Accession Number : AD0719758

Title :   Flight Data Analysis and Electromechanical Simulation of Sounding Rocket Stability.

Descriptive Note : Final rept. 25 Aug 69-24 Jan 71,

Corporate Author : ACCUMETRICS CORP CAMBRIDGE MASS

Personal Author(s) : Fryklund,Donald H. ; Anderson,Oiva R.

Report Date : 24 NOV 1970

Pagination or Media Count : 62

Abstract : The post-burnout angular motions of three divergent NIRO sounding rocket flights have been examined using rigid body energy techniques previously developed. Two of these flights exhibited roll-pitch lock-in through burnout and for several seconds after. All exhibited a rapid initial increase in coning angle followed by an actual decrease and a later more gradual divergence consistent with increased altitude. The rigid body kinetic energy histories show a double peaked character which implies that energy is temporarily stored internally such as in structural deformation. The magnitude of the energy in transverse motion is small enough so that de-spun damping of reasonable weight penalty is feasible. The previous study indicated that coning divergence of a spin-stabilized sounding rocket could be eliminated by the use of a passive de-spun rotor stabilization system. (Author)

Descriptors :   (*SIMULATORS, DESIGN), (*SOUNDING ROCKETS, STABILITY), FLIGHT TESTING, ROLL, PITCH(MOTION), KINETIC ENERGY, DEFORMATION, STABILIZATION SYSTEMS, PERFORMANCE(ENGINEERING), ROCKETS, DAMPING, SPIN STABILIZED AMMUNITION, YAW

Subject Categories : Test Facilities, Equipment and Methods
      Rockets

Distribution Statement : APPROVED FOR PUBLIC RELEASE