Vendetta Final Proposal Part 2 - Cal Poly

the center-of-gravity location closest to that corresponding to the desired static margin. The code then outputs the
center-of-gravity location and the remaining fuel payload. This is done at 10-second intervals throughout the 5-hour
mission. Using this data, the center-of-gravity path can then be plotted against corresponding to the desired static
margin.
The next step was to balance the weapons payload. Because the weapons payload was placed in a rotary
launcher, the center-of-gravity of the payload was concentrated in one location. If it had been placed in a more
conventional arrangement spread across the belly of the aircraft, the center-of-gravity of the weapons would have also
been spread across the belly of the aircraft. By concentrating the center-of-gravity of the weapons payload in one
location and placing the weapons payload on top of the aircraft’s empty weight center-of-gravity location, deployment of
the weapons payload did not generate any problems in balancing the aircraft or in disturbing the static margin. The
center-of-gravity is shown tracking along the path of the desired static margin by means of fuel monitoring and pumping
in Figure 9.2.
Figure 9.2 - Center-of-Gravity Excursion
The figure indicates that the center-of-gravity location at takeoff gross weight is slightly aft of the neutral point;
however, the center-of-gravity tracks the desired static margin shortly after the aircraft has transitioned to supercruise.
Notice the path of the aerodynamic center as it shifts during the transition from subsonic to supersonic flight. It is clear
that the aircraft flies supersonically shortly after takeoff, or when the aircraft’s gross weight is just below takeoff gross
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