Evaluation of an optimal guidance algorithm for aero-assisted orbit transfer

1992 ◽  
Author(s):  
N. MELAMED ◽  
A. CALISE
Keyword(s):  
Orbit Transfer ◽  
Optimal Guidance ◽  
Guidance Algorithm

scholarly journals Optimal Aerial Guidance in General Wind Fields

2020 ◽  
Author(s):  
Ely Paiva ◽  
Guilherme Pereira
Keyword(s):  
Analytical Solution ◽  
Minimum Principle ◽  
Wind Fields ◽  
Control Effort ◽  
Optimal Guidance ◽  
Guidance Algorithm ◽  
Point To Point ◽  
Iterative Procedures ◽  
Derivatives Of ◽  
Wind Perturbation

<div>This paper presents an optimal guidance approach</div><div>for a UAV point-to-point navigation in 2D, under wind perturbation, with a general desired airspeed profile. A cost function weighting the travel time and the control effort is minimized through the Pontryagin’s Minimum Principle, involving the derivatives of the airspeed velocities. Two iterative procedures for a guidance algorithm under general wind fields were developed, including an analytical solution for the optimal heading in minimum-time paths. Different cases from the literature are compared and a hard wind scenario test is presented.</div>

Optimization of aerospace aircraft guidance to the landing area

2021 ◽  
Author(s):  
A.Yu. Melnikov ◽  
S.N. Ilukhin
Keyword(s):  
Maximum Principle ◽  
Boundary Value ◽  
Flight Simulation ◽  
Motion Model ◽  
Algorithm Efficiency ◽  
Simulation Procedure ◽  
Optimal Guidance ◽  
Guidance Algorithm ◽  
The Pontryagin Maximum Principle ◽  
Significant Factors

The article considers a technique for constructing an optimal guidance procedure for an aerospace aircraft. The technique is based on the adaptation of the Pontryagin maximum principle for the considered class of problems. At the same time the guidance accuracy is ensured by solving a boundary value problem, which is periodically performed during the flight. The developed procedure for predicting the final parameters of the optimal flight according to a simplified motion model is presented, which also makes it possible to determine the value of the actual miss. A detailed mathematical description of the proposed technique is given. The feasibility of the proposed technique is ensured by minimizing the amount of computational operations. The guidance algorithm efficiency is illustrated by a numerical example with a flight simulation procedure taking into account all significant factors. The paper also provides examples of solving boundary value problems and the results of modeling the optimal guidance.

scholarly journals Optimal Aerial Guidance in General Wind Fields

2020 ◽  
Author(s):  
Ely Paiva ◽  
Guilherme Pereira
Keyword(s):  
Analytical Solution ◽  
Minimum Principle ◽  
Wind Fields ◽  
Control Effort ◽  
Optimal Guidance ◽  
Guidance Algorithm ◽  
Point To Point ◽  
Iterative Procedures ◽  
Derivatives Of ◽  
Wind Perturbation

<div>This paper presents an optimal guidance approach</div><div>for a UAV point-to-point navigation in 2D, under wind perturbation, with a general desired airspeed profile. A cost function weighting the travel time and the control effort is minimized through the Pontryagin’s Minimum Principle, involving the derivatives of the airspeed velocities. Two iterative procedures for a guidance algorithm under general wind fields were developed, including an analytical solution for the optimal heading in minimum-time paths. Different cases from the literature are compared and a hard wind scenario test is presented.</div>

On-line Ascent Phase Trajectory Optimal Guidance Algorithm based on Pseudo-spectral Method and Sensitivity Updates

2015 ◽  
Vol 68 (6) ◽  
pp. 1056-1074 ◽  
Author(s):  
Da Zhang ◽  
Lei Liu ◽  
Yongji Wang
Keyword(s):  
Spectral Method ◽  
Direct Method ◽  
Lipschitz Constant ◽  
Model Parameters ◽  
Hypersonic Vehicles ◽  
Air Breathing ◽  
Optimal Guidance ◽  
Guidance Algorithm ◽  
Pseudo Spectral Method ◽  
Pseudo Spectral

The objective of this paper is to investigate an online method to generate an optimal ascent trajectory for air-breathing hypersonic vehicles. A direct method called the Pseudo-spectral method shows promise for real-time optimal guidance. A significant barrier to this optimisation-based control strategy is computational delay, especially when the solution time of the non-linear programming problem exceeds the sampling time. Therefore, an online guidance algorithm for an air-breathing hypersonic vehicles with process constraints and terminal states constraints is proposed based on the Pseudo-spectral method and sensitivity analysis in this paper, which can reduce online computational costs and improve performance significantly. The proposed ascent optimal guidance method can successively generate online open-loop suboptimal controls without the design procedure of an inner-loop feedback controller. Considering model parameters' uncertainties and external disturbance, a sampling theorem is proposed that indicates the effect of the Lipschitz constant of the dynamics on sampling frequency. The simulation results indicate that the proposed method offers improved performance and has promising ability to generate an optimal ascent trajectory for air-breathing hypersonic vehicles.

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