CN205770160U - A kind of unmanned plane - Google Patents
A kind of unmanned plane Download PDFInfo
- Publication number
- CN205770160U CN205770160U CN201620489962.2U CN201620489962U CN205770160U CN 205770160 U CN205770160 U CN 205770160U CN 201620489962 U CN201620489962 U CN 201620489962U CN 205770160 U CN205770160 U CN 205770160U
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- CN
- China
- Prior art keywords
- fuselage
- unmanned plane
- power arm
- rotor
- frame
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Abstract
This utility model relates to a kind of unmanned plane, including organizing rotor, the fuselage of metal material and English truss formula power arm more, described English truss formula power arm connects rotor power system by limit mounting plate, the installation site of two groups of adjacent rotors for fuselage in arranging one on the other, described fuselage includes shell and openable upper cover, being provided with bracing frame in described shell, described underbelly connects undercarriage.Unmanned plane stiff super of the present utility model, stability is good, and flight efficiency is high.
Description
Technical field
This utility model belongs to unmanned air vehicle technique field, is specifically related to a kind of novel unmanned plane.
Background technology
Unmanned plane has on military and civil area and is widely applied very much.Current most of many rotors are unmanned
Machine, fuselage poor rigidity, poor stability, power arm is installed built on the sand, and rotor installs inconvenience, therefore
A kind of ease of assembly and stable connection it is provided, and the strong unmanned plane of rigidity is necessary.
Utility model content
The purpose of this utility model is to solve above-mentioned technical problem, it is provided that a kind of employing all-metal construction
Unmanned plane.
For achieving the above object, this utility model adopts the following technical scheme that
A kind of unmanned plane, including organizing rotor, the fuselage of metal material and English truss formula power arm, institute more
State English truss formula power arm and connect rotor power system, two groups of adjacent rotors by limit mounting plate
Installation site for fuselage in arranging one on the other, described fuselage includes shell and can beat
The upper cover opened, is provided with bracing frame in described shell, described underbelly connects undercarriage.
Described English truss formula power arm passes through a pulling force locking fixture and two rotatable positioning members
It is connected with fuselage.
Described English truss formula power arm includes three support bars, and three described support bars are by tripod phase
Support and connect.
Described rotor power system includes reduction box, is provided with train of reduction gears, and has in described reduction box
Enterprising air port, side air-out mouth.
Described undercarriage includes that multiple vertical frame, each described vertical frame include three vertical supporting bars, three
Individual described vertical supporting bar links together by the combination of triangular shape truss, three described vertical supporting bars
Top is connected with fuselage by a plate, and the bottom of three described vertical supporting bars is passed through many after converging
Angle locking member is connected with inclined shore bar and horizontal brace rod.
The other end of described inclined shore bar connects support chassis by a flexible elbow.
This utility model unmanned plane, owing to using fuselage and English truss formula power arm, the institute of metal material
State English truss formula power arm and connect rotor power system, two groups of adjacent rotors by limit mounting plate
Installation site for fuselage in arranging one on the other, described fuselage includes shell and can beat
The upper cover opened, is provided with bracing frame in described shell, described underbelly connects undercarriage so that fuselage
Rigidity is strong, and can be opened by upper cover and overhaul and safeguard, and English truss formula power arm is owing to adopting
Use triangular shape Welding Structure, stabilized structure, improve the stability of unmanned plane, two groups of adjacent rotations
The installation site of the wing for fuselage in arranging one on the other so that unmanned plane is in the feelings of many rotors
Compact conformation under condition, solve many rotors take up room at grade greatly, unmanned plane body big
Problem, thus improve flight efficiency on the basis of reducing type.
Accompanying drawing explanation
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 connection enlarged diagram with rotor of unmanned plane；
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 the connection diagram of rotor power system and power arm；
Fig. 7 show the connection diagram of power arm and fuselage.
Detailed description of the invention
Below, in conjunction with example, substantive distinguishing features of the present utility model and advantage are further described, this
Utility model is including, but not limited to listed embodiment.
Seeing shown in Fig. 1-7, a kind of unmanned plane, including the fuselage 10 organizing rotor 40, metal material more
And the English truss formula power arm 20 of metal material, described English truss formula power arm passes through limit mounting plate
80 connect rotor power system 30 (can be found in shown in Fig. 6), the installation site of two groups of adjacent rotors
In arranging one on the other for fuselage.
Shown in Figure 2, described fuselage includes shell 12 and openable upper cover 11, described shell
Inside being provided with the battery case 50 of metal supporting frames 13 and multiple metal material, the connection of described underbelly is risen and fallen
Frame 60.
Wherein, described battery case 50 is connected by keeper with fuselage 10, at the bottom of the shell of fuselage 10
Portion and on cover and offer corresponding battery load hole 14, after battery is arranged in this battery load hole,
Upper end is covered by corresponding battery case, and battery case is connected by keeper with the bottom of fuselage upper cover and shell.
Being covered by battery by arranging battery case, i.e. can protect battery, the installation also making battery is more convenient,
This battery case uses metal material to make, the heat radiation that beneficially battery is the best, and protection
Property is strong.
Support frame as described above includes multiple main frame, and multiple described main frame hearts in the frame intersect and outboard end
Being respectively directed to different directions, described enclosure is divided into multiple region, and (supplying cell is arranged on this district
In territory), two sides of each described main frame connect a body side frame respectively；Each described side frame
One end of frame is connected with corresponding main frame, the other end is connected and shape with the inwall of described shell
Become three-legged structure, thus improve the support strength of bracing frame, improve the intensity of fuselage.
Wherein, described main frame is rectangular frame, and described body side frame is U-frame frame, described upper cover with
Support connects fixing by keeper, and described shell is polygonal body shape structure.
Shown in Figure 3, described rotor power system 3 includes reduction box 33, is provided with in described reduction box
Train of reduction gears 32, and there is enterprising air port, side air-out mouth 34, reduction box is by drive shaft 31, rotation
Wing folder 35 is connected with two rotors 40, and described reduction box 33 housing is made by metal material, passes through
Enterprising air port enters cold wind, internal train of reduction gears drive, force to be circulated, and hot blast goes out from side
Air port 34 is discharged, and effectively dispels the heat reduction box.
Shown in Figure 4, described undercarriage 60 includes multiple vertical frame 62, each described vertical frame bag
Include three vertical supporting bars and (include that first vertical supporting bar the 63, second vertical supporting bar the 64, the 3rd erects
To support bar 65), three described vertical supporting bars link together by the combination of triangular shape truss, three institutes
State the top of vertical supporting bar to be connected with the bottom of fuselage 10 by a plate 66, three described vertically
The bottom of support bar (is respectively provided with connecting hole on three directions by multi-angle locking member 67, uses after converging
In being connected with three vertical supporting bars, inclined shore bar 61 and horizontal brace rod 68) prop up with inclination
Strut 61 and horizontal brace rod 68 are connected, and horizontal brace rod 68 is by cross connecting piece 69 even
Be connected together the criss-cross structure of formation, respectively by multi-angle locking member 67 and four inclined shore bars
61 and vertical frame 62 be connected, with fixed landing gear, poly-after so can realizing undercarriage multiple spot stress
Jiao supports in a bit, can converge into a bit by vertical active force, and multi-angle stress transfers some support to,
Improve uniform force degree, and simplify the work safeguarded and change.
Further, shown in Figure 5, the other end of each described inclined shore bar 61 passes through one
Flexible elbow 71 connects support chassis 70.Described support chassis 70 upper surface has the end from chassis
The protuberance 72 that end face center outwardly convex is formed, described protuberance has jack, for flexible elbow 71
Connection end insert and connect, the described flexible other end of elbow 71 and the interface phase on inclined shore bar
After grafting, locked by keeper.
By utilizing flexible elbow to connect the support chassis 70 of undercarriage, it is adapted to relative complex out-of-flatness
The landing problem on ground, effectively improves the aircraft landing requirement to ground, utilizes flexible material
Feature and the cooperation of disc type footing, make the aircraft can be relative complex rubble, muddy, marsh, rice
The flooring-safe such as field, dirt road lands.
Shown in Figure 6, concrete, in this utility model, described limit mounting plate 80 is metallic plate,
Its joint face being connected with power arm is provided with first convex tendon the 81, second convex tendon 82, is placed in the first convex tendon
81, the 3rd convex tendon 83 between the second convex tendon 82, respectively with English truss formula power arm 20 corresponding
Individual support bar 21 is connected to a fixed, described limit mounting plate 80 and the joint face of rotor power system 30
For plane, being connected by keeper, this limit mounting plate 80 is provided with louvre 84, it is simple to rotor moves
The reduction box that the metal material of Force system 30 makes dispels the heat.
By using limit mounting plate 80 to connect the end of English truss formula power arm 20 and rotor power system
Face, thus while utility English truss formula power arm 20 so that rotor power system 30 with
The connection of power arm is more stable, it is ensured that the installation accuracy of rotor and angle, thus is ensured unmanned
The flight efficiency of machine is in preferable state.
Shown in Figure 7, described English truss formula power arm 20 is by a pulling force locking fixture 90
And two rotatable positioning members 92 are connected with fuselage.Concrete, 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 tension connects, i.e. the respective end of pulling force locking fixture 90 and the respective end of tripod 91
Tension connects, by the briquetting of pulling force locking fixture 90 after handle presses with the respective end of tripod 91
Extruding and realize pushing down locking, rotatable positioning member 92 welds with tripod, tripod 91 and English truss
Formula power arm 20 welds, owing to using such structure, and ease of assembly and dismounting, convenient transport, and
Stable connection, position location is accurate, will not rock.
Shown in Figure 7, described English truss formula power arm includes what three three-legged structures linked together
Support bar, three described support bars support connection, and the three of the side being connected with fuselage mutually by tripod
The triangle area that the area at angle is connected with rotor power system more than the other end, i.e. three support bars are from fuselage
Lateral rotor dynamical system side is that i.e. English truss reduces structure to truss centroclinal convergent manner structure.
It should be noted that in this utility model, the metal of described employing can be steel, aluminium or
Aluminum alloy materials makes, and does not limits.
This utility model unmanned plane, owing to using fuselage and English truss formula power arm, the institute of metal material
State English truss formula power arm and connect rotor power system by limit mounting plate, two groups of adjacent rotors
Installation site is in arranging one on the other for fuselage, and described fuselage includes shell and openable
Upper cover, is provided with bracing frame in described shell, described underbelly connects undercarriage so that fuselage rigidity is strong,
And can be opened by upper cover and overhaul and safeguard, and English truss formula power arm is owing to using triangular shape gold
The Welding Structure belonged to, stabilized structure, improve the stability of unmanned plane, the peace of two groups of adjacent rotors
Holding position for fuselage in arranging one on the other so that unmanned plane is structure in the case of many rotors
Compact, solve many rotors and take up room greatly at grade, the problem that unmanned plane body is big, thus
Flight efficiency is improved on the basis of reducing type.
The above is only preferred implementation of the present utility model, it is noted that for the art
Those of ordinary skill for, on the premise of without departing from this utility model principle, it is also possible to make some
Improvements and modifications, these improvements and modifications should be regarded as protection domain of the present utility model.
Claims (6)
1. a unmanned plane, it is characterised in that include organizing rotor, the fuselage of metal material and triangle more
Truss-like power arm, described English truss formula power arm connects rotor power system by limit mounting plate,
The installation site of two groups of adjacent rotors for fuselage in arranging one on the other, described fuselage bag
Including shell and openable upper cover, be provided with bracing frame in described shell, described underbelly connects
Fall frame.
Unmanned plane the most according to claim 1, it is characterised in that described English truss formula power arm
It is connected with fuselage by a pulling force locking fixture and two rotatable positioning members.
Unmanned plane the most according to claim 1 or claim 2, it is characterised in that described English truss formula is moved
The arm of force includes that three support bars, three described support bars support connection mutually by tripod.
Unmanned plane the most according to claim 3, it is characterised in that described rotor power system includes
Reduction box, is provided with train of reduction gears, and has enterprising air port, side air-out mouth in described reduction box.
Unmanned plane the most according to claim 4, it is characterised in that described undercarriage includes multiple perpendicular
To frame, each described vertical frame includes that triangular shape pressed by three vertical supporting bars, three described vertical supporting bars
Truss combination links together, and the top of three described vertical supporting bars is by a plate with fuselage even
Connect, the bottom of three described vertical supporting bars converge after by multi-angle locking member and inclined shore bar and
Horizontal brace rod is connected.
Unmanned plane the most according to claim 5, it is characterised in that another of described inclined shore bar
Hold and connect support chassis by a flexible elbow.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620489962.2U CN205770160U (en) | 2016-05-25 | 2016-05-25 | A kind of unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620489962.2U CN205770160U (en) | 2016-05-25 | 2016-05-25 | A kind of unmanned plane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205770160U true CN205770160U (en) | 2016-12-07 |
Family
ID=58109936
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620489962.2U Expired - Fee Related CN205770160U (en) | 2016-05-25 | 2016-05-25 | A kind of unmanned plane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205770160U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107021204A (en) * | 2017-05-24 | 2017-08-08 | 东北大学 | A kind of multi-rotor unmanned aerial vehicle frame based on contignation |
| CN107434039A (en) * | 2016-05-25 | 2017-12-05 | 天津宏宇天翔科技有限公司 | A kind of unmanned plane |
-
2016
- 2016-05-25 CN CN201620489962.2U patent/CN205770160U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107434039A (en) * | 2016-05-25 | 2017-12-05 | 天津宏宇天翔科技有限公司 | A kind of unmanned plane |
| CN107021204A (en) * | 2017-05-24 | 2017-08-08 | 东北大学 | A kind of multi-rotor unmanned aerial vehicle frame based on contignation |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 300270 Tianjin Binhai New Area, Dagang seaside street, red flag Road south side of bungalow 7. Patentee after: Tianjin City tianxiang Hongyu Technology Co. Ltd. Address before: 300270 Tianjin Binhai New Area, Dagang seaside street, red flag Road south side of bungalow 7. Patentee before: TIANJIN HONGYU TIANXIANG TECHNOLOGY CO., LTD. |
|
| CP01 | Change in the name or title of a patent holder | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20161207 Termination date: 20210525 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |