Showing papers on "Guidance system published in 1993"

The modelling of dynamic route guidance systems

Abstract: In attempting to simulate the operation of a dynamic route guidance system, the modelling task is concerned both with the operation of the control system and with the implications this has for modelling driver behaviour (whether or not the driver is receiving information from the controller) and network conditions. The aim of this paper is to provide an overview of the modelling issues that need to be considered when addressing such a problem, and that have been identified by various authors in reports on experimental/survey work and in discussion papers. We achieve this by presenting a structured survey of recent research into dynamic route guidance and highlighting issues that are critical to its effectiveness. It is our belief that the development of a model that adequately represents the performance of a dynamic route guidance system is of the utmost importance to the success of the system. It will not only provide a means for evaluating the potential benefits, but should also provide an essential insight into the most appropriate means for its implementation and improve our understanding of transportation networks.

Further on-the-road tests of driver interfaces : examination of a route guidance system and a car phone

Abstract: This report describes driver performance and behavior when using an in- vehicle route guidance system, and a manually dialed car phone. It also provides normative data for driving without use of an in- vehicle information system. Description of the route guidance system and drivers' preferences, are also included.

Navigation system for guiding vehicle orally

Abstract: A vehicle route guidance system includes a map information storage section 10 which has a road type storage section 10a for storing various types of roads such as toll roads, express highways and motorways. A route guidance control section 26 reads out map information including road type information and route information. A road type change point detecting section 26a detects a road type change point. The route guidance control section 26 causes a display 28 and a voice controller 30 to perform the route guidance when a vehicle approaches a point a given distance short of the road type change point. The voice controller 30 responds to the instruction from the route guidance control section 26 to announce the route guidance for informing the driver of the entry to a toll road, express highway or motorway.

Application of the active-pixel-sensor concept to guidance and navigation

Abstract: Charge-coupled devices (CCDs) have been used extensively in the past in star trackers and fine guidance systems. A new technology, the active pixel sensor, is a possible successor to CCDs. This technology potentially features the same sensitivity and performance of the CCD with additional improvements. These improvements include random access capability, easy window-of- interest readout, non-destructive readout for signal-to-noise improvement, high radiation tolerance, simplified clocking voltages, and easy integration with other on-chip signal processing circuitry. The state-of-the-art of this emerging technology and its potential application to guidance and navigation systems is discussed.

Generalized guidance law for collision courses

Abstract: A new generalized guidance law for collision courses is presented. When the missile and target axial accelerations or decelerations are constant, there exists a rectilinear collision course. The guidance law presented, which is called the true guidance law, gives theoretical lateral acceleration commands to guide the missile on a collision course. However, since it is very difficult to realize the true guidance law on most existing tactical missiles, this paper shows a method for simply implementing the guidance law, which is called the simplified guidance law. The small perturbation equation of the true guidance law shows that the definition of an effective navigation constant is the same expression as that in the case of conventional proportional navigation. The performance of the two guidance laws presented is compared with that of proportional navigation using simulation studies of a simple model of a short range air-to-air missile. The simulation results show that the guidance laws presented can intercept the target using far smaller lateral acceleration commands than prepared for proportional navigation. The inner launch envelope shows that the guidance laws presented provide an overall performance improvement over proportional navigation.

A comparison of route guidance destination entry methods

Abstract: This paper examined four touchscreen methods for entering a destination into a route guidance system. Different issues were studied, including interface, performance, errors, and levels of difficulties.

Advanced Cruise Missile guidance system description

Abstract: This paper provides a functional description of the navigation and guidance system in the Advanced Cruise Missile (ACM), one of the Air Force's newest stealth missiles. It also discusses some of the areas of improvement over the Air Launched Cruise Missile (ALCM). The Kalman Filter design accommodates velocity updates, including lateral velocities, and a nominal number of position updates from terrain correlation matching (TERCOM) to achieve a high accuracy, long range mission. >

Scatter-rider guidance system for terminal homing seekers

Abstract: The present invention is an initial guidance system for a missile that haso other guidance or inadequate terminal homing guidance to lock onto a target at the time of missile launch. A laser beam projected from the missile launch station is aimed toward the target. Light from the beam is reflected in random directions (scattered) from aerosol particles that are ever present in the atmosphere. This scattered light strikes light detectors that are located on the sides of the missile. When the missile flies off the direction of the target, the amplitudes of impacting light on these detectors are different on different sides of the missile. Guidance controls activated by these amplitude differences cause the missile to veer toward the center of the beam and thus fly in a direction that is more toward the target.

Integrated guidance system and method for providing guidance to a projectile on a trajectory

Abstract: An inertial measurement unit is provided which includes a core inertial measurement unit having accelerometers and gyroscopes aligned along x, y and z axes to provide signals to an onboard computer to determine position of the vehicle upon which they are mounted while in movement. A fourth accelerometer is pivoted perpendicular to the direction of the gravitational field for measuring the gravitational field about the axis upon which it is mounted to provide a reference set of data to an onboard computer prior to movement of the vehicle upon which the system is mounted.

Guidance system for visually and audibly handicapped person

Abstract: PURPOSE:To surely guide a visually and audially handicapped person in a shop, etc., to make the name of a desired article in the shop, etc., confirm by the person, to guide the person to a place where the article is displayed, and to arrange and distribute the desired article. CONSTITUTION:A guidance processing managing device 1 transmits a guidance signal S18 via a computer 8 for guidance control and transmission/reception parts 6a, 6b. The device also receives a guidance request signal S13 transmitted from a portable device 3 via the transmission/reception parts 6a, 6b and handicapped person sensors 5a-5c. The approach (of the visually/audially handicapped person) of the portable device 3 is discriminated from a reception signal by the handicapped person sensors (5a-5c), and approach information is sent out of transmission/reception parts 7a-7c to the computer 8 for guidance control. The computer 8 for guidance control transmits information analyzed based on the reception signal from the transmission/reception parts 7a-7c as the guidance signal S18. The guidance signal S18 is received by the transmission/ reception part 15 of the portable device 3, and a microcomputer 16 informs guidance information to a transporter by operating an annunciator 17.

Flight test development and evaluation of a Kalman filter state estimator for low-altitude flight

Abstract: Flight operations dependent on digitized terrain elevation data for navigational reference or trajectory generation are constrained in minimum flight altitude, due to airborne navigation errors and inaccuracies of the reference terrain elevation data. This limitation is not restrictive in traditional medium-altitude implementations of such databases, such as in unmanned aerial vehicles, missiles, or high-performance, high-speed aircraft. In low-altitude, lower speed terrain hugging helicopter missions, however, such constraints on minimum flight altitudes greatly reduce the effectiveness of their missions and diminish the benefits of employing terrain elevation maps. A Kalman filter state estimator has been developed which blends airborne navigation, stored terrain elevation data, and a radar altimeter in estimating above-ground-level (AGL) altitude. This AGL state estimator was integrated in a near-terrain guidance system aboard a research helicopter and flight tested in moderately rugged terrain over a variety of flight and system conditions. The minimum operating altitude of the terrain database referenced guidance system was reduced from 300 ft to 150 ft with the addition of this Kalman filter state estimator. >

Method and apparatus for sensing guidewire signals

Abstract: The present invention features a material handling vehicle that is capable of operating in a manned mode, a wire guidance mode, and a rail guidance mode. This manned material handling vehicle contains a steering management control system comprising a logic program which allows the vehicle to adapt itself to different wire control systems. That is, the particular parameters, frequency and amplitude of the underlying wire guidance system can be determined. In this manner, the manned vehicle is universally adaptive to a wide variety of wire guidance systems.

Voice route-guidance system

Abstract: A route guidance system for vehicles is adapted to carry out route guidance based on stored data relating to a route from a start position to a destination. The route guidance is based on a detected present position of the vehicle and on the stored data relating to the route to the destination. The distance between the present position of the vehicle and the destination is detected and if the distance is not greater than a predetermined value it is judged that the vehicle is approaching the destination. The route guidance is terminated in response to the distance not greater than the predetermined value, and the route guidance is again started after being terminated responsive to an instruction from a restart directing means if it is not detected that a distance between the present position of the vehicle and the destination is not greater than the predetermined value.

Guidance to Collision of a Variable-Speed Missile

Abstract: Proportional Navigation (PN), the most used guidance law for short range homing missiles, is based on the asumption that missile speed is constant. However, the speed of a highly maneuverable modern missile varies considerably during flight, and the performance of PN is far from being satisfactory in that case. In this article we define a new guidance law that steers the heading of a variable-speed missile to a straight line collision course. The performance improvement of the missile using the new guidance law as compared to PN is demonstrated by simulation.

Rotational motion and guidance system approximations in optimizable operational launch vehicle simulations

Abstract: Launch planning and operations for a current U.S. launch system involve the use of 3-degree-of-f reedom (DOF) and 6DOF simulations. To account for statistical dispersions in component weights, engine performances, and launch site wind predictions, propellant margin must be left unburned in the final stage of the vehicle. Additional margin must be held back in the 3DOF simulation only to account for differences in 3DOF and 6DOF simulated trajectories. Since many missions are weight critical and the 3DOF simulation is used for initial shaping of the trajectory, any reduction in the 3DOF propellant margin should result in an increase in vehicle performance that can be significant for planning purposes. This paper seeks to enhance the current optimizable 3DOF simulation, making it more like the nonoptimizable 6DOF, which should allow a reduction in the 3DOF-to-6DOF margin component. The simulation is enhanced by simplifying the 6DOF closed-loop guidance system and using the result as a preprocessor of 3DOF steering commands. This provides a mimicry of vehicle rotational inertial characteristics in the 3DOF simulation. In addition, approximations of trajectory quantities are fed back based on what they would be if the enhanced 3DOF were a 6DOF. This paper discusses the guidance simplification and the trajectory quantity derivations and shows the resulting impacts on a 3DOF trajectory in terms of vehicle attitude and angle-of-attack time histories.

Simulation development of a forward sensor-enhanced low-altitude guidance system

Abstract: The requirement to operate aircraft at low-altitude near the terrain is common in the military community and essential for helicopters. The risk and crew workload in this flight regime is severe, with navigation, guidance, and obstacle avoidance demanding high attention, A guidance system relying on digitized terrain elevation maps has been developed that employs airborne navigation, mission requirements, aircraft performance limits, and radar altimeter returns to generate a valley-seeking, low-altitude trajectory between waypoints for display to the pilot. This system has been flight demonstrated to 150 ft above ground level attitude, and is primarily limited by the ability of the pilot to perform obstacle detection and avoidance. In this study, a wide field of view forward sensor has been modeled and incorporated in the guidance system for the purpose of relieving the pilot of the obstacle avoidance duty. The results of a piloted, motion-based simulation of this enhanced low-altitude guidance system is presented. Simulated flights to 50 ft altitude in the presence of obstacles were demonstrated while maintaining situational awareness and close tracking of the guidance trajectory. >

The future of head-up guidance

Abstract: The use of head-up displays in allowing aircraft to operate in low visibility is examined. A head-up guidance system that incorporates modern optics, holographic display, wide field of view, pilot-in-loop, optimized intuitive symbology, high quality sensors including ring laser gyro platforms, and modern electronics is described. The results of online studies are discussed. >

An automatic guidance system of an autonomous vehicle: the trajectory generation and the control algorithm

Abstract: This paper presents a trajectory generation method using smooth functions for an automatic guidance system of an autonomous vehicle with two differentially driven wheels within structured environments. A control algorithm based on an incrementally generated smooth trajectory gives a good performance when implemented on an experimental vehicle.

Characteristics of combined levitation and guidance EDS maglev system

Abstract: A levitation method has been introduced which uses 8-shape levitation coils arranged on the vertical surface of the guideway. These coils can act as a guidance means as well as the levitation means. The characteristics of this system are examined using numerical examples and experimental data. The cables connecting right and left coils are not connected to a high-voltage power source unlike the usual guidance system which is combined with propulsion. Thus the electric insulation of the cables is not a problem at present. Numerical examples show that the levitation characteristics of the combined levitation and guidance system are almost the same as in the system without the guidance function, and that it attains reduced running resistance with necessary guidance stiffness obtained. A test run was done at Miyazaki Test Line equipped with coils of this type arranged about 120 m, and the results show stable running and balanced displacement which agrees with calculated values.

Pacific rim transtech conference proceedings. volume i. modeling route guidance systems using the integration model

Abstract: The in-vehicle Route Guidance Systems could be a cost effective means of alleviating the impact of traffic congestion in urban areas. The enhancements and extensions are described of the integration traffic simulation model's features for representing the routing behavior of vehicles having varying levels of access to RGS, different system architectures, and different routing objectives. Various tools for modeling the routing behavior and response of non-guided background vehicles are demonstrated. The behavior and performance of a number of different vehicle types are demonstrated on a test network of 2000 links for Warren, Michigan. A sensitivity analysis is made of the travel time benefits of the TravTek route guidance logic, with respect to market penetration level.

Initial on-the-road tests of driver information system interfaces: route guidance, traffic information, ivsaws, and vehicle monitoring. final report

Abstract: The purpose of these experiments was to examine the safety and ease of use of simulated driver information system interfaces and to provide data that might be used to certify those qualities. In the first experiment, 6 pairs of drivers (12 participants) drove an instrumented car over a 19-turn, 35-minute route aided by an experimental route guidance system. The route guidance was provided on a head-up display (HUD), on the instrument panel (IP), or by voice. Drivers also used the other three information systems. The purpose of this experiment was to discover flaws in the driver interface or test protocol that were so serious that the experiment could not continue. There were none. In the second experiment, 43 drivers followed the same route using the same route guidance system and other information systems. Drivers made very few turn errors (mean = 1.8), with the fewest for the HUD, followed by the IP and voice designs. Also considered were measures obtained from the instrumented car including the mean and standard deviation of steering wheel angle, throttle position, speed and lane variance. There were very few differences among the three route guidance interfaces. Eye glance durations and frequencies were also obtained, as well as ratings of safety and ease of use of the driver interfaces.

Refuging guidance system

Abstract: PURPOSE:To provide a refuging guidance system which can refuging guidance even a visual sense handicapped person even when smoke is generated in an evacuation passage at the time of generating fire in referense to the refuging guidance system to make people to refuge at the time of fire. CONSTITUTION:Guidance lamps 1, 2, 3,... and speakers 11, 12, 13... are installed in prescribed intervals to refuging exits 100 in the refuging passage of a building. The system is also provided with a guidance lamp flickering/guidance sound generating device 80 which permits the guidance lamps 1, 2, 3,... installed to the evacuation exits 100 to repeat flickering in prescribed time successively toward the refuging exit 100 and permits the speakers 11, 12, 13,... to repeat sending a guidance sound in prescribed time successively toward the refuging exit 100 with the contact of a self-fire alarming board device when fire is generated and the contact is turned on.

Inertial Sensor Performance Requirements for a Long Range Artillery Rocket

Abstract: : With continuing advances in rocket propulsion systems for extended- range artillery, it is possible that operational ranges of 60 kilometers (up from the current 30 km) will be the norm within 20 years. However if the munitions are unguided, the dispersion errors at these long ranges, due to such factors as muzzle velocity errors and down-range weather conditions, make effective use of such rounds prohibitively expensive. This report investigates the performance required of inertial components that could be used for an onboard guidance system that would enable the rocket to determine its position to a sufficient level of accuracy. The high dynamics of the launch environment and the relatively short flight times make for unusual conditions for an inertial navigation system. It is shown that some components are of critical importance and must be of high performance (thus of more expense) while others are of much less importance and savings can be made when specifying the instruments for those functions.

Advanced technology for road transport: ivhs and att. chapter 11. advance - the illinois dynamic navigation and route guidance demonstration program

Abstract: This chapter presents the objectives and system design of the ADVANCE (Advanced Driver and Vehicle Advisory Navigation Concept) program. The project will implement, test and evaluate a large scale route guidance system in a suburban area near Chicago. Brief details of this trial are presented. For the covering abstract see IRRD 864133.

Monte Carlo analysis of the Titan III/Transfer Orbit Stage guidance system for the Mars Observer mission

Abstract: An important part of space launch vehicle mission planning for a planetary mission is the integrated analysis of guidance and performance dispersions for both booster and upper stage vehicles. For the Mars Observer mission, an integrated trajectory analysis was used to maximize the scientific payload and to minimize injection errors by optimizing the energy management of both vehicles. This was accomplished by designing the Titan III booster vehicle to inject into a hyperbolic departure plane, and the Transfer Orbit Stage (TOS) to correct any booster dispersions. An integrated Monte Carlo analysis of the performance and guidance dispersions of both vehicles provided sensitivities, an evaluation of their guidance schemes and an injection error covariance matrix. The polynomial guidance schemes used for the Titan III variable flight azimuth computations and the TOS solid rocket motor ignition time and burn direction derivations accounted for a wide variation of launch times, performance dispersions, and target conditions. The Mars Observer spacecraft was launched on 25 September 1992 on the Titan III/TOS vehicle. The post flight analysis indicated that a near perfect park orbit injection was achieved, followed by a trans-Mars injection with less than 2sigma errors.

Local path planning for an AUV using a cooperative control system

Abstract: A decentralized control system based on distributed parallel processing is proposed for an autonomous underwater vehicle (AUV). The software architecture is inspired by an object-oriented model aimed at the representation of a group of problem solvers. Preliminary developments related to the path planing near the sea bed were performed. A guidance system is assisted by a local grid map built in real time. Simulations using a model for a vehicle developed at the University of Tokyo were carried out, and the first results are discussed in this paper. >

Learning method by automatic correction of operation example

Abstract: PURPOSE:To improve the reliability of the operation guidance by adding a learning function to a guidance system based on the stored examples after evaluating the result (success or failure) obtained by applying the operation guidance to the real operation to analyze the factor of failure and to correct the examples. CONSTITUTION:The past operation examples are analyzed for execution of the operation guidance, and the result obtained by applying the operation guidance to a real operation is evaluated. If the application of the operation guidance fails, the factor of this failure is automatically analyzed based on the area logic. Then the example is corrected so that the difference is increased between the operation data obtained when an operating action is carried out based on the operation guidance and an extracted similar example. Meanwhile the reliability is reduced if the analysis of the failure factor is impossible.

Route-guidance system

Abstract: A route guidance system for vehicles is adapted to carry out route guidance even if the vehicle has moved without the passage of a transit point set in the route guidance system. To this effect, the route guidance system comprises means for setting a desired transit point, means for storing data relating to a route from a start position to a destination via the transit point, and means for detecting the present position of the vehicle. A control means compares the detected present position of the vehicle with said transit point in order to judge whether or not the vehicle has passed through the transit point, and issues route guidance from the present position to the transit point when the vehicle has not yet passed through the transit point and from the present position to the destination when the vehicle has passed through the transit point.

Landing guidance system

Abstract: PURPOSE:To enable a landing guidance system of an aircraft which is inexpensive and highly accurate to be developed. CONSTITUTION:A GPS reception device 11 and an operation device 12 are provided at a ground device 1 and a GPS receiver 26 is provided at a device 2 on the plane. The ground device 1 calculates a distance-measurement error of the GPS, transmits this distance-measurement error information to the device 2 on the plane by using a conventional transmission means, corrects a distance- measurement error according to the GPS receiver 26 of the device 2 on the plane, and then obtains an accurate distance information at all times, thus eliminating a need for using expensive DME transponder and interrogator.