CN211055359U - Tail structure suitable for multi-rotor unmanned aerial vehicle and multi-rotor unmanned aerial vehicle - Google Patents
Tail structure suitable for multi-rotor unmanned aerial vehicle and multi-rotor unmanned aerial vehicle Download PDFInfo
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- CN211055359U CN211055359U CN201921946915.6U CN201921946915U CN211055359U CN 211055359 U CN211055359 U CN 211055359U CN 201921946915 U CN201921946915 U CN 201921946915U CN 211055359 U CN211055359 U CN 211055359U
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Abstract
The utility model discloses a tail structure suitable for multi-rotor unmanned aerial vehicle and multi-rotor unmanned aerial vehicle, the tail structure is installed at the tail of the multi-rotor unmanned aerial vehicle, and the bottom of the tail structure is provided with a first airplane wheel; the tail structure comprises a main bearing structure frame and a forward propulsion device; the afterbody at many rotor unmanned aerial vehicle is installed to main load structure frame's front end, and to the rear end at main load structure frame was installed to advancing device, to advancing device and many rotor unmanned aerial vehicle electricity be connected, and the bottom at main load structure frame is installed to first wheel. The utility model discloses install in many rotor unmanned aerial vehicle back, its steering arm turns to the arm length than traditional rotor aircraft, and under same steering effort, deflection moment is bigger, turns to more nimble, rapider, has overcome traditional many rotor unmanned aerial vehicle and has used that the center of gravity is narrow, the course turns to shortcoming such as response slow, anti crosswind poor stability.
Description
Technical Field
The utility model relates to a many rotor unmanned aerial vehicle technical field, more specifically the afterbody structure and many rotor unmanned aerial vehicle suitable for many rotor unmanned aerial vehicle that says so relate to one kind.
Background
With the rapid development of computer technology and artificial intelligence technology, the design and manufacture of unmanned aerial vehicles make great progress, and the unmanned aerial vehicles are more and more widely applied and more prominent in various national civilization fields such as industry, agriculture, national defense and social management. The most, most popular of the current unmanned aerial vehicle applications are multi-rotor unmanned aerial vehicles. Although many rotor unmanned aerial vehicle have simple structure, make characteristics such as easy, easy operation, use economy, but many rotor unmanned aerial vehicle focus of tradition coincide with the geometric centre, and the rotor fuses lift and gesture adjustment and integrates into one, and the defect of bringing is that it is narrow to use the center of gravity, and the course turns to the response slow, and anti-wind stability is poor, uses the limitation big.
Therefore, how to solve the technical scheme that the multi-rotor unmanned aerial vehicle has poor course stability and weak crosswind resistance is a problem that needs to be solved urgently by technical personnel in the field.
SUMMERY OF THE UTILITY MODEL
In view of this, the utility model provides a tail structure and many rotor unmanned aerial vehicle suitable for many rotor unmanned aerial vehicle, its aim at solve the poor defect of course poor stability and anti side wind ability of many rotor unmanned aerial vehicle among the prior art.
In order to achieve the above purpose, the utility model adopts the following technical scheme:
a tail structure suitable for a multi-rotor unmanned aerial vehicle is installed at the tail of the multi-rotor unmanned aerial vehicle, and a first wheel is installed at the bottom of the tail structure;
the tail structure comprises a main bearing structure frame and a forward propulsion device;
the front end of main load structure frame is installed many rotor unmanned aerial vehicle's afterbody, it installs to advancing device main load structure frame's rear end, it connects to advancing device with many rotor unmanned aerial vehicle electricity, first wheel is installed main load structure frame's bottom.
Preferably, the main bearing structure frame comprises a hollow rigid light material plate and a rigid light material support rod;
the two same hollow rigid light material plates are crossed and fixed to form a herringbone shape, the rigid light material supporting rod is horizontally arranged between the two hollow rigid light material plates, the crossed fixed ends of the two hollow rigid light material plates are rear ends, and the branched ends of the two hollow rigid light material plates are installed on the multi-rotor unmanned aerial vehicle through bolts.
Preferably, the forward propulsion device is of a propeller structure, and the propeller structure is arranged on the crossed fixed ends of the two hollow rigid light material plates.
Preferably, the first machine wheel is fixedly arranged at the bottom of the crossed fixed end of the two hollow rigid light material plates.
A multi-rotor drone, the multi-rotor drone comprising a tail structure.
Preferably, many rotor unmanned aerial vehicle include the undercarriage, the undercarriage is installed many rotor unmanned aerial vehicle's of many rotors bottom, just the undercarriage be with the wheel structure of first wheel looks adaptation.
According to the technical scheme, compared with the prior art, the utility model discloses a tail structure and multi-rotor unmanned aerial vehicle suitable for multi-rotor unmanned aerial vehicle, firstly, the structure can effectively extend the traditional multi-rotor unmanned aerial vehicle structure backwards, a tail truss structure is introduced, the mechanical model of the structure is greatly changed, the steering arm of the multi-rotor unmanned aerial vehicle is longer than that of the traditional rotorcraft after the tail structure is introduced, under the same steering force, the deflection moment is larger, the steering is more flexible and quicker, the limitation of the structural design of the traditional rotorcraft is broken through, the defects of narrow using gravity center, slow course steering response, poor anti-crosswind stability and the like of the traditional multi-rotor unmanned aerial vehicle are overcome, the structural expansion and the use gravity center range are enlarged, the course stability, the anti-crosswind capability, the improvement of the flight performance of the gravity center and the like are improved, and the development and application of the medium and large heavy-duty multi-rotor unmanned aerial vehicle with wide market prospect are facilitated.
Secondly, this structure changes traditional many rotor unmanned aerial vehicle's support landing mode into wheel year landing mode, has reduced unmanned aerial vehicle landing impact load, can effectively improve organism structure life and guarantee airborne equipment's safety. Meanwhile, the airplane wheel landing system is more convenient for maintenance, management and use of large and medium-sized heavy-load multi-rotor unmanned aerial vehicles entering and exiting the hangar, and matched special vehicles are reduced.
Finally, the utility model discloses add on main load structure frame to advance power device to solve many rotor unmanned aerial vehicle defect that the speed of cruising is low, be favorable to improving aircraft application range and result of use.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required to be used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the provided drawings without creative efforts.
FIG. 1 is a schematic view of a tail structure provided by the present invention;
fig. 2 is a schematic structural diagram of a tail portion provided with a first wheel according to the present invention;
fig. 3 is a schematic diagram illustrating an overall structure of a multi-rotor unmanned aerial vehicle with a tail structure according to the present invention;
fig. 4 is a schematic view of the mechanical principle of the tail structure provided by the present invention;
the airplane comprises a main bearing structure frame 1, a hollow rigid light material plate 101, a rigid light material supporting rod 102, a propeller structure 2, a multi-rotor unmanned aerial vehicle 3, a first airplane wheel 4 and an undercarriage 5.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
The embodiment of the utility model discloses a tail structure suitable for a multi-rotor unmanned aerial vehicle, which is arranged at the tail part of a multi-rotor unmanned aerial vehicle 3, and the bottom of the tail structure is provided with a first engine 4;
the tail structure comprises a main bearing structure frame 1 and a forward propulsion device;
the afterbody at many rotor unmanned aerial vehicle 3 is installed to main load structure frame 1's front end, and to the rear end at main load structure frame 1 at advancing device, to advancing device and many rotor unmanned aerial vehicle 3 electricity be connected, and the bottom at main load structure frame 1 is installed to first wheel 4.
In order to further optimize the technical scheme, the main bearing structure frame 1 comprises a hollow rigid light material plate 101 and a rigid light material support rod 102;
the two same hollow rigid light material plates 101 are crosswise fixed and then form a herringbone shape, the rigid light material support rod 102 is horizontally arranged between the two hollow rigid light material plates 101, the crossed fixed ends of the two hollow rigid light material plates 101 are rear ends, and the branched ends of the two hollow rigid light material plates 101 are installed on the multi-rotor unmanned aerial vehicle 3 through bolts.
It should be noted that, the main bearing structure frame 1 in the present invention can also be a single pipe structure or a single section structure; in addition, the rigid light material in the embodiment can be aluminum alloy, magnesium alloy, carbon fiber or magnesium-aluminum alloy, and the selected material only needs to satisfy the characteristics of light weight and high strength.
In order to further optimize the technical scheme, the forward propulsion device is a propeller structure 2, and the propeller structure 2 is arranged on the crossed fixed ends of the two hollow rigid light material plates 101.
In order to further optimize the technical scheme, the first machine wheel 4 is fixedly arranged at the bottom of the crossed fixed end of the two hollow rigid light material plates 101.
This embodiment still discloses a many rotor unmanned aerial vehicle, and many rotor unmanned aerial vehicle 3 includes the afterbody structure.
In order to further optimize above-mentioned technical scheme, many rotor unmanned aerial vehicle 3 includes undercarriage 5, and undercarriage 5 installs in many rotor unmanned aerial vehicle 3's bottom, and undercarriage 5 is the wheel structure with 4 looks adaptations of first locomotive.
The utility model discloses a theory of operation does:
as shown in fig. 3, 3 structures of traditional many rotor unmanned aerial vehicle extend backward, introduce afterbody truss structure, and its mechanical model has taken place great change, and original center of gravity shifts to a point from the o point, uses the focus scope to become between o ~ a from the o point, can see according to the contrast, and afterbody structure turns to the arm of force ae and turns to the arm of force oc longer than traditional rotor aircraft, under same steering force effect, deflection moment is bigger, turns to more in a flexible way, more rapidly.
At the flight lift F1Lift of the tail rotor F2Under the combined action, the course stability and the crosswind resistance are improved. In crosswind FfUnder the conditions of F1And F2A balancing moment about the centre of gravity a, crosswind FfThe disturbance to the flight of the aircraft will be reduced, thereby enhancing the wind resistance of the aircraft. Under normal conditions, only the resultant lift force F (F)1+F2) Greater than or equal to flight gravity P (including P)1+P2Including fuel, mission loads, etc.), the aircraft may remain in flight at a given altitude.
Wherein: f1-rotor lift, F2-tail rotor lift, Ff-tail attitude force, P1-traditional rotorcraft gravity, P2-newly added tail gravity, F, P-resultant lift and gravity.
In order to further optimize the technical scheme, the first machine wheel 4 is fixedly arranged at the bottom of the crossed fixed end of the two hollow rigid light material plates 101.
The embodiments in the present description are described in a progressive manner, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other. The device disclosed by the embodiment corresponds to the method disclosed by the embodiment, so that the description is simple, and the relevant points can be referred to the method part for description.
The previous description of the disclosed embodiments is provided to enable any person skilled in the art to make or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the invention. Thus, the present invention is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Claims (6)
1. A tail structure suitable for a multi-rotor unmanned aerial vehicle, characterized in that the tail structure is mounted at the tail of the multi-rotor unmanned aerial vehicle (3), and a first wheel (4) is mounted at the bottom of the tail structure;
the tail structure comprises a main bearing structure frame (1) and a forward propulsion device;
the front end of main load structure frame (1) is installed the afterbody of many rotor unmanned aerial vehicle (3), it installs to advancing device main load structure frame's (1) rear end, advance advancing device with many rotor unmanned aerial vehicle (3) electricity are connected, install first wheel (4) main load structure frame's (1) bottom.
2. A tail structure suitable for multi-rotor unmanned aerial vehicle according to claim 1, wherein the main heavy structure frame (1) comprises an openwork rigid lightweight material plate (101) and a rigid lightweight material support rod (102);
the multi-rotor unmanned aerial vehicle is characterized in that the two same hollow rigid light material plates (101) are crosswise fixed and then form a herringbone shape, the rigid light material supporting rod (102) is horizontally arranged between the two hollow rigid light material plates (101), the crossed fixed end of the two hollow rigid light material plates (101) is the rear end, and the branched end of the two hollow rigid light material plates (101) is installed on the multi-rotor unmanned aerial vehicle (3) through a bolt.
3. A tail structure suitable for a multi-rotor unmanned aerial vehicle according to claim 2, wherein the forward propulsion means is a propeller structure (2), and the propeller structure (2) is mounted on the crossed fixed ends of the two hollow rigid lightweight material plates (101).
4. A tail structure suitable for a multi-rotor unmanned aerial vehicle according to claim 2, wherein the first wheel (4) is fixedly installed at the bottom of the crossed fixed end of the two hollow rigid lightweight material plates (101).
5. A multi-rotor drone, characterized in that the multi-rotor drone (3) comprises a tail structure suitable for multi-rotor drones, according to any one of claims 1 to 4.
6. A multi-rotor unmanned aerial vehicle according to claim 5, wherein the multi-rotor unmanned aerial vehicle (3) comprises an undercarriage (5), the undercarriage (5) is mounted on the bottom of the multi-rotor unmanned aerial vehicle (3), and the undercarriage (5) is a wheel structure adapted to the first wheel (4).
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| Application Number | Priority Date | Filing Date | Title |
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| CN201921946915.6U CN211055359U (en) | 2019-11-12 | 2019-11-12 | Tail structure suitable for multi-rotor unmanned aerial vehicle and multi-rotor unmanned aerial vehicle |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201921946915.6U CN211055359U (en) | 2019-11-12 | 2019-11-12 | Tail structure suitable for multi-rotor unmanned aerial vehicle and multi-rotor unmanned aerial vehicle |
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| CN211055359U true CN211055359U (en) | 2020-07-21 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110861763A (en) * | 2019-11-12 | 2020-03-06 | 汉中天行智能飞行器有限责任公司 | Tail structure suitable for multi-rotor unmanned aerial vehicle |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110861763A (en) * | 2019-11-12 | 2020-03-06 | 汉中天行智能飞行器有限责任公司 | Tail structure suitable for multi-rotor unmanned aerial vehicle |
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