Impacting small Near Earth Objects

Gil-Fernández, Jesús; Panzeca, R.; Corral, Cristina

doi:10.1016/j.asr.2008.02.023

Cited by 11 publications

(15 citation statements)

References 4 publications

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“…The performances of the GNC system are validated in a high fidelity simulator upgraded from a previous tool for impact missions 4 . The hybrid (continuous/discrete), multi-rate simulator has the GNC software (SW) included as Embedded Matlab Functions®, allowing efficient Monte Carlo simulation and also debugging of a particular case.…”

Section: A High-fidelity Simulator (Chilon † † )mentioning

confidence: 99%

Autonomous GNC Algorithms for Rendezvous Missions to Near-Earth-Objects

Gil-Fernández

Prieto-Llanos

Cadenas-Gorgojo

et al. 2008

AIAA/AAS Astrodynamics Specialist Conference and Exhibit

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This paper presents the design of an autonomous GNC system for the rendezvous phase of low-cost missions to very small, faint Near Earth Object (NEO). The optical navigation problem presents a strong relation between the approach strategy and the best combination of sensors, algorithms and actuators. First of all the problem is globally analyzed and the rendezvous strategy defined, from detection of the asteroid to insertion into a desired bounded orbit, considering the observability of the full spacecraft state relative to the asteroid. Then, for each sub-phase the GNC algorithms, including the Image Processing, are described for different propulsion systems (impulsive and low-thrust), and including or not an altimeter. Monte Carlo simulations for different NEO (Apophis and 2003 SM84) are run to tune the algorithms and to asses the system performances. The simulation tool includes high-fidelity models of the optical sensors (navigation camera and star-tracker). The conclusions show the driving parameters and the feasibility of the proposed GNC system.

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Section: A High-fidelity Simulator (Chilon † † )mentioning

confidence: 99%

Autonomous GNC Algorithms for Rendezvous Missions to Near-Earth-Objects

Gil-Fernández

Prieto-Llanos

Cadenas-Gorgojo

et al. 2008

AIAA/AAS Astrodynamics Specialist Conference and Exhibit

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“…Gil-Fernández et al [7,8] describe various terminal-phase guidance laws of a kinetic impactor as applied to the European Space Agencys Don Quijote mission (now canceled). This work was continued in more detail by Hawkins et al [9].…”

Section: Introductionmentioning

confidence: 99%

New near-optimal feedback guidance algorithms for space missions

Hawkins

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“…The equation of motion of the spacecraft with respect to the target becomes (5) where g represents the sum of apparent gravitational accelerations on the target, as follows:…”

Section: Mathematical Modelingmentioning

confidence: 99%

“…Gil-Fernández et al [4,5] describe various terminal-phase guidance laws of a kinetic impactor as applied to the European Space Agency's Don Quijote mission (now cancelled). This work was continued in more detail by Hawkins et al [6].…”

Section: Introductionmentioning

confidence: 99%

Spacecraft Guidance Algorithms for Asteroid Intercept and Rendezvous Missions

Hawkins¹,

Guo²,

Wie³

2012

International Journal of Aeronautical and Space Sciences

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This paper presents a comprehensive review of spacecraft guidance algorithms for asteroid intercept and rendezvous missions. Classical proportional navigation (PN) guidance is reviewed first, followed by pulsed PN guidance, augmented PN guidance, predictive feedback guidance, Lambert guidance, and other guidance laws based on orbit perturbation theory. Optimal feedback guidance laws satisfying various terminal constraints are also discussed. Finally, the zero-effort-velocity (ZEV) error, analogous to the well-known zero-effort-miss (ZEM) distance, is introduced, leading to a generalized ZEM/ZEV guidance law. These various feedback guidance laws can be easily applied to real asteroid intercept and rendezvous missions. However, differing mission requirements and spacecraft capabilities will require continued research on terminal-phase guidance laws.

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Impacting small Near Earth Objects

Cited by 11 publications

References 4 publications

Autonomous GNC Algorithms for Rendezvous Missions to Near-Earth-Objects

Autonomous GNC Algorithms for Rendezvous Missions to Near-Earth-Objects

New near-optimal feedback guidance algorithms for space missions

Spacecraft Guidance Algorithms for Asteroid Intercept and Rendezvous Missions

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