CN201329631Y - Mould parting surface structure of helicopter composite material blade forming mould - Google Patents

Abstract

The utility model discloses a mould parting surface structure of a helicopter composite materials blade forming mould, which belongs to the composite material forming technique and relates to an improvement of a composite material blade forming mould. The mould parting surface structure is formed by jointing an upper mould (1) and a lower mould (2), and is characterized in that on a chordwise sectional plane of the upper mould (1) and the lower mould (2), a clearance section (4) is arranged in the middle portion of a mould parting surface of the upper mould (1) and the lower mould (2), and the chordwise length of the mould parting surface at two ends of the clearance section (4) is not less than 10 mm. The utility model not only reduces processing area of a joint surface of the upper mould and the lower mould of the mould, but also enable the total mould to be flat in jointing, a mould joint surface clearance is controlled under 0.2 mm, which is extremely uniform, thereby increasing blade forming quality.

Description

Composite material blade of helicopter mould die joint structure

Technical field

The utility model belongs to the composite material forming technology, relates to the improvement to the composite material blade of helicopter mould.

Background technology

Existing composite material blade of helicopter mould is whole die joint, and blade die cavity both sides all are contact-making surface.Its shortcoming is: the die joint working (finishing) area is too big up and down for mould, and upper and lower mould can't be fitted smooth, causes matched moulds excesssive gap and gap inhomogeneous, greatly influences the Forming Quality of blade.

Summary of the invention

The purpose of this utility model is: propose a kind of can reduce mould up and down the die joint working (finishing) area, guarantee the composite material blade of helicopter mould in upper and lower mould matched moulds gap again.

The technical solution of the utility model is: composite material blade of helicopter mould die joint structure, form by upper die and lower die are involutory, the blade die cavity is arranged between upper die and lower die, it is characterized in that, on the tangential section of upper die and lower die, there is a gap section at the middle part of the die joint of upper die and lower die, this gap section is opened up to stretching, extension along blade, the clearance t of gap section=0.3～0.5mm, the allocations of gap section on upper die and lower die is respectively 1/2t, and the tangential length of the die joint at section two ends, gap is not less than 10mm.

The utility model has the advantages that: the working (finishing) area that has both reduced mould upper and lower mould land area, also reduced the fitting area of entire die matched moulds, it is smooth to make entire die fit, and the matched moulds clearance control is below 0.2mm, and very even, thereby improved the Forming Quality of blade.And, can not influence the heat-transfer effect of upper die and lower die.

Description of drawings

Fig. 1 is a structural representation of the present utility model.

The specific embodiment

Below the utility model is described in further details.Referring to Fig. 1, composite material blade of helicopter mould die joint structure, by patrix 1 and 2 involutory compositions of counterdie, between patrix 1 and counterdie 2, blade die cavity 3 is arranged, it is characterized in that, on the tangential section of patrix 1 and counterdie 2, there is a gap section 4 at the middle part of the die joint of patrix 1 and counterdie 2, this gap section 4 is opened up to stretching, extension along blade, the clearance t of gap section=0.3～0.5mm, the allocations of gap section 4 on patrix 1 and counterdie 2 is respectively 1/2t, and the tangential length of the die joint at section two ends, gap is not less than 10mm.

Operation principle of the present utility model is: the middle part at the die joint of upper die and lower die increases a gap section, this gap section is opened up to stretching, extension along blade, both reduced the working (finishing) area of mould upper and lower mould land area, also reduced the fitting area of entire die matched moulds, it is smooth to make entire die fit, the matched moulds clearance control and can not influence the heat-transfer effect of upper die and lower die below 0.2mm, thereby has improved the Forming Quality of blade.

Among the embodiment of the present utility model, the clearance t=0.4mm of gap section, the allocations of gap section 4 on patrix 1 and counterdie 2 is respectively 0.2mm, and the tangential length of the die joint at section two ends, gap is 20mm.

Claims (1)

1, composite material blade of helicopter mould die joint structure, by patrix [1] and counterdie [2] involutory composition, between patrix [1] and counterdie [2], blade die cavity [3] is arranged, it is characterized in that, on the tangential section of patrix [1] and counterdie [2], there is a gap section [4] at the middle part of the die joint of patrix [1] and counterdie [2], this gap section [4] is opened up to stretching, extension along blade, the clearance t of gap section=0.3～0.5mm, the allocations of gap section [4] on patrix [1] and counterdie [2] is respectively 1/2t, and the tangential length of the die joint at gap section [4] two ends is not less than 10mm.