Long-Lifetime Lunar Repeat Ground Track Orbits

Russell, Ryan P.; Lara, Martı́n

doi:10.2514/1.27104

Cited by 41 publications

(25 citation statements)

References 19 publications

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“…perturbations Russell and Lara 2007;Lara 2011). However, the above-mentioned studies did not include the orbit maintenance problem to take advantage of high-precision orbit design.…”

Section: -24mentioning

confidence: 99%

High-precision repeat-groundtrack orbit design and maintenance for Earth observation missions

Jia

et al. 2017

Celest Mech Dyn Astr

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The focus of this paper is the design and station keeping of repeat-groundtrack orbits for Sun-synchronous satellite. A method to compute the semimajor axis of the orbit is presented together with a station-keeping strategy to compensate for the perturbation due to the atmospheric drag. The results show that the nodal period converges gradually with the increase of the order used in the zonal perturbations up to J15. A differential correction algorithm is performed to obtain the nominal semimajor axis of the reference orbit from the inputs of the desired nodal period, eccentricity, inclination and argument of perigee. To keep the satellite in the proximity of the repeat-groundtrack condition, a practical orbit maintenance strategy is proposed in the presence of errors in the orbital measurements and control, as well as in the estimation of the semimajor axis decay rate. The performance of the maintenance strategy is assessed via the Monte Carlo simulation and the validation in a high fidelity model. Numerical simulations substantiate the validity of proposed mean-elements-based orbit maintenance strategy for repeat-groundtrack orbits.

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“…perturbations Russell and Lara 2007;Lara 2011). However, the above-mentioned studies did not include the orbit maintenance problem to take advantage of high-precision orbit design.…”

Section: -24mentioning

confidence: 99%

High-precision repeat-groundtrack orbit design and maintenance for Earth observation missions

Jia

et al. 2017

Celest Mech Dyn Astr

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“…For most lunar landing problems, knowledge of the parking orbit before the descent phase is, however, more critical than the gravity field perturbations induced during the relatively short descent phase (Floberghagen 2002). Therefore, numerous studies have been conducted to design or analyze the mapping orbits around the Moon with precise lunar flight dynamics, by focusing on investigating orbital behavior that minimizes mission costs as well as increases mission effectiveness while mapping the Moon (Abad et al 2009, Elipe & Lara 2003, Folta & Quinn 2006, Manglik 2005, Park & Junkins 1995, Russell & Lara 2007.…”

Section: Introductionmentioning

confidence: 99%

Development of Precise Lunar Orbit Propagator and Lunar Polar Orbiter's Lifetime Analysis

Song¹,

Park²,

Kim³

et al. 2010

Journal of Astronomy and Space Sciences

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To prepare for a Korean lunar orbiter mission, a precise lunar orbit propagator; Yonsei precise lunar orbit propagator (YSPLOP) is developed. In the propagator, accelerations due to the Moon's non-spherical gravity, the point masses of the Earth, Moon, Sun, Mars, Jupiter and also, solar radiation pressures can be included. The developed propagator's performance is validated and propagation errors between YSPOLP and STK/Astrogator are found to have about maximum 4-m, in along-track direction during 30 days (Earth's time) of propagation. Also, it is found that the lifetime of a lunar polar orbiter is strongly affected by the different degrees and orders of the lunar gravity model, by a third body's gravitational attractions (especially the Earth), and by the different orbital inclinations. The reliable lifetime of circular lunar polar orbiter at about 100 km altitude is estimated to have about 160 days (Earth's time). However, to estimate the reasonable lifetime of circular lunar polar orbiter at about 100 km altitude, it is strongly recommended to consider at least 50 × 50 degrees and orders of the lunar gravity field. The results provided in this paper are expected to make further progress in the design fields of Korea's lunar orbiter missions.

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“…FIRE is particularly suited for problems that favor higher speeds and smooth derivatives, such as trajectory optimization (Russell 2007(Russell , 2004Hull 1979;Sauer 1989), orbit determination (Campbell and Speckman 2004;Russell and Lara 2007;Koon et al 1999;Lo et al 2004) and Monte Carlo sensitivity analysis (Desai and Cheatwood 1999;Aiello 2005). The new system generally favors speed in sacrifice of relatively more memory.…”

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confidence: 98%

“…(2004), Russell and Lam (2006), Russell and Lara (2007), Aiello (2005), Lo et al (2004)]. The importance of the solar system data, robust reliability of the current ephemeris systems (like JPL's SPICE Acton 1996) and the need for precise trajectory computations have led to wide spread use of ephemerides amongst scientists, engineers, and their associated software.…”

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confidence: 99%

A fast, accurate, and smooth planetary ephemeris retrieval system

Arora

Russell

2010

Celest Mech Dyn Astr

Self Cite

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Precise trajectory simulations typically require an ephemeris retrieval system, i.e. some mechanism to identify planetary body states and orientations at given times. However, the ephemeris systems most commonly used throughout industry and academia are, by design, general in their capabilities and application. Here, we introduce a new system called FIRE (Fast Interpolated Runtime Ephemeris) that is designed for custom trajectory applications that favor speed and smooth derivatives. The new system minimizes the overhead associated with ephemeris calls through the use of archived splines, a runtime ephemeris (stored in random access memory of the computer), and batch processing routines. Further, our approach naturally provides first and second time derivatives for a small additional computational cost. The derivative capability is particularly attractive for optimization and targeting where smooth and accurate derivatives are important. Relative performance comparisons with the Jet Propulsion Laboratory's Spacecraft Planet Instrument C-matrix Events ephemeris system show typical speed improvements of approximately two orders of magnitude (250 times) for various state and orientation calls. Performance comparisons for high fidelity trajectory propagations are also considered and a factor of 70 in performance increase is achieved for typical cases. The new tool has potential value to any high precision application or software requiring fast, accurate, and smooth ephemeris data.

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Long-Lifetime Lunar Repeat Ground Track Orbits

Cited by 41 publications

References 19 publications

High-precision repeat-groundtrack orbit design and maintenance for Earth observation missions

High-precision repeat-groundtrack orbit design and maintenance for Earth observation missions

Development of Precise Lunar Orbit Propagator and Lunar Polar Orbiter's Lifetime Analysis

A fast, accurate, and smooth planetary ephemeris retrieval system

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