Flight-Path Angle Guidance for Aero-Gravity Assist Maneuvers on Hyperbolic Trajectories

2016 ◽  
Author(s):  
Antonio Mazzaracchio
Keyword(s):  
Flight Path ◽  
Gravity Assist ◽  
Flight Path Angle ◽  
Hyperbolic Trajectories

Effects of Descent Flight-Path Angle on Fuel Consumption of Commercial Aircraft

2019 ◽  
Vol 56 (1) ◽  
pp. 313-323 ◽  
Author(s):  
Enis T. Turgut ◽  
Oznur Usanmaz ◽  
Mustafa Cavcar ◽  
Tuncay Dogeroglu ◽  
Kadir Armutlu
Keyword(s):  
Fuel Consumption ◽  
Flight Path ◽  
Commercial Aircraft ◽  
Flight Path Angle

scholarly journals Finite-Horizon Optimal Tracking Guidance for Aircraft Based on Approximate Dynamic Programming

2019 ◽  
Vol 2019 ◽  
pp. 1-12
Author(s):  
Shizheng Wan ◽  
Xiaofei Chang ◽  
Quancheng Li ◽  
Jie Yan
Keyword(s):  
Dynamic Programming ◽  
Approximate Dynamic Programming ◽  
Least Squares Method ◽  
Flight Path ◽  
Finite Horizon ◽  
Dynamic Programming Method ◽  
Reference Trajectory ◽  
Linear Quadratic ◽  
Optimal Tracking ◽  
Flight Path Angle

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.

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

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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