Autolanding a 737 Using GPS Integrity Beacons

Cohen, Clark E.; Cobb, H. Stewart; Lawrence, David G.; Pervan, Boris; Powell, J. David; Parkinson, Bradford W.; Aubrey, Gerald J.; Loewe, W.; Ormiston, D.; McNally, Brenna; Kaufmann, David N.; Wullschleger, Victor; Swider, Raymond

doi:10.1002/j.2161-4296.1995.tb01901.x

Cited by 28 publications

(15 citation statements)

References 2 publications

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“…This work aims at exploiting changes in satellite geometry to obtain fast and accurate estimates of carrier phase cycle ambiguities [4]. Implementations of this principle for aircraft precision approach and landing include the pseudo-satellite ('pseudolite')-based Integrity Beacon Landing System (IBLS) in the early 1990's [17][18][19], an augmentation of GPS using low earth orbiting (LEO) 'GlobalStar' satellites in 2000 [20], and a GPS augmentation system using Iridium LEO satellites in 2010 [14]. In each of the above references, greatly improved positioning performance was achieved by exploiting the fast relative angular motion between user receiver and the few ranging sources (pseudolites or LEO SVs) in view during short (five-to-ten minute long) mission durations.…”

Section: A First Analysis Of the Impact Of Geometric Diversity On Biamentioning

confidence: 99%

Exploiting Satellite Motion in ARAIM: Measurement Error Model Refinement Using Experimental Data

Joerger¹,

Pervan

2016

Proceedings of the 29th International Technical Meeting of the Satellite Division of the Institute of Navigation (ION GNSS+ 201

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In this work, a new time-sequential positioning and fault detection method is derived and analyzed for dualfrequency, multi-constellation Advanced Receiver Autonomous Integrity Monitoring (ARAIM). Unlike conventional 'snapshot' ARAIM, the sequential approach exploits changes in satellite geometry at the cost of slightly higher computation and memory loads. From the perspective of users on earth, the motion of any given GNSS satellite is small over short time intervals. But, the accumulated effect geometry variations of redundant satellites from multiple GNSS constellations can be substantial. This paper quantifies the potential performance benefit brought by satellite motion to ARAIM. It specifically addresses the following research challenges: (a) defining and experimentally validating raw GNSS code and carrier error models over time, consistent with established ARAIM assumptions, (b) designing estimators and fault-detectors capable of exploiting satellite motion for positioning, carrier phase cycle ambiguity estimation, and integrity evaluation, and (c) formulating these processes in a computationally-efficient implementation. A modular algorithm is designed, only requiring a minor augmentation of the snapshot airborne ARAIM multiple hypothesis solution separation (MHSS) algorithm. Other modifications to enable time-sequential ARAIM include additional ground segment performance commitments, and the inclusion of extra parameters in the broadcast integrity support message (ISM). Availability is analyzed worldwide for aircraft precision approach navigation applications. Results show substantial performance improvements for sequential ARAIM over snapshot ARAIM, not only to achieve 'localizer precision vertical' (LPV) requirements using depleted GPS and Galileo constellations, but also to fulfill much more stringent requirements including a ten-meter vertical alert limit.

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Section: A First Analysis Of the Impact Of Geometric Diversity On Biamentioning

confidence: 99%

Exploiting Satellite Motion in ARAIM: Measurement Error Model Refinement Using Experimental Data

Joerger¹,

Pervan

2016

Proceedings of the 29th International Technical Meeting of the Satellite Division of the Institute of Navigation (ION GNSS+ 201

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“…Additional minor modi cations were necessary in the airborne system to provide the aircraft autopilotwith an analog GPS navigationoutput that emulated the nominal ILS glideslope and localizer signal. 16 Realtime aircraft attitude for the two-antenna moment arm correction was obtained from one of the 737's two onboard inertial units. On the ground, two pseudolites were situated under the approach path 3.5 km from the runway threshold, corresponding to a pseudolite over ight altitude of 600 ft. As was the case in earlier ight tests, the ratio of pseudolite bubble radius to the radius of closest approach was set to approximately 3:1 for both pseudolites.…”

Section: Boeing 737 Automatic Landingsmentioning

confidence: 99%

Cycle Ambiguity Estimation for Aircraft Precision Landing Using the Global Positioning System

Pervan

Parkinson

1997

Journal of Guidance, Control, and Dynamics

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Measurements of the Global Positioning System carrier phase can provide the basis for the highest level of satellite-based navigation performance. In particular, the potential exists to exceed even the stringent navigation requirements for aircraft precision approach and landing. The principal dif culty in this use of carrier phase, however, lies in the real-time, high-integrity resolution of the unknown integer cycle ambiguities. A new methodology is introduced, using carrier phase measurements from ground-based pseudolites, for explicit estimation of the cycle ambiguities. The mathematical basis of the new approach is detailed, and high-speed nonlinear information smoothing algorithms suitable for real-time airborne execution are derived. Extensive ight-test data, including the results of automatic landings of a Boeing 737 aircraft, are presented as experimental validation of algorithm performance.

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“…Most of the improvements in the ALS system have been on the guidance instruments, such as GNSS Integrity Beacons, Global Positioning System, Microwave Landing System, and Auto-land Position Sensor [2][3][4][5]. By using improvement calculation methods and high accuracy instruments, these systems provide more accurate flight data to the ALS and can help to make landings smoother.…”

Section: Introductionmentioning

confidence: 99%

Intelligent landing control system for civil aviation aircraft with dual fuzzy neural network

Zhang

2011

2011 Eighth International Conference on Fuzzy Systems and Knowledge Discovery (FSKD)

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This paper presents the intelligent landing control system that overcome wind disturbance problem of a civil aviation aircraft during the landing phase when subjected to severe winds and failures such as stuck control surfaces. The controller architecture uses a dual fuzzy neural network (DFNN) controller, which is capable of implementing fuzzy inference in general and neural network mechanism in particular. A systematic method for mapping an existing rule base into a set of dual fuzzy neural network weights has also been presented. However, in order to utilize this method to initialize the dual fuzzy neural network weights, such a rule base obtained from domain experts or from experimental data through systematic, knowledge acquisition methods has been proposed. It uses one neural network as on-line learning and does not need a priori training. Simulations show that it improved the performance of conventional automatic landing system (ALS) and guide the aircraft to a safe landing.

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Autolanding a 737 Using GPS Integrity Beacons

Cited by 28 publications

References 2 publications

Exploiting Satellite Motion in ARAIM: Measurement Error Model Refinement Using Experimental Data

Exploiting Satellite Motion in ARAIM: Measurement Error Model Refinement Using Experimental Data

Cycle Ambiguity Estimation for Aircraft Precision Landing Using the Global Positioning System

Intelligent landing control system for civil aviation aircraft with dual fuzzy neural network

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