CN210257394U

CN210257394U - Aircraft combined material door body forming die

Info

Publication number: CN210257394U
Application number: CN201920793082.8U
Authority: CN
Inventors: 孙建毅
Original assignee: Guizhou Anshun Longfei Auto Parts Co Ltd
Current assignee: Guizhou Anshun Longfei Auto Parts Co Ltd
Priority date: 2019-05-29
Filing date: 2019-05-29
Publication date: 2020-04-07
Anticipated expiration: 2029-05-29

Abstract

The utility model discloses an aircraft combined material door body forming die, it is concrete including the die, the concrete upper end both sides of die are provided with four round holes, be provided with the connecting rod in the round hole, the connecting rod upper end fixed connection terrace die is concrete, the concrete up end of die is provided with a body shaping groove, door body shaping groove upper end is provided with combined material goods, door body shaping groove lower extreme bottom is provided with the recess, the kicking block has been placed to the recess inside, the recess bottom is provided with the screw hole, screw hole threaded connection threaded rod, door body shaping groove lower extreme both sides are provided with the through-hole, the through-hole bottom is provided with the runner pipe. An aircraft combined material door body forming die, through setting up the through-hole, the air vent internal diameter is greater than air vent internal diameter down on the through-hole, plays the cushioning effect when the punching press, when the drawing of patterns, increase gaseous area of contact sets up threaded rod and kicking block cooperation, when the drawing of patterns of the mould body, carries out the drawing of patterns to its bottom.

Description

Aircraft combined material door body forming die

Technical Field

The utility model relates to the technical field of mold, in particular to aircraft combined material door body forming die.

Background

The composite material is a new material formed by optimizing and combining material components with different properties by using an advanced material preparation technology, and is widely applied to various fields due to the properties of excellent chemical stability, friction reduction, wear resistance, self lubrication, heat resistance, fatigue resistance, creep resistance, noise elimination, electric insulation and the like.

SUMMERY OF THE UTILITY MODEL

The utility model discloses a main aim at provides an aircraft combined material door body forming die can effectively solve the problem in the background art.

In order to achieve the above purpose, the utility model adopts the following technical scheme:

the utility model provides an aircraft combined material door body forming die, it is concrete including the die, the concrete upper end both sides of die are provided with four round holes, be provided with the connecting rod in the round hole, the concrete male die of connecting rod upper end fixed connection, the concrete up end of die is provided with a body shaping groove, door body shaping groove upper end is provided with combined material goods, door body shaping groove lower extreme bottom is provided with the recess, the kicking block has been placed to the recess inside, the recess bottom is provided with the screw hole, screw hole threaded connection threaded rod, door body shaping groove lower extreme both sides are provided with the through-hole, the through-hole bottom is provided with the runner pipe, the runner pipe.

Preferably, round hole bottom fixed mounting has buffer spring, buffer spring top fixed connection buffer block, the terrace die specifically inlays through the connecting rod and inserts in the round hole with the concrete sliding connection of die.

Preferably, the upper end and the lower end of the through hole are respectively provided with an upper vent hole and a lower vent hole, and the inner diameter of the upper vent hole is larger than that of the lower vent hole.

Preferably, the upper end of the top block is provided with a groove end face matched with the arc of the door body forming groove, and a silica gel layer is fixedly mounted on the groove end face.

Preferably, the bottom end of the sealing valve is in threaded connection with a vent pipe, the interior of the vent pipe is of a hollow structure, a sealing ring is sleeved on a screw rod of the sealing valve, and the sealing valve is inserted through the sealing ring and is in threaded connection with a flow pipe.

Preferably, the external thread at the upper end of the vent pipe is matched with the internal thread at the lower end of the flow pipe, and the outer end of the thread of the vent pipe is sleeved with a sealing gasket.

Compared with the prior art, the utility model discloses following beneficial effect has:

the utility model discloses in, through setting up the through-hole, the air vent internal diameter is greater than air vent internal diameter down on the through-hole, play the cushioning effect when the punching press, when the drawing of patterns, increase gas contact area, increase lifting surface area, make the mould body atress during the drawing of patterns even, avoid damaging the mould body, through setting up threaded rod and kicking block cooperation, when the mould body drawing of patterns, carry out the drawing of patterns to its bottom, the kicking block upper end sets to concave type and is provided with the silica gel layer on and, the protection mould, increase mould life, through set up the breather pipe on the seal valve, can be sealed and the state of ventilating switches wantonly, one is multi-purpose, and the cost is saved, and.

Drawings

Fig. 1 is a schematic view of the overall structure of the composite door body forming mold for an airplane of the present invention;

fig. 2 is a schematic view of the screw rod and the top block of the composite material door body forming mold for an airplane according to the present invention;

fig. 3 is a schematic structural view of a through hole of the composite door body forming mold for an airplane of the present invention;

fig. 4 is a schematic structural diagram of the sealing valve of the composite door body forming mold for an airplane of the present invention.

In the figure: 1. a female die is concrete; 2. a male die body; 3. a connecting rod; 4. a door body forming groove; 5. a composite article; 6. a groove; 61. a top block; 611. end faces of the grooves; 612. a silica gel layer; 7. a threaded hole; 8. a threaded rod; 9. a circular hole; 10. a buffer spring; 11. a buffer block; 12. a flow-through tube; 13. a sealing valve; 131. a breather pipe; 132. a seal ring; 133. a gasket; 14. a through hole; 141. an upper vent; 142. a lower vent.

Detailed Description

In order to make the technical means, creation features, achievement purposes and functions of the present invention easy to understand, the present invention is further described below with reference to the following embodiments.

In the description of the present invention, it should be noted that the terms "upper", "lower", "inner", "outer", "front end", "rear end", "both ends", "one end", "the other end" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplification of description, but do not indicate or imply that the device or element to which the reference is made must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first" and "second" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.

In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "disposed," "connected," and the like are to be construed broadly, and for example, "connected" may be either fixedly connected or detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art.

As shown in fig. 1 to 4, an aircraft composite door body forming mold is characterized in that: including the concrete 1 of die, the concrete 1 upper end both sides of die are provided with four round holes 9, be provided with connecting rod 3 in the round hole 9, the concrete 2 of connecting rod 3 upper end fixed connection terrace die, the concrete 1 up end of die is provided with a body shaping groove 4, body shaping groove 4 upper end is provided with combined material goods 5, 4 lower extreme bottoms in body shaping groove are provided with recess 6, kicking block 61 has been placed to recess 6 inside, recess 6 bottoms are provided with

screw hole

7, 7 threaded connection threaded rod 8 in screw hole, 4 lower extreme both sides in body shaping groove are provided with through-

hole

14, 14 bottoms in through-hole are provided with runner pipe 12, the 12 lower extreme of runner pipe.

The bottom end of the round hole 9 is fixedly provided with a buffer spring 10, the top end of the buffer spring 10 is fixedly connected with a buffer block 11, the male die body 2 is embedded in the round hole 9 through the connecting rod 3 and is in sliding connection with the female die body 1, when punching is carried out to form a film, the buffer block 11 is contacted with the bottom of the connecting rod 3, and the buffer spring 10 has the effect of buffering impact force, so that the device has certain buffering performance and prevents the die from being damaged due to overlarge impact; the upper end and the lower end of the through hole 14 are respectively provided with an upper vent hole 141 and a lower vent hole 142, the inner diameter of the upper vent hole 141 is larger than that of the lower vent hole 142, so that air can be uniformly discharged when air is required to be discharged, and the contact area can be increased when air is required to be introduced and demoulded, so that the stress area is increased, demoulding is easier, and a mould cannot be damaged; the upper end of the top block 61 is provided with a groove end surface 611 matched with the arc of the door body forming groove 4, a silica gel layer 612 is fixedly arranged on the groove end surface 611, the silica gel layer 612 has buffering and anti-skidding functions, and when the top block 61 moves upwards for demoulding, a mould in demoulding cannot be damaged; the bottom end of the sealing valve 13 is connected with a vent pipe 131 in a threaded manner, the interior of the vent pipe 131 is of a hollow structure, a sealing ring 132 is sleeved on a screw rod of the sealing valve 13, the sealing valve 13 penetrates through the sealing ring 132 to be connected with the flow pipe 12 in a threaded manner, and the sealing ring 132 can keep the joint from air leakage and keep the air tightness of the whole device; the external thread of the upper end of the breather pipe 131 is matched with the internal thread of the lower end of the flow pipe 12, and the outer end of the thread of the breather pipe 131 is sleeved with a sealing gasket 133, so that the breather pipe is multipurpose, the efficiency is improved, and the cost is saved.

It should be noted that, the utility model relates to an aircraft composite door body forming die, through installing door body shaping groove 4 on the die body 1, utilize the punching press of the punch body 2, realize the integrated into one piece mould, when using, screw up the seal valve 13 with runner pipe 12 threaded connection, place composite material in door body shaping groove 4, reuse punch body 2 to punch, the whole punching press process gas tightness is good, punch body 2 has orbital execution punching press through connecting rod 3, the buffer spring 10 and the buffer block 11 that set up in the round hole 9, can effectively slow down the impact force, avoid the strong impact to damage whole mould, the through-hole 14 on runner pipe 12 that sets up in door body shaping groove 4 lower extreme, the through-hole 14 can be timely released the interior gas during punching press, avoid the air to intervene in the composite material, when needing the drawing of patterns, screw down seal valve 13, the vent pipe 131 and the vent pipe 131 on the die are communicated with the air blower to realize the upper part of the die to be demolded, the threaded rod 8 is rotated again to enable the top block 61 placed in the groove 6 to move upwards to realize the bottom demolding, and the groove end face 611 and the silica gel layer 612 are arranged on the top block 61 to prevent the die from being damaged.

The basic principles and the main features of the invention and the advantages of the invention have been shown and described above. It will be understood by those skilled in the art that the present invention is not limited to the above embodiments, and that the foregoing embodiments and descriptions are provided only to illustrate the principles of the present invention without departing from the spirit and scope of the present invention. The scope of the invention is defined by the appended claims and equivalents thereof.

Claims

1. The utility model provides an aircraft combined material door body forming die which characterized in that: comprises a female die body (1), four round holes (9) are arranged on two sides of the upper end of the female die body (1), a connecting rod (3) is arranged in the round hole (9), the upper end of the connecting rod (3) is fixedly connected with the male die body (2), a door body forming groove (4) is arranged on the upper end surface of the female die body (1), a composite material product (5) is arranged at the upper end of the door body forming groove (4), a groove (6) is arranged at the bottom of the lower end of the door body forming groove (4), a top block (61) is arranged in the groove (6), the bottom of the groove (6) is provided with a threaded hole (7), the threaded hole (7) is in threaded connection with a threaded rod (8), through holes (14) are formed in two sides of the lower end of the door body forming groove (4), a circulating pipe (12) is arranged at the bottom end of each through hole (14), and a sealing valve (13) is arranged at the lower end of each circulating pipe (12).

2. The aircraft composite door body molding die according to claim 1, characterized in that: round hole (9) bottom fixed mounting has buffer spring (10), buffer spring (10) top fixed connection buffer block (11), the terrace die is concrete (2) to inlay through connecting rod (3) and insert in round hole (9) with the concrete (1) sliding connection of die.

3. The aircraft composite door body molding die according to claim 1, characterized in that: the upper end and the lower end of the through hole (14) are respectively provided with an upper vent hole (141) and a lower vent hole (142), and the inner diameter of the upper vent hole (141) is larger than that of the lower vent hole (142).

4. The aircraft composite door body molding die according to claim 1, characterized in that: the upper end of the top block (61) is arranged to be a groove end face (611) matched with the arc of the door body forming groove (4), and a silica gel layer (612) is fixedly mounted on the groove end face (611).

5. The aircraft composite door body molding die according to claim 1, characterized in that: seal valve (13) bottom threaded connection has breather pipe (131), breather pipe (131) are inside to be hollow structure, seal valve (13) screw rod cover is equipped with sealing washer (132), seal valve (13) have been alternated seal ring (132) threaded connection runner pipe (12).

6. The aircraft composite door body molding die of claim 5, wherein: the upper end external thread of breather pipe (131) and the internal thread phase-match of runner pipe (12) lower extreme, breather pipe (131) screw thread outer pot head is equipped with sealed pad (133).