1st ACT global trajectory optimisation competition: Results found at the Jet Propulsion Laboratory

A tool developed for the preliminary design of low-thrust trajectories is described. The trajectory is discretized into segments and a nonlinear programming method is used for optimization. The tool is easy to use, has robust convergence, and can handle many intermediate encounters. In addition, the tool has a wide variety of features, including several options for objective function and different low-thrust propulsion models (e.g., solar electric propulsion, nuclear electric propulsion, and solar sail). High-thrust, impulsive trajectories can also be optimized.

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“…[14][15][16][17] MALTO also played a key role in JPL's winning entry for the Global Trajectory Optimization Competition. 18…”

Section: Testing and Applicationsmentioning

confidence: 99%

Implementation of a Low-Thrust Trajectory Optimization Algorithm for Preliminary Design

Sims

Finlayson

Rinderle

et al. 2006

AIAA/AAS Astrodynamics Specialist Conference and Exhibit

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“…In particular, for the arrival conditions at Venus we use objective function in Eq. (14), with ω l = 1, while for the arrival conditions at Mercury (last level) the objective function was: (15) whereṽ is the spacecraft velocity relative to Mercury at arrival. The pruning functions were selected based on the required effect of the gravity-assist maneuvers.…”

Section: Fig 5 Solutions Found By De A) and Mbh B) Over All 100 Runsmentioning

confidence: 99%

An Incremental Algorithm for the Optimization of Multiple Gravity Assist Trajectories

Ceriotti¹,

Vasile²,

Bombardelli

2014

Computational Intelligence in Aerospace Sciences

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“…For example, in order for a kinetic impactor to deliver collisional energies greater than 1000 J/kg it would need an impact mass of more than 50 tons and relative velocity larger than 50 km/s. Considering retrograde trajectories, impact velocities of at least 60 km/s are possible [25] even without using advanced propulsion concepts [26] . Therefore, assuming impact velocities close to 50 km/s only a few tons of impact mass would be required to provide a collisional energy on the order of 100 J/kg.…”

Section: B Kinetic Impactor and Nuclear Interceptormentioning

confidence: 99%

Consequences of Asteroid Fragmentation During Impact Hazard Mitigation

Sánchez

Vasile

Radice

2010

Journal of Guidance, Control, and Dynamics

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The consequences of the fragmentation of an Earth threatening asteroid due to an attempted deflection are examined in this paper. The minimum required energy for a successful impulsive deflection of a threatening object is computed and compared to the energy required to break-up a small size asteroid. The results show that the fragmentation of an asteroid that underwent an impulsive deflection, such as a kinetic impact or a nuclear explosion, is a very plausible event. A statistical model is used to approximate the number and size of the fragments as well as the distribution of velocities at the instant after the deflection attempt takes place. This distribution of velocities is a function of the energy provided by the deflection attempt, while the number and size of the asteroidal fragments is a function of the size of the largest fragment. The model takes also into account the gravity forces that could lead to a re-aggregation of the asteroid after fragmentation. The probability distribution of the pieces after the deflection is then propagated forward in time until the encounter with the Earth. A probability damage factor (i.e., expected damage caused by a given size fragment multiplied by its impact probability) is then computed and analyzed for different plausible scenarios, characterized by different levels of deflection energies and lead times.

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1st ACT global trajectory optimisation competition: Results found at the Jet Propulsion Laboratory

Cited by 17 publications

References 6 publications

Implementation of a Low-Thrust Trajectory Optimization Algorithm for Preliminary Design

Implementation of a Low-Thrust Trajectory Optimization Algorithm for Preliminary Design

An Incremental Algorithm for the Optimization of Multiple Gravity Assist Trajectories

Consequences of Asteroid Fragmentation During Impact Hazard Mitigation

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