A flexible pressure tooling and method for controlling assembly damage at the leading edge of an unmanned aerial vehicle

Abstract

The invention discloses a flexible pressure application tool for controlling the assembly damage of the front edge of an unmanned aerial vehicle, comprising: a first support block, a second support block, a screw, a wire thread sleeve, a screw rod, a first nut, a second nut, and foam glue and soft foam. The first support block is connected with the assembly tooling; the second support block is connected with the first support block by screws; the wire screw sleeve is installed at the corresponding position of the first support block and the second support block; the screw rod is installed on the wire screw The two nuts are installed on the screw rod; the soft foam is attached to the lower end of the screw rod through foam glue. Except for the support block which is machine-added, all finished parts are used as tooling components, which are low in cost and easy to assemble; the screw has an adjustable function, which makes the tooling flexible and can adapt to different airfoils and different sizes; the tooling is in contact with the leading edge The position adopts a soft foam structure, which can effectively control the structural damage of the leading edge and protect the leading edge while realizing the bonding and pressure of the ultra-thin leading edge and the rib.

Description

Technical field [0001] The present invention relates to a flexible pressing tool and method for controlling the front edge of the drone, belongs to the field of light flexible aircraft structure assembly. Background technique [0002] Since the solar aircraft is a large-scale aircraft with low wing load, the structure weight coefficient is relatively large, the sensitivity of the aircraft performance is enhanced, and the structural part is generally used to have a low density, high specific strength, and high ratio. The composite material is designed, and the composite amount of composite can take up to 95% by weight, so the solar aircraft structure has the characteristics of large flexibility, thin wall and large-area glue. In particular, the leading edge structure is used to reduce the ultra-thin prepreg, less thickness of 0.1 mm, which is easy to cause damage during the mixing process of the glue, and bring great challenges to the assembly. [0003] Traditionally controlling a...

AI Technical Summary

Problems solved by technology

In particular, the front edge structure adopts ultra-thin prepreg for weight reduction. The thickness is less than 0.1mm, which is very easy to cause damage during the process of bonding and pressing, which brings great challenges to assembly.

[0003] Traditionally, the method of controlling assembly accuracy and bonding quality is to design large-scale assembly tooling according to the requirements of the assembly shape. However, due to the dispersion of composite materials and the complexity of the structure of solar aircraft, it is difficult to control the gap between the tooling and the leading edge, so that sufficient pressure cannot be achieved. Affect the bonding effect; at the same time, the cost of large-scale assembly tooling processing and subsequent maintenance is also extremely high

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