The empennage provides the stability of the aircraft ( Crane, 1997). The empennage (also known as the tail assembly) consists of tailplane, vertical fin, and the portions of fuselage to which the tailplane and fin are attached. Reza Hedayati, Mojtaba Sadighi, in Bird Strike, 2016 7.7 Empennage and wingĪn aircraft wing is a fin with a surface that produces aerodynamic lift force for flight ( Wing, 2015). A ± 15-degree angular rotation range was considered. This arrangement is proved to strongly increase the rotational rigidity of the movable surfaces, with a consequent more relevant stress transmission at the attachment rear spar, where the surface is hinged, and on the front spar, on which the actuator insists any transmission on the front spar has to be carefully taken into consideration for their impact on the other device supported by the spar, that is the LE.

5, to guarantee an adequate aerodynamic smoothness even for large deflections. The inboard movable surface was connected to a rubber fairing, Fig. Rigid elements were used to link the movable parts to the fixed structure only the rotational DOF around the pivot axis was allowed. The actuation is obtained in a way similar to that proposed for the TE: two independent actuators, once more simulated through expanding bars, were hinged between the front spar and the movable surfaces of the WL, eccentrically deployed with respect to their pivot. Outboard and inboard independent rotations were enabled.

The winglet considered in this study was integrated with two movable surfaces along its span. The generalised geometry of the fuel tank is shown in Figure 4.7a. Also, the space in front of the inboard flap is not used for fuel volume, as this is likely to be where the main landing gear will be stowed. The space ahead of the ailerons will not be used for fuel tankage, as the wing section here is too thin. Each tank occupies the space between the leading edge and trailing edge high-lift structure and associated mechanisms. Such factors must be considered separately when deciding the overall location of fuel tanks.įor the aircraft in this project, we can consider the fuel to be held in wing tanks on each side of the aircraft fuselage as shown in Figure 4.7. Note: these factors do not account for landing gear or other significant intrusions into the available space. Typically, reduce the available internal volume to 85 per cent for integral tanks and to 65 per cent for bladder or ‘bag tanks’. To determine the usable capacity of a fuel tank it is possible to calculate the external volume and then reduce this value to account for internal obstructions caused by structural and system components within the tank. Marchman III, in Aircraft Design Projects, 2003 Estimation of wing fuel volume

X wing front view