CN220786151U - Asymmetric four-rotor aircraft - Google Patents
Asymmetric four-rotor aircraft Download PDFInfo
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- CN220786151U CN220786151U CN202322524325.7U CN202322524325U CN220786151U CN 220786151 U CN220786151 U CN 220786151U CN 202322524325 U CN202322524325 U CN 202322524325U CN 220786151 U CN220786151 U CN 220786151U
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Abstract
The utility model provides an asymmetric four-rotor aircraft, which comprises a cross-shaped aircraft body and 4 ducts, wherein the front and rear directions of the aircraft body are longer, the front end of the aircraft body is provided with a first duct, the rear end of the aircraft body is provided with a second duct, the left and right directions of the aircraft body are shorter, the right end of the aircraft body is provided with a third duct, and the left end of the aircraft body is provided with a fourth duct; the inside motor cabinet that all is provided with of 4 culverts, all be provided with brushless motor on the motor cabinet, first culvert, second culvert, third culvert and fourth culvert correspond first motor, second motor, third motor and fourth motor respectively. The beneficial effects of the utility model are as follows: the utility model provides an asymmetric quadrotor aircraft adopting two groups of different motors and blades, thereby realizing the asymmetry of quadrotors, solving the problem that the two groups of motors and blades with different specifications cannot fly stably because of different generated anti-torque, and having simple operation and convenient use.
Description
Technical Field
The utility model belongs to the field of unmanned aerial vehicles, and particularly relates to an asymmetric four-rotor aircraft.
Background
Currently, four-rotor aircraft on the market are mostly in an X layout, and four motors and blades are all of the same specification. The layout of such a quad-rotor aircraft is demanding in terms of motors and blades, and there are many limitations. The traditional cross layout four-rotor aircraft has the defects of complex control organism and inconvenient operation due to different reverse torque caused by different motor types and different blades. There is a need for a simple-to-operate cross-layout quad-rotor aircraft.
Disclosure of Invention
In view of this, the present utility model aims to propose an asymmetric quadrotor aircraft.
In order to achieve the above purpose, the technical scheme of the utility model is realized as follows:
The asymmetric four-rotor aircraft comprises a cross-shaped aircraft body and 4 ducts, wherein the front and rear directions of the aircraft body are longer, the front end of the aircraft body is provided with a first duct, the rear end of the aircraft body is provided with a second duct, the left and right directions of the aircraft body are shorter, the right end of the aircraft body is provided with a third duct, and the left end of the aircraft body is provided with a fourth duct;
The inside of the 4 ducts is provided with motor bases, the motor bases are provided with brushless motors, and the first duct, the second duct, the third duct and the fourth duct correspond to the first motor, the second motor, the third motor and the fourth motor respectively;
The first motor is provided with a positive paddle, the second motor is provided with a negative paddle, the third motor is provided with a positive paddle, and the fourth motor is provided with a negative paddle. The first motor is the same as the second motor in model and the installed propeller in specification, and the third motor is the same as the fourth motor in model and the installed propeller in specification.
Further, the device also comprises 2 pods, and the pods are arranged on the left side and the right side of the bottom of the fuselage.
Further, a brushless motor is further arranged in the hanging cabin, a fifth motor is arranged on the right side, a sixth motor is arranged on the left side, a positive propeller is arranged on the fifth motor, a negative propeller is arranged on the sixth motor, and the model of the fifth motor is the same as that of the sixth motor, and the installed propeller is of the same specification.
Further, a flying controller placing table and an electronic speed regulator ESC are further arranged on the machine body, a flying controller is installed on the flying controller placing table, and the flying controller is respectively connected with the electronic speed regulator ESC, the first motor, the second motor, the third motor, the fourth motor, the fifth motor and the sixth motor.
Further, the flight controller is an F3 flight controller.
Further, an attitude sensor is arranged in the flight controller.
Further, the machine body comprises an upper machine body and a lower machine body, and the upper machine body is connected with the lower machine body through a stud.
Further, the fuselage is connected to the third duct and the fourth duct by connecting struts.
Further, the length ratio of the length direction to the width direction of the machine body is 2:1.
Further, the first motor and the second motor adopt a 70 mm-diameter bypass QF3027-KV2200, and the propeller adopts a 70 mm-diameter bypass twelve-leaf blade;
The third motor and the fourth motor adopt Langyu third generation X2220-KV2200, and the propeller adopts GEMFAN Qianfeng 7035 three-blade propellers;
The model of the duct motor suit adopted by the fifth motor and the sixth motor is a duct QF1611-KV5000 with the diameter of 30mm, and the propeller adopts six blades with the diameter of 30 mm.
The utility model has the advantages and positive effects that: by adopting the technical scheme, the utility model provides the asymmetric quadrotor aircraft adopting the two groups of different motors and the paddles, thereby realizing the asymmetry of the quadrotor and solving the problem that the two groups of motors and the paddles with different specifications cannot fly stably because of different generated anti-torque. Solves the problems of the prior art that the requirements on the take-off and landing environment are harsh, the fixed point reconnaissance is impossible, the maneuvering performance is low and the working efficiency is low. The operation is simple and the use is convenient.
Drawings
In order to more clearly illustrate the embodiments of the utility model or the technical solutions in the prior art, the drawings that are required in the embodiments or the description of the prior art will be briefly described, it being obvious that the drawings in the following description are only embodiments of the utility model and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic diagram of the structure of the present utility model;
Fig. 2 is a top view of the present utility model.
In the figure:
1-a first duct; 2-a second duct; 3-a third duct; 4-fourth duct; 5-a fifth motor; 6-a sixth motor; 7-a fuselage; 8-a flight controller mounting table; 9-connecting struts; 10-flight controller; 11-electronic speed governor ESC
Detailed Description
The following description of the embodiments of the present utility model will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present utility model, but not all embodiments. All other embodiments, which can be made by a person skilled in the art without any inventive effort, based on the embodiments of the present utility model are within the scope of the protection of the present utility model, and the embodiments of the present utility model and the features of the embodiments can be combined with each other without conflict.
In the following description, numerous specific details are set forth in order to provide a thorough understanding of the present utility model, but the present utility model may be practiced in other ways other than those described herein, and persons skilled in the art will readily appreciate that the present utility model is not limited to the specific embodiments disclosed below.
In the following, the present utility model will be described in detail with reference to the drawings, wherein the sectional view of the device structure is not partially enlarged to general scale for the convenience of description, and the drawings are only illustrative, and should not limit the scope of the present utility model. In addition, the three-dimensional dimensions of length, width and height should be included in actual fabrication.
In the description of the present utility model, it should be understood that the terms "center", "longitudinal", "lateral", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, are merely for convenience in describing the present utility model and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present utility model. Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first", "a second", etc. may explicitly or implicitly include one or more such feature. In the description of the present utility model, unless otherwise indicated, the meaning of "a plurality" is two or more.
In the description of the present utility model, it should be noted that, unless explicitly specified and limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be either fixedly connected, detachably connected, or integrally connected, for example; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the present utility model can be understood by those of ordinary skill in the art in a specific case.
As shown in fig. 1 and 2, the utility model comprises a cross-shaped machine body 7 and 4 ducts, wherein the machine body is relatively long in the front-rear direction, the front end is provided with a first duct 1, the rear end is provided with a second duct 2, the machine body is relatively short in the left-right direction, the right end is provided with a third duct 3, and the left end is provided with a fourth duct 4; the length ratio of the length direction to the width direction of the machine body is 2:1.
The inside of the 4 ducts is provided with motor bases, the motor bases are provided with brushless motors, and the first duct 1, the second duct 2, the third duct 3 and the fourth duct 4 correspond to the first motor, the second motor, the third motor and the fourth motor respectively;
The first motor is provided with a positive paddle, the second motor is provided with a negative paddle, the third motor is provided with a positive paddle, and the fourth motor is provided with a negative paddle.
The types of the first motor and the second motor are the same as the types of the adopted propellers, so that the sizes of the counter torque generated by the two brushless motors in the flat flight state are the same. The first motor and the second motor adopt a 70 mm-diameter bypass QF3027-KV2200, and the screw propeller adopts a 70 mm-diameter bypass twelve-leaf blade.
The model of the third motor and the model of the fourth motor are the same as the specifications of the adopted propellers, so that the sizes of the counter torque generated by the two brushless motors in the flat flight state are the same. The third motor and the fourth motor adopt Langyu third generation X2220-KV2200, and the propeller adopts GEMFAN Qianfeng 7035 three-blade propeller.
And 2 pods mounted on the left and right sides of the bottom (near the middle) of the fuselage.
The inside of the hanging cabin is also provided with a brushless motor, the right side is provided with a fifth motor 5, the left side is provided with a sixth motor 6, the fifth motor 5 is provided with a positive paddle, and the sixth motor 6 is provided with a negative paddle. The fifth motor 5 is the same as the sixth motor 6 in type and propeller specifications, so that the reverse torque generated by the two brushless motors in the flat flight state is the same. Thrust forward of the aircraft cruising is provided by the fifth and sixth electric machines. The model of the duct motor suit adopted by the fifth motor and the sixth motor is a duct QF1611-KV5000 with the diameter of 30mm, and the propeller adopts six blades with the diameter of 30 mm.
The aircraft body is also provided with a flight controller placing table 8 and an electronic speed regulator ESC 11, an F3 flight controller 10 is installed on the flight controller placing table 8, an attitude sensor is arranged in the aircraft body, and the F3 flight controller 10 is respectively connected with the electronic speed regulator ESC 11, the first motor, the second motor, the third motor, the fourth motor, the fifth motor 5 and the sixth motor 6.
The machine body 7 comprises an upper machine body and a lower machine body, and the upper machine body and the lower machine body are connected through studs. The fuselage 7 is connected to the third and fourth ducts by connecting struts 9.
When the aircraft performs head-up pitching, the first motor accelerates, the thrust is increased, and the torsion is increased; the second motor is decelerated, the thrust is reduced, the torsion is reduced, therefore, the aircraft is pitching forward, and the fuselage is yawed clockwise due to different counter-torque generated by the blades at the front side and the rear side. In order to correct the influence of the positive torque, the fifth motor is required to accelerate, the sixth motor is required to decelerate, and the airplane is corrected in the anticlockwise direction. The fifth motor accelerates and the torsion increases; the sixth motor decelerates and the torque decreases, so the aircraft rolls left. In order to correct the attitude of the aircraft, the third motor is required to be decelerated, the thrust is reduced, and the torsion is reduced; and the fourth motor accelerates, the thrust is increased, the torsion is increased, the aircraft rolls leftwards, and the aircraft yaw anticlockwise due to different reverse torsion, so that the correction of the aircraft attitude is further accelerated. When the aircraft is pitching low, the correction of the aircraft attitude can be expedited, as opposed to that described above.
When the aircraft does left yaw motion, the fifth motor accelerates, the thrust is increased, and the torsion is increased; the sixth motor is decelerated, the thrust is reduced, the torsion is reduced, therefore, the aircraft yaw leftwards, and the airframe rolls leftwards due to different counter torque generated by the blades at the left side and the right side. In order to correct the influence of the positive torque, the third motor is required to reduce the speed and the thrust is reduced; and the fourth motor accelerates, the torsion increases, and the airplane rolls right. And the torque of the third motor is reduced, and the torque of the fourth motor is increased, so that the airplane is yawed anticlockwise and is consistent with the left yaw direction, and the correction of the airplane attitude is further accelerated. When the aircraft does right yaw motion, the method is opposite to the method and can accelerate the correction of the aircraft posture.
When the aircraft does left roll motion, the third motor accelerates, the thrust is increased, and the torsion is increased; the fourth motor is decelerated, the thrust is reduced, the torsion is reduced, therefore, the aircraft rolls leftwards, and the machine body is yaw clockwise due to different counter torque generated by the blades at the left side and the right side. In order to correct the influence of the positive torque, a fifth motor is required to accelerate, so that the thrust is increased; and the sixth motor is decelerated, the thrust is reduced, and the airplane does anticlockwise yaw. And the torque force of the fifth motor is increased; the torsion of the sixth motor is reduced, so that the aircraft rolls leftwards, and the correction of the aircraft attitude is further accelerated. When the aircraft makes right roll motions, the method is opposite to the method and can accelerate the correction of the aircraft posture.
The utility model provides an asymmetric quadrotor aircraft adopting two groups of different motors and blades, thereby realizing the asymmetry of quadrotors and solving the problem that the two groups of motors and blades with different specifications cannot fly stably because of different generated anti-torque. Solves the problems of the prior art that the requirements on the take-off and landing environment are harsh, the fixed point reconnaissance is impossible, the maneuvering performance is low and the working efficiency is low.
The foregoing describes the embodiments of the present utility model in detail, but the description is only a preferred embodiment of the present utility model and should not be construed as limiting the scope of the utility model. All equivalent changes and modifications within the scope of the present utility model are intended to be covered by the present utility model.
Claims (10)
1. An asymmetric quadrotor aircraft, characterized in that: the cross-shaped machine body and 4 ducts, wherein the front direction and the rear direction of the machine body are longer, the front end of the machine body is provided with a first duct, the rear end of the machine body is provided with a second duct, the left direction and the right direction of the machine body are shorter, the right end of the machine body is provided with a third duct, and the left end of the machine body is provided with a fourth duct;
The inside of the 4 ducts is provided with motor bases, the motor bases are provided with brushless motors, and the first duct, the second duct, the third duct and the fourth duct correspond to the first motor, the second motor, the third motor and the fourth motor respectively;
the first motor is provided with a positive paddle, the second motor is provided with a negative paddle, the third motor is provided with a positive paddle, and the fourth motor is provided with a negative paddle; the first motor is the same as the second motor in model and the installed propeller in specification, and the third motor is the same as the fourth motor in model and the installed propeller in specification.
2. The asymmetric four-rotor aircraft of claim 1, wherein: the device also comprises 2 pods, wherein the pods are arranged on the left side and the right side of the bottom of the fuselage.
3. The asymmetric four-rotor aircraft of claim 2, wherein: the inside of the hanging cabin is also provided with a brushless motor, the right side is provided with a fifth motor, the left side is provided with a sixth motor, the fifth motor is provided with a positive propeller, the sixth motor is provided with a negative propeller, and the model of the fifth motor is the same as that of the sixth motor and the installed propeller.
4. The asymmetric four-rotor aircraft of claim 1, wherein: the aircraft body is also provided with a flight controller placing table and an electronic speed regulator ESC, the flight controller placing table is provided with a flight controller, and the flight controller is respectively connected with the electronic speed regulator ESC, the first motor, the second motor, the third motor, the fourth motor, the fifth motor and the sixth motor.
5. The asymmetric four-rotor aircraft of claim 4, wherein: the flight controller is an F3 flight controller.
6. The asymmetric four-rotor aircraft of claim 4, wherein: and an attitude sensor is arranged in the flight controller.
7. The asymmetric four-rotor aircraft of claim 1, wherein: the machine body comprises an upper machine body and a lower machine body, and the upper machine body is connected with the lower machine body through a stud.
8. The asymmetric four-rotor aircraft of claim 1, wherein: the fuselage is connected with the third duct and the fourth duct through connecting struts.
9. The asymmetric four-rotor aircraft of claim 1, wherein: the length ratio of the length direction to the width direction of the machine body is 2:1.
10. An asymmetric quadrotor aircraft as claimed in claim 3, wherein: the first motor and the second motor adopt a 70 mm-diameter bypass QF3027-KV2200, and the propeller adopts a 70 mm-diameter bypass twelve-leaf blade;
The third motor and the fourth motor adopt Langyu third generation X2220-KV2200, and the propeller adopts GEMFAN Qianfeng 7035 three-blade propellers;
The model of the duct motor suit adopted by the fifth motor and the sixth motor is a duct QF1611-KV5000 with the diameter of 30mm, and the propeller adopts six blades with the diameter of 30 mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322524325.7U CN220786151U (en) | 2023-09-18 | 2023-09-18 | Asymmetric four-rotor aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322524325.7U CN220786151U (en) | 2023-09-18 | 2023-09-18 | Asymmetric four-rotor aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN220786151U true CN220786151U (en) | 2024-04-16 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202322524325.7U Active CN220786151U (en) | 2023-09-18 | 2023-09-18 | Asymmetric four-rotor aircraft |
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|---|---|
| CN (1) | CN220786151U (en) |
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2023
- 2023-09-18 CN CN202322524325.7U patent/CN220786151U/en active Active
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