Accession Number:

AD0257797

Title:

THEORY OF ARTIFICIAL STABILIZATION OF MISSILES AND SPACE VEHICLES WITH EXPOSITION OF FOUR CONTROL PRINCIPLES

Descriptive Note:

Technical note

Corporate Author:

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION HUNTSVILLE AL GEORGE C MARSHALL SPACE FLIGHT CENTER/PROGRAM OFFICE

Personal Author(s):

Report Date:

1961-06-01

Pagination or Media Count:

28.0

Abstract:

The theory of artificial stabilization of missiles and space vehicles in propelled flight is derived by a more rigorous method than has been done in the past. The relationship between the rotary loop and path loop in their reactions to artificial stabilization schemes is emphasized. The path reaction modes are classified by setting them into relation to two singular solutions, the drift minimum and load minimum modes. Two interesting other control modes are developed, concerned with local lateral acceleration along the missile axis. These are the maximum comfort control mode and the method of controlling the center or hinge point of the motion resulting from the combination of the rotary with the path motion.

Subject Categories:

  • Guided Missiles
  • Unmanned Spacecraft

Distribution Statement:

APPROVED FOR PUBLIC RELEASE