(4) Control Surface
1. Moment of inertia of control surface. In order to ensure that the steering
system has sufficient frequency bandwidth and prevent the structural resonance damage caused by the low natural frequency of the steering mechanism, the method of increasing the stiffness of the steering mechanism is
used, and the weight of the steering mechanism is also increased. A simple
and effective method is to reduce the inertia of the control plane and
increase the natural frequency of the rudder control mechanism by changing
the material or the specific structure of the profile without affecting the
aerodynamic shape of the control surface.
2. “Balance” or “Overbalance” in the control surface. In order to prevent the
dynamic flutter of rudder control mechanism, besides changing the geometrical shape of control plane or profile, structural materials, and mass
distribution, the main commonly used method is to install a proper counterweight before the control surface spindle, which is used to adjust the
relative position between the center of mass and the spindle so that it can be
on or in front of the spindle in order to achieve “balance” or “overbalance”,
such is the case with Sea Sparrows and Aspide.
3. “Compensation” or “Overcompensation” of the control plane is listed in the
above section.
(5) Energy
There is energy source dedicated to the control executing system, also shared
with seeker antennas, and even power the whole missile power grid at the same
time. It covers a wide range of issues, which are complex and need to be
explored. The summary is as follows:
1. Ballistic function of energy design. Different from ground energy, the power
and total power of missile-borne energy are limited, so the rated power of
missile-borne energy (taking control execution system as an example) is not
determined by the product of the maximum hinge moment and the maximum rudder deviation velocity that may occur in all control trajectories, and
the total power is not the product of the power and the longest flight time.
According to the control trajectory function, the power spectrum and total
work–time curve which may appear in practice are obtained, and the rated
power and total work of energy are determined accordingly.
2. Study on the working condition of control trajectory. For the control execution system, the variation law of control plane deflection angle and the
curve of control plane angular velocity and hinge moment varying with flight
time are mainly studied. For seeker antenna, the variation law of antenna
deflection angle and the curve of antenna swing angular velocity and inertia
moment with flight time are studied. For the full-missile power grid, the
current consumption, voltage, and frequency curves of all power supply
subsystems with time-of-flight are mainly studied. Three groups of power
spectrum and total power–time curves are obtained as the basis for energy
88
9 High-Temperature and High-Speed Gas Turbine Pump …
1. Moment of inertia of control surface. In order to ensure that the steering
system has sufficient frequency bandwidth and prevent the structural resonance damage caused by the low natural frequency of the steering mechanism, the method of increasing the stiffness of the steering mechanism is
used, and the weight of the steering mechanism is also increased. A simple
and effective method is to reduce the inertia of the control plane and
increase the natural frequency of the rudder control mechanism by changing
the material or the specific structure of the profile without affecting the
aerodynamic shape of the control surface.
2. “Balance” or “Overbalance” in the control surface. In order to prevent the
dynamic flutter of rudder control mechanism, besides changing the geometrical shape of control plane or profile, structural materials, and mass
distribution, the main commonly used method is to install a proper counterweight before the control surface spindle, which is used to adjust the
relative position between the center of mass and the spindle so that it can be
on or in front of the spindle in order to achieve “balance” or “overbalance”,
such is the case with Sea Sparrows and Aspide.
3. “Compensation” or “Overcompensation” of the control plane is listed in the
above section.
(5) Energy
There is energy source dedicated to the control executing system, also shared
with seeker antennas, and even power the whole missile power grid at the same
time. It covers a wide range of issues, which are complex and need to be
explored. The summary is as follows:
1. Ballistic function of energy design. Different from ground energy, the power
and total power of missile-borne energy are limited, so the rated power of
missile-borne energy (taking control execution system as an example) is not
determined by the product of the maximum hinge moment and the maximum rudder deviation velocity that may occur in all control trajectories, and
the total power is not the product of the power and the longest flight time.
According to the control trajectory function, the power spectrum and total
work–time curve which may appear in practice are obtained, and the rated
power and total work of energy are determined accordingly.
2. Study on the working condition of control trajectory. For the control execution system, the variation law of control plane deflection angle and the
curve of control plane angular velocity and hinge moment varying with flight
time are mainly studied. For seeker antenna, the variation law of antenna
deflection angle and the curve of antenna swing angular velocity and inertia
moment with flight time are studied. For the full-missile power grid, the
current consumption, voltage, and frequency curves of all power supply
subsystems with time-of-flight are mainly studied. Three groups of power
spectrum and total power–time curves are obtained as the basis for energy
88
9 High-Temperature and High-Speed Gas Turbine Pump …