Optimal Trajectory and Control Generation for Landing of Multiple Aircraft in the Presence of Obstacles

Mohan, Krithika; Patterson, Michael; Rao, Anil V.

doi:10.2514/6.2012-4826

Cited by 14 publications

(12 citation statements)

References 18 publications

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“…Other strategies could bring better convergence to the algorithm with the cost of a less accurate representation of the separation volume. This would be, for example, in case of a sphere [32] or an ellipsoid [33]. These are geometrical forms that can be expressed by a single equation and,…”

Section: Separation Volumementioning

confidence: 99%

Conflict-Free Trajectory Optimization with Target Tracking and Conformance Monitoring

Vilardaga¹,

Prats²,

Duan³

et al. 2018

Journal of Aircraft

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This paper proposes an optimisation framework that computes conflict free optimal trajectories in dense terminal airspace, while continuously monitoring trajectory conformance in an effort to improve predictability. The objective is to allow, as much as possible, continuous vertical trajectory profiles without impacting negatively on airspace capacity. Given ADS-B (Automatic Dependent Surveillance-Broadcast) intent information, we predict the future state of potential intruder aircraft and use this nominal trajectory as a constraint in the ownship trajectory optimisation process. In it, a continuous multiphase optimal control problem is solved, taking into account spatial and temporal constraints. Additionally, a linearised Kalman filter keeps track of the target by estimating the deviations of its actual trajectory from its nominal trajectory, issuing a warning when an appropriate threshold is exceeded. This may be due to unexpected events, biases in the performance and weather models, wrong parameter assumptions, etc. An illustrative example is given, based on a computer simulation of two hypothetical trajectories in the Barcelona terminal manoeuvring area. The results show how this framework resolves the problem of uncertainties in the trajectory predictions and results in a more efficient conflict resolution.

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Section: Separation Volumementioning

confidence: 99%

Conflict-Free Trajectory Optimization with Target Tracking and Conformance Monitoring

Vilardaga¹,

Prats²,

Duan³

et al. 2018

Journal of Aircraft

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“…7 Thus, a cost function is chosen that attempts to maximize the amount of control margin during flight.…”

Section: Cost Functionsmentioning

confidence: 99%

Optimal trajectory for time-on-target of a guided projectile using direct collocation method

Chen

Wang

2013

Proceedings 2013 International Conference on Mechatronic Sciences, Electric Engineering and Computer (MEC)

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The problem of multi-phase trajectory optimization of a guided projectile is studied. The objective of this paper is to determine an optimal steering law for a low lift-to-drag ratio projectile. An optimization performance and path constraint are derived that attempt to control different projectiles which are launched successively impact the terminal target simultaneous. The whole trajectory of each projectile is divided into four phases and formulated as an optimal control problem which is transcribed to a nonlinear programming problem by using Gauss pseudospectral method. The time of flight is chosen as the strictly constraint. Finally, the results illustrate the key features of the optimal trajectory, and demonstrate the effectiveness of Gauss pseudospectral method to trajectory design.

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“…The vehicle with trim-flaps is a kind of medium lift-drag ratio vehicle, which has a simpler structure than that of lift type vehicle. Since the 1990s, scholars like Shui et al [4][5][6][7] have done some studies in conceptual design and return optimal trajectory for vehicles with trim-flaps.…”

Section: Introductionmentioning

confidence: 99%

Optimal Skip Entry Trajectory for Lunar Return Vehicle with Trim-Flaps

Wang

Yao

2017

Mathematical Problems in Engineering

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A medium lift-to-drag ratio lunar return vehicle with trim-flaps is presented in this paper. The trajectory optimization design under heat-rate constrain for skip entry lunar return vehicle is analyzed. The optimization problem with a first-order state constraint is introduced. The trajectory applying the Pontryagin maximum principle under the performance of minimum heat is optimized, and the optimal expression of lift coefficient is derived. The simulation studies show that this research method can decrease the heat-rate effectively.

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Optimal Trajectory and Control Generation for Landing of Multiple Aircraft in the Presence of Obstacles

Cited by 14 publications

References 18 publications

Conflict-Free Trajectory Optimization with Target Tracking and Conformance Monitoring

Conflict-Free Trajectory Optimization with Target Tracking and Conformance Monitoring

Optimal trajectory for time-on-target of a guided projectile using direct collocation method

Optimal Skip Entry Trajectory for Lunar Return Vehicle with Trim-Flaps

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