An evolutionary discretized Lambert approach for optimal long-range rendezvous considering impulse limit

Shirazi, Abolfazl; Ceberio, Josu; Lozano, José A.

doi:10.1016/j.ast.2019.105400

Cited by 15 publications

(11 citation statements)

References 33 publications

(30 reference statements)

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Different geosynchronous orbits are simulated and the results are evaluated regarding the differences in orbital elements. Then, a trajectory optimization problem for long-range space rendezvous is analyzed and simulated to demonstrate the practicality of the proposed application [35]. Finally, comparisons are illustrated between the results from HOMA and two other space orbit simulation software packages including PROPAT and STK.…”

Section: Simulationmentioning

confidence: 99%

See 1 more Smart Citation

Simulation Framework for Orbit Propagation and Space Trajectory Visualization

Shirazi

Ceberio

Lozano

2021

IEEE Aerosp. Electron. Syst. Mag.

Self Cite

View full text Add to dashboard Cite

In this paper, an interactive tool for simulation of satellites dynamics and autonomous spacecraft guidance is presented. Different geopotential models for orbit propagation of Earth-orbiting satellites are provided, which consider Earth's gravitational field with various accuracies. The presented software is a 3D visualization platform for space orbit simulation with analytical capabilities through various modules. Taking advantage of a graphical user interface, it can evaluate, analyze and illustrate the motion of satellite based on different orbit propagation schemes. Several cases of satellites and autonomous spacecraft in the space rendezvous mission are simulated regarding different propagation models to demonstrate the performance of the application in space mission analysis, ground track visualization and trajectory optimization. Results are validated by comparing with other state-of-the-art tools, such as AGI System Toolkit (STK).

show abstract

Section: Simulationmentioning

confidence: 99%

“…In this section, a multi-impulse trajectory optimization problem is optimized and simulated to illustrate the capability of this tool. An evolutionary algorithm based on a discretized Lambert problem as described in [35] is linked to the platform to solve a long-range space rendezvous problem considering impulse limit.…”

Section: Autonomous Space Rendezvousmentioning

confidence: 99%

Simulation Framework for Orbit Propagation and Space Trajectory Visualization

Shirazi

Ceberio

Lozano

2021

IEEE Aerosp. Electron. Syst. Mag.

Self Cite

View full text Add to dashboard Cite

show abstract

“…The proposed implementation is firstly validated on a test case proposed by Shirazi et al [11] and then employed in the context of a future Mars Sample Return mission. For the last case, two optimal rendezvous trajectories that allow the SRO to capture the OS will be computed taking advantage of the developed optimization framework.…”

Section: Optimal Control Problemmentioning

confidence: 99%

“…Before being applied in the context of a future Mars Sample Return mission, the algorithm developed in chapter 3 is tested on a reference case proposed by Shirazi et al [11]. Two non-coplanar, elliptical Earth orbits are selected and an optimal solution is sought for the most efficient rendezvous trajectory between the two spacecrafts.…”

Section: Numerical Examplementioning

confidence: 99%

Optimal rendezvous trajectory between Sample Return Orbiter and Orbiting Sample Container in a Mars Sample Return mission

Fossà

Bettanini

2020

Acta Astronautica

View full text Add to dashboard Cite

A trajectory optimization problem is examined to determine the most fuel-efficient rendezvous trajectory between spacecrafts in different orbits. To explore the whole range of feasible solutions, the wait time and the total time of flight are treated as free parameters while the initial and transfer orbits are not restricted to a particular one. To improve the accuracy of the numerical computation, the Kepler's time of flight equation is posed in terms of universal variables while the Lagrange coefficients are employed to obtain three-dimensional orbit information. The optimal rendezvous trajectory is then obtained enforcing the determined necessary conditions to be satisfied given only the initial state vectors of the involved spacecrafts. Two optimal rendezvous trajectories between a Sample Return Orbiter (SRO) and an Orbiting Sample Container (OS) are computed in the context of a future Mars Sample Return mission to demonstrate the reliability of the proposed solution. Finally, orbital perturbations due to the real shape of planet Mars and the solar radiation pressure are taken into account to determine the additional energy required to compensate these perturbations while performing the rendezvous manoeuvre.

show abstract

“…Karthikeyan et al proposed a two-pulse maneuver strategy to meet the constraints of reentry terminal time and flight-direction angle based on the Lambert problem [7]. Aiming at the constraint of orbital maneuvering pulse size, Shirazia et al characterized the multipulse rendezvous problem as a multisegment two-point boundary value problem [8].…”

Section: Introductionmentioning

confidence: 99%

Multisatellite Flyby Inspection Trajectory Optimization Based on Constraint Repairing

et al. 2021

View full text Add to dashboard Cite

With the rapid development of on-orbit services and space situational awareness, there is an urgent demand for multisatellite flyby inspection (MSFI) that can obtain information about a large number of space targets with little fuel consumption in a short time. There are two kinds of constraints, namely inspection constraints (ICs) at each flyby point and transfer process constraints (TPCs) in the actual mission. Further considering the influence of discrete and continuous variables such as inspection sequence, time, and maneuver scheme, it is complex and difficult to solve MSFI. To optimize it efficiently, the task flow and the problem model are defined firstly. Then, the algorithm framework based on constraint repairing is given, which contains repair methods of the ICs and the TPCs. Finally, the proposed method is compared with the nonrepair optimization method in two numerical examples. The results indicate that when the constraints are hard to meet, it is better and more efficient than the nonrepair method.

show abstract

An evolutionary discretized Lambert approach for optimal long-range rendezvous considering impulse limit

Cited by 15 publications

References 33 publications

Simulation Framework for Orbit Propagation and Space Trajectory Visualization

Simulation Framework for Orbit Propagation and Space Trajectory Visualization

Optimal rendezvous trajectory between Sample Return Orbiter and Orbiting Sample Container in a Mars Sample Return mission

Multisatellite Flyby Inspection Trajectory Optimization Based on Constraint Repairing

Contact Info

Product

Resources

About