CN213892899U - Modular cross type multi-rotor aircraft - Google Patents
Modular cross type multi-rotor aircraft Download PDFInfo
- Publication number
- CN213892899U CN213892899U CN202022638576.4U CN202022638576U CN213892899U CN 213892899 U CN213892899 U CN 213892899U CN 202022638576 U CN202022638576 U CN 202022638576U CN 213892899 U CN213892899 U CN 213892899U
- Authority
- CN
- China
- Prior art keywords
- rotor
- module
- fuselage
- outer contour
- aircraft
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Abstract
The utility model discloses a modularized crossed multi-rotor aircraft, belonging to the technical field of aviation, wherein the aircraft comprises a fuselage module, and the fuselage module adopts a polygonal outer contour; the aircraft comprises a fuselage module, a plurality of rotor modules, a folding arm module and a landing gear module, wherein the fuselage module is provided with a flight control module above, the rotor modules are correspondingly arranged according to the polygonal outer contour of the fuselage module, the rotor modules are connected with the fuselage module through the folding arm module, and the landing gear module is movably arranged below the folding arm module; the utility model discloses a crossing rotor is as the lifting surface, not only can self-balancing reaction torque, easily realizes the odd number rotor overall arrangement, has the advantage that task strong adaptability, flight stability are good, compact structure, performance are strong moreover. And moreover, the modularized splicing is adopted, so that the manufacturing cost of the aircraft is greatly reduced, and the interchangeability of parts is increased.
Description
Technical Field
The utility model belongs to the technical field of the aviation, specifically indicate a many rotor crafts of modularization staggered.
Background
The field of aviation has emerged at present, and many devices can help people to complete tasks in extreme environments by means of the carrier of the aircraft. Wherein many rotor crafts because its simple structure has and controls advantages such as simple, the reliability is high and the maintenance cost is low, more and more appear in people's daily life, work and amusement. Multi-rotor aircraft, also called multi-axis aircraft, can be seen as a class of helicopters with three or more rotors, which can be subdivided into three rotors, four rotors, six rotors, eight rotors, etc., depending on the number of rotors. It is generally believed that the greater the number of propellers, the smoother the flight and the easier the operation.
Because the single rotor can produce the counter torque when rotatory, consequently, many rotor crafts on the market at present are for offsetting the counter torque, most all adopt the even number rotor overall arrangement that has symmetrical structure, especially with four rotors and six rotor crafts many, this kind of aircraft is every to the rotor can offset respective counter torque each other, also just owing to this reason, the aircraft of odd number rotor overall arrangement is rare, even if there are some, also do not realize the modularization, and organism structural arrangement is not compact, service environment is single, can't use in adverse circumstances such as gust, strong convection current environment, poor stability, and then lead to its work efficiency low, with high costs, the dispatch is loaded down with trivial details, inconvenient transportation. The modularized machine type has great advantages in work efficiency, work cost and dispatching command.
SUMMERY OF THE UTILITY MODEL
In view of the above-mentioned prior art not enough, an object of the utility model is to provide a many rotor crafts of crossing of modularization, adopt the crossing rotor as the lifting surface, not only can self-balancing reaction torque, easily realize odd rotor overall arrangement to solve among the prior art many rotor crafts of odd rotor overall arrangement and be difficult to realize, and the structure is scattered, the not high scheduling problem of modularization degree.
In order to achieve the above purpose, the utility model adopts the following technical scheme:
a modularized cross type multi-rotor aircraft comprises a fuselage module, wherein the fuselage module adopts a polygonal outer contour; the aircraft comprises a fuselage module, a plurality of rotor modules, a folding arm module and a landing gear module, wherein the fuselage module is provided with a flight control module above, the rotor modules are correspondingly arranged according to the polygonal outer contour of the fuselage module, the rotor modules are connected with the fuselage module through the folding arm module, and the landing gear module is movably arranged below the folding arm module; the utility model discloses utilize the fuselage module, fly the control module, folding arm module, the rotor module, undercarriage module integrates respectively into the module, can realize many rotor crafts of fast assembly through simple concatenation module.
Rotor module adopt crossing rotor overall arrangement, include: the device comprises a base, a motor gear, a large gear, a pair of reversing bevel gears, two rotor shafts, a bearing, a propeller hub and a rotor wing; the motor is arranged on the base and provides power for the rotation of the rotor wing, and the bearing is also arranged on the base; the two rotor wing shafts respectively penetrate through the bearings; the motor gear is arranged on the motor shaft and is fastened with the motor shaft through a bolt; the large gear is arranged at the lower end of one of the rotor shafts, the motor gear and the large gear are meshed to form primary speed reduction, and the pair of reversing bevel gears are respectively arranged in the middle parts of the two rotor shafts and are meshed with each other to enable the two rotor shafts to rotate in opposite directions; the hub is mounted on top of the rotor shaft and the rotor is mounted on the hub. The rotor module adopts the crossed dual rotors to provide lift force, and has the advantages of good flight stability, compact structure and strong anti-crosswind capability. The crossed double rotors rotate in the opposite directions synchronously, so that the respective generated reactive torques can be balanced mutually, and no additional mechanism is needed for balancing the reactive torques.
Further, the machine body module comprises an upper machine body plate, a lower machine body plate and a folding fixing piece which are arranged up and down; wherein the folding fixing piece is positioned between the upper plate of the machine body and the lower plate of the machine body and is respectively fixedly connected with the upper plate of the machine body and the lower plate of the machine body through screws,
further, the polygonal outer contour adopted by the fuselage module is a triangular outer contour, a quadrangular outer contour or a pentagonal outer contour, namely the fuselage upper plate, and the fuselage lower plate is a triangular outer contour, a quadrangular outer contour or a pentagonal outer contour. The adopted fuselage modules provide various types of replaceable fuselage modules, and can respectively form multiple rotors with different layouts, for example, the fuselage modules can be replaced by triangular fuselage modules to form a three-rotor aircraft; the replacement is a pentagonal fuselage module that can make up a penta-rotor aircraft. Folding arm module adopts folding mechanism design for many rotor crafts collapsible extension, can reduce the volume under the storage environment, reduces space occupancy.
Further, the folding arm module comprises: the folding rotary part is arranged on the folding arm; the folding rotating part is fixedly arranged at the inner end of the folding arm and is connected with the folding fixing part of the machine body module through a pin, so that the folding arm module can rotate relative to the machine body module; the rotor module mounting seat is fixed at the outer end of the folding arm, a mounting interface butted with the rotor module is reserved on the rotor module mounting seat, and the undercarriage connecting piece is fixedly mounted below the middle part of the folding arm.
Furthermore, the flight control module is arranged above the upper plate of the airplane body.
The utility model discloses with prior art's beneficial effect lie in:
the utility model discloses a crossing rotor is as the lifting surface, not only can self-balancing reaction torque, easily realizes the odd number rotor overall arrangement, has the advantage that task strong adaptability, flight stability are good, compact structure, performance are strong moreover. And moreover, the modularized splicing is adopted, so that the manufacturing cost of the aircraft is greatly reduced, and the interchangeability of parts is increased.
Drawings
Fig. 1 is a schematic view of a modular cross-type quad-rotor aircraft according to embodiment 1 of the present invention;
FIG. 2 is a schematic view of a modular cross-quad rotor embodiment in a collapsed state;
FIG. 3 is a schematic view of a fuselage module of a modular cross-quad rotor embodiment;
figure 4 is a schematic diagram of a modular cross-type multi-rotor aircraft folding arm module of the present invention;
figure 5 is a schematic view of a modular cross-type multi-rotor aircraft rotor module of the present invention;
fig. 6 is a schematic view of a modular cross-type tri-rotor aircraft according to embodiment 2 of the present invention;
fig. 7 is a schematic view of a modular cross-type five-rotor aircraft according to embodiment 3 of the present invention;
in the figure, 1-fuselage module, 2-flight control module, 3-folding arm module, 4-rotor module, 5-landing gear module, 6-fuselage upper plate, 7-fuselage lower plate, 8-folding fixed part, 9-folding arm, 10-folding rotary part, 11-rotor module mounting seat, 12-landing gear connecting part, 13-base, 14-motor, 15-motor gear, 16-large gear, 17-reversing bevel gear, 18-rotor shaft, 19-bearing, 20-hub, 21-rotor.
Detailed Description
In order to facilitate understanding of those skilled in the art, the present invention will be further described with reference to the following examples and drawings, which are not intended to limit the present invention.
In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplification of description, but do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention. The terms "mounted," "connected," and "coupled" are to be construed broadly and may, for example, be fixedly coupled, detachably coupled, or integrally coupled; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art.
Example 1
As shown in fig. 1 to 5, the present invention relates to a modularized cross-type quad-rotor aircraft, which is composed of a fuselage module 1, a flight control module 2, a folding arm module 3, a rotor module 4, a landing gear module 5, etc.;
the fuselage module 1 comprises: the device comprises a machine body upper plate 6, a machine body lower plate 7 and a folding fixing piece 8; the four folding fixing pieces 8 are positioned between the upper machine body plate 6 and the lower machine body plate 7 and are fixedly connected with the upper machine body plate 6 and the lower machine body plate 7 through screws respectively, and the upper machine body plate 6 and the lower machine body plate 7 adopt quadrilateral outlines.
The flight control module 2 is arranged above the upper body plate 6 and is responsible for control and navigation of the aircraft.
In this embodiment, the folding arm modules 3 have four sets, and the single-set folding arm module 3 includes: folding arm 9, folding swivel 10, rotor module mount 11, landing gear attachment 12; the folding rotating part 10 is fixedly arranged at the inner end of the folding arm 9 and is connected with the folding fixing part 8 of the airframe module 1 through a pin, so that the folding arm module 3 can rotate relative to the airframe module 1, the rotor wing module mounting seat 11 is fixed at the outer end of the folding arm 9, a mounting interface butted with the rotor wing module 4 is reserved on the folding arm, and the undercarriage connecting part 12 is fixedly arranged below the middle part of the folding arm 9.
The landing gear modules 5 are four in number, are respectively installed on landing gear connecting pieces 12 of the four sets of folding arm modules 3, and can rotate around the landing gear connecting pieces 12.
Folding arm module 3 adopt folding mechanism design for many rotor crafts collapsible extension, can reduce the volume under the storage environment, reduce space occupancy.
The crossed double rotors rotate in the opposite directions synchronously, so that the respective generated reactive torques can be balanced mutually, and no additional mechanism is needed for balancing the reactive torques.
Example 2
As shown in fig. 6, the main difference between the modularized cross type three-rotor aircraft of the present invention and embodiment 1 is: the fuselage module 1 of the embodiment adopts an upper fuselage plate 6 and a lower fuselage plate 7 with triangular outer outlines;
the body module 1 of the present embodiment is mounted with three folding fixtures 8;
the folding arm modules 3 of the present embodiment have three sets, which are respectively connected to three folding fixing members 8;
the rotor modules 4 of the present embodiment have three sets, and are respectively connected to the rotor module mounting seats 11 of the three sets of folding arm modules 3;
the landing gear module 5 of this embodiment has three pieces, each of which is connected to a landing gear connection 12 of three sets of folding arm modules 3.
Example 3
As shown in fig. 7, the main difference between the modularized cross five-rotor aircraft of the present invention and embodiment 1 is: the fuselage module 1 of the embodiment adopts an upper fuselage plate 6 and a lower fuselage plate 7 with pentagonal outer contours;
the body module 1 of the present embodiment is mounted with five folding fixtures 8;
the folding arm module 3 of the present embodiment has five sets, which are respectively connected with five folding fixing pieces 8;
the rotor modules 4 of the present embodiment are five in number and are respectively connected to the rotor module mounting seats 11 of the five sets of folding arm modules 3;
the landing gear module 5 of this embodiment has five pieces, which are connected to the landing gear connectors 12 of the five sets of folding arm modules 3.
The utility model discloses the specific application route is many, and the above-mentioned only is the preferred embodiment of the utility model, should point out, to ordinary skilled person in this technical field, under the prerequisite that does not deviate from the utility model discloses the principle can also be made a plurality of improvements, for example these improvements of fuselage module also should be regarded as the utility model discloses a protection scope.
Claims (5)
1. The modularized crossed multi-rotor aircraft is characterized by comprising a fuselage module (1), wherein the fuselage module (1) adopts a polygonal outer contour;
the aircraft is characterized in that a flight control module (2) is arranged above the aircraft body module (1), a plurality of groups of rotor modules (4) are correspondingly arranged according to the polygonal outer contour of the aircraft body module (1), the rotor modules (4) are connected with the aircraft body module (1) through folding arm modules (3), and a landing gear module (5) is movably arranged below the folding arm modules (3);
rotor module (4) adopt crossing rotor overall arrangement, include: the rotary wing device comprises a base (13), a motor (14), a motor gear (15), a large gear (16), a pair of reversing bevel gears (17), two rotor wing shafts (18), a bearing (19), a hub (20) and a rotor wing (21);
the motor (14) is arranged on the base (13) and provides power for the rotation of the rotor wing (21), and the bearing (19) is also arranged on the base (13); the two rotor wing shafts (18) respectively penetrate through the bearings (19); the motor gear (15) is arranged on the motor shaft and is fastened with the motor shaft through a bolt; the large gear (16) is arranged at the lower end of one of the rotor shafts (18), the motor gear (15) and the large gear (16) are meshed to form a first-stage speed reduction, and the pair of reversing bevel gears (17) are respectively arranged in the middle of the two rotor shafts (18) and are meshed with each other to enable the two rotor shafts (18) to rotate in opposite directions; a hub (20) is mounted on top of the rotor shaft (18) and a rotor (21) is mounted on the hub (20).
2. A modular cross-type multi-rotor aircraft according to claim 1, wherein the fuselage module (1) comprises a fuselage upper plate (6), a fuselage lower plate (7) and folding fasteners (8) arranged one above the other; the folding fixing piece (8) is positioned between the upper plate (6) and the lower plate (7) of the machine body and is fixedly connected with the upper plate (6) and the lower plate (7) of the machine body through screws respectively.
3. A modular cross-type rotorcraft according to claim 2, wherein the fuselage modules (1) have a polygonal outer contour, such as a triangular outer contour, a quadrangular outer contour, or a pentagonal outer contour, i.e. the upper fuselage plate (6) and the lower fuselage plate (7) have a triangular outer contour, a quadrangular outer contour, or a pentagonal outer contour.
4. A modular cross-type multi-rotor aircraft according to claim 1, characterized in that the folded arm modules (3) comprise: a folding arm (9), a folding rotary member (10), a rotor module mounting base (11), and an undercarriage connecting member (12); the folding rotating piece (10) is fixedly arranged at the inner end of the folding arm (9) and is connected with the folding fixing piece (8) of the machine body module (1) through a pin, so that the folding arm module (3) can rotate relative to the machine body module (1); rotor module mount pad (11) be fixed in folding arm (9) outer end, leave the installation interface with rotor module (4) butt joint above, undercarriage connecting piece (12) fixed mounting is in folding arm (9) middle part below.
5. A modular cross-type multi-rotor aircraft according to claim 1, wherein the flight control module (2) is mounted above the fuselage plate (6).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022638576.4U CN213892899U (en) | 2020-11-16 | 2020-11-16 | Modular cross type multi-rotor aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022638576.4U CN213892899U (en) | 2020-11-16 | 2020-11-16 | Modular cross type multi-rotor aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN213892899U true CN213892899U (en) | 2021-08-06 |
Family
ID=77119230
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202022638576.4U Active CN213892899U (en) | 2020-11-16 | 2020-11-16 | Modular cross type multi-rotor aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN213892899U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113086174A (en) * | 2021-05-11 | 2021-07-09 | 南京壮大智能科技研究院有限公司 | Modular cross type unmanned aerial vehicle and working method thereof |
-
2020
- 2020-11-16 CN CN202022638576.4U patent/CN213892899U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113086174A (en) * | 2021-05-11 | 2021-07-09 | 南京壮大智能科技研究院有限公司 | Modular cross type unmanned aerial vehicle and working method thereof |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN112262075B (en) | Electric tilting rotor aircraft | |
| CN103935511A (en) | Tilt-three-rotor craft | |
| CN103935510A (en) | Tilted four-rotor aircraft | |
| CN103332293A (en) | Tilting double-duct subminiature unmanned plane | |
| CN205675239U (en) | Hybrid power four dual rotation propeller tiltrotor | |
| CN111483590A (en) | Coaxial contra-rotating dual-rotor speed reduction transmission structure | |
| JP2023511703A (en) | Fail-operational VTOL aircraft | |
| CN102267564A (en) | Tiltable main power system adopted for microminiature short-distance/vertically taking off and landing flyer | |
| CN111003166A (en) | Tandem electric double-rotor helicopter and control system thereof | |
| CN213892899U (en) | Modular cross type multi-rotor aircraft | |
| CN111645855B (en) | Diaxon module and use unmanned aerial vehicle of this subassembly | |
| CN101177167A (en) | Power-driven system of aircraft | |
| CN106672223A (en) | Hybrid tilt rotor aircraft with four coaxial contra-rotating propellers | |
| CN102874406A (en) | Crossed type dual-rotor unmanned helicopter | |
| CN113148136A (en) | Unmanned aerial vehicle with fixed wing and many rotors switch function | |
| CN109383759A (en) | A kind of aircraft adjusting flight attitude based on rudder face | |
| CN210971521U (en) | Front and back rotor wing synchronous tilting and hanging disc type rotor wing aircraft | |
| CN106965921A (en) | Fixed-wing and the integral unmanned aerial vehicle of many rotors | |
| CN209064352U (en) | A kind of non-3 points of coaxial multirotor helicopters | |
| CN209567073U (en) | A kind of aircraft adjusting flight attitude based on rudder face | |
| CN108100267B (en) | Motor cluster power system | |
| CN207346096U (en) | A kind of VTOL Fixed Wing AirVehicle of propeller postposition | |
| CN113086174A (en) | Modular cross type unmanned aerial vehicle and working method thereof | |
| CN210122194U (en) | Vertical take-off and landing fixed wing aircraft | |
| CN210455231U (en) | Full-electric tilt rotor unmanned aerial vehicle |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |