CN204507257U - A kind of fuel power multi-rotor aerocraft - Google Patents
A kind of fuel power multi-rotor aerocraft Download PDFInfo
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- CN204507257U CN204507257U CN201520042448.XU CN201520042448U CN204507257U CN 204507257 U CN204507257 U CN 204507257U CN 201520042448 U CN201520042448 U CN 201520042448U CN 204507257 U CN204507257 U CN 204507257U
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Abstract
The utility model discloses a kind of fuel power multi-rotor aerocraft, comprise the mainframe of ground flight controller and aircraft and be fixed on the under-chassis of mainframe lower end, the balance bracket of horizontal positioned is fixed with in the upper end of mainframe, balance bracket is provided with the symmetrical rotor support installed of many groups, one end of rotor support is fixed on the center of balance bracket, the other end is provided with rotor, also comprise the battery pack be fixed on mainframe, described battery pack is connected with the motor of rotor respectively by wire; Mainframe is provided with at least one fuel engines, mainframe is also provided with fuel tank, fuel engines is provided with main screw, also comprise the antenna be arranged on mainframe.Adopt the technical solution of the utility model, structure is simple, reliable and stable, can realize various flight attitude, adopts fuel power, and flight cruise duration and load carrying ability are greatly improved, and application is extensive.
Description
Technical field
The utility model belongs to aircraft, is specifically related to a kind of fuel power multi-rotor aerocraft.
Background technology
Current aircraft is mostly remote control electric, it provides flight lift by multiple rotor, flight balance and change of flight attitude is realized by the rotating speed changing rotor, because various attitude flare maneuver realizes by the change of each motor speed purely, therefore it possesses the quick action and simple physical construction that other aircraft cannot possess, but there is many defects in electronic many rotors, because electronic many rotors are by battery power, cruise duration and load carrying ability are under many restrictions, be difficult to control flight attitude, poor stability, its field of application is also restricted.
Summary of the invention
The purpose of this utility model is to provide a kind of fuel power multi-rotor aerocraft, this Flight Vehicle Structure is simple, cost is low, during aircraft flight, realization balance and lift separate, reliable and stable, various flight attitude can be realized, adopt fuel power, flight cruise duration and load carrying ability are greatly improved, and application is extensive.
For achieving the above object, a kind of fuel power multi-rotor aerocraft of the present utility model, comprise the mainframe of ground flight controller and aircraft and be fixed on the under-chassis of mainframe lower end, the balance bracket of horizontal positioned is fixed with in the upper end of mainframe, balance bracket is evenly provided with the symmetrical rotor support installed of many groups centered by the center of circle, one end of each rotor support is fixed on the center of balance bracket, the other end is fixed with the rotor for aircraft balance and pose adjustment, the screw propeller blade face of described rotor and balance bracket are all horizontal, described rotor is by its speed of its electric machine control, also comprise the battery pack be fixed on mainframe, described battery pack is connected with the motor of rotor respectively by wire, mainframe is provided with at least one fuel engines, mainframe is also provided with fuel tank, fuel engines is provided with by its dynamical axis the main screw providing flight lift, and the central axis of described main screw is in horizontal surface and with the center of circle of balance bracket on same line, also comprise the antenna be arranged on mainframe.
After have employed technique scheme, send instruction by flight controller to antenna, main screw can be driven to provide lift, drive rotor to reach equilibrium activity, thus achieve various flight attitude.
Preferably, described mainframe is provided with a fuel engines, one group of symmetrical rotor support installed is arranged with the sidespin wing of offsetting fuel engines torsion respectively wherein, the screw propeller blade face of the described sidespin wing and the screw propeller blade face of rotor perpendicular, the described sidespin wing is by its speed of its electric machine control, and battery pack is connected by the motor of wire with the sidespin wing.This group sidespin wing can balance the torsion that fuel engines produces.
Preferably, described mainframe is provided with two fuel enginess.These two fuel enginess coaxially install up and down or horizontal symmetrical is installed, and its screw propeller rotates in the opposite direction, and cancel each other torsion, does not now need to arrange the sidespin wing.
Preferably, described balance bracket is enclosed shape.
Preferably, the shape of described balance bracket is annular arrangement or rectangle.
Preferably, described aerial band GPS positioning function.
In technique scheme, the utility model has following beneficial effect: the first, and this Flight Vehicle Structure is simple, and cost is low; The second, this aircraft is symmetrically installed with many group rotors and one group of sidespin wing, and during aircraft flight, realization balance and lift separate, and can realize various flight attitude, reliable and stable; 3rd, adopt fuel oil to be the defect that many rotors of major impetus well solve electronic many rotors, spark ignition engine provides prevailing lift, and therefore fly cruise duration and load carrying ability are greatly improved, and application also will be more extensive.
Accompanying drawing explanation
Fig. 1 is the structural representation of a kind of fuel power multi-rotor aerocraft of the utility model.
Detailed description of the invention
Below in conjunction with drawings and Examples, a kind of fuel power multi-rotor aerocraft of the utility model is described in further detail.The accompanying drawing forming the application is used to provide further understanding of the present utility model, and schematic description and description of the present utility model, for explaining the utility model, is not formed improper restriction of the present utility model.
Embodiment one
As seen from Figure 1, a kind of fuel power multi-rotor aerocraft of the present embodiment, comprise the mainframe 1 of ground flight controller and aircraft and be fixed on the under-chassis 2 of mainframe 1 lower end, the balance bracket 3 of horizontal positioned is fixed with in the upper end of mainframe 1, balance bracket 3 is evenly provided with the symmetrical rotor support 4 installed of many groups centered by the center of circle, one end of each rotor support 4 is fixed on the center of balance bracket 3, the other end is fixed with the rotor 5 for aircraft balance and pose adjustment, screw propeller blade face and the balance bracket 3 of described rotor 5 are all horizontal, described rotor 5 is by its speed of its electric machine control, also comprise the battery pack 6 be fixed on mainframe 1, described battery pack 6 is connected respectively by the motor of wire with rotor 5, mainframe 1 is provided with a fuel engines 8, mainframe 1 is also provided with fuel tank 9, fuel engines 8 is provided with by its dynamical axis the main screw 10 providing flight lift, and the central axis of described main screw 10 is in horizontal surface and be on same line with the center of circle of balance bracket 3, also comprise the antenna 11 be arranged on mainframe 1.
One group of symmetrical rotor support 4 installed is arranged with the sidespin wing 7 of offsetting fuel engines torsion respectively wherein, the screw propeller blade face of the described sidespin wing 7 and the screw propeller blade face of rotor 5 perpendicular, the described sidespin wing 7 is by its speed of its electric machine control, and battery pack 6 is connected by the motor of wire with the sidespin wing 7.This group sidespin wing 7 can balance the torsion that fuel engines 8 produces.
In the present embodiment, aircraft fly time, relies on 6 rotors 5 realize aircraft balance and pose adjustment, rely on the main screw 10 below it to provide the prevailing lift of flight, achieve balance and lift separate, reliable and stable.
In the present embodiment, balance bracket 3 is closed shapes, and its shape can be annular arrangement, also can be the various closed shapes such as rectangle.GPS positioning function is with by described antenna 11.
In the present embodiment, aircraft is when normal flight, and fuel engines work vertical motion should be slightly less than thrust when taking off except extrapolability.Engine throttle achieves Based Intelligent Control, after electronic rotor produces certain lift, if aircraft can not strengthen by ascent engine throttle gradually, specified altitude assignment is reached until liftoff, during falling head, electronic rotor reduces certain thrust, if can't decline or decline, very slow engine throttle slightly reduces, until drop to specified altitude assignment to recover there is throttle.When flight, other action is controlled by multiple rotor 5 and the sidespin wing 7 completely, ensures to realize various flight attitude.May be used for pesticide spraying, power construction messenger leads to be put, and rescue transport, the aspects such as aerial photography, application widely.
Embodiment two
Be with the difference of embodiment one, in the present embodiment, described mainframe 1 be provided with two fuel enginess 8.These two fuel enginess about 8 are coaxially installed or horizontal symmetrical is installed, and its screw propeller rotates in the opposite direction, and cancel each other torsion, does not now need to arrange the sidespin wing 7.In the present embodiment, by arranging multiple stage fuel engines, also can add lift, realizing manned driving or the unpiloted function of ground remote control.
The above; it is only embodiment of the present utility model; not the utility model is imposed any restrictions; every above embodiment is done according to the utility model technical spirit any simple modification, change and equivalent method change, all still belong in the protection domain of technical solutions of the utility model.
Claims (5)
1. a fuel power multi-rotor aerocraft, comprise the mainframe (1) of ground flight controller and aircraft and be fixed on the under-chassis (2) of mainframe (1) lower end, it is characterized in that: the balance bracket (3) being fixed with horizontal positioned in the upper end of mainframe (1), balance bracket (3) is evenly provided with the symmetrical rotor support (4) installed of many groups centered by the center of circle, one end of each rotor support (4) is fixed on the center of balance bracket (3), the other end is fixed with the rotor (5) for aircraft balance and pose adjustment, screw propeller blade face and the balance bracket (3) of described rotor (5) are all horizontal, described rotor (5) is by its speed of its electric machine control, also comprise the battery pack (6) be fixed on mainframe (1), described battery pack (6) is connected respectively by the motor of wire with rotor (5), mainframe (1) is provided with at least one fuel engines (8), mainframe (1) is also provided with fuel tank (9), fuel engines (8) is provided with by its dynamical axis the main screw (10) providing flight lift, and the central axis of described main screw (10) is in horizontal surface and be on same line with the center of circle of balance bracket (3), also comprise the antenna (11) be arranged on mainframe (1).
2. a kind of fuel power multi-rotor aerocraft according to claim 1, it is characterized in that: described mainframe (1) is provided with a fuel engines (8), one group of symmetrical rotor support (4) installed is arranged with the sidespin wing (7) of offsetting fuel engines torsion respectively wherein, the screw propeller blade face of the described sidespin wing (7) and the screw propeller blade face of rotor (5) perpendicular, the described sidespin wing (7) is by its speed of its electric machine control, and battery pack (6) is connected by the motor of wire with the sidespin wing (7).
3. a kind of fuel power multi-rotor aerocraft according to claim 1, is characterized in that: described mainframe (1) is provided with two fuel enginess (8).
4. a kind of fuel power multi-rotor aerocraft according to claim 1 and 2, is characterized in that: described balance bracket (3) is enclosed shape.
5. a kind of fuel power multi-rotor aerocraft according to claim 4, is characterized in that: the shape of described balance bracket (3) is annular arrangement or rectangle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520042448.XU CN204507257U (en) | 2015-01-22 | 2015-01-22 | A kind of fuel power multi-rotor aerocraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520042448.XU CN204507257U (en) | 2015-01-22 | 2015-01-22 | A kind of fuel power multi-rotor aerocraft |
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| Publication Number | Publication Date |
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| CN204507257U true CN204507257U (en) | 2015-07-29 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201520042448.XU Expired - Fee Related CN204507257U (en) | 2015-01-22 | 2015-01-22 | A kind of fuel power multi-rotor aerocraft |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105035328A (en) * | 2015-08-19 | 2015-11-11 | 张旭超 | Hybrid-power flight vehicle |
| CN105438460A (en) * | 2015-12-16 | 2016-03-30 | 西北工业大学 | Dual-power synergistically driven unmanned aerial vehicle |
| CN105468009A (en) * | 2015-12-25 | 2016-04-06 | 西北工业大学 | System and method for multi-power integrated flight control applied in micro air vehicle |
| CN105836101A (en) * | 2016-05-20 | 2016-08-10 | 辽宁辽飞航空科技有限公司 | Oil-driven variable-distance multi-rotor aircraft bearing rack |
| CN105836134A (en) * | 2016-05-09 | 2016-08-10 | 四川马可视觉网络科技有限公司 | Rotary type spraying aircraft |
| CN105857591A (en) * | 2016-05-09 | 2016-08-17 | 四川马可视觉网络科技有限公司 | Vehicle body of simple sprinkling aerial vehicle |
| CN108773481A (en) * | 2018-07-02 | 2018-11-09 | 广州天翔航空科技有限公司 | Electronic Manned Flying System |
| CN109383759A (en) * | 2018-11-05 | 2019-02-26 | 南方科技大学 | A kind of aircraft adjusting flight attitude based on rudder face |
| CN114379773A (en) * | 2016-04-17 | 2022-04-22 | L·沃尔皮 | Unmanned aerial vehicle of robot with installation mechanism |
-
2015
- 2015-01-22 CN CN201520042448.XU patent/CN204507257U/en not_active Expired - Fee Related
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105035328A (en) * | 2015-08-19 | 2015-11-11 | 张旭超 | Hybrid-power flight vehicle |
| CN105438460A (en) * | 2015-12-16 | 2016-03-30 | 西北工业大学 | Dual-power synergistically driven unmanned aerial vehicle |
| CN105468009A (en) * | 2015-12-25 | 2016-04-06 | 西北工业大学 | System and method for multi-power integrated flight control applied in micro air vehicle |
| CN105468009B (en) * | 2015-12-25 | 2017-05-31 | 西北工业大学 | It is applied to many power fusion flight control system and the method for micro air vehicle |
| CN114379773A (en) * | 2016-04-17 | 2022-04-22 | L·沃尔皮 | Unmanned aerial vehicle of robot with installation mechanism |
| CN105836134A (en) * | 2016-05-09 | 2016-08-10 | 四川马可视觉网络科技有限公司 | Rotary type spraying aircraft |
| CN105857591A (en) * | 2016-05-09 | 2016-08-17 | 四川马可视觉网络科技有限公司 | Vehicle body of simple sprinkling aerial vehicle |
| CN105836101A (en) * | 2016-05-20 | 2016-08-10 | 辽宁辽飞航空科技有限公司 | Oil-driven variable-distance multi-rotor aircraft bearing rack |
| CN108773481A (en) * | 2018-07-02 | 2018-11-09 | 广州天翔航空科技有限公司 | Electronic Manned Flying System |
| CN108773481B (en) * | 2018-07-02 | 2024-05-21 | 深圳市翔农创新科技有限公司 | Electric manned flight system |
| CN109383759A (en) * | 2018-11-05 | 2019-02-26 | 南方科技大学 | A kind of aircraft adjusting flight attitude based on rudder face |
| CN109383759B (en) * | 2018-11-05 | 2023-08-22 | 南方科技大学 | Aircraft capable of adjusting flight attitude based on control surface |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20150729 Termination date: 20170122 |