Optimum trajectories to circular synchronous equatorial orbit for smaller-than-optimum apogee motors /
Omer F. Spurlock and Fred Teren.

Description

Main Author

Spurlock, Omer F.

Related Names

Teren, Fred.
Lewis Research Center.
United States. National Aeronautics and Space Administration.

Language(s)

English

Published

Washington, D.C. : National Aeronautics and Space Administration: 1970.

Subjects

Trajectory.
Synchronous orbit.
Calculus of variations.
Optimum trajectories.

Summary

Analysis, procedure, and results are presented for maximizing payload capability for trajectories to circular synchronous equatorial orbit where thea pogee motor total impulse is much smaller than optimum. The trajectories begin at launch and are numerically integrated to insertion into the final orbit. Constraints on parking orbit perigee radius and duration are included. These trajectories, unlike conventional synchronous orbit trajectories, were found to require noncircular parking orbits and large amounts of inclination reduction before the apogee burn. The analysis and procedure were also applied to the conventional circular synchronous equatorial orbit problem where the burn and coast durations are optimum. Results are presented for the Applications Technology Satellite (ATS)-E missiod, which is an example of a problem where the apogee motor is small, and for the conventional case where the apogee motor is of optimum size.

Physical Description

28 p. : ill.; 27 cm.

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