CN109367800A - A kind of novel gondola for aviation loading - Google Patents
A kind of novel gondola for aviation loading Download PDFInfo
- Publication number
- CN109367800A CN109367800A CN201810991372.3A CN201810991372A CN109367800A CN 109367800 A CN109367800 A CN 109367800A CN 201810991372 A CN201810991372 A CN 201810991372A CN 109367800 A CN109367800 A CN 109367800A
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- cabin
- hatch door
- bearing beam
- forward flange
- flange disk
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- 238000003466 welding Methods 0.000 claims abstract description 14
- 238000000034 method Methods 0.000 claims abstract description 5
- 230000009977 dual effect Effects 0.000 claims description 5
- 230000007704 transition Effects 0.000 abstract description 9
- 230000032258 transport Effects 0.000 abstract description 4
- 239000000463 material Substances 0.000 description 17
- 230000000694 effects Effects 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 206010044565 Tremor Diseases 0.000 description 2
- 239000000295 fuel oil Substances 0.000 description 2
- 238000003825 pressing Methods 0.000 description 2
- 230000009467 reduction Effects 0.000 description 2
- 241001478750 Chlorophytum comosum Species 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
Classifications
-
- 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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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Body Structure For Vehicles (AREA)
- Connection Of Plates (AREA)
Abstract
A kind of novel gondola for aviation loading, it is related to aviation loading equipment technical field, in order to solve the technical problem of length pilot's transition cycle of training, including skeleton component, radome fairing and several hatch doors, skeleton component includes forward flange disk and rear stub, lower bearing beam and upper bearing beam are fixed between forward flange disk and rear stub, cargo compartment is formed between upper bearing beam and lower bearing beam and outside is enclosed equipped with skinpiston, skinpiston is shelly-shaped in column and both ends are respectively welded in forward flange disk and rear stub, there are two lifting lugs for upper bearing beam setting, the forward flange disk other side is fixed with file cabin and front fairing, the rear stub other side is fixed with tool cabin and rear radome fairing, file cabin and tool cabin use cross type welding structure and section is in cross, main hatch door is provided on skinpiston and forward flange disk and rear method Blue disk is provided with a secondary hatch door；The present invention has the advantages that classification transports, is easy to loading and unloading, aerodynamic performance is good and safety and stability.
Description
Technical field
The present invention relates to aviation loading equipment technical fields, more particularly to a kind of Novel spider plant for aviation loading
Cabin.
Background technique
With the continuous promotion of China's modernization military strength, the continuous improvement of military training level, at so one
Under under background condition, military training security system needs constantly to reinforce.Under conventional conditions, the personal luggage of pilot, phase
It closes flight file and related training tool is various and heavier, therefore ground service security force is often all followed to carry out transition, cause
The transition period is long, and flies transition times there are time nonsynchronous problem with pilot, is unfavorable for flight training.According to this
One status can ensure pilot's transition training needs, shorten the transition period to allow aircraft vehicle more to train associated baggage,
Need to design a kind of device for aviation loading, and gondola refer to certain airborne equipment or weapon are installed and hang in fuselage or
Streamlined nacelle under wing is best design alternative, while guaranteeing that all relevant supplies can accompany with pilot,
Ensure compliance with integrated air power, the high efficiency of loading and unloading, effectively lossless transport and the security and stability of aircraft.
Summary of the invention
It is an object of the invention to: the technical problem in order to solve length pilot's transition cycle of training, the present invention provide one
Kind is used for the novel gondola of aviation loading.
The present invention specifically uses following technical scheme to achieve the goals above:
A kind of novel gondola for aviation loading, including skeleton component, radome fairing and several hatch doors, the radome fairing by
Front fairing and rear radome fairing composition, skeleton component include forward flange disk and rear stub in the form of annular discs, and forward flange disk is with after
Be fixed with lower bearing beam and the upper bearing beam as entire gondola main load-bearing part between ring flange, upper bearing beam and lower bearing beam it
Between form the cargo compartment of storage retinue luggage and outside is enclosed equipped with skinpiston, skinpiston is shelly-shaped in column and both ends are distinguished
It is welded in forward flange disk and rear stub, upper bearing beam is provided through skinpiston and be connected with aircraft two hang
Ear, the forward flange disk other side are fixed with file cabin and wrap the front fairing in file cabin, and the rear stub other side is fixed with work
Tool cabin and the rear radome fairing for wrapping tool cabin, file cabin and tool cabin are in ten using cross type welding structure and section
Font, is provided with main hatch door on skinpiston and forward flange disk and rear stub are provided with a secondary hatch door, radome fairing, illiteracy
The center line of skin siding, forward flange disk and rear stub mutually coincides.
On the basis of above technical scheme, front fairing and rear radome fairing shape are meet aerodynamic loading demand streamlined
And it is respectively welded in forward flange disk and rear stub, front fairing and rear radome fairing are connected with skinpiston both ends respectively.
On the basis of above technical scheme, file cabin end be fixed with by front fairing wrap up gondola head, gondola head with
Disk is connect before being fixed with support front fairing between file cabin, and what tool cabin end was fixed with radome fairing after support is followed by disk.
On the basis of above technical scheme, secondary hatch door on forward flange disk and rear stub respectively with file cabin and tool cabin
Sectional dimension shape it is identical, be fixed on ring flange by hatch door hinge at the top of secondary hatch door, secondary hatch door bottom is respectively and fixedly provided with
One lid lock for hatch door opening and closing.
On the basis of above technical scheme, the installation being fixed on skinpiston is provided between skinpiston and main hatch door
Plate, main hatch door passes through several small-sized force-bearings lock that its four side is arranged in and mounting plate is connected and set between main hatch door and mounting plate
It is equipped with liner plate.
On the basis of above technical scheme, lower bearing beam upper surface and upper bearing beam lower surface are provided with several universal hang
Ring is equipped with safety rope in swivel.
On the basis of above technical scheme, pass through weldering between upper bearing beam and lower bearing beam and forward flange disk and rear stub
It connects and the dual fixation of thread connection.
Beneficial effects of the present invention are as follows:
1, structure of the invention is compact, and design rationally, by file cabin, cargo compartment and tool cabin transports related flight text respectively
Part, retinue luggage and related training tool be not only able to satisfy property money and have followed pilot's transition simultaneously, but also can effectively improve many and diverse
The efficiency of loading and unloading of goods and materials；And radome fairing, skinpiston, forward flange disk and rear stub center line mutually coincide, deepen one
Body degree and more meet aerodynamic demands, and then improves security performance；It is welded between forward flange disk and rear stub
There is whole skinpiston, is convenient for pressing equal strength reasonable layout material in structure, overall and local stiffness is more preferable, and skinpiston is not easy
Unstability improves aerodynamic characteristic, simultaneously because reducing number of rivets using welding, and then reduces assembly work amount, allows table
Face is more smooth, improves aerodynamic configuration accuracy, in a disguised form reduces fuel oil loss；Shell is both designed as out of my cabin for tool cabin and file
Cross type welding structure, enhances shell load ability, and its section be it is cross, further enhance whole knot
Structure intensity and security performance.
2, cowling design of the invention reduces resistance, more meets aerodynamic demands, and radome fairing is adopted at streamlined
Reduce number of rivets with welding, and then reduces assembly work amount；Radome fairing is connected with the skinpiston at middle part, allows gondola table
Face integration, further promotes surface to be more in line with aerodynamic demands, improves rectification effect to meet aerodynamic loading；Before connect disk
Certain supporting role is all played with disk is followed by, makes the fixation of radome fairing more reliable and more stable, it is strong to further increase overall structure
Degree and security performance, the gondola head of setting also further improve rectification effect.
3, the size shape of secondary hatch door of the invention is identical as the corresponding sectional dimension shape in cabin, convenient for loading and unloading goods and materials, into
And the goods and materials efficiency of loading and unloading is improved, hatch door hinge and lid lock are provided on secondary hatch door, structure is simple, conveniently opening and closing.
4, main hatch door of the invention is open by design, opens main hatch door and is all turned on small-sized force-bearing lock and removes master
Hatch door will not be hindered by hatch door when avoiding handling goods and materials, further improve the goods and materials efficiency of loading and unloading；Simultaneously when main hatch door is set up
When, it allows main hatch door tightly to lock with skinpiston by several small-sized force-bearings lock on main four side of hatch door and becames one, prevented to fly
The possibility that hatch door is opened suddenly during row has greatly ensured the reliability of entire gondola Material Transportation.
5, the safety rope that swivel of the invention and Qi Nei are worn is used to fasten the goods and materials of cargo compartment, reduces due to flight
Shakiness in the process and caused by goods and materials collisions, to improve practicability.
6, the present invention is fixed aboard by lifting lug, and lifting lug is arranged on upper bearing beam, upper bearing beam and lower load
Middle part of the Liang Jun as gondola is improved by welding and the dual fixation of thread connection and is hung so that middle part is main bearing position
The enabling capabilities of cabin rear and front end, to play the role of improving entire gondola security performance.
Detailed description of the invention
Fig. 1 is outline structural diagram of the invention；
Fig. 2 is schematic diagram of internal structure of the invention；
Fig. 3 is the structural schematic diagram near secondary hatch door of the invention；
Appended drawing reference:
1- front fairing, radome fairing after 2-, 3- forward flange disk, 4- rear stub, the upper bearing beam of 5-, bearing beam under 6-,
6.1- swivel, 7- cargo compartment, 8- skinpiston, 9- lifting lug, 10- file cabin, 10.1- gondola head meet disk, 11- before 10.2-
Tool cabin, 11.1- are followed by disk, the main hatch door of 12-, and 12.1- small-sized force-bearing is locked, 13- pair hatch door, 13.1- hatch door hinge, and 13.2- mouthfuls
Cover lock.
Specific embodiment
In order to which those skilled in the art better understand the present invention, with reference to the accompanying drawing with following embodiment to the present invention
It is described in further detail.
Embodiment 1
As shown in Figure 1, a kind of novel gondola for aviation loading, including skeleton component, radome fairing and several hatch doors, institute
It states radome fairing to be made of front fairing 1 and rear radome fairing 2, skeleton component includes forward flange disk 3 and rear stub in the form of annular discs
4, lower bearing beam 6 and the upper bearing beam 5 as entire gondola main load-bearing part are fixed between forward flange disk 3 and rear stub 4, on
The cargo compartment 7 and outside that storage retinue luggage is formed between bearing beam 5 and lower bearing beam 6 are enclosed equipped with skinpiston 8, covering wall
Plate 8 is shelly-shaped in column and both ends are respectively welded on forward flange disk 3 and rear stub 4, and upper bearing beam 5 is provided through covering wall
Plate 8 and two lifting lugs 9 being connected with aircraft, 3 other side of forward flange disk are fixed with file cabin 10 and wrap file cabin 10
Front fairing 1,4 other side of rear stub are fixed with tool cabin 11 and wrap the rear radome fairing 2 in tool cabin 11,10 He of file cabin
Tool cabin 11 is using cross type welding structure and section is in cross, be provided on skinpiston 8 main hatch door 12 and
Forward flange disk 3 and rear stub 4 are provided with a secondary hatch door 13, radome fairing, skinpiston 8, forward flange disk 3 and rear stub
4 center line mutually coincides.
Transport related flight file, retinue luggage and correlation training respectively by file cabin 10, cargo compartment 7 and tool cabin 11
Tool had not only been able to satisfy property money and has followed pilot's transition simultaneously, but also can effectively improve the efficiency of loading and unloading of many and diverse goods and materials；And it is whole
The center line of stream cover, skinpiston 8, forward flange disk 3 and rear stub 4 mutually coincides, and deepens integrated degree and more meets
Aerodynamic demands, and then improve security performance；Whole skinpiston 8 is welded between forward flange disk 3 and rear stub 4,
Convenient for pressing equal strength reasonable layout material in structure, overall and local stiffness is more preferable, and skinpiston 8 is not easy unstability, improves gas
Dynamic characteristic simultaneously because reducing number of rivets using welding, and then reduces assembly work amount, makes surface more smooth, mention
High aerodynamic configuration accuracy, in a disguised form reduces fuel oil loss；Tool cabin 11 and 10 shell of file cabin are both designed as right-angled intersection
Type welding structure, enhances shell load ability, and its section be it is cross, further enhance overall structural strength and
Security performance.
Embodiment 2
As shown in Figure 1, the present embodiment is to be further optimized on the basis of embodiment 1, specifically:
Front fairing 1 and 2 shape of rear radome fairing are to meet the streamlined of aerodynamic loading demand and be respectively welded at preceding method
On blue disk 3 and rear stub 4, front fairing 1 and rear radome fairing 2 are connected with 8 both ends of skinpiston respectively.
10 end of file cabin is fixed with the gondola head 10.1 wrapped up by front fairing 1, gondola head 10.1 and file cabin 10 it
Between be fixed with support front fairing 1 before connect disk 10.2, what 11 end of tool cabin was fixed with radome fairing 2 after support is followed by disk
11.1。
Cowling design more meets aerodynamic demands at streamlined, reduction resistance, and radome fairing is using welding reduction
Number of rivets, and then reduce assembly work amount；Radome fairing is connected with the skinpiston 8 at middle part, makes gondola surface integrated,
Further surface is promoted to be more in line with aerodynamic demands, improves rectification effect to meet aerodynamic loading；Before connect disk 10.2 and after
It connects disk 11.1 and all plays certain supporting role, make the fixation of radome fairing more reliable and more stable, it is strong to further increase overall structure
Degree and security performance, the gondola head 10.1 of setting also further improve rectification effect.
Embodiment 3
As shown in Figure 1 to Figure 2, the present embodiment is further optimized on the basis of embodiment 2, specifically:
Secondary hatch door 13 on the forward flange disk 3 and rear stub 4 sectional dimension shape with file cabin 10 and tool cabin 11 respectively
Shape is identical, and secondary 13 top of hatch door is fixed on ring flange by hatch door hinge 13.1, and secondary 13 bottom of hatch door is respectively and fixedly provided with one
Lid lock 13.2 for hatch door opening and closing.
The size shape of secondary hatch door 13 is identical as the corresponding sectional dimension shape in cabin, convenient for handling goods and materials, and then improves object
The efficiency of loading and unloading is provided, hatch door hinge 13.1 and lid lock 13.2 are provided on secondary hatch door 13, structure is simple, conveniently opening and closing.
Embodiment 4
As shown in Figure 1 to Figure 2, the present embodiment is further optimized on the basis of embodiment 3, specifically:
The mounting plate being fixed on skinpiston 8 is provided between skinpiston 8 and main hatch door 12, main hatch door 12 is by setting
Several small-sized force-bearings lock 12.1 and mounting plate on its four side is set to connect and be provided with liner plate between main hatch door 12 and mounting plate.
Main hatch door 12 is open by design, opens main hatch door 12 and is all turned on small-sized force-bearing lock 12.1 and removes main cabin
Door 12 will not be hindered by hatch door when avoiding handling goods and materials, further improve the goods and materials efficiency of loading and unloading；Simultaneously when main hatch door 12 is pacified
When upper, allowed main hatch door 12 tightly to lock with skinpiston 8 by several small-sized force-bearings lock 12.1 on main 12 4 side of hatch door and become one
Body has prevented the possibility that hatch door in flight course is opened suddenly, has greatly ensured the reliability of entire gondola Material Transportation.
Embodiment 5
As shown in Figure 1 to Figure 2, the present embodiment is further optimized on the basis of embodiment 3, specifically:
Lower 6 upper surface of bearing beam and 5 lower surface of upper bearing beam are provided with several swivels 6.1, in swivel 6.1
It is equipped with safety rope.
The safety rope that swivel 6.1 and Qi Nei are worn is used to fasten the goods and materials of cargo compartment 7, reduces due in flight course
Shakiness and caused by goods and materials collision and so on, to improve practicability.
Embodiment 5
As shown in Figure 1 to Figure 2, the present embodiment is further optimized on the basis of embodiment 3, specifically:
It is dual by welding and thread connection between upper bearing beam 5 and lower bearing beam 6 and forward flange disk 3 and rear stub 4
It is fixed.
Entire gondola is fixed aboard by lifting lug 9, and lifting lug 9 is arranged on upper bearing beam 5, upper bearing beam 5 with
Lower bearing beam 6 is mentioned so that middle part is main bearing position by welding and the dual fixation of thread connection as the middle part of gondola
The high enabling capabilities of gondola rear and front end, to play the role of improving entire gondola security performance.
The above, only presently preferred embodiments of the present invention, are not intended to limit the invention, patent protection model of the invention
It encloses and is subject to claims, it is all to change with equivalent structure made by specification and accompanying drawing content of the invention, similarly
It should be included within the scope of the present invention.
Claims (7)
1. a kind of novel gondola for aviation loading, which is characterized in that including skeleton component, radome fairing and several hatch doors, institute
Radome fairing is stated to be made of front fairing (1) and rear radome fairing (2), skeleton component include forward flange disk (3) in the form of annular discs and after
Ring flange (4) is fixed with lower bearing beam (6) and upper bearing beam (5), upper bearing beam between forward flange disk (3) and rear stub (4)
(5) cargo compartment (7) are formed between lower bearing beam (6) and outside is enclosed equipped with skinpiston (8), skinpiston (8) is in column shell
Shape and both ends are respectively welded on forward flange disk (3) and rear stub (4), and upper bearing beam (5) is provided through skinpiston
(8) and with aircraft two lifting lugs (9) being connected, forward flange disk (3) other side are fixed with file cabin (10) and wrap file
The front fairing (1) in cabin (10), rear stub (4) other side are fixed with tool cabin (11) and wrap the rear whole of tool cabin (11)
Stream cover (2), file cabin (10) and tool cabin (11) are in cross, skinpiston using cross type welding structure and section
(8) it is provided with main hatch door (12) on and forward flange disk (3) and rear stub (4) are provided with a secondary hatch door (13).
2. a kind of novel gondola for aviation loading according to claim 1, which is characterized in that the front fairing
(1) and rear radome fairing (2) shape is to meet the streamlined of aerodynamic loading demand and be respectively welded at forward flange disk (3) and rear method
On blue disk (4).
3. a kind of novel gondola for aviation loading according to claim 2, which is characterized in that the file cabin (10)
End is fixed with the gondola head (10.1) wrapped up by front fairing (1), is fixed between gondola head (10.1) and file cabin (10)
It is connect disk (10.2) before support front fairing (1), radome fairing (2) is followed by disk after tool cabin (11) end is fixed with support
(11.1)。
4. a kind of novel gondola for aviation loading according to claim 3, which is characterized in that the forward flange disk
(3) the secondary hatch door (13) and in rear stub (4) is identical as the sectional dimension shape of file cabin (10) and tool cabin (11) respectively,
It is fixed on ring flange by hatch door hinge (13.1) at the top of secondary hatch door (13), secondary hatch door (13) bottom is respectively and fixedly provided with a use
In the lid lock of hatch door opening and closing
(13.2)。
5. a kind of novel gondola for aviation loading according to claim 4, which is characterized in that the skinpiston
(8) be provided with the mounting plate being fixed on skinpiston (8) between main hatch door (12), main hatch door (12) by setting its four
Several small-sized force-bearings lock (12.1) on side connect with mounting plate and is provided with liner plate between main hatch door (12) and mounting plate.
6. according to claim 1 to a kind of novel gondola for aviation loading described in any one in 5, which is characterized in that
Lower bearing beam (6) upper surface and upper bearing beam (5) lower surface are provided with several swivels (6.1), swivel
(6.1) safety rope is equipped in.
7. according to claim 1 to a kind of novel gondola for aviation loading described in any one in 5, which is characterized in that
Pass through welding and thread connection between the upper bearing beam (5) and lower bearing beam (6) and forward flange disk (3) and rear stub (4)
Dual fixation.
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 true CN109367800A (en) | 2019-02-22 |
| CN109367800B CN109367800B (en) | 2021-10-15 |
Family
ID=65404752
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810991372.3A Active CN109367800B (en) | 2018-08-28 | 2018-08-28 | Novel nacelle for aerial cargo |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109367800B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114093211A (en) * | 2021-11-05 | 2022-02-25 | 河北汉光重工有限责任公司 | Full-section cargo hold roll-on training rack of conveyer |
| 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 |
| CN114229010A (en) * | 2022-02-23 | 2022-03-25 | 四川腾盾科技有限公司 | Low-cost simple unmanned aerial vehicle nacelle structure |
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| 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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| 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 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114093211A (en) * | 2021-11-05 | 2022-02-25 | 河北汉光重工有限责任公司 | Full-section cargo hold roll-on training rack of conveyer |
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| CN114229010A (en) * | 2022-02-23 | 2022-03-25 | 四川腾盾科技有限公司 | Low-cost simple unmanned aerial vehicle nacelle structure |
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| Publication number | Publication date |
|---|---|
| CN109367800B (en) | 2021-10-15 |
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