CN204688408U - A kind of four rotor unmanned aircrafts - Google Patents
A kind of four rotor unmanned aircrafts Download PDFInfo
- Publication number
- CN204688408U CN204688408U CN201520190373.XU CN201520190373U CN204688408U CN 204688408 U CN204688408 U CN 204688408U CN 201520190373 U CN201520190373 U CN 201520190373U CN 204688408 U CN204688408 U CN 204688408U
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- China
- Prior art keywords
- fin
- rotor
- wing
- rotor unmanned
- unmanned aircrafts
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Abstract
The utility model relates to a kind of four rotor unmanned aircrafts, comprise body, wing and rotor assemblies, described wing is arranged on body both sides, described rotor assemblies is arranged on wing, described rotor assemblies comprises base, fixed link, driving device, attaching parts and multiple fin, described base is provided with sleeve pipe, sleeve pipe is fixedly connected with by fixed leg with fixed link, described fixed leg is provided with flexible member, described base is provided with resettlement section, described driving device comprises motor, motor is arranged in described resettlement section, the all sides of described attaching parts are provided with and connect sheet, connect sheet and be provided with multiple matching hole, described fin is provided with multiple perforation, matching hole is connected by fastener with described perforation.The rotor assemblies vibrations of four rotor unmanned aircrafts of the present utility model are little, thus improve the flight stability of unmanned vehicle; Meanwhile, by regulating fin and the connection connecting sheet, the length that adjustment fin is overhanging, thus adjustment airworthiness.
Description
Technical field
The utility model relates to a kind of unmanned vehicle, particularly a kind of four rotor unmanned aircrafts.
Background technology
Along with the development of technology, unmanned vehicle starts to play a significant role in every field.Unmanned vehicle attitude is changeable, in order to increase the load capacity of unmanned vehicle, unmanned vehicle have employed the physical construction of four rotors, control to make the coordinated movement of various economic factors between its each rotor by airborne navigational system, the flight attitude realizing four rotor wing unmanned aerial vehicles adjusts automatically, can complete various motion and the task such as vertical takeoff and landing (VTOL) control, hovering control, driftage control, roll unloads, pitch control subsystem on request.And existing rotor assemblies often to there will be vibrations excessive, thus affect flight stability.And fin is dismantled and adjustment comparatively bothers, impact maintenance and adjustment.
Utility model content
The utility model, in order to solve the problem of prior art, provides a kind of rotor assemblies stable, is convenient to four rotor unmanned aircrafts keeping in repair adjustment.
Concrete technical scheme is as follows: a kind of four rotor unmanned aircrafts, comprise body, wing and rotor assemblies, described wing is arranged on body both sides, described rotor assemblies is arranged on wing, described rotor assemblies comprises base, fixed link, driving device, attaching parts and multiple fin, described base is provided with sleeve pipe, sleeve pipe is fixedly connected with by fixed leg with fixed link, described fixed leg is provided with flexible member, described base is provided with resettlement section, described driving device comprises motor, motor is arranged in described resettlement section, the all sides of described attaching parts are provided with and connect sheet, connect sheet and be provided with multiple matching hole, described fin is provided with multiple perforation, matching hole is connected by fastener with described perforation.
It is below attached technical scheme of the present utility model.
Preferably, described resettlement section comprises perisporium, described perisporium wound motor.
Preferably, described driving device comprises driving wheel and follower, and follower is provided with take-off lever, and take-off lever is provided with external thread section.
Preferably, described attaching parts comprises centre hole and nut, is provided with negative thread bottom centre hole, thus connects with external thread section, passes through fastening nuts in end.
Preferably, described matching hole and perforation are all in a straight line.
Preferably, described fin has two at least.
Technique effect of the present utility model: the rotor assemblies vibrations of four rotor unmanned aircrafts of the present utility model are little, thus improve the flight stability of unmanned vehicle; Meanwhile, by regulating fin and the connection connecting sheet, the length that adjustment fin is overhanging, thus adjustment airworthiness.
Accompanying drawing explanation
Fig. 1 is the schematic diagram of four rotor unmanned aircrafts of the utility model embodiment.
Fig. 2 is the exploded drawings of the rotor assemblies of the utility model embodiment.
Detailed description of the invention
Below in conjunction with accompanying drawing, the utility model is described further.
As shown in Figure 1 to Figure 2, four rotor unmanned aircrafts of the present embodiment comprise body 100, wing 101, rotor assemblies 102 and alighting gear 103, and described wing 101 is arranged on body 100 both sides.Described wing 101 two ends are provided with rotor assemblies 102, and rotor assemblies 102 has four, and front and back respectively have two.Described alighting gear 103 is arranged on below body 100.Described rotor assemblies 102 comprises base 20, fixed link 12, driving device 30, attaching parts 33 and multiple fin 35.Described base 20 side is provided with sleeve pipe 21, and sleeve pipe 21 is connected with fixed link 12.Fixed link 12 is provided with knock hole 121, and sleeve pipe 21 is provided with through hole 22, and fixed leg 23 is arranged in knock hole 121 and through hole 22, sleeve pipe 21 and fixed link 12 is fixed.Described fixed leg 23 is provided with flexible member 29, and flexible member 29 winding, on fixed leg 12, makes fixed link 12 be subject to pining down of flexible member 29, thus makes fixed link 12 reduce the impact being subject to external force, and in the present embodiment, described flexible member 29 is nylon rope.Described base 20 opposite side is provided with resettlement section 24, and it is for accommodating driving device 30.Described driving device 30 comprises motor 31, driving wheel 311 and follower 312, and described resettlement section 24 is cylindrical, perisporium 241 wound motor 31 of resettlement section 24, thus is wrapped by motor 31, prevents it from shaking, affects flight stability.The diameter of described driving wheel 311 is less than follower 312, and driving wheel 311 and follower 312 engage, thus forms reduction assemblies.Described follower 312 is provided with take-off lever 32, and its projection is at follower 312 center, and it comprises external thread section 321.Described attaching parts 33 comprises centre hole 331, is provided with negative thread bottom centre hole 331, thus connects with external thread section 321, fastening by nut 34 in end, and attaching parts 33 is connected with take-off lever 32.Described attaching parts 33 weeks sides are provided with and connect sheet 334, connect sheet 334 and are provided with multiple matching hole 333.Described fin 35 is provided with multiple perforation 351, fastener 40 through perforation 351 and matching hole 333 by fin 35 with connect sheet 334 and be fixedly connected with.Described multiple matching hole 333 and multiple perforation 351 all in a straight line, thus by different matching holes 333 is corresponding with perforation 351, regulate the length that fin 35 stretches out, thus regulate the performance of aircraft; Meanwhile, can conveniently be dismantled by fastener 40.In the present embodiment, described fin is provided with two, and described fastener is bolt assembly.Those skilled in the art are known, connect sheet and fin by increasing, and attaching parts 33 can be connected with 3 or more fins.
The rotor assemblies vibrations of four rotor unmanned aircrafts of the present embodiment are little, thus improve the flight stability of unmanned vehicle; Meanwhile, by regulating fin and the connection connecting sheet, the length that adjustment fin is overhanging, thus adjustment airworthiness.It is to be noted; above-mentioned preferred embodiment is only and technical conceive of the present utility model and feature is described; its object is to person skilled in the art can be understood content of the present utility model and implement according to this, protection domain of the present utility model can not be limited with this.All equivalences done according to the utility model Spirit Essence change or modify, and all should be encompassed within protection domain of the present utility model.
Claims (6)
1. a rotor unmanned aircraft, comprise body, wing and rotor assemblies, described wing is arranged on body both sides, described rotor assemblies is arranged on wing, it is characterized in that: described rotor assemblies comprises base, fixed link, driving device, attaching parts and multiple fin, described base is provided with sleeve pipe, sleeve pipe is fixedly connected with by fixed leg with fixed link, described fixed leg is provided with flexible member, described base is provided with resettlement section, described driving device comprises motor, motor is arranged in described resettlement section, the all sides of described attaching parts are provided with and connect sheet, connect sheet and be provided with multiple matching hole, described fin is provided with multiple perforation, matching hole is connected by fastener with described perforation.
2. four rotor unmanned aircrafts as claimed in claim 1, is characterized in that: described resettlement section comprises perisporium, described perisporium wound motor.
3. four rotor unmanned aircrafts as claimed in claim 2, is characterized in that: described driving device comprises driving wheel and follower, and follower is provided with take-off lever, and take-off lever is provided with external thread section.
4. four rotor unmanned aircrafts as claimed in claim 3, is characterized in that: described attaching parts comprises centre hole and nut, is provided with negative thread bottom centre hole, thus connects with external thread section, passes through fastening nuts in end.
5. four rotor unmanned aircrafts as claimed in claim 4, is characterized in that: described matching hole and perforation are all in a straight line.
6. four rotor unmanned aircrafts as claimed in claim 5, is characterized in that: described fin has two at least.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520190373.XU CN204688408U (en) | 2015-03-30 | 2015-03-30 | A kind of four rotor unmanned aircrafts |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520190373.XU CN204688408U (en) | 2015-03-30 | 2015-03-30 | A kind of four rotor unmanned aircrafts |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204688408U true CN204688408U (en) | 2015-10-07 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520190373.XU Expired - Fee Related CN204688408U (en) | 2015-03-30 | 2015-03-30 | A kind of four rotor unmanned aircrafts |
Country Status (1)
| Country | Link |
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| CN (1) | CN204688408U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105366048A (en) * | 2015-11-30 | 2016-03-02 | 湖北易瓦特科技股份有限公司 | Multi-rotor unmanned aerial vehicle |
-
2015
- 2015-03-30 CN CN201520190373.XU patent/CN204688408U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105366048A (en) * | 2015-11-30 | 2016-03-02 | 湖北易瓦特科技股份有限公司 | Multi-rotor unmanned aerial vehicle |
| CN105366048B (en) * | 2015-11-30 | 2018-12-11 | 易瓦特科技股份公司 | More rotor unmanned flight equipment |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20151007 Termination date: 20160330 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |