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Specifications and Dimensions
Structure
Wing design
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Structure

Fuselage

Conventional light alloy semi-monocoque and fail safe construction with frames and stringers and extensive use of integrally machined panels. Cross section of 'double lobe' design but externally faired to present oval shape.

The fuselage structure of the VC10

Drawing by J. Clark, The Aeroplane

In the entire structure use is made of integrally machined panels. One example of this are the fuselage side panels that include the window surrounds. These panels were machined from large flat billets, creating ten different thicknesses and stringers all in one piece. The resulting panels were then curvatured to suit the fuselage shape.

Wings

Cantilever low wing monoplane with a high lift wing section. Aspect ratio 7.29; thickness/chord ratio (type 1101) 13 percent at root and 9 percent at tip, (other versions with leading edge chord extension) 17 percent at root; dihedral 3; sweepback at quarter chord 3230'; incidence 4 at root. All metal structure with four spanwise members in inner wings reducing to two outboard, and wing skins integrally machined from light alloy billets. Fail safe design philosophies employed.

General layout of the (type 1102/3) wing from the Structural Repair Manual

Flight controls

Aluminium alloy ailerons with honeycomb core trailing edges, each aileron is divided into two sections with individual Boulton Paul electro-hydraulic power control units. No trim tabs; three Redux bonded laminated light alloy spoilers on top surface of each wing with individual hydraulic actuation and working in conjunction with ailerons to provide differential roll control. Spoilers can also be used as air brakes. Hydraulically actuated light alloy Fowler flaps in five sections per wing, total area 508sq ft (47.2 m2). Slats in four sections per wing over most of each wing leading edge; one boundary layer fence per wing (two on the type 1101s); hot air anti icing of wing leading edge and slats. Electro-hydraulic power operated elevators each in two sections with individual PCUs, mounted on cantilever T-tail with hydraulically actuated variable incidence tailplane. Rudder in three sections, also with individual PCUs; no trim tabs; hot air anti icing in leading edges. Further info on flight controls can be found here (link will be added in the future).

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