CN205770149U - A kind of fixed-wing rotor mixing unmanned plane of multi-configuration - Google Patents
A kind of fixed-wing rotor mixing unmanned plane of multi-configuration Download PDFInfo
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- CN205770149U CN205770149U CN201620480748.0U CN201620480748U CN205770149U CN 205770149 U CN205770149 U CN 205770149U CN 201620480748 U CN201620480748 U CN 201620480748U CN 205770149 U CN205770149 U CN 205770149U
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Abstract
This utility model discloses the fixed-wing rotor mixing unmanned plane of a kind of multi-configuration, including rotor assemblies, fixed-wing system and equipment compartment, described equipment compartment includes nacelle, flight controller it is provided with in nacelle, sensor and power supply, fixed-wing system includes body and the steering wheel being located on body and dynamical system, fixed-wing system is connected with equipment compartment by i.e. interface, rotor assemblies is connected with equipment compartment also by i.e. interface simultaneously, when fixed-wing system is all plugged on equipment compartment with rotor assemblies, rotor assemblies work mutually auxiliary with fixed-wing system becomes and mixes unmanned plane, rotor assemblies becomes rotor wing unmanned aerial vehicle when being individually plugged on equipment compartment, fixed-wing system becomes fixed-wing unmanned plane when being individually plugged on equipment compartment.This utility model a machine three-use, can change between the Three models of rotor wing unmanned aerial vehicle, fixed-wing unmanned plane and mixing unmanned plane easily according to demand, will not become heavy burden when having only to rotor or fixed-wing function each other, improve flight efficiency.
Description
Technical field
This utility model relates to vehicle technology field, and the fixed-wing rotor mixing particularly relating to a kind of multi-configuration is unmanned
Machine.
Background technology
Fixed wing airplane utilizes the motion of wing relative wind to produce lift opposing gravity, has that flight speed is fast, voyage
Far, load-carrying is big, energy efficiency advantages of higher, but landing needs distance runway, it is impossible to realize hovering；
And gyroplane utilizes one or more rotor to produce pulling force opposing gravity, by controlling Plane of rotation and the water of rotor
The inclination angle of plane provides the power of aircraft transverse movement, simple in construction, it is possible to VTOL and hovering,
But speed compared with slow, load-carrying is little, energy efficiency is low.Fixed-wing rotor mixing unmanned plane is to grow up recent years
A kind of new vertical landing aircraft, use the mode that combines with rotor platform of fixed-wing to obtain simple and effective
VTOL scheme.Fixed-wing rotor integration unmanned plane has many relative to other kinds of aircraft
Performance advantage: as having the Fixed Wing AirVehicle of VTOL performance, fixed-wing rotor mixing unmanned plane is the most permissible
VTOL, is not limited by landing place, has again a high speed long voyage feature of fixed wing airplane, perform many its
The inexecutable task of his aircraft.Existing fixed-wing rotor mixing unmanned plane, rotor can not depart from fixed-wing list
Solely perform aerial mission, rotor assemblies all can not be dismantled during fixed-wing mode flight, thus cause traditional
Fixed-wing rotor mixing unmanned plane application degree of freedom is poor, only possesses a kind of structural feature, during fixed-wing work, and rotor
Becoming heavy burden, affect flight efficiency, during rotor work, fixed-wing becomes heavy burden equally, have impact on the load-carrying of aircraft
Ability.
Utility model content
The technical assignment of technical problem to be solved in the utility model and proposition is to improve prior art, carries
For the fixed-wing rotor mixing unmanned plane of a kind of multi-configuration, solve fixed-wing rotor mixing nothing traditional in current technology
Man-machine application degree of freedom is poor, and flight efficiency when fixed-wing and rotor are to influence each other its work, using effect is the best
Problem.
For solving above technical problem, the technical solution of the utility model is:
A kind of fixed-wing rotor mixing unmanned plane of multi-configuration, including rotor assemblies, fixed-wing system and equipment compartment,
It is characterized in that, described equipment compartment includes nacelle, is provided with flight controller, sensor and power supply in nacelle,
Fixed-wing system includes body and the steering wheel that is located on body and dynamical system, fixed-wing system by i.e. interface with
Equipment compartment connects, and rotor assemblies is connected with equipment compartment also by i.e. interface simultaneously, fixed-wing system and rotor assemblies
When being all plugged on equipment compartment, rotor assemblies work mutually auxiliary with fixed-wing system becomes and mixes unmanned plane, rotor assemblies list
Becoming rotor wing unmanned aerial vehicle when being solely plugged on equipment compartment, fixed-wing system becomes fixed-wing when being individually plugged on equipment compartment
Unmanned plane.The fixed-wing rotor mixing unmanned plane of multi-configuration described in the utility model can realize a machine three-use, rotation
Wing unmanned plane, fixed-wing unmanned plane and mixing unmanned plane Three models freely switch, and mixing unmanned plane is consolidated with traditional
Determine wing rotor mixing unmanned plane functional similarity, be provided with flight controller in nacelle and control rotor group by i.e. interface
The duty of part, rotor wing unmanned aerial vehicle, fixed-wing unmanned plane are then the parts being completely independent work, rotor assemblies,
Fixed-wing system will not become heavy burden each other, can be greatly improved flight efficiency.
Further, described rotor assemblies uses single rotor or many rotor structures, uses difference according to the actual requirements
Structure, ensure both stability when being applied in combination.
Further, rotor assemblies includes that Power Component and frame, some frames are plugged on equipment compartment, and machine
Frame is along the symmetrical distribution of equipment compartment, and Power Component is arranged on the end of frame, and each Power Component is mechanical, electrical by electricity
Mediation propeller forms so that when rotor assemblies is assembled on equipment compartment, the left and right weight balancing of aircraft, it is ensured that fly
The stationarity of row.
Further, described rotor assemblies uses four rotor structures, Stability Analysis of Structures, improves having a smooth flight property, suitable
The flight that sum velocity is slow and voyage is short, work of can hovering, do not limited by landing place.
Further, described fixed-wing system uses front motive force structure or tail motive force structure, and front motive force is tied
Structure is more stable pneumatic, good heat dissipation, and the air-flow of tail motive force structure is on the weak side, weak heat-dissipating, occurs fried in fault
During machine, only head is impaired, and electromotor and oar chance of injury are low.
Compared with prior art, this utility model advantage is:
The fixed-wing rotor mixing unmanned plane of multi-configuration described in the utility model can as three kinds of unmanned plane configurations,
Can change between the Three models of rotor wing unmanned aerial vehicle, fixed-wing unmanned plane and mixing unmanned plane easily according to demand,
Simple in construction, combines, splits conveniently, will not become heavy burden each other when having only to rotor or fixed-wing flight function,
Flight efficiency can be greatly improved.
Accompanying drawing explanation
Fig. 1 is high-level schematic functional block diagram of the present utility model；
Fig. 2 is mixing unmanned plane structural representation of the present utility model；
Fig. 3 is rotor wing unmanned aerial vehicle structural representation of the present utility model；
Fig. 4 is fixed-wing unmanned plane structural representation of the present utility model.
Detailed description of the invention
Below in conjunction with the accompanying drawing in this utility model embodiment, the technical scheme in this utility model embodiment is entered
Row clearly and completely describes, it is clear that described embodiment is only a part of embodiment of this utility model, and
It is not all, of embodiment.Based on the embodiment in this utility model, those of ordinary skill in the art are not making
The every other embodiment obtained under creative work premise, broadly falls into the scope of this utility model protection.
The fixed-wing rotor mixing unmanned plane of a kind of multi-configuration disclosed in this utility model embodiment, improves application freely
Degree, is dismountable attachment structure between rotor and fixed-wing, can realize a machine three-use, according to demand can be easily
Change between the Three models of rotor wing unmanned aerial vehicle, fixed-wing unmanned plane and mixing unmanned plane, having only to rotor or solid
Heavy burden will not be become each other, it is ensured that rotor or the flight efficiency of fixed-wing when determining wing flight function.
As shown in Figures 1 to 4, the fixed-wing rotor mixing unmanned plane of a kind of multi-configuration, including rotor assemblies, admittedly
Determine wing system and equipment compartment 1, it is characterised in that described equipment compartment 1 includes nacelle, is provided with and flies in nacelle
Line control unit, sensor and power supply, fixed-wing system includes body and the steering wheel being located on body and dynamical system,
Fixed-wing system is connected with equipment compartment 1 by i.e. interface, and fixed-wing system uses front motive force structure or tail to promote
Power structure, motive force structure before using in the present embodiment, aerodynamic force is good, perfect heat-dissipating, and stability in use is good,
Rotor assemblies is connected with equipment compartment 1 also by i.e. interface simultaneously, and fixed-wing system and rotor assemblies are all plugged on and set
Becoming for rotor assemblies work mutually auxiliary with fixed-wing system time on cabin 1 and mix unmanned plane, rotor assemblies is individually plugged on
Becoming rotor wing unmanned aerial vehicle during equipment compartment 1, fixed-wing system becomes fixed-wing when being individually plugged on equipment compartment 1 unmanned
Machine
Rotor assemblies uses single rotor or many rotor structures, and in the present embodiment, rotor assemblies uses four rotor structures,
Rotor assemblies includes Power Component 2 and frame 3, and some frames 3 are plugged on equipment compartment 1, and frame 3 is along setting
The standby symmetrical distribution in cabin 1, Power Component 2 is arranged on the end of frame 3, each Power Component 2 by motor,
Electricity mediation propeller composition.
Mixing unmanned plane: rotor assemblies, fixed-wing system are combined into equipment nacelle and mix unmanned plane, such as figure 2 above
Shown in, this kind of configuration takes into account both four rotor configurations and fixed-wing configuration advantage, it is possible to VTOL, not by landing
Place limits, and possess that fixed-wing unmanned plane speed is fast, long boat time and the advantage of long voyage, but flight speed,
Voyages etc. are owing to the impact of rotor assemblies is not as fixed-wing configuration.
Rotor wing unmanned aerial vehicle: rotor assemblies and equipment nacelle are combined into four rotor wing unmanned aerial vehicles, as it is shown on figure 3, this kind of structure
Type is suitable for the flight that speed is slow and voyage is short, work of can hovering, and is not limited by landing place
Fixed-wing unmanned plane: fixed-wing system and equipment compartment are combined into fixed-wing unmanned plane, as shown in Figure 4, this kind
Configuration is suitable for that speed is fast and requires high flight during voyage boat, it is impossible to hovering work, landing needs runway.
Below it is only preferred implementation of the present utility model, it is noted that above-mentioned preferred implementation should not
Being considered as restriction of the present utility model, protection domain of the present utility model should be with claim limited range
Accurate.For those skilled in the art, without departing from spirit and scope of the present utility model,
Can also make some improvements and modifications, these improvements and modifications also should be regarded as protection domain of the present utility model.
Claims (5)
1. a fixed-wing rotor mixing unmanned plane for multi-configuration, including rotor assemblies, fixed-wing system and equipment compartment
(1), it is characterised in that described equipment compartment (1) includes nacelle, be provided with in nacelle flight controller,
Sensor and power supply, fixed-wing system includes body and the steering wheel being located on body and dynamical system, fixed-wing system
Being connected with equipment compartment (1) by i.e. interface, rotor assemblies is also by i.e. interface with equipment compartment (1) even simultaneously
Connecing, fixed-wing system is all plugged on rotor assemblies work mutually auxiliary with fixed-wing system time on equipment compartment (1) with rotor assemblies
Being made for mixing unmanned plane, rotor assemblies becomes rotor wing unmanned aerial vehicle, fixed-wing system when being individually plugged on equipment compartment (1)
System becomes fixed-wing unmanned plane when being individually plugged on equipment compartment (1).
The fixed-wing rotor mixing unmanned plane of multi-configuration the most according to claim 1, it is characterised in that described
Rotor assemblies use single rotor or many rotor structures.
The fixed-wing rotor mixing unmanned plane of multi-configuration the most according to claim 2, it is characterised in that described
Rotor assemblies include that Power Component (2) and frame (3), some frames (3) are plugged on equipment compartment (1),
And frame (3) is arranged on the end of frame (3) along equipment compartment (1) symmetrical distribution, Power Component (2)
Portion, each Power Component (2) is made up of electric mechanical, electrical mediation propeller.
The fixed-wing rotor mixing unmanned plane of multi-configuration the most according to claim 3, it is characterised in that described
Rotor assemblies use four rotor structures.
The fixed-wing rotor mixing unmanned plane of multi-configuration the most according to claim 1, it is characterised in that described
Fixed-wing system use before motive force structure or tail motive force structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620480748.0U CN205770149U (en) | 2016-05-24 | 2016-05-24 | A kind of fixed-wing rotor mixing unmanned plane of multi-configuration |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620480748.0U CN205770149U (en) | 2016-05-24 | 2016-05-24 | A kind of fixed-wing rotor mixing unmanned plane of multi-configuration |
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| CN205770149U true CN205770149U (en) | 2016-12-07 |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106965921A (en) * | 2017-05-09 | 2017-07-21 | 嘉兴安行信息科技有限公司 | Fixed-wing and the integral unmanned aerial vehicle of many rotors |
| CN106986016A (en) * | 2017-04-06 | 2017-07-28 | 苏州恩济智能科技有限公司 | One kind quickly disconnects adaptive cruise VUAV |
| CN108045573A (en) * | 2017-12-05 | 2018-05-18 | 长沙展朔轩兴信息科技有限公司 | Pull in front and others push behind the multi-functional fixed-wing unmanned plane of formula |
| WO2018107564A1 (en) * | 2016-12-14 | 2018-06-21 | 深圳市大疆创新科技有限公司 | Unmanned aerial vehicle |
| CN110562452A (en) * | 2019-09-23 | 2019-12-13 | 浙江驭云航空科技有限公司 | Can dismantle VTOL unmanned aerial vehicle of use |
| CN117885923A (en) * | 2024-03-14 | 2024-04-16 | 航大汉来（天津）航空技术有限公司 | Long-endurance patrol unmanned aerial vehicle |
-
2016
- 2016-05-24 CN CN201620480748.0U patent/CN205770149U/en active Active
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2018107564A1 (en) * | 2016-12-14 | 2018-06-21 | 深圳市大疆创新科技有限公司 | Unmanned aerial vehicle |
| CN106986016A (en) * | 2017-04-06 | 2017-07-28 | 苏州恩济智能科技有限公司 | One kind quickly disconnects adaptive cruise VUAV |
| CN106986016B (en) * | 2017-04-06 | 2019-09-03 | 苏州恩济智能科技有限公司 | It is a kind of quickly to disconnect adaptive cruise vertical take-off and landing drone |
| CN106965921A (en) * | 2017-05-09 | 2017-07-21 | 嘉兴安行信息科技有限公司 | Fixed-wing and the integral unmanned aerial vehicle of many rotors |
| CN108045573A (en) * | 2017-12-05 | 2018-05-18 | 长沙展朔轩兴信息科技有限公司 | Pull in front and others push behind the multi-functional fixed-wing unmanned plane of formula |
| CN110562452A (en) * | 2019-09-23 | 2019-12-13 | 浙江驭云航空科技有限公司 | Can dismantle VTOL unmanned aerial vehicle of use |
| CN117885923A (en) * | 2024-03-14 | 2024-04-16 | 航大汉来（天津）航空技术有限公司 | Long-endurance patrol unmanned aerial vehicle |
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| Date | Code | Title | Description |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address |
Address after: 643000 Aviation Avenue 9, Zigong Aviation Industrial Park, Zigong City, Sichuan Province Patentee after: China Electric Special Aircraft Systems Engineering Co., Ltd. Address before: 618300 No. 74 Taizhong Road, Guanghan City, Deyang City, Sichuan Province Patentee before: In Dianke (Deyang Guanghan) Special Aircraft System Engineering Co. Ltd. |
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| CP03 | Change of name, title or address |