CN112589424B - Flexible pressing tool and method for controlling assembly damage of front edge of unmanned aerial vehicle - Google Patents
Flexible pressing tool and method for controlling assembly damage of front edge of unmanned aerial vehicle Download PDFInfo
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- CN112589424B CN112589424B CN202110246930.5A CN202110246930A CN112589424B CN 112589424 B CN112589424 B CN 112589424B CN 202110246930 A CN202110246930 A CN 202110246930A CN 112589424 B CN112589424 B CN 112589424B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P19/00—Machines for simply fitting together or separating metal parts or objects, or metal and non-metal parts, whether or not involving some deformation; Tools or devices therefor so far as not provided for in other classes
- B23P19/04—Machines for simply fitting together or separating metal parts or objects, or metal and non-metal parts, whether or not involving some deformation; Tools or devices therefor so far as not provided for in other classes for assembling or disassembling parts
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Abstract
The invention discloses a flexible pressing tool for controlling assembly damage of a front edge of an unmanned aerial vehicle, which comprises: the support device comprises a first support block, a second support block, a screw, a steel wire thread insert, a screw rod, a first nut, a second nut, foam rubber and soft foam. The first supporting block is connected with the assembly tool; the second supporting block is connected with the first supporting block through a screw; the steel wire thread insert is arranged at the corresponding position of the first supporting block and the second supporting block; the screw rod is arranged on the steel wire thread insert; two nuts are arranged on the screw rod; the soft foam is attached to the lower end of the screw through foam rubber. Except that the supporting blocks are machined, all finished parts are taken as tool component parts, so that the cost is low and the combination is convenient; the screw has an adjustable function, so that the tool has the characteristic of flexibility and can adapt to different wing profiles and different size requirements; the contact position of the tool and the front edge adopts a soft foam structure, so that the damage of the front edge structure can be effectively controlled while the gluing and pressing of the ultrathin front edge and the wing ribs are realized, and the effect of protecting the front edge is achieved.
Description
Technical Field
The invention relates to a flexible pressing tool and a flexible pressing method for controlling assembly damage of a front edge of an unmanned aerial vehicle, and belongs to the field of light flexible aircraft structure assembly.
Background
The solar aircraft is an ultra-light aircraft with large scale and low wing load, the structural weight coefficient is relatively large, the sensitivity of the performance of the aircraft to the structural weight is enhanced, the structural parts are generally designed by selecting composite materials with low density, high specific strength and high specific rigidity, and the using amount of the composite materials can account for more than 95% of the weight of the structure, so that the solar aircraft structure has the characteristics of large flexibility, thin wall, large-area bonding and the like. Particularly, the front edge structure adopts ultrathin prepreg for weight reduction, the thickness is less than 0.1mm, damage is easily caused in the gluing and pressing process, and great challenge is brought to assembly.
The traditional method for controlling the assembly precision and the bonding quality is to design a large assembly tool according to the assembly appearance requirement, but due to the composite material dispersibility and the structural complexity of the solar aircraft, the gap between the tool and the front edge is difficult to control, so that sufficient pressure cannot be applied, and the bonding effect is influenced; meanwhile, the processing and subsequent maintenance costs of the large-scale assembly tool are extremely high.
Therefore, it is very necessary to design a flexible pressing tool for leading edge and rib glue joint, which has simple structure, low cost and convenient use and maintenance, so that the tool can meet the assembly requirements of ribs with different wing profiles and different sizes, and can effectively control the pressing damage.
Disclosure of Invention
The technical problem solved by the invention is as follows: overcome prior art's not enough, provide a flexible frock of exerting pressure for controlling unmanned aerial vehicle leading edge assembly damage, when the realization that can be low-cost is fully exerted pressure to unmanned aerial vehicle leading edge, control leading edge damage effectively.
The purpose of the invention is realized by the following technical scheme:
the utility model provides a frock of exerting pressure flexibly for controlling unmanned aerial vehicle leading edge assembly damage, includes: the device comprises a first supporting block, a second supporting block, a screw, a steel wire thread sleeve, a screw rod, a first nut, a second nut, foam rubber and soft foam;
the lower end of the first supporting block is fixedly connected with an assembly tool of the unmanned aerial vehicle, and one end of the second supporting block is fixedly connected with the upper end of the first supporting block through a steel wire thread sleeve and a screw;
the second supporting block is also provided with a plurality of screw rod installation through holes, steel wire screw sleeves are arranged in the screw rod installation through holes, and the screw rods are installed on the steel wire screw sleeves arranged in the screw rod installation through holes; the soft foam passes through the foamed cement subsides and attaches in the screw rod bottom, and with unmanned aerial vehicle leading edge surface contact, first nut and second nut are installed in the screw rod upper end and are screwed up each other, adjust about going on the screw rod through rotatory first nut and second nut to adjust the pressure of screw rod to unmanned aerial vehicle leading edge.
Furthermore, a plurality of screw rod mounting through holes arranged on the second supporting block are arranged into two parallel straight lines along the length direction of the second supporting block, and the screw rod mounting through holes on one straight line correspond to the screw rod mounting through holes on the other straight line one by one.
Further, the distribution range of the screw rod along the length direction of the second support block covers the front edge part of the unmanned aerial vehicle.
Furthermore, the distance between the two parallel straight lines is 10-15mm, and the distance between the adjacent screw mounting through holes on the same straight line is 40-60 mm.
Furthermore, the first supporting block is of a columnar structure with a rectangular cross section, and the thickness of the first supporting block is 20-40 mm; the width is 30-60mm, and the width refers to the direction of the connecting line of the two blind holes at the top end of the first supporting block, namely the length direction of the second supporting block;
the second supporting block is of a columnar structure with a rectangular cross section, the long side of the rectangular cross section is the width of the second supporting block and ranges from 30mm to 60mm, the short side of the rectangular cross section is the thickness of the second supporting block and ranges from 20mm to 40mm, and the thickness direction of the second supporting block is the same as the direction of the screw mounting through hole.
Furthermore, the first supporting block and the second supporting block are made of plastic materials.
Furthermore, a groove at the bottom of the first supporting block is matched with an assembling tool, the width of the groove is the same as the thickness of the assembling tool, and the depth of the groove is 50-80 mm; two blind holes for mounting the steel wire thread insert are processed at the top of the first supporting block, the depth of each blind hole is 20-40mm, and the distance between the blind holes is 15-30 mm;
two through holes are formed in one end of the second supporting block, the distance is 15-30mm, the two through holes correspond to the blind holes in the top of the first supporting block, a steel wire thread sleeve is installed in the through holes, and the first supporting block and the second supporting block are fixedly connected through screws; the length of the screw is smaller than the sum of the depth of the blind hole of the first supporting block and the thickness of the second supporting block.
Further, the length of the screw is determined according to the position of the front edge of the unmanned aerial vehicle and the height of the wing profile.
Furthermore, the foam adhesive is epoxy adhesive, the width and the length of the soft foam are the same and are both 5-15mm, and the thickness is 2-4 mm.
Further, the invention provides a flexible pressing method for controlling the assembly damage of the front edge of the unmanned aerial vehicle, which comprises the following steps:
the method comprises the following steps: screwing the first nuts and the second nuts on the screw rods mutually to form nut assemblies, wherein the nut assemblies are positioned above the second supporting block;
step two: the nut assemblies on the screw rods are respectively rotated to enable the screw rods to be screwed out in the direction above the second supporting block, so that the screw rods are ensured not to contact the front edge of the unmanned aerial vehicle during installation;
step three: connecting the first supporting block and the second supporting block together by using a screw;
step four: connecting the first supporting block with an assembling tool;
step five: respectively rotating the nut assemblies on the screw rods to enable the screw rods to extend towards the direction of the front edge of the unmanned aerial vehicle;
step six: the soft foam is made to fully contact the outer surface of the front edge of the unmanned aerial vehicle, pressure is applied to the joint of the front edge of the unmanned aerial vehicle and the wing rib, the front edge of the unmanned aerial vehicle is not deformed due to normal external force, and the positions of all points of the soft foam are fit to the appearance of the front edge of the unmanned aerial vehicle.
Compared with the prior art, the invention has the following advantages:
(1) the invention adopts machining for the supporting block, and all selects finished parts as the components of the tool, and has the characteristics of low cost, convenient combination and the like.
(2) All the screws of the adjustable tool have adjustable functions, so that the tool has the characteristic of flexibility and can meet the requirements of different front edge shapes and different sizes.
(3) The contact position of the tool and the front edge adopts a soft foam structure, so that the damage of the front edge can be effectively controlled while the sufficient pressure is applied, and the effect of protecting the structure is achieved.
(4) The invention has simple integral structure and does not change the original assembly scheme.
Drawings
Fig. 1 shows a schematic diagram of a flexible pressing tool for controlling assembly damage of a leading edge of an unmanned aerial vehicle, provided by an embodiment of the invention;
fig. 2 shows a schematic diagram of a flexible pressing tool for controlling assembly damage of a leading edge of an unmanned aerial vehicle according to an embodiment of the invention;
fig. 3 shows a partial enlarged view of a flexible pressing tool area a for controlling the assembly damage of the leading edge of the unmanned aerial vehicle, provided by the embodiment of the invention;
fig. 4 shows a partial enlarged view of a flexible pressing tool area B for controlling the assembly damage of the leading edge of the unmanned aerial vehicle, provided by the embodiment of the invention;
fig. 5 shows a partial enlarged view of a flexible pressing tool area C for controlling the assembly damage of the leading edge of the unmanned aerial vehicle, provided by the embodiment of the invention.
Detailed Description
The invention provides a flexible pressing tool for controlling the assembly damage of the front edge of an unmanned aerial vehicle, which adopts machining for a supporting block and selects finished parts as the components of the tool, and has the characteristics of low cost, convenient combination and the like; all the screws have adjustable functions, so that the tool has the characteristic of flexibility and can adapt to requirements of different wing profiles and different sizes; the contact position of the tool and the easily damaged front edge adopts a soft foam structure, so that the damage of the front edge can be effectively controlled while the full pressure application is realized; meanwhile, the tool has the characteristics of convenience in installation and convenience in use.
The invention provides a flexible pressing tool for controlling assembly damage of a front edge of an unmanned aerial vehicle. As shown in fig. 1 to 5, the flexible pressing tool includes: the device comprises a first supporting block 1, a second supporting block 2, a screw 3, a steel wire thread insert 4, a screw rod 5, a first nut 6, a second nut 7, foam rubber 8 and soft foam 9;
the lower end of the first supporting block 1 is fixedly connected with an assembly tool 12 of the unmanned aerial vehicle, and one end of the second supporting block 2 is fixedly connected with the upper end of the first supporting block 1 through a steel wire thread sleeve 4 and a screw 3;
a plurality of screw rod installation through holes are further formed in the second supporting block 2, steel wire thread sleeves 4 are arranged in the screw rod installation through holes, and the screw rods 5 are installed on the steel wire thread sleeves 4 arranged in the screw rod installation through holes; the soft foam 9 is attached to the bottom end of the screw rod 5 through foam rubber 8 and is in contact with the surface of the front edge of the unmanned aerial vehicle, and the first nut 6 and the second nut 7 are installed at the upper end of the screw rod 5 and are screwed tightly to play a role in preventing looseness; adjust screw rod 5 from top to bottom through rotatory first nut 6 and second nut 7 to the pressure of adjusting screw rod 5 to the unmanned aerial vehicle leading edge.
The plurality of screw mounting through holes arranged on the second supporting block 2 are arranged into two parallel straight lines along the length direction of the second supporting block 2, and the screw mounting through holes on one straight line correspond to the screw mounting through holes on the other straight line one by one.
The distribution range of the screw rods 5 along the length direction of the second supporting block 2 covers the front edge part of the unmanned aerial vehicle.
The distance between two parallel straight lines is 10-15mm, and the distance between adjacent screw mounting through holes on the same straight line is 40-60 mm.
The first supporting block 1 is of a columnar structure with a rectangular section, the thickness is 20-40mm, and the stability of installation and use of other parts is guaranteed; the width is 30-60mm, and enough space and edge distance of the two rows of through holes are ensured, wherein the width refers to the direction of the connecting line of the two blind holes at the top end of the first supporting block 1, namely the length direction of the second supporting block 2;
the second supporting block 2 is a columnar structure with a rectangular cross section, the long side of the rectangular cross section is the width of the second supporting block 2, the range is 30-60mm, enough space and edge distance of the two rows of through holes are ensured, the short side of the rectangular cross section is the thickness of the second supporting block 2, the range is 20-40mm, the stability of installation and use of other parts is ensured, and the thickness direction of the second supporting block 2 is the same as the direction of the screw rod installation through hole.
The first supporting block 1 and the second supporting block 2 are made of plastic materials, so that the weight is reduced, and the installation is convenient.
The bottom of the first supporting block 1 is provided with a groove which is matched with an assembling tool and is connected by adopting two standard parts, the specification is M3-M5, the width of the groove is the same as the thickness of the assembling tool, and the depth of the groove is 50-80 mm; the firm connection is ensured. Two blind holes for mounting the steel wire thread insert 4 are processed at the top of the first supporting block 1, the depth of the blind holes is 20-40mm, and the distance between the blind holes is 15-30 mm;
two through holes are processed at one end of the second supporting block 2, the distance is 15-30mm, the two through holes correspond to the blind holes at the top of the first supporting block 1, a steel wire threaded sleeve 4 is installed in the through holes, and the first supporting block 1 and the second supporting block 2 are fixedly connected through a screw 3; the screw is a standard part and has the specification of M3-M4, and the length of the screw 3 is smaller than the sum of the depth of the blind hole of the first supporting block 1 and the thickness of the second supporting block 2, so that the screw is completely screwed in.
The screw 5 adopts a standard part with the specification of M3-M5, and the length of the screw 5 is determined according to the position of the front edge of the unmanned aerial vehicle and the height of an airfoil.
The wire thread insert adopts a standard piece, the specification is M3-M5, the length is insufficient, splicing can be carried out, and the screw rod needs to be ensured to rotate smoothly.
The foam adhesive 8 is epoxy adhesive and has certain strength when bonding two materials of metal and foam. The soft foam is made of soft foam, has the same width and length, is 5-15mm, has the thickness of 2-4mm, and can meet the shape following requirement while effectively controlling the damage of the front edge.
In the above-mentioned flexible frock of exerting pressure that is used for controlling unmanned aerial vehicle leading edge assembly damage, the frock part that uses except that the supporting shoe is the standard component.
The embodiment of the invention comprises the following steps:
the wire thread insert 4 is installed at the corresponding position of the first supporting block 1 and the second supporting block 2. Specifically, the steel wire swivel nut 4 is installed in the blind hole of the first supporting block 1 and the through hole of the second supporting block 2, so that the steel wire swivel nut penetrates through the whole blind hole and the through hole, the splicing mode can be adopted, and meanwhile, the screw rod 5 is required to be guaranteed to rotate smoothly.
The screw 5 is mounted on the wire thread insert 4. Specifically, the screw 5 is rotatably inserted through the wire thread insert 4.
A first nut 6 and a second nut 7 are mounted on the screw 5. Specifically, the first nut 6 and the second nut 7 are rotatably mounted to the top position of the screw 5 and are screwed to each other.
The foam rubber 8 is coated on the bottom end of the screw 5. Specifically, the foam rubber 8 is proportioned according to the use specification and coated on the top end of the screw rod 5.
The soft foam 9 is attached on top of the foam 8. Specifically, the middle position of the soft foam is contacted with the foam adhesive, and the foam adhesive is continuously pressed and cured by using an adhesive tape or a heavy object.
In the implementation, the bottom of the first supporting block 1 is grooved and assembled by an assembling tool, two standard parts are adopted for connection, the specification is M3, the groove width is the same as the thickness of the assembling tool, the groove depth is 50mm, and firm connection is ensured.
In the implementation, two blind holes for installing the steel wire thread insert 4 are processed at the top of the first supporting block 1, the depth of each blind hole is 30mm, and the distance is 18 mm.
In the implementation, two through holes for installing the wire thread inserts 4 are processed at one end of the second supporting block 2, and the distance is 18 mm.
In the implementation, two rows of 6 groups of through holes (determined according to the front edge range) for installing the wire thread inserts 4 are processed at the other end of the second supporting block 2, and two holes in each group are arranged at the interval of 12 mm; the group-to-group spacing was 50 mm.
In the implementation, the thickness of the first supporting block 1 is 25mm, and the stability of installation and use of other parts is ensured; the width is 30mm (the connecting line direction of two through holes at the top end), and enough space and edge distance between two rows of through holes are ensured.
In the above embodiment, the height of the first supporting block 2 is 20mm (in the direction of the through hole), and the stability of the installation and use of other parts should be ensured; the width is 30mm, and the two rows of through holes are ensured to have enough space and edge distance.
In the implementation, the first supporting block 1 and the second supporting block 2 are made of plastic materials, so that the weight is reduced, and the installation is convenient.
In the implementation, the first supporting block 1 and the second supporting block 2 are connected by the screw 3, the screw 3 is a standard component, the specification is M3, the length is smaller than the sum of the depth of the blind hole of the first supporting block 1 and the thickness of the first supporting block 2, and the screw is ensured to be screwed in completely.
In the above embodiment, the wire thread insert 4 is made of a standard component, and has a specification of M3, and the length is insufficient to enable splicing, but the screw rod 5 needs to be ensured to rotate smoothly.
In the above embodiment, the screw 5 is a standard piece with the specification of M3, and the length is determined according to the position of the front edge and the height of the airfoil.
In the above embodiment, the first nut 6 and the second nut 7 are standard pieces, and have a specification of M3.
In the above embodiment, the first nut 6 and the second nut 7 are screwed with each other at the upper end of the screw 5 to play a role of anti-loosening; so that the screw 5 can be adjusted up and down by rotating the first nut 6 and the second nut 7.
In the above embodiment, the foam adhesive 8 is an epoxy adhesive, and has a certain strength when bonding two materials, namely metal and foam.
In the implementation, the soft foam 9 is made of a rubber soft foam, the width and the length are both 5mm, the thickness is 2mm, and the shape following requirement is met while the damage of the front edge can be effectively controlled.
In the implementation, the selected tool parts except the supporting block are standard parts.
According to the flexible pressing tool, the first supporting block, the second supporting block, the screw, the steel wire thread insert, the screw, the first nut, the second nut, the foam adhesive and the soft foam form a whole, finished parts are selected as the components of the tool except for machining the supporting blocks, and the flexible pressing tool has the characteristics of low cost, convenience and quickness in combination and the like; all the screws have an adjustable function, so that the tool has the characteristic of flexibility and can adapt to different front edge appearance requirements; the contact position of the tool and the front edge adopts a soft foam structure, so that the damage of the front edge structure can be effectively controlled while the gluing and pressing of the ultrathin front edge and the wing ribs are realized, and the effect of protecting the front edge is achieved.
The invention further provides a flexible pressing method for controlling the assembly damage of the front edge of the unmanned aerial vehicle. Fig. 1 shows a schematic use diagram of a flexible pressing tool for controlling the assembly damage of a leading edge of an unmanned aerial vehicle according to an embodiment of the present invention, where 11 denotes the leading edge of the unmanned aerial vehicle, 12 denotes the assembly tool of the unmanned aerial vehicle, and 13 denotes a rib. The flexible pressing method comprises the following steps:
the method comprises the following steps: screwing the first nuts 6 and the second nuts 7 on the screw rods 5 to form nut assemblies, wherein the nut assemblies are positioned above the second supporting block 2;
step two: the nut assemblies on the screw rods 5 are respectively rotated to enable the screw rods 5 to be screwed out in the direction above the second supporting block 2, so that the screw rods are ensured not to contact the front edge of the unmanned aerial vehicle during installation;
step three: connecting the first supporting block 1 and the second supporting block 2 together by using a screw 3;
step four: connecting the first supporting block 1 with an assembling tool;
step five: respectively rotating the nut assemblies on the screw rods 5 to enable the screw rods 5 to extend towards the direction of the front edge of the unmanned aerial vehicle;
step six: make the soft foam 9 fully contact unmanned aerial vehicle leading edge surface, exert pressure to the unmanned aerial vehicle leading edge 11 and 13 splice of wing rib, and make the unmanned aerial vehicle leading edge not warp because of normal external force, the 9 each point positions of soft foam fit for unmanned aerial vehicle leading edge appearance this moment, guarantee the effect of exerting pressure.
The supporting tool provided by the invention integrates the first supporting block, the second supporting block, the screw, the steel wire thread sleeve, the screw, the first nut, the second nut, the foam adhesive and the soft foam, and has the characteristics of convenience in installation and convenience in use, and the overall assembly scheme of the wing is not changed.
The above-described embodiments are merely preferred embodiments of the present invention, and general changes and substitutions by those skilled in the art within the technical scope of the present invention are included in the protection scope of the present invention.
Claims (5)
1. The utility model provides a frock of exerting pressure flexibly for controlling unmanned aerial vehicle leading edge assembly damage which characterized in that includes: the device comprises a first supporting block (1), a second supporting block (2), a screw (3), a steel wire thread sleeve (4), a screw rod (5), a first nut (6), a second nut (7), foam rubber (8) and soft foam (9);
the lower end of the first supporting block (1) is fixedly connected with an assembly tool of the unmanned aerial vehicle, and one end of the second supporting block (2) is fixedly connected with the upper end of the first supporting block (1) through a steel wire threaded sleeve (4) and a screw (3);
a plurality of screw rod installation through holes are further formed in the second supporting block (2), steel wire thread sleeves (4) are arranged in the screw rod installation through holes, and the screw rods (5) are installed on the steel wire thread sleeves (4) arranged in the screw rod installation through holes; soft foam (9) are attached to the bottom end of the screw rod (5) through foam adhesive (8) and are in surface contact with the front edge of the unmanned aerial vehicle, a first nut (6) and a second nut (7) are installed at the upper end of the screw rod (5) and are screwed up with each other, the screw rod (5) is adjusted up and down by rotating the first nut (6) and the second nut (7), and therefore the pressure of the screw rod (5) on the front edge of the unmanned aerial vehicle is adjusted;
a plurality of screw mounting through holes arranged on the second supporting block (2) are arranged into two parallel straight lines along the length direction of the second supporting block (2), and the screw mounting through holes on one straight line correspond to the screw mounting through holes on the other straight line one by one;
the distribution range of the screw (5) along the length direction of the second supporting block (2) covers the front edge part of the unmanned aerial vehicle;
the distance between the two parallel straight lines is 10-15mm, and the distance between the adjacent screw mounting through holes on the same straight line is 40-60 mm;
the foam adhesive (8) is epoxy adhesive, the width and the length of the soft foam (9) are the same, and are both 5-15mm, and the thickness is 2-4 mm;
the front edge structure of the unmanned aerial vehicle adopts ultrathin prepreg, and the thickness of the prepreg is less than 0.1 mm;
the pressing method realized by using the flexible pressing tool for controlling the assembly damage of the front edge of the unmanned aerial vehicle comprises the following steps:
the method comprises the following steps: screwing a first nut (6) and a second nut (7) on each screw (5) to form a nut assembly, wherein the nut assembly is positioned above the second supporting block (2);
step two: the nut assemblies on the screw rods (5) are respectively rotated to enable the screw rods (5) to be screwed out in the direction above the second supporting block (2), so that the screw rods cannot contact with the front edge of the unmanned aerial vehicle during installation;
step three: the first supporting block (1) and the second supporting block (2) are connected together by a screw (3);
step four: connecting the first supporting block (1) with an assembling tool;
step five: respectively rotating the nut assemblies on the screw rods (5) to enable the screw rods (5) to extend in the direction of the front edge of the unmanned aerial vehicle;
step six: make soft foam (9) fully contact unmanned aerial vehicle leading edge surface, apply pressure to the unmanned aerial vehicle leading edge and rib splice, and make unmanned aerial vehicle leading edge not warp because of normal external force, soft foam (9) each point position fit for unmanned aerial vehicle leading edge appearance this moment.
2. The flexible pressing tool for controlling the assembly damage of the front edge of the unmanned aerial vehicle according to claim 1, wherein the first supporting block (1) is of a columnar structure with a rectangular section, and the thickness of the first supporting block is 20-40 mm; the width is 30-60mm, and the width refers to the direction of the connecting line of the two blind holes at the top end of the first supporting block (1), namely the length direction of the second supporting block (2);
the second supporting block (2) is of a columnar structure with a rectangular cross section, the long side of the rectangular cross section is the width of the second supporting block (2) and ranges from 30mm to 60mm, the short side of the rectangular cross section is the thickness of the second supporting block (2) and ranges from 20mm to 40mm, and the thickness direction of the second supporting block (2) is the same as the direction of the screw rod installation through hole.
3. The flexible pressing tool for controlling the assembly damage of the front edge of the unmanned aerial vehicle according to claim 1, is characterized in that: the first supporting block (1) and the second supporting block (2) are made of plastic materials.
4. The flexible pressing tool for controlling the assembly damage of the front edge of the unmanned aerial vehicle according to claim 1, is characterized in that: the bottom of the first supporting block (1) is provided with a groove which is matched with an assembling tool, the width of the groove is the same as the thickness of the assembling tool, and the depth of the groove is 50-80 mm; two blind holes for mounting the steel wire thread insert (4) are processed at the top of the first supporting block (1), the depth of the blind holes is 20-40mm, and the distance between the blind holes is 15-30 mm; two through holes are processed at one end of the second supporting block (2), the distance is 15-30mm, the two through holes correspond to the blind holes at the top of the first supporting block (1), a steel wire thread sleeve (4) is installed in the through holes, and the first supporting block (1) and the second supporting block (2) are fixedly connected through a screw (3); the length of the screw (3) is smaller than the sum of the depth of the blind hole of the first supporting block (1) and the thickness of the second supporting block (2).
5. The flexible pressing tool for controlling the assembly damage of the front edge of the unmanned aerial vehicle according to claim 1, is characterized in that: the length of the screw (5) is determined according to the position of the front edge of the unmanned aerial vehicle and the height of the wing profile.
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| CN112758306B (en) * | 2021-04-08 | 2021-07-16 | 中国航天空气动力技术研究院 | Self-tensioning wing rib, wing and skin laying method |
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| ES2209575B1 (en) * | 2001-07-06 | 2005-07-16 | M. Torres Diseños Industriales, S.A. | FLEXIBLE SYSTEM FOR THE CONSTRUCTION OF STRUCTURES. |
| CN1317107C (en) * | 2005-05-26 | 2007-05-23 | 上海交通大学 | Flexible device for multipoint clamping and positioning spatial 3D thin wall part |
| CN204526163U (en) * | 2015-03-31 | 2015-08-05 | 重庆长安汽车股份有限公司 | The bonding flexible frock of automotive bumper quick plastic exemplar assembly |
| KR101931493B1 (en) * | 2017-04-21 | 2018-12-24 | 한국정밀기계(주) | Module type flexible jig system |
| CN107263365A (en) * | 2017-08-21 | 2017-10-20 | 泰安华鲁锻压机床有限公司 | Support Position and the adjustable multi-point flexibly board supporting device of quantity |
| CN208147681U (en) * | 2018-03-30 | 2018-11-27 | 湖南鸿鑫富诚科技有限公司 | Fixture for automobile component |
| CN210191848U (en) * | 2019-06-10 | 2020-03-27 | 成都尼晟科技有限公司 | Fixing device is used in aircraft frame processing |
| CN212311830U (en) * | 2020-05-26 | 2021-01-08 | 苏州苏仕朗智能科技有限公司 | Flexible clamping device for lead frame |
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| CN112589424A (en) | 2021-04-02 |
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