CN109367800B - Novel nacelle for aerial cargo - Google Patents
Novel nacelle for aerial cargo Download PDFInfo
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- CN109367800B CN109367800B CN201810991372.3A CN201810991372A CN109367800B CN 109367800 B CN109367800 B CN 109367800B CN 201810991372 A CN201810991372 A CN 201810991372A CN 109367800 B CN109367800 B CN 109367800B
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- 238000003466 welding Methods 0.000 claims abstract description 15
- 230000000149 penetrating effect Effects 0.000 claims description 5
- 230000007704 transition Effects 0.000 abstract description 4
- 239000000463 material Substances 0.000 description 19
- 230000000694 effects Effects 0.000 description 6
- 238000000034 method Methods 0.000 description 4
- 239000011365 complex material Substances 0.000 description 2
- 239000000295 fuel oil Substances 0.000 description 2
- 230000010354 integration Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
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Abstract
A novel pod for aviation cargo relates to the technical field of aviation cargo equipment, and aims to solve the technical problem of long transition training period of pilots, and comprises a framework component, the frame assembly comprises a front flange and a rear flange, a lower bearing beam and an upper bearing beam are fixed between the front flange and the rear flange, a cargo cabin is formed between the upper bearing beam and the lower bearing beam, a skin wallboard is arranged around the outer part of the cargo cabin, the skin wallboard is in a cylindrical shell shape, two ends of the skin wallboard are respectively welded on one sides of the front flange and the rear flange, the upper bearing beam is provided with two lifting lugs, the other side of the front flange is fixed with a file cabin and a front fairing, the other side of the rear flange is fixed with a tool cabin and a rear fairing, the file cabin and the tool cabin adopt a cross welding structure, the cross sections of the file cabin and the tool cabin are in a cross shape, a main cabin door is arranged on the skin wallboard, and the front flange and the rear flange are both provided with an auxiliary cabin door; the invention has the advantages of classified transportation, convenient loading and unloading, good aerodynamic performance, safety and stability.
Description
Technical Field
The invention relates to the technical field of aerial cargo equipment, in particular to a novel pod for aerial cargo.
Background
With the continuous improvement of modern military strength and the continuous improvement of military training level, under the background condition of the times, the army training guarantee system needs to be continuously strengthened. Under traditional conditions, personal luggage, relevant flight files and relevant training tools of pilots are numerous and heavy, so that the pilots often follow ground service support troops to transfer, the transfer period is long, and the problem of time asynchronism between the pilots and the time of driving the aircraft to transfer is solved, and flight training is not facilitated. According to the current situation, in order to enable the aircraft to carry more relevant luggage for training, ensure the requirement of transition training of a pilot and shorten the transition period, a device for aerial cargo needs to be designed, and the pod is a streamline-shaped nacelle which is provided with certain airborne equipment or weapons and is hung below a fuselage or wings, so that the pod is the best design choice, and the aircraft is ensured to conform to the overall aerodynamic force, high loading and unloading efficiency, effective lossless transportation and safety and stability of the aircraft while ensuring that all relevant goods and materials can follow the pilot.
Disclosure of Invention
The invention aims to: in order to solve the technical problem of long transition training period of pilots, the invention provides a novel pod for aerial cargo.
The invention specifically adopts the following technical scheme for realizing the purpose:
a novel pod for aerial cargo comprises a framework assembly, a fairing and a plurality of pod doors, wherein the fairing consists of a front fairing and a rear fairing, the framework assembly comprises a disk-shaped front flange and a disk-shaped rear flange, a lower bearing beam and an upper bearing beam serving as a main bearing part of the whole pod are fixed between the front flange and the rear flange, a cargo cabin for storing accompanying luggage is formed between the upper bearing beam and the lower bearing beam, a skin wallboard is arranged around the outer part of the cargo cabin, the skin wallboard is in a column shell shape, two ends of the skin wallboard are respectively welded on one side of the front flange and one side of the rear flange, the upper bearing beam is provided with two lifting lugs which penetrate through the skin wallboard and are connected with an airplane, a file cabin and a front fairing for wrapping the file cabin are fixed on the other side of the front flange, a tool cabin and a rear fairing for wrapping the tool cabin are fixed on the other side of the rear flange, the file cabin and the tool cabin adopt a cross-shaped welding structure, and the cross section is in a cross shape, the skin wallboard is provided with a main cabin door, the front flange plate and the rear flange plate are respectively provided with an auxiliary cabin door, and the center lines of the fairing, the skin wallboard, the front flange plate and the rear flange plate are mutually overlapped.
On the basis of the technical scheme, the front fairing and the rear fairing are streamline in shape and meet the requirements of pneumatic load and are welded on the front flange plate and the rear flange plate respectively, and the front fairing and the rear fairing are connected with two ends of the skin wall plate respectively.
On the basis of the technical scheme, a nacelle head wrapped by a front fairing is fixed at the end part of the file cabin, a front flange for supporting the front fairing is fixed between the nacelle head and the file cabin, and a rear flange for supporting the rear fairing is fixed at the end part of the tool cabin.
On the basis of the technical scheme, the auxiliary cabin doors on the front flange plate and the rear flange plate are respectively the same as the sectional sizes and shapes of the file cabin and the tool cabin, the tops of the auxiliary cabin doors are fixed on the flange plates through cabin door hinges, and the bottoms of the auxiliary cabin doors are respectively fixed with a cover lock for opening and closing the cabin doors.
On the basis of the technical scheme, a mounting plate fixed on the skin wall plate is arranged between the skin wall plate and the main cabin door, the main cabin door is connected with the mounting plate through a plurality of small bearing locks arranged on four sides of the main cabin door, and a lining plate is arranged between the main cabin door and the mounting plate.
On the basis of the technical scheme, the upper surface of the lower bearing beam and the lower surface of the upper bearing beam are both provided with a plurality of universal lifting rings, and safety ropes are arranged in the universal lifting rings in a penetrating mode.
On the basis of the technical scheme, the upper bearing beam and the lower bearing beam are fixed with the front flange plate and the rear flange plate through welding and threaded connection.
The invention has the following beneficial effects:
1. the invention has compact structure and reasonable design, and can transport related flight files, accompanying luggage and related training tools through the file cabin, the cargo cabin and the tool cabin respectively, thereby not only meeting the requirement that all materials are transferred along with a pilot, but also effectively improving the loading and unloading efficiency of complex materials; the center lines of the fairing, the skin wall plate, the front flange plate and the rear flange plate are superposed with each other, so that the integration degree is deepened, the aerodynamic requirements are better met, and the safety performance is further improved; the integral skin wallboard is welded between the front flange plate and the rear flange plate, so that materials are reasonably distributed according to equal strength on the structure, the overall rigidity and the local rigidity are better, the skin wallboard is not easy to destabilize, the pneumatic characteristic is improved, meanwhile, the number of rivets is reduced by adopting welding, the assembly workload is further reduced, the surface is smoother, the pneumatic appearance accuracy is improved, and the fuel oil loss is reduced by changing phases; the tool cabin and the file cabin shell are both designed into a cross welding structure, so that the bearing capacity of the shell is enhanced, and the cross sections of the tool cabin and the file cabin shell are both cross, so that the strength and the safety performance of the whole structure are further enhanced.
2. The fairing is designed into a streamline type, reduces resistance and better meets aerodynamic requirements, and the number of rivets is reduced by welding the fairing, so that the assembly workload is further reduced; the fairing is connected with the skin wall plate in the middle, so that the surface of the nacelle is integrated, the surface is further promoted to better meet aerodynamic requirements, and the fairing effect is improved to meet aerodynamic loads; the front flange and the rear flange both play a certain supporting role, so that the fixing of the fairing is more stable and reliable, the strength and the safety performance of the whole structure are further improved, and the fairing effect is further improved by the arranged pod head.
3. The size and shape of the auxiliary cabin door are the same as the cross section size and shape of the corresponding cabin, so that the material loading and unloading are facilitated, the material loading and unloading efficiency is improved, and the cabin door hinge and the cover lock are arranged on the auxiliary cabin door, so that the auxiliary cabin door is simple in structure and convenient to open and close.
4. The main cabin door is designed in an open mode, the small bearing locks are completely opened when the main cabin door is opened, and the main cabin door is disassembled, so that the situation that goods and materials are loaded and unloaded cannot be hindered by the cabin door is avoided, and the goods and materials loading and unloading efficiency is further improved; meanwhile, when the main cabin door is installed, the main cabin door and the skin wall plate are tightly locked and integrated into a whole through a plurality of small bearing locks on four sides of the main cabin door, the possibility that the cabin door is suddenly opened in the flight process is avoided, and the reliability of the whole pod material transportation is greatly guaranteed.
5. The universal lifting ring and the safety rope penetrating through the universal lifting ring are used for fastening materials in the cargo hold, so that the occurrence of material collision and the like caused by instability in the flying process is reduced, and the practicability is improved.
6. The lifting lug is fixed on the airplane, the lifting lug is arranged on the upper bearing beam, and the upper bearing beam and the lower bearing beam are both used as the middle part of the nacelle, so that the middle part is a main bearing part, the supporting capability of the front end and the rear end of the nacelle is improved through welding and threaded connection double fixation, and the effect of improving the safety performance of the whole nacelle is achieved.
Drawings
FIG. 1 is a schematic view of the present invention;
FIG. 2 is a schematic view of the internal structure of the present invention;
FIG. 3 is a schematic view of the structure near the secondary hatch of the present invention;
reference numerals:
1-front fairing, 2-rear fairing, 3-front flange, 4-rear flange, 5-upper bearing beam, 6-lower bearing beam, 6.1-universal lifting ring, 7-cargo cabin, 8-skin wall plate, 9-lifting lug, 10-file cabin, 10.1-pod head, 10.2-front flange, 11-tool cabin, 11.1-rear flange, 12-main cabin door, 12.1-small bearing lock, 13-auxiliary cabin door, 13.1-cabin door hinge and 13.2-cover lock.
Detailed Description
For a better understanding of the present invention by those skilled in the art, the present invention will be described in further detail below with reference to the accompanying drawings and the following examples.
Example 1
As shown in figure 1, a novel pod for aerial cargo comprises a framework component, a fairing and a plurality of pod doors, wherein the fairing consists of a front fairing 1 and a rear fairing 2, the framework component comprises a disk-shaped front flange 3 and a disk-shaped rear flange 4, a lower bearing beam 6 and an upper bearing beam 5 serving as a main bearing part of the whole pod are fixed between the front flange 3 and the rear flange 4, a cargo cabin 7 for storing accompanying luggage is formed between the upper bearing beam 5 and the lower bearing beam 6, a skin panel 8 is surrounded on the outer side of the cargo cabin 7, the skin panel 8 is in a column shell shape, two ends of the skin panel are respectively welded on one side of the front flange 3 and one side of the rear flange 4, the upper bearing beam 5 is provided with two lifting lugs 9 which penetrate through the skin panel 8 and are connected with an airplane, the other side of the front flange 3 is fixed with a file cabin 10 and the front fairing 1 for wrapping the file cabin 10, the other side of the rear flange 4 is fixed with a tool cabin 11 and the rear fairing 2 for wrapping the tool cabin 11, the file cabin 10 and the tool cabin 11 are of a cross-shaped welding structure and have cross sections, the skin wall plate 8 is provided with a main cabin door 12, the front flange plate 3 and the rear flange plate 4 are respectively provided with an auxiliary cabin door 13, and the center lines of the fairing, the skin wall plate 8, the front flange plate 3 and the rear flange plate 4 are mutually overlapped.
Related flight files, accompanying luggage and related training tools are respectively transported through the file cabin 10, the cargo cabin 7 and the tool cabin 11, so that the situation that all materials are transferred along with a pilot at the same time can be met, and the loading and unloading efficiency of complex materials can be effectively improved; the center lines of the fairing, the skin wall plate 8, the front flange plate 3 and the rear flange plate 4 are superposed with each other, so that the integration degree is deepened, the aerodynamic requirement is better met, and the safety performance is further improved; the integral skin wallboard 8 is welded between the front flange plate 3 and the rear flange plate 4, materials are reasonably distributed according to equal strength on the structure, the overall rigidity and the local rigidity are better, the skin wallboard 8 is not easy to be unstable, the pneumatic characteristic is improved, meanwhile, the number of rivets is reduced due to welding, the assembly workload is further reduced, the surface is smoother, the pneumatic appearance accuracy is improved, and the fuel oil loss is reduced in a phase-changing manner; the tool cabin 11 and the file cabin 10 are both designed into a cross-shaped welding structure, so that the bearing capacity of the shell is enhanced, and the cross sections of the shell are cross-shaped, so that the strength and the safety performance of the whole structure are further enhanced.
Example 2
As shown in fig. 1, the present embodiment is further optimized based on embodiment 1, and specifically includes:
the front fairing 1 and the rear fairing 2 are streamline in shape and meet the requirements of pneumatic load and are respectively welded on the front flange plate 3 and the rear flange plate 4, and the front fairing 1 and the rear fairing 2 are respectively connected with two ends of the skin wall plate 8.
A nacelle head 10.1 wrapped by the front fairing 1 is fixed at the end part of the document cabin 10, a front flange 10.2 supporting the front fairing 1 is fixed between the nacelle head 10.1 and the document cabin 10, and a rear flange 11.1 supporting the rear fairing 2 is fixed at the end part of the tool cabin 11.
The fairing is designed into a streamline type, so that the resistance is reduced, the aerodynamic requirements are better met, and the number of rivets is reduced by welding the fairing, so that the assembly workload is reduced; the fairing is connected with the skin wall plate 8 in the middle, so that the surface of the nacelle is integrated, the surface is further promoted to meet aerodynamic requirements, and the fairing effect is improved to meet aerodynamic loads; the front flange 10.2 and the rear flange 11.1 both play a certain supporting role, so that the fixing of the fairing is more stable and reliable, the overall structural strength and the safety performance are further improved, and the rectification effect is further improved by the arranged pod head 10.1.
Example 3
As shown in fig. 1 to fig. 2, the present embodiment is further optimized on the basis of embodiment 2, specifically:
the auxiliary cabin doors 13 on the front flange 3 and the rear flange 4 are respectively the same as the file cabin 10 and the tool cabin 11 in cross-sectional size and shape, the tops of the auxiliary cabin doors 13 are fixed on the flanges through door hinges 13.1, and the bottoms of the auxiliary cabin doors 13 are respectively fixed with a cover lock 13.2 for opening and closing the cabin doors.
The size and shape of the auxiliary cabin door 13 are the same as the cross section size and shape of the corresponding cabin, so that the material loading and unloading are facilitated, the material loading and unloading efficiency is improved, the cabin door hinge 13.1 and the cover lock 13.2 are arranged on the auxiliary cabin door 13, the structure is simple, and the opening and closing are convenient.
Example 4
As shown in fig. 1 to fig. 2, the present embodiment is further optimized on the basis of embodiment 3, specifically:
a mounting plate fixed on the skin wall panel 8 is arranged between the skin wall panel 8 and the main cabin door 12, the main cabin door 12 is connected with the mounting plate through a plurality of small bearing locks 12.1 arranged on four sides of the main cabin door 12, and a lining plate is arranged between the main cabin door 12 and the mounting plate.
The main cabin door 12 is designed in an open mode, the small bearing locks 12.1 are completely opened when the main cabin door 12 is opened, and the main cabin door 12 is disassembled, so that the situation that goods and materials are not blocked by the cabin door when being loaded and unloaded is avoided, and the goods and materials loading and unloading efficiency is further improved; meanwhile, when the main cabin door 12 is installed, the main cabin door 12 and the skin wall plate 8 are tightly locked and integrated into a whole through a plurality of small bearing locks 12.1 on four sides of the main cabin door 12, so that the possibility of sudden opening of the cabin door in the flight process is avoided, and the reliability of the whole pod material transportation is greatly guaranteed.
Example 5
As shown in fig. 1 to fig. 2, the present embodiment is further optimized based on embodiment 3, specifically.
The upper surface of the lower bearing beam 6 and the lower surface of the upper bearing beam 5 are both provided with a plurality of universal lifting rings 6.1, and safety ropes are arranged in the universal lifting rings 6.1 in a penetrating way.
The universal lifting ring 6.1 and the safety rope penetrating through the universal lifting ring are used for fastening materials of the cargo hold 7, so that the occurrence of the conditions of material collision and the like caused by instability in the flying process is reduced, and the practicability is improved.
Example 6
As shown in fig. 1 to fig. 2, the present embodiment is further optimized on the basis of embodiment 3, specifically:
the upper bearing beam 5 and the lower bearing beam 6 are fixed with the front flange 3 and the rear flange 4 by welding and screw thread connection.
The whole nacelle is fixed on an airplane through the lifting lugs 9, the lifting lugs 9 are arranged on the upper bearing beam 5, the upper bearing beam 5 and the lower bearing beam 6 are both used as the middle part of the nacelle, so that the middle part is a main bearing part, the supporting capacity of the front end and the rear end of the nacelle is improved through welding and threaded connection double fixation, and the effect of improving the safety performance of the whole nacelle is achieved.
The above description is only a preferred embodiment of the present invention, and not intended to limit the present invention, the scope of the present invention is defined by the appended claims, and all structural changes that can be made by using the contents of the description and the drawings of the present invention are intended to be embraced therein.
Claims (5)
1. A novel nacelle for an aerial carrier is characterized by comprising a framework assembly, a fairing and a plurality of cabin doors, wherein the fairing comprises a front fairing (1) and a rear fairing (2), the framework assembly comprises a disc-shaped front flange (3) and a disc-shaped rear flange (4), a lower bearing beam (6) and an upper bearing beam (5) are fixed between the front flange (3) and the rear flange (4), a cargo cabin (7) is formed between the upper bearing beam (5) and the lower bearing beam (6), a skin panel (8) surrounds the outer part of the cargo cabin, the skin panel (8) is in a column shell shape, two ends of the skin panel are respectively welded on one sides of the front flange (3) and the rear flange (4), the upper bearing beam (5) is provided with two lifting lugs (9) which penetrate through the skin panel (8) and are connected with an airplane, a file cabin (10) and the front fairing (1) wrapping the file cabin (10) are fixed on the other side of the front flange (3), a tool cabin (11) and a rear fairing (2) wrapping the tool cabin (11) are fixed on the other side of the rear flange plate (4), the file cabin (10) and the tool cabin (11) adopt a cross-shaped welding structure and have cross sections, a main cabin door (12) is arranged on the skin wall plate (8), and an auxiliary cabin door (13) is arranged on each of the front flange plate (3) and the rear flange plate (4); the front fairing (1) and the rear fairing (2) are streamline in shape meeting the requirement of aerodynamic load and are respectively welded on the front flange plate (3) and the rear flange plate (4); a nacelle head (10.1) wrapped by a front fairing (1) is fixed at the end part of the file cabin (10), a front flange (10.2) for supporting the front fairing (1) is fixed between the nacelle head (10.1) and the file cabin (10), and a rear flange (11.1) for supporting the rear fairing (2) is fixed at the end part of the tool cabin (11).
2. The novel pod for air cargo according to claim 1, wherein the secondary hatches (13) on the front flange (3) and the rear flange (4) have the same cross-sectional dimensions and shapes as the document pod (10) and the tool pod (11), respectively, the tops of the secondary hatches (13) are fixed on the flanges through hatches hinges (13.1), and the bottoms of the secondary hatches (13) are fixed with hatch locks (13.2) for opening and closing the hatches.
3. The new pod for air cargo according to claim 2, characterized in that between the skin panel (8) and the main door (12) there is a mounting plate fixed to the skin panel (8), the main door (12) is connected to the mounting plate by means of a number of small force-bearing locks (12.1) arranged on its four sides and a lining plate is arranged between the main door (12) and the mounting plate.
4. The novel pod for air cargo according to any one of claims 1 to 3, characterized in that the upper surface of the lower bearing beam (6) and the lower surface of the upper bearing beam (5) are provided with a plurality of universal hoisting rings (6.1), and safety ropes are arranged in the universal hoisting rings (6.1) in a penetrating manner.
5. The novel pod for air cargo according to any of claims 1 to 3 wherein the upper and lower carrier beams (5, 6) are fixed to the front flange (3) and the rear flange (4) by welding and screwing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810991372.3A CN109367800B (en) | 2018-08-28 | 2018-08-28 | Novel nacelle for aerial cargo |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810991372.3A CN109367800B (en) | 2018-08-28 | 2018-08-28 | Novel nacelle for aerial cargo |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109367800A CN109367800A (en) | 2019-02-22 |
| CN109367800B true CN109367800B (en) | 2021-10-15 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201810991372.3A Active CN109367800B (en) | 2018-08-28 | 2018-08-28 | Novel nacelle for aerial cargo |
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Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114093211B (en) * | 2021-11-05 | 2024-04-12 | 河北汉光重工有限责任公司 | Rolling-on training bench for full-section cargo hold of conveyor |
| CN114212258A (en) * | 2021-12-17 | 2022-03-22 | 江西洪都航空工业集团有限责任公司 | Can throw and put cigarette liquid case of drawing |
| CN114229010B (en) * | 2022-02-23 | 2022-07-01 | 四川腾盾科技有限公司 | Low-cost simple unmanned aerial vehicle nacelle structure |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN203094453U (en) * | 2012-12-10 | 2013-07-31 | 成都飞机工业（集团）有限责任公司 | Highly integrated smoke writing nacelle |
| CN104986337A (en) * | 2015-07-17 | 2015-10-21 | 成都飞机工业（集团）有限责任公司 | Air-drop stable descending delivery hanging cabin |
| KR20160001456A (en) * | 2014-06-27 | 2016-01-06 | 이엠코리아주식회사 | Weapn station |
| CN107672810A (en) * | 2016-08-01 | 2018-02-09 | 北京遥感设备研究所 | A kind of general hang flies nacelle device |
| CN207482206U (en) * | 2017-11-09 | 2018-06-12 | 彩虹无人机科技有限公司 | Unmanned plane airborne geophysical prospecting magnetic puts crystal detection nacelle device |
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2018
- 2018-08-28 CN CN201810991372.3A patent/CN109367800B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN203094453U (en) * | 2012-12-10 | 2013-07-31 | 成都飞机工业（集团）有限责任公司 | Highly integrated smoke writing nacelle |
| KR20160001456A (en) * | 2014-06-27 | 2016-01-06 | 이엠코리아주식회사 | Weapn station |
| CN104986337A (en) * | 2015-07-17 | 2015-10-21 | 成都飞机工业（集团）有限责任公司 | Air-drop stable descending delivery hanging cabin |
| CN107672810A (en) * | 2016-08-01 | 2018-02-09 | 北京遥感设备研究所 | A kind of general hang flies nacelle device |
| CN207482206U (en) * | 2017-11-09 | 2018-06-12 | 彩虹无人机科技有限公司 | Unmanned plane airborne geophysical prospecting magnetic puts crystal detection nacelle device |
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| CN109367800A (en) | 2019-02-22 |
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