CN112061387A - Rotor wing mounting structure based on unmanned aerial vehicle wing - Google Patents
Rotor wing mounting structure based on unmanned aerial vehicle wing Download PDFInfo
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- CN112061387A CN112061387A CN202010949377.7A CN202010949377A CN112061387A CN 112061387 A CN112061387 A CN 112061387A CN 202010949377 A CN202010949377 A CN 202010949377A CN 112061387 A CN112061387 A CN 112061387A
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- wing
- rotor
- unmanned aerial
- aerial vehicle
- propeller
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/26—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
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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
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/10—Wings
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/20—Rotors; Rotor supports
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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)
- Remote Sensing (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention relates to a rotor wing mounting structure based on an unmanned aerial vehicle wing, which comprises a rack assembly, a stay bar assembly and a rotor wing power unit, wherein the rack assembly is positioned on the wing, one end of the stay bar assembly is connected with the rack assembly, and the other end of the stay bar assembly is connected with the rotor wing power unit. The structure of the invention has the advantages of high modularization degree, simple structure, small aerodynamic resistance, flexible installation position, suitability for transformation of the fixed wing unmanned aerial vehicle and the like.
Description
Technical Field
The invention belongs to the field of unmanned aerial vehicles, relates to a rotor wing mounting structure, and particularly relates to a rotor wing mounting structure based on wings of an unmanned aerial vehicle.
Background
The fixed-wing unmanned aerial vehicle has the advantages of high flying speed, long endurance time, strong load carrying capacity and the like, and is widely applied to military and civil fields. But the conventional fixed wing unmanned aerial vehicle has high requirements on take-off and landing sites, so that the further popularization and application of the conventional fixed wing unmanned aerial vehicle are limited. The rotor unmanned aerial vehicle with the vertical take-off and landing function has small dependence on a ground take-off and landing field, can take off and land flexibly and hover in the air, but has relatively poor indexes of flying height, speed, time of flight and the like.
In order to combine the advantages of two types of unmanned aerial vehicles, hybrid wing unmanned aerial vehicles combining multiple rotors and fixed wings have attracted much attention in recent years, and have come to be of many models. Hybrid wing unmanned aerial vehicle generally will many rotors distribute and install on fixed wing unmanned aerial vehicle organism structure (install more on wing structure), realize the VTOL function through the rotor, convert fixed wing flight mode into again after the lift-off.
The installation of rotor components on fixed-wing airframe structures is mainly of two types: firstly, with the help of organism structural configuration, if prolong former unmanned aerial vehicle tail vaulting pole to arrange the rotor at tail vaulting pole both ends. The installation form enables the structure layout of the machine body to be coupled with the layout of the rotor wing, and the design constraint is large; and secondly, adding an installation structure according to a rotor wing layout result, such as adding a wing load hanging point. The mounting form greatly changes the original machine body structure, and the aerodynamic interference resistance between the rotor wing mounting structure and the original machine body structure is large.
Disclosure of Invention
The technical problem solved by the invention is as follows: reduce mixed wing unmanned aerial vehicle's the rotor overall arrangement design degree of difficulty, with fixed wing unmanned aerial vehicle design and rotor design looks decoupling zero, the later stage is through the mounting structure combination and generate mixed wing unmanned aerial vehicle. The invention provides a rotor wing mounting structure based on an unmanned aerial vehicle wing. The structure of the invention has the advantages of high modularization degree, simple structure, small aerodynamic resistance, flexible installation position, suitability for transformation of the fixed wing unmanned aerial vehicle and the like.
The technical scheme of the invention is as follows: a rotor wing installation structure based on unmanned aerial vehicle wings comprises a rack assembly, a stay bar assembly and a rotor wing power unit, wherein the rack assembly is positioned on the wings, one end of the stay bar assembly is connected with the rack assembly, and the other end of the stay bar assembly is connected with the rotor wing power unit;
the frame component comprises an upper beam, a lower beam, a front joint and a rear joint, the upper beam and the lower beam wrap the wing airfoil, and the upper beam and the lower beam are attached to the surface of the wing in a curved surface manner; the upper beam and the lower beam are fixedly connected through a front joint and a rear joint;
the stay bar component: the support rod is of a hollow rod-shaped structure, one end of the support rod is fixedly connected with the front joint or the rear joint, and the other end of the support rod is fixedly connected with the mounting seat;
the mounting seat is used for mounting a rotor wing power unit;
the rotor power unit provides rotor power output and comprises an engine and a propeller; the engine is fixed on the mounting seat and can drive the propeller to rotate.
The further technical scheme of the invention is as follows: the mounting seat is an integrally formed part and is divided into a disc-shaped part and a cylindrical part, the circumference of the cylindrical part is vertical to the axis of the disc-shaped part, and the two parts are internally provided with cavities which are communicated with each other; the disc-shaped structure is used for installing an engine, and the columnar body is fixedly connected with the support rod.
The further technical scheme of the invention is as follows: the engine is an electric motor or a fuel engine.
The further technical scheme of the invention is as follows: the propeller can be two-blade propeller or multi-blade propeller, and the direction of the propeller can be positive propeller or negative propeller.
The further technical scheme of the invention is as follows: the outer surfaces of the upper beam and the lower beam are smooth continuously and are designed in a streamline mode along the course direction.
Effects of the invention
The invention has the technical effects that: the rotor wing mounting structure has the beneficial effects that:
1. the modularization degree is high: the support rod assembly for mounting the rotor wing power unit is in a modular design, is interchangeable, is convenient to maintain and replace, and can effectively reduce the production and management cost.
2. The structure is simple: the invention has the advantages of clear functions of structural parts, clear force transmission routes, small number of parts, conventional structure and low production, processing and assembly costs.
3. The pneumatic resistance is small: the invention has the advantages that the upper part and the lower part of the rack assembly wrap the wings, the surface is smooth, the appearance adopts a streamline design, and the aerodynamic resistance and the interference resistance can be reduced to the minimum.
4. The installation position is flexible: the rotor wing mounting structure has no requirement on a wing mounting hanging point, and after the regional enhancement design is carried out on the wing, the rotor wing mounting structure is flexible in mounting position and convenient for later stage replacement and installation of engines and rotor wings of various specifications.
5. Be applicable to fixed wing unmanned aerial vehicle transformation: after the mounting area of the rotor on the wing is determined according to the wing strength calculation result and the rotor load requirement, the rotor mounting structure can realize rotor mounting without changing the wing structure.
Drawings
FIG. 1 is a diagram illustrating the effect of installation of an embodiment of the present invention;
FIG. 2 is an exploded schematic view of an embodiment of the present invention;
fig. 3 is an exploded view of the principal components of an embodiment of the invention.
Wherein: 1-wing, 2-rotor mounting structure, 3-frame assembly, 4-brace rod assembly, 5-rotor power unit, 6-upper beam, 7-rear joint, 8-lower beam, 9-front joint, 10-quick-release pin, 11-brace rod, 12-mounting seat, 13-engine, 14-propeller.
Detailed Description
Referring to fig. 1-3, the following description will discuss an embodiment of the present invention in further detail with reference to the drawings and the detailed description.
The rotor wing mounting structure mainly comprises a rack assembly, a stay bar assembly and a rotor wing power unit:
1. a rack assembly: the installation is fixed on the wing structure and provides the installation interface of the stay bar component. The frame assembly mainly comprises an upper beam, a lower beam, a front joint and a rear joint. The frame component wraps the wing airfoil through an upper beam and a lower beam, the upper beam and the lower beam are attached to the surface of the wing through curved surfaces, the outer surfaces of the upper beam and the lower beam are smooth continuously, and the outer surface of the upper beam and the lower beam is designed in a streamline mode along the course. The front joint and the rear joint are respectively positioned at the foremost end and the rearmost end of the rack assembly and are fixedly connected with the upper beam and the lower beam.
2. The stay bar component: the mounting is fixed on the frame component and provides a mounting interface of the rotor wing power unit. The stay bar component mainly comprises a stay bar and a mounting seat. The stay bar is a hollow rod-shaped structure, and the length is determined by referring to the size of the rotor wing. One end of the support rod is connected with the rack assembly, and the other end of the support rod is connected with the mounting seat. The mount pad is used for installing rotor power pack, and mechanical interface coordinates the design according to rotor power pack installation demand.
3. A rotor power unit: the installation is fixed on the stay bar component, and the power output of the rotor wing is provided. The rotor power unit mainly comprises an engine and a propeller. The engine may be in the form of an electric motor or a fuel-powered engine, depending on the overall design. The propeller structure can be two-blade propeller or multi-blade propeller, and the propeller direction can be positive propeller or negative propeller.
Design separating surfaces are arranged between the rack assembly and the wings and between the rotor wing power unit and the stay bar assembly, and the design separating surfaces are not detached in use and are only detached when the system breaks down and needs to be overhauled. For using the parting surface between vaulting pole subassembly and the frame subassembly, can adopt the fast-assembling quick-release design, can reduce the part size after dismantling the separation, the unmanned aerial vehicle part of being convenient for vanning or loading.
Fig. 1 is a diagram showing the installation effect of an example of the invention, and a rotor wing installation structure 2 is fixed at a designated section position of a wing 1 in a clamping manner. The installation effect is succinct, does not destroy wing structural integrity. Figure 2 is an exploded schematic view of an example of the present invention, the rotor mounting structure 2 being divided into a frame assembly 3, a strut assembly 4 and a rotor power unit 5. The front support rod assembly and the rear support rod assembly are in modular design and have interchangeability. In use and maintenance, the strut assembly 4 and the rotor power unit 5 are disassembled and assembled as an integral component to facilitate component loading or boxing.
Fig. 3 is an exploded view of main parts, and the frame assembly 3 comprises an upper beam 6, a rear joint 7, a lower beam 8 and a front joint 9. The course shapes of the upper beam 6 and the lower beam 8 adopt a streamline design, so that the aerodynamic resistance is reduced to the maximum extent. The upper beam 6 and the lower beam 8 wrap the wing 1 up and down and are fused with the outer surface of the wing 1 for transition, so that aerodynamic interference resistance of parts is reduced to the maximum extent. The upper beam 6 and the lower beam 8 adopt a hollow design with flanging, so that the structural strength is ensured, the structural weight is maximally reduced, and the rotor load is transferred to the wing 1 in a surface contact manner. The front and rear joints 9, 7 fit inside the upper and lower spars 6, 8, transferring rotor loads to the upper and lower spars 6, 8. The stay bar assembly 4 comprises a quick release pin 10, a stay bar 11 and a mounting seat 12. The stay bar 11 is a thin-walled cylindrical structure and can bear various loads transmitted by the rotor power unit 5. One side of a support rod 11 is connected with a mounting seat 12, the other side of the support rod is in butt joint with the rack assembly 3, and the support rod 11 is fixedly arranged on a front joint 9 or a rear joint 7 of the rack assembly 3 through a quick-release pin 10. The rotor power unit 5 comprises an engine 13 and a propeller 14, wherein the engine 13 is a brushless motor in the example, and the propeller 14 is a double-blade fixed pitch propeller.
The above-described embodiments of the present invention should not be construed as limiting the claims of the present invention, and the skilled person should fall within the scope of the claims of the present invention if he or she makes corresponding changes without inventive efforts through the inspiration of the present invention.
Claims (5)
1. A rotor wing installation structure based on unmanned aerial vehicle wings is characterized by comprising a rack assembly, a stay bar assembly and a rotor wing power unit, wherein the rack assembly is positioned on the wings;
the frame assembly comprises an upper beam (6), a lower beam (8), a front joint (9) and a rear joint (7), the upper beam (6) and the lower beam (8) wrap the wing airfoil, and the upper beam (6) and the lower beam (8) are attached to the surface of the wing in a curved surface manner; the upper beam (6) and the lower beam (8) are fixedly connected through a front joint (9) and a rear joint (7);
the stay bar component: the device comprises a stay bar (11) and a mounting seat (12), wherein the stay bar (11) is of a hollow rod-shaped structure, one end of the stay bar (11) is fixedly connected with a front joint (9) or a rear joint (7), and the other end of the stay bar (11) is fixedly connected with the mounting seat (12);
the mounting seat (12) is used for mounting a rotor wing power unit;
the rotor power unit provides rotor power output and comprises an engine (13) and a propeller (14); the engine (13) is fixed on the mounting base (12), and the engine (13) can drive the propeller (14) to rotate.
2. The rotor mounting structure based on unmanned aerial vehicle wing of claim 1, characterized in that, the mounting base (12) is a one-piece part, and is divided into two parts, namely a disc-shaped part and a cylindrical part, the circumference of the cylindrical part is perpendicular to the axis of the disc-shaped part, and the two parts are internally provided with cavities and communicated with each other; the disc-shaped structure is used for installing an engine (13), and the columnar body is fixedly connected with the support rod (11).
3. A rotor mounting structure based on a wing of an unmanned aerial vehicle according to claim 1, wherein the engine (13) is selected from an electric motor or a fuel engine.
4. Rotor mounting structure based on unmanned aerial vehicle wing according to claim 1, characterized in that, the screw propeller (14) can be selected from two-blade propeller or multi-blade propeller, and the screw propeller direction can be positive propeller or negative propeller.
5. A rotor mounting structure based on unmanned aerial vehicle wing according to claim 1, characterized in that, the outer surface of the upper beam (6) and the lower beam (8) is continuous and smooth, and is designed along the course streamline.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010949377.7A CN112061387A (en) | 2020-09-10 | 2020-09-10 | Rotor wing mounting structure based on unmanned aerial vehicle wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010949377.7A CN112061387A (en) | 2020-09-10 | 2020-09-10 | Rotor wing mounting structure based on unmanned aerial vehicle wing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112061387A true CN112061387A (en) | 2020-12-11 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010949377.7A Pending CN112061387A (en) | 2020-09-10 | 2020-09-10 | Rotor wing mounting structure based on unmanned aerial vehicle wing |
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| CN (1) | CN112061387A (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20150136897A1 (en) * | 2012-06-01 | 2015-05-21 | Logo-Team Ug (Haftungsbeschrankt) | Aircraft, preferably unmanned |
| CN106741820A (en) * | 2016-12-20 | 2017-05-31 | 中国科学院长春光学精密机械与物理研究所 | A kind of VTOL fixed-wing unmanned vehicle |
| CN206766345U (en) * | 2017-04-20 | 2017-12-19 | 西北工业大学明德学院 | A kind of four rotor wing unmanned aerial vehicles with crawl function |
| CN109178301A (en) * | 2018-09-04 | 2019-01-11 | 西北工业大学 | A kind of fixed-wing rotor mixing unmanned plane |
| CN109720564A (en) * | 2019-02-13 | 2019-05-07 | 深圳创壹通航科技有限公司 | Fixed-wing unmanned plane and its control method with VTOL function |
| US20190152593A1 (en) * | 2015-11-04 | 2019-05-23 | Fuvex Sistemas, S.L. (95%) | Aerodyne with vertical-takeoff-and-landing ability |
-
2020
- 2020-09-10 CN CN202010949377.7A patent/CN112061387A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20150136897A1 (en) * | 2012-06-01 | 2015-05-21 | Logo-Team Ug (Haftungsbeschrankt) | Aircraft, preferably unmanned |
| US20190152593A1 (en) * | 2015-11-04 | 2019-05-23 | Fuvex Sistemas, S.L. (95%) | Aerodyne with vertical-takeoff-and-landing ability |
| CN106741820A (en) * | 2016-12-20 | 2017-05-31 | 中国科学院长春光学精密机械与物理研究所 | A kind of VTOL fixed-wing unmanned vehicle |
| CN206766345U (en) * | 2017-04-20 | 2017-12-19 | 西北工业大学明德学院 | A kind of four rotor wing unmanned aerial vehicles with crawl function |
| CN109178301A (en) * | 2018-09-04 | 2019-01-11 | 西北工业大学 | A kind of fixed-wing rotor mixing unmanned plane |
| CN109720564A (en) * | 2019-02-13 | 2019-05-07 | 深圳创壹通航科技有限公司 | Fixed-wing unmanned plane and its control method with VTOL function |
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Application publication date: 20201211 |