Safe rendezvous scenario design for geostationary satellites with collocation constraints

Abstract

Rendezvous on the geostationary orbit (GEO) is much more complex than that on the low earth orbit and has a higher critical requirement for safety performance. This paper presents a safe scenario design method for GEO rendezvous proximity missions where the safety Furthermore, an exhaustive analysis is performed to find the dangerous regions of the V-bar keeping positions and the appropriate semi-major axis of the fly-by ellipse, considering the safety requirements of both the target and the collocated satellite. A geometry method is then developed for designing a feasible and suboptimal safe rendezvous scenario. The method is tested by designing four rendezvous scenarios with ±V-bar approach directions respectively in the situations with and without one collocated satellite. Safety performance and velocity increments of the scenarios are compared and a conclusion is reached that the collocated satellite has a significant influence on the scenario design.

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

“…Even so, significant simplifications are still present in the proposed model and the algorithm is not applicable when a highly accurate solution is required. Suitable rendezvous strategies and automated guidance algorithms must be then considered to guarantee a safe manoeuvre and the spacecrafts integrity [18,19]. The aforementioned guidance laws are based on the study of the target and chaser relative dynamics and beyond the scope of the conducted work.…”

Novel Gaussian mixture model based nonsingular terminal sliding mode control for spacecraft close-range proximity with complex shape obstacle

“…During the spacecraft close-range proximity maneuvers, the stringent safety is among the most critical requirements, and hence, it is notable that such complex space missions have motivated the development of collision avoidance technologies. Many researchers [6][7][8][9][10] transformed the collision avoidance problem into a constrained optimization problem and applied optimization algorithms [6][7][8][9][10] to design safe trajectories. However, because of the high computational burden, applications of these methods are limited.…”

Motion planning of spacecraft with obstacle avoidance under low uncertainty using the improved equal-collision-probability-curve and improved linear quadratic regulator strategy

“…Therefore, many engineers and academicians devoted themselves to the motion planning of spacecraft proximity operations with obstacle collision. Moreover, researchers have divided the solution of the collision avoidance problem into the optimization method, [11][12][13][14][15][16] and the analytical control method. [17][18][19][20][21][22][23][24] The first kind of the collision avoidance schemes is established on the optimization theory.…”

“…[17][18][19][20][21][22][23][24] The first kind of the collision avoidance schemes is established on the optimization theory. To apply the optimization algorithm in the collision avoidance problem, many academicians [11][12][13][14][15][16] converted those collision problems into an optimization problem with safe constraint. Subsequently, they utilized the optimization algorithms [11][12][13][14][15][16] to obtain the safe trajectory.…”

“…To apply the optimization algorithm in the collision avoidance problem, many academicians [11][12][13][14][15][16] converted those collision problems into an optimization problem with safe constraint. Subsequently, they utilized the optimization algorithms [11][12][13][14][15][16] to obtain the safe trajectory. For example, an evolutionary multi-objective heuristic algorithm 11 is employed for the optimization problem with multiple object safe constraint.…”