Two-Body Optimization for Deflecting Earth-Crossing Asteroids

Park, Sang Young; Ross, I. Michael

doi:10.2514/2.4413

Cited by 31 publications

(35 citation statements)

References 7 publications

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“…Finally the out-of-plane component h of ˆo pt δ v is negligible compared to the other two for large ∆t but becomes comparable for short anticipating times. These conclusions are consistent with the results presented by Park and Ross [10] and by Conway [12]. …”

Section: Optimal Action Directions Analysissupporting

confidence: 94%

“…When a continuous deviation action is applied, the total variation in the orbital parameters is computed by (10) where is the acceleration vector, given by the continuous thrust. Note that in this case the derivative of M, also takes into account the change in mean anomaly due to the change in the angular velocity n on the thrusting arc, because the term n cannot be ignored as is done for the impulsive maneuver case.…”

Section: Low-thrust Action Deviation Formulasmentioning

confidence: 99%

“…A more general approach was used by Park and Ross [10,11] to determine the near-optimal direction of an impulsive maneuver. A similar approach was used by Conway [12].…”

Section: Introductionmentioning

confidence: 99%

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A Multi-criteria Assessment of Deflection Methods for Dangerous NEOs

Cuartielles¹,

Colombo²,

Vasile³

et al. 2007

AIP Conference Proceedings

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Abstract.Over the last few years, the possible scenario of an asteroid threatening to impact the Earth has stimulated an intense debate among the scientific community about possible deviation methods. In this paper we present a comparative assessment of some of the more feasible mitigation schemes reviewed in the literature (i.e. solar collector, nuclear blast, kinetic impactor, low-thrust propulsion and mass driver). For each strategy, a multi-criteria optimization method has been used to construct a set of Pareto optimal solutions, minimizing both the mass of the spacecraft and the warning time, while simultaneously maximizing the deviation. A dominance criterion has then been defined and used to compare all the Pareto sets. The achievable deviation at the MOID, either for a low-thrust or for an impulsive maneuver, has been computed through a set of analytical formulas. The variation in the orbit of the NEO has been estimated through a deviation action model that takes into account the wet mass of the spacecraft on the Earth. Finally the technology readiness level of each strategy has been used to recompute a more realistic value for the required warning time.

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Section: Optimal Action Directions Analysissupporting

confidence: 94%

Section: Low-thrust Action Deviation Formulasmentioning

confidence: 99%

See 1 more Smart Citation

A Multi-criteria Assessment of Deflection Methods for Dangerous NEOs

Cuartielles¹,

Colombo²,

Vasile³

et al. 2007

AIP Conference Proceedings

View full text Add to dashboard Cite

show abstract

“…Recently, the astrodynamical optimization problem was formulated for Earth-crossing asteroids (ECAs) and presented accurate impulse angles as well as impulse magnitude according to impulse time ____________________ 6 Chapter nomenclature available in chapter notes, p. 217.…”

Section: Introductionmentioning

confidence: 99%

“…6). The minimum impulse change in velocity (∆V) requirement is not a monotonically decreasing function of warning time; rather, there is a finer structure associated with the orbital period of the colliding asteroid.…”

Section: Introductionmentioning

confidence: 99%

Mission Functionality for Deflecting Earth-Crossing Asteroids/Comets

Park

Mazanek

2003

Journal of Guidance, Control, and Dynamics

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IntroductionAn infrequent but significant hazard to life and property due to impacting asteroids and comets exists. Earth-approaching asteroids and comets also represent a significant resource for commercial exploitation, space exploration, and scientific research. The impact problem and those planetary bodies that could be a threat have been discussed in great depth in a wide range of publications. A popular planetary defense method is the deflection of asteroids and comets on a collision orbit with the Earth by changing their orbital velocities. It is fundamental to estimate required changes in the orbital velocities of dangerous objects to avoid a collision.A detailed optimization problem is formulated to calculate optimal impulses for deflecting Earthcrossing asteroids/comets, using nonlinear programming. The constrained optimization problem is based on a three-dimensional patched conic method to include the Earth's gravitational effects and the asteroid/ comet's orbital inclination. The magnitudes and impulse angles of optimal impulse change in velocity (∆V) are accurately computed at various points on the asteroid/comet's orbit to provide a given target separation distance. Based on these change in velocity analyses, we can establish the approximate cost and build strategies to prevent possible catastrophe due to the objects.

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Deflection of Earth-Crossing Asteroids/Comets Using Rendezvous Spacecraft and Laser Ablation

Park

Mazanek

2005

J of Astronaut Sci

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Two-Body Optimization for Deflecting Earth-Crossing Asteroids

Cited by 31 publications

References 7 publications

A Multi-criteria Assessment of Deflection Methods for Dangerous NEOs

A Multi-criteria Assessment of Deflection Methods for Dangerous NEOs

Mission Functionality for Deflecting Earth-Crossing Asteroids/Comets

Deflection of Earth-Crossing Asteroids/Comets Using Rendezvous Spacecraft and Laser Ablation

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