ARTEMIS Mission Design

Sweetser, Theodore H.; Broschart, Stephen B.; Angelopoulos, V.; Whiffen, Gregory J.; Folta, David; Chung, Min-Kun; Hatch, Sara J.; Woodard, Mark

doi:10.1007/978-1-4614-9554-3_4

Cited by 11 publications

(14 citation statements)

References 11 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The Halo orbit from which the spacecraft is departing is chosen to have a z−excursion of 5000 km around the EM libration point L 2 , see Figure 3. The choice for this specific Halo orbit is motivated by the successful Artemis mission [22,23] During the period represented in Figure 1, asteroid 2006RH 120 does 17 clockwise revolutions around the origin of the CR3BP frame, and 3.6 revolutions in Earth inertial reference frame. The evolution of the energy of 2006RH 120 and its distance to the Earth-Moon libration point L 2 as the asteroid evolves on its orbit are given in Figure 4.…”

Section: Rendezvous To 2006rh 120mentioning

confidence: 99%

“…Rendezvous missions to asteroids in the inner solar system can be found in [10,17] but they concern asteroids on elliptic orbits which is not the case for us since TCOs are presenting complex orbits and therefore require a different methodology. Our assumption on the hibernating location for the spacecraft, a Halo orbit around the Earth-Moon unstable Libration points L 2 , is motivated in part from the successful Artemis mission [22,23] and in part from the constraint on the duration of the mission, mostly impacted by the time of detection of the asteroid. Indeed, the Arthemis mission demonstrated low delta-v (∆v) station keeping on Halo orbits around L 1 and L 2 .…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Rendezvous missions to temporarily captured near Earth asteroids

Brelsford

Chyba

Haberkorn

et al. 2016

Planetary and Space Science

View full text Add to dashboard Cite

Missions to rendezvous with or capture an asteroid present significant interest both from a geophysical and safety point of view. They are key to the understanding of our solar system are as well stepping stones for interplanetary human flight. In this paper, we focus on a rendezvous mission with 2006RH 120 , an asteroid classified as a Temporarily Captured Orbiter (TCO). TCOs form a new population of near Earth objects presenting many advantages toward that goal. Prior to the mission, we consider the spacecraft hibernating on a Halo orbit around the Earth-Moon's L 2 libration point. The objective is to design a transfer for the spacecraft from the parking orbit to rendezvous with 2006RH 120 while minimizing the fuel consumption. Our transfers use indirect methods, based on the Pontryagin Maximum Principle, combined with continuation techniques and a direct method to address the sensitivity of the initialization. We demonstrate that a rendezvous mission with 2006RH 120 can be accomplished with low delta-v. This exploratory work can be seen as a first step to identify good candidates for a rendezvous on a given TCO trajectory.

show abstract

Section: Rendezvous To 2006rh 120mentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Rendezvous missions to temporarily captured near Earth asteroids

Brelsford

Chyba

Haberkorn

et al. 2016

Planetary and Space Science

View full text Add to dashboard Cite

show abstract

“…For example, if the motion of the satellite is limited in the planet-moonmoon system, such as the Saturn-Tethys-Telesto-spacecraft, Saturn-Tethys-Calypso-spacecraft, and Saturn-Dione-Helenspacecraft systems, they are typical R4BP systems. If the motion of the satellite is limited in the planet-moon system while the Sun's gravitational influence cannot be neglected, such as ARTEMIS mission [1], the system needs to be modeled as the R4BP as well. Meanwhile, for the mission exploring the Sun-planet system, such as GALA and PLANCK [2], the R3BP model is suitable when we consider the Sun and the barycenter of the planet and its moon as two dominant masses move around their center of mass along either circular or elliptic orbits.…”

Section: Introductionmentioning

confidence: 99%

Approximate Analytical Methodology for the Restricted Three-Body and Four-Body Models Based on Polynomial Series

Qian¹,

Yang²,

Yang³

et al. 2016

International Journal of Aerospace Engineering

View full text Add to dashboard Cite

The restricted three-body problem (R3BP) and restricted four-body problem (R4BP) are modeled based on the rotating frame. The conservative autonomous system for the R3BP and nonautonomous system with period parametric resonance due to the fourth body are derived. From the vibrational point of view, the methodology of polynomial series is proposed to solve for these problems analytically. By introducing the polynomial series relations among the three directions of motion, the three-degree-of-freedom coupled equations are transferred into one degree-of-freedom containing the full dynamics of the original autonomous system for the R3BP. As for the R4BP case, the methodology of polynomial series combined with the iterative approach is proposed. During the iterative approach, the nonautonomous system can be treated as pseudoautonomous equation and the final polynomial series relations and one-degree-of-freedom system can be derived iteratively.

show abstract

“…to a planetary flyby, in which case a two body approximation is sufficient for mission design purposes). This is the case of libration point (LP) missions, for which dynamical systems techniques were introduced relatively recently and are now widely spread [7,8,10,11,14,22]. Genesis [14] has been the first LP mission to make use of a heteroclinic connection between objects related to the L 1 and L 2 points of the Sun-Earth system.…”

Section: Introductionmentioning

confidence: 99%

“…Genesis [14] has been the first LP mission to make use of a heteroclinic connection between objects related to the L 1 and L 2 points of the Sun-Earth system. More recently, Artemis [22] has also used heteroclinic connections between the L 1 and L 2 dynamics but in the Earth-Moon system, with a more complex final trajectory. The trajectories of these two missions are shown in Figure 1.…”

Section: Introductionmentioning

confidence: 99%

Numerical continuation of families of heteroclinic connections between periodic orbits in a Hamiltonian system

2013

View full text Add to dashboard Cite

Abstract. This paper is devoted to the numerical computation and continuation of families of heteroclinic connections between hyperbolic periodic orbits of a Hamiltonian system. We describe a method that requires the numerical continuation of a nonlinear system that involves the initial conditions of the two periodic orbits, the linear approximations of the corresponding manifolds and a point in a given Poincaré section where the unstable and stable manifolds match. The method is applied to compute families of heteroclinic orbits between planar Lyapunov periodic orbits around the collinear equilibrium points of the Restricted Three-Body Problem in different scenarios. In one of them, for the Sun-Jupiter mass parameter, we provide ranges of energy for which the transition between different resonances is possible.

show abstract

ARTEMIS Mission Design

Cited by 11 publications

References 11 publications

Rendezvous missions to temporarily captured near Earth asteroids

Rendezvous missions to temporarily captured near Earth asteroids

Approximate Analytical Methodology for the Restricted Three-Body and Four-Body Models Based on Polynomial Series

Numerical continuation of families of heteroclinic connections between periodic orbits in a Hamiltonian system

Contact Info

Product

Resources

About