Report of the Second Piloted Aircraft Flight Control System - Acgsc.org

Equation (5) may be def bed in terms of the no-load time constant T
and the reciprocal of the damping ratio. This quantity is here designated
the "inertia index - E." The new term is employed in this paper becauee
the term "bmging ratiow or other tern sometimes associated vith the
reciprocal of the damping ratio would have no meaning in the type of
transient associated vith the hydraulic servomotor.
Equation (5) expreseed in terme of the parameters T and E
is
Equating like coefficients in equatione (5) and (6)
Substituting equation (3) in equation (7) the general expression
for E is obtained:
Linear equation for approximation of the deceleration phase. - In
the deceleration phase of the transient the pilot valve areas are reduced
to small values. Consequently the flow rate through the vdves is
affected to a far greater degree by the reducing value area than by
variatione in the pressure drop across the valve. For this reason the
reeponee in the deceleration phase does not deviate si&ficsatly from
the no-load reeponee. Equation (2) may therefore be used to approdmate
the deceleration phase.
Evaluation of coefficient for the rotary. servomotor. - By means of
a parallel development expressions for T and E can be obtained for
the rotary motor. These expreesione are given below.