| 摘要 |
An ultralight aircraft is described, in particular a helicopter, falling within the limits of a basic weight ranging from 210 to 230 kg and a maximum weight of 450 kg, the length (L) of which ranges between 4950 and 5150 mm. The structure (50), constituting the characteristic framework of the helicopter, is formed by several tubular elements of titanium alloy which converge in a plurality of central knots (KC1...KC4) lying on the helicopter's symmetry plane, and of pairs of lateral knots (KL1...KL7) symmetrical with respect to said plane, the spatial position of which, referred to a triad of axes, is defined in relation to the length (M) of the structure selected as a basic parameter. |
