CN115352620B - Nose landing gear cabin structure of water plane - Google Patents
Nose landing gear cabin structure of water plane Download PDFInfo
- Publication number
- CN115352620B CN115352620B CN202211077331.6A CN202211077331A CN115352620B CN 115352620 B CN115352620 B CN 115352620B CN 202211077331 A CN202211077331 A CN 202211077331A CN 115352620 B CN115352620 B CN 115352620B
- Authority
- CN
- China
- Prior art keywords
- landing gear
- side wall
- wall plate
- support
- cabin door
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 title claims abstract description 44
- 238000009434 installation Methods 0.000 claims abstract description 9
- 238000007789 sealing Methods 0.000 claims abstract description 5
- 230000003014 reinforcing effect Effects 0.000 claims description 9
- 230000005540 biological transmission Effects 0.000 claims description 4
- 238000007599 discharging Methods 0.000 claims description 2
- 230000002411 adverse Effects 0.000 abstract description 4
- 230000000694 effects Effects 0.000 abstract description 3
- 230000005484 gravity Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000002787 reinforcement Effects 0.000 description 1
- 238000005728 strengthening Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
- B64C25/16—Fairings movable in conjunction with undercarriage elements
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/001—Devices not provided for in the groups B64C25/02 - B64C25/68
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Body Structure For Vehicles (AREA)
Abstract
The application provides a front landing gear cabin structure of a water plane, which belongs to the technical field of aircraft fuselage structural design, wherein a watertight front end frame of the structure is connected with a right side wall plate, a left side wall plate and an inclined cover plate and ensures sealing, and a cabin door upper lock support is arranged on a web plate; an upper cross beam is arranged on the inclined cover plate; the rear support truss is matched with the front support truss for use and is supported on the left side wall plate and the right side wall plate; the upper cross beam is positioned above the top inclined cover plate, and two ends of the upper cross beam are connected with the vertical beams to form a continuous transverse stiffening beam assembly; the nose landing gear pivot bearing mount pad is arranged between two vertical beams, in the right side wallboard outside, corresponds in the position of nose landing gear pivot bearing mount pad, has arranged the longeron, and the longeron is connected on the vertical beam, has solved the big installation problem of locking mechanism volume is received and released to the nose landing gear hatch door of seaplane, and the problem that V type ship bottom installation space is little can also avoid taking water take off and bring the adverse effect to the focus.
Description
Technical Field
The application belongs to the technical field of aircraft fuselage structure design, and particularly relates to a nose landing gear cabin structure of a water plane.
Background
The nose landing gear cabin of the aircraft is a nose landing gear mounting and accommodating structure and is responsible for bearing and transmitting landing gear loads and simultaneously providing support for a landing gear mounting and retracting mechanism. A retraction mechanism for the forward lift door is also mounted within the nose landing gear bay. Nose landing gear is typically stowed forward with the shaft typically near the frame web and lower fuselage skin panels to facilitate load transfer.
The nose landing gear cabin of a certain water plane is also used for installing and accommodating the nose landing gear, but unlike a common civil plane, the nose landing gear cabin is used for bearing water load and water internal pressure load after leaving water, and the load can be transmitted to the retraction mechanism, so that the retraction mechanism and the lock mechanism are high in strength and large in occupied space, the nose landing gear is retracted backwards, and a certain difficulty is brought to the layout of the nose landing gear cabin. At the same time the nose landing gear bay is being flown into the bay during the take-off and landing of the aircraft, so sealing and drainage measures are taken into account.
Disclosure of Invention
In order to solve the problem of difficult layout of a nose landing gear cabin structure of a water plane in the related art, the invention provides the nose landing gear cabin structure of the water plane, which comprises the following technical scheme:
A water craft nose landing gear bay structure comprising: the watertight front end frame, the inclined cover plate, the rear support truss, the right side wall plate, the front landing gear rotating shaft bearing mounting seat, the left side wall plate, the front lifting right cabin door folding and unfolding support, the front support truss, the front lifting left cabin door folding and unfolding support and the vertical beam,
The watertight front end frame is connected with the right side wall plate, the left side wall plate and the inclined cover plate and ensures sealing, and a cabin door upper lock support is arranged on the web plate; the inclined cover plate is close to the landing gear structure, and an upper cross beam is arranged on the inclined cover plate; the rear supporting truss is matched with the front supporting truss for use, and is supported on the left side wall plate and the right side wall plate at the same time, so that a direct force transmission path is provided for the front right cabin door folding and unfolding support and the front left cabin door folding and unfolding support; the upper cross beam is positioned above the top inclined cover plate, and two ends of the upper cross beam are connected with the vertical beams to form a continuous transverse stiffening beam assembly; the nose landing gear pivot bearing mount pad is arranged between two vertical beams, corresponds in the position of nose landing gear pivot bearing mount pad in the right side wallboard outside, has arranged the longeron, and the longeron is connected on the vertical beam.
Wherein, the upper part of the front cabin is provided with 3 cover plates.
The rear support truss and the front support truss are of integral machine part truss type structures, are connected with the right side wall plate and the left side wall plate, and are connected with the front right cabin door folding and unfolding support and the front left cabin door folding and unfolding support.
Wherein the seaplane nose landing gear bay structure further comprises: the hinge of the front cabin door is provided with a plurality of hinges,
Each front hatch door hinge is provided with a support and a support short beam corresponding to the installation position of the rear part of the right side wall plate.
Wherein the seaplane nose landing gear bay structure further comprises: a front lifting cabin door is arranged on the front side of the cabin door,
And each front lifting cabin door is provided with a drainage bucket for draining accumulated water in the cabin out of the cabin.
Wherein, vertical strengthening ribs are arranged on the front landing gear rotating shaft bearing mounting seat.
The front landing gear rotating shaft bearing mounting seat is provided with a water outlet for discharging accumulated water in a bearing area to one side of the landing gear.
Wherein, the arrangement of the upper cross beam is consistent with the frame station.
The structure layout of the front landing gear cabin structure of the water plane can solve the problem of large installation size of the front landing gear cabin door retraction locking mechanism of the water plane and small installation space of the V-shaped ship bottom, and can also provide a drainage channel in the cabin after the water plane takes off, so that adverse effects of taking off with water on the gravity center are avoided.
Drawings
FIG. 1 is a schematic view of a nose landing gear bay of a water craft according to an embodiment of the present application;
FIG. 2 is a schematic view of a nose landing gear bay truss girder structure provided by an embodiment of the present application;
Fig. 3 is a schematic view of an external reinforcing structure of a sidewall plate according to an embodiment of the present application.
Reference numerals illustrate:
1-watertight front end frame, 2-inclined cover plate, 3-upper cross beam, 4-rear support truss, 5-right side wall plate, 6-drainage bucket, 7-front cabin door hinge, 8-front cabin door, 9-cabin door upper lock support, 10-front landing gear rotating shaft bearing mounting seat, 11-left side wall plate, 12-front right cabin door folding and unfolding support, 13-front support truss, 14-front left cabin door folding and unfolding support, 15-vertical beam, 16-longitudinal beam, 17-support and 18-support short beam.
Detailed Description
The application is described in further detail below with reference to specific embodiments and figures.
The present invention provides a nose landing gear bay structure for a water craft, see figures 1 to 3, comprising: the front end frame 1, the inclined cover plate 2, the rear support truss 4, the right side wall plate 5, the drainage hopper 6, the front cabin door hinge 7, the front cabin door 8, the front landing gear rotating shaft bearing mounting seat 10, the left side wall plate 11, the front right cabin door folding and unfolding support 12, the front support truss 13, the front left cabin door folding and unfolding support 14 and the vertical beam 15.
The watertight front end frame 1 is connected with the right side wall plate 5, the left side wall plate 11 and the inclined cover plate 2, and ensures sealing, and a cabin door upper lock support 9 is arranged on the web plate for installation support of the cabin door upper lock.
The inclined cover plate 2 is arranged close to the landing gear structure as much as possible so as to compress the landing gear volume to the maximum extent and reduce the structure weight.
The upper cross beam 3 is arranged on the inclined cover plate 2 and plays a role in reinforcing the inclined cover plate 2. The upper part of the front cabin is provided with 3 cover plates, and the volume of the front cabin is compressed as little as possible on the premise of containing the front landing gear and the cabin door mechanism, thereby realizing the purposes of reducing weight and increasing the residual buoyancy of the ship body.
The rear support truss 4 is matched with the front support truss 13 for use, and is supported on the left side wall plate and the right side wall plate at the same time, so as to provide a direct force transmission path for the front right cabin door folding and unfolding support 12 and the front left cabin door folding and unfolding support 14. Specifically, the rear support truss 4 and the front support truss 13 are of integral machine-added part truss type structures, are connected with the right side wall plate 5 and the left side wall plate 11, and are connected with a front right cabin door folding support 12 and a front left cabin door folding support 14. The reinforcing structure can balance side load generated by the front cabin door support in a local small assembly, force is directly transferred, the side load is not outwards diffused, the influence range of the side load is reduced, and the weight of the structure to be reinforced is reduced.
The upper cross beams 3 are positioned above the top inclined cover plates, the number of the upper cross beams is consistent with that of the frames, and two ends of the upper cross beams are connected with the vertical beams 15 to form a continuous transverse stiffening beam assembly. In the present invention, the upper cross member 3 is arranged in line with the frame station and is connected to the vertical beams 15 to form a continuous reinforcement structure.
The nose landing gear shaft bearing mount 10 is disposed between two vertical beams 15 with stringers 16 reinforcing to spread side loads through the stringers 16 to the vertical beams 15.
In the present invention, outside the right side wall panel 5, corresponding to the position of the nose landing gear shaft bearing mount 10, stringers 16 are arranged, which stringers 16 are connected to the front and rear vertical beams 15 for reinforcing the side load of the bearing area.
Each front door hinge 7 is provided with a support 17 and a supporting short beam 18 corresponding to the mounting position of the rear part of the right side wall plate 5, and is used for reinforcing the support load transmission area and diffusing the hydrodynamic load of the hinge joint.
Further, the front door hinge 7, if the standing position is consistent with the frame, will function to spread the load without the additional arrangement of the brackets 17 and the support stubs 18.
The water drainage hopper 6 is arranged on the front cabin door 8, and when the aircraft is water, water can enter the front cabin through the water drainage hopper 6; when the aircraft takes off, water in the cabin can be rapidly discharged out of the cabin through the drainage hopper 6, so that adverse influence of accumulated water on the gravity center during water surface take-off is avoided.
The right side wall plate 5 is mainly provided with a horizontal reinforcing rib, and a vertical reinforcing rib is arranged at the position of the front landing gear rotating shaft bearing mounting seat 10 so as to spread the vertical load of the landing gear.
A water outlet is arranged at the front landing gear rotating shaft bearing mounting seat 10, so that accumulated water in a bearing area can be discharged to one side of the landing gear, and the outside of the machine body is discharged.
The invention provides a front landing gear cabin structure of a water plane, which can solve the problem of large installation volume of a retraction locking mechanism of a front landing gear cabin door of the water plane and small installation space of a V-shaped ship bottom, and can also provide a drainage channel in a cabin after the water plane takes off so as to avoid adverse effects on the gravity center caused by taking off with water.
The foregoing has outlined rather broadly the more detailed description of the application in order that the detailed description thereof that follows may be better understood, and in order that the present application may be better understood. It should be noted that it will be apparent to those skilled in the art that several variations and modifications can be made without departing from the spirit of the application, which are all within the scope of the application.
Claims (6)
1. A water craft nose landing gear bay structure comprising: the watertight front end frame, the inclined cover plate, the rear support truss, the right side wall plate, the front landing gear rotating shaft bearing mounting seat, the left side wall plate, the front lifting right cabin door folding and unfolding support, the front support truss, the front lifting left cabin door folding and unfolding support and the vertical beam,
The watertight front end frame is connected with the right side wall plate, the left side wall plate and the inclined cover plate and ensures sealing, and a cabin door upper lock support is arranged on the web plate; the inclined cover plate is close to the landing gear structure, and an upper cross beam is arranged on the inclined cover plate; the rear supporting truss is matched with the front supporting truss for use, and is supported on the left side wall plate and the right side wall plate at the same time, so that a direct force transmission path is provided for the front right cabin door folding and unfolding support and the front left cabin door folding and unfolding support; the upper cross beam is positioned above the top inclined cover plate, and two ends of the upper cross beam are connected with the vertical beams to form a continuous transverse stiffening beam assembly; the front landing gear rotating shaft bearing mounting seat is arranged between the two vertical beams, and a longitudinal beam is arranged at the outer side of the right side wall plate and corresponds to the position of the front landing gear rotating shaft bearing mounting seat and is connected to the vertical beams;
the rear support truss and the front support truss are of integral machine part truss type structures, are connected with the right side wall plate and the left side wall plate, and are connected with a front right cabin door retraction support and a front left cabin door retraction support;
the water craft nose landing gear bay structure further comprises: a front lifting cabin door is arranged on the front side of the cabin door,
And each front lifting cabin door is provided with a drainage bucket for draining accumulated water in the cabin out of the cabin.
2. The water craft nose landing gear bay structure of claim 1, wherein,
Three cover plates are arranged at the upper part of the front cabin.
3. The water craft nose landing gear bay structure of claim 1, further comprising: the hinge of the front cabin door is provided with a plurality of hinges,
Each front hatch door hinge is provided with a support and a support short beam corresponding to the installation position of the rear part of the right side wall plate.
4. The water craft nose landing gear bay structure of claim 1, wherein,
Vertical reinforcing ribs are arranged on the front landing gear rotating shaft bearing mounting seat.
5. The water craft nose landing gear bay structure of claim 1, wherein,
The front landing gear rotating shaft bearing mounting seat is provided with a water outlet for discharging accumulated water in a bearing area to one side of the landing gear.
6. The water craft nose landing gear bay structure of claim 1, wherein,
The arrangement of the upper cross beam is consistent with the frame station.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211077331.6A CN115352620B (en) | 2022-09-02 | 2022-09-02 | Nose landing gear cabin structure of water plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211077331.6A CN115352620B (en) | 2022-09-02 | 2022-09-02 | Nose landing gear cabin structure of water plane |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN115352620A CN115352620A (en) | 2022-11-18 |
| CN115352620B true CN115352620B (en) | 2024-07-19 |
Family
ID=84007162
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211077331.6A Active CN115352620B (en) | 2022-09-02 | 2022-09-02 | Nose landing gear cabin structure of water plane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115352620B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117326049B (en) * | 2023-11-15 | 2024-10-22 | 中航通飞华南飞机工业有限公司 | Fairing of high-prop main landing gear of large-scale water plane |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101693468A (en) * | 2009-03-04 | 2010-04-14 | 刘世英 | Amphibious large aircraft without air-stairs |
| CN103158853A (en) * | 2011-12-12 | 2013-06-19 | 空中客车运营简化股份公司 | Aircraft nose structure and aircraft with the same |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2603553A1 (en) * | 1986-09-10 | 1988-03-11 | Fernandez Manuel | Amphibious float including a main landing gear in front of the centre of gravity of the aircraft which is retractable by means of a sliding hatch and at the rear end a steering wheel and a retractable rudder |
| US5645250A (en) * | 1993-08-26 | 1997-07-08 | Gevers; David E. | Multi-purpose aircraft |
| GB2290275A (en) * | 1994-06-18 | 1995-12-20 | James Labouchere | Seaplane hull |
| CN110861775B (en) * | 2019-11-26 | 2022-04-29 | 交通运输部南海航海保障中心广州海事测绘中心 | Unmanned aerial vehicle structure for hydrology monitoring |
| CN217198633U (en) * | 2021-11-17 | 2022-08-16 | 青岛万航无人机科技有限公司 | Rescue unmanned aerial vehicle is with forcing to land and using stabilizing mean |
| CN216401767U (en) * | 2021-12-31 | 2022-04-29 | 上海峰飞航空科技有限公司 | Get drainage with unmanned aerial vehicle that hangs down |
-
2022
- 2022-09-02 CN CN202211077331.6A patent/CN115352620B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101693468A (en) * | 2009-03-04 | 2010-04-14 | 刘世英 | Amphibious large aircraft without air-stairs |
| CN103158853A (en) * | 2011-12-12 | 2013-06-19 | 空中客车运营简化股份公司 | Aircraft nose structure and aircraft with the same |
Also Published As
| Publication number | Publication date |
|---|---|
| CN115352620A (en) | 2022-11-18 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CA2020932C (en) | High-capacity fuselage for aircraft | |
| CN115352620B (en) | Nose landing gear cabin structure of water plane | |
| US8915470B2 (en) | Aircraft nose and nose landing gear bay structure | |
| RU2392184C2 (en) | Commercial aircraft | |
| EP2404826A1 (en) | Amphibious large aircraft without airstairs | |
| CN105730671B (en) | Aircraft rear structure | |
| EP2905228A1 (en) | Fuselage airframe and tank | |
| CN102530233A (en) | Front part of an aircraft fuselage incorporating a bay for stowing landing gear | |
| CN113562195A (en) | Box plate frame combined satellite configuration | |
| CN103857591A (en) | Improved front landing-gear well | |
| CN212605879U (en) | Rocket ejection type thrust cone connecting angle box structure | |
| NL2031870B1 (en) | A penetrating high wing structure of civil aircraft with blended-wing-body | |
| CN111302186A (en) | Passenger liner cabin unit lift | |
| CN212401540U (en) | Aircraft body and rotor craft thereof | |
| CN216003090U (en) | Engine back support structure and airplane | |
| CN110893905A (en) | Front section region of an aircraft with simplified structure | |
| CN114348265A (en) | Wing body fusion body and aircraft | |
| CN115384754B (en) | Structure for hanging point of boarding ladder on side part of airplane body of water plane | |
| CN215436806U (en) | Hinge type cabin bottom door supporting structure of dredging engineering ship | |
| CN113581476A (en) | Engine back support structure and airplane | |
| RU2176970C2 (en) | Compartment of flying vehicle with external store pylons | |
| CN219707284U (en) | Ballast tank structure convenient to overhaul | |
| CN222690892U (en) | A bracket suitable for installing satellite communication equipment on Ka-32A11BC helicopter | |
| CN214356728U (en) | Composite material nacelle structure | |
| CN221699017U (en) | Fixing structure of suspension type oil tank of V-shaped ship bottom cabin of water plane |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |