CN107571055A - A kind of deep hole machining fixture and processing method for guided missile rudder face skeleton component - Google Patents

Abstract

A deep hole processing fixture and processing method for missile rudder surface skeleton components, the fixture includes brackets, latches, positioning blocks, pre-processing fixing blocks, rear processing fixing blocks and other components, during processing, parts to be processed are installed by positioning , installation of processing fixtures, positioning processing and other steps to complete the deep hole processing of the missile rudder surface skeleton skin riveting components. Through the implementation of the present invention, it is realized that the fitter drills and reams the deep hole on the radial drilling machine, and the manufacturing accuracy of the deep hole processing device is used to ensure the processing accuracy of the deep hole of the skeleton skin riveting assembly, the product quality is reliable, the processing efficiency is significantly improved, and effective The efficiency bottleneck of deep hole processing of rudder surface skeleton skin riveting components is solved. The device has the advantages of simple operation, good reliability and strong practicability, and can be popularized in deep hole processing and production of missile rudder surfaces.

Description

A deep hole processing fixture and processing method for missile rudder surface skeleton components

technical field

The invention relates to a missile rudder surface processing technology, in particular to a deep hole processing fixture and a processing method for a missile rudder surface skeleton assembly.

Background technique

The rudder surface is an indispensable and important component of modern missiles. As the control surface of the missile, its main purpose is to provide lift and flight control force for the missile during flight, so that the missile can fly according to the predetermined trajectory. The main part of the rudder surface——skeleton-skin riveted component generally adopts an aluminum alloy frame structure, and the outer surface is riveted with skin. In order to strengthen the strength and rigidity of the notch of the skeleton, stainless steel bushings are embedded in the notch. The processing method is to press the stainless steel bushing into the notch of the skeleton after the skeleton is processed, then rivet the skin, then finish the root rib surface and the notch, and finally process the deep hole of the notch. Since the front edge side of the skeleton skin riveting component is a closed cavity, the processing tool can only be extended from one end, the overhang is very large, the hole size accuracy is relatively high, the tolerance level can reach IT8, and the hole surface roughness requirement is Ra1. .6μm, and the shape and position tolerances are required to be within 0.02mm. In the usual processing technology, the method of drilling the bottom hole and milling the hole with the end mill end tooth is usually used. The processing efficiency is low, which has seriously restricted the production capacity of the rudder surface processing and production, thus affecting the overall production progress of the entire missile. The bottleneck of mass production capacity of missiles.

Contents of the invention

In order to solve the above-mentioned technical problems, the present invention provides a deep hole processing fixture and processing method for missile rudder surface skeleton components.

The present invention is achieved through the following technical solutions.

The present invention provides a deep hole processing fixture for missile rudder surface skeleton components, including a bracket, a latch, a positioning block, a front processing fixing block and a rear processing fixing block, the positioning block is fixed on the bracket; the front processing fixing block The block is arranged on the surface of the bracket, and the front processing fixed block is provided with a bushing hole corresponding to the position and size of the hole to be processed in the rudder surface skeleton skin riveting assembly; the rear processing fixed block is arranged at the bottom center of the bracket, and the rudder The right end of the surface skeleton skin riveting assembly is fixed on the rear processing fixing block, and the rear processing fixing block is provided with a processing groove corresponding to the position and size of the hole to be processed in the rudder surface skeleton skin riveting assembly.

The bracket is also provided with a lateral fixing block, and the lateral fixing block is provided with a threaded hole, and the lateral fixing screw passes through the threaded hole to fasten the rudder surface skeleton skin riveting assembly on the fixing block.

The lateral fixing block is located on one side of the rudder surface skeleton skin riveting assembly, corresponding to the fixing block.

It also includes a replaceable drill sleeve and a replaceable reaming sleeve. When drilling, the replaceable drill sleeve is placed in the bushing hole of the pre-processed fixed block. When the reaming operation is performed, the The hinge replacement sleeve is placed in the bushing hole of the pre-processed fixed block.

It also includes a drill template body and a hinge template body. When performing a drilling operation, the drill template body is fixed on the processing groove of the post-processing fixed block. When performing a reaming operation, the hinge template body is fixed on the On the processing groove of the post-processing fixed block.

It also includes a fastening positioning pin, a fastening nut, a fastening bolt and a fastening screw sleeve. Two positioning holes are arranged on the post-processed fixing block, and the fastening positioning pin passes through the fastening nut and enters one of the positioning holes. , the fastening bolt passes through the fastening nut and enters another positioning hole; during drilling operation, the fastening positioning pin fixes the drilling mold body through the fastening nut, and the fastening bolt fixes the drilling mold body through the fastening nut. During the reaming operation, the fastening positioning pin fixes the hinge mold body through the fastening nut, and the fastening bolt fixes the hinge mold body through the fastening screw sleeve.

When performing drilling operations, the drilling holes of the replaceable drill sleeve and the drilling holes of the drilling template body remain coaxial; when performing reaming operations, the drilling holes of the replaceable reaming sleeve and the drilling holes of the reaming template body remain coaxial.

The connection between the fixed block and the bracket is provided with a front positioning screw and a front positioning pin; the connection between the front processing fixed block and the bracket is provided with a front processing fixing pin and a front processing fixing screw; the rear processing fixing block There are post-processing positioning pins and post-processing fixing screws at the connection with the bracket; lateral fixing screws are provided at the connection between the lateral positioning block and the bracket.

The front positioning screw, the front processing fixing screw, the rear processing fixing screw and the lateral fixing screw are all hexagon socket screws.

A deep hole processing method for a missile rudder surface skeleton skin riveting assembly, comprising the following steps:

Step 1: Calibrate the verticality of the bracket. After the verticality meets the operation requirements, position the rudder surface skeleton skin riveting assembly on the bracket through the bolt, and then tighten the screw to fix the rudder surface skeleton skin riveting assembly on the fixed block. side;

Step 2: Put the replaceable drill set into the bushing hole of the positioning block, put the drill template body into the rectangular groove of the post-processed fixing block, and make the positioning holes on both sides of the drill template body pass through the fastening positioning pins respectively, tightly Fastening nuts, fastening bolts and fastening nuts are used for fixing, and the edge of the positioning block is in contact with one side of the rudder surface skeleton skin riveting assembly during installation;

Step 3: Install the positioning mandrel on the machine spindle of the radial drilling machine, rotate the rocker arm of the machine tool, so that the positioning mandrel can be smoothly inserted into the corresponding hole of the drill body, so that the coaxiality with the hole on the drill body is not greater than φ0 .01mm, the perpendicularity with the bracket is not more than 0.01mm, then replace the positioning mandrel with a drill bit to drill the bottom hole;

Step 4: After the bottom hole is drilled, replace the replaceable drill sleeve with a replaceable reamer sleeve, replace the drill body with a reamer body, replace the tool with a reamer, and perform reaming.

The beneficial effects of the present invention are: through the implementation of the present invention, the fitter drills and reams the deep hole on the radial drilling machine, and utilizes the manufacturing precision of the deep hole processing device to ensure the deep hole processing precision of the skeleton skin riveting assembly, and the product quality is reliable , the processing efficiency is significantly improved, effectively solving the efficiency bottleneck of deep hole processing of the rudder surface skeleton skin riveting components. The device has the advantages of simple operation, good reliability and strong practicability, and can be popularized in deep hole processing and production of missile rudder surfaces.

Description of drawings

Fig. 1 is a schematic view of the fixture structure of the present invention;

Fig. 2 is a top view of the fixture structure of the present invention;

Fig. 3 is the structural representation of post processing fixed block of the present invention;

Fig. 4 is the structural representation of drill body and hinged body of the present invention;

Fig. 5 is the plan view of drill template body and hinge template body of the present invention;

Fig. 6 is the structure schematic diagram of the rudder surface skeleton skin riveting assembly that the present invention needs to process;

In the figure: 1-bracket, 2-bolt, 3-positioning block, 4-fixing block for front processing, 5-replaceable drill sleeve, 6-replaceable hinge sleeve, 7-fixing block for rear processing, 8-drilling mold Body, 9-hinge mold body, 10-front positioning screw, 11-front processing fixing pin, 12-front processing fixing screw, 13-front fixing pin, 14-rear processing positioning pin, 15-rear Processing fixing screw, 16-fastening positioning pin, 17-fastening nut, 18-fastening bolt, 19-fastening screw sleeve, 20-lateral fixing screw, 21-lateral fixing screw, 22-lateral fixing block , 23- rudder surface skeleton skin riveting components.

detailed description

The technical solution of the present invention is further described below, but the scope of protection is not limited to the description.

As shown in Figures 1 to 6, a deep hole processing fixture for the missile rudder surface skeleton assembly includes a bracket 1, a latch 2, a positioning block 3, a front processing fixing block 4 and a rear processing fixing block 7, positioning The block 3 is fixed on the bracket 1; the front processing fixed block 4 is arranged on the surface of the bracket 1, and the front processing fixed block 4 is provided with a bush corresponding to the position and size of the hole to be processed in the rudder surface skeleton skin riveting assembly 23 hole; the rear processing fixed block 7 is arranged on the bottom center of the support 1, and the right end of the rudder surface skeleton skin riveting assembly 23 is fixed on the rear processing fixed block 7, and the rear processing fixed block 7 is provided with the rudder surface skeleton The skin riveting assembly 23 is to be machined with holes corresponding to the positions and sizes.

The hole to be processed for the rudder surface frame skin riveting assembly 23 to be processed is located at the lower part of the rudder surface, and the bottom of the rudder surface needs to be fixed during clamping to prevent vibration and displacement during processing from affecting the processing hole.

A plurality of bolts 2 can be set at the bottom of the bracket 1 to fix the rudder surface skeleton skin riveting assembly 23, making its positioning on the bracket 1 more reliable, preventing the deformation of the parts from reducing the machining accuracy during the fixing process.

The support 1 is also provided with a lateral fixing block 22, and the lateral fixing block 22 is provided with a threaded hole, and the lateral fixing screw rod 21 passes through the threaded hole to fasten the rudder surface skeleton skin riveting assembly 23 on the fixing block 3 .

Use the screw device to fix the rudder surface skeleton skin riveting assembly 23 laterally, which can ensure the stability of the lateral position during positioning and processing, and ensure the processing accuracy. Use the screw device to fasten the rudder surface skeleton The clamping of the skin riveting assembly 23 is easy to operate, and it is convenient for the operator to operate on the fixture. The tightness of the clamping can also be adjusted by the tightening degree of the screw rod, which can prevent the rudder surface of the part to be processed due to too tight clamping. Deformation of the skeleton-skin riveting assembly 23 can also prevent fastening effects from being too loosely clamped.

The lateral fixing block 22 is located on one side of the rudder surface skeleton skin riveting assembly 23 , corresponding to the fixing block 3 .

A plurality of fixed blocks 3 and lateral fixed blocks 22 can also be set on the support 1, and the rudder surface skeleton skin riveting assembly 23 is segmentally fixed, especially when the missile rudder surface rudder surface skeleton skin riveting assembly to be processed When the size is too large, a plurality of fixing blocks 3 and lateral fixing blocks 22 need to be set for fixing, so as to prevent the parts from being deformed during the processing and reducing the processing accuracy.

It also includes a replaceable drill sleeve 5 and a replaceable reaming sleeve 6. When drilling, the replaceable drill sleeve 5 is placed in the bushing hole of the pre-processed fixed block 4, and the reaming operation is performed. , place the replaceable hinge sleeve 6 in the bushing hole of the pre-processed fixing block 4 .

Also comprise a drill template body 8 and a hinge template body 9, when carrying out the drilling operation, the drill template body 8 is fixed on the processing groove of the described rear processing fixed block 7, when carrying out the reaming operation, the hinge The mold body 9 is fixed on the processing groove of the post processing fixing block 7 .

Set different drill sleeves and reaming sleeves, and set up replaceable molds, which can complete the entire processing process through one clamping of the parts to be processed, prevent the deformation of the parts to be processed during the process of replacing fixtures and molds, and can effectively reduce The vibration and displacement of the parts to be processed is beneficial to ensure the coaxiality of multiple deep hole processing.

Also include fastening positioning pin 16, fastening nut 17, fastening bolt 18 and fastening screw sleeve 19, two positioning holes are provided on the described post processing fixed block 7, fastening positioning pin 16 passes fastening nut 17 enters one of the positioning holes, and the fastening bolt 18 passes through the fastening nut 19 and enters the other positioning hole; when performing drilling operations, the fastening positioning pin 16 fixes the drilling template body 8 by the fastening nut 17 , the fastening bolt 18 fixes the drilling template body 8 through the fastening screw sleeve 19; when performing the reaming operation, the fastening positioning pin 16 fixes the reaming mold body 9 through the fastening nut 17, and the fastening bolt 18 passes through the tightening The solid screw sleeve 19 fixes the hinge body 9.

When carrying out the drilling operation, the drilling of the replaceable drill sleeve 5 and the drilling of the drill body 8 remain coaxial; Stay on-axis.

The positioning accuracy of the replaceable drill sleeve 5 and the drill body 8 as well as the replaceable hinge sleeve 6 and the hinge body 9 during installation will directly affect the machining accuracy of the parts, and the coaxiality is controlled during the fixture installation to make it Keeping the same axis can ensure the processing accuracy of the rudder surface skeleton skin riveting assembly 23 .

The connection between the fixed block 3 and the bracket 1 is provided with a pre-positioning screw 10 and a pre-positioning pin 13; Screw 12; rear processing positioning pin 14 and rear processing fixing screw 15 are provided at the connection between rear processing fixing block 7 and bracket 1; lateral fixing screws 20 are provided at the connection between lateral positioning block 22 and bracket 1.

By arranging positioning pins and positioning screws on each positioning block and fixing block, it can ensure the firm connection between the parts and the bracket 1, and prevent the vibration and rotation of the tool during the machining process from causing the rudder surface skeleton skin riveting assembly to be damaged. Machining accuracy drops.

The front positioning screw 10 , the front processing fixing screw 12 , the rear processing fixing screw 15 and the lateral fixing screw 20 are all hexagon socket screws.

A deep hole processing method for a missile rudder surface skeleton skin riveting assembly, comprising the following steps:

Step 1: Calibrate the verticality of the bracket 1. After the verticality meets the operation requirements, position the rudder surface skeleton skin riveting assembly 23 on the bracket 1 through the pin 2, and then tighten the screw 21 to secure the rudder surface skeleton skin riveting assembly 23. The tight top is fixed on the side of the fixed block 3; correcting the verticality of the bracket 1 is the first step to ensure the machining accuracy. Since the radial drilling machine used is a linear path, if the verticality of the bracket 1 does not meet the processing requirements , it will cause the drilled hole to be tilted and the part will be scrapped.

Step 2: Put the replaceable drill bushing 5 into the bushing hole of the front processing fixed block 4, put the drill template body 8 into the rectangular groove of the rear processing fixed block 7, and position the upper and lower sides of the drill template body 8 Holes are respectively fixed by fastening positioning pin 16, fastening nut 17, fastening bolt 18 and fastening nut 19, and the edge of locating block 3 contacts with one side of rudder surface skeleton skin riveting assembly 23 during installation; The replaceable drill sleeve 5 is placed in the bushing hole of the pre-processing fixed block 4, which can ensure that the processed drilling is carried out according to the required processing accuracy, and can also protect the pre-processed fixed block 4 so that it can be processed During the process, it is not in contact with the processing tool to prevent it from causing damage to the tool.

Step 3: Install the positioning mandrel on the machine tool spindle of the radial drilling machine, rotate the rocker arm of the machine tool, so that the positioning mandrel can be smoothly inserted into the corresponding hole of the drill body 8, so that the coaxiality with the hole on the drill body 8 is not the same. greater than φ0.01mm, and the perpendicularity with bracket 1 is not greater than 0.01mm, then replace the positioning mandrel with a drill bit for bottom hole drilling;

Step 4: After the bottom hole is drilled, replace the replaceable drill sleeve 5 with the replaceable reamer sleeve 6, replace the drill body 8 with the reamer body 9, replace the cutting tool with a reamer, and perform the reaming operation.

Use the operation process of step-by-step processing to ensure the coaxiality of the drilled hole and the reamed hole, and use the processing method of drilling first and then reaming, so that the riveting assembly 23 of the rudder surface skeleton skin of the part to be processed does not occur during the processing Disassembly and assembly can ensure the processing accuracy of the drilled hole and the reamed hole without mutual influence between the two.

The original processing method is to mill the hole with an end mill end tooth after drilling the bottom hole. The dimensional accuracy of the hole is easily out of tolerance, and the processing time is 150 minutes per piece. However, the fixture according to the present invention is used for processing, and the single piece takes 75 minutes. Min/piece, its processing capacity is twice that of the original, and the processing efficiency has been significantly improved. Through the implementation of the present invention, it is realized that the fitter drills and reams the deep hole on the radial drilling machine, and the manufacturing accuracy of the deep hole processing device is used to ensure the processing accuracy of the deep hole of the skeleton skin riveting assembly, the product quality is reliable, the processing efficiency is significantly improved, and effective The efficiency bottleneck of deep hole processing of rudder surface skeleton skin riveting components is solved. The device has the advantages of simple operation, good reliability and strong practicability, and can be popularized in deep hole processing and production of missile rudder surfaces.

Claims (10)

1. A kind of 1. deep hole machining fixture for guided missile rudder face skeleton component, it is characterised in that：Including support (1), latch (2), Locating piece (3), preposition processing fixed block (4) and rearmounted processing fixed block (7), locating piece (3) are fixed on support (1)；Before The surface that processing fixed block (4) is arranged at support (1) is put, is provided with and rudder face skeleton covering riveting on preposition processing fixed block (4) Connected components (23) unprocessed hole location and the corresponding bush hole of size；Rearmounted processing fixed block (7) is arranged at the bottom of support (1) End center, the right-hand member of rudder face skeleton covering riveting component (23) are fixed on rearmounted processing fixed block (7), rearmounted processing fixed block (7) processing groove corresponding with rudder face skeleton covering riveting component (23) unprocessed hole location and size is provided with.
2. 2. it is used for the deep hole machining fixture of guided missile rudder face skeleton covering riveting component as claimed in claim 1, it is characterised in that： It is additionally provided with the support (1) and laterallys secure block (22), is laterallyd secure block (22) and be provided with screwed hole, laterally secure screw rod (21) Rudder face skeleton covering riveting component (23) is anchored on fixed block (3) through screwed hole.
3. 3. it is used for the deep hole machining fixture of guided missile rudder face skeleton covering riveting component as claimed in claim 2, it is characterised in that： The side for lateralling secure block (22) and being located at rudder face skeleton covering riveting component (23), it is corresponding with fixed block (3).
4. 4. it is used for the deep hole machining fixture of guided missile rudder face skeleton covering riveting component as claimed in claim 1, it is characterised in that： Also include a renewable bushing (5) and an interchangeable hinge sleeve (6), when carrying out drilling operation, renewable bushing (5) is placed in described In the bush hole of preposition processing fixed block (4), when carrying out reaming operations, it is solid that interchangeable hinge sleeve (6) is placed in the preposition processing In the bush hole for determining block (4).
5. 5. it is used for the deep hole machining fixture of guided missile rudder face skeleton covering riveting component as claimed in claim 4, it is characterised in that： Also include a model drilling body (8) and a hinge die body (9), when carrying out drilling operation, model drilling body (8) is fixed on described rearmounted Process in the processing groove of fixed block (7), when carrying out reaming operations, hinge die body (9) is fixed on the rearmounted processing fixed block (7) in processing groove.
6. 6. it is used for the deep hole machining fixture of guided missile rudder face skeleton covering riveting component as claimed in claim 5, it is characterised in that： Also include securing dowel (16), clamp nut (17), fastening bolt (18) and fastening swivel nut (19), the rearmounted processing is solid Determine block (7) and be provided with two positioning holes, securing dowel (16) enters in one of positioning hole through clamp nut (17), tightly Fixing bolt (18) enters in another positioning hole through fastening swivel nut (19)；When carrying out drilling operation, securing dowel (16) Model drilling body (8) is fixed by clamp nut (17), fastening bolt (18) is entered by fastening swivel nut (19) to model drilling body (8) Row is fixed；When carrying out reaming operations, hinge die body (9) is fixed by clamp nut (17) for securing dowel (16), tightly Hinge die body (9) is fixed by fastening swivel nut (19) for fixing bolt (18).
7. 7. it is used for the deep hole machining fixture of guided missile rudder face skeleton covering riveting component as claimed in claim 6, it is characterised in that： When carrying out drilling operation, the drilling of renewable bushing (5) keeps coaxial with the drilling of model drilling body (8)；When carrying out reaming operations, The drilling of interchangeable hinge sleeve (6) and the drilling of hinge die body (9) keep coaxial.
8. 8. it is used for the deep hole machining fixture of guided missile rudder face skeleton covering riveting component as claimed in claim 1, it is characterised in that： The fixed block (3) is provided with preposition positioning screw (10) and preposition alignment pin (13) with support (1) connection；It is preposition to add Work fixed block (4) is provided with preposition processing steady pin (11) and preposition processing fixing screws (12) with support (1) connection；Afterwards Put processing fixed block (7) and support (1) connection is provided with rearmounted locating and machining pin (14) and rearmounted processing fixing screws (15)；Lateral register block (22) is provided with support (1) connection and laterallys secure screw (20).
9. 9. it is used for the deep hole machining fixture of guided missile rudder face skeleton covering riveting component as claimed in claim 8, it is characterised in that： The preposition positioning screw (10), preposition processing fixing screws (12), rearmounted processing fixing screws and laterally secure spiral shell at (15) It is soket head cap screw to follow closely (20).
10. 10. a kind of deep hole processing method for guided missile rudder face skeleton covering riveting component, it is characterised in that comprise the following steps：

    Step 1：The perpendicularity of correcting bracket (1), meet after perpendicularity and covered rudder face skeleton by latch (2) after operation requires Skin riveting component (23) positioning is positioned on support (1), then screws screw rod (21) by rudder face skeleton covering riveting component (23) Press closer and be fixed on fixed block (3) side, the side at the edge of locating piece (3) and rudder face skeleton covering riveting component (23) during installation It is in contact；

    Step 2：Renewable bushing (5) is loaded in the bush hole of locating piece (4), model drilling body (8) is loaded into rearmounted processing fixed block (7) in rectangular channel, both sides positioning hole in model drilling body (8) is made respectively by securing dowel (16), clamp nut (17), to fasten Bolt (18) and fastening swivel nut (19) are fixed；

    Step 3：Location mandril is arranged on the machine tool chief axis of radial drilling machine, rotates lathe rocking arm, location mandril is smoothly inserted Enter in model drilling body (8) respective aperture, the axiality in itself and hole in model drilling body (8) is not more than φ 0.01mm, it is vertical with support (1) Degree is not more than 0.01mm, and then changing location mandril into drill bit carries out bottom outlet drilling；

    Step 4：After bottom outlet is drilled, renewable bushing (5) is replaced with interchangeable hinge sleeve (6), model drilling body (8) is replaced with hinge die body (9), change cutter into reamer, carry out reaming operations.