Spherical aircraft

Abstract

The utility model discloses a spherical aircraft. The spherical aircraft comprises a main shell, a mounting bracket, a flight module, a control module, a plurality of infrared emitters, an infrared receiver and an airflow sensor, a containing space is formed in the main shell, and a plurality of through holes communicating the containing space with the outside are formed in the outer surface of the main shell. The mounting bracket is mounted in the accommodating space; the flight module control module, the infrared receiver and the airflow sensor are all mounted on the mounting bracket; the plurality of infrared emitters are mounted on the mounting bracket, the infrared emitters are used for reflecting infrared rays to the outside, infrared bands of the infrared emitters with different emitting directions are different, and the infrared light emitting direction of at least one infrared emitter is upward; the infrared light emitting directions of the at least four infrared emitters face the horizontal direction and face the front direction, the rear direction, the left direction and the right direction respectively; according to the technical scheme, the damage risk caused by collision between the aircraft and the obstacle can be effectively reduced.

Description

Technical Field

[0001] The present application relates to the technical field of aircraft, and in particular to a spherical aircraft. Background Art

[0002] Spherical flying machines are very interesting toys. This flying toy can fly, roll, and even flip in the air through remote control or automatic control, bringing a lot of fun to people. However, during flight, the user needs to control the flying direction and speed of the spherical flying toy through a remote control or mobile phone app, otherwise the aircraft is likely to hit obstacles and cause damage. Utility Model Content

[0003] An embodiment of the present application provides a spherical aircraft, which can effectively reduce the risk of damage caused by collision between the aircraft and obstacles.

[0004] The embodiment of the present application provides a spherical aircraft, comprising a main shell, a mounting bracket, a flight module, a control module, a plurality of infrared transmitters, an infrared receiver and an airflow sensor; a containing space is formed inside the main shell, the main shell is spherical, and a plurality of through holes connecting the containing space with the outside are opened on the outer surface; the mounting bracket is installed in the containing space and connected to the main shell; the flight module control module, the infrared receiver and the airflow sensor are all installed on the mounting bracket; a plurality of infrared transmitters are installed on the mounting bracket, the infrared transmitters are used to reflect infrared light to the outside, and the infrared bands of the infrared transmitters with different emission directions are different, at least one of the infrared transmitters emits infrared light in an upward direction, and at least four of the infrared transmitters emit infrared light in a horizontal direction and in four directions, front, back, left and right, respectively;

[0005] The flight module, the plurality of infrared transmitters, the infrared receiver and the airflow sensor are all controlled by the control module, and the control module is used to control the flight direction of the spherical aircraft.

[0006] In a possible implementation, the mounting bracket includes:

[0007] A bracket body, provided with a mounting cavity for mounting the control module and connected to the main housing; and

[0008] A plurality of first connecting arms are connected to the bracket body and are symmetrically arranged relative to the bracket body. One end of the first connecting arm away from the bracket body is connected to the main shell and is provided with an installation groove for installing the infrared emitter.

[0009] In a possible implementation, the first connecting arm includes a connecting portion and a mounting portion connected to each other, the connecting portion is connected to the bracket body, and the mounting portion is provided with the mounting groove;

[0010] Wherein, the main shell is provided with a mounting hole for mounting the mounting part.

[0011] In a possible implementation, a flight module is further included, the flight module includes a plurality of drive components, the drive components include a motor and a rotor connected to a drive shaft of the motor, and the motor is electrically connected to the control module;

[0012] The mounting bracket also includes:

[0013] A plurality of second connecting arms are connected to the bracket body, and an assembly cavity for installing the motor is provided on one of the second connecting arms.

[0014] In a possible implementation, the second connecting arm is provided with a heat dissipation hole connecting the assembly cavity and the outside.

[0015] In a possible implementation, there are four first connecting arms, and two adjacent first connecting arms are vertically arranged;

[0016] There are four second connecting arms, and two adjacent second connecting arms are vertically arranged;

[0017] The first connecting arm and the second connecting arm are both located on the same horizontal plane, and the angle between two adjacent first connecting arms and the second connecting arms is 45°.

[0018] In a possible implementation, the mounting bracket further includes an annular connecting member connected to middle portions of the plurality of first connecting arms and the plurality of second connecting arms.

[0019] In a possible implementation, the drive components are four and are symmetrically arranged relative to the support body, the rotor has a plurality of blades, and the blades are arranged obliquely;

[0020] Wherein, the inclination direction of the blades of the two driving assemblies located on the same straight line is arranged opposite to the inclination direction of the blades of the two driving assemblies located on another straight line.

[0021] In a possible implementation, the mounting bracket includes an upper bracket and a lower bracket, the lower bracket forms part of the bracket body, part of the second connecting arm and the first connecting arm; part of the bracket body and part of the second connecting arm are formed on the lower bracket;

[0022] The upper bracket and the lower bracket enclose the installation cavity and the assembly cavity, and the infrared receiver is installed on the upper bracket.

[0023] In a possible implementation, the control module includes a control board and a battery, and the flight module, the plurality of infrared transmitters, the infrared receiver, and the airflow sensor are all electrically connected to the control board; and / or

[0024] It also includes an LED light strip, which is installed on the main shell.

[0025] Based on the aircraft of the embodiment of the present application, during the flight of the aircraft, the infrared transmitter will emit infrared light to the outside world. When the infrared light emitted by the infrared transmitter in the corresponding position is reflected by the external object, it can be received by the infrared receiver. Since the infrared bands reflected by the external objects in different positions are different, the infrared receiver can receive the corresponding infrared light and transmit the signal to the control board in time. The control board can timely analyze which position has obstacles and control the flight module to fly in the opposite direction to avoid the risk of damage caused by the aircraft encountering obstacles. The present application can effectively sense obstacles in front, behind, left, right and top of the aircraft by arranging the infrared transmitter and the receiver in different directions, so as to adjust the flight direction in time to avoid collision; the present application is also provided with an airflow sensor. When there is an obstacle at the bottom of the aircraft, the obstacle will reflect the wind blown out by the rotor back. After the airflow sensor detects the reflected wind, it will transmit a signal to the control module. The control module determines that there is an obstacle at the bottom and will make an upward flight action at this time. The present application can effectively reduce the risk of damage caused by the collision between the aircraft and the obstacle and extend the service life of the aircraft by timely identifying obstacles and adjusting the flight trajectory. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on the structures shown in these drawings without paying any creative work.

[0027] Figure 1 A schematic diagram of the structure of a spherical aircraft provided in an embodiment of the present application;

[0028] Figure 2 A front view of a spherical aircraft provided in an embodiment of the present application;

[0029] Figure 3 for Figure 2 Sectional view at AA in the middle;

[0030] Figure 4 An exploded view of a spherical aircraft provided in an embodiment of the present application;

[0031] Figure 5 A schematic diagram of the structure after the mounting bracket and the drive assembly provided in the embodiment of the present application are assembled;

[0032] Figure 6 An exploded schematic diagram of a mounting bracket and a drive assembly provided in an embodiment of the present application;

[0033] Description of Figure Numbers:

[0034] 100, main housing; 110, upper housing; 120, lower housing; 130, through hole; 140, mounting hole;

[0035] 200, mounting bracket; 210, upper bracket; 220, lower bracket; 230, mounting cavity; 240, assembly cavity; 250, bracket body; 260, first connecting arm; 261, connecting part; 262, mounting part; 263, mounting groove; 270, second connecting arm; 280, annular connecting member;

[0036] 300, driving assembly; 310, motor; 320, rotor; 400, control module; 510, infrared transmitter; 520, infrared receiver; 600, LED light strip.

[0037] The realization of the purpose, functional features and advantages of this application will be further explained in conjunction with embodiments and with reference to the accompanying drawings. DETAILED DESCRIPTION

[0038] In order to make the objectives, technical solutions and advantages of the present application clearer, the following part will further describe the embodiments of the present application in detail in conjunction with the accompanying drawings.

[0039] When the following description refers to the drawings, unless otherwise indicated, the same numbers in different drawings represent the same or similar elements. The embodiments described in the following exemplary embodiments do not represent all embodiments consistent with the present application. Instead, they are only examples of devices and methods consistent with some aspects of the present application as detailed in the attached claims.

[0040] In the description of the present application, it should be understood that the terms "first", "second", etc. are used for descriptive purposes only and should not be understood as indicating or implying relative importance. For those of ordinary skill in the art, the specific meanings of the above terms in the present application can be understood according to the specific circumstances. In addition, in the description of the present application, unless otherwise specified, "multiple" refers to two or more. "And / or" describes the association relationship of associated objects, indicating that three relationships may exist. For example, A and / or B can represent: A exists alone, A and B exist at the same time, and B exists alone. The character " / " generally indicates that the objects associated before and after are in an "or" relationship.

[0041] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as those commonly understood by those skilled in the art to which this application belongs. The terms used in this specification are only for the purpose of describing specific embodiments and are not intended to limit this application. The term "and / or" used herein includes any and all combinations of one or more of the related listed items.

[0042] See also Figures 1 to 3 The embodiment of the present application proposes a spherical aircraft, including a main shell 100, a mounting bracket 200, a flight module, a control module 400, a plurality of infrared transmitters 510, an infrared receiver 520 and an airflow sensor (not shown in the figure).

[0043] The main shell 100 is spherical, with an accommodating space inside, and a plurality of through holes 130 are provided on the outer surface to connect the outside with the accommodating space. The plurality of through holes 130 are arranged at intervals, and may be circular, rectangular, rhombus, hexagonal, etc. When the main shell 100 is a honeycomb structure, the overall structure of the main shell 100 can evenly disperse pressure and stress when subjected to force, thereby improving the strength of the structure and effectively reducing noise and vibration. In addition, the honeycomb structure can use less material, increase strength, and make the area of ​​the through hole 130 relatively large, thereby ensuring the stability and smoothness of air circulation.

[0044] In some structural forms, the main housing 100 includes an upper housing 110 and a lower housing 120 provided with a plurality of through holes 130, and the upper housing 110 and the lower housing 120 enclose a receiving space. The upper housing 110 and the lower housing 120 are fixed by one or more methods including but not limited to snap-fit, screw connection, and bonding. Here, the specific connection method of the upper housing 110 and the lower housing 120 is not limited in this application.

[0045] Furthermore, a plurality of positioning and fixing columns are arranged in an array at the edge of the upper shell 110, and a plurality of positioning and fixing parts that match the positioning and fixing columns are arranged in an array at the edge of the lower shell 120. The positioning and fixing columns are fixed in the positioning and fixing parts so that the upper shell 110 and the lower shell 120 are buckled and fixed. In addition, threaded holes are arranged on the positioning and fixing columns, and abutment parts are arranged in the positioning and fixing parts. When installed in place, the studs of the screws or bolts pass through the positioning and fixing parts and are fixed in the threaded holes, and the heads of the screws or bolts abut against the abutment parts.

[0046] The mounting bracket 200 is installed in the accommodating space and connected to the main housing 100. The center of the mounting bracket 200 coincides with the center of the main housing 100. Figure 5 and Figure 6 The mounting bracket 200 includes an upper bracket 210 and a lower bracket 220. The upper bracket 210 and the lower bracket 220 are fixed by one or more methods including but not limited to snap-fit, screw connection, and bonding. Here, the present application does not limit the specific connection method of the upper shell 110 and the lower shell 120.

[0047] It can be understood that in order to improve the assembly efficiency of the upper bracket 210 and the lower bracket 220, one of the upper bracket 210 and the lower bracket 220 is provided with a positioning column, and the other is provided with a positioning hole that cooperates with the positioning column, so that the upper bracket 210 and the lower bracket 220 can be positioned when they are assembled and fixed.

[0048] The flight module includes a plurality of drive components 300, please refer to Figure 5 and Figure 6 The driving assembly 300 includes a motor 310 and a rotor 320. The motor 310 is mounted on the mounting bracket 200, and the rotor 320 is mounted on the driving shaft of the motor 310. During flight, the motor 310 drives the rotor 320 to rotate, so that the aircraft can fly.

[0049] See also Figures 4 to 6 , multiple infrared transmitters 510 are installed on the mounting bracket 200, and the infrared transmitters 510 are used to reflect infrared light to the outside. Among them, the infrared bands of the infrared transmitters 510 with different emission directions are different. At least one infrared transmitter 510 emits infrared light in an upward direction, and at least four infrared transmitters 510 emit infrared light in a horizontal direction and in four directions, front, back, left, and right. The infrared receiver 520 is installed on the mounting bracket 200, and is used to receive the infrared light emitted by the infrared transmitter 510 and reflected from the outside. The infrared receiver 520 is installed on the upper bracket 210.

[0050] The airflow sensor is mounted on the mounting bracket 200. The airflow sensor can be mounted on the outer wall of the lower bracket 220. The control module 400 includes a control board and a battery. The flight module, multiple infrared transmitters 510, infrared receivers 520 and airflow sensors are all electrically connected to the control board. The battery is used to provide power to the control board, the flight module, multiple infrared transmitters 510, infrared receivers 520 and the airflow sensor.

[0051] Based on the spherical aircraft of the embodiment of the present application, during the flight of the aircraft, the infrared transmitter 510 will emit infrared light to the outside world. When the infrared light emitted by the infrared transmitter 510 in the corresponding direction is reflected by external objects, it can be received by the infrared receiver 520. Since the infrared bands reflected by external objects in different directions are different, the infrared receiver 520 can receive the corresponding infrared light and transmit the signal to the control board in time. The control board can timely analyze which direction has obstacles and control the flight module to fly in the opposite direction to avoid the risk of damage caused by the aircraft encountering obstacles. The present application can effectively sense obstacles in front, behind, left, right and top of the aircraft by arranging the infrared transmitter 510 and the receiver in different directions, so as to adjust the flight direction in time and avoid collisions.

[0052] In addition, when there is an obstacle at the bottom of the aircraft, the obstacle will reflect the wind blown by the rotor 320 back. After the airflow sensor detects the reflected wind, it will send a signal to the control module 400. The control module 400 determines that there is an obstacle at the bottom and will make an upward flight action. The present application can effectively reduce the risk of damage caused by the collision between the aircraft and the obstacle and extend the service life of the aircraft by timely identifying obstacles and adjusting the flight trajectory.

[0053] To facilitate installation of the control module 400 and the infrared transmitter 510, please refer to Figure 5 and Figure 6 The mounting bracket 200 includes a bracket body 250 and a plurality of first connecting arms 260. The lower bracket 220 forms part of the bracket body 250 and the first connecting arms 260. The upper bracket 210 forms part of the bracket body 250. The upper bracket 210 and the lower bracket 220 enclose a mounting cavity 230. The bracket body 250 is connected to the main housing 100 and is provided with a mounting cavity 230. The battery and the control board are both installed in the mounting cavity 230. The bracket body 250 and the main housing 100 include, but are not limited to, connection forms such as snap-fit, screw connection, and bonding.

[0054] See also Figure 5 and Figure 6, a plurality of first connecting arms 260 are connected to the bracket body 250 and are symmetrically arranged relative to the bracket body 250. One end of the first connecting arm 260 away from the bracket body 250 is connected to the main shell 100, and one end of the first connecting arm 260 away from the bracket body 250 is provided with a mounting groove 263 for mounting the infrared emitter 510. With such an arrangement, the mounting bracket 200 can mount the infrared emitter 510 in the corresponding orientation and can also protect the infrared emitter 510. In addition, the first connecting arm 260 is connected to the main shell 100, which can improve the stability of the connection between the mounting bracket 200 and the main shell 100, making the structure of the aircraft of the present application more stable.

[0055] Further, the first connecting arm 260 includes a connecting portion 261 and a mounting portion 262 connected to each other, the connecting portion 261 is connected to the bracket body 250, and the mounting portion 262 is provided with a mounting groove 263. Among them, the main housing 100 is provided with a mounting hole 140. During installation, the mounting portion 262 is inserted into the mounting hole 140, thereby improving the stability of the connection between the mounting bracket 200 and the main housing 100.

[0056] In some structural forms, see Figure 4 The upper housing 110 is connected with a fixed shaft, which is connected to the upper bracket 210, wherein the infrared emitter 510 disposed on the top of the aircraft is fixed in the fixed shaft. In this way, the infrared emitter 510 can be easily installed, and the stability of the connection between the mounting bracket 200 and the main housing 100 can also be improved.

[0057] In some structural forms, please continue to see Figures 4 to 6 , the drive assembly 300 has four blades, which are symmetrically arranged relative to the bracket body 250, and the rotor 320 has multiple blades, which are arranged obliquely. Among them, the inclination direction of the blades of the two drive assemblies 300 located on the same straight line is opposite to the inclination direction of the blades of the two drive assemblies 300 located on another straight line, that is, the rotation direction of the two rotors 320 located on the same straight line is opposite to the rotation direction of the two rotors 320 located on another straight line. The present application can achieve more precise aircraft attitude control by symmetrically arranging the blades. When turning or changing direction is required, a more precise turning radius and turning angle can be achieved by adjusting the rotation speed and direction of different blades, and a variety of movement modes of the aircraft can be achieved, such as vertical take-off and landing, rolling, pitching and yaw, etc., which increases the maneuverability and adaptability of the aircraft.

[0058] In order to facilitate the installation of the flight module, the mounting bracket 200 also includes a plurality of second connecting arms 270, wherein the upper bracket 210 forms part of the second connecting arm 270, and the lower bracket 220 forms part of the second connecting arm 270. In the present application, a second connecting arm 270 is provided with an assembly cavity 240 for installing a motor 310. The upper bracket 210 and the lower bracket 220 are enclosed to form the assembly cavity 240. One end of the second connecting arm 270 is connected to the bracket body 250, and the other end is connected to the main housing 100, so that it is convenient to install the drive assembly 300 and the assembly stability of the drive assembly 300 can be improved. In some structural forms, the second connecting arm 270 is provided with a heat dissipation hole connecting the assembly cavity 240 and the outside world. In this way, the motor 310 can be cooled to avoid overheating and ensure the normal operation of the equipment.

[0059] In some embodiments, there are four first connecting arms 260, and two adjacent first connecting arms 260 are arranged vertically. There are four second connecting arms 270, and two adjacent second connecting arms 270 are arranged vertically. Among them, the first connecting arm 260 and the second connecting arm 270 are both located on the same horizontal plane, and the angle between the two adjacent first connecting arms 260 and the second connecting arm 270 is 45°. The present application can improve the connection stability between the mounting bracket 200 and the main shell 100 by setting a plurality of first connecting arms 260 and second connecting arms 270, thereby making the overall structure of the aircraft more stable, and can simultaneously meet the installation requirements of the infrared emitter 510 and the drive assembly 300.

[0060] In some embodiments, see Figure 5 and Figure 6 The mounting bracket 200 further includes an annular connecting member 280, which is connected to the middle of the plurality of first connecting arms 260 and the plurality of second connecting arms 270. This arrangement can provide a more balanced support structure and enhance the overall stability.

[0061] The present application embodiment also includes an LED light strip 600, see Figure 4 , the LED light strip 600 is installed on the main housing 100. In some structural forms, the outer surface of the main housing 100 is provided with a receiving groove, and the LED light strip 600 is installed in the receiving groove. The LED light strip 600 can provide a variety of different light colors, so that the quadcopter toy shows a colorful effect at night. The light effect increases the visual appeal of the toy and makes it more eye-catching. Moreover, at night or in a low-light environment, the LED light strip 600 can increase the visibility of the quadcopter toy.

[0062] The same or similar numbers in the drawings of this embodiment correspond to the same or similar parts; in the description of this application, it should be understood that if the terms "up", "down", "left", "right", etc. indicate directions or positional relationships based on the directions or positional relationships shown in the drawings, it is only for the convenience of describing this application and simplifying the description, and does not indicate or imply that the device or element referred to must have a specific direction, be constructed and operated in a specific direction. Therefore, the terms describing the positional relationship in the drawings are only used for illustrative purposes and cannot be understood as limitations on this application. For ordinary technicians in this field, the specific meanings of the above terms can be understood according to specific circumstances.

[0063] The above are only preferred embodiments of the present application and are not intended to limit the present application. Any modifications, equivalent substitutions and improvements made within the spirit and principles of the present application should be included in the protection scope of the present application.

Claims

1. A spherical aircraft, characterized in that: include: A main shell body, with a containing space formed inside, the main shell body is spherical, and a plurality of through holes connecting the containing space with the outside are opened on the outer surface; A mounting bracket, mounted in the accommodating space and connected to the main housing; The flight module, the control module, the infrared receiver and the airflow sensor are all mounted on the mounting bracket; as well as A plurality of infrared emitters are mounted on the mounting bracket, the infrared emitters are used to reflect infrared light to the outside, and the infrared bands of the infrared emitters with different emission directions are different, at least one infrared emitter emits infrared light in an upward direction, and at least four infrared emitters emit infrared light in a horizontal direction and in four directions, front, back, left, and right, respectively; The flight module, the plurality of infrared transmitters, the infrared receiver and the airflow sensor are all controlled by the control module, and the control module is used to control the flight direction of the spherical aircraft.

2. The spherical aircraft according to claim 1, characterized in that: The mounting bracket comprises: A bracket body, provided with a mounting cavity for mounting the control module and connected to the main housing; and A plurality of first connecting arms are connected to the bracket body and are symmetrically arranged relative to the bracket body. One end of the first connecting arm away from the bracket body is connected to the main shell and is provided with an installation groove for installing the infrared emitter.

3. The spherical aircraft according to claim 2, characterized in that: The first connecting arm comprises a connecting portion and a mounting portion connected to each other, the connecting portion is connected to the bracket body, and the mounting portion is provided with the mounting groove; Wherein, the main shell is provided with a mounting hole for mounting the mounting part.

4. The spherical aircraft according to claim 2, characterized in that: Also includes a flight module, the flight module includes a plurality of drive components, the drive components include a motor and a rotor connected to the motor drive shaft, the motor is electrically connected to the control module; The mounting bracket also includes: A plurality of second connecting arms are connected to the bracket body, and an assembly cavity for installing the motor is provided on one of the second connecting arms.

5. The spherical aircraft according to claim 4, characterized in that: The second connecting arm is provided with a heat dissipation hole connecting the assembly cavity and the outside.

6. The spherical aircraft according to claim 4, characterized in that: There are four first connecting arms, and two adjacent first connecting arms are vertically arranged; There are four second connecting arms, and two adjacent second connecting arms are vertically arranged; The first connecting arm and the second connecting arm are both located on the same horizontal plane, and the angle between two adjacent first connecting arms and the second connecting arms is 45°.

7. The spherical aircraft according to claim 6, characterized in that: The mounting bracket further includes an annular connecting member connected to the middle portions of the plurality of first connecting arms and the plurality of second connecting arms.

8. The spherical aircraft according to claim 4, characterized in that: The drive components are four and are symmetrically arranged relative to the support body. The rotor has a plurality of blades, and the blades are arranged in an inclined manner. Wherein, the inclination direction of the blades of the two driving assemblies located on the same straight line is arranged opposite to the inclination direction of the blades of the two driving assemblies located on another straight line.

9. The spherical aircraft according to claim 4, characterized in that: The mounting bracket comprises an upper bracket and a lower bracket, wherein the lower bracket forms part of the bracket body, part of the second connecting arm and the first connecting arm; and part of the bracket body and part of the second connecting arm are formed on the lower bracket; The upper bracket and the lower bracket enclose the installation cavity and the assembly cavity, and the infrared receiver is installed on the upper bracket.

10. The spherical aircraft according to any one of claims 1 to 8, characterized in that: The control module includes a control board and a battery, and the flight module, the plurality of infrared transmitters, the infrared receiver and the airflow sensor are all electrically connected to the control board; and / or It also includes an LED light strip, which is installed on the main shell.

Images