A new shape-based multiple-impulse strategy for coplanar orbital maneuvers

Shakouri, Amir; Kiani, Maryam; Pourtakdoust, Seid H.

doi:10.1016/j.actaastro.2019.05.004

Cited by 7 publications

(4 citation statements)

References 39 publications

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“…Therefore, rapid initial trajectory design is very important for trajectory optimization. And SB methods are presented in initial low-thrust trajectory design due to the rapidity of their calculations [13]- [23]. Recently, the FFS approximation of the trajectory shape was developed [24]- [28].…”

Section: Introductionmentioning

confidence: 99%

Fast Cooperative Trajectory Optimization for Close-Range Satellite Formation Using Bezier Shape-Based Method

Fan

Huo

et al. 2020

IEEE Access

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Close-range formation flying of multiple satellites is an important technology for future space missions, where formation reconfiguration is a very important field and needs to design suitable flight paths and consider the risk of collisions between satellites. This paper uses the Bezier shape-based (SB) method to rapidly generate the low-thrust collision-avoidance flight paths in the formation reconfiguration. The reconfiguration process of two satellite formations is considered and compared with the finite Fourier series (FFS) method. The simulation results show that the Bezier method spends less computation time to obtain better performance index than the FFS method. In order to verify the applicability of the results obtained by the Bezier method to a direct solver, the results are applied to the Gauss pseudospectral method (GPM) solver as an initial guess. The results show that the Bezier method can take a short time to design suitable initial collision-avoidance flight paths for an direct optimization solver. This is very important for the rapid feasibility evaluation of numerous flight scenarios at the stage of initial mission design and onboard flight paths generation. INDEX TERMS Bezier shape-based method, close-range satellites formation, collision-avoidance, low-thrust trajectory approximation, preliminary mission analysis.

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Section: Introductionmentioning

confidence: 99%

Fast Cooperative Trajectory Optimization for Close-Range Satellite Formation Using Bezier Shape-Based Method

Fan

Huo

et al. 2020

IEEE Access

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“…Shape-based approaches are the other popular trajectory design methods that are applicable in both continuous and impulsive transfer types [28]. The popularity of these approaches is because they reduce the computational costs by imposing geometric constraints on the trajectories [29,30]. The solution to the trajectory optimization problem can be achieved from two different approaches, i.e., analytical or numerical.…”

Section: On-orbit Servicingmentioning

confidence: 99%

Workspace Control of Free-Floating Space Manipulators for Implementation in a Novel On-Orbit Servicing Mission Architecture

Rousso¹

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An industrialized On-Orbit Servicing (OOS) mission architecture is proposed in this thesis which signifies the role of space manipulators in performing OOS missions. This mission architecture summarizes a procedure for OOS mission design based on a series of multi-objective optimization problems. To enhance proximity operations, it is concluded that the existence of an output tracking control system for space manipulators is beneficial. This thesis develops an output tracking controller to control the end-effector pose of an N-link free-floating space manipulator, with non-zero momentum. We employ feedback linearization on the Lie algebra of the Special Euclidean group SE(3) to remove the nonlinear influence from the system's dynamics and momentum in the controlled end-effector motion. Space manipulators are modelled as open-chain rigid multi-body systems, connected by either single or multi degree of freedom joints. The dynamics and kinematics of free-floating space manipulators are formulated on SE(3) using the exponential parameterization of screw motions. Multi-degree of freedom joints are modelled as the combination of the joints' individual exponential screw motion mappings to describe their motions as homogeneous transformations. The free-floating systems' equations of motion are obtained through an Euler-Lagrange derivation and decoupled into the base and manipulator motions. The conservation of linear and angular momentum is then considered as an affine nonholonomic constraint to the system, allowing for the dynamic reduction of a space manipulator system with conserved non-zero momentum. Due to the system's free-floating nature, the equations of motion are restricted to the manipulator's joint space which defines the region of controlled states.Two control cases are considered in this thesis, the first involving control over the output's linear motion and the second considering control over the end-effector pose. The first control case performs feedback linearization on R 3 where the resulting linear end-effector motion is controlled by a classical PID controller defined to impart a critically damped response in the error dynamics. For full pose control, feedback linearization is employed on se(3) for subsequent control using a modified feedforward, feedback PID control structure I first and foremost would like to extend my significant gratitude to my supervisor Dr. Robin Chhabra for providing me with constant support and the wonderful research experience. Aside from the tremendous technical insight and knowledge you have shared with me, you have also been a figure of compassion, perseverance and professionalism for which I very much appreciate. It has been a pleasure to conduct my research under your supervision. I would also like to acknowledge my colleagues in the ASRoM lab who have given their support and feedback in my research and have shared their friendship.I cannot describe the appreciation and love I have for my mom, Maria, my dad, Gilles, and my brother, Chris. To my parents in particular, th...

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“…The distinguished feature of shape-based approaches is having fewer design variables comparing to their counterparts that do not consider constraints. Shakouri et al propose a set of constraint equations to generate multi-impulse shape-based transfer trajectories between eccentric orbits in a central gravity [20]. A favorite geometry for designing continuous Figure 2.2: Velocity increments applied to a trajectory shape-based maneuvers is the use of spiral functions [21].…”

Section: Transfer Typementioning

confidence: 99%

“…A trajectory is called smooth, if the curves before and after an impulse intersect and share an identical tangent direction at the intersection point [69]. The smoothness condition at the intersection of any two sequential arcs can be formulated in the polar coordinates as follows [20]:…”

Section: Multi-impulse Smooth Trajectoriesmentioning

confidence: 99%

An Evolutionary Framework for Multi-Objective Trajectory Design and Robust Model Predictive Control in Long-Range Rendezvous Missions

Samsam¹

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This thesis presents an optimization architecture for on-orbit servicing mission design in the long-range rendezvous phase. We develop a methodology to generate Pareto Optimal trajectories for long-range rendezvous of a servicing satellite with a moving target. The methodology employs a multi-impulse shape-based trajectory planning algorithm for in-plane orbit transfer, based on the two-body problem. We first derive the necessary and sufficient conditions that determine the set of smooth impulsive trajectories connecting the servicing satellite to the orbiting target. The Pareto Optimal trajectories from this set are then obtained using a constrained multiobjective optimization algorithm developed based on the Non-dominated Sorting Genetic Algorithm-II (NSGA-II). Transfer time and control effort are the two Pareto cost functions that are considered in the multi-objective optimization. To reduce the risk of collision in populated orbits and to remain in an orbital regime, we include restrictions on orbital elements as part of the constraints. Further, a maximum available impulse is considered as an upper-bound for velocity changes in an impulsive trajectory. The number of impulses along with the location of the first impulse in the parking orbit and the orbital parameters of the intermediate orbits form the set of design variables. We demonstrate the superiority of the developed trajectory planner by comparing its results with those obtained from another multi-objective evolutionary algorithm called the Multi-Objective Genetic Algorithm and an optimal Lambert approach. In an on-orbit servicing mission, a solution from the Pareto frontier set of optimal trajectories may be selected based on the mission requirements.To robustly follow the generated reference trajectories in a J 2 -perturbed orbital environment, we propose a Nonlinear Model Predictive Control (NMPC) scheme. The control signals are velocity increments at the time of applying each impulse, and the variable horizon is considered to be the time difference between every two impulses in the reference trajectory. To avoid singularities, the equinoctial orbital elements are used in the process model that includes the secular and first-order long-periodic effects iii

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A new shape-based multiple-impulse strategy for coplanar orbital maneuvers

Cited by 7 publications

References 39 publications

Fast Cooperative Trajectory Optimization for Close-Range Satellite Formation Using Bezier Shape-Based Method

Fast Cooperative Trajectory Optimization for Close-Range Satellite Formation Using Bezier Shape-Based Method

Workspace Control of Free-Floating Space Manipulators for Implementation in a Novel On-Orbit Servicing Mission Architecture

An Evolutionary Framework for Multi-Objective Trajectory Design and Robust Model Predictive Control in Long-Range Rendezvous Missions

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