GB686592A - Improvements in or relating to tanks for the accommodation of liquid - Google Patents

Abstract

686,592. Aircraft fuel tanks; de-icing and boundary layer control systems for aircraft. FAIREY AVIATION CO., Ltd. May 19, 1950 [May 26, 1949] No. 14133/49. Class 4. [Also in Group XXIX] A liquid fuel tank for aircraft comprises an outer wall 10, Fig. 2 forming the outer skin of the wing, a corrugated inner wall, channel section members 18 lying along the ridges 17 of the corrugation between the inner and outer walls and means such as rivets 20 securing the inner and outer walls to the channel members 18, the latter having apertures 21 affording access to the intericars of the channels and through which the sealing medium introduced into the spaces between the inner and outer walls passes. In the form shown in Fig. 1, the corrugated inner wall extends between the leading edge of the front spar, and between the front and rear spars 11, 12, the ribs 13, 14 acting as tank baffles. In tapered wings the corrugations of the inner wall are tapered in pitch and depth. As shown in Fig. 4, the space between the inner and outer walls 16, 22 may be divided into compartments by fore-and-aft walls 24 and the compartments connected by tubes 25 to a pneumatic system for de-icing or cooling purposes. Alternatively, to provide a boundary layer bleed system, the outer wall is formed with apertures 26 communicating with the ducts formed between the inner and outer walls and the tubes 25 and connected to a low pressure area outside the aircraft.