Development of non-linear guidance algorithms for asteroids close-proximity operations

Roberto Furfaro, Brian Gaudet, Daniel Wibben, Jules Simo

Research output: Contribution to conferencePaper

11 Citations (Scopus)

Abstract

In this paper, we discuss non-linear methodologies that can be employed to devise real-time algorithms suitable for guidance and control of spacecrafts during asteroid close-proximity operations. Combination of optimal and sliding control theory provide the theoretical framework for the development of guidance laws that generates thrust commands as function of the estimated spacecraft state. Using a Lyapunov second theorem one can design non-linear guidance laws that are proven to be globally stable against unknown perturbations with known upper bound. Such algorithms can be employed for autonomous targeting of points of the asteroid surface (soft landing , Touch-And-Go (TAG) maneuvers). Here, we theoretically derived and tested the Optimal Sliding Guidance (OSG)
for close-proximity operations. The guidance algorithm has its root in the generalized ZEM/ZEV feedback guidance and its mathematical equations are naturally derived by a proper definition of a sliding surface as function of Zero-Effort-Miss and Zero-Effort-Velocity. Thus, the sliding surface allows a natural augmentation of the energy-optimalguidance via a sliding mode that ensures global stability for the proposed algorithm. A set of Monte Carlo simulations in realistic environment are executed to assess the guidance performance in typical operational scenarios found during asteroids close-proximity operations. OSG is shown to satisfy stringent requirements for asteroid pinpoint landing and sampling accuracy.

Conference

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

Fingerprint

Asteroids
Landing
Spacecraft
Electronic guidance systems
Control theory
Sampling
Feedback

Keywords

  • guidance control systems
  • algorithmic design
  • asteroid orbit control
  • operational control
  • non-linear methods

Cite this

Furfaro, R., Gaudet, B., Wibben, D., & Simo, J. (2013). Development of non-linear guidance algorithms for asteroids close-proximity operations. Paper presented at AIAA Guidance, Navigation and Control Conference 2013, Boston, Massachusetts, United States. https://doi.org/10.2514/6.2013-4711
Furfaro, Roberto ; Gaudet, Brian ; Wibben, Daniel ; Simo, Jules. / Development of non-linear guidance algorithms for asteroids close-proximity operations. Paper presented at AIAA Guidance, Navigation and Control Conference 2013, Boston, Massachusetts, United States.18 p.
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Furfaro, R, Gaudet, B, Wibben, D & Simo, J 2013, 'Development of non-linear guidance algorithms for asteroids close-proximity operations' Paper presented at AIAA Guidance, Navigation and Control Conference 2013, Boston, Massachusetts, United States, 19/08/13 - 22/08/13, . https://doi.org/10.2514/6.2013-4711

Development of non-linear guidance algorithms for asteroids close-proximity operations. / Furfaro, Roberto; Gaudet, Brian; Wibben, Daniel; Simo, Jules.

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

Research output: Contribution to conferencePaper

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AB - In this paper, we discuss non-linear methodologies that can be employed to devise real-time algorithms suitable for guidance and control of spacecrafts during asteroid close-proximity operations. Combination of optimal and sliding control theory provide the theoretical framework for the development of guidance laws that generates thrust commands as function of the estimated spacecraft state. Using a Lyapunov second theorem one can design non-linear guidance laws that are proven to be globally stable against unknown perturbations with known upper bound. Such algorithms can be employed for autonomous targeting of points of the asteroid surface (soft landing , Touch-And-Go (TAG) maneuvers). Here, we theoretically derived and tested the Optimal Sliding Guidance (OSG)for close-proximity operations. The guidance algorithm has its root in the generalized ZEM/ZEV feedback guidance and its mathematical equations are naturally derived by a proper definition of a sliding surface as function of Zero-Effort-Miss and Zero-Effort-Velocity. Thus, the sliding surface allows a natural augmentation of the energy-optimalguidance via a sliding mode that ensures global stability for the proposed algorithm. A set of Monte Carlo simulations in realistic environment are executed to assess the guidance performance in typical operational scenarios found during asteroids close-proximity operations. OSG is shown to satisfy stringent requirements for asteroid pinpoint landing and sampling accuracy.

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Furfaro R, Gaudet B, Wibben D, Simo J. Development of non-linear guidance algorithms for asteroids close-proximity operations. 2013. Paper presented at AIAA Guidance, Navigation and Control Conference 2013, Boston, Massachusetts, United States. https://doi.org/10.2514/6.2013-4711