Construction of an optimal flight trajectory in the glonass accuracy field

Skrypnik, Oleg Nicolaevich; Arefyeveva, N. G.

doi:10.23919/icins.2017.7995606

Cited by 4 publications

(4 citation statements)

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“…In paper (Jin et al, 2009), the ambiguity solution was estimated using GPS/GLONASS data for purpose of aircraft attitude orientation. More recently, a scientific issue of interest using GLONASS is also the continuous monitoring and optimisation of flight trajectory with control functions during approach and landing (Skrypnik & Arefyeveva, 2017;Baburov et al, 2017;Skrypnik et al, 2018;Gorskiy et al, 2019;Skrypnik & Arefyev, 2020). Furthermore, the GLONASS system is being used together with other telemetry sensors at airports within the Russian Federation as part of the 'Digital Smart Airport' programme (Khadonova et al, 2020).…”

Section: Scientific Knowledgde Analysismentioning

confidence: 99%

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Improving positioning accuracy of aircraft using SPP method in GLONASS system

Krasuski,

Ciećko,

Grunwald

et al. 2024

AoT

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The paper presents the results of a study showing the accuracy of the determination of aircraft position coordinates based on the SPP (Single Point Positioning) solution in the GLONASS (Globalnaja Navigatsionnaya Sputnikovaya Sistema) system. For this purpose, the paper develops and implements an algorithm for the correction of position errors as parameters describing positioning accuracy. The proposed algorithm uses position error values determined for a single GNSS (Global Navigation Satellite Systems) receiver, which are joined in a linear combination to determine the positioning accuracy of the aircraft. The algorithm uses linear coefficients as an inverse function of the number of GLONASS satellites being tracked by the GNSS receiver. The developed algorithm was tested for GLONASS satellite data recorded by Topcon HiPer Pro and Javad Alpha geodetic receivers, during a flight test carried out with a Cessna 172 aircraft around the military airport in Dęblin. Navigation calculations were carried out using RTKLIB v.2.4.3 and Scilab v.6.0.0 software. On the basis of the tests carried out, it was found that for single Topcon HiPer Pro and Javad Alpha receivers, position errors were up to ±11.4 m. However, by using the position error correction algorithm for both receivers, GLONASS positioning accuracy is up to ±3.6 m. The developed algorithm reduces position errors by 60-80% for all BLh (B- Latitude, L- Longitude, h- ellipsoidal height) coordinates. The paper shows the possibility of testing and implementing the proposed mathematical algorithm for the SPP solution in a GPS (Global Positioning System) navigation system. In this case the position errors from the GPS SPP solution range from -0.9 m to +0.9 m for all BLh coordinates. The obtained results showed that application the GLONASS and GPS system in air transport is important. The algorithm used in this work can also be applied to other global GNSS navigation systems (e.g. Galileo (European Navigation Satellite system) or BeiDou (Chinese Navigation Satellite System)) in air transport and navigation.

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Section: Scientific Knowledgde Analysismentioning

confidence: 99%

“…Krasuski, K., Ciećko, A., Grunwald, G., Kirschenstein, M., Archives of Transport, 69(1),[21][22][23][24][25][26][27][28][29][30][31][32][33][34][35][36][37] 2024 …”

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Improving positioning accuracy of aircraft using SPP method in GLONASS system

Krasuski,

Ciećko,

Grunwald

et al. 2024

AoT

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“…The accuracy of SNS positioning depends on location of navigation satellites relative to an aircraft and is characterized by dilution of precision which changes both in time and in space [2,11]. Correspondingly, the accuracy of SNS positioning also changes in time and space, thus leading to changes of track holding accuracy.…”

Section: Introductionmentioning

confidence: 99%

Algorithms for aircraft track optimization in flexible routing

et al. 2019

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The authors consider the problem of optimization of aircraft flight tracks in air traffic management (ATM) on basis of flexible routing technologies which involve the use of satellite navigation systems (SNS). It is shown that in optimizing a trajectory it is necessary to take into account the accuracy of track holding in flight which depends on accuracy of the navigation system and external flight path disturbances, e.g. wind. For solving the problem of optimization the authors propose to use the theory of graphs. The technique of constructing a dynamic SNS accuracy field and representing it as a graph was developed. It is proposed that the SNS field could be characterized by geometric dilution of precision changing both in space and in time. Based on the theory of graphs (A-star algorithm) the technique of constructing a trajectory of optimal length under conditions of SNS accuracy variations and external flight path disturbances is proposed. The criterion of optimization based on minimizing the true track is offered. The cost function taking into account the track holding accuracy in navigating by SNS and effects of external flight disturbances is justified. The article represents the results of A-star algorithm application for optimal flight track construction under conditions of SNS accuracy field variation and presence of prohibited zones in the provide zone of airspace

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“…Поскольку воздушная обстановка в предоставляемом ВП является динамичной, задача конструирования оптимальной траектории должна решаться в бортовой системе самолетовождения в реальном масштабе времени и, по возможности, с учетом изменения точности определения координат ВС по данным ССН [2,3].…”

Section: Introductionunclassified

Optimization of an aircraft flight trajectory in the GLONASS dynamic accuracy field

Skrypnik

Арефьева

Арефьев

2018

Naučn. vestn. MGTU GA

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Advanced technologies in air traffic management assume the transition to flexible routing based on the use of the satellite navigation systems. However, the accuracy of these systems depends on the location of the navigation satellites in relation to the target object and will vary in the available airspace. Therefore, the designed optimal flight path of the aircraft should be built taking into account the accuracy of its keeping in the variable navigation-time field (accuracy field) of the satellite navigation system. The accuracy field of the satellite navigation systems can be characterized by the geometric factor (spatial, horizontal and vertical). The geometric factor of the satellite navigation system is determined by the relative position of the consumer and the satellites upon which the navigation problem is solved, and is a deterministic value. Due to the orbital motion of satellites and the movement of the consumer, the geometric factor will change in space and time. Knowing the laws of the satellites orbital motion it is possible to calculate the geometric factor for any point in the air space and for any moment of time according to the known almanac of the system. This allows predicting the expected accuracy of the navigation and time determination during the flight on a particular air route. Optimization methods based on the algorithms of A-star and Dijkstra graph theory are chosen for aircraft flight trajectories construction. Mathematical modeling is used for the optimal trajectory construction in the GLONASS dynamic accuracy fields with their various structures in static and dynamic problem setting.

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Construction of an optimal flight trajectory in the glonass accuracy field

Cited by 4 publications

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Improving positioning accuracy of aircraft using SPP method in GLONASS system

Improving positioning accuracy of aircraft using SPP method in GLONASS system

Algorithms for aircraft track optimization in flexible routing

Optimization of an aircraft flight trajectory in the GLONASS dynamic accuracy field

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