Showing papers on "Guidance system published in 1977"

Shipboard point defense system and elements therefor

Abstract: A combined defense and navigational system on a naval vessel is disclosed. The disclosed system includes a track-while-scan pulse radar which is controlled to provide either navigational information or tracking information on selected targets. Additionally, the disclosed system includes a plurality of guided missiles, each of which may be vertically launched and directed toward intercept of a selected target either by commands from the track-while-scan radar or from an active guidance system in each such missile.

History of Inertial Navigation

Abstract: the guidance system used by the Germans in 1942 in the V–2 missile can be considered to be the first use of inertial navigation. It is true that Foucault defined the gyroscope in 1852 and that Schuler developed the gyrocompass in 1908, but the former device was only a measuring instrument and the latter, although of inertial quality, was only a partial inertial system. The Sperry flight instruments of the late 1920's and early 1930's were attitude–indicating not velocity or position-indicating devices. Earnest development of inertial navigation systems began in the United States in the late 1940's and early 1950's by the M.I.T. Instrumentation Laboratory, Northrop and Autonetics under Air Force sponsorship. This work led to the inertial guidance systems for ballistic missiles—both land and ship launched. The 1960's brought the Space Age and the advance of inertial guidance in Apollo. During this time inertial guidance systems also found their way into military and then commercial airplanes. Behind the system development was the simultaneous and necessary development of theory, analysis, components, subsystems and testing. The author, whose professional career has been simultaneous with the growth of inertial navigation, draws on his personal experiences in the field of direct association with many of the people and events involved.

Guidance systems for mobile craft

Abstract: A missile is guided onto a target by means of a laser beam, so that the missile can determine and correct its displacement from the boresight of the laser beam. This leads to greater accuracy of guidance, and avoids the need for very narrow beams which could be lost by the missile.

Shipboard point defense system and elements therefor

Abstract: A combined defense and navigational system on a naval vessel is disclosed. The disclosed system includes a track-while-scan pulse radar which is controlled to provide either navigational information or tracking information on selected targets. Additionally, the disclosed system includes a plurality of guided missiles, each of which may be vertically launched and directed toward intercept of a selected target either by commands from the track-while-scan radar or from an active guidance system in each such missile.

Shipboard point defense system and elements therefor

Abstract: A combined defense and navigational system on a naval Vessel is disclosed. The disclosed system includes a track-while-scan pulse radar which is controlled to provide either navigational information or tracking information on selected targets. Additionally, the disclosed system includes a plurality of guided missiles, each of which may be vertically launched and directed toward intercept of a selected target either by commands from the track-while-scan radar or from an active guidance system in each such missile.

Hybrid terminal assist landing

Abstract: Control of multiple remotely piloted vehicles provided through a system ced the Hybrid Terminal Assist Landing. This system, also referred to as HYTAL, is composed of two principal subsystems, an RF approach control subsystem and a precise optical landing point homing and ranging subsystem. By using a hybrid combination of RF and optical sensors, the remotely piloted vehicle, RPV or other aircraft approach control and recovery guidance system can be optimized with respect to performance complexity, size, weight and cost.

Shipboard point defense system and elements therefor

Abstract: A combined defense and navigational system on a naval vessel is disclosed. The disclosed system includes a track-while-scan pulse radar which is controlled to provide either navigational information or tracking information on selected targets. Additionally, the disclosed system includes a plurality of guided missiles, each of which may be vertically launched and directed toward intercept of a selected target either by commands from the track-while-scan radar or from an active guidance system in each such missile.

Shipboard point defense system and elements therefor

Abstract: A combined defense and navigational system on a naval vessel is disclosed The disclosed system includes a track-while-scan pulse radar which is controlled to provide either navigational information or tracking information on selected targets Additionally, the disclosed system includes a plurality of guided missiles, each of which may be vertically launched and directed toward intercept of a selected target either by commands from the track-while-scan radar or from an active guidance system in each such missile The invention herein described was made in the course of or under a contract or subcontract thereunder, with the Department of Defense

Direction finding device and guidance system

Abstract: A direction finding device employs a magnetic field sensor utilizing a vibrating magnetic reed switch with adjustable magnetic bias to vary the sensitivity or dead band. By sensing magnetic North, it indicates audibly, visually or by nerve stimulus any departure from a preset course. When attached to a moving object or person it serves as a warning or guidance system.

Missile roll position processor

Abstract: A weapon system using a line of sight guidance system is provided with a missile containing two symmetrically located optical receivers. Information contained in a beam into which a missile is launched is used by the two receivers and associated processor means to derive roll position for the missile. Because the roll signal is derived electronically, mechanical means for determining roll position of the missile in the form of a conventional roll gyro, for example, may be eliminated. Elimination of the mechanical roll gyro from the missile permits much higher launch accelerations than are realistically feasible with missile control systems employing mechanically derived roll data. A processor located in the missile receives its signals from the pair of optical receivers. The processor uses the data from the first receiver to derive the position error of the missile relative to beam center. The data of the second receiver is used by the processor, along with a phase angle reference from the first receiver signal to develop a signal representation of the missile roll angle. The signal representation is further processed, when used with missile control systems requiring the roll reference signal in the form of a linear voltage with missile roll angle, to develop a missile roll angle reference in the form of two ramp voltages, each representing 360° of missile roll angle and being separated in phase by 180°.

A discrete adaptive guidance system for a roving vehicle

Abstract: An adaptive guidance technique which provides a self-correcting path following capability in an environment sensitive semi-autonomous roving robot is described. A real-time maneuver planning function performs tradeoffs between speed, magnitude of expected deviations and accelerations to best satisfy the design goals of vehicle safety and reliability, subsystem autonomy, performance accuracy and operational efficiency. The appropriate combination of maneuver parameters is selected through an iterative process using knowledge of vehicle performance characteristics, environmental model updates and vehicle state.

Route guidance system for car - continuously compares programmed destination with memory of coded signals from road junction transmitters

Abstract: A route guidance system is for either pedestrian use in large city complexes, or for use in motor vehicles. It enables automatic display of location during the journey in relation to a pre-programmed destination. An information input facility (1) enables a user to enter his start point and ultimate destination in coded form. A radio receiver (5) picks-up coded information from position detectors located a specific road junctions. This information is used to address a memory (2) containing positional details. The memory output is compared (3) with the input and instructions of how to proceed displayed (4) within the drivers field of vision.

Fully automated urban traffic system

Abstract: The replacement of the driver with an automatic system which could perform the functions of guiding and routing a vehicle with a human's capability of responding to changing traffic demands was discussed The problem was divided into four technological areas; guidance, routing, computing, and communications It was determined that the latter three areas being developed independent of any need for fully automated urban traffic A guidance system that would meet system requirements was not being developed but was technically feasible

Balanceeswitching mechanism for guidance system of dual mode vehicle

Abstract: PURPOSE:To make it possible to take in and out a guidance system including a guidance wheel always at an equal distance with respect to a center of vehicle, in such a way that at least a pair of springs are arranged between an arm supporting an axle and the axle

Development of the German A-4 guidance and control system, 1939 - 1945: A memoir

Abstract: The development by 1943 of a fully inertial navigational system for the German A-4 (V-2) missile is detailed. This flight control system used a triple-axis stabilized platform with two longitudinal accelerometers and one lateral accelerometer.

Simulation of the flight of a short range air defense system rocket before radar acquisition

Abstract: : This report deals with the problem of digitally simulating the motion of a Short Range Air Defense System (SHORADS) rocket during launch and until the rocket has been acquired by a launcher-fixed tracking radar. Physical and mathematical models of the launcher, the rocket per se and its environment, the rocket's control system and the pre-radar-acquisition guidance system are presented. The pre-acquisition guidance sensor is a dual field of view infrared angle sensor. The rocket is of the folding-wing, tube-launched, boost-sustain type and rolls at an essentially constant rate. Control torques are generated by deflecting the thrust of the solid-propellant, sustainer rocket motor and are available about a single rocket-fixed axis. The models for the launcher and rocket include the anomalistic effects of tipoff, launcher slew rate, rocket dynamic unbalance and thrust misalignment, aerodynamic forces and moments, jet damping, variable mass, and moments of inertia of the rocket and winds. Two computer codes - one for the launch phase and one for the post-launch, controlled phase - are also described and typical simulation results are presented and discussed. The rocket simulated performs well when various combinations of anomalies are present, but large slew rates of the launcher result in failure of the rocket to enter the field of view of the infrared sensor, if it is launched from a 'lagging' tube.

An Evaluation Method of Route Guidance System for Automobile Traffic

Abstract: This paper describes a method for evaluating the effectiveness of the route guidance system, which provides a driver with individual information to accomplish a trip under such objectives as the travel time saving, the fuel saving, the reduced air pollution and the reduced traffic accident etc.. In this paper the travel time saving is chosen as an evaluation criterion of this system. The travel time indicates the time required from a driver's specific origin (O) to his specific destination (D). Multiple routes may be chosen with each specific -D , owing to his route choice criteria and to his trial and error. The route choice probability is defined, based on a traffic study of a driver's comprehension of road configuration. On the other hand, the travel time along the selected route is affected by the vehicular type, the traffic flow, the traffic regulation, the traffic signal and the weather etc.. In this paper the travel time is defined in terms of a conditional probability density function. The characteristics of the function are examined by a traffic study of travel time using an improved license matching technique. The probability density function of the travel time in the case of the specific O-D is composed of the route choice probability and the conditional probability density functions, mentioned above. Comparing the probability density function of a guided vehicle with that of a non-guided vehicle, a mathematical formula to calculate the amount of travel time saving is derived.

On the vehicle development of the dual mode bus system

Abstract: Vehicles for the Dial Mode Bus System and a system which can be technically put into practical application has been developed. This paper introduces an outline of the system and vehicle. As regards the operational stability of the lateral guidance system, analyses, computations using a simulation model, and experiments using test cars were conducted on two types of guidance system, a linked type, which is to link mechanically the guidance wheel with the steered wheel, and a non-linked type. /GMRL/