHICH AUTOMATICALLY ESTABLISHED TWO-WAY DIGITAL COMMUNICATION BETWEEN MOVING VEHICLES AND ANTENNAS EMBEDDED IN THE ROADWAY. THE SYSTEM IS DESTINATION ORIENTED. AT THE BEGINNING OF HIS TRIP, THE DRIVER ENTERS A CODE WORD REPRESENTING THE ADDRESS OF HIS DESTINATION INTO THE UNIT IN HIS CAR. AS HIS VEHICLE APPROACHES EACH INSTRUMENTED INTERSECTION, THE DESTINATION CODE IS TRANSMITTED TO THE ROADSIDE EQUIPMENT, WHERE IT IS DECODED IN ACCORDANCE WITH A STORED PROGRAM. AN APPROPRIATE MANEUVER INSTRUCTION IS CALCULATED, RETURNED TO THE VEHICLE, AND DISPLAYED TO THE DRIVER IN THE LENGTH OF TIME NECESSARY FOR THE VEHICLE TO TRAVEL A DISTANCE OF APPROXIMATELY FIVE FEET AT INTERSTATE HIGHWAY DRIVING SPEEDS. / AUTHOR/

A Landing Approach Guidance Scheme for Unpowered Lifting Vehicles

Abstract: Subsonic glide landing approach guidance for unpowered lifting vehicles, using perturbation feedback and approximation of heading and position coordinates

Studies in the Methodology of Weapons Systems Effectiveness Analysis - Using the Techniques of Simulation, Optimization and Statistics. Phase II. Volume 3. Effects of Parameter Variations on the Capability of a Proportional Navigation Missile Against an Optimally Evading Target in the Horizontal Plane

Abstract: : The problem considered is a two-dimensional, constant velocity, point model of a target in an encounter with a proportional navigation pursuer. The horizontal plane is chosen so that the effects of gravity may be neglected. Constraints on the turning rate and time delays in both the pursuer's and target's guidance system are included. The sensitivity of the miss distance to variations in the parameters associated with pursuer and evader is presented.

Evaluation of strapdown guidance systems on interplanetary missions.

Abstract: Evaluation method for strapdown spacecraft guidance systems on automated interplanetary missions, using cost and system performance efficiency probability model

Gyroscopic devices of ballistic missiles

Abstract: : This book is intended for people interested in problems of rocket and missile guidance The principal types of gyro-devices for guiding modern ballistic rockets are discussed Data is presented on structural plans of guidance systems, their specific parts, and their functions Much attention has been paid to physical principles of operating gyro-devices, factors affecting their accuracy, and hydrostabilizers as the principal master-measuring devices of modern rockets The book is based on open Soviet and Western materials (Author)

Electronic terminal guidance for all-weather vtol operations

Abstract: The requirement for all-weather, VTOL terminal guidance is established. The recommendation for a first-generation, all-weather terminal landing system for the 1970's is presented. The recommendation includes some aircraft characteristics as well as a combination of airborne and ground-based electronics which includes an autopilot with force stick steering, a self-contained radar guidance system and a microwave type of ILS/DME cooperative guidance system. The recommendation also includes terminal-based, fog dispersal equipment and a definition of visibility minimums. The system gives the pilot essentially “zero-zero” guidance capability. A self-contained, perspective approach radar is described and results given. Developmental obstacles to all-weather landing capability are listed including: long lead times historically related to the multitudinous agencies involved in cooperative electronic systems (not necessarily self-contained), the meaning of redundancy, the role of pilot and co-pilot, etc. Many references are included for more detailed examinations.