UA91069C2 - Method and device for air transportation of aircraft parts - Google Patents

Abstract

A method and a device for air transportation of aircraft parts. According to the invention, an aerodynamic surface (5.1) subject to transportation is fastened on a carrier-aircraft (1) in such a way that it is transformed into a biplane.

Description

According to the present invention, above its fuselage 2, the carrier aircraft 1 carries a second bearing plane 5.I, 5. and 5.PI, respectively, which is parallel to the first bearing plane C and which belongs to an aircraft (not shown) that is different from the carrier aircraft 1. The engine is not installed on any of the bearing planes 5.1, 5.II and 5.III.

Each of the second bearing planes 5.1, 5.II and 5.III is fixed on the carrier plane 1 by means of the first structure, for example, in the form of lattices from the first of the rigid rods 6, which detachably connect it to the first bearing plane 3, and with the help of a second structure, for example, also in the form of lattices from the second rigid rods 7, connecting it to the mentioned fuselage 2 of the carrier aircraft 1. From the side of the mentioned first bearing plane C, the first rigid rods 6 rest on the fastening means 8 (in detail not shown), as a rule, are intended for manipulating the wings of the mentioned first carrier plane 3.

In the execution examples | and III, shown in Fig. 1-6, the second supporting planes 5.1 and 5.II, are the main supporting planes of aircraft (not shown), different from the carrier aircraft 1, which contain their flaps 9, ailerons 10, slats 11 for increasing the lifting force, etc. Typically, each of them contains a wing 122 and a wing 120, connected to each other by a central caisson 13. Said caisson 13 is equipped with a removable leading edge part 14 and a removable trailing edge part 15, they provide continuity with the leading edges and trailing edges of the mentioned wings 125 and 120.

From the side of the second bearing planes 5.1 and 5.II, the first rigid rods 6 rest on the fastening means 15 (not shown in detail), which are provided for fastening the engines on the mentioned wings 122 and 120.

In the example of implementation I, shown in fig. 1-3, the second carrier plane 5.I has a span similar to the span of the first carrier plane Z of the carrier aircraft 1. In the example of implementation II shown in Fig. 4 - b, on the contrary, the second carrier plane 5.II has a span that exceeds the span of said first carrier plane From carrier aircraft 1.

In the example implementation of HER, shown in Fig. 7-9, the second supporting plane is a horizontal tail of the aircraft (not shown), much larger than the carrier aircraft 1. This horizontal tail 5.III contains the left element 16C1 and the right element 160, which are connected to each other by the central caisson 17. Horizontal tail contains a rudder of height 18 and similarly to what was described above, the central caisson 17 is equipped with a part 19 of the attack rib, which is removable and a part 20 of the flow rib, which is also removable.

In connection with the above, it is clear that the second bearing plane 5.1, 5.II or 5.1 can be separately fixed on the carrier plane 1 with the help of rods 6, 7 at the place of its manufacture, then transported completely and in a set by this carrier plane (which becomes a biplane) to the assembly point, where the above-mentioned second bearing surface is unloaded from the carrier aircraft 1 and connected to other parts of the aircraft for which it is intended.

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