Doubly Averaged Effect of the Moon and Sun on a High Altitude Earth Satellite Orbit

The secular effect of the moon or sun on a high altitude earth satellite orbit is approximated by spreading the moon or sun into a circular ring of matter and averaging over one orbit of the satellite. Calculations are performed to first order in eccentricity for satellite radii inside and outside t...

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Main Author: Ash,Michael E
Format: Report
Language:English
Subjects:
Equations of motion
High orbit trajectories
Moon
Numerical integration
Partial differential equations
Perturbations
Spacecraft trajectories
Spacecraft Trajectories and Reentry
Sun
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description The secular effect of the moon or sun on a high altitude earth satellite orbit is approximated by spreading the moon or sun into a circular ring of matter and averaging over one orbit of the satellite. Calculations are performed to first order in eccentricity for satellite radii inside and outside the lunar radius. The secular variations in semi-major axis and inclination to the ring plane are zero and those of the other orbital elements are given by infinite series. (Modified author abstract)
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Calculations are performed to first order in eccentricity for satellite radii inside and outside the lunar radius. The secular variations in semi-major axis and inclination to the ring plane are zero and those of the other orbital elements are given by infinite series. (Modified author abstract)</description><language>eng</language><subject>Equations of motion ; High orbit trajectories ; Moon ; Numerical integration ; Partial differential equations ; Perturbations ; Spacecraft trajectories ; Spacecraft Trajectories and Reentry ; Sun</subject><creationdate>1974</creationdate><rights>APPROVED FOR PUBLIC RELEASE</rights><oa>free_for_read</oa><woscitedreferencessubscribed>false</woscitedreferencessubscribed></display><links><openurl>$$Topenurl_article</openurl><openurlfulltext>$$Topenurlfull_article</openurlfulltext><thumbnail>$$Tsyndetics_thumb_exl</thumbnail><link.rule.ids>230,777,882,27548,27549</link.rule.ids><linktorsrc>$$Uhttps://apps.dtic.mil/sti/citations/AD0776022$$EView_record_in_DTIC$$FView_record_in_$$GDTIC$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>Ash,Michael E</creatorcontrib><creatorcontrib>MASSACHUSETTS INST OF TECH LEXINGTON LINCOLN LAB</creatorcontrib><title>Doubly Averaged Effect of the Moon and Sun on a High Altitude Earth Satellite Orbit</title><description>The secular effect of the moon or sun on a high altitude earth satellite orbit is approximated by spreading the moon or sun into a circular ring of matter and averaging over one orbit of the satellite. Calculations are performed to first order in eccentricity for satellite radii inside and outside the lunar radius. The secular variations in semi-major axis and inclination to the ring plane are zero and those of the other orbital elements are given by infinite series. (Modified author abstract)</description><subject>Equations of motion</subject><subject>High orbit trajectories</subject><subject>Moon</subject><subject>Numerical integration</subject><subject>Partial differential equations</subject><subject>Perturbations</subject><subject>Spacecraft trajectories</subject><subject>Spacecraft Trajectories and Reentry</subject><subject>Sun</subject><fulltext>true</fulltext><rsrctype>report</rsrctype><creationdate>1974</creationdate><recordtype>report</recordtype><sourceid>1RU</sourceid><recordid>eNqFybEKwjAURuEsDqK-gcP_AkKpYOdgI13EIe4lbW6aQEggvRF8exHcnc4HZyt0n-sU35AvKmYhC-UczYzswJ5wzznBJAtdE77EEBYPGTlwtQRlCntowxRjYMKjTIH3YuNMXOnw604cb-p5HU6WwzyuHBLxKPum6y5N257_7A85XjOM</recordid><startdate>19740301</startdate><enddate>19740301</enddate><creator>Ash,Michael E</creator><scope>1RU</scope><scope>BHM</scope></search><sort><creationdate>19740301</creationdate><title>Doubly Averaged Effect of the Moon and Sun on a High Altitude Earth Satellite Orbit</title><author>Ash,Michael E</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-dtic_stinet_AD07760223</frbrgroupid><rsrctype>reports</rsrctype><prefilter>reports</prefilter><language>eng</language><creationdate>1974</creationdate><topic>Equations of motion</topic><topic>High orbit trajectories</topic><topic>Moon</topic><topic>Numerical integration</topic><topic>Partial differential equations</topic><topic>Perturbations</topic><topic>Spacecraft trajectories</topic><topic>Spacecraft Trajectories and Reentry</topic><topic>Sun</topic><toplevel>online_resources</toplevel><creatorcontrib>Ash,Michael E</creatorcontrib><creatorcontrib>MASSACHUSETTS INST OF TECH LEXINGTON LINCOLN LAB</creatorcontrib><collection>DTIC Technical Reports</collection><collection>DTIC STINET</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>Ash,Michael E</au><aucorp>MASSACHUSETTS INST OF TECH LEXINGTON LINCOLN LAB</aucorp><format>book</format><genre>unknown</genre><ristype>RPRT</ristype><btitle>Doubly Averaged Effect of the Moon and Sun on a High Altitude Earth Satellite Orbit</btitle><date>1974-03-01</date><risdate>1974</risdate><abstract>The secular effect of the moon or sun on a high altitude earth satellite orbit is approximated by spreading the moon or sun into a circular ring of matter and averaging over one orbit of the satellite. Calculations are performed to first order in eccentricity for satellite radii inside and outside the lunar radius. The secular variations in semi-major axis and inclination to the ring plane are zero and those of the other orbital elements are given by infinite series. (Modified author abstract)</abstract><oa>free_for_read</oa></addata></record>
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recordid cdi_dtic_stinet_AD0776022
source DTIC Technical Reports
subjects Equations of motion
High orbit trajectories
Moon
Numerical integration
Partial differential equations
Perturbations
Spacecraft trajectories
Spacecraft Trajectories and Reentry
Sun
title Doubly Averaged Effect of the Moon and Sun on a High Altitude Earth Satellite Orbit
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