CN114669647A

CN114669647A - Aerospace cable fairing forming device

Info

Publication number: CN114669647A
Application number: CN202210603601.6A
Authority: CN
Inventors: 王雷; 沈进
Original assignee: Jiangsu Tongda Machinery Co ltd
Current assignee: Jiangsu Tongda Machinery Co ltd
Priority date: 2022-05-31
Filing date: 2022-05-31
Publication date: 2022-06-28

Abstract

The invention discloses a forming device of a space cable fairing, which comprises a punching machine table, wherein a machine cover is fixed at the top end of the punching machine table; the invention completes the assembly and fixation of the lower die by automatically driving the first positioning posts on the supporting plate to be inserted into the first positioning holes at the two sides of the lower die, and automatically drive the second positioning column to be inserted into the second positioning hole to complete the assembly and fixation of the upper die, thereby the device is convenient for assembling and disassembling the forming die conveniently, the servo motor drives the second screw rod to rotate, the limiting box clamps the left side and the right side of the alloy plate, simultaneously starting the bidirectional cylinder to drive the clamping plate and the limiting plate to move towards the alloy plate and clamp the front side and the rear side of the alloy plate to finish the automatic calibration and adjustment of the position of the alloy plate, thereby the device can carry out automatic position calibration and adjustment on the raw alloy plate of the fairing, the rotating disc is rotated to drive the ejection block to eject the fairing body out of the fairing die cavity, so that the stamped fairing blank is easy to take out.

Description

Aerospace cable fairing forming device

Technical Field

The invention relates to the technical field of spacecraft part processing, in particular to a forming device for a spacecraft cable fairing.

Background

The spacecraft, also known as a space craft and a space craft, runs in space according to the law of celestial body mechanics, executes specific tasks such as exploration, development and utilization of space and celestial bodies, basically runs in a solar system, mainly comprises an instrument cabin, an engine, a control system and the like, runs outside the earth atmosphere after getting rid of the obstruction of the atmosphere, can receive all electromagnetic radiation information from the universe celestial body, opens up full-wave band astronomical observation, when the spacecraft flies at high speed in the atmosphere, the head-on airflow meets the spacecraft cabin body and is suddenly compressed, local airflow is also blocked, meanwhile, the airflow and the surface of the cabin body also generate friction, these all cause the temperature of the surface of the cabin to rise, causing pneumatic heating, and in order to protect the cables whose outer surface spans the cabin section, a fairing is often used for protection.

In the process of processing the spacecraft cable fairing, the fairing raw material alloy plate needs to be subjected to punch forming processing, most of the existing spacecraft cable fairing punch forming devices are single in structure, forming dies of the existing spacecraft cable fairing punch forming devices are generally fixedly arranged with a device body and cannot be assembled and disassembled conveniently, so that the forming dies are inconvenient to replace or maintain, the use is inconvenient, and the fairing blank is easy to be embedded with a die cavity in an interference manner after the punching is finished, the existing spacecraft cable fairing punch forming devices do not have the blank ejection function, so that the stamped fairing blank is difficult to take out, the labor intensity of workers is increased, the processing efficiency is reduced, in addition, the existing spacecraft cable fairing punch forming devices also need to manually adjust the position of the fairing raw material alloy plate, time and labor are wasted, and the automation degree is lower, therefore, the invention provides an aerospace cable fairing forming device which is used for solving the problems in the prior art.

Disclosure of Invention

In view of the above problems, the invention aims to provide an aerospace cable fairing forming device, which solves the problems that the existing aerospace cable fairing punch forming device cannot conveniently assemble and disassemble a forming die, does not have a blank ejection function, and cannot automatically calibrate and adjust the position of a fairing raw material alloy plate.

In order to achieve the purpose of the invention, the invention is realized by the following technical scheme: a forming device for a spaceflight cable fairing comprises a stamping machine table, wherein a machine cover is fixed at the top end of the stamping machine table, a lower die is arranged on the upper surface of the stamping machine table, a fairing die cavity is formed in the top end of the lower die, an ejection assembly is arranged in the lower die, gears driven to rotate by a motor are arranged on two sides in the stamping machine table, a rack is meshed with the top end of the gear, a supporting plate which penetrates through the stamping machine table in a sliding mode is fixed at the top end of the rack, a first positioning column is fixed on the upper portion of one side, close to the lower die, of the supporting plate, first positioning holes matched with the first positioning column are formed in two sides of the lower die, a hydraulic cylinder is arranged at the top end of the machine cover, an assembly seat is connected to the bottom end of the hydraulic cylinder, an upper die is arranged at the bottom end of the assembly seat, a stamping block is arranged at the bottom end of the upper die, a bidirectional lead screw driven to rotate by a servo motor is arranged in the assembly seat, the two-way lead screw both sides all have the screw thread to cup joint the frid and the threaded connection opposite direction that slide through the assembly seat, the frid is close to the lower part of last mould one side and is fixed with the second reference column, go up the mould both sides and all seted up the second locating hole that matches with the second reference column, aircraft bonnet both sides wall all is equipped with calibration assembly.

The further improvement lies in that: the cavity that is located fairing die cavity below is seted up to the lower mould inside, ejecting subassembly cup joints the thread piece on first lead screw including the first lead screw and the screw thread that locate in the cavity, thread piece top is equipped with the arc arch, fairing die cavity bottom has seted up the liftout groove, it is equipped with ejecting piece to slide in the liftout groove, ejecting piece bottom mounting has the fore-set that slides and run through to the cavity in, the fore-set bottom is the arc design, first lead screw runs through to the lower mould outside through the bearing and is connected with the carousel.

The further improvement lies in that: the left side and the right side of the thread block are both fixed with sliding blocks, and the left side wall and the right side wall of the cavity are both provided with sliding grooves matched with the sliding blocks.

The further improvement lies in that: the calibration subassembly is including being fixed in frame on the aircraft bonnet left and right sides inner wall and locating the second lead screw in the frame, the second lead screw passes through the servo motor drive rotation, the thread sleeve has been cup jointed to the screw thread on the second lead screw, both ends all are fixed with the connecting rod that slides and run through the frame about the thread sleeve, the one end that the connecting rod is located the frame outside is fixed with L type support frame, and is two sets of be fixed with spacing box between the L type support frame.

The further improvement is that: the lower surface of the limiting box is flush with the upper surface of the lower die, a bidirectional cylinder is arranged inside the limiting box, clamping plates which penetrate through the limiting box in a sliding mode are fixed at the output ends of the front side and the rear side of the bidirectional cylinder, and a limiting plate is fixed at one end, located outside the limiting box, of each clamping plate.

The further improvement lies in that: the hydraulic cylinder is characterized in that sleeve pipes mounted at the top end of the hood are arranged on two sides of the hydraulic cylinder, telescopic rods are slidably arranged inside the sleeve pipes, and the bottom ends of the telescopic rods are located outside the sleeve pipes and fixedly connected with the assembling seat.

The further improvement lies in that: the thread plate top is fixed with the stopper, the inside top of assembly seat is seted up the spacing groove that matches with the stopper, the stopper top extends to the spacing inslot.

The further improvement is that: the mould closing device is characterized in that a mould closing guide post is fixed at the bottom end of the upper mould, the mould closing guide posts are symmetrically distributed at four corners of the bottom end of the upper mould, and a mould closing guide hole matched with the mould closing guide post is formed in the top end of the lower mould.

The further improvement lies in that: the bottom end of the lower die is symmetrically fixed with limiting sliding strips, the top end of the stamping machine table is provided with limiting sliding rails matched with the limiting sliding strips, and the top end of the stamping machine table is rotatably connected with pulleys distributed below the lower die in an equidistance mode.

The further improvement lies in that: the front of the hood is hinged with a protective door, a transparent observation window is installed on the protective door, and a tool box is arranged at the bottom end inside the punching machine table in a sliding mode.

The invention has the beneficial effects that: the invention comprises a stamping machine table, wherein a gear is driven to rotate by a motor, a gear drives a rack to move towards a lower die, first positioning posts on a supporting plate to be inserted into first positioning holes on two sides of the lower die, the assembly and the fixation of the lower die are completed, a bidirectional screw rod is driven to rotate by a servo motor, threaded plates on two sides of the bidirectional screw rod move towards the upper die until second positioning posts are inserted into second positioning holes, the assembly and the fixation of an upper die are completed, so that the device is convenient to assemble and disassemble a forming die conveniently, and further convenient to replace or maintain the forming die, a second screw rod is driven to rotate by the servo motor, a threaded sleeve on the second screw rod drives a connecting rod and an L-shaped supporting frame to move towards the lower die and drives a limiting box to clamp the left side and the right side of an alloy plate, and a bidirectional cylinder is started to drive a clamping plate and a limiting plate to move towards the alloy plate and clamp the front side and the back side of the alloy plate, the automatic position calibration adjustment of the alloy plate is completed, so that the device can perform automatic position calibration adjustment on the fairing raw material alloy plate, the first screw rod is driven to rotate by rotating the turntable, the thread block on the first screw rod moves towards the ejection column until the arc-shaped protrusion ejects the ejection column, the ejection column drives the ejection block to eject the fairing body out of a fairing die cavity, and therefore the stamping formed fairing blank is easy to take out, the labor intensity of workers is reduced to a certain extent, and the machining efficiency is improved.

Drawings

FIG. 1 is a front view of the present invention;

FIG. 2 is a front cross-sectional view of the present invention;

FIG. 3 is an enlarged view of the invention at A;

FIG. 4 is an enlarged view of the invention at B;

FIG. 5 is an enlarged view of the invention at C;

FIG. 6 is a side cross-sectional view of a lower mold of the present invention;

FIG. 7 is a top view of the lower mold of the present invention;

FIG. 8 is a top cross-sectional view of the spacing box of the present invention;

fig. 9 is a schematic perspective view of the lower mold and the upper mold according to the present invention.

Wherein: 1. a stamping machine table; 2. a hood; 3. a lower die; 4. a fairing cavity; 5. a gear; 6. a rack; 7. a support plate; 8. a first positioning post; 9. a first positioning hole; 10. a hydraulic cylinder; 11. assembling a seat; 12. an upper die; 13. stamping the blocks; 14. a bidirectional screw rod; 15. a thread plate; 16. a second positioning column; 17. a second positioning hole; 18. a cavity; 19. a first lead screw; 20. a thread block; 21. an arc-shaped bulge; 22. ejecting the groove; 23. ejecting a block; 24. a top pillar; 25. a turntable; 26. a slider; 27. a frame; 28. a second lead screw; 29. a threaded sleeve; 30. a connecting rod; 31. an L-shaped support frame; 32. a limiting box; 33. a bidirectional cylinder; 34. a splint; 35. a limiting plate; 36. a sleeve; 37. a telescopic rod; 38. a limiting block; 39. a die assembly guide post; 40. a die closing guide hole; 41. a limiting slide bar; 42. a pulley; 43. a protective machine door; 44. a tool box.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," "third," "fourth," and the like 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 should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; 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 meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.

Referring to fig. 1, 2, 3, 4, 5, 6, 7, 8, and 9, the embodiment provides an aerospace cable fairing forming apparatus, which includes a stamping machine 1, a machine cover 2 is fixed on a top end of the stamping machine 1, the machine cover 2 is fixedly welded to the stamping machine 1, a lower mold 3 is arranged on an upper surface of the stamping machine 1, the lower mold 3 is located at a middle position of a top end of the stamping machine 1, a fairing mold cavity 4 for fairing forming is formed at a top end of the lower mold 3, an ejection assembly is arranged inside the lower mold 3, a fairing blank formed in the fairing mold cavity 4 is ejected out by the ejection assembly, gears 5 driven to rotate by a motor are arranged on two sides inside the stamping machine 1, a rack 6 is engaged with the top end of the gear 5, the rack 6 is driven to laterally displace by the rotation of the gear 5, a support plate 7 slidably penetrating through the top end of the rack 6 is fixed on the top end of the stamping machine 1, the top end of the punching machine table 1 is provided with a through groove matched with the supporting plate 7 for the supporting plate 7 to pass through and slide, the width of the rack 6 is larger than that of the through groove, the upper part of one side of the supporting plate 7 close to the lower die 3 is fixedly provided with a first positioning column 8, both sides of the lower die 3 are provided with first positioning holes 9 matched with the first positioning columns 8, the gear 5 drives the rack 6 to move towards the lower die 3 through the rotation of the motor driving gear 5, the gear 5 drives the rack 6 to move towards the lower die 3, and the first positioning columns 8 on the supporting plate 7 are inserted into the first positioning holes 9 on both sides of the lower die 3 to complete the assembly and fixation of the lower die 3, the top end of the hood 2 is provided with a hydraulic cylinder 10, the bottom end of the hydraulic cylinder 10 is connected with an assembly seat 11, the bottom end of the assembly seat 11 is provided with an upper die 12, the bottom end of the upper die 12 is provided with a punching block 13, the punching block 13 is matched with the fairing cavity 4 and matched with each other to form an alloy plate, a bidirectional screw rod 14 driven to rotate by a servo motor is arranged inside the assembly seat 11, the two sides of the bidirectional screw 14 are respectively in threaded sleeve connection with a threaded plate 15 which slidably penetrates through the assembly base 11, the threaded connection directions are opposite, the bottom end of the assembly base 11 is provided with a through groove matched with the threaded plate 15, so that the threaded plate 15 can slide in a penetrating manner, a second positioning column 16 is fixed at the lower part of the threaded plate 15, which is close to one side of the upper die 12, two sides of the upper die 12 are respectively provided with a second positioning hole 17 matched with the second positioning column 16, the bidirectional screw 14 is driven by a servo motor to rotate, the threaded plates 15 at two sides of the bidirectional screw 14 move towards the upper die 12 until the second positioning column 16 is inserted into the second positioning hole 17, the assembly and the fixation of the upper die are completed, so that the device is convenient to assemble and disassemble the forming die, the two side walls of the hood 2 are respectively provided with a calibration component, the calibration components are used for carrying out position calibration on the alloy plate at the top end of the lower die 3, and the processing precision is ensured, and no manual operation is needed.

The lower die 3 is internally provided with a cavity 18 positioned below the fairing die cavity 4, the cavity 18 is a cuboid, the ejection assembly comprises a first screw rod 19 arranged in the cavity 18 and a thread block 20 in threaded sleeve connection with the first screw rod 19, the top end of the thread block 20 is provided with an arc-shaped bulge 21, the bottom end of the fairing die cavity 4 is provided with an ejection groove 22, the ejection groove 22 is internally provided with an ejection block 23 in a sliding manner, the outer wall of the ejection block 23 is attached to the inner wall of the ejection groove 22, the bottom end of the ejection block 23 is fixedly provided with an ejection column 24 which penetrates into the cavity 18 in a sliding manner, the bottom end of the ejection column 24 is in an arc-shaped design, the first screw rod 19 penetrates to the outside of the lower die 3 through a bearing and is connected with a turntable 25, the first screw rod 19 is driven to rotate by rotating the turntable 25, the thread block 20 on the first screw rod 19 is enabled to move towards the ejection column 24, the ejection column 24 is jacked up until the arc-shaped bulge 21 jacks up the ejection column 24, the ejection column 24 drives the ejection block 23 to eject the fairing body out of the fairing die cavity 4, thereby the punched and formed fairing blank is easy to take out.

The left side and the right side of the thread block 20 are both fixed with sliding blocks 26, sliding grooves matched with the sliding blocks 26 are formed in the left side wall and the right side wall of the cavity 18, the sliding blocks 26 extend into the sliding grooves, the thread block 20 is limited through the matching of the sliding grooves and the sliding blocks 26, and the thread block 20 is more stable in the moving process.

The calibration assembly comprises a frame 27 fixed on the inner walls of the left side and the right side of the hood 2 and a second lead screw 28 arranged in the frame 27, the second lead screw 28 is rotatably connected in the frame 27, the second lead screw 28 is driven to rotate by a servo motor, a thread sleeve 29 is sleeved on the second lead screw 28, a connecting rod 30 which penetrates through the frame 27 in a sliding manner is fixed at each of the upper end and the lower end of the thread sleeve 29, through grooves matched with the connecting rod 30 are formed in each of the upper side and the lower side of the frame 27 for the connecting rod 30 to penetrate and slide, an L-shaped support frame 31 is fixed at one end of the connecting rod 30 positioned outside the frame 27, a limit box 32 is fixed between the two groups of L-shaped support frames 31, the second lead screw 28 is driven to rotate by the servo motor, the thread sleeve 29 on the second lead screw 28 drives the connecting rod 30 and the L-shaped support frame 31 to move towards the lower die 3 and drives the limit box 32 to clamp the left side and the right side of the alloy plate, the lower surface of spacing box 32 is equal to the upper surface of bed die 3, the inside two-way cylinder 33 that is equipped with of spacing box 32, the output of both sides all is fixed with the splint 34 that slide and run through spacing box 32 around two-way cylinder 33, splint 34 are located the outside one end of spacing box 32 and are fixed with limiting plate 35, move and carry out the centre gripping to alloy panel's front and back both sides through starting two-way cylinder 33 drive splint 34 and limiting plate 35, accomplish the automatic calibration adjustment of alloy panel position.

The hydraulic cylinder 10 is provided with two sides with sleeves 36 mounted on the top of the hood 2, the bottom ends of the sleeves 36 are located inside the hood 2, telescopic rods 37 are slidably arranged inside the sleeves 36, the bottom ends of the telescopic rods 37 are located outside the sleeves 36 and fixedly connected with the assembling seat 11, and the telescopic rods 37 and the sleeves 36 are matched to play a certain limiting role in the assembling seat 11, so that the upper die 12 is more stable in the lifting process.

The threaded plate 15 top is fixed with stopper 38, and the spacing groove that matches with stopper 38 is seted up on the inside top of assembly seat 11, and stopper 38 top extends to the spacing inslot, comes to carry on spacingly to threaded plate 15 through the cooperation of spacing groove and stopper 38 to it is more stable to make threaded plate 15 remove the in-process.

The bottom end of the upper die 12 is fixed with die closing guide posts 39, the die closing guide posts 39 are provided with four groups, the four groups of die closing guide posts 39 are symmetrically distributed at four corners of the bottom end of the upper die 12, the top end of the lower die 3 is provided with die closing guide holes 40 matched with the die closing guide posts 39, the die closing guide posts 39 are inserted into the die closing guide holes 40 during die closing, and the die closing accuracy is guaranteed.

3 bottom end symmetries of bed die are fixed with spacing draw runner 41, and the spacing slide rail that matches with spacing draw runner 41 is seted up on punching press board 1 top, and spacing draw runner 41 extends to in the spacing slide rail, plays the spacing guide effect to bed die 3, avoids bed die 3 to take place the skew, and 1 top of punching press board is rotated and is connected with the equidistance and distributes in the pulley 42 of bed die 3 below, makes the bed die be convenient for slide on 1 top of punching press board through setting up pulley 42.

The front of aircraft bonnet 2 is articulated to be installed protection machine door 43, and protection machine door 43 passes through the hinge symmetry and articulates to be installed in aircraft bonnet 2 openly, installs transparent observation window on the protection machine door 43, and the user of being convenient for observes, and the inside bottom of punching press board 1 slides and is equipped with toolbox 44, and the user of being convenient for deposits the machining tool.

When the fairing is required to be subjected to punch forming processing through the aerospace cable fairing forming device, the method comprises the following steps:

firstly, a lower die 3 and an upper die 12 are placed on a punching machine table 1, a limiting slide bar 41 at the bottom end of the lower die 3 is inserted into a limiting slide rail at the top end of the punching machine table 1, then the lower die 3 and the upper die 12 are pushed to the right below the assembling seat 11 by using the pulley 42, the motor is started again to drive the gear 5 to rotate, the gear 5 drives the rack 6 to move towards the lower die 3, and the first positioning columns 8 on the supporting plate 7 are inserted into the first positioning holes 9 at the two sides of the lower die 3 to complete the assembly and fixation of the lower die, then the hydraulic cylinder 10 is started to drive the assembly seat 11 to descend until the lower surface of the assembly seat 11 is attached to the upper surface of the upper die 12, then, a servo motor is started to drive the bidirectional screw rod 14 to rotate, so that the thread plates 15 on two sides of the bidirectional screw rod 14 move towards the upper die 12 until the second positioning column 16 is inserted into the second positioning hole 17, and the assembly and fixation of the upper die are completed;

after the lower die 3 and the upper die 12 are assembled, firstly, a fairing raw material alloy plate to be processed is placed at the top end of the lower die 3, then a servo motor is started to drive a second screw rod 28 to rotate, a threaded sleeve 29 on the second screw rod 28 drives a connecting rod 30 and an L-shaped support frame 31 to move towards the lower die 3 and drives a limiting box 32 to clamp the left side and the right side of the alloy plate, meanwhile, a bidirectional cylinder 33 is started to drive a clamping plate 34 and a limiting plate 35 to move towards the alloy plate and clamp the front side and the rear side of the alloy plate, so that the position of the alloy plate is adjusted through clamping in four directions, automatic calibration and adjustment of the position of the alloy plate are completed, and then the limiting box 32 and the limiting plate 35 are reset;

and step three, after the position of the alloy plate is adjusted, firstly starting the hydraulic cylinder 10 to drive the assembly seat 11 and the upper die 12 to descend, stamping the alloy plate by using the stamping block 13 until the upper die 12 and the lower die 3 are combined, forming the fairing by matching the stamping block 13 with the fairing cavity 4, then starting the hydraulic cylinder 10 to lift the upper die 12, wherein the stamped fairing is embedded in the fairing cavity 4 in an interference manner, then rotating the turntable 25 to drive the first screw rod 19 to rotate, so that the thread block 20 on the first screw rod 19 moves towards the direction of the ejection column 24 until the arc-shaped protrusion 21 ejects the ejection column 24, and then driving the ejection block 23 by the ejection column 24 to eject the fairing body out of the fairing cavity 4, thereby finishing stamping forming and taking materials after the fairing.

The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.

Claims

1. The utility model provides an aerospace cable radome fairing forming device which characterized in that: the stamping machine comprises a stamping machine table (1), a machine cover (2) is fixed at the top end of the stamping machine table (1), a lower die (3) is arranged on the upper surface of the stamping machine table (1), a fairing die cavity (4) is formed in the top end of the lower die (3), an ejection assembly is arranged inside the lower die (3), gears (5) driven to rotate through a motor are arranged on two sides inside the stamping machine table (1), a rack (6) is meshed with the top end of the gears (5), a supporting plate (7) penetrating through the stamping machine table (1) in a sliding mode is fixed at the top end of the rack (6), a first positioning column (8) is fixed on the upper portion of one side, close to the lower die (3), of the supporting plate (7), a first positioning hole (9) matched with the first positioning column (8) is formed in each of two sides of the lower die (3), a hydraulic cylinder (10) is arranged at the top end of the machine cover (2), an assembling seat (11) is connected with the bottom of the hydraulic cylinder (10), assembly seat (11) bottom is equipped with mould (12), it is equipped with punching press piece (13) to go up mould (12) bottom, assembly seat (11) inside is equipped with two-way lead screw (14) through servo motor drive rotation, the equal screw thread in two-way lead screw (14) both sides has cup jointed screw plate (15) and the opposite direction of threaded connection that slide run through assembly seat (11), the lower part that screw plate (15) are close to last mould (12) one side is fixed with second reference column (16), go up mould (12) both sides and all offer second locating hole (17) that match with second reference column (16), aircraft bonnet (2) both sides wall all is equipped with calibration assembly.

2. An aerospace cable fairing forming apparatus as recited in claim 1, wherein: the inner part of the lower die (3) is provided with a cavity (18) below the fairing die cavity (4), the ejection assembly comprises a first screw rod (19) arranged in the cavity (18) and a thread block (20) sleeved on the first screw rod (19) in a threaded manner, the top end of the thread block (20) is provided with an arc-shaped protrusion (21), the bottom end of the fairing die cavity (4) is provided with an ejection groove (22), the ejection groove (22) is internally provided with an ejection block (23) in a sliding manner, the bottom end of the ejection block (23) is fixed with an ejection column (24) which penetrates into the cavity (18) in a sliding manner, the bottom end of the ejection column (24) is designed in an arc manner, and the first screw rod (19) penetrates through the outer part of the lower die (3) through a bearing and is connected with a turntable (25).

3. An aerospace cable fairing forming apparatus as recited in claim 2, wherein: the left side and the right side of the thread block (20) are both fixed with sliding blocks (26), and the left side wall and the right side wall of the cavity (18) are both provided with sliding grooves matched with the sliding blocks (26).

4. An aerospace cable fairing forming apparatus as recited in claim 1, wherein: the calibration subassembly is including being fixed in frame (27) on the aircraft bonnet (2) left and right sides inner wall and locating second lead screw (28) in frame (27), second lead screw (28) are rotatory through the servo motor drive, threaded sleeve (29) have been gone up in second lead screw (28), both ends all are fixed with connecting rod (30) that slide and run through frame (27) about threaded sleeve (29), connecting rod (30) are located the outside one end of frame (27) and are fixed with L type support frame (31), and are two sets of be fixed with spacing box (32) between L type support frame (31).

5. An aerospace cable fairing forming apparatus as recited in claim 4, wherein: the lower surface of spacing box (32) and the upper surface of bed die (3) keep level, inside two-way cylinder (33) that is equipped with of spacing box (32), the output of both sides all is fixed with splint (34) that the slip runs through spacing box (32) around two-way cylinder (33), splint (34) are located the outside one end of spacing box (32) and are fixed with limiting plate (35).

6. An aerospace cable fairing forming apparatus as recited in claim 1, wherein: the hydraulic cylinder (10) is characterized in that two sides of the hydraulic cylinder (10) are respectively provided with a sleeve (36) installed at the top end of the hood (2), an expansion rod (37) is arranged inside the sleeve (36) in a sliding mode, and the bottom end of the expansion rod (37) is located outside the sleeve (36) and fixedly connected with the assembling seat (11).

7. An aerospace cable fairing forming apparatus as recited in claim 1, wherein: the threaded plate (15) top is fixed with stopper (38), the inside top of assembly seat (11) is seted up the spacing groove that matches with stopper (38), stopper (38) top extends to the spacing inslot.

8. An aerospace cable fairing forming apparatus as recited in claim 1, wherein: the bottom end of the upper die (12) is fixed with die closing guide posts (39), the die closing guide posts (39) are symmetrically distributed at four corners of the bottom end of the upper die (12), and die closing guide holes (40) matched with the die closing guide posts (39) are formed in the top end of the lower die (3).

9. An aerospace cable fairing forming apparatus as recited in claim 1, wherein: the stamping machine is characterized in that limiting sliding strips (41) are symmetrically fixed to the bottom end of the lower die (3), limiting sliding rails matched with the limiting sliding strips (41) are arranged on the top end of the stamping machine table (1), and pulleys (42) distributed below the lower die (3) in an equidistance mode are rotatably connected to the top end of the stamping machine table (1).

10. An aerospace cable fairing forming apparatus as recited in claim 1, wherein: the utility model discloses a punching press board, including aircraft bonnet (2), aircraft bonnet (2) openly articulated install protection machine door (43), install transparent observation window on protection machine door (43), the inside bottom of punching press board (1) slides and is equipped with tool holder (44).