The contraction of satellite orbits under the influence of air drag: Part III High-eccentricity orbits

Title

The contraction of satellite orbits under the influence of air drag: Part III High-eccentricity orbits

 Author

King-Hele, D.G.

Institution

Royal Aircraft Establishment RAE

 Date

1962-01-31

 Abstract

The effect of air drag on satellite orbits of eccentricity e less than 0.2 was studied in Parts I and II. Here the theory for values of e between 0.2 and 1 is presented. Equations are derived which show how perigee distance and orbital period vary with eccentricity during the satellite's life, and how eccentricity is related to time; and formulae are obtained for the lifetime and the air density at perigee, in terms of the rate of change of period. The results are also presented graphically and their implications and limitations are discussed.

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 Publisher

Ministry of Aviation, Royal Aircraft Establishment, RAE Farnborough

 Access restriction

Campus only

 Source

RAE Technical Note No. Space 1

 Part of collection

Aerospace Engineering Reports

 Document type

report

 Rights

© 1962 Ministry of Aviation, Royal Aircraft Establishment
Files
PDF Tech_Note_Space_0001.pdf 15.14 MB
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