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LOW-THRUST ROCKET STEERING PROGRAM FOR MINIMUM TIME TRANSFER BETWEEN PLANETARY ORBITS
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English
Abstract
A mathematical analysis of the problem of a minimum time steering program for a low-thrust rocket with constant thrust-acceleration going from one planetary orbit to another is presented. Formal methods of the calculus of variations are employed. The assumed boundary conditions are zero radial velocity at the initial and final radii, and initial and final angular momenta equal to the local circular values. Only one central force field is included in the analysis. Results of numerical integration are presented for a thrust to mass ratio of 10-4 Earth “g”'s and a final-to-initial radius ratio of 1.5.
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FAULDERS, C., "LOW-THRUST ROCKET STEERING PROGRAM FOR MINIMUM TIME TRANSFER BETWEEN PLANETARY ORBITS," SAE Technical Paper 580376, 1958, https://doi.org/10.4271/580376.Also In
References
- “Power-Limited Flight -- Optimization in Gravitational Fields” Irving J. H. Space Technology Class Notes U.C.L.A. Extension February 17 1958 McGraw-Hill Book Company, Inc. New York, N.Y. Spring 1959 “Space Technology”
- “A Method of Determining Steering Programs for Low Thrust Interplanetary Vehicles” Rodriguez Edward A.R.S. Preprint 645-58 June 1958
- “Interplanetary Trajectories Under Low-Thrust Radial Acceleration” Copeland Jack A.R.S. Preprint 648-58 June 1958
- “Flight Mechanics of a Low Thrust Space Vehicle” Perkins Frank Second Annual AFOSR Astronautics Symposium 1958
- “Calculus of Variations” Weinstock Robert McGraw-Hill Book Company, Inc. New York, N. Y. 1952