CN107434039A - A kind of unmanned plane - Google Patents
A kind of unmanned plane Download PDFInfo
- Publication number
- CN107434039A CN107434039A CN201610355314.2A CN201610355314A CN107434039A CN 107434039 A CN107434039 A CN 107434039A CN 201610355314 A CN201610355314 A CN 201610355314A CN 107434039 A CN107434039 A CN 107434039A
- Authority
- CN
- China
- Prior art keywords
- fuselage
- unmanned plane
- power arm
- rotor
- frame
- 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.)
- Pending
Links
- 238000009434 installation Methods 0.000 claims abstract description 11
- 239000007769 metal material Substances 0.000 claims abstract description 11
- 238000010586 diagram Methods 0.000 description 6
- 210000002435 tendon Anatomy 0.000 description 5
- 239000002184 metal Substances 0.000 description 3
- 229910052751 metal Inorganic materials 0.000 description 3
- 239000004411 aluminium Substances 0.000 description 2
- 229910052782 aluminium Inorganic materials 0.000 description 2
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 238000003466 welding Methods 0.000 description 2
- 240000007594 Oryza sativa Species 0.000 description 1
- 235000007164 Oryza sativa Nutrition 0.000 description 1
- 229910000831 Steel Inorganic materials 0.000 description 1
- 230000037237 body shape Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000005034 decoration Methods 0.000 description 1
- 238000005183 dynamical system Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- PCHJSUWPFVWCPO-UHFFFAOYSA-N gold Chemical compound [Au] PCHJSUWPFVWCPO-UHFFFAOYSA-N 0.000 description 1
- 239000010931 gold Substances 0.000 description 1
- 229910052737 gold Inorganic materials 0.000 description 1
- 238000003780 insertion Methods 0.000 description 1
- 230000037431 insertion Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 235000009566 rice Nutrition 0.000 description 1
- 239000011435 rock Substances 0.000 description 1
- 239000004576 sand Substances 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
Classifications
-
- 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
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/04—Arrangement or disposition on aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Remote Sensing (AREA)
- Toys (AREA)
Abstract
The present invention relates to a kind of unmanned plane, including multigroup rotor, the fuselage of metal material and English truss formula power arm, the English truss formula power arm connects rotor power system by the way that plate is mounted, the installation site of two groups of adjacent rotors is in set one on the other for fuselage, the fuselage includes shell and openable upper lid, support frame is provided with the shell, the underbelly connects undercarriage.The unmanned plane stiff super of the present invention, stability is good, and flight efficiency is high.
Description
Technical field
The invention belongs to unmanned air vehicle technique field, and in particular to a kind of new unmanned plane.
Background technology
Unmanned plane has on military and civil area to be widely applied very much.Current most of more rotors nobody
Machine, fuselage poor rigidity, stability are poor, and power arm is installed built on the sand, and rotor installation is inconvenient, therefore
A kind of ease of assembly and stable connection be provided, and rigidity it is strong unmanned plane it is necessary.
The content of the invention
It is an object of the invention to solve above-mentioned technical problem, there is provided a kind of nothing using all-metal construction
It is man-machine.
To achieve the above object, the present invention adopts the following technical scheme that：
A kind of unmanned plane, including the fuselage of multigroup rotor, metal material and English truss formula power arm, institute
State English truss formula power arm and connect rotor power system, adjacent two groups of rotors by the way that plate is mounted
Installation site for fuselage in setting one on the other, the fuselage includes shell and can beaten
The upper lid opened, the shell is interior to be provided with support frame, and the underbelly connects undercarriage.
The English truss formula power arm passes through a pulling force locking fixture and two rotatable positioning members
It is connected with fuselage.
The English truss formula power arm includes three support bars, and three support bars pass through tripod phase
Support connection.
The rotor power system includes reduction box, is provided with train of reduction gears in the reduction box, and have
Upper air inlet, side air-out mouth.
The undercarriage includes multiple vertical framves, and each vertical frame includes three vertical supporting bars, and three
The individual vertical supporting bar links together by the combination of triangular shape truss, three vertical supporting bars
Top is connected by a connecting plate with fuselage, by more after the bottom convergence of three vertical supporting bars
Angle locking member is connected with inclined shore bar and horizontal brace rod.
The other end of the inclined shore bar connects support chassis by a flexible elbow.
Unmanned plane of the present invention, due to using metal material fuselage and English truss formula power arm, described three
Angle truss-like power arm connects rotor power system, the peace of adjacent two groups of rotors by the way that plate is mounted
For holding position in setting one on the other for fuselage, the fuselage includes shell and openable
Upper lid, the shell is interior to be provided with support frame, and the underbelly connects undercarriage so that fuselage rigidity
By force, and it can be overhauled and be safeguarded by upper lid opening, and English truss formula power arm is due to using three
Horn shape welding structure, stabilized structure improve the stability of unmanned plane, adjacent two groups of rotors
Installation site is in set one on the other for fuselage so that unmanned plane is in the case of more rotors
Compact-sized, solving the problems, such as more rotors, space-consuming is big at grade, unmanned plane body is big,
So as to improve flight efficiency on the basis of type is reduced.
Brief description of the drawings
Fig. 1 is the schematic diagram of unmanned plane；
Fig. 2 is the structural representation of the fuselage of unmanned plane；
Fig. 3 is the rotor power system of unmanned plane and the connection enlarged diagram of rotor；
Fig. 4 is the schematic diagram of the undercarriage of unmanned plane；
Fig. 5 show the connection diagram of undercarriage and support chassis；
Fig. 6 show rotor power system and the connection diagram of power arm；
Fig. 7 show the connection diagram of power arm and fuselage.
Embodiment
Below, the substantive distinguishing features and advantage of the present invention are further described with reference to example, the present invention
Including but not limited to listed embodiment.
Referring to shown in Fig. 1-7, a kind of unmanned plane, include the fuselage 10 of multigroup rotor 40, metal material
And the English truss formula power arm 20 of metal material, the English truss formula power arm is by being mounted plate
80 connection rotor power systems 30 (reference can be made to shown in Fig. 6), the installation site of adjacent two groups of rotors
It is in set one on the other for fuselage.
Shown in Figure 2, the fuselage includes shell 12 and openable upper lid 11, the shell
The interior battery case 50 provided with metal supporting frames 13 and multiple metal materials, the underbelly connection are risen and fallen
Frame 60.
Wherein, the battery case 50 is connected with fuselage 10 by keeper, the shell bottom of fuselage 10
Corresponding battery load hole 14 is offered in portion and upper lid, after battery is arranged in the battery load hole,
Upper end is covered by corresponding battery case, and battery case is connected with the bottom of lid and shell on fuselage by keeper.
By setting battery case to cover battery, you can to protect battery, also make it that the installation of battery is more convenient,
The battery case is made using metal material, is advantageous to battery good radiating in the course of the work, and protect
Property is strong.
Support frame as described above includes multiple main frames, and the heart intersects and outboard end multiple main frames in the frame
Different directions is respectively directed to, the enclosure is divided into multiple regions, and (supplying cell is arranged on the area
In domain), each a body side frame is connected respectively on two sides of the main frame；Each side frame
One end of frame is connected with a corresponding main frame, the other end is connected and shape with the inwall of the shell
Into three-legged structure, so as to improve the support strength of support frame, the intensity of fuselage is improved.
Wherein, the main frame is rectangular frame, and the body side frame is U-frame frame, the upper Gai Yuzhi
Support is connected by keeper, and the shell is polygonal body shape structure.
Shown in Figure 3, the rotor power system 3 includes reduction box 33, is provided with the reduction box
Train of reduction gears 32, and pass through drive shaft 31, rotation with upper air inlet, side air-out mouth 34, reduction box
Wing folder 35 is connected with two rotors 40, and the housing of reduction box 33 is made by metal material, is passed through
Upper air inlet enters cold wind, is driven by the train of reduction gears of inside, pressure is circulated, and hot blast goes out from side
Air port 34 is discharged, and effectively reduction box is radiated.
Shown in Figure 4, the undercarriage 60 includes multiple vertical framves 62, each vertical frame bag
Including three vertical supporting bars, (including the first vertical supporting bar 63, the second vertical supporting bar the 64, the 3rd are perpendicular
To support bar 65), three vertical supporting bars link together by the combination of triangular shape truss, three institutes
The top for stating vertical supporting bar is connected by a connecting plate 66 with the bottom of fuselage 10, and three described vertical
After the bottom convergence of support bar by multi-angle locking member 67 (there is connecting hole respectively on three directions, use
It is connected in three vertical supporting bars, inclined shore bar 61 and horizontal brace rod 68) with tilting branch
Strut 61 and horizontal brace rod 68 are connected, and horizontal brace rod 68 is connected by cross connecting piece 69
It is connected together to form criss-cross structure, passes through multi-angle locking member 67 and four inclined shore bars respectively
61 and vertical frame 62 be connected, with fixed landing gear, gather after can so realizing undercarriage multiple spot stress
It is burnt to be supported in a bit, vertical active force can be converged into a bit, multi-angle stress switchs to a little support,
Uniform force degree is improved, and simplifies the work safeguarded and changed.
Further, shown in Figure 5, the other end of each inclined shore bar 61 passes through one
Flexible elbow 71 connects support chassis 70.The upper surface of support chassis 70 has a bottom from chassis
The protuberance 72 that end face center outwardly convex is formed, the protuberance has jack, for flexible elbow 71
Connection end insertion connection, the other end and the interface phase on inclined shore bar of the flexible elbow 71
After grafting, locked by keeper.
By using the support chassis 70 of flexible elbow connection undercarriage, relative complex out-of-flatness is adapted to
The landing problem on ground, the requirement that aircraft lands to ground is effectively improved, utilizes flexible material
The cooperation of feature and disc type footing, allow aircraft in relative complex rubble, miriness, marsh, rice
The flooring-safes such as field, dirt road land.
Shown in Figure 6, specifically, in the present invention, the limit installation plate 80 is metallic plate, its
The joint face being connected with power arm be provided with the first convex tendon 81, the second convex tendon 82, be placed in the first convex tendon 81,
The 3rd convex tendon 83 between second convex tendon 82, respectively a branch corresponding with English truss formula power arm 20
Strut 21 is connected to a fixed, and the plate 80 and the joint face of rotor power system 30 of being mounted is flat
Face, connected by keeper, the limit installation plate 80 is provided with heat emission hole 84, is easy to rotor power system
The reduction box that the metal material of system 30 makes is radiated.
English truss formula power arm 20 and the bottom of rotor power system are connected by using plate 80 is mounted
Face, so as to while utility English truss formula power arm 20 so that rotor power system 30 with
The connection of power arm is more stable, the installation accuracy and angle of rotor is ensure that, so as to be able to ensure nobody
The flight efficiency of machine is in preferable state.
Shown in Figure 7, the English truss formula power arm 20 passes through a pulling force locking fixture 90
And two rotatable positioning members 92 are connected with fuselage.Specifically, described pulling force locking fixture 90
And two rotatable positioning members 92 are connected with tripod 91, wherein, pulling force locking fixture 90 with
Tripod 91 tenses connection, the i.e. respective end of pulling force locking fixture 90 and the respective end of tripod 91
Connection is tensed, by respective end of the briquetting of pulling force locking fixture 90 after handle pressure with tripod 91
Extrude and realize and push down locking, rotatable positioning member 92 welds with tripod, tripod 91 and English truss
Formula power arm 20 welds, due to structure as use, ease of assembly and dismounting, and convenience in transport, and
Stable connection, position location is accurate, will not rock.
Shown in Figure 7, the English truss formula power arm includes what three three-legged structures linked together
Support bar, three support bars mutually support connection, and the three of the side being connected with fuselage by tripod
The area at angle is more than the triangle area that is connected with rotor power system of the other end, i.e. three support bars are from fuselage
Lateral rotor dynamical system side is to reduce structure to the centroclinal convergent manner structure of truss, i.e. English truss.
It should be noted that in the present invention, the metal of described use can be that steel, aluminium or aluminium close
Golden material makes, specific unlimited.
Unmanned plane of the present invention, due to using metal material fuselage and English truss formula power arm, described three
Angle truss-like power arm connects rotor power system, the installation of adjacent two groups of rotors by the way that plate is mounted
Position for fuselage in setting one on the other, the fuselage include shell and it is openable on
Lid, the shell is interior to be provided with support frame, and the underbelly connects undercarriage so that and fuselage is rigidly strong,
And can be overhauled and be safeguarded by upper lid opening, and English truss formula power arm is due to using triangular shape gold
The welding structure of category, stabilized structure, improve the stability of unmanned plane, the peace of adjacent two groups of rotors
Holding position is in set one on the other for fuselage so that unmanned plane structure in the case of more rotors
It is compact, the problem of solving more rotors space-consuming be big at grade, and unmanned plane body is big, so as to
Flight efficiency is improved on the basis of type is reduced.
Described above is only the preferred embodiment of the present invention, it is noted that for the general of the art
For logical technical staff, under the premise without departing from the principles of the invention, some improvement and profit can also be made
Decorations, these improvements and modifications should be regarded as protection scope of the present invention.
Claims (6)
1. a kind of unmanned plane, it is characterised in that fuselage and triangle including multigroup rotor, metal material
Truss-like power arm, the English truss formula power arm connect rotor power system by the way that plate is mounted,
The installation site of two groups of adjacent rotors is in set one on the other for fuselage, the fuselage bag
Shell and openable upper lid are included, is provided with support frame in the shell, the underbelly connects
Fall frame.
2. unmanned plane according to claim 1, it is characterised in that the English truss formula power arm
It is connected by a pulling force locking fixture and two rotatable positioning members with fuselage.
3. unmanned plane according to claim 1 or claim 2, it is characterised in that the English truss formula is moved
The arm of force includes three support bars, and three support bars mutually support connection by tripod.
4. unmanned plane according to claim 3, it is characterised in that the rotor power system includes
Reduction box, the reduction box is interior to be provided with train of reduction gears, and with upper air inlet, side air-out mouth.
5. unmanned plane according to claim 4, it is characterised in that the undercarriage includes multiple perpendicular
To frame, each vertical frame includes three vertical supporting bars, and three vertical supporting bars press triangular shape
Truss combination is linked together, and the top of three vertical supporting bars is connected by a connecting plate and fuselage
Connect, after the bottom convergence of three vertical supporting bars by multi-angle locking member and inclined shore bar and
Horizontal brace rod is connected.
6. unmanned plane according to claim 5, it is characterised in that the inclined shore bar it is another
End connects support chassis by a flexible elbow.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610355314.2A CN107434039A (en) | 2016-05-25 | 2016-05-25 | A kind of unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610355314.2A CN107434039A (en) | 2016-05-25 | 2016-05-25 | A kind of unmanned plane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107434039A true CN107434039A (en) | 2017-12-05 |
Family
ID=60454168
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610355314.2A Pending CN107434039A (en) | 2016-05-25 | 2016-05-25 | A kind of unmanned plane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107434039A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2024142196A1 (en) * | 2022-12-27 | 2024-07-04 | 株式会社クボタ | Flying apparatus |
| WO2024142197A1 (en) * | 2022-12-27 | 2024-07-04 | 株式会社クボタ | Flying apparatus |
| WO2024142206A1 (en) * | 2022-12-27 | 2024-07-04 | 株式会社クボタ | Flying device |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104002964A (en) * | 2014-05-30 | 2014-08-27 | 深圳一电科技有限公司 | Multi-rotor unmanned aerial vehicle |
| CN104627366A (en) * | 2015-02-10 | 2015-05-20 | 曹兵 | Oil drive variable pitch quadrotor type multifunctional fire-fighting unmanned aerial vehicle |
| CN204688411U (en) * | 2015-06-01 | 2015-10-07 | 金陵科技学院 | A kind of bird transport unmanned plane |
| US20150321755A1 (en) * | 2014-04-28 | 2015-11-12 | Arch Aerial, Llc | Collapsible multi-rotor uav |
| CN205044951U (en) * | 2015-10-22 | 2016-02-24 | 深圳市科卫泰实业发展有限公司 | Folding many rotor unmanned aerial vehicle of horn |
| CN205059987U (en) * | 2015-09-06 | 2016-03-02 | 深圳市道通智能航空技术有限公司 | Casing and aircraft |
| CN105398570A (en) * | 2015-11-26 | 2016-03-16 | 北京浩恒征途航空科技有限公司 | Oil-operated multi- rotor aerocraft |
| CN105438458A (en) * | 2015-12-04 | 2016-03-30 | 上海交通大学 | Double-layer and eight-rotor-wing aircraft |
| CN205770160U (en) * | 2016-05-25 | 2016-12-07 | 天津宏宇天翔科技有限公司 | A kind of unmanned plane |
-
2016
- 2016-05-25 CN CN201610355314.2A patent/CN107434039A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20150321755A1 (en) * | 2014-04-28 | 2015-11-12 | Arch Aerial, Llc | Collapsible multi-rotor uav |
| CN104002964A (en) * | 2014-05-30 | 2014-08-27 | 深圳一电科技有限公司 | Multi-rotor unmanned aerial vehicle |
| CN104627366A (en) * | 2015-02-10 | 2015-05-20 | 曹兵 | Oil drive variable pitch quadrotor type multifunctional fire-fighting unmanned aerial vehicle |
| CN204688411U (en) * | 2015-06-01 | 2015-10-07 | 金陵科技学院 | A kind of bird transport unmanned plane |
| CN205059987U (en) * | 2015-09-06 | 2016-03-02 | 深圳市道通智能航空技术有限公司 | Casing and aircraft |
| CN205044951U (en) * | 2015-10-22 | 2016-02-24 | 深圳市科卫泰实业发展有限公司 | Folding many rotor unmanned aerial vehicle of horn |
| CN105398570A (en) * | 2015-11-26 | 2016-03-16 | 北京浩恒征途航空科技有限公司 | Oil-operated multi- rotor aerocraft |
| CN105438458A (en) * | 2015-12-04 | 2016-03-30 | 上海交通大学 | Double-layer and eight-rotor-wing aircraft |
| CN205770160U (en) * | 2016-05-25 | 2016-12-07 | 天津宏宇天翔科技有限公司 | A kind of unmanned plane |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2024142196A1 (en) * | 2022-12-27 | 2024-07-04 | 株式会社クボタ | Flying apparatus |
| WO2024142197A1 (en) * | 2022-12-27 | 2024-07-04 | 株式会社クボタ | Flying apparatus |
| WO2024142206A1 (en) * | 2022-12-27 | 2024-07-04 | 株式会社クボタ | Flying device |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107434039A (en) | A kind of unmanned plane | |
| CN203793629U (en) | Head cover structure for unmanned aerial vehicle | |
| CN205770160U (en) | A kind of unmanned plane | |
| CN202280266U (en) | Dismounting type wind-proof shed for full-automatic welding operation | |
| CN110242513A (en) | A kind of gear-box Airborne pollen replacement system and its replacing options | |
| CN209209056U (en) | Portable multifunctional unmanned plane landing platform | |
| CN206375436U (en) | A kind of lifting suspension bucket | |
| CN206914317U (en) | Quarry tipper accumulator cabinet | |
| CN109436063A (en) | A kind of damping rain-proof type engineering explosion transport device | |
| CN212173853U (en) | Can promote convertible baffle box | |
| CN209145339U (en) | A kind of double-layer detachable reinforcement shed | |
| CN214615556U (en) | Steel construction safety rope linkage | |
| CN204940533U (en) | Lifting folding type movable case room | |
| CN205336215U (en) | Multisection section trussed girder of dish formula spotlight ware rack | |
| CN208618867U (en) | A kind of hanging steel platform mounting structure based on tubular truss chord member | |
| CN206202898U (en) | Novel reactor extranal packing box | |
| CN207194213U (en) | The anti-acoustic shell of music | |
| CN203793589U (en) | Locating structure of top cover of four-axis agricultural aircraft | |
| CN208949959U (en) | A kind of U-shaped coal scuttle and wheel loader | |
| CN206181917U (en) | A space frame for urban afforestation | |
| CN218141346U (en) | Tool box structure | |
| CN212577881U (en) | A welding auxiliary fixtures for steel case roof beam | |
| CN203793596U (en) | Four-shaft agricultural aircraft top cover and body assembly | |
| CN217946245U (en) | Steel and aluminum alloy mixed structure shelter | |
| CN107187437A (en) | A kind of quarry tipper accumulator cabinet |
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 | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20171205 |