Accession Number:

ADA202693

Title:

Optimal Launch Time for a Discontinuous Low Thrust Orbit Transfer

Descriptive Note:

Master's thesis,

Corporate Author:

AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING

Personal Author(s):

Report Date:

1988-12-01

Pagination or Media Count:

66.0

Abstract:

This thesis searches for the optimal launch time of a discontinuous, low thrust transfer between non-coplanar, circular orbits. The spacecraft is assumed to be solar-powered rocket that cannot provide thrust in the earths shadow. Two time scales are used to calculate a minimum time trajectory. The fast timescale produces a control law which maximizes a change in orbital elements for a single orbit. The slow timescale incorporates the control law so that the final boundary conditions are met in minimum time. Minimum transfer times are determined between winter and summer. Keywords Low thrust Electric propulsion Orbit transfer Solar propulsion Transfer trajectories. jhd

Subject Categories:

  • Electric and Ion Propulsion
  • Spacecraft Trajectories and Reentry

Distribution Statement:

APPROVED FOR PUBLIC RELEASE