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Showing papers on "Guidance system published in 1986"


Patent
William R. Yueh1
08 Dec 1986
TL;DR: In this paper, a method and apparatus for identifying inertial reference unit (IRU) errors in a guided missile employing a multi-mode guidance system and constructing correction terms to recover the missile true position is presented.
Abstract: A method and apparatus for identifying inertial reference unit (IRU) errors in a guided missile employing a multi-mode guidance system and constructing correction terms to recover the missile true position. Discrepancy parameters are introduced to indicate misalignment between missile and launching platform (or ship) inertial frames where the missile onboard executive computer simultaneously processes the data provided from missile onboard sensors and target relevant data uplinked from the launching platform. The discrepancy parameters are employed to construct correction factors used to reduce the discrepancies. This updated missile configuration is then coupled with the target state estimator outputs to reconstruct smoothed line-of-sight (LOS) angles for terminal homing engagement.

52 citations


01 Apr 1986
TL;DR: Air traffic control simulations have established that the automated air-traffic-management concept provides an efficient method for controlling various mixes of 4D-equipped and unequipped aircraft, as well as low- and high-performance aircraft.
Abstract: An automated air-traffic-management concept that has the potential for significantly increasing the efficiency of traffic flows in high-density terminal areas is discussed. The concept's implementation depends on the techniques for controlling the landing time of all aircraft entering the terminal area, both those that are equipped with on-board four dimensional guidance systems as well as those aircraft types that are conventionally equipped. The two major ground-based elements of the system are a scheduler which assigns conflict-free landing times and a profile descent advisor. Landing times provided by the scheduler are uplinked to equipped aircraft and translated into the appropriate four dimensional trajectory by the on-board flight-management system. The controller issues descent advisories to unequipped aircraft to help them achieve the assigned landing times. Air traffic control simulations have established that the concept provides an efficient method for controlling various mixes of four dimensional-equipped and unequipped, as well as low-and high-performance, aircraft.

50 citations


Patent
03 Feb 1986
TL;DR: In this paper, a sensor is used to detect the position of a target and for detecting the positions of a missile, and a fire control processor is provided that computes a trajectory for the missile to the target and is connected to the sensor to determine any variations between the actual missile position from a computed trajectory.
Abstract: A missile guidance system including a sensor for detecting the position of a target and for detecting the position of a missile. A fire control processor is provided that computes a trajectory for the missile to the target and is connected to the sensor to determine any variations between the actual missile position from a computed trajectory missile position. A transmitter connected to this guidance computer then provides guidance information to the missile. The guidance information includes the missile position relative to the target and enables a processor on board the missile to recompute a new trajectory to the target. This guidance information is transmitted as a single pulse during a predetermined time interval as a periodic update to the missile.

39 citations


Patent
02 Apr 1986
TL;DR: In this article, the authors proposed a fixed beam guidance system based on the concept of using paired fixed overlapping beams, sequentially radiated by different fixed antennas, for small airports.
Abstract: The invention provides independent guidance and monitoring to be integrated into an MLS landing system and also provides a scaled-down MLS landing guidance system useable at small airports. In both cases an added fixed beam precision guidance system is integrated into the MLS time sequence format. The fixed beam guidance system is based upon the concept of using paired fixed overlapping beams, sequentially radiated by different fixed antennas. One pair is oriented to left and right of the centerline of the runway, and the other pair is oriented above and below the desired glideslope. The first set of paired beams overlap at the centerline of the runway in such a manner that an aircraft approaching exactly on centerline will intercept equal signal intensities to indicate an on-course approach. Conversely when the aircraft is off-course to one side of the centerline, it will intercept a stronger signal intensity for the fixed guidance beam which is directed to that side of the centerline and a weaker signal intensity for the fixed beam which is directed to the other side of the centerline. Similar operation is provided by the overlapped guidance beams operating in the elevation mode.

34 citations


Patent
Kohji Kamejima1, Yuriko Ogawa1
05 Feb 1986
TL;DR: In this article, a method for guiding a mobile object along a path within a predetermined environment and a guidance system was proposed, which consisted of first memory means (7) to store prediction patterns of objects within the environment, second memory mean (8) to extract sequence of the prediction patterns from the objects stored in the first memory and a control device (2) which compares for matching the prediction pattern obtained from said first and second memory means and a feature pattern from an observed image, on the basis of positional information of the mobile object (1), and delivering a guidance signal to
Abstract: The invention relates to a method for guiding a mobile object along a path within a predetermined environment and a guidance system. The system comprises first memory means (7) to store prediction patterns of objects within the environment, second memory means (8) to store an extraction sequence of the prediction patterns of the objects stored in said first memory means (7) and a control device (2) which compares for matching the prediction pattern obtained from said first and second memory means and a feature pattern obtained from an observed image, on the basis of positional information of the mobile object (1), and delivering a guidance signal thereto so as to diminish a difference between both patterns, when the pattern matching is possible.

27 citations


Patent
19 Dec 1986
TL;DR: In this article, a bus is launched from a launch station remote from a target with the bus missile carrying a plurality of sub-missiles, which are arranged to deploy ahead of the bus and are guided to the target under the control of a guidance beam generated in and transmitted from the bus.
Abstract: A missile system and a method of missile guidance in which a bus missile is launched from a launch station remote from a target with the bus missile carrying a plurality of sub-missiles. The sub-missiles are then launched from the bus missile during flight of the bus missile. The sub-missiles are arranged to deploy ahead of the bus missile and are guided to the target under the control of a guidance beam generated in and transmitted from the bus missile.

26 citations


Patent
08 Oct 1986
TL;DR: In this paper, a guidance apparatus for guiding a missile (18) to a target (20) by a beam (16) is disclosed, which includes a device (12) for projecting the beam, the orientation of which controls the flight path of the missile, and a circuit for generating a signal when the missile is in a predetermined spatial relationship (e.g., the center coded portion) with respect to said beam.
Abstract: A guidance apparatus (10) for guiding a missile (18) to a target (20) by a beam (16) is disclosed. The apparatus (10) includes a device (12) for projecting the beam (16), the orientation of which controls the flight path of the missile (18). The missile (18) includes a circuit for generating a signal when the missile (18) is in a predetermined spatial relationship (e.g., the center coded portion) with respect to said beam (16). When such signal is generated, the angular position of the missile with respect to the target is determined. This positioned relationship is then provided to ground based circuitry (56, 58 and 60) which forms a part of apparatus (10) and which adjusts the orientation of the beam (16) to reduce the angular separation of missile and target.

20 citations


Patent
31 Oct 1986
TL;DR: In this article, a system for modifying the demand component to compensate for the lateral acceleration generated by the coupling of the acceleration along its longitudinal axis and the angle between the body of the missile and the sightline is presented.
Abstract: In known guidance systems, the missile is guided by a control loop which includes the missile and a ground-based tracker, the tracker determining the relative positions of the missile and target and hence the lateral acceleration to be applied to the missile. However, these systems do not take account of the lateral acceleration generated by the coupling of the missile acceleration along its longitudinal axis and the angle between the body of the missile and the sightline, as in cases where acceleration is small the effect is insignificant. Described herein is a system for modifying the demand component to effect compensation for the lateral acceleration component imparted to the missile by virtue of its angle of incidence. This is accomplished by modifying the demand component in accordance with a stored predetermined time-varying gain term thereby to effect compensation of the lateral acceleration component imparted to the missile by virtue of the angle of incidence of the missile.

17 citations



Patent
Thomas J. Doty1
29 Aug 1986
TL;DR: In this article, a controllable mobile apparatus such as a mobile robot travels to a commanded destination under the control of a guidance system that provides speed and direction commands to the robot.
Abstract: A controllable mobile apparatus such as a mobile robot travels to a commanded destination under the control of a guidance system that provides speed and direction commands to the controllable mobile apparatus. A plurality of wheels carry the mobile apparatus to the commanded position in response to the speed commands from the guidance system. Steering commands will cause the selected members of the plurality of wheels to vary their angles by a predetermined amount in response to the steering commands that are provided by the guidance system. Additionally, a braking system is provided for stopping the controllable mobile apparatus when it encounters loss of power or communications with the guidance system.

12 citations


Journal ArticleDOI
TL;DR: In this article, a tradeoff between radome compensation and wing size for a homing-missile is discussed. But the tradeoff is not specifically related to guidance performance.
Abstract: The aerodynamic configuration of a homing missile is usually based on aerodynamic studies against the spectrum of threats to be engaged The most "aerodynamically efficient" missile is often selected from single fly-out studies not specifically related to guidance This paper delineates a tradeoff related to guidance system performance that can affect the aerodynamic configuration This tradeoff is between radome compensation and wing size It is shown that radome compensation can be used to reduce wing size, and thereby a missile's drag and weight A quantitative example is presented for a representative design

Patent
31 Oct 1986
TL;DR: In this paper, a system in which the obscuration of the target by the missile flare is reduced by guiding the missile along a trajectory displaced from the sightline until the target subtense is the same size as that of the missile is described.
Abstract: In automatic command to line of sight guidance systems, the missile and target are tracked remotely and a guidance computer processes the tracking data to provide a guidance command for the missile. In such systems, the target and missile must be visible but when the angular subtense of the missile flare is greater than that of the target, the target is totally obscured by the flare when the missile is on sightline leading to the erroneous guidance commands. Described herein is a system in which the obscuration of the target by the missile flare is reduced by guiding the missile along a trajectory displaced from the sightline until the target subtense is the same size as that of the missile.

Proceedings ArticleDOI
D. Polvani1
01 Jan 1986
TL;DR: In this article, the authors proposed an adaptive search technique to locate the center of the magnetic anomaly to within several feet using a scalar magnetometer whose outputs are successively subtracted along the path of sensor motion to form an approximation to the spatial gradient of the sensor's output.
Abstract: Increasing interest in underwater autonomous vehicles has resulted in a search for suitable guidance systems. Magnetic techniques could provide supplementary guidance for autonomous vehicles that need occasional precise position fixes to update their standard navigational systems, or that want to return to a particular spot on the ocean bottom with great accuracy. A small permanent magnet resting at a precisely known spot on the ocean's bottom or naturally occurring key features in a magnetic survey of the bottom could provide the necessary magnetic signal. Of the several magnetic guidance approaches considered, an adaptive search technique seems the most promising. In adaptive search, the location of each successive search pass is determined by information gathered on the previous pass. Computer simulation results show that three search passes are usually sufficient to locate the center of the magnetic anomaly to within several feet. The favored sensor configuration is a scalar magnetometer whose outputs are successively subtracted along the path of sensor motion to form an approximation to the spatial gradient of the sensor's output. Data interpretation for this technique appears simple enough to be done automatically by either algorithmic or artificial intelligence techniques.

Patent
24 Dec 1986
TL;DR: In this paper, the authors proposed a fixed beam guidance system based on the concept of using paired fixed overlapping beams, sequentially radiated by different fixed antennas, for small airports.
Abstract: The invention provides independent guidance and monitoring to be integrated into an MLS landing system and also provides a scaled-down MLS landing guidance system useable at small airports. In both cases an added fixed beam precision guidance system is integrated into the MLS time sequence format. The fixed beam guidance system is based upon the concept of using paired fixed overlapping beams, sequentially radiated by different fixed antennas. One pair is oriented to left and right of the centerline of the runway, and the other pair is oriented above and below the desired glideslope. The first set of paired beams overlap at the centerline of the runway in such a manner that an aircraft approaching exactly on centerline will intercept equal signal intensities to indicate an on-course approach. Conversely when the aircraft is off-course to one side of the centerline, it will intercept a stronger signal intensity for the fixed guidance beam which is directed to that side of the centerline and a weaker signal intensity for the fixed beam which is directed to the other side of the centerline. Similar operation is provided by the overlapped guidance beams operating in the elevation mode.


Patent
06 Aug 1986
TL;DR: In this article, an anthropomorphous telemanipulator is used to clean an airport runway lighting system using a vehicular mounted, whose ground movements in tracing and circumnavigating the runway light patterns are controlled by an automatic guidance system.
Abstract: An airport runway lighting system is cleaned using a anthropomorphous telemanipulator, vehicular mounted, whose ground movements in tracing and circumnavigating the runway light patterns are controlled by an automatic guidance system. Cleaning may be effected ultrasonically. The specification also envisages such guidance systems being used for other aircraft servicing vehicles, e.g. baggage trucks and mobile passenger lounges.

Journal ArticleDOI
TL;DR: The landing system requirements/synthesis study has defined the pilot/vehicle interface and imaging sensor suite required, based on the concept of augmenting pilot forward vision with sensor imagery and guidance symbology on a HUD during low visibility landings.
Abstract: All weather tactical aircraft recovery and high sortie generation rates from forward, possibly battle damaged landing areas will reqire autonomous landing guidance systems which are independent of ground-based cooperative aids. A recently completed study has examined the operational requirements and assessed current and near term technology for an answer to this need. The Landing Systems Requirements/Synthesis Study has defined the Pilot/vehicle Interface and imaging sensor suite required, based on the concept of augmenting pilot forward vision with sensor imagery and guidance symbology on a HUD during low visibility landings. Image processing technology was also assessed for potential enhancement of the information presented to the pilot. This paper summarizes the final report of the Study, which is in publication.

Patent
02 May 1986
TL;DR: In this article, a guidance system on a machine, especially a machine tool, consisting of a twist resistant, vibratioin damping support body, of concrete for example, and at least one body fastened thereon or integrated therein, which is not of itself twist-resistant, and which forms the guidance ways, is described.
Abstract: The present invention relates to a guidance system on a machine, especially a machine tool, consisting of a twist-resistant, vibratioin damping support body, of concrete for example, and at least one body fastened thereon or integrated therein, which is not of itself twist-resistant, and which forms the guidance ways. In order to endow such guidance ways with minimal thermal expansion and elasticity, make them very hard, give them good low-lubrication running characteristics, and enable them to be manufactured simply and very accurately, the body forming the guidance ways consists of sinterable nonmetals, especially ceramic material.



Patent
07 Oct 1986


01 Jan 1986
TL;DR: In this article, a review of the challenges, problems and solutions encountered to date during guidance system development, with emphasis on technology advances which will benefit an operational Orbit Transfer Vehicle (OTV).
Abstract: The Aeroassist Flight Experiment scheduled for the early 1990's will demonstrate the use of a low L/D lifting brake using aerodynamic drag to return a spacecraft from a high energy to a low earth orbit. The experimental vehicle will be deployed and retrieved by the Shuttle Orbiter. This paper reviews some of the challenges, problems, and solutions encountered to date during guidance system development, with emphasis on technology advances which will benefit an operational Orbit Transfer Vehicle (OTV). Key factors to be discussed include guidance alternatives, aerodynamic modeling, navigation requirements, the impact of atmospheric uncertainties, and flight profile alternatives considered during initial planning.


Journal ArticleDOI
TL;DR: The results of an experiment using a small car indicate the good accuracy and good performance of this location and guidance system, controlled by a dead-reckoning computer which has a route setting system in the computer memory.
Abstract: _An experimental on-board location and guidance system is described which is controlled by a dead-reckoning computer which has a route setting system in the computer memory. The location and heading of the vehicles are essentially computed from the rotation of both wheels. The steering system is operated by comparing the predicted position, which is computed using location, heading and velocity data, with the route stored in the memory. The results of an experiment using a small car indicate the good accuracy and good performance of this system.


01 Jul 1986
TL;DR: In this article, a computer-simulation study was undertaken to investigate a maximum concealment guidance technique (pop-up maneuver), which military aircraft may use to capture a glide path from masked, low-altitude flight typical of terrain following/terrain avoidance flight enroute.
Abstract: A computer-simulation study was undertaken to investigate a maximum concealment guidance technique (pop-up maneuver), which military aircraft may use to capture a glide path from masked, low-altitude flight typical of terrain following/terrain avoidance flight enroute. The guidance system applied to this problem is the Fuel Conservative Guidance System. Previous studies using this system have concentrated on the saving of fuel in basically conventional land and ship-based operations. Because this system is based on energy-management concepts, it also has direct application to the pop-up approach which exploits aircraft performance. Although the algorithm was initially designed to reduce fuel consumption, the commanded deceleration is at its upper limit during the pop-up and, therefore, is a good approximation of a minimum-time solution. Using the model of a powered-lift aircraft, the results of the study demonstrated that guidance commands generated by the system are well within the capability of an automatic flight-control system. Results for several initial approach conditions are presented.