Accession Number : AD0821571
Title : ANALYTIC SIMULATION OF THE BLUE GOOSE VEHICLE ATTITUDE CONTROL SYSTEM.
Descriptive Note : Technical rept. Mar-Apr 67,
Corporate Author : AIR FORCE WEAPONS LAB KIRTLAND AFB NM
Personal Author(s) : Lynch, Urban H. DeH.
Report Date : OCT 1967
Pagination or Media Count : 82
Abstract : The analytic simulation used to develop specifications for the Blue Goose Vehicle Attitude Control System is discussed. The Blue Goose is a 15,500-pound spinning, fin-stable sounding rocket. The sensing element of the guidance package is a roll-stabilized platform upon which is mounted two two-degree-of-freedom gyros for sensing Euler angle roll, pitch and yaw. Guidance laws are such that the vehicle is commanded to fly a zero-yaw, gravity-turn trajectory. Computer results reveal that trajectory dispersion can conservatively be held to 10 mils. The report discusses the effects of control force, spin, lag, rate feedback, and total time of control on trajectory dispersion. (Author)
Descriptors : *ATTITUDE CONTROL SYSTEMS), (*SOUNDING ROCKETS, (*SURFACE TO AIR MISSILES, ATTITUDE CONTROL SYSTEMS), SIMULATION, INERTIAL GUIDANCE, PITCH(MOTION), VELOCITY, ROCKET TRAJECTORIES, COMPUTER PROGRAMS, RANGE(DISTANCE), FINS.
Subject Categories : Surface-launched Guided Missiles
Distribution Statement : APPROVED FOR PUBLIC RELEASE