GB894822A - Improvements in aircraft - Google Patents

Abstract

894,822. Aircraft. BRISTOL SIDDELEY ENGINES Ltd. Aug. 27, 1959 [Sept. 1, 1958], No. 28068/58. Class 4. [Also in Group XXVI] An aircraft comprises two elongated accommodation bodies 11, 12 spaced apart side by side and each comprising a pointed forebody 11a 12a, a centrebody 11b, 12b, of constant depth and width, and an after body 11c 12c, tapering in width, the bodies being connected only in the region of their centrebodies and afterbodies by a power plant body 13 of generally rectangular transverse section, comprising an air intake 16 at its forward end, and a diffuser passage 17 leading from the intake to air heating means 31, 32 discharging into propulsion nozzles 33, 36, at the rear of body 13, and two wings 39 with swept back leading edges one extending laterally from each body 11, 12. The upper wall of the diffuser is double walled, and contains fuel tanks 26, 27, and a passage 25 connecting the two bodies 11, 12. A wedge shaped part 20 of the upper wall is tiltable about a lateral axis 22 to the chain-dot position, for low speed flight. The diffuser contains structural, air-flow straightening, grids 28, 29. The upper surfaces of the wings 39 and bodies 11, 12, 13 are continuous, and fences 14 are provided between the bodies 13, and 11, 12, along the parts 11e 12e of the latter, where their cross-section changes from circular to D-shape. Control surfaces 41, 45 are provided on the wings and bodies. The air heating section 15 is divided into two parts by a partition 30 structurally integral with a fin 43 supporting a rudder 44. Each part contains four gas turbine engines 32 in two superimposed pairs, and a ram jet burner 31. The accommodation layout, Fig. 4, includes passenger compartments 45, connected by passage 25, toilet compartments 46, a crew compartment 47, and refrigeration plant 48 used in high speed flight, all compartments having heat insulating linings.