Showing papers on "Guidance system published in 1975"

Method and apparatus for guiding a jet aircraft in a noise-abated post-takeoff climb

Abstract: A pilot guidance system that computes and displays pitch and speed steering commands is automatically operated during the post-takeoff climb (at specified times clocked from the start of the takeoff run), to present commands that assist the pilot in cutting (and later in restoring) thrust for a predetermined interval to reduce engine noise, and in guiding the aircraft in a safe, gentle climb over the proximate community. The specified times (unique for each model of aircraft, airport, runway and departure flight path), synchronize the thrust cutback interval with the boundaries of the community in line with chosen departure path.

Missile tracking and guidance system

Abstract: A missile guidance system is disclosed which utilizes one optical system for visually tracking a target and directing a missile thereto by means of infrared (IR) energy emitted from the missile. The optical system includes a single objective lens for receiving both visible and infrared energy and directing those energies on a first prism. The first prism separates the visible energy from the infrared energy and directs the visible energy to an eyepiece for a viewer. A first image of infrared energy is directed to a first infrared sensor by a retrodirective reflector. A second image of infrared energy is directed at a second sensor by a rotating prism. The output signals from the first and second sensors are provided to missile control circuitry which compares these signals with reference signals and thereby generates command signals for steering the missile to the target.

Self-aligning roll out guidance system

Abstract: Guidance along the runway centerline when visibility conditions do not permit adequate visual cues for manual control are provided utilizing lateral acceleration and bank angle information. An aircraft type airborne vehicle can touchdown with a crab angle in the presence of a crosswind and the present system provides the proper command to decrab the aircraft and return the aircraft to the centerline.

Static self-contained laser seeker system for active missile guidance

Abstract: Four pulse-repetition-frequency coded laser diode arrays emit four beams in quadrature relationship having a central optical axis coinciding with the missile axis. The returned reflected energy from a target impinges upon an optically centered holographic quadrant selector detection system which provides quadrature output signals. These quadrature output signals are passed through respective pulse-repetition-frequency discriminators corresponding to the quadrature prf coded transmitted beams. The outputs from the discriminators are processed through a null comparison circuit to provide output signals for actuating the servo guidance system of the missile to center the optical axis, which is also the missile axis, on the target so that the missile continuously seeks and eventually flies into the target.

Bolt-on guidance system for lift truck

Abstract: An automatic guidance device for a self-powered cargo-moving vehicle is bolted directly over the steering column of the vehicle and is operated by a vehicle-borne sensor which follows a magnetic wire path, the guidance system having an automatic, sensor-directed mode, a manually operated power steering mode, and a manual override mode in which the guidance device is effectively disconnected and steering is undertaken by a direct mechanical linkage with the vehicle steering column.

Guidance system for lift truck

Abstract: An automatic guidance device for a self-powered cargo-moving vehicle is operated by a vehicle-borne sensor which follows a buried, energized wire path and includes a circuit which first switches on the automatic guidance circuit when the vehicle is heading away from the wire after it has either passed over the wire or has closely approached the wire. At all other times the vehicle is power steered through the guidance circuit under the operator's control.

Self defense missile

Abstract: A self defense missile, for bombers in particular, wherein the slower flying bomber is being overtaken by a faster flying hostile aircraft in the rear quadrant. The self defense missile is an unpowered missile having wings to provide lift, a guidance system to control the direction of flight of the missile, and a homing detection in the tail of the missile to cause the missile to fly into the path of the hostile aircraft. In operation, the self defense missile is launched parallel to the direction of flight of the bomber. As the missile slows down, the wings give it lift to keep it at the appropriate altitude. The homing detector in the tail guides on the approaching hostile aircraft and the guidance system keeps the self defense missile on a collision course. This action by the self defense missile and the increasing speed of closing caused by the slowing of the missile, forces the hostile aircraft to break off pursuit to take evasive action of face destruction upon intercept when the self defense missile is overtaken.

Time-controlled descent guidance in uncertain winds

Abstract: A procedure has been developed for constructing a statistical model of the altitude-dependent mean wind profile from the historical record of wind measurements at particular locations. The model is constructed by fitting a Markov process, with altitude as the stage variable, to the historical wind data. The wind model, together with the aircraft dynamics and the error characteristics of the navigation system, are incorporated in the design of a state estimator, which gives the minimum variance estimate of the aircraft state and the wind vector. The state and wind estimates are used as inputs to a linear feedback law for guiding the aircraft along the nominal trajectory. An example design of a time-constrained (4D RNAV) descent guidance system is presented, showing tracking accuracy, control activity, and probability of arrival time with and without the wind estimator.

Software engineering of a navigation and guidance system for commercial aircraft

Abstract: The avionics experimental configuration of the considered system is briefly reviewed, taking into account the concept of an advanced air traffic management system, flight critical and noncritical functions, and display system characteristics. Cockpit displays and the navigation computer are examined. Attention is given to the functions performed in the navigation computer, major programs in the navigation computer, and questions of software development.

Four-dimensional guidance algorithms for aircraft in an air traffic control environment

Abstract: Theoretical development and computer implementation of three guidance algorithms are presented. From a small set of input parameters the algorithms generate the ground track, altitude profile, and speed profile required to implement an experimental 4-D guidance system. Given a sequence of waypoints that define a nominal flight path, the first algorithm generates a realistic, flyable ground track consisting of a sequence of straight line segments and circular arcs. Each circular turn is constrained by the minimum turning radius of the aircraft. The ground track and the specified waypoint altitudes are used as inputs to the second algorithm which generates the altitude profile. The altitude profile consists of piecewise constant flight path angle segments, each segment lying within specified upper and lower bounds. The third algorithm generates a feasible speed profile subject to constraints on the rate of change in speed, permissible speed ranges, and effects of wind. Flight path parameters are then combined into a chronological sequence to form the 4-D guidance vectors. These vectors can be used to drive the autopilot/autothrottle of the aircraft so that a 4-D flight path could be tracked completely automatically; or these vectors may be used to drive the flight director and other cockpit displays, thereby enabling the pilot to track a 4-D flight path manually.

Apollo experience report guidance and control systems: Lunar module abort guidance system

Abstract: The history of a unique development program that produced an operational fixed guidance system of inertial quality is presented. Each phase of development, beginning with requirement definition and concluding with qualification and testing, is addressed, and developmental problems are emphasized. Software generation and mission operations are described, and specifications for the inertial reference unit are included, as are flight performance results. Significant program observations are noted.

Experimental and simulation study results of an Adaptive Video Guidance System /AVGS/

Abstract: Studies relating to stellar-body exploration programs have pointed out the need for an adaptive guidance scheme capable of providing automatic real-time guidance and site selection capability. For the case of a planetary lander, without such guidance, targeting is limited to what are believed to be generally benign areas in order to ensure a reasonable landing-success probability. Typically, the Mars Viking Lander will be jeopardized by obstacles exceeding 22 centimers in diameter. The benefits of on-board navigation and real-time selection of a landing site and obstacle avoidance have been demonstrated by the Apollo lunar landings, in which man performed the surface sensing and steering functions. Therefore, an Adaptive Video Guidance System (AVGS) has been developed, bread-boarded, and flown on a six-degree-of-freedom simulator.

Analysis of navigation and guidance requirements for commercial VTOL operations

Abstract: The paper presents some results of a program undertaken to define navigation and guidance requirements for commercial VTOL operations in the takeoff, cruise, terminal and landing phases of flight in weather conditions up to and including Category III. Quantitative navigation requirements are given for the parameters range, coverage, operation near obstacles, horizontal accuracy, multiple landing aircraft, multiple pad requirements, inertial/radio-inertial requirements, reliability/redundancy, update rate, and data link requirements in all flight phases. A multi-configuration straw-man navigation and guidance system for commercial VTOL operations is presented. Operation of the system is keyed to a fully automatic approach for navigation, guidance and control, with pilot as monitor-manager. The system is a hybrid navigator using a relatively low-cost inertial sensor with DME updates and MLS in the approach/departure phases.

Laser beam guidance system for foggy conditions - is effective for vehicles ships or aircraft using fixed sources and reflectors

Abstract: The coherent light of laser beams, which is emitted in different colours, is used for the guidance system. The condensates of fog causes the light beams to illuminate. Thus, a lateral guidance and limitation are achieved, which represent a practical and secure aid protecting live and limb. A limited number of light sources provide a wide guidance distance. By means of further focussing and diversion at curves and at crossing points of the terrain, the fixing point and similar reference points can be marked, also the direction is indicated. This applies also to the movement of ships and to air traffic.

Performance of the MADGE Aircraft Guidance System

Abstract: MADGE (Microwave Aircraft Digital Guidance Equipment) is a portable equipment which assists the landing of all types of aircraft at a variety of sites. It contains a digital data link operating at 5 GHz. Distance is derived in the air by measuring go-and-return time; angles are measured on the ground by passive interferometer receivers. Flight results relating to coverage and accuracy are presented.

Measurement of missile position and attitude by lasers

Abstract: : This report presents a method for measuring the position and attitude of spinning rockets and missiles by the use of multiple laser trackers. While the immediate application of this system is in range instrumentation, it has potential as a guidance system - particularly for a guidance system using midcourse or terminal correction. The main advantage of a laser tracking system over existing camera tracking systems is that it would permit near real time reduction of range test data. The program objective is to obtain rocket position and attitude for determination of vehicle aeroballistic parameters from flight tests. The constraints are as follows: (1) Process real time or near time data; (2) Obtain accuracy equal to or better than currently available; (3) Obtain data regardless of flight abnormalities; (4) Obtain high reliability for data acquisition; (5) Extend testing capability to low ambient light situation including night operation; and (6) Reduce overall cost of data acquisition and reduction.

Development of a unified guidance system for geocentric transfer

Abstract: A method is presented for open loop guidance of a solar electric propulsion spacecraft to geosynchronsus orbit. The method consists of determining the thrust vector profiles on the ground with an optimization computer program, and performing updates based on the difference between the actual trajectory and that predicted with a precision simulation computer program. The motivation for performing the guidance analysis during the mission planning phase is discussed, and a spacecraft design option that employs attitude orientation constraints is presented. The improvements required in both the optimization program and simulation program are set forth, together with the efforts to integrate the programs into the ground support software for the guidance system.

Switch guidance system for remote controlled units in buildings - used for control of blinds, shutters and other units in large buildings

Abstract: The guidance electrodes of the switch cells are phased through a number of cutouts. These cutouts are manually or automatically reinforced and can therefore motivate the guidance signals. At the same time a lightmeter controls the maximum or minimum light values permitted and automatically cuts into the guidance system when required. The control circuit includes an amplifier associated with a blocking oscillator. An LC generation in also included together with an impulse repeater.