Guidance strategies for near-optimum take-off performance in a windshear

Miele, A.; Wang, T; Melvin, W. W.

doi:10.1007/bf00938475

Cited by 65 publications

(18 citation statements)

References 26 publications

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“…However, the number of control variables reduces to one (the angle of attack a) if the power setting ft is specified in advance. The quantities defined by the analytical relations (6) can be computed a posteriori once the values of jc, -h, V, y, a, and ft are known.…”

Section: A Equations Of Motionmentioning

confidence: 99%

Optimization and acceleration guidance of flight trajectories in a windshear

Miele

Wang

Melvin

1987

Journal of Guidance, Control, and Dynamics

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This paper is concerned with guidance strategies for near-optimum performance in a windshear. The takeoff problem is considered with reference to flight in a vertical plane. In addition to the horizontal shear, the presence of a downdraft is assumed. First, trajectories for optimum performance in a windshear are determined for different windshear models and intensities. Use is made of the methods of optimal control theory in conjunction with the dual sequential gradient-restoration algorithm (DSGRA) for optimal control problems. In this approach, global information on the wind flowfield is needed. Then, guidance strategies for near-optimum performance in a windshear are developed, starting from the optimal trajectories. Specifically, an acceleration guidance scheme based on the relative acceleration is presented in both analytical and feedback control forms. In this approach, local information on the wind flowfield is needed. Numerical experiments show that the acceleration guidance scheme produces trajectories that are quite close to the optimum trajectories. In addition, the near-optimum trajectories are superior to the trajectories arising from alternative guidance schemes. An important characteristic of the acceleration guidance scheme is its simplicity. Indeed, this guidance scheme is implementable if local information on the windshear, the downdraft, and the state of the aircraft is available. ARL-acceleration of gravity, ft s~2 --altitude, ft s gain coefficient = lift force, Ib s mass, Ib ft -1 s 2 = reference surface, ft 2 = thrust force, Ib = relative velocity, ft s" 1 = absolute velocity, ft s" 1 = mg = weight, Ib = wind velocity, ft s~l = /*-cpmponent of wind velocity, ft s" 1 -^-component of wind velocity, ft s" 1 = horizontal distance, ft -relative angle of attack, rad = absolute angle of attack, rad = engine power setting = relative path inclination, rad = absolute path inclination, rad = thrust inclination, rad = pitch attitude angle, rad = air density, Ib ft" 4 s 2

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Section: A Equations Of Motionmentioning

confidence: 99%

Optimization and acceleration guidance of flight trajectories in a windshear

Miele

Wang

Melvin

1987

Journal of Guidance, Control, and Dynamics

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“…In this connection, we can refer to papers [6,13,[18][19][20]22,23,29] where optimal control theory, robust control techniques, and differential game theory have been used to design appropriate controls. Both the case of known wind velocity field and the case of unknown wind disturbances have been considered.…”

Section: Introductionmentioning

confidence: 99%

Aircraft Control During Cruise Flight in Windshear Conditions: Viability Approach

et al. 2017

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This paper addresses the analysis of aircraft control capabilities during the cruise phase (flying at the established level with practically constant configuration and speed) in the presence of windshears. The study uses a point-mass aircraft model describing flight in a vertical plane. The problem is formulated as a differential game against wind disturbances. The first player, autopilot, controls the angle of attack and the power setting, whereas the second player, wind, produces dangerous gusts. The state variables of the model are subjected to constraints expressing aircraft safety conditions. Namely, the altitude, path inclination, and velocity are constrained. Viability theory is used to find the so-called viability kernel, the maximal subset of the state constraint where the aircraft trajectories can remain arbitrary long if the first player utilizes an appropriate feedback control, and the second player generates any admissible disturbances. The computations are based on grid methods developed by the authors and implemented on a multiprocessor computer system.

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“…Other investigations have been concemed with the design of controllers to enhance the chances for survival while encountering windshear during takeoff or landing. Primary among these have been the pioneering studies of Miele; e.g., see [2], [7]- [9] and many others referenced in [lo]. The socalled simplified gamma guidance scheme, espoused by Miele, is one based on attaining "near-optimal'' trajectories in the presence of a given windshear structure; it has been shown to have good survival capability in the prescribed windshear model.…”

Section: Introductionmentioning

confidence: 99%