Accession Number : AD0691512

Title :   SOUNDING ROCKET POST-BURNOUT STABILIZATION STUDY.

Descriptive Note : Final rept. 5 Aug 68-4 May 69,

Corporate Author : ACCUMETRICS CORP CAMBRIDGE MASS

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

Report Date : 04 JUN 1969

Pagination or Media Count : 68

Abstract : The stability conditions for a sounding rocket have been examined by expressing the Euler equations of motion in terms of power. Stability criteria were derived from this power in Euler quantities and their time derivatives. Data for a divergent Nike-Tomahawk flight were examined on the basis of momentum, energy and power about the roll and transverse axes and correlated with the derived power expression and with aerodynamic input power. Coning divergence appears to be initiated by a perturbation at last stage burnout, which is followed by a transient phase of about four seconds duration during which energy is being fed into the vehicle transverse axis. This transient phase is characterized by a coning rate higher than the natural pitch frequency and by raped increase in coning angle. One hypothesis put forth as a possible source of the transverse energy was parametric pumping due to the non-alignment of the coning axis and velocity vector. Design criteria were established for a damper mounted on a de-spun portion of the vehicle. This damper is de-coupled from the roll motion and, therefore, acts directly to absorb energy out of the transverse axis. (Author)

Descriptors :   (*PROPELLANT BURN OUT, SOUNDING ROCKETS), (*SOUNDING ROCKETS, ROCKET TRAJECTORIES), (*ROCKET TRAJECTORIES, STABILITY), PROPELLANT BURN OUT, PARTIAL DIFFERENTIAL EQUATIONS, EQUATIONS OF MOTION, SPIN STABILIZATION, KINETIC ENERGY, AERODYNAMIC CHARACTERISTICS, MOMENT OF INERTIA, TORQUE, DAMPING, STABILIZATION SYSTEMS

Subject Categories : Armor
      Rockets
      Combustion and Ignition

Distribution Statement : APPROVED FOR PUBLIC RELEASE