Understanding Vertical Collision Risk and Navigation Performance for Unmanned Aircraft

McFadyen, Aaron; Martin, Terrence

doi:10.1109/dasc.2018.8569707

Cited by 12 publications

(9 citation statements)

References 18 publications

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“…α y P y (y)dy 130 70 P y (y)dy = 5.935 (13) α y is chosen from Table 1 because the shadow is made toward the centerline. The calculated shadow angle at left and right edge of wall1 is 2.009 deg and 5.935 deg, respectively.…”

Section: Appendixmentioning

confidence: 99%

“…The minor modifications to Hsu model have been made to represent the flight scenarios/situations considered [7], e.g. application to time-based separation standard [8], [9], lateral/longitudinal separation standard [10], [11], extension of Reich model [12], and application to unmanned aircraft [13]. In addition, there are many parameters which significantly affect the calculated collision probability, so data analysis of actual flight is also important and has been conducted [14], [15].…”

Section: Introductionmentioning

confidence: 99%

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Accurate Estimation of Ground Obstacle Collision Probability During ILS Approach

Mori

Fujita

2020

IEEE Access

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This paper proposes a new high-accuracy calculation method to estimate collision probability to ground obstacles during Instrument Landing System (ILS) approach. The current collision risk model (CRM) used to evaluate the ground obstacle collision probability was developed in the 1970s. In this CRM, a shadowing technique is used to avoid over-estimation of the risk when there are multiple obstacles located close to each other. However, this shadowing still overestimates the risk due to several conservative assumptions. This paper proposes mathematical modifications to the calculation of shadowing to address the risk overestimation. To validate the proposed method, 10 6 sets of aircraft trajectories are generated so that the actual risk can be estimated by counting the number of collisions. The result shows that the risk calculated by the proposed method is much closer to the actual risk compared to the one calculated by the current CRM. The proposed model will help introduce ILS approach at obstacles-sensitive airports. INDEX TERMS Collision risk model, aircraft navigation, approach, landing, safety.

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Section: Appendixmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Accurate Estimation of Ground Obstacle Collision Probability During ILS Approach

Mori

Fujita

2020

IEEE Access

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“…Separation requirements have been long-established and applied for manned aircraft 13 , and the factors that contribute to such requirements, such as collision avoidance, navigational uncertainties, and wake turbulence effects, are also applicable for UAS operations. Several studies have been conducted to calculate the risk of collision on an unmanned aircraft to ensure safe operation alongside other aircraft, manned or unmanned, in the airspace [14][15][16][17] .…”

Section: Introductionmentioning

confidence: 99%

“…Several studies have been conducted to calculate the risk of collision on an unmanned aircraft to ensure safe operation alongside other aircraft, manned or unmanned, in the airspace. [14][15][16][17] Additional study has also begun to investigate the navigation performance of common multirotor UAS 18 which can be used to determine the separation requirement that takes the navigational errors into account.…”

Section: Introductionmentioning

confidence: 99%

Numerical studies on modeling the near- and far-field wake vortex of a quadrotor in forward flight

Nathanael

Wang

Low

2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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The operation of Unmanned Aerial Systems (UAS) is expected to keep increasing in the future with its rapid advancement and ever-expanding applications. One of the safety measures that need to be put into place for safe UAS operations is separation requirements. This article presents the results from flow simulations of quadrotor propellers using the Overset method in ANSYS Fluent 19.2 and the Virtual Blade Model (VBM) method in OpenFOAM as part of ongoing work to establish a wake vortex–based safe separation distance for UAS operations. The near-field flow simulation using the Reynolds-averaged Navier–Stokes turbulence model was validated with mesh convergence and turbulence model studies and verified with simulation and experimental data in the literature to ensure that the propeller simulation methods could generate a realistic near-field flow of multi-rotor UAS in forward flight. The far-field flow simulation using the Large Eddy Simulation turbulence model was validated with a mesh convergence study by calculating and comparing the circulation strength of the vortices in the far-field flow of each mesh setup but not verified due to a lack of existing experimental data.

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“…The distance required to fulfill the separation minima depends on whether navigational error or wake-vortex encounter poses a bigger hazard to the following aircraft [1]. When applied to the UTM, the navigational based separation requirement would depend on the navigational aids available to the UAS [2], whether ground-based or vehicle-based. On the other hand, the hazard posed by the wake-vortex is based on its generation mechanism, the stability of the vortex pair, and the static and dynamic stability of the follower aircraft.…”

Section: Introductionmentioning

confidence: 99%

Framework for the Estimation of Safe Wake Separation Distance between Same-Track Multi-Rotor UAS

Wang

Nathanael

et al. 2021

AIAA Scitech 2021 Forum

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Understanding Vertical Collision Risk and Navigation Performance for Unmanned Aircraft

Cited by 12 publications

References 18 publications

Accurate Estimation of Ground Obstacle Collision Probability During ILS Approach

Accurate Estimation of Ground Obstacle Collision Probability During ILS Approach

Numerical studies on modeling the near- and far-field wake vortex of a quadrotor in forward flight

Framework for the Estimation of Safe Wake Separation Distance between Same-Track Multi-Rotor UAS

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