A Coordinated Assembly Method for Unmanned Fixed-wing Aircraft Fuselage

Abstract

The invention discloses a coordinated assembly method for an unmanned fixed-wing aircraft fuselage.The method comprises the following steps ofthe first step,front fuselage main body assembly, whereina multi-functional assembly system is used for positioning a front fuselage partition plate, a truss, a front landing chassis, a first-phase preparation rear crossbeam, an airspeed tube, a support seat, afirst-phase preparation door and a main rocker arm; the second step,middle fuselage main body assembly, wherein a middle fuselage partition plate, a middle fuselage truss, middle fuselage left aircraft skin, middle fuselage right aircraft skin, middle fuselage upper aircraft skin, middle fuselage lower aircraft skin and a middle fuselage covering cap are positioned; the third step, rear fuselage main body assembly, whereina rear fuselage partition frame, a rear fuselage truss, rear fuselage left aircraft skin, rear fuselage right aircraft skin, rear fuselage upper aircraft skin, rear fuselage lower aircraft skin, a rear fuselage covering cap and an aircraft tail cover are positioned; the fourth step, fuselage intersection point hole positionfinishing; the fifth step, wing body connecting intersection point hole position finishing, wherein a wing body intersection point finishing component is used for completing the finishing of wing body intersection point hole positions of two middle fuselage partition frames.

Description

technical field [0001] The invention belongs to the technical field of fuselage coordination of unmanned fixed-wing aircraft, and in particular relates to a coordinated assembly method of fuselage of unmanned fixed-wing aircraft. Background technique [0002] At present, the R&D, production and manufacturing of large UAVs in China are in a stage of rapid development, and their assembly and manufacturing technology is highly dependent on the traditional manned aircraft assembly technology, and has not yet formed its own system. Compared with traditional manned aircraft, large-scale UAVs have stronger maneuverability, smaller dimensions, lighter body weight, and lower rigidity of the fuselage structure. As the final link of manufacturing, UAV assembly directly affects aircraft quality and Therefore, the assembly and manufacturing methods of large UAVs also need to be converted in a timely manner, instead of relying entirely on the traditional segmented assembly of fuselage com...

AI Technical Summary

Problems solved by technology

[0004] Due to the small size of the fuselage, the structural rigidity and strength of the fuselage are much lower than those of the above-mentioned models, and the connection and intersection points involved in the fuselage are extremely accurate, and the coordination relationship is complicated. Segments cannot be coordinated as a whole, and segmental assembly leads to long coordination routes, and the accumulation of tolerances directly affects the accuracy of the hole positions at the intersection points of each segment, resulting in out-of-tolerance dimensions and scrapped parts, which cannot meet the requirements for aerodynamic shape and assembly accuracy; at the same time, the fuselage is segmented Assembly requires at least five sets of tooling (front fuselage, middle fuselage, rear fuselage, fuselage alignment and finishing frame), which increases a lot of cost, leads to long fuselage assembly cycle, large workshop area, and insufficient company resources Reasonable use

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