Deflecting small asteroids using laser ablation: Deep space navigation and asteroid orbit control for LightTouch2 Mission

Massimo Vetrisano, Joao Branco, Joan-Pau Sanchez Cuartielles, Daniel Garcia Yarnoz, Massimiliano Vasile

Research output: Contribution to conferencePaper

2 Citations (Scopus)

Abstract

This paper presents a low-cost, low mass, mission design to successfully intercept and deflect a small and faint, 4 m in diameter asteroid. Intended to be launched after 2025, the laser-ablating mission, LightTouch2 will be used to deflect the orbit of the asteroid by at least 1 m/s. This will be achieved with a total mission lifetime of less than three years. Analysis includes the initial approach of the spacecraft, the operations of the laser at an optimal spacecraft-to-asteroid distance of 50 m and the relative orbit of the spacecraft that flies in formation with the asteroid. Analysis includes line-of-sight measurements with radiometric tracking from ground station to improve the trajectory estimate and observability of the spacecraft, collision avoidance and mapping strategies. The spacecraft will also need optimal discrete control. This is achieved by impulse-bit manoeuvres used to account for the perturbations caused by the resultant thrust on the asteroid, plume impingement, laser recoil and solar radiation pressure. The spacecraft controls its trajectory within a 1 m box from the reference trajectory to enable the laser to optimally focussing the laser beam. The proposed approach uses an unscented Kalman filter to estimate the relative spacecraft-asteroid position, velocity and perturbative acceleration.

Conference

ConferenceAIAA Guidance, Navigation and Control Conference 2013
CountryUnited States
CityBoston, Massachusetts
Period19/08/1322/08/13

Fingerprint

Asteroids
Laser ablation
Spacecraft
Navigation
Orbits
Trajectories
Lasers
Observability
Collision avoidance
Laser radiation
Solar radiation
Kalman filters
Laser beams

Keywords

  • near Earth objects
  • asteroid deflection
  • asteroid orbit control
  • LightTouch2 Mission
  • laser ablation
  • deep space manoeuvres

Cite this

Vetrisano, M., Branco, J., Sanchez Cuartielles, J-P., Garcia Yarnoz, D., & Vasile, M. (2013). Deflecting small asteroids using laser ablation: Deep space navigation and asteroid orbit control for LightTouch2 Mission. Paper presented at AIAA Guidance, Navigation and Control Conference 2013, Boston, Massachusetts, United States. https://doi.org/10.2514/6.2013-5250
Vetrisano, Massimo ; Branco, Joao ; Sanchez Cuartielles, Joan-Pau ; Garcia Yarnoz, Daniel ; Vasile, Massimiliano. / Deflecting small asteroids using laser ablation : Deep space navigation and asteroid orbit control for LightTouch2 Mission. Paper presented at AIAA Guidance, Navigation and Control Conference 2013, Boston, Massachusetts, United States.21 p.
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Vetrisano, M, Branco, J, Sanchez Cuartielles, J-P, Garcia Yarnoz, D & Vasile, M 2013, 'Deflecting small asteroids using laser ablation: Deep space navigation and asteroid orbit control for LightTouch2 Mission' Paper presented at AIAA Guidance, Navigation and Control Conference 2013, Boston, Massachusetts, United States, 19/08/13 - 22/08/13, . https://doi.org/10.2514/6.2013-5250

Deflecting small asteroids using laser ablation : Deep space navigation and asteroid orbit control for LightTouch2 Mission. / Vetrisano, Massimo; Branco, Joao; Sanchez Cuartielles, Joan-Pau; Garcia Yarnoz, Daniel; Vasile, Massimiliano.

2013. Paper presented at AIAA Guidance, Navigation and Control Conference 2013, Boston, Massachusetts, United States.

Research output: Contribution to conferencePaper

TY - CONF

T1 - Deflecting small asteroids using laser ablation

T2 - Deep space navigation and asteroid orbit control for LightTouch2 Mission

AU - Vetrisano, Massimo

AU - Branco, Joao

AU - Sanchez Cuartielles, Joan-Pau

AU - Garcia Yarnoz, Daniel

AU - Vasile, Massimiliano

PY - 2013/8/19

Y1 - 2013/8/19

N2 - This paper presents a low-cost, low mass, mission design to successfully intercept and deflect a small and faint, 4 m in diameter asteroid. Intended to be launched after 2025, the laser-ablating mission, LightTouch2 will be used to deflect the orbit of the asteroid by at least 1 m/s. This will be achieved with a total mission lifetime of less than three years. Analysis includes the initial approach of the spacecraft, the operations of the laser at an optimal spacecraft-to-asteroid distance of 50 m and the relative orbit of the spacecraft that flies in formation with the asteroid. Analysis includes line-of-sight measurements with radiometric tracking from ground station to improve the trajectory estimate and observability of the spacecraft, collision avoidance and mapping strategies. The spacecraft will also need optimal discrete control. This is achieved by impulse-bit manoeuvres used to account for the perturbations caused by the resultant thrust on the asteroid, plume impingement, laser recoil and solar radiation pressure. The spacecraft controls its trajectory within a 1 m box from the reference trajectory to enable the laser to optimally focussing the laser beam. The proposed approach uses an unscented Kalman filter to estimate the relative spacecraft-asteroid position, velocity and perturbative acceleration.

AB - This paper presents a low-cost, low mass, mission design to successfully intercept and deflect a small and faint, 4 m in diameter asteroid. Intended to be launched after 2025, the laser-ablating mission, LightTouch2 will be used to deflect the orbit of the asteroid by at least 1 m/s. This will be achieved with a total mission lifetime of less than three years. Analysis includes the initial approach of the spacecraft, the operations of the laser at an optimal spacecraft-to-asteroid distance of 50 m and the relative orbit of the spacecraft that flies in formation with the asteroid. Analysis includes line-of-sight measurements with radiometric tracking from ground station to improve the trajectory estimate and observability of the spacecraft, collision avoidance and mapping strategies. The spacecraft will also need optimal discrete control. This is achieved by impulse-bit manoeuvres used to account for the perturbations caused by the resultant thrust on the asteroid, plume impingement, laser recoil and solar radiation pressure. The spacecraft controls its trajectory within a 1 m box from the reference trajectory to enable the laser to optimally focussing the laser beam. The proposed approach uses an unscented Kalman filter to estimate the relative spacecraft-asteroid position, velocity and perturbative acceleration.

KW - near Earth objects

KW - asteroid deflection

KW - asteroid orbit control

KW - LightTouch2 Mission

KW - laser ablation

KW - deep space manoeuvres

UR - https://www.aiaa.org/boston2013/

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DO - 10.2514/6.2013-5250

M3 - Paper

ER -

Vetrisano M, Branco J, Sanchez Cuartielles J-P, Garcia Yarnoz D, Vasile M. Deflecting small asteroids using laser ablation: Deep space navigation and asteroid orbit control for LightTouch2 Mission. 2013. Paper presented at AIAA Guidance, Navigation and Control Conference 2013, Boston, Massachusetts, United States. https://doi.org/10.2514/6.2013-5250