Accession Number:

AD0767533

Title:

The Design, Fabrication, and Evaluation of a Ring Wing Canard Control System for a Short Range Missile.

Descriptive Note:

Technical rept.,

Corporate Author:

ARMY MISSILE COMMAND REDSTONE ARSENAL ALA GUIDANCE AND CONTROL DIRECTORATE

Personal Author(s):

Report Date:

1973-08-01

Pagination or Media Count:

72.0

Abstract:

The report covers the ring wing canard control system from its initial design phase through a series of wind tunnel tests and into the present design improvement phase. The initial design used a low drift air bearing developed on an in-house gyro program. The gyro rotor was modified to interface with a ring wing air foil. Wind tunnel tests were conducted to determine the flow characteristics, center of pressure, nutation rate, precession rate, normal force coefficient, and pitching moment coefficient of the ring wing. The ring wing canard gyro control concept mechanizes a sensor controller to guide a missile without any requirements for inflight power, preflight power, electronics, or preconditioning. The design is of fire-and-forget technology as its control is completely self-contained. The simplicity of this design gives guided missile performance at slightly over free rocket cost. Author

Subject Categories:

  • Guided Missiles

Distribution Statement:

APPROVED FOR PUBLIC RELEASE