CN211719072U - Aircraft sheet metal training rack for simulating aircraft skin structure - Google Patents
Aircraft sheet metal training rack for simulating aircraft skin structure Download PDFInfo
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- CN211719072U CN211719072U CN202020876216.5U CN202020876216U CN211719072U CN 211719072 U CN211719072 U CN 211719072U CN 202020876216 U CN202020876216 U CN 202020876216U CN 211719072 U CN211719072 U CN 211719072U
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Abstract
The utility model discloses a real rack of instructing of aircraft panel beating of simulation aircraft skin structure, its technical scheme main points are: the aircraft skin is a cambered surface, the aircraft skin is fixed on the rack fixing base, the purlins are horizontally fixed on the rack fixing base respectively, the bulkheads have the same radian as the aircraft skin and are vertically fixed with the purlins, and the two skin openings are symmetrically formed in the aircraft skin; compared with the traditional plane rack, the aircraft sheet metal training rack for simulating the aircraft skin structure realizes the disassembly, assembly and replacement of the skin repair training cover plate, and improves the use efficiency of the training rack; moreover, the rack also has the advantages of simple structure and convenient manufacture.
Description
Technical Field
The utility model relates to a real rack of instructing of aircraft panel beating, concretely relates to real rack of instructing of aircraft panel beating of simulation aircraft skin structure.
Background
The metal plate work is one of important work for repairing an airplane structure, the metal plate training work is mainly completed by an aviation 147 training mechanism at present, main training equipment is mainly a planar metal plate training frame, the training time is generally one week, the training effect is fed back from a maintenance department of an airline company, a student basically grasps the operation process and method of the metal plate work, but the actual metal plate repair on an airplane has a larger gap, and a corresponding maintenance scheme is made according to the damage condition of a skin basically and cannot be realized.
Traditional plane panel beating rack, aluminum plate size are exactly the volume plane size, but actual aircraft skin structure has certain circular arc, when doing the panel beating and repairing, and the circular arc size has often been neglected to the aluminum plate patch that the repair was used, if the aluminum plate patch neglected the circular arc size of adoption then can influence real time operation when the simulation training of reality, need improve for this reason.
SUMMERY OF THE UTILITY MODEL
To the problem of mentioning in the background art, the utility model aims at providing a real rack of instructing of aircraft panel beating of simulation aircraft skin structure to solve the problem of mentioning in the background art.
The above technical purpose of the present invention can be achieved by the following technical solutions:
the utility model provides a real rack of instructing of aircraft panel beating of simulation aircraft skin structure, includes rack fixed baseplate, aircraft skin, a plurality of stringer, a plurality of bulkhead, two skin openings, two skin repair exercise apron, a plurality of layer board nut and a plurality of countersunk screw, the aircraft skin is the cambered surface, the aircraft skin is fixed on the rack fixed baseplate, a plurality of the stringer level respectively is fixed on the rack fixed baseplate, a plurality of bulkhead have respectively with the same radian of aircraft skin and perpendicular with the stringer is fixed, two skin opening symmetry is seted up on the aircraft skin, two skin repair exercise apron is respectively through a plurality of layer board nut and a plurality of countersunk screw is fixed on the aircraft skin the skin opening part.
By adopting the technical scheme, compared with a traditional plane rack, the plane sheet metal training rack for simulating the aircraft skin structure is closer to the operation of repairing the aircraft sheet metal, the size of an aluminum plate of the traditional plane sheet metal rack is the measurement plane size, the aircraft skin structure in the rack has a certain circular arc, when the sheet metal is repaired, an aluminum plate patch used for repairing does not ignore the circular arc size, and the aircraft sheet metal training rack for simulating the aircraft skin structure is more in line with the requirement of actual operation; the bracket fixes the skin repair exercise cover plate by using the support plate nut, so that the skin repair exercise cover plate is disassembled, assembled and replaced, and the use efficiency of the practical training bracket is improved; moreover, the rack also has the advantages of simple structure and convenient manufacture.
Preferably, the rack fixing base comprises two first arc-shaped supporting rods, two second arc-shaped supporting rods and two base platforms, the two first arc-shaped supporting rods are fixedly connected with the purlins and the partition frames, the second arc-shaped supporting rods are fixedly welded on the first arc-shaped supporting rods, and the two base platforms are fixedly welded at the bottom ends of the first arc-shaped supporting rods and the bottom ends of the second arc-shaped supporting rods respectively.
Through adopting above-mentioned technical scheme, its manufacturing is comparatively convenient when rack fixed baseplate comprises first arc bracing piece, second arc bracing piece and base station, and support stability is higher.
Preferably, a horizontal reinforcing connecting rod is welded and fixed between the two first arc-shaped supporting rods.
Through adopting above-mentioned technical scheme, strengthen the connecting rod and can improve rack fixed baseplate's structural stability.
Preferably, the skin opening is rectangular in shape with rounded corners.
By adopting the technical scheme, the most common skin replacement state is set to meet the requirement of maintenance of the aircraft skin.
Preferably, the vertical height distance between two adjacent stringers is 200 mm.
By adopting the technical scheme, the data size is set as the data size adopted in practical application.
Preferably, the vertical height distance between the uppermost and lowermost stringers and the edge of the aircraft skin is 95 mm.
By adopting the technical scheme, the data size is set as the data size adopted in practical application.
Preferably, the direct-view length and width of the aircraft skin is 1600 × 800mm, and the radius of the arc surface of the aircraft skin in the shape of an arc surface is 2000 mm.
By adopting the technical scheme, the cambered surface of the aircraft skin is controlled to ensure that the cambered surface can be attached to the actual aircraft surface skin as much as possible.
Preferably, the cross section of the stringer is pi-shaped without outer convex edges.
By adopting the technical scheme, the cross section of the stringer is in the shape, so that the material can be saved, the weight is reduced, and better bending resistance and torsion resistance can be achieved.
Preferably, the cross section of the partition frame is in a double-hook J shape.
By adopting the technical scheme, the section of the partition frame is in the shape, so that the material can be saved, the weight is reduced, the better bending resistance and torsion resistance can be achieved, and the partition frame can be conveniently connected and fixed with the stringer.
To sum up, the utility model discloses mainly have following beneficial effect:
compared with a traditional plane rack, the metal plate training rack of the simulated aircraft skin structure is closer to the work of aircraft metal plate repair, the size of an aluminum plate of the traditional plane metal plate rack is the measurement plane size, the aircraft skin structure in the rack has a certain circular arc, when the metal plate is repaired, an aluminum plate patch used for repairing does not ignore the circular arc size, and the aircraft metal plate training rack of the simulated aircraft skin structure is more in line with the requirement of actual work; the bracket fixes the skin repair exercise cover plate by using the support plate nut, so that the skin repair exercise cover plate is disassembled, assembled and replaced, and the use efficiency of the practical training bracket is improved; moreover, the rack also has the advantages of simple structure and convenient manufacture.
Drawings
FIG. 1 is a schematic structural diagram of an aircraft sheet metal training rack for simulating an aircraft skin structure;
FIG. 2 is a schematic structural view of a fixed base for a display stand;
FIG. 3 is one of the schematic structural views for showing the skin repair practice cover plate;
FIG. 4 is a schematic structural view for showing an aircraft skin;
FIG. 5 is a schematic structural view for showing a section of a stringer;
FIG. 6 is a schematic structural view for showing a cross section of a bulkhead;
fig. 7 is a second schematic view for showing the structure of the skin repair practice cover plate.
Reference numerals: 1. a rack fixing base; 2. aircraft skin; 3. a stringer; 4. a bulkhead; 5. a skin opening; 6. covering a skin repair exercise cover plate; 7. a screw cap of the pallet; 8. a countersunk head screw; 11. a first arc-shaped support rod; 12. a second arc-shaped support rod; 13. a base station; 14. and a reinforcing connecting rod.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
Referring to fig. 1, 2 and 3, an aircraft sheet metal training rack simulating an aircraft skin structure comprises a rack fixing base 1, an aircraft skin 2, four stringers 3, four bulkheads 4, two skin openings 5, two skin repair practice cover plates 6, a plurality of support plate nuts 7 and a plurality of countersunk screws 8, wherein the aircraft skin 2 is a cambered surface, the aircraft skin 2 is fixed on the rack fixing base 1, the four stringers 3 are respectively and horizontally fixed on the rack fixing base 1, the four bulkheads 4 respectively have the same radian as the aircraft skin 2 and are vertically fixed with the stringers 3, the two skin openings 5 are symmetrically arranged on the aircraft skin 2, and the two skin repair practice cover plates 6 are respectively fixed on the skin openings 5 on the aircraft skin 2 through the support plate nuts 7 and the countersunk screws 8.
Referring to fig. 1 and 2, wherein the rack fixing base 1 includes two first arc-shaped supporting rods 11, two second arc-shaped supporting rods 12 and two base platforms 13, the two first arc-shaped supporting rods 11 are connected and fixed with the stringer 3 and the bulkhead 4, the second arc-shaped supporting rods 12 are welded and fixed on the first arc-shaped supporting rods 11, the two base platforms 13 are welded and fixed at the bottom ends of the first arc-shaped supporting rods 11 and the second arc-shaped supporting rods 12, when the rack fixing base 1 is composed of the first arc-shaped supporting rods 11, the second arc-shaped supporting rods 12 and the base platforms 13, the processing and manufacturing are convenient, and the supporting stability is high.
Referring to fig. 1, 2 and 4, a horizontal reinforcing connecting rod 14 is welded and fixed between the two first arc-shaped support rods 11, and the reinforcing connecting rod 14 can improve the structural stability of the gantry fixing base 1; wherein the skin opening 5 is rectangular with rounded corners, which is arranged to accommodate the most common skin replacement conditions for maintenance of the aircraft skin 2; wherein the vertical height distance between two adjacent stringers 3 is 200mm, which is set as the data size adopted in practical application; the vertical height distance of the uppermost and lowermost stringers 3 from the edge of the aircraft skin 2 is 95mm, which is set to the data size used in the actual application.
Referring to fig. 1 and 4, the length and width of the aircraft skin 2 as seen directly is 1600 × 800mm, the radius of the arc surface of the arc-shaped aircraft skin 2 is 2000mm, and the control of the arc surface of the aircraft skin 2 can ensure that the aircraft skin is attached to the actual aircraft surface skin as much as possible.
Referring to fig. 5, 6 and 7, the section of the stringer 3 is a pi shape without outer convex edge, and the section of the stringer 3 is set to be the shape, so that the material can be saved, the weight can be reduced, and the better bending resistance and torsion resistance can be achieved; the section of the partition frame 4 is in a double-hook J shape, and the section of the partition frame 4 is arranged in the shape, so that the material is saved, the weight is reduced, better bending resistance and torsion resistance can be achieved, and the partition frame can be conveniently connected and fixed with the stringer 3.
Wherein the covering in this device adopts: model 2024-T4 aviation aluminum plate, plate thickness: 2 mm; the stringer 3 adopts: 7075 aviation duralumin, material thickness: 1.5 mm; the partition frame 4 adopts: 7075 aviation duralumin, material thickness: 1.5 mm; the skin repair practice cover plate 6 adopts: type 2024-T4 aviation aluminium plate (aircraft common skin material: type 2024-T4 aviation aluminium plate, the same material is adopted to obtain the same exercise hand feeling, especially drilling), plate thickness: 1.5mm, fix on aircraft skin 2 bulkhead 4 through countersunk head screw 8, skin repair exercise apron 6 can be dismantled, is convenient for change the exercise.
The steps adopted in the training process are as follows:
1. the damage condition of the structure of the aircraft skin 2 is visually checked, as shown in the figure, the crack damage of the aircraft skin 2 is simulated, the damage size is measured, and meanwhile, the damages such as corrosion, pits, puncture and the like can also be simulated.
2. The damage condition of the aircraft skin 2 is further detected by using nondestructive detection equipment, such as: eddy current nondestructive testing equipment is utilized.
3. And inquiring an SRM structure maintenance manual according to the damage condition of the aircraft skin 2, and formulating a repair and maintenance scheme of the aircraft skin 2.
4. According to the aircraft skin 2 repair and maintenance scheme, work cards, tools, consumables and the like are prepared.
5. The aircraft skin 2 repair work is carried out according to the aircraft skin 2 repair maintenance protocol.
6. After the repair is completed, the quality of the repair is assessed, with the aid of a non-destructive testing device.
7. The maintenance quality is qualified, and the local paint spraying work (according to the condition) at the repair position of the aircraft skin 2 is finished.
8. The skin repair practice cover 6 is removed and a new skin repair practice cover 6 is installed.
The use principle and the advantages are as follows:
compared with a traditional plane rack, the metal plate practical training rack of the simulated aircraft skin structure is closer to the work of aircraft metal plate repair, the size of an aluminum plate of the traditional plane metal plate rack is the measurement plane size, the aircraft skin 2 structure in the rack is of a certain circular arc, when the metal plate is repaired, an aluminum plate patch used for repairing does not ignore the circular arc size, and the aircraft metal plate practical training rack of the simulated aircraft skin structure is more in line with the requirement of actual work; in addition, the bracket fixes the skin repair exercise cover plate 6 by using the supporting plate nut 7, so that the skin repair exercise cover plate 6 is disassembled, assembled and replaced, and the use efficiency of the practical training bracket is improved; moreover, the rack also has the advantages of simple structure and convenient manufacture.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (9)
1. The utility model provides a real rack of instructing of aircraft panel beating of simulation aircraft skin structure which characterized in that: including rack fixed baseplate (1), aircraft skin (2), a plurality of stringer (3), a plurality of bulkhead (4), two skin openings (5), two skin repair exercise apron (6), a plurality of layer board nut (7) and a plurality of countersunk screw (8), aircraft skin (2) are the cambered surface, aircraft skin (2) are fixed on rack fixed baseplate (1), a plurality of stringer (3) level fixation respectively on rack fixed baseplate (1), a plurality of bulkhead (4) have respectively with aircraft skin (2) the same radian and perpendicular with stringer (3) are fixed, two skin opening (5) symmetry is seted up on aircraft skin (2), two skin repair exercise apron (6) are respectively through a plurality of layer board nut (7) and a plurality of countersunk screw (8) are fixed on aircraft skin (2) skin opening (5) department.
2. The aircraft sheet metal training rack for simulating the aircraft skin structure according to claim 1, characterized in that: the rack fixing base (1) comprises two first arc-shaped supporting rods (11), two second arc-shaped supporting rods (12) and two base stations (13), wherein the first arc-shaped supporting rods (11) are fixedly connected with purlins (3) and partition frames (4), the second arc-shaped supporting rods (12) are fixedly welded on the first arc-shaped supporting rods (11), and the base stations (13) are fixedly welded at the bottom ends of the first arc-shaped supporting rods (11) and the second arc-shaped supporting rods (12) respectively.
3. The aircraft sheet metal training rack for simulating the aircraft skin structure according to claim 2, characterized in that: a horizontal reinforcing connecting rod (14) is welded and fixed between the two first arc-shaped supporting rods (11).
4. The aircraft sheet metal training rack for simulating the aircraft skin structure according to claim 1, characterized in that: the skin opening (5) is rectangular with rounded corners.
5. The aircraft sheet metal training rack for simulating the aircraft skin structure according to claim 1, characterized in that: the vertical height distance between two adjacent stringers (3) is 200 mm.
6. The aircraft sheet metal training rack for simulating the aircraft skin structure according to claim 1, characterized in that: the vertical height distance between the uppermost and lowermost stringers (3) and the edge of the aircraft skin (2) is 95 mm.
7. The aircraft sheet metal training rack for simulating the aircraft skin structure according to claim 1, characterized in that: the direct-view length and width of the aircraft skin (2) are 1600 × 800mm, and the arc surface radius of the aircraft skin (2) in the shape of an arc surface is 2000 mm.
8. The aircraft sheet metal training rack for simulating the aircraft skin structure according to claim 1, characterized in that: the section of the stringer (3) is pi-shaped without an outer convex edge.
9. The aircraft sheet metal training rack for simulating the aircraft skin structure according to claim 1, characterized in that: the section of the partition frame (4) is in a double-hook J shape.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020876216.5U CN211719072U (en) | 2020-05-22 | 2020-05-22 | Aircraft sheet metal training rack for simulating aircraft skin structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020876216.5U CN211719072U (en) | 2020-05-22 | 2020-05-22 | Aircraft sheet metal training rack for simulating aircraft skin structure |
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| Publication Number | Publication Date |
|---|---|
| CN211719072U true CN211719072U (en) | 2020-10-20 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202020876216.5U Expired - Fee Related CN211719072U (en) | 2020-05-22 | 2020-05-22 | Aircraft sheet metal training rack for simulating aircraft skin structure |
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| CN (1) | CN211719072U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114872001A (en) * | 2022-05-24 | 2022-08-09 | 上海航天精密机械研究所 | Sectional type assembly flexible assembling device and assembling method |
-
2020
- 2020-05-22 CN CN202020876216.5U patent/CN211719072U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114872001A (en) * | 2022-05-24 | 2022-08-09 | 上海航天精密机械研究所 | Sectional type assembly flexible assembling device and assembling method |
| CN114872001B (en) * | 2022-05-24 | 2023-08-22 | 上海航天精密机械研究所 | Sectional type assembly flexible assembly device and assembly method |
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|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20201020 Termination date: 20210522 |
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| CF01 | Termination of patent right due to non-payment of annual fee |