The long-term prediction of artificial satellite orbits

Cefola, P. J.; Long, Anne; Holloway, Greg

doi:10.2514/6.1974-170

Cited by 24 publications

(11 citation statements)

References 15 publications

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“…They are discussed in more detail in [Broucke and Cefola, 1972], [Cefola, Long, and Holloway, 1974], [Long, McClain, and Cefola, 1975], [Cefola and Broucke, 1975], [McClain, 1977 and1978], and [Shaver, 1980].…”

Section: Equinoctial Elementsmentioning

confidence: 99%

“…The equations of motion resulting from this conversion are called the Variation-of-Parameters (VOP) equations of motion. The derivation of these equations is discussed in some detail in [Cefola, Long, and Holloway, 1974] and [McClain, 1977].…”

Section: Variation-of-parameters (Vop) Equations Of Motionmentioning

confidence: 99%

“…Only a summary of the application of this procedure to (2.2-3) will be given here. More details can be found in [Cefola, Long, and Holloway, 1974], [McClain, 1977], [McClain, Long, and Early, 1978] and [Green, 1979]. To apply the Generalized Method of Averaging we first assume that the osculating orbit elementsâ i are related to a set of mean elements a i by a near-identity transformation: (a, h, k, p, q, λ, t) ( 1 )…”

Section: Equations Of Averagingmentioning

confidence: 99%

“…The limits (F 1 , F 2 ) in (1a) or (L 1 , L 2 ) in (1b) now indicate the values of F or L at shadow exit and entry. If we assume the shadow is a circular cylinder in shape, the shadow exit and entry longitudes are determined by the shadow equation (as explained in [Escobal, 1965] and [Cefola, Long, and Holloway, 1974]):…”

Section: Solar Radiation Pressurementioning

confidence: 99%

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Semianalytic Satellite Theory

Danielson¹,

Sagovac²,

Neta³

et al. 1995

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Section: Equinoctial Elementsmentioning

confidence: 99%

Section: Variation-of-parameters (Vop) Equations Of Motionmentioning

confidence: 99%

Section: Equations Of Averagingmentioning

confidence: 99%

Section: Solar Radiation Pressurementioning

confidence: 99%

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Semianalytic Satellite Theory

Danielson¹,

Sagovac²,

Neta³

et al. 1995

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“…The averaged analytical propagator is based on a set of analytical formulae to propagate the perturbed Keplerian motion over a complete revolution; the averaged orbital elements variationsẊ are then numerically propagated, as it is done in classical semi-analytical techniques (Cefola et al, 1974):…”

Section: Transfer Modelmentioning

confidence: 99%

Automatic trajectory planning for low-thrust active removal mission in low-earth orbit

Carlo

Martin

Vasile

2017

Advances in Space Research

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In this paper two strategies are proposed to de-orbit up to 10 noncooperative objects per year from the region within 800 and 1400 km altitude in Low Earth Orbit (LEO). The underlying idea is to use a single servicing spacecraft to de-orbit several objects applying two different approaches. The first strategy is analogous to the Traveling Salesman Problem: the servicing spacecraft rendezvous with multiple objects in order to physically attach a de-orbiting kit that reduces the perigee of the orbit. The second strategy is analogous to the Vehicle Routing Problem: the servicing spacecraft rendezvous and docks with an object, spirals it down to a lower altitude orbit, undocks, and then spirals up to the next target.In order to maximise the number of de-orbited objects with minimum propellant consumption, an optimal sequence of targets is identified using a bio-inspired incremental automatic planning and scheduling discrete optimisation algorithm. The optimisation of the resulting sequence is realised using a direct transcription method based on an asymptotic analytical solution of the perturbed Keplerian motion. The analytical model takes into account the perturbations deriving from the J 2 gravitational effect and the atmospheric drag.

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Mathematics of attitude-constrained optimal low-thrust orbit transfer

Kechichian

2017

Aerotec. Missili Spaz.

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The long-term prediction of artificial satellite orbits

Cited by 24 publications

References 15 publications

Semianalytic Satellite Theory

Semianalytic Satellite Theory

Automatic trajectory planning for low-thrust active removal mission in low-earth orbit

Mathematics of attitude-constrained optimal low-thrust orbit transfer

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