CN106081092A - A kind of many rotor wing unmanned aerial vehicles - Google Patents
A kind of many rotor wing unmanned aerial vehicles Download PDFInfo
- Publication number
- CN106081092A CN106081092A CN201610728837.7A CN201610728837A CN106081092A CN 106081092 A CN106081092 A CN 106081092A CN 201610728837 A CN201610728837 A CN 201610728837A CN 106081092 A CN106081092 A CN 106081092A
- Authority
- CN
- China
- Prior art keywords
- support arm
- rotor
- circular hole
- unmanned aerial
- wing unmanned
- 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
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Classifications
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- 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
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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
- B64C1/30—Parts of fuselage relatively movable to reduce overall dimensions of aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/12—Rotor drives
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
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- 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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2101/00—UAVs specially adapted for particular uses or applications
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- 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 provides a kind of many rotor wing unmanned aerial vehicles, and including fuselage, rotor, rotor support arm and the dynamical system providing power for rotor, fuselage is connected with rotor support arm, and rotor support arm is connected with rotor, and described fuselage includes upper shell and lower house, and lower house is bowl shaped structure；Described rotor support arm includes support arm base and support arm, described support arm base is fixed on the opening part of lower house, support arm base is provided with the fixed plate being perpendicular to support arm base, and described fixed plate is provided with the first circular hole being positioned at fixed plate top and the second circle being positioned at fixed plate bottom determines hole.The invention has the beneficial effects as follows that the space that unmanned plane takies after folding is less, easily portable.
Description
Technical field
The present invention relates to unmanned air vehicle technique field, particularly relate to a kind of folding unmanned plane.
Background technology
UAV is called for short " unmanned plane ", and english abbreviation is " UAV ", utilizes radio robot and provides for oneself
The most manned aircraft that presetting apparatus is handled, unmanned plane, by application, can be divided into military and civilian, and civilian aspect is unmanned
Machine+sector application, is real just the needing of unmanned plane；At present taking photo by plane, agricultural, plant protection, auto heterodyne, express transportation, disaster relief, sight
Examine wild animal, monitoring infectious disease, mapping, news report, electric inspection process, the disaster relief, movies-making, manufacture romance etc. field
Application, has greatly expanded the purposes of unmanned plane itself, and developed country is also in actively extension sector application and development unmanned plane skill
Art.
Classifying by flying platform configuration, unmanned plane can be divided into fixed-wing unmanned plane, rotor wing unmanned aerial vehicle, unmanned airship, the umbrella wing
Unmanned plane, flapping wing unmanned plane etc., wherein rotor wing unmanned aerial vehicle is because of its simple in construction, low cost, good stability, just has relatively broad
Application space.
In prior art, the unmanned plane of some rotors often has multi-disc rotor, and therefore, every rotor is required to corresponding one
Fixed separate space, in order to form lift for it and create conditions.In other words, in existing unmanned plane scheme, rotor occupies unmanned
The sectional area of the machine overwhelming majority, returns carrying of unmanned plane and brings inconvenience.
At present, existing unmanned plane generally use collapsible or detachable rotor to reduce the parking space that unmanned plane takies,
Wherein dismounting rotor relates to the connectivity problem of rotor medium power system, easily causes the unstability that dynamical system connects, folding
It is unreasonable that folded unmanned plane there is also folding angles, it is impossible to what effective minimizing unmanned plane was deposited takes up room.
Summary of the invention
It is an object of the invention to provide a kind of rotor support arm folding unmanned plane, to improve the portability of unmanned plane.
The technical scheme is that a kind of many rotor wing unmanned aerial vehicles, including fuselage, rotor, rotor support arm and carry for rotor
For the dynamical system of power, fuselage is connected with rotor support arm, and rotor support arm is connected with rotor, described fuselage include upper shell with under
Housing, lower house is bowl shaped structure；Described rotor support arm includes that support arm base and support arm, described support arm base are fixed on lower house
Opening part, support arm base is provided with the fixed plate being perpendicular to support arm base, and described fixed plate is provided with and is positioned at fixed plate top
The first circular hole and be positioned at fixed plate bottom second circle determine hole.First circular hole and the second circular hole form at 2 and fix, and improve
The stability that support arm is fixing, the first circular hole releases fixing simultaneously, and support arm can rotate down folding with the second circular hole for the center of circle.
The many rotor wing unmanned aerial vehicles of one according to claim 1, it is characterised in that: outside described second circular hole to lower house
The tangent line on surface and the angle of horizontal direction are 110 °-130 °, the tangent line of the most described second circular hole to lower house outer surface
Being 120 ° with the angle of horizontal direction, the fuselage of bowl-type makes many rotor wing unmanned aerial vehicles rotor support arm more to gather, and saves further
Space.
Described support arm is provided with the first fixing hole matched with the first circular hole, the second circle matched with the second circular hole
Hole, described first circular hole and the first fixing hole be connected by alignment pin, and the second circular hole and the second fixing hole are connected by bearing pin.
The axially location of described alignment pin uses snap ring to fix, and the axially location of bearing pin is adopted and is tightened by bolts.The folding of unmanned plane be with
Second circular hole and the second fixing hole are the rotation in the center of circle, thus be accordingly used in and fix the alignment pin of the first circular hole and the first fixing hole and only need
Playing the limit function to support arm, owing to it releases fixing frequency, snap ring is fixing is more convenient for fixing and releases solid
Fixed, for fixing the second circular hole and the bearing pin of the second fixing hole, then need to have concurrently the function of limit function and rotating shaft, and bearing pin leads to
Often need not to be released completely fixing, therefore, bolt locking is conducive to strengthening fixing stability.
The top of described first fixing hole is provided with the opening that spacing is closed, opening on the first fixing hole with alignment pin diameter compatible
Mouth can make alignment pin only loosen in the case of without being fully drawn out alignment pin, it is achieved the releasing between support arm and base
Fixing.
The dynamical system of described many rotor wing unmanned aerial vehicles includes, including for driving the mechanical, electrical mediation of the brushless electric of rotor to fly
Control mainboard, brushless motor and electricity are transposed inside support arm, and brushless motor is adjusted with electricity and is connected by wire, and electricity is adjusted and passed through wire
It is connected with the control mainboard that flies being positioned at fuselage interior.
Being divided into upper and lower two cabins by dividing plate inside described fuselage lower house, its upperdeck indoor are provided with and fly to control mainboard peace
Dress position, its lower floor cabin is provided with supply unit installation position.
The midpoint of the first circular hole and the second circular hole is positioned at same level with flying control mainboard installation position.First circular hole and second
The midpoint of circular hole is provided with electric lead passage, is more easily attached with the control mainboard that flies being positioned at same level, improves even
The stability connect.
The present invention has the advantage that with good effect: owing to using technique scheme, unmanned plane takies after folding
Space is less, easily portable.
Accompanying drawing explanation
Fig. 1 is the structural representation of the present invention
Fig. 2 is the connection diagram of rotor support arm and fuselage
Fig. 3 is the structural representation of rotor support arm
Fig. 4 is fuselage interior structural representation
In figure:
1, upper shell 2, lower house 3, rotor support arm
4, rotor 5, electricity tune 6, brushless motor
7, cabin, upper strata 8, lower floor cabin 9, fly control mainboard installation position
31, alignment pin 32, bearing pin 33, fixed plate
Detailed description of the invention
The many rotor wing unmanned aerial vehicles of one as Figure 1-4, including fuselage, rotor 4, rotor support arm 3 and provide dynamic for rotor 4
The dynamical system of power, fuselage is connected with rotor support arm 3, and rotor support arm 3 is connected with rotor 4, described fuselage include upper shell 1 and under
Housing 2, lower house 2 is bowl shaped structure；Described rotor support arm 3 includes support arm base and support arm, under described support arm base is fixed on
The opening part of housing, support arm base is provided with the fixed plate 33 being perpendicular to support arm base, described fixed plate be provided be positioned at fixing
First circular hole on plate top and the second circle being positioned at fixed plate bottom determine hole.
Described second circular hole is 110 °-130 ° to the tangent line of lower house outer surface and the angle of horizontal direction, preferred institute
Stating the second circular hole to the tangent line of lower house outer surface and the angle of horizontal direction is 120 °.
Described support arm is provided with the first fixing hole matched with the first circular hole, the second circle matched with the second circular hole
Hole, described first circular hole and the first fixing hole are connected by alignment pin 31, and the second circular hole and the second fixing hole are by bearing pin 32
Connect.
The axially location of described alignment pin 31 uses snap ring to fix, and the axially location of bearing pin 32 is adopted and is tightened by bolts.
The top of described first fixing hole is provided with the opening that spacing is closed with alignment pin 31 diameter compatible, loosens on alignment pin 31
Snap ring, support arm is separated with alignment pin 31 by opening, and rotates with bearing pin 32 for the center of circle, it is achieved folding.
The dynamical system of described many rotor wing unmanned aerial vehicles includes, adjusts 5 and including the brushless motor 6 for driving rotor, electricity
Flying to control mainboard 9, brushless motor 6 and electricity adjust 5 to be positioned at inside support arm, and brushless motor 6 adjusts 5 to be connected by wire with electricity, and electricity adjusts 5
It is connected with the control mainboard 9 that flies being positioned at fuselage interior by wire.
Described fuselage lower house 2 is internal is divided into upper and lower two cabins by dividing plate, is provided with and flies to control mainboard in its cabin, upper strata 7
Installation position 9, its lower floor cabin 8 is provided with supply unit installation position.
The midpoint of the first circular hole and the second circular hole is positioned at same level with flying control mainboard 9 installation position.First circular hole and
The midpoint of two circular holes is provided with electric lead passage, is more easily attached with the control mainboard 9 that flies being positioned at same level, improves
The stability connected.
Above one embodiment of the present of invention is described in detail, but described content has been only the preferable enforcement of the present invention
Example, it is impossible to be considered the practical range for limiting the present invention.All impartial changes made according to the present patent application scope and improvement
Deng, within all should still belonging to the patent covering scope of the present invention.
Claims (9)
1. a rotor wing unmanned aerial vehicle more than, including fuselage, rotor, rotor support arm and the dynamical system providing power for rotor, fuselage
Being connected with rotor support arm, rotor support arm is connected with rotor, it is characterised in that: described fuselage includes upper shell and lower house, lower casing
Body is bowl shaped structure；Described rotor support arm includes that support arm base and support arm, described support arm base are fixed on the opening part of lower house,
Support arm base is provided with the fixed plate being perpendicular to support arm base, and described fixed plate is provided with the first circular hole being positioned at fixed plate top
Hole is determined with the second circle being positioned at fixed plate bottom.
The many rotor wing unmanned aerial vehicles of one the most according to claim 1, it is characterised in that: described second circular hole is to lower house appearance
The tangent line in face and the angle of horizontal direction are 110 °-130 °.
The many rotor wing unmanned aerial vehicles of one the most according to claim 2, it is characterised in that: described second circular hole is to lower house appearance
The tangent line in face and the angle of horizontal direction are 120 °.
The many rotor wing unmanned aerial vehicles of one the most according to claim 1, it is characterised in that: described support arm is provided with and the first circular hole
The first fixing hole matched, the second circular hole matched with the second circular hole, described first circular hole and the first fixing hole are by fixed
Position pin is connected, and the second circular hole and the second fixing hole are connected by bearing pin.
The many rotor wing unmanned aerial vehicles of one the most according to claim 4, it is characterised in that: described alignment pin axially position employing
Snap ring is fixed, and the axially location of bearing pin is adopted and is tightened by bolts.
6. according to any one the many rotor wing unmanned aerial vehicle of described one in claim 4 or 5, it is characterised in that: described first is solid
The top determining hole is provided with the opening that spacing is closed with alignment pin diameter compatible.
The many rotor wing unmanned aerial vehicles of one the most according to claim 1, it is characterised in that: the dynamical system of described many rotor wing unmanned aerial vehicles
System includes, including for driving the mechanical, electrical mediation of the brushless electric of rotor to fly control mainboard, brushless motor and electricity are transposed in support arm
Portion, brushless motor is connected by wire with electricity tune, and electricity is adjusted and is connected with the control mainboard that flies being positioned at fuselage interior by wire.
The many rotor wing unmanned aerial vehicles of one the most according to claim 7, it is characterised in that: by dividing plate inside described fuselage lower house
Being divided into upper and lower two cabins, its upperdeck indoor are provided with and fly to control mainboard installation position, and its lower floor cabin is provided with supply unit peace
Dress position.
The many rotor wing unmanned aerial vehicles of one the most according to claim 8, it is characterised in that: the first circular hole and the midpoint of the second circular hole
It is positioned at same level with flying control mainboard installation position.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610728837.7A CN106081092A (en) | 2016-08-26 | 2016-08-26 | A kind of many rotor wing unmanned aerial vehicles |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610728837.7A CN106081092A (en) | 2016-08-26 | 2016-08-26 | A kind of many rotor wing unmanned aerial vehicles |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106081092A true CN106081092A (en) | 2016-11-09 |
Family
ID=57225369
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610728837.7A Pending CN106081092A (en) | 2016-08-26 | 2016-08-26 | A kind of many rotor wing unmanned aerial vehicles |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106081092A (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2909972B1 (en) * | 2006-12-18 | 2009-10-23 | Novadem Sarl | VERTICAL TAKE-OFF AIRCRAFT |
| CN104309801A (en) * | 2014-09-26 | 2015-01-28 | 金陵科技学院 | Rotary wing type unmanned plane with spherical solar collector at central section and landing seat thereof |
| CN204979231U (en) * | 2015-09-21 | 2016-01-20 | 北京浩恒征途航空科技有限公司 | Many rotors unmanned vehicles and folding self -lock device thereof |
| CN205010490U (en) * | 2015-08-27 | 2016-02-03 | 零度智控（北京）智能科技有限公司 | Device for connecting unmanned aerial vehicle horn and fuselage |
| CN205022857U (en) * | 2015-09-30 | 2016-02-10 | 湖南云顶智能科技有限公司 | Unmanned aerial vehicle horn folding mechanism and unmanned aerial vehicle |
| CN205952309U (en) * | 2016-08-26 | 2017-02-15 | 威海星煜无人机科技有限公司 | Unmanned aerial vehicle with multiple rotor wings |
-
2016
- 2016-08-26 CN CN201610728837.7A patent/CN106081092A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2909972B1 (en) * | 2006-12-18 | 2009-10-23 | Novadem Sarl | VERTICAL TAKE-OFF AIRCRAFT |
| CN104309801A (en) * | 2014-09-26 | 2015-01-28 | 金陵科技学院 | Rotary wing type unmanned plane with spherical solar collector at central section and landing seat thereof |
| CN205010490U (en) * | 2015-08-27 | 2016-02-03 | 零度智控（北京）智能科技有限公司 | Device for connecting unmanned aerial vehicle horn and fuselage |
| CN204979231U (en) * | 2015-09-21 | 2016-01-20 | 北京浩恒征途航空科技有限公司 | Many rotors unmanned vehicles and folding self -lock device thereof |
| CN205022857U (en) * | 2015-09-30 | 2016-02-10 | 湖南云顶智能科技有限公司 | Unmanned aerial vehicle horn folding mechanism and unmanned aerial vehicle |
| CN205952309U (en) * | 2016-08-26 | 2017-02-15 | 威海星煜无人机科技有限公司 | Unmanned aerial vehicle with multiple rotor wings |
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| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into 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: 20161109 |