Trajectory optimization of aerial slung load release for piloted helicopters

Wang, Luofeng; Chen, Renliang; Yan, Xufei

doi:10.1016/j.cja.2020.07.025

Cited by 4 publications

(1 citation statement)

References 16 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Among the trajectory optimization algorithms developed in recent years, including indirect methods and direct methods [9][10][11][12][13][14], convex optimization algorithms have great advantages in onboard aerospace applications because the convex optimization problem can be solved in polynomial time with no need for initial guesses supplied by the user [15]. However, most of the original trajectory optimization problems are infinite and nonconvex, which cannot be solved by convex optimization methods directly [16].…”

Section: Introductionmentioning

confidence: 99%

A Convex Approach for Trajectory Optimization of Super-Synchronous-Transfer-Orbit Large Launch Systems with Time-Position Constraints

Sun

Chen

et al. 2022

International Journal of Aerospace Engineering

View full text Add to dashboard Cite

This paper presents a trajectory optimization algorithm for super-synchronous-transfer-orbit (SSTO) large launch systems by convex optimization. The payload of SSTO launch systems is typically a geostationary equatorial orbit (GEO) satellite, and the time and position of orbital injection are constrained, which is quite different from the case of general satellites. In this paper, the optimal control problem of SSTO large launch systems is formulated considering the terminal constraints including orbital elements and the time-position equation. To improve the computational performance of the algorithm, the terminal orbital element constraints are expressed in the perifocal coordinate system with second-order equations. And then, several convexification techniques and their modified strategies are applied to transform the original trajectory optimization problem into a series of convex optimization problems, which can be solved iteratively with high accuracy and computational efficiency. Considering the time-position constraint of the payload, the flight time updater design method is proposed to correct the error of time during the flight, which lays solid foundation for the subsequent flight phase, guaranteeing that the GEO satellite settles into the required position. Finally, simulation results indicate the high efficiency and accuracy and strong robustness of the proposed algorithm in different special situations including engine failure and time delay. The algorithm proposed in this paper has great development potential and application prospect in onboard trajectory optimization of SSTO launch missions and similar situations.

show abstract