Orbital Stability Zones about Asteroids II. The Destabilizing Effects of Eccentric Orbits and of Solar Radiation

نویسندگان

  • DOUGLAS P. HAMILTON
  • JOSEPH A. BURNS
چکیده

The gravitational effects of the Sun on a particle orbiting another massive body which itself moves on a circular path around the Sun have been studied extensively. Most recently, D. P. Hamilton and J. A. Burns (1991, Zcarus 92, 118-131) characterized the size and shape of a stability zone around an asteroid on a circular heliocentric orbit within which material could remain bound for an extended period of time. We now consider two additional effects analytically and numerically: the asteroid’s nonzero heliocentric eccentricity and solar radiation pressure. In both of these cases, our numerical integrations apply directly to a spherical asteroid, “Amphitrite,” with semimajor axis 2.55 AU, radiusR, = 100 km, and density 2.38 g/cm3. For an asteroid on an eccentric orbit we argue, based on numerical integrations and analytical approximations, that the stability zone scales roughly as the size of the Hill sphere calculated at the asteroid’s pericenter. This scaling holds for large values of eccentricity and allows results for one asteroid with a given mass, semimajor axis, and eccentricity to be used for another with different values of these parameters. We compare predictions of the scaling law to numerical integrations for an “Amphitrite” with various orbital eccentricities and find good agreement for prograde orbits and for those with orbital planes nearly normal to the asteroid’s heliocentric path, but not for retrograde orbits. We apply our results to the minor planet 951 Gaspra. We also determine that solar radiation pressure is a very efficient mechanism for removing relatively small particles from the circumasteroidal zone. Radiation pressure acting on an orbiting grain can cause large oscillations in the grain’s orbital eccentricity which in turn can lead to either escape from the system or impact with the asteroid. We find numerically that particles with radius 0.1 mm started on circular orbits escape from “Amphitrite” at all distances beyond 130 R,. Grains of this size started anywhere between the asteroid’s surface and 130 R, are forced to crash into the minor planet; smaller grains are even more severely affected. The orbits of millimeter-sized grains are also strongly perturbed. Planar paths bound for 20 years are found to extend to only -40% of the critical distance found by Hamilton and Burns (1991); orbits with inclinations near 90” are somewhat more resilient. In all cases, orbital evolution occurs on time scales comparable to the asteroid’s orbital period. Particles larger than a few centimeters are only slightly affected by radiation pressure. These results can be applied to “Gaspra,” an asteroid only one-thousandth as massive as “Amphitrite,” by increasing all particle sizes by a factor of -10. o 1%~

برای دانلود متن کامل این مقاله و بیش از 32 میلیون مقاله دیگر ابتدا ثبت نام کنید

ثبت نام

اگر عضو سایت هستید لطفا وارد حساب کاربری خود شوید

منابع مشابه

The Rosetta Target Asteroids Environment

The ROSETTA spacecraft will y-by a few asteroids during its course to the nal cometary target. The candidate asteroids presently are 140 Siwa (C-type) and 4979 Otawara. An alternative interesting trajectory reaching four asteroids (5331 Erimomisaki, 905 Universitas, 1515 Perrotin and 4247 Grahamsmith) has also been found by ESA. With the limited data presently available on these bodies we calcu...

متن کامل

Study of the Environment around the Rosetta Candidate Target Asteroids

The ROSETTA spacecraft will y-by a few asteroids during its course to the nal cometary target. The candidate asteroids presently are 3840 Mimistrobel (S-type), 2703 Rodari (S-type) and 140 Siwa (C-type). With the limited data presently available on these bodies we calculated some approximate quantities which may be useful to select the y-by tra-jectories of the ROSETTA probe. In particular we d...

متن کامل

Orbital Perturbation Effect on LEO Satellite Trajectory

A satellite, in its orbit, is affected by perturbing forces, such as atmospheric drag, solar radiation pressure, Earth oblateness, and gravity of the celestial masses (other than the Earth). In this paper, the effects of these forces on the trajectories of different types of LEO satellites and a sample satellite (Z-SAT) are discussed. A few analyses are done on these orbits and the relevant res...

متن کامل

Temporary orbital capture of ejecta from comets and asteroids: Application to the Deep Impact experiment

The trajectories of dust particles ejected from the surface of a comet or asteroid after a cratering impact are influenced by the interplay of solar radiation pressure, solar tide, cometary outgassing (for comets) and the body’s irregular gravity field. In this paper we evaluate the ability of these forces to cause ejecta to become captured in temporary orbits about the parent body. We concentr...

متن کامل

Fuzzy Sliding Mode for Spacecraft Formation Control in Eccentric Orbits

The problem of relative motion control for spacecraft formation flying in eccentric orbits is considered in this paper. Due to the presence of nonlinear dynamics and external disturbances, a robust fuzzy sliding mode controller is developed. The slopes of sliding surfaces of the conventional sliding mode controller are tuned according to error states using a fuzzy logic and reach the pre-define...

متن کامل

ذخیره در منابع من


  با ذخیره ی این منبع در منابع من، دسترسی به آن را برای استفاده های بعدی آسان تر کنید

برای دانلود متن کامل این مقاله و بیش از 32 میلیون مقاله دیگر ابتدا ثبت نام کنید

ثبت نام

اگر عضو سایت هستید لطفا وارد حساب کاربری خود شوید

عنوان ژورنال:

دوره   شماره 

صفحات  -

تاریخ انتشار 2002