Aquila A211 Instructions d'exploitation télécharger pdf (Page 109)

Aviation

AIRPLANE FLIGHT MANUAL

AQUILA AT01

Section 7

SYSTEM DESCRIPTION

Document No.: Issue: Supersedes Issue: Date: Page:

FM-AT01-1010-100E

A.12 A.05 (30/09/2003) 17/09/2008 7 - 5

7.2 AIRFRAME

The majority of the aircraft structure is constructed in composite design. Glass fibre

(GFRP) as well as carbon fibre materials (CFRP) are used that are bedded into an

epoxy resin matrix. The aircraft structure consists of both, monolithic GFRP or CFRP

shells / structural components and sandwich shells with a structural foam core based on

PVC.

7.2.1 Fuselage

The fuselage forms one structural unit along with the vertical and horizontal stabilizers.

The fuselage and vertical stabilizer as a monolithic component consists of two half-

shells. While the fuselage portion of the half-shells is fabricated from solid fibreglass

laminate, the vertical stabilizer portion has a sandwich structure. The GFRP-skin of the

fuselage is reinforced by four carbon fibre stringers, arranged lengthwise along the

entire fuselage.

Four ring frames and a baggage compartment bulkhead support and stiffen the fuselage

shells in the tail boom section. In the forward fuselage section adjacent to the wing-

body-intersection, the landing gear frame, seat frame and the shear frame of the wing-

body-joint are positioned for the transmission of the several loads into the fuselage

structure and to stiffen the structure in these sections. At its front side, the fuselage

ends with the firewall at which the engine is attached to. The firewall, designed as a

GFRP/CFRP sandwich composite, has on its front side in the engine compartment a fire

protection lining that consists of a special fire-resistant ceramic fleece and a stainless

steel sheet.

The landing gear frame, which supports together with the seat frame the main landing

gear struts, is supplemented in the upper section by a compact CFRP/GFRP roll-over

bar.

7.2.2 Wing

The wing is designed with a triple trapezoid planform that tapers off in winglets at its

wing tips. The wing consists of an upper and a lower shell in GFRP sandwich composite

design that are both locally reinforced by CFRP unidirectional straps in the region of the

wing spar bonding area. Both, the left and the right wing form one structural unit which

are connected by a rigid wing main spar in the middle section. The wing spar is a

continuous unit from wing tip to wing tip and has a “double-T” (I-beam) cross-section

with chords manufactured from CFRP unidirectional fibres (rovings) and a GFRP

sandwich web.

Each wing half ends on its inboard side with a forward and rearward root rib, separated

by the wing spar, which are joined to the shear frame in the fuselage mid section by a

shear bolt on each fwd and rearward root rib. The four shear bolts are installed from the

cabin through the fuselage bushings into the wing bolt housings in the wing root ribs

and axially secured with bolts.

1 2 ... 104 105 106 107 108 109 110 111 112 113 114 ... 145 146

Commentaires sur ces manuels

Pas de commentaire

Aquila A211 Instructions d'exploitation Page 109

Commentaires sur ces manuels