Showing papers on "Guidance system published in 1968"

Vehicle road guidance system

Abstract: A vehicle road guidance system in which two guide conductors are provided along a road and the distance between them is monitored by the vehicle to control the steering mechanism of the vehicle.

Missile guidance system using an injection laser active missile seeker

Abstract: A missile guidance system utilizing an integrated active missile infrared eker including an injection laser transmitter, a semiconductor detector and a conical scanning acquisition and guidance system.

Optical range resolution system

Abstract: Disclosed is improved sensor apparatus for guidance systems, and the sensor apparatus includes means for receiving light reflected from a target and for processing this light to provide steering signals to the missile guidance and control mechanism; more specifically, the sensor apparatus includes means for receiving a single pulse of light reflected from the target and for forming a two-dimensional image therefrom, quantizing the data from the image, and re-forming the quantized data into a straight-line image from which a time-dependent signal is generated to be input to the missile control mechanism.

Optimal Terminal Guidance of an Air-to-Surface Missile

Abstract: An optimal guidance law for the linearized equations of an air-to-surf ace missile is constructed. This guidance law is based on information supplied from an inertial platform and a noisy TV tracker. The mean square miss distances of missiles respectively using the optimal guidance law, pursuit guidance, or proportional guidance are compared. This comparison is made for typical initial position and velocity errors, and a variety of system parameter variations, and nominal terminal trajectories. The mean-square miss distance in each case was obtained from a computer solution of the matrix Riccati equation for the covariance matrix of the state vector of the linearized missile equations. I. Introduction T HE aim of this paper is to study the practicality of using linear stochastic optimum control theory to design a guidance system for the terminal guidance of an air-to-surface missile (ASM). The design of the best possible guidance system for a missile is an intriguing objective. The design of an exactly optimum guidance system for a missile governed by nonlinear equations with random system and sensor errors is beyond the scope of presently existing theory. However approximation of the nonlinear missile equations by linearized equations and the design of an optimal guidance system for the linearized missile equations offers a possibility for improved performance. In this paper the details of constructing such a guidance system for the terminal guidance of an air-to-surface missile are carried out. The air-to-surface missile is assumed to be equipped with both an inertial platform and a television (TV) tracking system. Random system errors due to winds and random sensor errors in the tracker are assumed to be present. A blind zone near the target in which the tracker cannot see the target due to the target filling the entire TV screen is considered. The performance of the linearized optimal guidance system, pursuit guidance, and proportional guidance are compared by computing for each system the mean square position deviation perpendicular to a given nominal trajectory at the time this trajectory hits the target.

Method of monopulse angle gating for computer

Abstract: A monopulse angle-gated guidance system consisting of a radio frequency receiver having an antenna, feed assembly and detectors, and a guidance computer including the basic computer and multiple target processing and scanning circuitry. A monopulse angle-gated guidance system for providing pursuitnavigation information to the servo system of an associated missile and provides a direction-finding information of radiating sources to a pilot.

Vehicular guidance system with collision prevention

Abstract: A vehicular guidance system for self-propelled vehicles moving along a track includes a series of elongate conductors following one another in overlapping relationship, each conductor having a leading portion on one side and a trailing portion on the other side of the track for cooperation with a high frequency transmitter and a corresponding receiver, respectively, aboard each vehicle. With the length of each conductor portion exceeding that of a vehicle, signals picked up by the receiver of one vehicle indicate the presence of another vehicle immediately ahead.

Gyro reliability in the Apollo Guidance, Navigation, and Control system.

Abstract: Apollo gyro reliability covering guidance, navigation and control systems, stressing failure mode prediction

Guidance and Control for Atmospheric Entry

Abstract: Previous chapters in this book provide the foundation of physics and technology required for the development of spacecraft systems for atmospheric entry. Hardware systems design involves assembling the technological blocks in such a way as to satisfy mission requirements while at the same time not violating critical constraints on size, weight, reliability, power, environmental provisions, and performance. It is clear that guidance and control are important elements in any recentry system, whether it be manned or unmanned. This chapter examines the concepts and hardware for guidance and control of the Mercury, Gemini, and Apollo spacecraft. The reentry technology for manned spacecraft systems has matured very greatly in the 1960’s.

Terminal guidance for soft and accurate lunar landing for unmanned spacecraft.

Abstract: Soft, precise landings of unmanned lunar spacecraft may be needed for logistic support of future manned missions. The terminal descent guidance concept proposed in this paper utilizes proportional navigation plus logarithmic deceleration in the initial guided phase of flight and switches at a predetermined range to an unguided gravity turn, thereby achieving a soft landing with vertical attitude at touchdown. Guidance simulation studies have shown this concept to be effective in reducing the target miss distance resulting from dispersions in initial flight conditions caused by uncertainties in retro burnout and errors in instrument measurement and command execution. With the present technology and available spaceflight-proven instruments, this guidance concept can be easily implemented without exceeding practical design limitations. Moreover, it requires no knowledge of the local vertical throughout the terminal phase of flight. A landing accuracy of 500-ft circular error probability is achievable.

Postflight guidance accuracy analysis of Atlas

Abstract: Atlas/Centaur/Surveyor flights guidance accuracy, discussing postflight analysis of injection errors due to hardware, software and propulsion system

An evaluation technique for 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

Analytical calculation of partial derivatives relating lunar and planetary midcourse correction requirements to guidance system injection errors

Abstract: Two body equations of motion for calculating partial derivatives relating lunar and planetary midcourse correction requirements to guidance system injection errors

Simplicity: a virtue in rocket guidance

Abstract: The practice of navigation on ships and aircraft has become progressively simpler in the recent history of our art. In fact, the practitioner, the navigator, is all too often not fully aware of all the basic principles underlying his regularly successful practice of position location. The trend was not always in this direction and, in fact, is a relatively modern phenomenon. Complexity and insistence on an explicit solution during the early 19th century was all out of proportion to the accuracy of the input data. Contrary to the modern long term trend, we have seen the design practice of automatic inertial guidance systems proliferate complexity in an alarming manner during the past 10 years. Therefore, it is in the classical spirit of simplicity which has served us so well, that the following paper is presented. A brief description of several simplifying techniques utilizing analog components as employed in foreign guidance systems is given.