CN113619785A - Vertical take-off and landing unmanned aerial vehicle structure - Google Patents
Vertical take-off and landing unmanned aerial vehicle structure Download PDFInfo
- Publication number
- CN113619785A CN113619785A CN202110960877.5A CN202110960877A CN113619785A CN 113619785 A CN113619785 A CN 113619785A CN 202110960877 A CN202110960877 A CN 202110960877A CN 113619785 A CN113619785 A CN 113619785A
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- China
- Prior art keywords
- fuselage
- module
- tail section
- nose
- skid
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/068—Fuselage sections
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/52—Skis or runners
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/58—Arrangements or adaptations of shock-absorbers or springs
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/20—Rotorcraft characterised by having shrouded rotors, e.g. flying platforms
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
The utility model provides a VTOL unmanned aerial vehicle structure, this unmanned aerial vehicle structure contain the module and skid module are hung to locomotive module, fuselage middle section module, fuselage tail section module, rotor, constitute unmanned aerial vehicle's fuselage structure by locomotive module, fuselage middle section module, fuselage tail section module butt joint, the rotor hang the top that the module was installed at fuselage middle section module, the skid module install the bottom at fuselage middle section module.
Description
Technical Field
The application relates to an unmanned aerial vehicle structural design, and relates to a vertical take-off and landing unmanned aerial vehicle structure.
Background
Current VTOL drones are typically all composite monolithic structures. The unmanned aerial vehicle fuselage comprises the whole keel structure in bottom, vertical and horizontal bearing structure and the skin structure that maintains the appearance. The bottom or the top of the machine body is connected with a plurality of pairs of support arms, and one or a pair of propellers with shafts is arranged at the tail ends of the support arms. The landing gear structure is typically of the simple stick or skid type.
The problem that current VTOL unmanned aerial vehicle exists is:
(1) the impact resistance of the composite material integral structure body is poor, and the bearing capacity of the composite material integral structure body for sudden impact conditions such as bird collision is poor. When the local part of the unmanned aerial vehicle body is collided by birds or obstacles, the existing repair measures are to prepare composite material parts with considerable sizes and meeting the appearance requirements for reinforcement, the repair period is long, and the repair difficulty is large. For unmanned aerial vehicles with operation tasks, great economic loss can be brought.
(2) Current VTOL unmanned aerial vehicle is mostly the single power drive by one set of motor control, when electronic equipment became invalid, only leaned on the lift that the screw spin descends and produce, is difficult to keep out the impact load who produces when landing, and under this condition, simple rod-type or skid formula undercarriage can lead to the organism structure damage to the great load of organism structure transmission.
In the aspect of promoting maintainability, security, VTOL unmanned aerial vehicle structure has very big improvement space yet.
Disclosure of Invention
An object of this application is to provide a novel VTOL unmanned aerial vehicle structure based on modular design that can realize that quick maintenance maintains, security is high.
The utility model provides a VTOL unmanned aerial vehicle structure, its characterized in that, this unmanned aerial vehicle structure contain the module of nose module, fuselage middle section module, fuselage tail section module, rotor and hang module and skid module, unmanned aerial vehicle's fuselage structure comprises nose module, fuselage middle section module, fuselage tail section module butt joint, the rotor hang the module and install the top at fuselage middle section module, the skid module install the bottom at fuselage middle section module.
The aircraft nose module include aircraft nose covering, aircraft nose stringer, aircraft nose reinforcing frame, aircraft nose butt joint frame and aircraft nose floor and windshield, aircraft nose covering, aircraft nose stringer be the carbon-fibre composite structure, through co-curing technique interconnect, aircraft nose reinforcing frame, aircraft nose butt joint frame use bolted connection with adjacent structure.
The fuselage middle section module include fuselage middle section covering, fuselage middle section stringer, fuselage middle section rib frame, fuselage middle section butt joint frame and fuselage middle section floor, be equipped with the hatch door in the both sides in fuselage middle section, be equipped with the mounting hole that the module was hung to the rotor at the top in fuselage middle section, be equipped with the butt joint who is connected with the skid module in the bottom in fuselage middle section.
The fuselage tail section module comprises a fuselage tail section skin, a fuselage tail section stringer, a fuselage tail section reinforcing frame, a fuselage tail section butt-joint frame, a fuselage tail section floor and a maintenance opening cover, the fuselage tail section skin and the fuselage tail section stringer are made of carbon fiber composite materials and are mutually connected through co-curing technology, and the fuselage tail section reinforcing frame, the fuselage tail section butt-joint frame and an adjacent structure are connected through bolts.
The rotor wing hanging module comprises a hanging connector, a hanging rod and a shaftless rotor wing ducted fan, wherein the ducted fan is divided into an upper layer and a lower layer which are designed in a redundant manner.
The skid module constitute by attach fitting, skid frame and buffer, the skid frame contains two bow-shaped roof beams and two skid sill bars, the both ends of every bow-shaped roof beam are connected with the skid sill bar through a buffer respectively, attach fitting establishes at the top of bow-shaped roof beam, attach fitting matches with the butt joint of fuselage middle section bottom.
The beneficial effect of this application lies in: 1) the unmanned aerial vehicle that takes off and land vertically structure adopt modular structure design, when meeting with the bird and hitting or unexpected striking etc. and cause structural damage, the accessible is changed impaired module and is realized restoreing fast, shortens maintenance duration, has improved unmanned aerial vehicle that takes off and land vertically operation ability. 2) The rotor wing hanging module adopts a structural form of a double-layer ducted fan, and the two power systems are mutually backed up, so that the safety is improved. 3) The aluminum honeycomb buffer adopted by the skid type landing gear module is light in weight and can absorb larger impact energy, and the safety margin of the vertical take-off and landing unmanned aerial vehicle is improved.
The present application is described in further detail below with reference to the accompanying drawings of embodiments.
Drawings
FIG. 1 is a schematic view of unmanned aerial vehicle module assembly
FIG. 2 is a schematic view of a nose module
FIG. 3 is a mid-fuselage block diagram
FIG. 4 is a modular view of the aft section of the fuselage
FIG. 5 is a schematic view of a rotor hanging module
FIG. 6 is a schematic view of a skid module
FIG. 7 is a cross-sectional view of a hanging connector structure
FIG. 8 is a schematic cross-sectional view of a skid bumper construction
The numbering in the figures illustrates: 1 aircraft nose module, 2 aircraft middle section module, 3 aircraft tail section module, 4 rotor wing hanging module, 5 skid module, 6 cabin doors, 7 aircraft nose skins, 8 windshield glass, 9 aircraft nose stringers, 10 aircraft nose reinforcing frames, 11 aircraft nose butt joint frames, 12 butt joint holes, 13 aircraft nose floors, 14 aircraft nose floor supporting frames, 15 aircraft middle section skins, 16 aircraft middle section stringers, 17 aircraft middle section reinforcing frames, 18 aircraft middle section front butt joint frames, 19 aircraft middle section rear butt joint frames, 20 aircraft middle section floors, 21 aircraft middle section floor supporting frames, 22 mounting holes, 23 aircraft tail section skins, 24 aircraft tail section stringers, 25 aircraft tail section reinforcing frames, 26 aircraft tail section butt joint frames, 27 aircraft tail section floors, 28 aircraft tail section floor supporting frames, 29 maintenance covers, 30 hanging joints, 31 hanging rods, 32 ducted fans, 33 connecting joints, 34 beams, 35 skid bottom rods, 36 buffers, cambered surfaces, 28 aircraft tail section floors, 28 aircraft tail section floor supporting frames, 29 maintenance covers, 30 hanging rods, 31 hanging rods, 32 ducted fans, 33 connecting joints, 34 beams, 35 skid bottom rods, 36 buffer bottom rods, 37 reinforcing struts, 38 stop rings, 39 mounting feet, 40 cushioning material.
Detailed Description
Referring to the drawings, the vertical take-off and landing unmanned aerial vehicle structure is formed by butting a plurality of module structures, and is shown in fig. 1. The structure of the vertical take-off and landing unmanned aerial vehicle comprises a machine head module 1, a machine body middle section module 2, a machine body tail section module 3, a rotor wing hanging module 4 and a skid module 5, and a cabin door 6, wherein the machine body structure of the unmanned aerial vehicle is formed by butt joint of the machine head module 1, the machine body middle section module 2 and the machine body tail section module 3, the rotor wing hanging module 4 is installed at the top of the machine body middle section module 2, and the skid module 5 is installed at the bottom of the machine body middle section module 2.
In implementation, as shown in fig. 2, the nose module 1 includes a nose skin 7, a plurality of transverse nose stringers 9, a plurality of longitudinal nose reinforcing frames 10, a nose butt-joint frame 11, a nose floor 13, and a windshield 8, the nose skin 7 and the nose stringers 9 are made of carbon fiber composite materials and are formed into an integral structure by co-curing technology, the nose reinforcing frames 10 and the nose butt-joint frame 11 are made of metal structural members and are connected with the adjacent nose skin 7 and nose stringers 9 by bolts, the windshield 8 is embedded on the nose skin 7, and the windshield 8 is made of aircraft glass with a multilayer composite structure and an electric heating function so as to adapt to various special meteorological conditions. In order to reduce weight and improve durability, a machine head floor 13 is made of a paper honeycomb sandwich composite material and is arranged at the middle lower part of the machine head module 1 by a method of combining glue joint and bolt joint, the machine head floor 13 is supported by a machine head floor supporting frame 14, the lower end of the machine head floor supporting frame 14 is connected with a machine head skin 7 and a machine head stringer 9, and particularly, a butt joint hole 12 which is butted with a machine body middle section module 2 is arranged on a machine head butt joint frame 11.
As shown in fig. 3, the mid-fuselage module 2 includes a mid-fuselage skin 15, a plurality of transverse mid-fuselage stringers 16, a plurality of longitudinal mid-fuselage stiffening frames 17, a mid-fuselage front docking frame 18 and a mid-fuselage rear docking frame 19, and a mid-fuselage floor 20 and a mid-fuselage floor support frame 21. The front butt-joint frame 18 of the middle section of the fuselage is arranged at the front end of the middle section module 2 of the fuselage and is in butt joint with the nose module 1; the rear butt-joint frame 19 of the middle fuselage section is arranged at the rear end of the middle fuselage section module 2 and is in butt joint with the rear fuselage section module 3. The front butt-joint frame 18 of the middle section of the fuselage and the rear butt-joint frame 19 of the middle section of the fuselage are respectively provided with a butt-joint hole 12. Two sides of the machine body middle section 2 are provided with connecting door frames of the cabin doors 5, and the cabin doors 5 are outward-opening cabin doors and adopt a throwing-type opening mode. The top of fuselage middle section 2 is provided with mounting hole 22 for rotor hanging module 4, and the bottom of fuselage middle section 2 is provided with a butt joint connected with skid module 6, which is not shown in the figure. Similar to the head module 1, the fuselage middle skin 15 and the fuselage middle stringer 16 are formed by using a carbon fiber composite high-temperature co-curing technology, the fuselage middle reinforcing frame 17, the fuselage middle front butt frame 18 and the fuselage middle rear butt frame 19 are metal structural members and are connected with the adjacent fuselage middle skin 15 and fuselage middle stringer 16 by using bolts, the fuselage middle floor 20 is made of a paper honeycomb sandwich composite material and is arranged at the middle lower part of the fuselage middle module 2 by using a method of gluing and bolt connection combination, and the fuselage middle floor 20 is supported by the fuselage middle floor supporting frame 21.
As shown in fig. 4, the fuselage tail section module 3 includes a fuselage tail section skin 23, a plurality of transverse fuselage tail section stringers 24, a plurality of longitudinal fuselage tail section reinforcing frames 25, a fuselage tail section butt-joint frame 26, a fuselage tail section floor 27, and a maintenance cover 29. Similar to the fuselage middle section module 2 of the fuselage head module 1, the fuselage tail section skin 23 and the fuselage tail section stringer 24 are made of carbon fiber composite materials and are connected with each other through co-curing technology, and the fuselage tail section reinforcing frame 25 and the fuselage tail section butt-joint frame 26 are made of metal structural members and are connected with the adjacent fuselage tail section skin 23 and the fuselage tail section stringer 24 through bolts. The material of the fuselage tail section floor 27 is a paper honeycomb sandwich composite material, the material is arranged at the middle lower part of the fuselage tail section module 3 by a method of combining glue joint and bolt joint, and the fuselage tail section floor 27 is supported by a fuselage tail section floor supporting frame 28. The butt-joint frame 26 of the tail section of the fuselage is arranged at the front end of the module 2 of the tail section of the fuselage, the butt-joint frame 26 of the tail section of the fuselage is in butt joint with the butt-joint frame 19 of the back section of the middle section of the fuselage, and the butt-joint holes 12 are correspondingly arranged on the butt-joint frame 26 of the tail section of the fuselage.
As shown in fig. 5, the rotor wing hanging module 4 includes a hanging connector 30, hanging rods 31 and a shaftless rotor wing ducted fan 32, in the implementation, the plurality of hanging rods 31 are radially and uniformly connected around the hanging connector 30, the outer end of each hanging rod is connected with a ducted fan 32, and the ducted fan 32 of the present application is divided into an upper layer and a lower layer which are mutually redundant. Every layer of duct fan all adopts shaftless magnetic suspension orbit duct fan structure, and every layer has three flabellums, has the electromagnetism track in the duct, has avoided the frictional force between the structure during operation, has improved energy conversion efficiency, has reduced VTOL manned unmanned aerial vehicle's noise. The hanging joint 30 is internally provided with a stop ring 38 to realize radial restraint on the hanging rod 31, and the lower surface of the hanging joint 30 is connected with the mounting hole 22 at the top of the fuselage middle section skin 15 through a mounting base 39, so that the mounting efficiency is improved, as shown in figure 7.
As shown in fig. 6, the skid module 6 is composed of a connection joint 33, a skid frame and a buffer 36, the skid frame comprises two arched beams 34 and two skid bottom rods 35, two ends of each arched beam 34 are respectively connected with the skid bottom rods 35 through the buffer 36, the connection joint 33 is arranged at the top of the arched beam 34, the connection joint 33 is matched with a bottom butt joint of the fuselage middle section module 2, and a reinforcing stay 37 is arranged between the two arched beams 34 in order to ensure the rigidity of the skid module 6.
In the implementation, the two arched beams 34, the two skid bottom rods 35 and the reinforcing support rods 37 are made of high-strength steel pipes, so that the structure is simple, and the installation is convenient. Two bow-shaped roof beams 34 of skid rack set up respectively around the unmanned aerial vehicle focus, and after bow-shaped roof beam 34 absorbed impact energy through buffer 36, realize steadily descending. The buffer 36 is internally provided with a sleeve made of high-strength steel and an aluminum honeycomb buffer material 40 with stable buffer performance, as shown in fig. 8, and has light weight and strong impact resistance.
Claims (6)
1. The utility model provides a VTOL unmanned aerial vehicle structure, its characterized in that, this unmanned aerial vehicle structure contains the module of locomotive module, fuselage middle section module, fuselage tail section module, rotor and hangs module and skid module, constitutes unmanned aerial vehicle's fuselage structure by locomotive module, fuselage middle section module, fuselage tail section module butt joint, the rotor hang the module and install the top at fuselage middle section module, the skid module install the bottom at fuselage middle section module.
2. The structure of claim 1, wherein the nose module comprises a nose skin, a nose stringer, a nose reinforcing frame, a nose butt frame, a nose floor, and a windshield, the nose skin and the nose stringer are made of carbon fiber composite material and are connected to each other by co-curing, and the nose reinforcing frame, the nose butt frame, and the adjacent structure are connected by bolts.
3. The structure of claim 1, wherein the mid-fuselage module comprises a mid-fuselage skin, a mid-fuselage stringer, a mid-fuselage reinforcing frame, a mid-fuselage docking frame, and a mid-fuselage floor, wherein doors are provided on both sides of the mid-fuselage, a mounting hole for a rotor hanging module is provided on the top of the mid-fuselage, and a docking head connected to the skid module is provided on the bottom of the mid-fuselage.
4. The structure of claim 1, wherein the tail section module comprises a tail section skin, a tail section stringer, a tail section stiffener, a tail section butt-joint frame, a tail section floor and a maintenance cover, the tail section skin and the tail section stringer are made of carbon fiber composite material and are connected with each other by co-curing technology, and the tail section stiffener, the tail section butt-joint frame and the adjacent structure are connected by bolts.
5. The structure of claim 1, wherein the rotor hanging module comprises a hanging joint, a hanging rod, and a shaftless rotor ducted fan, and the ducted fan is divided into an upper layer and a lower layer which are designed as a redundant structure.
6. The structure of claim 1, wherein the skid module comprises a connection joint, a skid frame and a buffer, the skid frame comprises two arched beams and two skid bottom rods, two ends of each arched beam are respectively connected with the skid bottom rods through a buffer, the connection joint is arranged on the top of the arched beams, and the connection joint is matched with the butt joint at the bottom of the middle section of the fuselage.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110960877.5A CN113619785A (en) | 2021-08-20 | 2021-08-20 | Vertical take-off and landing unmanned aerial vehicle structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110960877.5A CN113619785A (en) | 2021-08-20 | 2021-08-20 | Vertical take-off and landing unmanned aerial vehicle structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113619785A true CN113619785A (en) | 2021-11-09 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110960877.5A Pending CN113619785A (en) | 2021-08-20 | 2021-08-20 | Vertical take-off and landing unmanned aerial vehicle structure |
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| CN (1) | CN113619785A (en) |
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|---|---|---|---|---|
| CN1177561A (en) * | 1996-10-07 | 1998-04-01 | 王新云 | Prestressing structure of aircraft and making method thereof |
| CN103158854A (en) * | 2011-12-12 | 2013-06-19 | 空中客车运营简化股份公司 | Aircraft nose structure |
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| US20150122940A1 (en) * | 2013-11-05 | 2015-05-07 | Airbus Helicopters | Rotorcraft fuselage structure incorporating a load-bearing middle floor interposed between a cabin space and an equipment space |
| EP3210882A1 (en) * | 2016-02-08 | 2017-08-30 | Bell Helicopter Textron Inc. | Composite wing structure and methods of manufacture |
| CN107985572A (en) * | 2017-12-16 | 2018-05-04 | 江苏福莱尔航空科技有限公司 | A kind of modularization fast disassembly type unmanned helicopter |
| CN110626520A (en) * | 2018-06-25 | 2019-12-31 | 空中客车运营简化股份公司 | Aircraft module, aircraft section, aircraft and aircraft section assembly method |
| CN110949654A (en) * | 2019-12-25 | 2020-04-03 | 彭振根 | Aircraft |
| CN211195749U (en) * | 2019-10-31 | 2020-08-07 | 南京航空航天大学 | Tilt shaftless duct rotor aerocar |
| CN111731475A (en) * | 2020-06-30 | 2020-10-02 | 湖南航天宏图无人机系统有限公司 | Vertical take-off and landing tilting composite wing aircraft |
| CN213262882U (en) * | 2020-09-23 | 2021-05-25 | 北京京东乾石科技有限公司 | Unmanned aerial vehicle's fuselage frame and unmanned aerial vehicle |
-
2021
- 2021-08-20 CN CN202110960877.5A patent/CN113619785A/en active Pending
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1177561A (en) * | 1996-10-07 | 1998-04-01 | 王新云 | Prestressing structure of aircraft and making method thereof |
| CN103158854A (en) * | 2011-12-12 | 2013-06-19 | 空中客车运营简化股份公司 | Aircraft nose structure |
| CN103879541A (en) * | 2012-12-21 | 2014-06-25 | 空中客车运营简化股份公司 | Aircraft Nose With Cockpit And Avionics Bay Modules Integrated Therein |
| US20150122940A1 (en) * | 2013-11-05 | 2015-05-07 | Airbus Helicopters | Rotorcraft fuselage structure incorporating a load-bearing middle floor interposed between a cabin space and an equipment space |
| EP3210882A1 (en) * | 2016-02-08 | 2017-08-30 | Bell Helicopter Textron Inc. | Composite wing structure and methods of manufacture |
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| CN211195749U (en) * | 2019-10-31 | 2020-08-07 | 南京航空航天大学 | Tilt shaftless duct rotor aerocar |
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| CN213262882U (en) * | 2020-09-23 | 2021-05-25 | 北京京东乾石科技有限公司 | Unmanned aerial vehicle's fuselage frame and unmanned aerial vehicle |
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Application publication date: 20211109 |
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