Back-Stepping Based Flight Path Angle Control Algorithm for Longitudinal Dynamics

Referring to the optimal tracking guidance of aircraft, the conventional time based kinematics model is transformed into a downrange based model by independent variable replacement. The deviations of in-flight altitude and flight path angle are penalized and corrected to achieve high precision tracking of reference trajectory. The tracking problem is solved as a linear quadratic regulator applying small perturbation theory, and the approximate dynamic programming method is used to cope with the solving of finite-horizon optimization. An actor-critic structure is established to approximate the optimal tracking controller and minimum cost function. The least squares method and Adam optimization algorithm are adopted to learn the parameters of critic network and actor network, respectively. A boosting trajectory with maximum final velocity is generated by Gauss pseudospectral method for the validation of guidance strategy. The results show that the trained feedback control parameters can effectively resist random wind disturbance, correct the initial altitude and flight path angle deviations, and achieve the goal of following a given trajectory.

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Optimal perturbation guidance with constraints on terminal flight-path angle and angle of attack

Proceedings of the Institution of Mechanical Engineers Part G Journal of Aerospace Engineering ◽

10.1177/0954410018823472 ◽

2019 ◽

Vol 233 (12) ◽

pp. 4436-4446

Author(s):

Penglei Zhao ◽

Wanchun Chen ◽

Wenbin Yu

Keyword(s):

Optimal Control ◽

Singular Perturbation ◽

Time Scale ◽

Angle Of Attack ◽

Flight Path ◽

Superior Performance ◽

Optimal Perturbation ◽

Optimal Guidance ◽

Flight Path Angle ◽

Guidance Problem

This paper presents the design of a singular-perturbation-based optimal guidance with constraints on terminal flight-path angle and angle of attack. By modeling the flight-control system dynamics as a first-order system, the angle of attack is introduced into the performance index as a state variable. To solve the resulting high-order optimal guidance problem analytically, the posed optimal guidance problem is divided into two sub-problems by utilizing the singular perturbation method according to two time scales: range, altitude, and flight-path angle are the slow time-scale variables while the angle of attack is the fast time-scale variable. The outer solutions are the optimal control of the slow-scale subsystem. Thereafter, by applying the stretching transformation, the fast-scale subsystem establishes the relationships between the outer solutions and acceleration command. Then, the optimal command can be obtained by solving the fast-scale subsystem also using the optimal control theory. The proposed guidance can achieve a near-zero terminal acceleration as well as a small miss distance. The superior performance of the guidance is demonstrated by adequate trajectory simulations.

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Carrier Landing Flight Path Angle Control via Higher-Order Sliding Mode

2014 Sixth International Conference on Intelligent Human-Machine Systems and Cybernetics ◽

10.1109/ihmsc.2014.138 ◽

2014 ◽

Cited By ~ 2

Author(s):

Junfeng Chen ◽

Wei Han ◽

Guang Xu

Keyword(s):

Sliding Mode ◽

Higher Order ◽

Flight Path ◽

Flight Path Angle

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Dynamic conversion of flight path angle commands to body attitude commands

Proceedings of the 2002 American Control Conference (IEEE Cat. No.CH37301) ◽

10.1109/acc.2002.1024807 ◽

2003 ◽

Cited By ~ 5

Author(s):

J.R. Cloutier ◽

D.T. Stansbery

Keyword(s):

Flight Path ◽

Body Attitude ◽

Flight Path Angle

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Dispersion reduction of artillery rockets guided by flight path steering method

The Aeronautical Journal ◽

10.1017/aer.2016.4 ◽

2016 ◽

Vol 120 (1225) ◽

pp. 435-456 ◽

Cited By ~ 1

Author(s):

S. Mandić

Keyword(s):

Measurement Errors ◽

Flight Path ◽

Guidance System ◽

Lateral Acceleration ◽

Dominant Factor ◽

Measurement Unit ◽

Impact Point ◽

Angle Correction ◽

Flight Path Angle ◽

The Impact

ABSTRACTArtillery rockets are sensitive to disturbances (total impulse variation, wind, thrust misalignment, etc.). As the range of ground-to-ground rockets increases, the accuracy of free flight rockets decreases. Requirements for the increase of the range and minimisation of the impact point dispersions can be solved by adding guidance and control systems to rockets. Based on the differences between the measured flight parameters and the calculated parameters for the nominal trajectory, the flight path angle correction algorithm is obtained by adding the correction to the nominal value. The flight path steering guidance system with lateral acceleration autopilot in the inner loop, is used for the guidance of hypothetical artillery rockets. The guidance algorithm given in this paper eliminates the time correction due to rocket velocity variations. Efficiency of the proposed algorithm is illustrated by numerical simulation. There is no practical influence of the external disturbances on impact point dispersion. It is also shown that the measurement errors of the inertial measurement unit are the dominant factor affecting impact point dispersion of artillery rockets modified by adding a guidance system based on the flight path steering method.

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