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COBEM 2023
27th International Congress of Mechanical Engineering
STUDY OF APPROXIMATION MANEUVERS WITH CLOSED-LOOP CONTROL FOR A SPACECRAFT OVER ASTEROIDS
Submission Author:
Luan Henrique Glasser , SP , Brazil
Co-Authors:
Luan Henrique Glasser, Evandro Marconi Rocco, Marcelo Lisboa Mota
Presenter: Luan Henrique Glasser
doi://10.26678/ABCM.COBEM2023.COB2023-2259
Abstract
In the last forty years, asteroid exploration came into focus of nations as United States, China, Japan and also to European Union. An evidence of that is the number of asteroid missions that happened during this period, among which the Hayabusa and the Osiris-REX can be found. In this time, the complexity of the missions have evolved from distant flybys, to sample-return, to asteroid deflection missions, so that, consequently, have also evolved sensors, actuators, overall equipment, instruments and, by extension, the spacecraft. Asteroid exploration is one of the space science, engineering and technology frontiers. Mastering this knowledge and ability is a key for the past, in order to understand Solar System formation and, maybe, the origin of life, but also for the future, making space more accessible for humankind. The challenge imposed to a spacecraft for it to move in an interplanetary flight, approach an asteroid and land is central in this discussion. The objective of this work was to study procedures for approaching a spacecraft to the asteroids (8567) 1996 HW1 and (1580) Betulia, in order to compute maneuvers with less velocity increment usage, to find landing conducive conditions and to simulate the complete maneuvers of approximation and landing. The Spacecraft Trajectory Simulator is a simulation environment dedicated to study spacecraft dynamics and trajectories, capable of performing guidance and control, and it was the main tool used to realize this work. As research results, this work has produced two maps, one for each asteroid, of landing conducive conditions. The maps could be used in mission analysis, to select landing conducive conditions and as input for mission design. This work has also demonstrated the usage procedure of those maps, successfully computed the consumption of velocity increments for different maneuvers and simulated complete maneuvers of approximation and landing.
Keywords
spacecraft dynamics, PID controller, orbital maneuvers, asteroids, Landing
