CN211442748U

CN211442748U - Aircraft fuselage and aircraft

Info

Publication number: CN211442748U
Application number: CN202021609673.4U
Authority: CN
Inventors: 陈方平; 张晓琪; 朱胜利; 李蕴仪; 曹子彧; 马辉
Original assignee: Beijing Yunsheng Intelligent Technology Co ltd
Current assignee: Beijing Yunsheng Intelligent Technology Co ltd
Priority date: 2020-08-06
Filing date: 2020-08-06
Publication date: 2020-09-08
Anticipated expiration: 2030-08-06

Abstract

The utility model provides an aircraft fuselage and aircraft relates to aircraft heat dissipation technical field, the utility model provides an aircraft fuselage includes organism portion, and organism portion is equipped with the device installation cavity, and the aircraft fuselage is equipped with inlet and drainage port, inlet and drainage port respectively with device installation cavity fluid intercommunication, the aircraft fuselage has the windward side, the inlet sets up in the windward side. The utility model provides an aircraft fuselage can utilize outside air current to dispel the heat to the inside device installation cavity of aircraft fuselage.

Description

Aircraft fuselage and aircraft

Technical Field

The utility model belongs to the technical field of the aircraft heat dissipation technique and specifically relates to an aircraft fuselage and aircraft are related to.

Background

The heat dissipation of the aircraft mainly comprises active heat dissipation and passive heat dissipation. The active heat dissipation mainly adopts a mode of accelerating the convection of cold air and hot air by a fan so as to improve the heat exchange efficiency; the passive heat dissipation adopts a mode of additionally arranging heat dissipation fins so as to increase the heat dissipation area. However, both active and passive heat dissipation increase the complexity of the internal hardware of the aircraft, resulting in an increase in the weight of the aircraft, and even requiring power consumption for heat dissipation, thereby increasing the load of the aircraft and resulting in a decrease in the endurance time of the aircraft.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide an aircraft fuselage and aircraft can utilize outside air current to dispel the heat to the inside device installation cavity of aircraft fuselage.

In a first aspect, the aircraft fuselage provided by the present invention comprises a fuselage portion, wherein the fuselage portion is provided with a device installation cavity; the aircraft fuselage is provided with a flow inlet and a flow outlet, and the flow inlet and the flow outlet are respectively communicated with the device installation cavity in a fluid mode; the aircraft fuselage has a windward side, and the inlet is arranged in the windward side.

With reference to the first aspect, the present invention provides a first possible implementation manner of the first aspect, wherein the aircraft fuselage further includes a horn portion connected to the fuselage portion; the machine arm part is provided with a flow passage branch, and the device mounting cavity and the flow passage branch form a cooling flow passage together; one end of the flow passage branch is communicated with the device installation cavity, and the flow passage branch is communicated with the flow inlet or the drainage port.

With reference to the first possible implementation manner of the first aspect, the present invention provides a second possible implementation manner of the first aspect, wherein the body portion and the horn portion are integrally formed.

With reference to the first aspect, the present invention provides a third possible implementation manner of the first aspect, wherein the arm part is mounted with a driving propeller; the windward side is arranged on the arm part and is positioned on the air outlet side of the driving propeller.

With reference to the third possible implementation manner of the first aspect, the present invention provides a fourth possible implementation manner of the first aspect, wherein the windward side and the wind-out direction included angle of the driving propeller are smaller than 90 degrees.

In combination with the first aspect, the present invention provides a fifth possible implementation manner of the first aspect, wherein the arm portion is provided with an air supply device, and an air outlet side of the air supply device faces the windward side.

With reference to the first aspect, the present invention provides a sixth possible implementation manner of the first aspect, wherein the aircraft body includes a body portion, and the body portion is provided with a device installation cavity; the cooling flow passage comprises the device mounting cavity, and the inlet and the outlet are respectively in fluid communication with the device mounting cavity.

In combination with the sixth possible implementation manner of the first aspect, the present invention provides a seventh possible implementation manner of the first aspect, wherein the supporting portion is connected to the bottom of the fuselage portion, the drainage port is disposed in the supporting portion, and an air outlet direction of the drainage port deviates from a preset traveling direction of the aircraft fuselage.

With reference to the first aspect, the present invention provides an eighth possible implementation manner of the first aspect, wherein the inflow port and the drainage port are respectively provided with a blocking device; the blocking device is used for blocking dust or water from entering the device installation cavity.

In a second aspect, the present invention provides an aircraft, comprising: the drive arrangement and the aircraft fuselage provided in the first aspect; the windward side is located in a preset advancing direction of the aircraft, and/or the windward side is located on an air outlet side of the driving device.

The embodiment of the utility model provides a following beneficial effect has been brought: the aircraft fuselage includes the organism portion, and organism portion is equipped with the device installation cavity, and the aircraft fuselage is equipped with inlet and drainage port, inlet and drainage port respectively with device installation cavity fluid intercommunication, and the aircraft fuselage has the windward side, and the inlet sets up in the windward side, and outside gas can get into the device installation cavity through the inlet to cool off the device installation cavity inside the aircraft fuselage, need not to add fin and fan, be favorable to alleviateing the weight and the energy consumption of aircraft.

In order to make the aforementioned and other objects, features and advantages of the present invention comprehensible, preferred embodiments accompanied with figures are described in detail below.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present invention or the related art, the drawings required to be used in the description of the embodiments or the related art will be briefly introduced below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.

Fig. 1 is a schematic view of an aircraft fuselage provided by an embodiment of the present invention;

fig. 2 is a partial cross-sectional view of an aircraft fuselage provided by an embodiment of the present invention;

fig. 3 is a schematic view of an aircraft provided by an embodiment of the present invention;

fig. 4 is a top view of an aircraft provided by an embodiment of the present invention;

FIG. 5 is an enlarged schematic view of position A of FIG. 4;

fig. 6 is a partial schematic view of an aircraft according to an embodiment of the present invention.

Icon: 100-an aircraft fuselage; 101-windward side; 110-a body portion; 120-a machine arm part; 121-air supply means; 130-a support; 140-a barrier device; 011-a cooling flow channel; 111-a device mounting cavity; 112-flow channel branch; 012-a flow inlet; 013-drainage port; 131-a first heat dissipation hole; 132-a second heat dissipation hole; 200-driving the propeller.

Detailed Description

The technical solution of the present invention will be described clearly and completely with reference to the accompanying drawings, and obviously, the described embodiments are some, but not all embodiments of the present invention. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.

In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplification of description, but do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance. The term "physical quantity" in the formula, unless otherwise noted, is understood to mean a basic quantity of a basic unit of international system of units, or a derived quantity derived from a basic quantity by a mathematical operation such as multiplication, division, differentiation, or integration.

In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art.

Example one

As shown in fig. 1, an aircraft fuselage 100 provided by the embodiment of the present invention includes a fuselage portion 110, where the fuselage portion 110 is provided with a device installation cavity 111; the aircraft fuselage 100 is provided with a flow inlet 012 and a flow outlet 013, the flow inlet 012 and the flow outlet 013 being in fluid communication with the device mounting cavity 111, respectively; the aircraft fuselage 100 has a windward side 101, and the inlet 012 is provided at the windward side 101. Wherein, inside being used for installing power mainboard and flight controller etc. of device installation cavity 111, the windward side 101 can adopt the terminal surface of aircraft advancing direction, and the aircraft receives the air resistance effect and has windward side 101 when advancing, imports device installation cavity 111 through inlet 012 with the outside low temperature gas of aircraft fuselage 100 to can cool off the inside device of aircraft fuselage 100, need not to add fin and fan, be favorable to alleviateing the weight and the energy consumption of aircraft.

Furthermore, the rotor of the rotary wing aircraft and the tail rotor of the helicopter are both capable of directing an airflow towards the aircraft fuselage 100, thereby forming a windward side 101 on the aircraft fuselage 100. External air can be introduced into the cooling channel 011 by a propeller or a tail rotor, thereby accelerating the flow rate of the gas inside the aircraft fuselage 100 to achieve a cooling effect.

As shown in fig. 1, 2 and 3, the aircraft fuselage 100 further comprises an arm section 120 connected to the fuselage section 110; the arm part 120 is provided with a flow channel branch 112, and the device mounting cavity 111 and the flow channel branch 112 together form a cooling flow channel 011; one end of the flow path branch 112 is connected to the device mounting chamber 111, and the flow path branch 112 is connected to the inlet 012 or the outlet 013. One end of the arm 120 is connected to the body 110, and the other end extends away from the body 110. The horn section 120 may comprise a side arm of a multi-rotor aircraft and is fitted with a drive propeller 200; the arm section 120 may also include the tail of the helicopter and be fitted with a tail rotor.

In some embodiments, the windward side 101 is a front end surface of the aircraft in a traveling state, and the airflow generated by the air resistance flows into the device mounting cavity 111 through the inlet 012, flows through the flow path branch 112, and is discharged through the outlet 013 arranged on the arm 120.

In the present embodiment, the windward side 101 is disposed on the horn 120, and the windward side 101 may be a front end surface of the horn 120 when the aircraft is in a traveling state, or the windward side 101 may be a side surface of the horn 120 that is generated by a tail of a helicopter. The low-temperature air outside the aircraft fuselage 100 flows from the flow channel branch 112 into the component installation chamber 111, so that an overall cooling of the aircraft fuselage 100 can be achieved.

Further, the body portion 110 is integrally formed with the arm portion 120. The machine body part 110 and the machine arm part 120 are processed into an integrated structure by means of injection molding or 3D printing and the like, so that a gap is prevented from being generated between the machine body part 110 and the machine arm part 120, sealing treatment is not needed between the device installation cavity 111 and the flow channel branch 112, the device installation cavity 111 can be ensured to be communicated with the flow channel branch 112, and the structural stability of the aircraft fuselage 100 can be improved.

As shown in fig. 3, the arm section 120 is mounted with a driving propeller 200; the windward side 101 is provided on the arm portion 120, and the windward side 101 is located on the air-out side of the driving propeller 200.

Specifically, in the multi-rotor aircraft, the driving propeller 200 blows air downwards, the driving propeller 200 is located above the arm 120, and the windward side 101 is configured as the top surface of the arm 120, so that the air flow blown onto the arm 120 by the self-driving propeller 200 can be utilized, and the air flow is introduced into the cooling flow channel 011 from the air inlet 012, thereby cooling the aircraft fuselage 100 and the internal devices.

In the multi-rotor aircraft, the drive propeller 200 is provided above or below the arm unit 120, the arm unit 120 blocks a part of the airflow generated by the drive propeller 200, and the inlet 012 is provided in the arm unit 120, so that the airflow blowing toward the arm unit 120 is used to radiate heat from the aircraft body 100, and there is no need to add a motor or a fan for ventilation, and the energy consumption of the aircraft is not increased.

Further, the included angle between the windward side 101 and the air outlet direction of the driving propeller 200 is less than 90 degrees. In order to increase the intake velocity of the cooling flow path 011, a plurality of intake ports 012 may be provided on the windward side 101, and the intake ports 012 may be provided at intervals in the extending direction of the horn unit 120. In addition, an included angle between the windward side 101 and the air outlet direction of the driving propeller 200 may be set to 80 degrees, 70 degrees, 60 degrees, 55 degrees, 50 degrees or 45 degrees, and the air that is blown to the arm portion 120 and does not enter the air inlet 012 may be guided by the windward side 101, thereby alleviating the problem that the arm portion 120 blocks the air flow. Furthermore, the top surface of the arm 120 is provided with the inclined windward side 101, so that the bending resistance of the arm 120 can be improved and the structural strength of the arm 120 can be enhanced while the weight of the arm 120 is reduced.

As shown in fig. 2 and 6, the horn unit 120 is provided with an air blowing device 121, and an air outlet side of the air blowing device 121 faces the windward side 101.

In some embodiments, the air blowing device 121 includes a fan rotatably connected to the arm portion 120, and the fan may be driven by an additional motor to introduce external air into the flow path branch 112.

In this embodiment, the air supply device 121 includes a fan, and the fan and the driving propeller 200 are driven by the same motor. The arm part 120 is provided with a mounting hole, the motor is connected in the mounting hole, and the motor is provided with a driving shaft in the vertical direction. The driving propeller 200 is connected to the driving shaft above the motor, the fan is connected to the driving shaft below the motor, and the fan is located in the mounting hole, thereby preventing the fan from being affected by the airflow generated by the driving propeller 200. The inside wall of mounting hole is as windward side 101, and is equipped with the side opening that communicates runner branch 112, and this side opening can regard as inlet 012, and fan drive gas flows to the direction that deviates from the drive shaft, and the air current can get into in the runner branch 112 through the side opening.

As shown in fig. 1, the fluid discharged through the discharge opening 013 has a horizontal direction driving force on the aircraft fuselage 100.

Specifically, outside air from aircraft fuselage 100 flows through inlet 012, into cooling channel 011, and exits through outlet 013. The outlet direction of the discharge opening 013 is arranged horizontally, so that the gas flow has a counter-propulsive effect on the aircraft fuselage 100 when the gas is discharged through the discharge opening 013.

In some embodiments, the drainage ports 013 are respectively disposed on two sides of the aircraft fuselage 100, and the air outlet direction of the drainage ports 013 is perpendicular to the preset traveling direction of the aircraft fuselage 100, so that the acting forces generated by the air flows discharged through the drainage ports 013 on the two sides cancel each other out, thereby ensuring that the aircraft fuselage 100 can maintain a stable posture.

The embodiment of the utility model provides an in, the direction of giving vent to anger of drainage port 013 deviates from the preset direction of travel of aircraft fuselage 100, and the gas through drainage port 013 exhanst can reverse thrust aircraft fuselage 100 to increase the drive power of aircraft, help increasing the continuation of the journey mileage of aircraft, prolong the duration of aircraft. Especially for a multi-rotor aircraft, the airflow blowing to the aircraft body 100 can be utilized, the airflow generated by the propeller is fully utilized, and the airflow is used for heat dissipation and driving the aircraft to move, so that the energy consumption of the aircraft is reduced.

As shown in fig. 1, 2 and 3, the bottom of the body 110 is connected to a support 130, the drainage port 013 is disposed on the support 130, and the air outlet direction of the drainage port 013 faces away from the preset traveling direction of the aircraft body. The gas absorbing the heat inside the device mounting cavity 111 flows into the inside of the supporting portion 130, thereby preventing the heat from being accumulated on the body portion 110. The drainage port 013 comprises a first heat dissipation hole 131 with an air outlet direction deviating from a preset advancing direction, gas in the cooling flow channel 011 is discharged through the first heat dissipation hole 131, heat inside the aircraft body 100 can be taken away, the aircraft body 100 can be reversely pushed to move towards the preset advancing direction, accordingly, driving force of the aircraft along the preset advancing direction is increased, energy consumption of the aircraft is reduced, and endurance time of the aircraft is prolonged.

It should be noted that, in order to make the wind resistance of the aircraft during traveling smaller, the fuselage portion 110 is usually set to be a streamline structure, the preset traveling direction does not represent that the aircraft can only fly along the preset traveling direction, but in a state that the aircraft flies along the preset traveling direction, the wind resistance received by the fuselage portion 110 is smaller, and the aircraft flies along the preset traveling direction, so that a larger cruising mileage can be obtained.

Further, two supporting portions 130 are connected to the bottom of the body portion 110, and the two supporting portions 130 are spaced apart from each other, so that the two supporting portions 130 can support the body portion 110 in the landing state of the aircraft. The air outlet 013 further includes second heat dissipation holes 132, the two second heat dissipation holes 132 are disposed on the two supporting portions 130 in a one-to-one correspondence manner, and the air outlet directions of the two second heat dissipation holes 132 are disposed oppositely, so that the air flows discharged from the two second heat dissipation holes 132 interact with each other, and the influence of the air flows discharged from the second heat dissipation holes 132 on the flight of the aircraft is reduced.

As shown in fig. 2, 4 and 5, the inlet 012 and the outlet 013 are respectively provided with the blocking device 140; the blocking device 140 serves to block dust or water from entering the device mounting chamber 111. The blocking device 140 includes a shield connected to the aircraft fuselage 100, and the shield has an end surface opposite to the inlet 012 or the outlet 013, and can block the inlet 012 or the outlet 013 to prevent external dust or water from entering the cooling flow channel 011. Further, the blocking device 140 may further include a filter screen through which the gas entering the cooling flow passage 011 is filtered, thereby preventing dust from entering the device mounting chamber 111.

Example two

As shown in fig. 1, 3 and 4, an embodiment of the present invention provides an aircraft, including: the driving device and the aircraft fuselage provided by the first embodiment; the windward side 101 is located in a predetermined direction of travel of the aircraft and/or the windward side 101 is located on the air outlet side of the drive.

Specifically, the aircraft flies in a predetermined traveling direction, the front of the aircraft is subjected to air resistance to form a windward side 101, and an air inlet 012 may be provided in the windward side 101 to introduce an air flow into the cooling flow channel 011. The driving device comprises a driving propeller 200 or a tail rotor of the helicopter, the windward side 101 is arranged at the air outlet side of the driving device, and the windward side 101 is provided with an air inlet 012, so that airflow can be input into the cooling flow channel 011 by the driving device, and the cooling of the aircraft body 100 and devices in the device installation cavity 111 is realized.

Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; although the present invention has been described in detail with reference to the foregoing embodiments, it should be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; such modifications and substitutions do not depart from the spirit and scope of the present invention.

Claims

1. An aircraft fuselage, characterized in that the aircraft fuselage (100) comprises a fuselage portion (110), the fuselage portion (110) being provided with an instrument mounting cavity (111);

the aircraft fuselage (100) is provided with a flow inlet (012) and a flow outlet (013), the flow inlet (012) and the flow outlet (013) are respectively in fluid communication with the device installation cavity (111);

the aircraft fuselage (100) has a windward side (101), and the inflow opening (012) is arranged on the windward side (101).

2. The aircraft fuselage of claim 1, characterized in that the aircraft fuselage (100) further comprises an arm section (120) connected to the fuselage section (110);

the machine arm part (120) is provided with a flow channel branch (112), and the device mounting cavity (111) and the flow channel branch (112) jointly form a cooling flow channel (011);

one end of the flow passage branch (112) is communicated with the device installation cavity (111), and the flow passage branch (112) is communicated with the flow inlet (012) or the flow outlet (013).

3. The aircraft fuselage of claim 2, characterized in that the fuselage section (110) is integrally formed with the arm section (120).

4. The aircraft fuselage of claim 2 or 3, characterized in that the arm section (120) is fitted with a driving propeller (200);

the windward side (101) is arranged on the arm portion (120), and the windward side (101) is located on the air outlet side of the driving propeller (200).

5. The aircraft fuselage of claim 4, characterised in that the angle between the wind-facing side (101) and the wind-exit direction of the driving propeller (200) is less than 90 degrees.

6. The aircraft fuselage of claim 2 or 3, characterized in that the arm section (120) is provided with air blowing means (121), the air outlet side of which air blowing means (121) is directed towards the windward side (101).

7. The aircraft fuselage of claim 1, characterized in that the fluid discharged via the drainage ports (013) has a horizontally-directed driving force on the aircraft fuselage (100).

8. The aircraft fuselage of claim 7, characterized in that a support (130) is connected to the bottom of the fuselage section (110), the drainage opening (013) being arranged on the support (130) and the outflow direction of the drainage opening (013) facing away from the preset direction of travel of the aircraft fuselage.

9. The aircraft fuselage of claim 1, characterised in that the inflow (012) and the outflow (013) are each provided with a barrier means (140);

the blocking device (140) is used for blocking dust or water from entering the device installation cavity (111).

10. An aircraft, characterized in that it comprises: a drive arrangement and an aircraft fuselage according to any of claims 1 to 9;

the windward side (101) is located in a preset advancing direction of the aircraft, and/or the windward side (101) is located on an air outlet side of the driving device.