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Record 4 of 61
Simulation of low thrust guidance problems
Author and Affiliation:
Dawkins, G. S.(Houston, University, Houston, Tex., United States)
Long, D.(NASA Johnson Space Center, Mission Planning and Analysis Div., Houston, Tex., United States)
Abstract: The determination of optimal rocket control profiles and the guidance procedures used to approximate these profiles have received much attention. Simple guidance procedures have sufficed for the Apollo flights. A modified version of the linear tangent guidance law is developed which can be used for a low-thrust orbital maneuvering system such as the space shuttle. The modification allows the estimation of gravity over long thrusting arcs which is necessary for low thrust systems.
Publication Date: May 01, 1974
Document ID:
19740052747
(Acquired Dec 04, 1995)
Accession Number: 74A35497
Subject Category: SPACE SCIENCES
Document Type: Journal Article
Publication Information: Automatica; 10; May 1974
Publisher Information: United Kingdom
Financial Sponsor: NASA; United States
Description: 6p; In English
Distribution Limits: Unclassified; Publicly available; Unlimited
Rights: Copyright
NASA Terms: CONTROL SIMULATION; LOW THRUST; OPTIMAL CONTROL; ROCKET THRUST; SPACECRAFT GUIDANCE; THRUST CONTROL; APOLLO FLIGHTS; FLIGHT CONTROL; SPACE SHUTTLES; SPACECRAFT MANEUVERS; TRAJECTORY OPTIMIZATION
Imprint And Other Notes: Automatica, vol. 10, May 1974, p. 303-308.
Miscellaneous Notes: p. 303-308
Availability Source: Other Sources
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