Accession Number:

AD0722291

Title:

Inertial Guidance of Ballistic Missiles

Descriptive Note:

Corporate Author:

FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSONAFB OH

Personal Author(s):

Report Date:

1971-01-08

Pagination or Media Count:

129.0

Abstract:

This monograph discusses the mathematical principles of certain allowed variants of inertial guidance of the flight of ballistic missiles, i.e., control without the use of any external information radio signals, radiation of stars and others. It is assumed that the providing of the assigned flight range of the missile is produced as a result of the well-timed switching-off of its engine by a signal entering from the computer. Fed into the input of the latter are readings of sensitive elements of the system of inertial guidance, and these measure the apparent acceleration of the missile or integrals from the apparent time acceleration. Control should be such that the deviation of the actual motion of the missile from the rates does not have an effect on the range of its flight. To accomplish this, measuring instruments are placed on the missile in a quite definite manner, and, in particular, the direction of their axes of sensitivity in a number of cases is stabilized by means of gyroscopes.

Subject Categories:

  • Guided Missiles

Distribution Statement:

APPROVED FOR PUBLIC RELEASE