CN217456362U

CN217456362U - Driving mechanism and aircraft

Info

Publication number: CN217456362U
Application number: CN202220220451.6U
Authority: CN
Inventors: 李治国
Original assignee: Hanwang Technology Co Ltd
Current assignee: Hanwang Technology Co Ltd
Priority date: 2022-01-26
Filing date: 2022-01-26
Publication date: 2022-09-20
Anticipated expiration: 2032-01-26

Abstract

The disclosure relates to the technical field of aircrafts, in particular to a driving mechanism and an aircraft. The drive mechanism that this disclosure provided installs on the aircraft, drive mechanism includes motor, impeller and drive mechanism. The motor is respectively connected with the impeller and the transmission mechanism, so that the motor drives the transmission mechanism to move and simultaneously drives the impeller to rotate, airflow generated by rotation of the impeller flows backwards and blows to electrical elements in the aircraft, the flow of the airflow can be accelerated through the impeller, the accelerated airflow carries out forced convection heat dissipation on the electrical elements, the heat dissipation performance of the aircraft is improved, the impeller is arranged on an output shaft of the motor, the flow velocity of the airflow in an inner cavity is accelerated, and the heat exchange efficiency of an axial air duct formed in the casing is improved.

Description

Driving mechanism and aircraft

Technical Field

The present disclosure relates to the field of aircraft technology, and in particular, to a driving mechanism and an aircraft.

Background

In recent years, aircraft have become more and more popular. Existing aircraft are largely classified into winged aircraft and wingless aircraft. Winged aircraft include fixed wing aircraft such as airplanes and gliders and moving wing aircraft such as rotary wing aircraft and ornithopters.

The heat dissipation effect of the traditional aircraft is general when the aircraft is used, and after the aircraft flies for a long time, the heat inside the aircraft is accumulated and is difficult to dissipate, so that the service life of the aircraft is influenced.

SUMMERY OF THE UTILITY MODEL

In order to solve the technical problem, the present disclosure provides a driving mechanism and an aircraft.

A first aspect of the present disclosure provides a drive mechanism for mounting on an aircraft, the drive mechanism comprising: the motor, the impeller and the transmission mechanism;

the motor is respectively connected with the impeller and the transmission mechanism, so that the motor drives the transmission mechanism to move and simultaneously drives the impeller to rotate.

Further, the motor includes an output shaft;

the impeller and the transmission mechanism are both arranged on the output shaft, and the output shaft is used for driving the impeller and the transmission mechanism to move simultaneously.

Further, the motor comprises a stator and an outer rotor, and the outer rotor is sleeved on the stator;

the outer rotor, the impeller and the output shaft are of an integrated structure.

Furthermore, the number of the impellers is multiple, and the impellers are uniformly arranged at intervals along the circumferential direction of the output shaft.

Furthermore, the transmission mechanism comprises a driving gear, and the driving gear and the output shaft are of an integrated structure.

A second aspect of the present disclosure provides an aircraft comprising a housing and said drive mechanism;

the shell is provided with an inner cavity, the driving mechanism is arranged in the inner cavity, the inner cavity is provided with a control unit and a power supply structure, and the driving mechanism, the control unit and the power supply structure are sequentially arranged along the length direction of the shell;

wherein the impeller is disposed opposite the control unit.

Furthermore, the shell is provided with a mounting hole, and the mounting hole is provided with a camera assembly;

the camera component is provided with an air inlet, the top of the shell is provided with a first air outlet, and air flow enters the inner cavity from the air inlet and flows to the control unit through the driving mechanism and then is discharged from the first air outlet.

Furthermore, a second air outlet and a third air outlet are arranged on both sides of the shell, and the second air outlet and the third air outlet are arranged at intervals;

the second air outlet is arranged on two sides of the shell corresponding to the control unit, and the third air outlet is arranged on two sides of the shell corresponding to the power supply structure.

Furthermore, at least one side of the shell is provided with a plurality of second air outlets, and the second air outlets are arranged at intervals along the length direction of the shell.

Furthermore, at least one side of the shell is provided with a plurality of third air outlets, and the third air outlets are arranged along the length direction of the shell at intervals.

Compared with the prior art, the technical scheme provided by the embodiment of the disclosure has the following advantages:

the drive mechanism that this disclosed embodiment provided installs on the aircraft, and drive mechanism includes motor, impeller and drive mechanism. The motor is respectively connected with the impeller and the transmission mechanism, so that the motor drives the transmission mechanism to move and simultaneously drives the impeller to rotate, the air flow generated by the rotation of the impeller flows backwards and blows towards the electrical elements in the aircraft, the flow of the air flow can be accelerated through the impeller, the accelerated air flow carries out forced convection heat dissipation on the electrical elements, the heat dissipation performance of the aircraft is improved, the impeller is arranged on an output shaft of the motor, the flow speed of the air flow in the inner cavity is accelerated, and the heat exchange efficiency of an axial air duct formed in the shell is improved.

Drawings

The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments consistent with the present disclosure and together with the description, serve to explain the principles of the disclosure.

In order to more clearly illustrate the embodiments or technical solutions in the prior art of the present disclosure, the drawings used in the description of the embodiments or prior art will be briefly described below, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without inventive exercise.

FIG. 1 is an exploded view of an aircraft according to an embodiment of the disclosure;

FIG. 2 is a cross-sectional view of an aircraft according to an embodiment of the disclosure;

FIG. 3 is a top view of an aircraft according to an embodiment of the disclosure;

FIG. 4 is a schematic side view illustration of an aircraft according to an embodiment of the disclosure;

FIG. 5 is a schematic illustration of another side-view configuration of the aircraft according to the disclosed embodiment;

FIG. 6 is a schematic illustration of the aircraft of an embodiment of the present disclosure with the hull removed;

FIG. 7 is a schematic structural diagram of a driving mechanism according to an embodiment of the disclosure;

fig. 8 is a cross-sectional view of a drive mechanism according to an embodiment of the disclosure.

Reference numerals: 11. a machine head; 111. mounting holes; 12. a body; 121. a first air outlet; 122. a second air outlet; 123. a third air outlet; 13. a left housing; 14. a right housing; 15. a fuselage frame; 16. a neck portion; 2. a camera assembly; 215. an air inlet; 22. a protective frame; 221. a boss portion; 3. a drive mechanism; 31. a motor; 311. an output shaft; 312. a stator; 313. an outer rotor; 32. an impeller; 33. a transmission mechanism; 4. a control unit; 5. a power supply structure.

Detailed Description

In order that the above objects, features and advantages of the present disclosure may be more clearly understood, aspects of the present disclosure will be further described below. It should be noted that the embodiments and features of the embodiments of the present disclosure may 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 disclosure, but the present disclosure may be practiced in other ways than those described herein; it is to be understood that the embodiments disclosed in the specification are only a few embodiments of the present disclosure, and not all embodiments.

As shown in fig. 6 to 8, the drive mechanism 3 provided in the embodiment of the present disclosure is mounted on an aircraft, and the drive mechanism 3 includes: a motor 31, an impeller 32 and a transmission mechanism 33; the motor 31 is respectively connected with the impeller 32 and the transmission mechanism 33, so that the motor 31 drives the transmission mechanism 33 to move and simultaneously drives the impeller 32 to rotate, airflow generated by rotation of the impeller 32 can well flow backwards and blow the airflow to electrical elements in an inner cavity of the aircraft, the airflow can flow at an accelerated speed after passing through the impeller 32, the accelerated airflow carries out forced convection heat dissipation on the electrical elements, and the heat dissipation performance of the aircraft is improved. The impeller 32 is arranged on the output shaft 311 of the motor 31, so that the flow velocity of the air flow in the inner cavity is accelerated, and the heat exchange efficiency of the axial air duct formed in the shell is improved.

In some embodiments, the motor 31 includes an output shaft 311; the impeller 32 and the transmission mechanism 33 are both arranged on the output shaft 311, the output shaft 311 is used for driving the impeller 32 and the transmission mechanism 33 to move simultaneously, so that when the output shaft 311 of the motor 31 rotates, the impeller 32 is driven to rotate and the transmission mechanism 33 is driven to move, the consumption of electric energy is not excessively increased, the efficiency of the motor is increased, the air flow in the inner cavity is increased in the operation process of the motor 31, and the heat dissipation efficiency is improved.

In some specific embodiments, the motor 31 includes a stator 312 and an outer rotor 313, the outer rotor 313 is sleeved on the stator 312, the outer rotor 313, the impeller 32 and the output shaft 311 are of an integrated structure, when the external rotor is electrified, the stator 312 of the motor 31 does not rotate, the outer rotor 313 of the motor 31 rotates at a high speed, a driving gear fixedly connected to the output shaft 311 of the motor 31 drives the wings to flap through a power transmission component, and the impeller 32 fixedly connected to the shaft of the motor 31 generates wind along the length direction of the casing, so as to dissipate heat for the control unit 4 and the power supply structure 5.

In some specific embodiments, the number of the impellers 32 is multiple, the plurality of impellers 32 are uniformly arranged along the circumferential direction of the output shaft 311 at intervals, when the impellers 32 rotate, air flow can flow through the middles of the impellers 32, circulation of the air flow is facilitated, heat dissipation efficiency can be improved, stable and smooth operation of the motor 31 is guaranteed, and meanwhile the service life of each internal component is prolonged.

In some embodiments, the transmission mechanism 33 includes a driving gear, and the driving gear is integrated with the output shaft 311.

Alternatively, the transmission 33 may include the frame of the body 12, a gear train, a linkage, and a swing bracket. The body 12 frame may be mounted to the housing for securing the transmission 33 to the housing. The gear train may be mounted to the frame of the body 12 and driven by a motor 31. The gear set can also be in transmission connection with the connecting rod. For example, one of the gears in the set may be connected to one end of a link such that rotation of the gear causes the link to move therewith. The other end of the connecting rod can be in pivot connection with the swinging bracket, so that the swinging bracket can move along with the swinging bracket under the driving of the connecting rod. In addition, the swing bracket can be pivotally connected with the fixed bracket so that the swing bracket is supported. The wings of the aircraft can be connected with the swing bracket, so that the wings are driven by the swing bracket to flap up and down. As shown in fig. 1-6, an aircraft provided by the embodiment of the present disclosure includes a housing and a drive mechanism 3; the casing is formed with the inner chamber, and actuating mechanism 3 sets up in the inner chamber, and the inner chamber is equipped with control unit 4 and power structure 5, and actuating mechanism 3, control unit 4 and power structure 5 set gradually along the length direction of casing. The impeller 32 is disposed opposite to the control unit 4, so that the air flow generated by the rotation of the impeller 32 flows backward well and blows toward the control unit 4. In this embodiment, the casing can form an axial air duct, the air flow can flow at an increased speed after passing through the impeller 32, the accelerated air flow performs forced convection heat dissipation on the control unit 4 and the power supply structure 5, the heat dissipation performance of the control unit 4 and the power supply structure 5 is improved, the impeller 32 is arranged on the output shaft 311 of the motor 31, the flow velocity of the air flow in the inner cavity is increased, and the heat exchange efficiency of the axial air duct formed in the casing is improved.

In some specific embodiments, in order to acquire the peripheral scene of the flight process of the aircraft, a camera assembly is installed on the aircraft to acquire an image of the peripheral environment of the aircraft. Camera subassembly 2 sets up in the neck 16 of aircraft, and the neck 16 of aircraft is equipped with the mounting hole 111 of installation camera subassembly 2, and camera subassembly 2 includes mount table and camera, and the camera is used for gathering all ring edge borders image, and the downward sloping during the camera installation can shoot the environment of aircraft below better for the overall arrangement of camera is more reasonable. The camera can be 360 degrees panorama cameras, can make camera and mount table threaded connection, fastener be connected, bond etc..

In some embodiments, to improve heat dissipation inside the aircraft, the aircraft is provided with an air inlet and an air outlet. The camera assembly 2 is provided with an air inlet 215, the top of the housing is provided with a first air outlet 121, and the air flow enters the inner cavity from the air inlet 215, flows to the control unit 4 through the driving mechanism 3 and is then discharged from the first air outlet 121. An airflow channel can be formed between the air inlet 215 and the first air outlet 121, airflow enters the inner cavity from the air inlet 215, flows to the control unit 4 through the driving mechanism 3 and then is discharged from the first air outlet 121, and in the flight process of the aircraft, the inner cavity can form heat dissipation airflow, and the airflow enters the inner cavity from the air inlet 215, flows to the control unit 4 through the driving mechanism 3 and then is discharged from the first air outlet 121, so that heat dissipation of internal elements of the aircraft is facilitated, hot airflow in the inner cavity is discharged, particularly, the heat dissipation speed of the driving mechanism 3 and the control unit 4 is increased, the heat dissipation effect is improved, the possibility of damage of the internal elements of the aircraft due to overheating is reduced, and the service life of the aircraft is prolonged.

In addition, the air resistance can be reduced through the air flow channel formed between the air inlet 215 and the first air outlet 121.

In the embodiment of the present disclosure, the number of the air inlets 215 is at least one, and may be set to be plural according to needs.

The first outlet port 121 may be provided in plurality. When the first air outlets 121 are two or more, the two or more first air outlets 121 are arranged at intervals along the length direction of the aircraft, so that the heat dissipation performance of the aircraft is further improved.

In some embodiments, the first air outlet 121 is disposed at the top of the housing, so that the airflow can be smoothly discharged from the first air outlet 121 after entering from the air inlet 215, thereby facilitating heat dissipation of the electronic devices inside the aircraft and reducing wind resistance. The first air outlet 121 is disposed opposite to the control unit 4, which is beneficial to heat dissipation of the control unit 4. The first air outlet 121 and the control unit 4 are arranged oppositely, so that air flow enters the inner cavity from the air inlet 215, flows to the control unit 4 through the driving mechanism 3 and then is discharged from the first air outlet 121, heat generated by the driving mechanism 3 and the control unit 4 can be discharged from the first air outlet 121, the possibility of damage of the driving mechanism 3 and the control unit 4 due to overheating is reduced, and the service life of the aircraft is prolonged.

In some specific embodiments, the second air outlet 122 and the third air outlet 123 are disposed on both sides of the housing, and the second air outlet 122 and the third air outlet 123 are disposed at intervals; the second air outlet 122 is disposed on two sides of the housing corresponding to the control unit 4, and the third air outlet 123 is disposed on two sides of the housing corresponding to the power supply structure 5.

The second air outlet 122 is disposed on two sides of the housing corresponding to the control unit 4, so that the air flow enters the inner cavity from the air inlet 215, flows through the driving mechanism 3, flows to the control unit 4, and is discharged from the second air outlet 122. In the flying process of the aircraft, the inner cavity can form heat dissipation airflow, the airflow enters the inner cavity from the air inlet 215, flows to the control unit 4 through the driving mechanism 3 and then is discharged from the second air outlets 122 on two sides, so that heat dissipation of internal elements of the aircraft is facilitated, hot airflow in the inner cavity is discharged, the heat dissipation speed of the control unit 4 is particularly accelerated, the heat dissipation effect is improved, the possibility of damage of the internal elements of the aircraft due to overheating is reduced, and the service life of the aircraft is prolonged.

Optionally, the number of the second air outlets 122 on each side of the housing is at least one, and may be set to be multiple according to needs. When the second air outlets 122 are two or more than two, the two or more than two second air outlets 122 are arranged at intervals along the length direction of the aircraft, so that the heat dissipation performance of the aircraft is further improved.

The third air outlet 123 is disposed on two sides of the housing corresponding to the power supply structure 5, so that the air flow enters the inner cavity from the air inlet 215 and flows to the driving mechanism 3, the control unit 4 and the power supply structure 5, and then is discharged from the third air outlet 123. In the flying process of the aircraft, the inner cavity can form heat dissipation airflow, the airflow enters the inner cavity from the air inlet 215, flows to the control unit 4 and the power supply structure 5 through the driving mechanism 3 and then is discharged from the third air outlets 123 on two sides, heat dissipation of internal elements of the aircraft is facilitated, hot airflow in the inner cavity is discharged, particularly, the heat dissipation speed of the power supply structure 5 is accelerated, the heat dissipation effect is improved, the possibility of damage of the internal elements of the aircraft due to overheating is reduced, and the service life of the aircraft is prolonged.

Optionally, the number of the third air outlets 123 on each side of the housing is at least one, and may be set to be multiple according to needs. When the third air outlets 123 are two or more, the two or more third air outlets 123 are arranged at intervals along the length direction of the aircraft, so that the heat dissipation performance of the aircraft is further improved.

When the housing is respectively provided with the first outlet 121, the two sets of second outlets 122 and the two sets of third outlets 123. After entering from the air inlet 215, the airflow forms a plurality of strands of airflow which are respectively discharged from the first air outlet 121, the two groups of second air outlets 122 and the two groups of third air outlets 123, so that the heat dissipation effect is improved, the possibility of damage of internal elements of the aircraft due to overheating is reduced, meanwhile, the wind resistance is reduced, and the service life of the aircraft is prolonged.

It is noted that, in this document, relational terms such as "first" and "second," and the like, may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of other identical elements in a process, method, article, or apparatus that comprises the element.

The foregoing is merely a detailed description of the disclosure that enables one skilled in the art to understand or practice the disclosure. 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 disclosure. Thus, the present disclosure 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

1. A drive mechanism for mounting on an aircraft, the drive mechanism comprising: a motor (31), an impeller (32) and a transmission mechanism (33);

the motor (31) is respectively connected with the impeller (32) and the transmission mechanism (33), so that the motor (31) drives the transmission mechanism (33) to move and simultaneously drives the impeller (32) to rotate;

the motor (31) comprises an output shaft (311);

the impeller (32) and the transmission mechanism (33) are both arranged on the output shaft (311), and the output shaft (311) is used for driving the impeller (32) and the transmission mechanism (33) to move simultaneously.

2. The drive mechanism according to claim 1, wherein the electric machine (31) comprises a stator (312) and an outer rotor (313), the outer rotor (313) being sleeved on the stator (312);

the outer rotor (313), the impeller (32) and the output shaft (311) are of an integrated structure.

3. The drive mechanism according to claim 1, wherein the number of the impellers (32) is plural, and the plural impellers (32) are arranged evenly and at intervals in a circumferential direction of the output shaft (311).

4. The drive mechanism as recited in claim 1, characterized in that the transmission mechanism (33) comprises a drive gear, which is of unitary construction with the output shaft (311).

5. An aircraft, characterized by comprising a housing and a drive mechanism (3) according to any one of claims 1 to 4;

the shell is provided with an inner cavity, the driving mechanism (3) is arranged in the inner cavity, the inner cavity is provided with a control unit (4) and a power supply structure (5), and the driving mechanism (3), the control unit (4) and the power supply structure (5) are sequentially arranged along the length direction of the shell;

wherein the impeller (32) is arranged opposite to the control unit (4).

6. The aircraft according to claim 5, characterized in that said housing is provided with a mounting hole (111), said mounting hole (111) being provided with a camera assembly (2);

the camera assembly (2) is provided with an air inlet (215), the top of the shell is provided with a first air outlet (121), and air flow enters the inner cavity from the air inlet (215) and flows to the control unit (4) through the driving mechanism (3) and then is discharged from the first air outlet (121).

7. The aircraft of claim 6, wherein a second air outlet (122) and a third air outlet (123) are provided on both sides of the housing, the second air outlet (122) and the third air outlet (123) being arranged at intervals;

the second air outlet (122) is arranged on two sides of the shell corresponding to the control unit (4), and the third air outlet (123) is arranged on two sides of the shell corresponding to the power supply structure (5).

8. The aircraft of claim 7, wherein at least one side of the housing is provided with a plurality of the second air outlets (122), and the plurality of second air outlets (122) are arranged at intervals along the length of the housing.

9. The aircraft of claim 8, characterized in that at least one side of the housing is provided with a plurality of said third air outlets (123), said third air outlets (123) being arranged at intervals along the length of the housing.