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  • 1
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    Optimum horizontal guidance techniques for aircraft (1978)
    In:  CASI
    Details
    Publication Date: 2006-03-02
    Description: Some problems of automatic guidance of an aircraft in the horizontal plane are described. The horizontal guidance tasks, which such a flight control system should be capable of performing, were identified as being of three types: guiding the aircraft from any initial location and initial heading to (1) any final location and heading; (2) intercept and fly along a line of specified direction; and (3) a final location with arbitrary final heading. Guidance problems such as capturing an ILS beam at a specified point on the beam, intercepting a VOR radial, and point-to-point navigation can be formulated in terms of these problems. The guidance laws minimize the arc distance to fly between initial and final conditions subject to constraints on the minimum turning radius.
    Keywords: AIRCRAFT COMMUNICATIONS AND NAVIGATION
    Type: NASA, Washington Fourth Inter-Center Control Systems Conf.; p 175-184
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Mixing four-dimensional equipped and unequipped aircraft in the terminal area (1985)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: AIRCRAFT COMMUNICATIONS AND NAVIGATION
    Type: Journal of Guidance, Control, and Dynamics (ISSN 0731-5090); 8; 296-303
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Time controlled descent guidance algorithm for simulation of advanced ATC systems (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Concepts and computer algorithms for generating time controlled four dimensional descent trajectories are described. The algorithms were implemented in the air traffic control simulator and used by experienced controllers in studies of advanced air traffic flow management procedures. A time controlled descent trajectory comprises a vector function of time, including position, altitude, and heading, that starts at the initial position of the aircraft and ends at touchdown. The trajectory provides a four dimensional reference path which will cause an aircraft tracking it to touchdown at a predetermined time with a minimum of fuel consumption. The problem of constructing such trajectories is divided into three subproblems involving synthesis of horizontal, vertical, and speed profiles. The horizontal profile is constructed as a sequence of turns and straight lines passing through a specified set of waypoints. The vertical profile consists of a sequence of level flight and constant descent angle segments defined by altitude waypoints. The speed profile is synthesized as a sequence of constant Mach number, constant indicated airspeed, and acceleration/deceleration legs. It is generated by integrating point mass differential equations of motion, which include the thrust and drag models of the aircraft.
    Keywords: AIRCRAFT COMMUNICATIONS AND NAVIGATION
    Type: NASA-TM-84373 , A-9372 , NAS 1.15:84373
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Algorithm for fixed-range optimal trajectories (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An algorithm for synthesizing optimal aircraft trajectories for specified range was developed and implemented in a computer program written in FORTRAN IV. The algorithm, its computer implementation, and a set of example optimum trajectories for the Boeing 727-100 aircraft are described. The algorithm optimizes trajectories with respect to a cost function that is the weighted sum of fuel cost and time cost. The optimum trajectory consists at most of a three segments: climb, cruise, and descent. The climb and descent profiles are generated by integrating a simplified set of kinematic and dynamic equations wherein the total energy of the aircraft is the independent or time like variable. At each energy level the optimum airspeeds and thrust settings are obtained as the values that minimize the variational Hamiltonian. Although the emphasis is on an off-line, open-loop computation, eventually the most important application will be in an on-board flight management system.
    Keywords: AIRCRAFT COMMUNICATIONS AND NAVIGATION
    Type: NASA-TP-1565 , A-8003
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Characteristics of constrained optimum trajectories with specified range (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Necessary conditions of optimality are derived for trajectories whose structure is limited to climb, steady cruise, and descent segments. The performance function consists of the sum of fuel and time costs, referred to as direct operating cost (DOC). The state variable is range to go and the independent variable is energy. In this formulation a cruise segment always occurs at the optimum cruise energy for sufficiently large range. At short ranges (500 n. mi. and less) a cruise segment may also occur below the optimum cruise energy. The existence of such a cruise segment depends primarily on the fuel flow vs thrust characteristics and on thrust constraints. If thrust is a free control variable along with airspeed, it is shown that such cruise segments will not generally occur. If thrust is constrained to some maximum value in climb and to some minimum in descent, such cruise segments generally will occur. Computer calculations of typical short-range trajectories obtained about a 1% cost penalty for constraining the thrust.
    Keywords: AIRCRAFT COMMUNICATIONS AND NAVIGATION
    Type: NASA-TM-78519 , A-7592
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    The 4D area navigation system description and flight test results (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A 4D area navigation system was designed to guide aircraft along a prespecified flight path (reference path) such that the aircraft would arrive at the approach gate at a time specified by the ATC controller. Key components to achieve this requirement were: (1) stored reference trajectories; (2) a continuously recomputed capture trajectory to a selected waypoint on the reference trajectory so as to achieve the desired time of arrival; (3) electronic situation displays; and (4) a control system to follow the overall trajectory in space and time. The system was implemented in a digital integrated avionics system (STOLAND) installed on a CV-340 airplane. Although the 4D system was designed primarily for automatic operation, it was flight tested in a flight director mode (the pilot follows the flight director commands), because the CV-340 autopilot servos were not tied to the avionics system. The flight test showed that, even in the flight director mode, the pilot did achieve the objectives of path tracking and time of arrival control with only moderate workload. The system also permitted controlled delay of the time of arrival by path stretching, which takes advantage of the continuously changing capture trajectory to predict the time of arrival. Simulations in the automatic and manual modes were used to complement the flight data.
    Keywords: AIRCRAFT COMMUNICATIONS AND NAVIGATION
    Type: NASA-TN-D-7874 , A-5788
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Flight experience with time-of-arrival control for STOL aircraft in the terminal area (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A research program on STOL operating systems is underway at the Ames Research Center. One investigation is concerned with design, analysis, and flight test of promising four-dimensional RNAV systems. One promising system generates a capture flight path from the present aircraft position to a waypoint on a selected fixed STOL approach route. It predicts arrival time at the runway and controls time and position along the path. The system was flight tested using a digital avionics system on a Convair 340 and on an experimental powered-lift STOL airplane. Flight tests in the flight director mode show that the pilot can choose and change the desired time of arrival, and meet this time within a few seconds, in spite of navigation errors and varying winds. Initial tests of the automatic mode using a flight simulator and the NASA Augmentor Wing Jet STOL Research Aircraft (AWJSRA) show that good time control was achieved at the cost of excess throttle activity. This fault was later corrected.
    Keywords: AIRCRAFT COMMUNICATIONS AND NAVIGATION
    Type: AIAA PAPER 75-1126 , American Institute of Aeronautics and Astronautics, Guidance and Control Conference; Aug 20, 1975 - Aug 22, 1975; Boston, MA
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Mixing 4D equipped and unequipped aircraft in the terminal area (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The problem of mixing four-dimensional (4D) equipped aircraft (aircraft equipped with on-board guidance systems that can predict and control the touchdown-time of an aircraft to an accuracy of a few seconds throughout the descent) with unequipped aircraft in the terminal area has been investigated via a real-time air traffic control simulation study. The objective of this study was to develop scheduling algorithms and operational procedures for various traffic mixes that ranged from 25 percent to 75 percent 4D equipped aircraft. Results indicate substantial reduction in controller workload and an increase in orderliness when more than 25 percent of the aircraft are 4D equipped. Moreover, this is accomplished without increasing the workload or adding delays for the unequipped aircraft.
    Keywords: AIRCRAFT COMMUNICATIONS AND NAVIGATION
    Type: AIAA PAPER 83-2240 , Guidance and Control Conference; Aug 15, 1983 - Aug 17, 1983; Gatlinburg, TN
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Mixing 4D-Equipped and Unequipped Aircraft in the Terminal Area (1984)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: On-board 4D guidance systems, which predict and control the touchdown time of an aircraft to an accuracy of a few seconds throughout the descent, were developed and demonstrated in several flight test programs. However, in addition to refinements of the on board system, two important issues still need to be considered. First, in order to make effective use of these on-board systems, it is necessary to understand and develop the interactions of the airborne and air traffic control (ATC) system in the proposed advanced environment. Unless the total system is understood, the advanced on-board system may prove unusable from an ATC standpoint. Second, in planning for a future system in which all aircraft are 4D equipped, it is necessary to confront the transition situation in which some percentage of traffic must still be handled by conventional means. In terms of 4D, this means that some traffic must still be given radar vectors and speed clearances (that is, be spaced by conventional distance separation techniques), while the 4D-equipped aircraft need to be issued time assignments. These apparent differences are reconciled and efficient ATC operation is developed.
    Keywords: AIRCRAFT COMMUNICATIONS AND NAVIGATION
    Type: NASA. Langley Research Center NASA Aircraft Controls Research, 1983; p 171-190
    Format: application/pdf
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  • 10
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    Development of the L-1011 four-dimensional flight management system (1984)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The development of 4-D guidance and control algorithms for the L-1011 Flight Management System is described. Four-D Flight Management is a concept by which an aircraft's flight is optimized along the 3-D path within the constraints of today's ATC environment, while its arrival time is controlled to fit into the air traffic flow without incurring or causing delays. The methods developed herein were designed to be compatible with the time-based en route metering techniques that were recently developed by the Dallas/Fort Worth and Denver Air Route Traffic Control Centers. The ensuing development of the 4-D guidance algorithms, the necessary control laws and the operational procedures are discussed. Results of computer simulation evaluation of the guidance algorithms and control laws are presented, along with a description of the software development procedures utilized.
    Keywords: AIRCRAFT COMMUNICATIONS AND NAVIGATION
    Type: NASA-CR-3700 , NAS 1.26:3700 , LR-30279
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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