An improved solution of the gravity field of Mars (GMM‐2B) from Mars Global Surveyor

Lemoine, F. G.; Smith, David E.; Rowlands, D. D.; Zuber, M. T.; Neumann, Gregory A.; Chinn, D. S.; Pavlis, D. E.

doi:10.1029/2000je001426

Cited by 239 publications

(162 citation statements)

References 32 publications

(7 reference statements)

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“…Moreover, the physical parameters from 1989 are still being used. Of particular importance are the Martian gravity field and the precession, which have been significantly improved in recent years (Lemoine et al 2001;Yuan et al 2001;Seidelmann et al 2002;Konopliv et al 2006).…”

Section: Introductionmentioning

confidence: 99%

First numerical ephemerides of the Martian moons

Lainey

Déhant²,

Pätzold

2007

A&A

116

127

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We present new ephemerides of Phobos and Deimos that are fit to observations from 1877 to 2005 and include recent spacecraft observations by Mars Global Surveyor and Mars Express. In contrast to earlier models, this is the first completely numerical one. In particular, the tidal effects have been modeled by the tidal bulge raised by each moon on the planet, instead of fitting secular accelerations in the satellite longitudes. This partly avoids absorbing the Deimos observational errors in its related tidal acceleration. Moreover, applying this model to other systems will be easier. Our estimate of the Martian dissipation is Q = 79.91 ± 0.69 (1σ-formal error) when assuming k 2 = 0.152 for the Martian Love number and Gm Ph = 0.68 × 10 6 m 3 /s 2 for the Phobos mass. We also report the possibility of fitting the Phobos oblateness gravity field. We suspect a non-uniform density for Phobos or a bias in either the observations or the Martian gravity field. A FORTRAN subroutine that computes the Martian moons' ephemerides is available on request.

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Section: Introductionmentioning

confidence: 99%

First numerical ephemerides of the Martian moons

Lainey

Déhant²,

Pätzold

2007

A&A

116

127

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“…In contrast, the sparse tracking of the ESA Mars Express spacecraft is due to its fixed high-gain antenna on the spacecraft bus. These recent NASA missions considerably improved the spatial resolution of the estimated Martian gravity field compared with earlier models [1][2][3]. The level of the unmodeled gravity anomalies decreased considerably as a result, and the nongravitational forces have a more noticeable impact on the adjusted trajectory.…”

mentioning

confidence: 99%

Effects of Self-Shadowing on Nonconservative Force Modeling for Mars-Orbiting Spacecraft

Mazarico¹,

Zuber²,

Lemoine³

et al. 2009

Journal of Spacecraft and Rockets

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Modeling improvements of nonconservative forces affecting Mars-orbiting spacecraft are presented in this study. Recent high-resolution gravity fields enable the recovery of smaller signals in the radio tracking data, previously obscured by mismodeled gravitational anomalies. In particular, the estimation of the atmospheric drag experienced by the spacecraft benefits from the new force models. More precise calculations of the spacecraft cross-sectional areas entering the equations for the atmospheric drag and direct solar radiation pressure are possible by accounting for the interplate self-shadowing of the spacecraft physical model. The relevant surface areas can change by as much as 20% on average, and the effects can be very variable within one orbit (10%). The benefits of these updated models are assessed with two spacecraft, the Mars Odyssey and the Mars Reconnaissance Orbiter. The changes in the nonconservative forces can significantly impact the reconstructed spacecraft trajectory and the estimated model parameters depend on the spacecraft geometry and orbit. The atmospheric density estimated by the Mars Odyssey is much improved with self-shadowing applied to the solar radiation, but improvements to both the drag force and the solar radiation are important in this case of the Mars Reconnaissance Orbiter.

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“…The spherical harmonic gravity of Mars was modelled as GMM2B (4 × 4) (Lemoine et al, 2001). Besides the gravitational perturbation from celestial bodies, solar radiation pressure was also included with the spherical solar radiation pressure model (Vallado, 2007).…”

Section: A R a D I O / O P T I C A L I N T E G R At E D Nav I G At I mentioning

confidence: 99%

A Radio/Optical Integrated Navigation Method Based on Ephemeris Correction for an Interplanetary Probe to approach a Target Planet

Fang

Ning

et al. 2015

J. Navigation

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To obtain accurate navigation results with respect to Earth simultaneously with those with respect to the target for an interplanetary probe to approach the target planet, this paper proposes a Radio/Optical integrated navigation method based on ephemeris correction, which deeply affects the fusion accuracy. In this paper, the model of the ephemeris error is established, and taking the analytical solution of the ephemeris uncertainty as measurement, the target ephemeris error and its covariance are estimated by Kalman filter and fed back to modify the force models. By correcting the target ephemeris and using information fusion, the Radio/Optical integrated navigation prevents the ephemeris uncertainty polluting the fusion accuracy, and efficiently combines the radio and optical navigation results. The results show the influence of the ephemeris error can be removed, and the Radio/Optical integrated navigation is capable of providing accurate navigation results with respect to Earth and the target. The results demonstrate the proposed method yields an accuracy superior to the conventional method, which proves its effectiveness.2. Optical navigation. 3. Radio navigation. 4. Ephemeris error estimation.

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An improved solution of the gravity field of Mars (GMM‐2B) from Mars Global Surveyor

Cited by 239 publications

References 32 publications

First numerical ephemerides of the Martian moons

First numerical ephemerides of the Martian moons

Effects of Self-Shadowing on Nonconservative Force Modeling for Mars-Orbiting Spacecraft

A Radio/Optical Integrated Navigation Method Based on Ephemeris Correction for an Interplanetary Probe to approach a Target Planet

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