Showing papers on "Guidance system published in 1976"

Missile guidance system utilizing polarization

Abstract: A missile guidance system in which a projectile or missile is fired toward predetermined target with the missile being tracked on its flight toward the target by radar, processing the radar information in a computer apparatus and finally computing a new trajectory from the missile to the target and transmitting correction signals to a correction device on the missile including thrusters on the missile to cause the trajectory of the missile to be changed to the newly computed trajectory for the missile This system corrects the trajectory of the missile while in flight by recomputing a trajectory from the missile to the predetermined target and making appropriate corrections each time Thisenables the missile to only contain radar reflecting means, and correction detection and control means on the missile rather than having gyro and other type devices on board the missile which take up a considerable amount of space and weight

Guidance system for missiles

Abstract: A missile guidance system is provided in which a sensor is pivotally mounted on the missile in a gimbal system having two degrees of freedom. The sensor is controlled during flight in such a manner that the axis of the sensor is aligned in a direction determined by the acceleration of the missile, and the sensor locates the target and determines the angle between the direction of the sensor axis and the direction of the target. Guidance information is derived from this angle for directing the missile toward the target. Compensation for gravity may be provided by means of a spring suitably arranged in the gimbal system. The sensor system may be either active or passive and may be responsive to any desired type of signal from the target.

Dual mode guidance system

Abstract: A dual mode missile guidance system employing a passive anti-radiation ser for midcourse guidance and an alternate sensor for terminal guidance. A broadband, body mounted conformal antenna comprises the midcourse sensor, and the alternate sensor is mounted on a stabilized platform within the missile radome. Detected video guidance signals from the midcourse sensor are video processed and utilized to adjust the system phase shifters for null tracking as well as for driving the stabilized platform to keep the alternate sensor directed at the target. Upon the occurrence of a predetermined condition, a handover switch connects the detected video guidance signals provided by the alternate guidance sensor processor for video processing and for control of the stabilized platform. Auto pilot signals are derived from the rate gyros mounted on the stabilized platform.

Simplified high accuracy guidance system

Abstract: A simplified guidance system for air-to-air missiles where the pilot adjusts his helmet sight to compensate for missile errors and this information is fed to a computer which computes correction data from error information, aircraft position information and missile position information, correction data is then sent via a radio link to the missile control system which changes the flight path accordingly.

Monitor for two frequency localizer guidance system

Abstract: A monitoring arrangement for use in a two frequency localizer guidance system using a single antenna array is disclosed. This monitoring arrangement is designed to provide monitoring signals equivalent to those that would be provided by monitors located at a distant point on the course and at a distant point located at a selected angle off the course. Additional monitoring for the clearance transmitter signals and means for determining the existence of major faults such as short circuits or open circuited lines or major injuries to the equipment.

A general interactive guidance for information retrieval and processing systems

Abstract: A general application guidance system -GAGS- was developed to support the problem solving enduser in applying DP-facilities without being a DP-professional. It has the following four main features:1. Dialogue supported methods dictionary: guides the user from a given application problem to the adequate solution method or program.2. Dialogue supported data dictionary: gives syntactic and semantic information about the data available in data administration systems such as data base systems.3. Dialogue supported execution facility: offers a system triggered execution of programs found with the help of the methods dictionary in order to process data identified by means of the data dictionary.4. Dialogue supported system guidance: enables the unexperienced user to work with software systems without being a DP-expert.The basic information structure for the interactive guidance which is the common overall feature of the four facilities listed above, is the information network. It is generated by breaking down the knowledge about the application area in question into information elements (network nodes) which are interconnected (network arcs).

Direct statistical analysis of missile guidance systems via CADET (trade name)

Abstract: : The Covariance Analysis DEscribing Function Technique (CADET) -- a technique conceived at TASC for the efficient direct statistical analysis of nonlinear systems with random inputs -- is applied to the study of a complicated, highly nonlinear model for a tactical missile homing guidance system Numerous parameter sensitivity studies are performed, with selected cases verified by the monte carlo method The validity of the assumptions underlying the CADET theory is investigated and the impact of possible errors in these assumptions on the accuracy of CADET is assessed In every realistic situation studied, CADET provides accurate missile performance projections with a small fraction of the computer time required for a comparably reliable monte carlo analysis

Apollo experience report guidance and control systems: Primary guidance, navigation, and control system development

Abstract: The primary guidance, navigation, and control systems for both the lunar module and the command module are described. Development of the Apollo primary guidance systems is traced from adaptation of the Polaris Mark II system through evolution from Block I to Block II configurations; the discussion includes design concepts used, test and qualification programs performed, and major problems encountered. The major subsystems (inertial, computer, and optical) are covered. Separate sections on the inertial components (gyroscopes and accelerometers) are presented because these components represent a major contribution to the success of the primary guidance, navigation, and control system.

Effects of modifications to the space shuttle entry guidance and control systems

Abstract: A nonlinear six degree of freedom entry simulation study was conducted to identify space shuttle guidance and control system software modifications which reduce the control system sensitivity to the guidance system sampling frequency. Several modifications which eliminated the control system sensitivity and associated control limit cycling were examined. The result of the modifications was a reduction in required reaction control system fuel.

A wind tunnel investigation of impulse effects on the motion of an impulse correction guidance missile

Abstract: : Wind tunnel tests were conducted for the Air Force Armament Laboratory to obtain experimental data at Mach number 3 on an impulse correction guidance system. The guidance system is based on the principle of impulse correction. The purpose of the test program was to determine if the interaction of the impulse explosion with the supersonic airflow caused an effect on the model motion. The small-amplitude free-oscillation technique was used to obtain data on a 0.5 scale model at angles of attack from 1 to 4.4 deg at Reynolds numbers, based on model length, of 12.2 x 100,000 and 23.1 x 100,000. The explosion which produced the impulse affected the model flow field. However, this perturbed flow field did not produce any significant effects on the model motion, apparently because of the short action time involved.

Performance limits of automatic steering controllers

Abstract: This paper deals with lateral guidance and indicates that improved design of lateral guidance systems can improve ride comfort, permit greater tolerance in guideway construction, and thereby reduce costs. The purpose of the study reported here is to determine the performance limits of steering controllers for rubber-tired vehicles operating on guideways where the reference path is characterized by a stochastic roughness, instead of being perfectly smooth.

Morphological Thinking on the Synthesis of a Beam-Riding Missile System

Abstract: In this paper, the concept of morphological approach to a general system design problem, first evolved by Zwicky, has been applied to the case of a beam-riding missile system. In a detailed study of the morphological box for the system, such sub-system combinations as are feasible but not conventionally employed are brought under close scrutiny to yield dimensions in which conventional beam-rider system engineering can expand to include the technology of today. The particular case of the combination of various types of terminal guidance system with the principal beam-riding guidance system has been studied in some depth and detail.