CN219192554U

CN219192554U - Improve electronic perpendicular take-off and landing aircraft motor heat dissipation intake duct structure

Info

Publication number: CN219192554U
Application number: CN202223333291.5U
Authority: CN
Inventors: 董明; 王继明; 姚远; 杨万里; 党铁红
Original assignee: Shanghai Volant Aerotech Ltd
Current assignee: Shanghai Volant Aerotech Ltd
Priority date: 2022-12-12
Filing date: 2022-12-12
Publication date: 2023-06-16
Anticipated expiration: 2032-12-12

Abstract

The utility model discloses a structure for improving a heat dissipation air inlet channel of an electric vertical take-off and landing aircraft motor, which comprises an NACA air inlet channel, wherein the NACA air inlet channel is arranged on a motor arm, a lip is arranged on the NACA air inlet channel, the end part of the motor arm is provided with a motor heat dissipation air inlet, the motor heat dissipation air inlet is communicated with the NACA air inlet channel, the end part of the motor arm is connected with a motor, the motor heat dissipation air inlet is oriented to the motor, the NACA air inlet channel is a gradually-expanding channel, the width of an air flow initial inlet of the NACA air inlet channel is set to be W1, the width of the lip is set to be W2, the depth and the length of the NACA air inlet channel are respectively set to be H and L, and W2/H is controlled to be 3-5,L to be not less than 2 times W2. In the structure, the NACA air inlet channel can improve heat dissipation of the motor, ensure safe and reliable operation of the motor, and lower aerodynamic resistance promotes voyage of the electric aircraft.

Description

Improve electronic perpendicular take-off and landing aircraft motor heat dissipation intake duct structure

Technical Field

The utility model relates to the technical field of aviation, in particular to a heat dissipation air inlet channel structure for an electric vertical take-off and landing aircraft motor.

Background

eVTOL (Electric Vertical Takeoff and Landing) electric vertical takeoff and landing aircraft applications relate to a variety of scene modes of urban passenger transport, regional passenger transport, freight transport, personal aircraft, emergency medical services, and the like. With advances in battery technology, automation and internet technology, mass urban air transport appears to be more viable than ever before. The possibilities of this urban air transport are currently receiving great attention. The most outstanding advantages of eVTOL are energy conservation, environmental protection, high efficiency, low energy consumption, near zero emission, low noise and vibration levels, and good riding comfort. In addition, the device has the characteristics of safety, reliability, simple structure, convenient operation and use, good maintainability/low cost, good economy and the like.

With the progress of urban area, land space becomes saturated, traffic jam is increasingly serious, and development of urban air available space and vertical three-dimensional traffic are needed. Future potential applications for eVTOL relate to a variety of scene modes for urban passenger transport, regional passenger transport, freight transport, personal aircraft, emergency medical services, and the like.

The electric vertical take-off and landing aircraft controls the motor to run through the motor controller, and the thrust of the propeller connected with the motor is adjusted by increasing or reducing the rotating speed of the motor, so that the forward flying speed of the electric vertical take-off and landing aircraft is controlled. When the motor runs at high speed, a large amount of heat is generated, and when the motor exceeds a certain temperature, the motor stops working, so that the motor stops running, loses thrust in flight and further generates a catastrophic accident. Therefore, there is a need to dissipate heat from the motor, and a conventional general heat dissipation method is to expose a motor heat sink assembly to air and dissipate heat from the motor by an air flow generated by the electric vertical takeoff and landing aircraft during flight. However, for an electric aircraft, the radiator assembly exposed to the air generates a large resistance during the forward stage of the aircraft due to the long flat flight stage, which is disadvantageous for the forward flat flight of the aircraft.

Disclosure of Invention

The utility model aims to provide an improved heat dissipation air inlet channel structure of an electric vertical take-off and landing aircraft motor, which aims to solve the problems in the background art. In order to achieve the above purpose, the present utility model provides the following technical solutions: the utility model provides an improve electronic perpendicular take-off and landing aircraft motor heat dissipation intake duct structure, includes the NACA intake duct, the NACA intake duct is seted up on the motor arm, be equipped with the lip on the NACA intake duct, motor heat dissipation air inlet is opened to the tip of motor arm, motor heat dissipation air inlet and NACA intake duct intercommunication, the end connection motor of motor arm, motor heat dissipation air inlet is towards the motor, the NACA intake duct is the divergent passageway, the air current initial entrance width of NACA intake duct is set to W1, and lip department width is set to W2, and the degree of depth and the length of NACA intake duct are set to H and L respectively, wherein W2/H control is not less than 2 times W2 at 3 ~ 5,L.

Preferably, two NACA air inlets are provided and are symmetrically arranged up and down along the motor arm, the motor heat dissipation air inlet comprises a motor heat dissipation upper air inlet and a motor heat dissipation lower air inlet, and the motor heat dissipation upper air inlet and the motor heat dissipation lower air inlet respectively correspond to the positions of the two NACA air inlets.

Preferably, a motor heat dissipation annular cavity is arranged between the motor heat dissipation upper air inlet and the motor heat dissipation lower air inlet, and the motor heat dissipation annular cavity is formed at the end part of the motor arm.

Preferably, the bottom edge of the NACA air inlet is in a variable-radius rounding structure, and the expansion angle of air flow entering the NACA air inlet is set to be theta, wherein theta is within 12 degrees.

The utility model has the technical effects and advantages that: in the structure, the NACA air inlet channel can improve heat dissipation of the motor, ensure safe and reliable operation of the motor, and lower aerodynamic resistance promotes voyage of the electric aircraft.

Drawings

FIG. 1 is a schematic top view of a propeller system with a heat dissipation air intake structure;

FIG. 2 is a schematic side view of a propeller system with a heat sink inlet structure;

FIG. 3 is a front isometric view of the present utility model;

FIG. 4 is a rear isometric view of the present utility model;

FIG. 5 is a graphical illustration of NACA inlet parameters according to the present utility model;

FIG. 6 is a graphical representation of NACA inlet inflow angle parameters according to the present utility model.

In the figure: 1. a propeller; 2. a fairing; 3-an electric motor; 4. a motor arm; NACA inlet duct; 7. a motor heat dissipation upper air inlet; 8. the motor dissipates heat the annular cavity; 9. the motor dissipates heat the lower air inlet.

Detailed Description

In order that the manner in which the above-recited features, advantages, objects and advantages of the present utility model are attained and can be readily understood, a more particular description of the utility model will be rendered by reference to the appended drawings, in which the terms "mounted," "connected," and "connected" are to be construed broadly, and may be either fixedly connected or detachably connected, or integrally or mechanically connected, or electrically connected, unless otherwise explicitly stated and defined; can be directly connected or indirectly connected through an intermediate medium, and can be communicated with the inside of two elements.

Examples

Fig. 1 is a schematic top view of a propeller system with a heat dissipation air inlet structure, a propeller 1 is mounted on a motor 3, a fairing 2 is used for improving airflow vortex downstream of the propeller, improving flow and reducing resistance, and the motor 3 is mounted on a motor arm 4. The NACA inlet duct 5 is arranged near the motor arm 4 near the motor 3, symmetrically arranged up and down, as shown in FIG. 2.

The NACA air intake duct 5 is not limited to the up-down arrangement shown in fig. 1 and 2, and may be circumferentially arranged on the motor arm 3 in an appropriate number according to the heat dissipation needs. The motor heat dissipation air inlet structure comprises an NACA air inlet 5, a motor heat dissipation upper air inlet 7, a motor heat dissipation annular cavity 8 and a motor heat dissipation lower air inlet 9. The high-speed incoming flow is diffused and enters through the NACA air inlet 5, enters the motor 3 through the motor heat dissipation upper air inlet 7 and the motor heat dissipation lower air inlet 9, and is cooled. The motor heat dissipation annular cavity 8 is used for balancing the pressure of the upper air inlet and the lower air inlet, so that the upper pressure and the lower pressure are uniform, and the motor 3 is cooled more uniformly. The NACA air inlet 5 is provided with a lip 10 (as shown in fig. 3), and the airflow is divided into two parts at the position of the lip 10, one part enters the motor 3 for cooling, the other part merges into the main flow, and the radius of the lip 10 cannot be too small to prevent the airflow from being separated.

The NACA inlet 5 is a gradually expanding channel, and parameters of the NACA inlet are shown in fig. 5 and 6. The initial inlet width of the NACA air inlet 5 is set to be W1, the width of the inlet at the lip 10 is set to be W2, the width of the inlet at the lip is set to be W2, the ratio of the height W2 to the depth H of the NACA air inlet 5 is generally recommended to be 3-5, the length of the NACA air inlet 5 is set to be L, and the L is generally recommended to be not less than 2 times W2. The air flow enters the NACA inlet 5 at an expansion angle θ (shown in FIG. 6), which is typically controlled to be within 12 ° in order to improve flow at the edges, the bottom edge of the NACA inlet 5 is rounded off with a varying radius to better conform to aerodynamic profile design.

Finally, it should be noted that: the foregoing description is only illustrative of the preferred embodiments of the present utility model, and although the present utility model has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that modifications may be made to the embodiments described, or equivalents may be substituted for elements thereof, and any modifications, equivalents, improvements or changes may be made without departing from the spirit and principles of the present utility model.

Claims

1. Improve electronic perpendicular take-off and landing aircraft motor heat dissipation intake duct structure, including the NACA intake duct, its characterized in that: the NACA air inlet is arranged on a motor arm, a lip is arranged on the NACA air inlet, a motor heat dissipation air inlet is formed in the end portion of the motor arm, the motor heat dissipation air inlet is communicated with the NACA air inlet, the end portion of the motor arm is connected with a motor, the motor heat dissipation air inlet faces towards the motor, the NACA air inlet is a gradually-expanding channel, the width of an air flow starting inlet of the NACA air inlet is set to be W1, the width of the lip is set to be W2, the depth and the length of the NACA air inlet are set to be H and L respectively, and W2/H is controlled to be 3-5,L to be not less than 2 times of W2.

2. The improved heat dissipation and air intake structure for an electric vertical takeoff and landing aircraft motor of claim 1, wherein: the NACA air inlets are arranged in two, and are symmetrically arranged up and down along the motor arm, the motor heat dissipation air inlet comprises a motor heat dissipation upper air inlet and a motor heat dissipation lower air inlet, and the motor heat dissipation upper air inlet and the motor heat dissipation lower air inlet respectively correspond to the positions of the two NACA air inlets.

3. The improved heat dissipation and air intake structure for an electric vertical takeoff and landing aircraft motor of claim 2, wherein: the motor cooling device is characterized in that a motor cooling annular cavity is arranged between the motor cooling upper air inlet and the motor cooling lower air inlet, and the motor cooling annular cavity is formed in the end part of the motor arm.

4. The improved heat dissipation and air intake structure for an electric vertical takeoff and landing aircraft motor of claim 1, wherein: the bottom edge of the NACA air inlet is of a variable-radius rounding structure, and the expansion angle of air flow entering the NACA air inlet is set to be theta, wherein theta is within 12 degrees.