Effects Analysis of Frozen Conditions for Spacecraft Relative Motion Dynamics

Soleymani, A.; Toloei, Alireza

doi:10.5829/idosi.ije.2012.25.04a.01

Cited by 1 publication

(2 citation statements)

References 5 publications

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“…Chobotov (2002) Source: Soleymani and Toloei (2012) and coworkers differentiate Brouwer's equations of motion to get the following expressions for the variation in eccentricity and argument of perigee up to J 3 perturbation terms (Cutting et al, 1978):…”

Section: Cutting Theorymentioning

confidence: 99%

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Spacecraft OMM reduction using stable frozen orbit conditions

Soleymani

Toloei

2015

Aircraft Eng & Aerospace Tech

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Purpose -The purpose of this research was to analyze application effects of the stable frozen orbit conditions in the spacecraft Orbital Maintenance Maneuver (OMM) reduction. Design/methodology/approach -One challenge in implementing these motions is maintaining the relations as it experiences orbital perturbations (zonal harmonics), most notably due to the non-spherical Earth. A natural phenomenon exists called a frozen orbit, for which the orbital elements: argument of perigee () and eccentricity (e) remain virtually fixed over extended periods of time. Findings -Simulation results show that, using stable frozen orbit condition results in considerable propellant saving, decreased OMM, increase of accuracy position errors and thus performance improvement of the spacecraft for orbiter mission is preferable. So, from among three proposed theories, the Brouwer-Hori theory has provided better accuracy and more stable conditions in the frozen orbit. Practical implications -Simulation algorithm has been achieved to solve this problem by extracting and combining the equations that govern the frozen conditions with the tangential forces (⌬V) equations for orbit correction. Originality/value -In all studies with content of harmonic perturbation effects on the spacecraft motion dynamics, main goal is to obtain a solution for optimization of the operation process, so that overshadowed mission costs. The case studies about this aim, mostly to the trajectory parameters optimization by considering the vehicle orbital conditions under various control methods are formed. While in this regards, the intrinsic properties of stable Earth orbits and using them effectively is less than to analyse the problems is considered.

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Section: Cutting Theorymentioning

confidence: 99%

“…Figures 1 and 2 show an example of the closed contours about the frozen conditions for the TOPEX mission. With farther from stable frozen conditions, closed contours are converted to pear shape (Soleymani and Toloei, 2012).…”

Section: Frozen Orbits Conditionsmentioning

confidence: 99%

Spacecraft OMM reduction using stable frozen orbit conditions

Soleymani

Toloei

2015

Aircraft Eng & Aerospace Tech

View full text Add to dashboard Cite

show abstract

Effects Analysis of Frozen Conditions for Spacecraft Relative Motion Dynamics

Cited by 1 publication

References 5 publications

Spacecraft OMM reduction using stable frozen orbit conditions

Spacecraft OMM reduction using stable frozen orbit conditions

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