CN209998423U - cutting tool for processing discontinuous hinge shaft hole of folding elastic wing - Google Patents
cutting tool for processing discontinuous hinge shaft hole of folding elastic wing Download PDFInfo
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- CN209998423U CN209998423U CN201920454028.0U CN201920454028U CN209998423U CN 209998423 U CN209998423 U CN 209998423U CN 201920454028 U CN201920454028 U CN 201920454028U CN 209998423 U CN209998423 U CN 209998423U
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Abstract
The utility model provides an a cutting tool for processing folding bullet wing discontinuity hinge hole, folding bullet wing be linear arrangement with side surface and have a plurality of bosss, folding bullet wing discontinuity hinge hole runs through all bosss, cutting tool is including connecting gradually the tool bit that rises at , cutter body and handle of a knife, the tool bit external diameter is this cutting tool's nominal diameter, it is d1 to establish the tool bit external diameter, it is d2 to establish the cutter body external diameter, then satisfy following relational expression between d1 and the d2 adopt the technical scheme of the utility model, to characteristics such as structure and the material in folding bullet wing discontinuity hinge hole, take corresponding measure to design corresponding cutting tool geometric parameters, make this cutting tool satisfy the cutting process demand in folding bullet wing discontinuity hinge hole to this cutting tool's geometric characteristics make cutting tool can carry out cutting process under the process condition of lower main shaft rotational speed and lower feed capacity, have established the basis for improving machining precision and processingquality.
Description
Technical Field
The utility model relates to the technical field of machining technology, especially indicate the cutting tool in the discontinuous hinge shaft hole of folding bullet wing.
Background
The folding missile wing is an important part in weapon ammunition such as guided missiles and the like, the material of the folding missile wing is mainly aluminum alloy, alloy steel or titanium alloy, the folding missile wing is hinged on the surface of the weapon ammunition through a hinged shaft hole arranged on the folding missile wing, under the condition of , in the routine storage and transportation process of the ammunition, the folding missile wing on the ammunition can be folded and covered on the surface of the ammunition, so that the effective storage volume of the ammunition is reduced, the transportation and the storage are convenient, when the ammunition is launched from a cartridge chamber, the folding missile wing can be unfolded, in order to ensure that the weapon ammunition keeps good service performance in use, the folding missile wing must be reliably unfolded when launched from the cartridge chamber, the machining precision of the hinged shaft hole of the folding missile wing must be higher, however, the hinged shaft hole of the folding missile wing is elongated holes with the length-diameter ratio larger than 10, partial areas of the elongated holes are also provided with partitions, and the partition degree precision between the unit holes of the folding missile wing cannot be ensured when the coaxial machining precision is machined by a technical.
SUMMERY OF THE UTILITY MODEL
In order to solve the technical problem, the utility model provides an kinds of cutting tool who is used for processing folding bullet wing discontinuity hinge shaft hole.
The utility model discloses a following technical scheme can realize.
The utility model provides a a cutting tool for processing folding bullet wing discontinuity hinge hole, folding bullet wing be linear arrangement with side surface and have a plurality of bosss, folding bullet wing discontinuity hinge hole runs through all bosss, cutting tool is including connecting gradually tool bit, cutter body and the handle of a knife that plays, the tool bit external diameter is this cutting tool's nominal diameter, establishes the tool bit external diameter is d1, establishes the cutter body external diameter is d2, then satisfies following relational expression between d1 and the d 2:
d2＝d1-0.3mm。
if the depth of the hinge shaft hole is L and the length of the cutting tool is L, the following relational expression is satisfied between L and L:
L＝l+50mm。
assuming that the length of the tool bit is l1, and the width of the block 3 with the largest width in the plurality of blocks 3 is kmax, the following relation is satisfied between l1 and kmax:
L1>kmax+30mm。
the folding missile wing is made of aluminum alloy with the grade of YG3X, and the geometric structural parameters of the cutting tool are as follows:
front angle: 15 degrees to 20 degrees;
relief angle: 12 to 15 degrees;
helix angle: 45 to 60 degrees.
The folding missile wing is made of alloy steel with the trademark YT15, and the geometric structural parameters of the cutting tool are as follows:
front angle: 8-15 degrees;
relief angle: 8 degrees to 12 degrees;
helix angle: 30 to 45 degrees.
The folding missile wing is made of titanium alloy with the trade name of YW2, and the geometric structural parameters of the cutting tool are as follows:
front angle: 5 degrees to 10 degrees;
relief angle: 5 degrees to 10 degrees;
helix angle: 30 to 45 degrees.
The cutting tool is a milling cutter or a comparating cutter.
The beneficial effects of the utility model reside in that: adopt the technical scheme of the utility model, to folding characteristics such as structure and the material in bullet wing discontinuity hinge shaft hole, take corresponding measure design corresponding cutting tool geometric parameters that have pertinence, make this cutting tool satisfy the cutting process demand in folding bullet wing discontinuity hinge shaft hole, and this cutting tool's geometric characteristics makes cutting tool can carry out cutting process under the technological condition of lower main shaft rotational speed and lower feed volume, cutting tool's vibration has been reduced, the needs of carrying out repetitious usage and cutting process have been satisfied, be favorable to improving the machining precision and the processingquality in folding bullet wing discontinuity hinge shaft hole. The utility model discloses simple structure, low in manufacturing cost is honest and clean.
Drawings
Fig. 1 is a schematic structural diagram of the present invention;
FIG. 2 is a part view of the folding missile wing of the utility model;
FIG. 3 is a flow chart of the present process for machining discontinuous hinge-pin holes of folded elastic wings;
fig. 4 is a schematic structural view of the folding missile wing blank of the utility model;
fig. 5 is a schematic view of the connection between the folding missile wing blank and the process block.
In the figure: 1-folding elastic wing, 2-folding elastic wing blank, 3-process block, 11-hinge shaft hole, 21-boss, 41-tool bit, 42-cutter body and 43-cutter handle.
Detailed Description
The following illustrates the present invention, but the scope of the invention is not limited thereto.
As shown in fig. 1 and 2, in this embodiment, the utility model provides an kinds of cutting tool for processing folding bullet wing discontinuity hinge hole, folding bullet wing be the linear arrangement with side surface and have a plurality of bosss 21, folding bullet wing discontinuity hinge hole runs through all bosss 21, cutting tool is including connecting gradually tool bit 41, cutter body 42 and the handle of a knife 43 that plays, tool bit 41 external diameter is this cutting tool's nominal diameter, it is d1 to establish tool bit 41 external diameter, it is d2 to establish cutter body 42 external diameter, then satisfy following relational expression between d1 and the d 2:
d2＝d1-0.3mm。
, if the depth of the hinge shaft hole 11 is L and the length of the cutting tool is L, the following relation is satisfied between L and L:
L＝l+50mm。
further, assuming that the length of the tool tip 41 is l1 and the width of the block 3 having the largest width among the plurality of blocks 3 is kmax, the following relationship is satisfied between l1 and kmax:
L1>kmax+30mm。
, when the folding missile wing is made of aluminum alloy with the mark of YG3X, the geometrical parameters of the cutting tool are as follows:
front angle: 15 degrees to 20 degrees;
relief angle: 12 to 15 degrees;
helix angle: 45 to 60 degrees.
, when the folding missile wing is made of alloy steel with the trademark YT15, the geometric structural parameters of the cutting tool are as follows:
front angle: 8-15 degrees;
relief angle: 8 degrees to 12 degrees;
helix angle: 30 to 45 degrees.
, when the folding missile wing is made of titanium alloy with the trade name YW2, the geometrical structure parameters of the cutting tool are as follows:
front angle: 5 degrees to 10 degrees;
relief angle: 5 degrees to 10 degrees;
helix angle: 30 to 45 degrees.
In addition, the utility model provides a cutting tool is milling cutter or comparison sword.
Adopt the technical scheme of the utility model, to folding characteristics such as structure and the material in bullet wing discontinuity hinge shaft hole, take corresponding measure design corresponding cutting tool geometric parameters that have pertinence, make this cutting tool satisfy the cutting process demand in folding bullet wing discontinuity hinge shaft hole, and this cutting tool's geometric characteristics makes cutting tool can carry out cutting process under the technological condition of lower main shaft rotational speed and lower feed volume, cutting tool's vibration has been reduced, the needs of carrying out repetitious usage and cutting process have been satisfied, be favorable to improving the machining precision and the processingquality in folding bullet wing discontinuity hinge shaft hole. The utility model discloses simple structure, low in manufacturing cost is honest and clean.
In addition, as shown in fig. 3, 4 and 5, the following steps can be adopted by using the cutting tool provided by the present invention:
step , providing a folding missile wing blank 2 according to a design drawing, wherein a plurality of bosses 21 are linearly arranged on the same side surface of the folding missile wing blank 2;
step two, preparing a plurality of process blocks 3, wherein the width of each process block 3 is equal to the distance between any two adjacent bosses 21 in the plurality of bosses 21 in the step , and then embedding the plurality of process blocks 3 between the two adjacent bosses 21, preferably, the width of all the process blocks 3 in the plurality of process blocks 3 is equal to .
And step three, clamping the folded elastic wing blank 2 embedded with the process block 3 in the step two on a machine tool, feeding cutting machining for multiple times by using a plurality of different cutting tools along the arrangement direction of the plurality of bosses 21, wherein the nominal diameter of the cutting tool used in each cutting machining is larger than that of the cutting tool used in the previous times of cutting machining, enabling the cutting tools to penetrate through all the bosses 21 and the process block 3, cutting off partial materials in the bosses 21 and the process block 3, obtaining hinge shaft holes 11 which penetrate through all the bosses 21 and are identical to in the design drawing on the folded elastic wing blank 2, and then removing the process block 3 to finish machining.
, using a plurality of different cutting tools to feed cutting along the direction of the plurality of bosses 21 for a plurality of times in the third step, wherein the cutting tools comprise a drill, a milling cutter and a reamer, and the cutting tool for processing the discontinuous hinge shaft hole of the folded elastic wing further comprises the following steps:
, when the folding missile wing blank 2 is made of aluminum alloy with the trademark of YG 3X;
the drilling machining process parameters in the step 1 are as follows:
main shaft rotating speed: 300-500 r/min;
feeding amount: 0.1-0.3 mm/r;
the milling parameters in the step 2 are as follows:
main shaft rotating speed: 500-800 r/min;
feeding amount: 0.1-0.3 mm/r;
the reaming process in the step 3 comprises the following process parameters:
main shaft rotating speed: 200-300 r/min;
feeding amount: 0.1 to 0.3 mm/r.
, when the folding missile wing blank 2 is made of alloy steel with the brand name YT 15;
the drilling in the step 1 has the following technological parameters:
main shaft rotating speed: 100 to 150 r/min;
feeding amount: 0.1-0.2 mm/r;
the milling parameters in the step 2 are as follows:
main shaft rotating speed: 200-400 r/min;
feeding amount: 0.1-0.2 mm/r;
the reaming process in the step 3 comprises the following process parameters:
main shaft rotating speed: 80-150 r/min;
feeding amount: 0.1 to 0.2 mm/r.
, when the folding missile wing blank 2 is made of titanium alloy with the brand number YW 2;
the drilling machining process parameters in the step 1 are as follows:
main shaft rotating speed: 80-120 r/min;
feeding amount: 0.08-0.15 mm/r;
the milling parameters in the step 2 are as follows:
main shaft rotating speed: 100 to 200 r/min;
feeding amount: 0.08-0.15 mm/r;
the reaming process in the step 3 comprises the following process parameters:
main shaft rotating speed: 50-100 r/min;
feeding amount: 0.08-0.15 mm/r.
And 3, reaming, namely feeding a reamer along the bottom hole of the milling cutter in the step 2 in an axial direction for reaming for at least 2 times, wherein the nominal diameter of the reamer used in each reaming is larger than that of the reamer used in the previous times, so that the reamer penetrates through the bottom hole of the milling cutter, part of materials in the boss 21 and the process block 3 are cut off, and the bottom hole of the milling cutter is expanded into a reaming hole 11 which is times the design drawing.
In summary, the process parameters of drilling, milling and reaming are shown in table 1:
TABLE 1 Process parameters for drilling, milling and reaming
, as shown in fig. 5, the milling cutter or the reamer is composed of a cutter head 41, a cutter body 42 and a cutter handle 43 which are sequentially connected to , the outer diameter of the cutter head 41 is the nominal diameter of the milling cutter or the reamer, the outer diameter of the cutter head 41 is d1, the outer diameter of the cutter body 42 is d2, and the following relation is satisfied between d1 and d 2:
d2＝d1-0.3mm。
preferably, the length of the tool tip 41 is l1, and the width of the block 3 with the largest width in the plurality of blocks 3 is kmax, so that the following relation is satisfied between l1 and kmax:
L1>kmax+30mm。
, when the folding missile wing blank 2 is made of aluminum alloy with the trademark of YG3X, the geometric parameters of the cutting tool are as follows:
front angle: 15 degrees to 20 degrees;
relief angle: 12 to 15 degrees;
helix angle: 45 to 60 degrees.
, when the folding missile wing blank 2 is made of alloy steel with the trademark YT15, the geometrical structure parameters of the cutting tool are as follows:
front angle: 8-15 degrees;
relief angle: 8 degrees to 12 degrees;
helix angle: 30 to 45 degrees.
, when the folding missile wing blank 2 is made of titanium alloy with the trade name YW2, the geometrical structure parameters of the cutting tool are as follows:
front angle: 5 degrees to 10 degrees;
relief angle: 5 degrees to 10 degrees;
helix angle: 30 to 45 degrees.
In summary, the geometry parameters of the various cutting tools are shown in table 2:
table 2 geometrical parameters of cutting tools
, when the depth of the hinge shaft hole 11 is L and the length of the cutting tool is L, the following relation is satisfied between L and L:
L＝l+50mm。
adopt above-mentioned cutting process scheme, through inlaying a plurality of technology pieces 3 on folding missile wing blank 2, make each boss 21 on folding missile wing blank 2 connect in carrying out the cutting process in-process temporarily, establish the basis for the cutting process axiality of guaranteeing hinge shaft hole 11, when carrying out hinge shaft hole 11 processing, cutting tool through using multiple different grade type again has carried out cutting process many times, make the blank material get rid of gradually, make because of cutting tool vibration or cutting tool assembly error cause final cutting process error reduce to minimum, improved machining precision and product quality, satisfied folding missile wing 1 hinge shaft hole 11's processing technology requirement, the utility model provides a processing technology easy operation only adopts the ordinary digit control machine tool that has used at present and just can realize, corresponding manufacturing cost is also not high, is favorable to improving the equipment utilization ratio of current ordinary digit control machine tool.
Claims (7)
- The cutting tool for machining the discontinuous hinge hole of the folding elastic wing is characterized in that a plurality of bosses (21) are linearly arranged on the surface of the folding elastic wing on the same side, the discontinuous hinge hole of the folding elastic wing penetrates through all the bosses (21), the cutting tool comprises a tool bit (41), a tool body (42) and a tool handle (43) which are sequentially connected to , the outer diameter of the tool bit (41) is the nominal diameter of the cutting tool, the outer diameter of the tool bit (41) is d1, the outer diameter of the tool body (42) is d2, and the following relational expression is satisfied between d1 and d 2:d2＝d1-0.3mm。
- 2. the cutting tool for machining the discontinuous hinge-axis hole of the folding elastic wing as claimed in claim 1, wherein: if the depth of the hinge shaft hole (11) is L and the length of the cutting tool is L, the following relation is satisfied between L and L:L＝l+50mm。
- 3. the cutting tool for machining the discontinuous hinge-axis hole of the folding elastic wing as claimed in claim 1, wherein: if the length of the tool bit (41) is l1, and the width of the process block (3) with the largest width in the plurality of process blocks (3) is kmax, the following relational expression is satisfied between l1 and kmax:L1>kmax+30mm。
- 4. the cutting tool for machining the discontinuous hinge-axis hole of the folding elastic wing as claimed in claim 1, wherein: the folding missile wing is made of aluminum alloy with the grade of YG3X, and the geometric structural parameters of the cutting tool are as follows:front angle: 15 degrees to 20 degrees;relief angle: 12 to 15 degrees;helix angle: 45 to 60 degrees.
- 5. The cutting tool for machining the discontinuous hinge-axis hole of the folding elastic wing as claimed in claim 1, wherein: the folding missile wing is made of alloy steel with the trademark YT15, and the geometric structural parameters of the cutting tool are as follows:front angle: 8-15 degrees;relief angle: 8 degrees to 12 degrees;helix angle: 30 to 45 degrees.
- 6. The cutting tool for machining the discontinuous hinge-axis hole of the folding elastic wing as claimed in claim 1, wherein: the folding missile wing is made of titanium alloy with the trade name of YW2, and the geometric structural parameters of the cutting tool are as follows:front angle: 5 degrees to 10 degrees;relief angle: 5 degrees to 10 degrees;helix angle: 30 to 45 degrees.
- 7. The cutting tool for machining the discontinuous hinge-axis hole of the folding elastic wing as claimed in claim 1, wherein: the cutting tool is a milling cutter or a reamer.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920454028.0U CN209998423U (en) | 2019-04-04 | 2019-04-04 | cutting tool for processing discontinuous hinge shaft hole of folding elastic wing |
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| CN201920454028.0U CN209998423U (en) | 2019-04-04 | 2019-04-04 | cutting tool for processing discontinuous hinge shaft hole of folding elastic wing |
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| CN209998423U true CN209998423U (en) | 2020-01-31 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110405411A (en) * | 2019-04-04 | 2019-11-05 | 贵州航天风华精密设备有限公司 | A kind of hinged shaft hole forming method of folding wing |
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2019
- 2019-04-04 CN CN201920454028.0U patent/CN209998423U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110405411A (en) * | 2019-04-04 | 2019-11-05 | 贵州航天风华精密设备有限公司 | A kind of hinged shaft hole forming method of folding wing |
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