CN103231464A - Honeycomb preforming method for large-curvature composite material interlayer piece - Google Patents

Abstract

The invention belongs to the field of aviation composite materials, and in particular relates to a honeycomb preforming method for a large-curvature composite material interlayer piece. According to the method, a honeycomb is prepaved according to the appearance and the position of a component before the component is formed, and the top of the honeycomb becomes the theoretical appearance of the component at a high temperature and a high pressure, so that the binding degree between the honeycomb and a cloth layer or a metal envelope is high when the component is formed; and the layering or gluing process is easy to implement. Compared with the conventional prior that the honeycomb is not preformed when a large-curvature honeycomb interlayer piece is formed, the position of the honeycomb is guaranteed, and the problem of slipping caused by the instability of the appearance of the honeycomb is effectively solved, so that the defects that the envelope is separated from the honeycomb and the like are reduced. Through a large amount of practice for forming the large-curvature composite material interlayer pieces with a certain machine type, the results show that both the repair rate and the rejection rate of the components after being subjected to the preformed honeycombs are greatly reduced.

Description

A kind of honeycomb preformation method for deep camber composite material interlayer spare

Technical field

The invention belongs to the aviation field of compound material, particularly relate to a kind of honeycomb preformation method for deep camber composite material interlayer spare.

Background technology

At present, the Composite Sandwich structure of using in the aerospace field is based on the cellular sandwich material.As typical interlayer spares such as tail boom, wing body radome fairings, honeycomb directly carries out lay according to the cellular line on the frock or use laser positioning projecting apparatus, but because the curvature of complicated interlayer spares such as tail boom is bigger, part vacuumize with forming process in honeycomb slippage easily takes place, solidify the back at part in addition and produce defectives such as covering and honeycomb unsticking, can cause reprocessing or scrapping of part like this.

Summary of the invention

Goal of the invention: a kind of honeycomb preformation method for deep camber composite material interlayer spare is provided, honeycomb is carried out pre-setting according to its theoretical profile in frock, can solve slippage or the depression problem of honeycomb effectively.

Technical scheme: a kind of honeycomb preformation method for deep camber composite material interlayer spare may further comprise the steps:

Step 1, clean shaping mould with acetone, make its smooth surface, no grease;

Step 2, according to the actual requirements according to digital-to-analogue establishment honeycomb cutting process, uses ultrasonic wave that honeycomb is cut;

Step 3, the honeycomb of well cutting is carried out oil removing, be laid on the shaping mould according to the cell-site line then, use protective tapes to be fixed on around the honeycomb at the edge of honeycomb, make honeycomb in shaping mould, keep dimensional stability;

Step 4, use sealing joint strip are made vacuum bag, and use vacuum film that honeycomb is protected, and vacuum bag is vacuumized, and make negative pressure be not less than 0.7bar; Be cured subsequently, cure parameter is thermostat temperature: 180 ℃ ± 10 ℃, constant temperature time: 1 hour ± 30 minutes, negative pressure was not less than 0.7bar.

Beneficial effect: the invention provides a kind of for the preformed technology of deep camber composite material interlayer spare honeycomb, make honeycomb before forming parts, carry out lay according to profile and the position of part in advance, make honeycomb reach its theoretical profile in advance through HTHP, make honeycomb like this when forming parts, with the applying degree height of layer of cloth or metal skin, be easy to spread the realization of layer or glued process.Honeycomb not being carried out preformed during with traditional deep camber honeycomb interlayer spare moulding compares, guaranteed the position of honeycomb, solve honeycomb effectively because the slippage problem that the profile instability causes, and then defectives such as minimizing covering and honeycomb unsticking, by a large amount of practices in the deep camber composite material interlayer spare moulding of certain type, the result shows through the part repair rate behind the honeycomb moulding after the preformed and scrappage and descends significantly.

Description of drawings

Fig. 1 is shaping schematic view of the present invention.

The specific embodiment

Below in conjunction with accompanying drawing the present invention is done to describe in further detail, as shown in Figure 1.

A kind of honeycomb preformation method for deep camber composite material interlayer spare may further comprise the steps:

Step 1, clean shaping mould with acetone, make its smooth surface, no grease, prevent from polluting honeycomb;

Step 2, according to the actual requirements, according to digital-to-analogue establishment honeycomb cutting process, this program is programmed according to the digital-to-analogue of honeycomb, uses the ultrasonic wave milling machine that honeycomb is cut then;

Step 3, the honeycomb of well cutting is carried out oil removing, prevent that honeycomb from polluting, be laid on the shaping mould according to the cell-site line then, use protective tapes to be fixed on around the honeycomb at the edge of honeycomb, make honeycomb in shaping mould, keep dimensional stability;

Step 4, use sealing joint strip are made vacuum bag, and use vacuum film that honeycomb is protected, and vacuum bag is vacuumized, and make negative pressure be not less than 0.7bar, and honeycomb is fitted fully with shaping mould under the effect of pressure like this; It is moulding to carry out the honeycomb HTHP subsequently, and parameter is thermostat temperature: 180 ℃ ± 10 ℃, constant temperature time: 1 hour ± 30 minutes, negative pressure was not less than 0.7bar.

Be example with the glued part of certain type tail boom structure,

Step 1, preparation honeycomb 2U and tail boom shaping mould use acetone to clean the shaping mould surface, make its smooth surface, no grease;

Step 2, (it is foundation that the honeycomb size is about 4m * 2m), and establishment honeycomb cutting process uses the ultrasonic wave milling machine that honeycomb is cut then, because the restriction of honeycomb fabric width needs 4 in honeycomb altogether with tail boom honeycomb digital-to-analogue;

Step 3, the honeycomb of well cutting is carried out oil removing, be laid on the shaping mould according to the cell-site line then, use protective tapes to be fixed on around the honeycomb at the edge of honeycomb, make honeycomb in shaping mould, keep dimensional stability;

Step 4, use sealing joint strip are made vacuum bag, and use vacuum film that honeycomb is protected, and vacuum bag is vacuumized, and make negative pressure be not less than 0.7bar; Be cured subsequently, cure parameter is thermostat temperature: 180 ℃ ± 10 ℃, constant temperature time: 1 hour ± 30 minutes, negative pressure was not less than 0.7bar.

Claims (1)

1. a honeycomb preformation method that is used for deep camber composite material interlayer spare is characterized in that, may further comprise the steps:

Step 1, clean shaping mould with acetone, make its smooth surface, no grease;

Step 2, according to the actual requirements according to digital-to-analogue establishment honeycomb cutting process, uses ultrasonic wave that honeycomb is cut;

Step 3, the honeycomb of well cutting is carried out oil removing, be laid on the shaping mould according to the cell-site line then, use protective tapes to be fixed on around the honeycomb at the edge of honeycomb, make honeycomb in shaping mould, keep dimensional stability;

Step 4, use sealing joint strip are made vacuum bag, and use vacuum film that honeycomb is protected, and vacuum bag is vacuumized, and make negative pressure be not less than 0.7bar; Be cured subsequently, cure parameter is thermostat temperature: 180 ℃ ± 10 ℃, constant temperature time: 1 hour ± 30 minutes, negative pressure was not less than 0.7bar.

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