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)
Flight Data Analysis and Electromechanical Simulation of Sounding Rocket Stability
1970
62 pages
Report
Keine Angabe
Englisch
Rockets , Simulators , Sounding rockets , Design , Stability , Flight testing , Roll , Pitch(Motion) , Kinetic energy , Deformation , Stabilization systems , Performance(Engineering) , Damping , Spin-stabilized ammunition , Yaw , Niro rockets , Burnout , Coning angle , Nike-Iroguois sounding rockets , Electromechanical simulation
Flight analysis of sounding rocket
Engineering Index Backfile | 1938
|Sounding Rocket Flight Data Summary, 1966-1976
NTIS | 1978
|Consort 1 sounding rocket flight
NTRS | 1989
|Consort 1 sounding rocket flight
AIAA | 1989
|