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):

Report Date:

1970-11-24

Pagination or Media Count:

62.0

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

Subject Categories:

  • Test Facilities, Equipment and Methods
  • Rockets

Distribution Statement:

APPROVED FOR PUBLIC RELEASE