Non-linear pulsed guidance for asteroid close-proximity operations

Roberto Furfaro, John N. Kidd, Daniel R. Wibben

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Abstract

Autonomous close proximity operations (hovering, landing, Touch-And-Go maneuvers) in the low-gravity environment exhibited by asteroids is particularly challenging. A set of non-linear, pulsed guidance algorithms have been developed for spacecraft that are required to execute autonomous closed-loop guidance to a designated point on the asteroid environment. The guidance algorithms development rely on the definition of a Lyapunov-like descent function that has the property of being negative definite along the trajectory defining the motion of the spacecraft. More specifically, we have defined a) a quickest descent pulsed guidance, where at each point along the guided trajectory, one selects a combination of thrusters (on-off mode) that makes the derivative of the descent function as negative as possible and b) a least effort pulsed guidance where one selects the combination of thrusters that ensure the minimum number of pulsing along the guided trajectory. The derived pulsed guidance laws require information about the current state and the target state and generates a class of feedback trajectories that have a built-in proof of global stability. Guidance simulations in asteroid dynamical environment modeling the spacecraft motion around 433 Eros show that the guidance approach is suitable for autonomously targeting positions and velocity during close-proximity operations.

Original languageEnglish (US)
Title of host publicationAdvances in the Astronautical Sciences
PublisherUnivelt Inc.
Pages1701-1716
Number of pages16
Volume150
ISBN (Print)9780877036050
StatePublished - 2014
Event2013 AAS/AIAA Astrodynamics Specialist Conference, Astrodynamics 2013 - Hilton Head Island, SC, United States
Duration: Aug 11 2013Aug 15 2013

Other

Other2013 AAS/AIAA Astrodynamics Specialist Conference, Astrodynamics 2013
CountryUnited States
CityHilton Head Island, SC
Period8/11/138/15/13

Fingerprint

Asteroids
asteroids
asteroid
Electronic guidance systems
proximity
trajectory
Trajectories
Spacecraft
spacecraft
descent
trajectories
Landing
targeting
Gravitation
spacecraft motion
hovering
gravity
Derivatives
Feedback
landing

ASJC Scopus subject areas

  • Aerospace Engineering
  • Space and Planetary Science

Cite this

Furfaro, R., Kidd, J. N., & Wibben, D. R. (2014). Non-linear pulsed guidance for asteroid close-proximity operations. In Advances in the Astronautical Sciences (Vol. 150, pp. 1701-1716). Univelt Inc..

Non-linear pulsed guidance for asteroid close-proximity operations. / Furfaro, Roberto; Kidd, John N.; Wibben, Daniel R.

Advances in the Astronautical Sciences. Vol. 150 Univelt Inc., 2014. p. 1701-1716.

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Furfaro, R, Kidd, JN & Wibben, DR 2014, Non-linear pulsed guidance for asteroid close-proximity operations. in Advances in the Astronautical Sciences. vol. 150, Univelt Inc., pp. 1701-1716, 2013 AAS/AIAA Astrodynamics Specialist Conference, Astrodynamics 2013, Hilton Head Island, SC, United States, 8/11/13.
Furfaro R, Kidd JN, Wibben DR. Non-linear pulsed guidance for asteroid close-proximity operations. In Advances in the Astronautical Sciences. Vol. 150. Univelt Inc. 2014. p. 1701-1716
Furfaro, Roberto ; Kidd, John N. ; Wibben, Daniel R. / Non-linear pulsed guidance for asteroid close-proximity operations. Advances in the Astronautical Sciences. Vol. 150 Univelt Inc., 2014. pp. 1701-1716
@inproceedings{54b2c6c01f3a4212ba0bbb46d730c7ce,
title = "Non-linear pulsed guidance for asteroid close-proximity operations",
abstract = "Autonomous close proximity operations (hovering, landing, Touch-And-Go maneuvers) in the low-gravity environment exhibited by asteroids is particularly challenging. A set of non-linear, pulsed guidance algorithms have been developed for spacecraft that are required to execute autonomous closed-loop guidance to a designated point on the asteroid environment. The guidance algorithms development rely on the definition of a Lyapunov-like descent function that has the property of being negative definite along the trajectory defining the motion of the spacecraft. More specifically, we have defined a) a quickest descent pulsed guidance, where at each point along the guided trajectory, one selects a combination of thrusters (on-off mode) that makes the derivative of the descent function as negative as possible and b) a least effort pulsed guidance where one selects the combination of thrusters that ensure the minimum number of pulsing along the guided trajectory. The derived pulsed guidance laws require information about the current state and the target state and generates a class of feedback trajectories that have a built-in proof of global stability. Guidance simulations in asteroid dynamical environment modeling the spacecraft motion around 433 Eros show that the guidance approach is suitable for autonomously targeting positions and velocity during close-proximity operations.",
author = "Roberto Furfaro and Kidd, {John N.} and Wibben, {Daniel R.}",
year = "2014",
language = "English (US)",
isbn = "9780877036050",
volume = "150",
pages = "1701--1716",
booktitle = "Advances in the Astronautical Sciences",
publisher = "Univelt Inc.",

}

TY - GEN

T1 - Non-linear pulsed guidance for asteroid close-proximity operations

AU - Furfaro, Roberto

AU - Kidd, John N.

AU - Wibben, Daniel R.

PY - 2014

Y1 - 2014

N2 - Autonomous close proximity operations (hovering, landing, Touch-And-Go maneuvers) in the low-gravity environment exhibited by asteroids is particularly challenging. A set of non-linear, pulsed guidance algorithms have been developed for spacecraft that are required to execute autonomous closed-loop guidance to a designated point on the asteroid environment. The guidance algorithms development rely on the definition of a Lyapunov-like descent function that has the property of being negative definite along the trajectory defining the motion of the spacecraft. More specifically, we have defined a) a quickest descent pulsed guidance, where at each point along the guided trajectory, one selects a combination of thrusters (on-off mode) that makes the derivative of the descent function as negative as possible and b) a least effort pulsed guidance where one selects the combination of thrusters that ensure the minimum number of pulsing along the guided trajectory. The derived pulsed guidance laws require information about the current state and the target state and generates a class of feedback trajectories that have a built-in proof of global stability. Guidance simulations in asteroid dynamical environment modeling the spacecraft motion around 433 Eros show that the guidance approach is suitable for autonomously targeting positions and velocity during close-proximity operations.

AB - Autonomous close proximity operations (hovering, landing, Touch-And-Go maneuvers) in the low-gravity environment exhibited by asteroids is particularly challenging. A set of non-linear, pulsed guidance algorithms have been developed for spacecraft that are required to execute autonomous closed-loop guidance to a designated point on the asteroid environment. The guidance algorithms development rely on the definition of a Lyapunov-like descent function that has the property of being negative definite along the trajectory defining the motion of the spacecraft. More specifically, we have defined a) a quickest descent pulsed guidance, where at each point along the guided trajectory, one selects a combination of thrusters (on-off mode) that makes the derivative of the descent function as negative as possible and b) a least effort pulsed guidance where one selects the combination of thrusters that ensure the minimum number of pulsing along the guided trajectory. The derived pulsed guidance laws require information about the current state and the target state and generates a class of feedback trajectories that have a built-in proof of global stability. Guidance simulations in asteroid dynamical environment modeling the spacecraft motion around 433 Eros show that the guidance approach is suitable for autonomously targeting positions and velocity during close-proximity operations.

UR - http://www.scopus.com/inward/record.url?scp=84898963737&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=84898963737&partnerID=8YFLogxK

M3 - Conference contribution

AN - SCOPUS:84898963737

SN - 9780877036050

VL - 150

SP - 1701

EP - 1716

BT - Advances in the Astronautical Sciences

PB - Univelt Inc.

ER -