US20220089271A1 - Unmanned aerial vehicle and heat dissipation structure - Google Patents
Unmanned aerial vehicle and heat dissipation structure Download PDFInfo
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- US20220089271A1 US20220089271A1 US17/457,697 US202117457697A US2022089271A1 US 20220089271 A1 US20220089271 A1 US 20220089271A1 US 202117457697 A US202117457697 A US 202117457697A US 2022089271 A1 US2022089271 A1 US 2022089271A1
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- 239000006260 foam Substances 0.000 claims description 5
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- 229910000881 Cu alloy Inorganic materials 0.000 claims description 4
- 239000000499 gel Substances 0.000 claims description 3
- 229910001092 metal group alloy Inorganic materials 0.000 description 10
- 239000013585 weight reducing agent Substances 0.000 description 4
- 229910000861 Mg alloy Inorganic materials 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 239000012530 fluid Substances 0.000 description 2
- FYYHWMGAXLPEAU-UHFFFAOYSA-N Magnesium Chemical compound [Mg] FYYHWMGAXLPEAU-UHFFFAOYSA-N 0.000 description 1
- 230000005534 acoustic noise Effects 0.000 description 1
- 238000005219 brazing Methods 0.000 description 1
- 229910052749 magnesium Inorganic materials 0.000 description 1
- 239000011777 magnesium Substances 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/08—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/08—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
- B64D33/10—Radiator arrangement
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U20/00—Constructional aspects of UAVs
- B64U20/90—Cooling
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- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
- H05K7/00—Constructional details common to different types of electric apparatus
- H05K7/20—Modifications to facilitate cooling, ventilating, or heating
- H05K7/20009—Modifications to facilitate cooling, ventilating, or heating using a gaseous coolant in electronic enclosures
- H05K7/20136—Forced ventilation, e.g. by fans
- H05K7/20145—Means for directing air flow, e.g. ducts, deflectors, plenum or guides
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- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
- H05K7/00—Constructional details common to different types of electric apparatus
- H05K7/20—Modifications to facilitate cooling, ventilating, or heating
- H05K7/20009—Modifications to facilitate cooling, ventilating, or heating using a gaseous coolant in electronic enclosures
- H05K7/20136—Forced ventilation, e.g. by fans
- H05K7/20154—Heat dissipaters coupled to components
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
- B64U10/13—Flying platforms
- B64U10/14—Flying platforms with four distinct rotor axes, e.g. quadcopters
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2101/00—UAVs specially adapted for particular uses or applications
- B64U2101/30—UAVs specially adapted for particular uses or applications for imaging, photography or videography
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/20—Rotors; Rotor supports
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Microelectronics & Electronic Packaging (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Remote Sensing (AREA)
- Cooling Or The Like Of Electrical Apparatus (AREA)
Abstract
A UAV includes a camera assembly, a heat generating device, and a heat dissipation structure including a housing, a heat dissipation device, and heat dissipation fan for providing an air flow into the housing. The housing receives the heat generating device and includes a first air inlet and a first air outlet. The heat dissipation device includes heat dissipation fins disposed in parallel. The first air inlet and the camera assembly are located at a same side of the housing. The camera assembly is disposed at a front portion of the housing. A heat dissipation air channel formed between two adjacent heat dissipation fins includes a second air inlet and a second air outlet that is connected with the first air outlet. The heat dissipation fan includes a third air inlet connected with the first air inlet and a third air outlet connected with the second air inlet.
Description
- This application is a continuation of U.S. application Ser. No. 16/687,258, filed on Nov. 18, 2019, which is a continuation application of International Application No. PCT/CN2017/090972, filed on Jun. 30, 2017, which claims priority to Chinese Patent Application No. 201720560892.X, filed on May 19, 2017, the entire contents of all of which are incorporated herein by reference.
- The present disclosure relates to the technology field of unmanned aerial vehicles and, more particularly, to an unmanned aerial vehicle and a heat dissipation structure.
- A typical unmanned aerial vehicle (“UAV”) may be provided with a heat dissipation structure to dissipate heat generated by a chip, a motherboard, or other heat generating devices of the UAV, thereby ensuring normal operations of the UAV. In conventional technologies, a small-sized UAV may include an axial fan brazed with a heat tube to form a heat dissipation module to dissipate heat. For a small-sized, compact UAV, this heat dissipation system has a high impedance. Because the axial fan can only produce a low wind pressure, the axial fan has a weak ability to overcome the system impedance. As a result, a heat dissipation efficiency is low. In addition, because the heat tube is used in the heat tube brazed heat dissipator, the weight of the heat tube brazed heat dissipator is heavy, which may reduce the continuous flight capability of the UAV.
- Because the weight of the UAV directly affects the continuous flight capability of the UAV, the lighter the weight, the longer the continuous flight time. On one hand, the heat dissipation system needs to use metal materials having a high heat dissipation performance, which may increase the weight of the UAV. On the other hand, because a battery of the small-sized UAV has limited continuous flight capability, the increase of the weight of the heat dissipation system may further reduce the continuous flight time of the battery. The conflict between these two needs renders design of a heat dissipation system for the UAV a difficult topic that needs to be addressed.
- In accordance with an aspect of the present disclosure, there is provided a heat dissipation structure including a housing configured to receive a heat generating device. The housing includes a first air inlet and a first air outlet. The heat dissipation structure also includes an alloy heat dissipation device disposed in the housing and including a plurality of heat dissipation fins disposed in parallel with one another. A heat dissipation air channel is formed between two adjacent heat dissipation fins. The heat dissipation air channel includes a second air inlet and a second air outlet, the second air outlet being connected with the first air outlet. The heat dissipation structure also includes a heat dissipation fan configured to provide a heat dissipation air flow to an inside space of the housing. The heat dissipation fan is disposed inside the housing, and includes a third air inlet and a third air outlet, the third air inlet being connected with the first air inlet and the third air outlet being connected with the second air inlet.
- In accordance with another aspect of the present disclosure, there is also provided an unmanned aerial vehicle including a camera assembly and a heat generating device. The unmanned aerial vehicle also includes a heat dissipation structure. The heat dissipation structure includes a housing configured to receive the heat generating device. The housing includes a first air inlet and a first air outlet. The heat dissipation structure also includes an alloy heat dissipation device disposed in the housing and including a plurality of heat dissipation fins disposed in parallel with one another. A heat dissipation air channel is formed between two adjacent heat dissipation fins. The heat dissipation air channel includes a second air inlet and a second air outlet, the second air outlet being connected with the first air outlet. The heat dissipation structure also includes a heat dissipation fan configured to provide a heat dissipation air flow to an inside space of the housing. The heat dissipation fan is disposed inside the housing, and includes a third air inlet and a third air outlet, the third air inlet being connected with the first air inlet and the third air outlet being connected with the second air inlet. The camera assembly is disposed at a front lower portion of the housing.
- According to the heat dissipation structure of the present disclosure, an alloy heat dissipation device may conduct heat from a heat generating device, and may convectively exchange heat with an air flow blown by a heat dissipation fan, thereby achieving heat dissipation for the heat generating device. The heat dissipation fan may provide a sufficiently strong wind volume and wind pressure. In addition, the alloy heat dissipation device has a light weight, such that not only the heat dissipation efficiency is increased, the weight of the heat dissipation structure is also reduced. The technical solution of the present disclosure can achieve excellent heat dissipation performance, solve the difficult issue relating to weight increase in the UAV due to the heat dissipation structure, and provide an optimal balance between the heat dissipation performance and the weight reduction for the UAV. The technical solution of the present disclosure uses a light weight structure to provide a strong heat dissipation performance, and also reduces a heat dissipation space to a maximum extent.
- To better describe the technical solutions of the various embodiments of the present disclosure, the accompanying drawings showing the various embodiments will be briefly described. As a person of ordinary skill in the art would appreciate, the drawings show only some embodiments of the present disclosure. Without departing from the scope of the present disclosure, those having ordinary skills in the art could derive other embodiments and drawings based on the disclosed drawings without inventive efforts.
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FIG. 1 is an exploded view of a UAV, according to an example embodiment. -
FIG. 2 is a perspective view of a structure of the UAV with a first housing removed, according to an example embodiment. -
FIG. 3 is an enlarged view of a metal alloy heat dissipation device and a heat dissipation fan, according to an example embodiment. -
FIG. 4 is a schematic illustration of a metal alloy heat dissipation device, according to an example embodiment. - Technical solutions of the present disclosure will be described in detail with reference to the drawings, in which the same numbers refer to the same or similar elements unless otherwise specified. It will be appreciated that the described embodiments represent some, rather than all, of the embodiments of the present disclosure. Other embodiments conceived or derived by those having ordinary skills in the art based on the described embodiments without inventive efforts should fall within the scope of the present disclosure.
- Embodiments of the present disclosure shown in the drawings will be described in detail below. When describing the accompanying drawings, unless otherwise noted, the same reference number in different drawings indicate the same or similar elements. The embodiments described below do not represent all of the possible embodiments of the present disclosure. Instead, the embodiments described below are only some devices and methods that are consistent with various aspects of invention defined by the claims.
- The terms used in the following descriptions are only for the purpose of describing specific embodiments, and are not intended to limit the scope of the present disclosure. In addition, the singular forms “a,” “an,” and “the” are intended to include the plural forms as well, unless the context indicates otherwise.
- It should be understood that in the present disclosure, relational terms such as first and second, etc., are only used to distinguish an entity or operation from another entity or operation, and do not necessarily imply that there is an actual relationship or order between the entities or operations. Similarly, “a” or “one” and similar terms do not limit the number of features, but only indicate that there exists at least one feature. In addition, unless otherwise noted, the terms “front,” “back” (or “rear”), “lower,” and/or “upper” and other similar terms are only for the convenience of descriptions, and are not intended to limit to a particular position, location, or space orientation. The terms “comprise,” “comprising,” “include,” and the like specify the presence of stated features, steps, operations, elements, and/or components appearing following these terms are included in an element or object appearing before these terms, but do not preclude the presence or addition of one or more other features, steps, operations, elements, components, and/or groups. When a first component is referred to as “connected” to or with a second component, it is intended that the first component may be directly connected to or with the second component or may be indirectly connected to or with the second component via an intermediate component. The connection may include mechanical and/or electrical connections. The connection may be permanent or detachable. The electrical connection may be wired or wireless. The “connection” may also refer to a connection forming a fluid conduit, such that a fluid (e.g., an air flow) may flow from one element to another element.
- The term “and/or” used herein includes any suitable combination of one or more related items listed. For example, A and/or B can mean A only, A and B, and B only. The symbol “/” means “or” between the related items separated by the symbol. The phrase “at least one of” A, B, or C encompasses all combinations of A, B, and C, such as A only, B only, C only, A and B, B and C, A and C, and A, B, and C. In this regard, A and/or B can mean at least one of A or B.
- The UAV and the heat dissipation structure will be described in detail with reference to the accompanying drawings. Unless otherwise noted, the embodiments shown in the drawings are not mutually exclusive, and they may be combined in any suitable manner.
- Referring to
FIG. 1 -FIG. 4 , the structure of the UAV is shown. AUAV 1 may include aheat generating device 90. The present disclosure provides a heat dissipation structure. The heat dissipation structure may be disposed in theUAV 1 and may be configured to dissipate heat generated by theheat generating device 90. The heat dissipation structure may include ahousing 10 and a metal alloyheat dissipation device 20. - The
housing 10 may be configured to receive or accommodate theheat generating device 90. Thehousing 10 may include afirst air inlet 101 and afirst air outlet 102. - The metal alloy
heat dissipation device 20 may be disposed within thehousing 10. The metal alloyheat dissipation device 20 may include a plurality ofheat dissipation fins 290 that are disposed in parallel with one another. A heatdissipation air channel 200 may be formed between two adjacentheat dissipation fins 290. Each heatdissipation air channel 200 may include asecond air inlet 201 and asecond air outlet 202. Thesecond air outlet 202 may be connected with thefirst air outlet 102 to allow an air to flow therethrough. - In some embodiments, a
heat dissipation fan 30 configured to provide a heat dissipation air flow to an inside space of thehousing 10 may be provided in thehousing 10. Theheat dissipation fan 30 may include athird air inlet 301 and athird air outlet 302. Thethird air inlet 301 and thefirst air inlet 101 may be connected to allow an air to flow therethrough. Thethird air outlet 302 and thesecond air inlet 201 may be connected to allow an air to flow therethrough. - In some embodiments, in the present heat dissipation structure, the metal alloy
heat dissipation device 20 may conduct heat from theheat generating device 90, and may exchange heat with the heat dissipation air flow blown by theheat dissipation fan 30 through convective heat exchange, thereby dissipating heat from theheat generating device 90. Theheat dissipation fan 30 may provide a strong wind volume and wind pressure. In some embodiments, the metal alloyheat dissipation device 20 may have a light weight. Thus, the heat dissipation structure of the present disclosure may increase heat dissipation efficiency and reduce the weight of the heat dissipation structure. Hence, the present disclosure can not only improve heat dissipation performance, but also solve the difficulty issue relating to weight increase in theUAV 1 due to the heat dissipation structure. The present disclosure optimally balances the heat dissipation performance and the weight reduction of theUAV 1. The present disclosure also provides the strongest heat dissipation performance with the least weight, and reduces a heat dissipation space to the maximum extent. - Referring to
FIG. 4 , in some embodiments, the heatdissipation air channel 200 may include afirst air channel 210, asecond air channel 220, and athird air channel 230 located between thefirst air channel 201 and thesecond air channel 220. Each of theheat dissipation fins 290 may include afirst fin portion 291, asecond pin portion 292, and an arc-shapedtransition portion 293 connecting thefirst fin portion 291 and thesecond fin portion 292. Thefirst fin portion 291 and thesecond fin portion 292 may be slantly disposed through the arc-shapedtransition portion 293. Two adjacentfirst fin portions 291 of twoheat dissipation fins 290 may form thefirst air channel 210. Two adjacentsecond fin portions 292 of twoheat dissipation fins 290 may form thesecond air channel 220. Two adjacent arc-shapedtransition portions 293 of twoheat dissipation fins 290 may form thethird air channel 230. An angle between thefirst fin portion 291 and thesecond fin portion 292 may be between 90° and 120°, such as, for example, 90°. The disclosed configuration increases a contact area between the heat dissipation air flow and theheat dissipation fins 290, thereby improving the convective heat exchange effect, increasing the heat dissipation efficiency, and achieving a better heat dissipation effect for theheat generating device 90. - Referring to
FIG. 1 andFIG. 3 , in some embodiments, thehousing 10 may include two air outlet groups. Each air outlet group may include at least onefirst air outlet 102. The two air outlet groups may be disposed at two opposing sides of thehousing 10 respectively. The plurality ofheat dissipation fins 290 may include two heat dissipation fin groups. Heatdissipation air channels 200 of the two heat dissipation fin groups may be symmetrically disposed relative to thehousing 10, such that thesecond air outlets 202 of the heatdissipation air channel 200 of the two heat dissipation fin groups correspond to thefirst air outlets 102 of the two air outlet groups. As shown inFIG. 1 , each air outlet group may include twofirst air outlets 102. This configuration may enable the heat dissipation air flow to uniformly flow in thehousing 10. The heat dissipation air flow may flow out from two sides of thehousing 10 simultaneously through the heatdissipation air channels 200 of the two heat dissipation fin groups. As a result, heat generated by theheat generating device 90 may be more uniformly dissipated, which may result in an improved heat dissipation efficiency. - In some embodiments, the
heat dissipation fan 30 may include afirst fan housing 304 and asecond fan housing 305 enclosing thefirst fan housing 304. Thefirst fan housing 304 may be a metal alloy housing. Thesecond fan housing 305 may be a plastic housing. Thus, theheat dissipation fan 30 may not only increases the strength of the structure, but also reduces the weight of the structure. In some embodiments, thefirst fan housing 304 may be a copper alloy housing, which may help theheat generating device 90 effectively dissipate heat. - In some embodiments, the metal alloy
heat dissipation device 20 may be a Magnesium alloy heat dissipation device. In other words, theheat dissipation fins 290 may include a Magnesium alloy material, which may further reduce the weight of the metal alloyheat dissipation device 20. Theheat dissipation fan 30 may be a thin centrifugal fan. In other words, an opening direction of thethird air inlet 301 of theheat dissipation fan 30 may be disposed in parallel with the axis direction (e.g., the Y direction shown inFIG. 3 ) of theheat dissipation fan 30. An opening direction (e.g., the X direction shown inFIG. 3 ) of thethird air outlet 302 of theheat dissipation fan 30 may be disposed perpendicularly with an axis direction (e.g., the Y direction shown inFIG. 3 ). Theheat dissipation fan 30 may provide a strong wind volume and strong wind pressure to more effectively dissipate heat generated by theheat generating device 90. - In some embodiments, the
heat dissipation fan 30 may draw cold air through thefirst air inlet 101 disposed on thehousing 10, which may be connected with thethird air inlet 301. Theheat dissipation fan 30 may blow the heat dissipation air flow out through thethird air outlet 302. The heat dissipation air flow may flow into the heatdissipation air channel 200 of the alloyheat dissipation device 20 through thesecond air inlet 201 of the heatdissipation air channel 200 of the alloyheat dissipation device 20. The alloyheat dissipation device 20 may conduct heat from theheat generating device 90, and may convectively exchange heat with the heat dissipation air flow blown by theheat dissipation fan 30, thereby achieving heat dissipation for theheat generating device 90. The heat dissipation air flow may exit thehousing 10 from two sides of thehousing 10 through thefirst air outlets 102 provided on thehousing 10 that are connected with thesecond air outlets 202 of the heatdissipation air channel 200 of the alloyheat dissipation device 20, thereby forming a complete heat dissipation system. In some embodiments, theheat dissipation fan 30 may have a thin centrifugal fan to provide a strong wind volume and wind pressure. In some embodiments, the alloyheat dissipation device 20 may be a Magnesium heat dissipation device, which may further reduce the weight of the heat dissipation structure. Thus, the heat dissipation structure of the present disclosure may not only increase the heat dissipation efficiency, but also reduce the weight of the heat dissipation structure. In addition, the heat dissipation structure of the present disclosure may not only improve heat dissipation performance, but also solve the difficult issue ofUAV 1 weight increase due to the heat dissipation structure. The present disclosure provides an optimal balance between the heat dissipation performance and the weight reduction of theUAV 1. The present disclosure also provides the strongest heat dissipation performance with the smallest weight, and can save the heat dissipation space to the maximum extent. - In some embodiments, a shielding
cover 40 may be provided between theheat generating device 90 and the alloyheat dissipation device 20. In some embodiments, the shieldingcover 40 may be a copper alloy shielding cover. In some embodiments,heat conducting gels 50 may be provided between the shieldingcover 40 and theheat generating device 90 and between the shieldingcover 40 and the allowheat dissipation device 20. - In some embodiments, the shielding
cover 40 may include a copper alloy with a high heat conduction coefficient to increase heat dissipation. Because fins of complex air channel cannot be provided onto the shieldingcover 40 through brazing, the shieldingcover 40 and the alloyheat dissipation device 20 may be independently disposed. The shieldingcover 40 may provide not only a shielding function, but also a heat dissipation function. Theheat dissipation fins 290 of the alloyheat dissipation device 20 may form corresponding heatdissipation air channels 200 based on the location of thefirst air outlet 102. Theheat conducting gels 50 may fill air gaps between the shieldingcover 40 and theheat generating device 90 and between the shieldingcover 40 and the alloyheat dissipation device 20, which may also dissipate heat from theheat generating device 90. - In some embodiments, wind blocking foams may be provided between the
heat dissipation fan 30 and thehousing 10 and between the alloyheat dissipation device 20 and thehousing 10. For example, the wind blocking foams 303 may be provided right above thethird air outlet 302 of theheat dissipation fan 30, to restrain theheat dissipation fan 30 from sucking in hot air from thethird air inlet 301. The wind blocking foams may be provided above the alloyheat dissipation device 20 to avoid leakage of the heat dissipation air flow. As a result, the cold air drawn from thefirst air inlet 101 of thehousing 10 may flow quickly and efficiently through all key locations after passing through theheat dissipation fan 30, to highly effectively take heat away from theheat generating device 90. Accordingly, a stable and reliable operating environment may be provided to a small-sized UAV. - Referring to
FIG. 1 andFIG. 2 , theUAV 1 may include acamera assembly 60, apropeller assembly 70, theheat generating device 90, and the heat dissipation structure described above. Thecamera assembly 60 may be provided at a front lower portion of thehousing 10. Thepropeller assembly 70 may be provided around thehousing 10 at various locations. Theheat generating device 90 may include a circuit board, abattery module 130, or other heat generating devices or parts. - In some embodiments, in the
UAV 1 of the present disclosure, the alloyheat dissipation device 20 of the heat dissipation structure may conduct heat from theheat generating device 90 through convective heat exchange. The alloyheat dissipation device 20 may exchange heat with the heat dissipation air flow blown by theheat dissipation fan 30, thereby dissipating heat for theheat generating device 90. The configurations of the air inlets and air outlets of the heat dissipation fan 30 (e.g., the configurations of thethird air inlet 301 and the third air outlet 302) may provide a strong wind volume and wind pressure. In addition, the alloyheat dissipation device 20 is light weight, which can not only increase the heat dissipation efficiency, but also reduce the weight of the heat dissipation structure. As a result, the disclosed heat dissipation structure can not only improve the heat dissipation performance, but also solve the difficulty issue ofUAV 1 weight increase due to the heat dissipation structure. The present disclosure optimally balances the heat dissipation performance and the weight reduction of theUAV 1. The present disclosure also provides the strongest heat dissipation performance with the smallest weight, and saves the heat dissipation space to the maximum extent. - In some embodiments, the
first air inlet 101 and thecamera assembly 60 are located on the same side of thehousing 10. Thefirst air inlet 101 may be provided at a bottom side of thehousing 10. The heat dissipation structure draws cold air from the front lower portion of thehousing 10, and expels hot air from two sides of the middle portion of thehousing 10, thereby forming a high-efficiency heat dissipation channel to dissipate heat generated by theheat generating device 90 disposed inside theUAV 1. The heat dissipation cold air flow drawn from outside environment may also dissipate heat for thecamera assembly 60 to enable thecamera assembly 60 to function stably and reliably. - In some embodiments, the
housing 10 may include afirst housing 110 and asecond housing 120. Thefirst housing 110 and thesecond housing 120 may form a receiving space therebetween. The alloyheat dissipation device 20, theheat dissipation fan 30, and theheat generating device 90 may be disposed in the receiving space. In some embodiments, thefirst housing 110 and thesecond housing 120 may be plastic housings. In some embodiments, abattery module 130 may be provided below thesecond housing 120. - In some embodiments, the
UAV 1 of the present disclosure includes a heat dissipation structure including a thin centrifugal fan and a Magnesium alloy heat dissipation device. Cold air may be drawn from the external environment from a front lower portion of thehousing 10, and hot air may be blown out from two sides of the middle portion of thehousing 10, thereby forming a high-efficiency heat dissipation channel to dissipate heat from theheat generating device 90 disposed inside theUAV 1. Because theheat dissipation fins 290 of the alloyheat dissipation device 20 are not exposed, the internal structure of theentire UAV 1 are enclosed by a plastic housing. When a user or operator touches the external plastic surface of theUAV 1, the user or operator would not have a scorching feeling on the hand. Further, because theheat dissipation fan 30 is separated by the housing of theUAV 1 from the external environment, the acoustic noise is effectively insulated, and the noise level is reduced. - The above descriptions explain in detail the various embodiments of the disclosed structures. The above descriptions use detailed examples to explain the principle and implementation of the disclosed structures. These explanations of the various embodiments are intended to facilitate the understanding of the disclosed structures and the ideas. A person having ordinary skills in the art may modify the detailed implementation and the application scope based on the present disclosure. Thus, the content of the present specification should not be interpreted as being limiting the scope of the present disclosure.
- Other embodiments of the present disclosure will be apparent to those skilled in the art from consideration of the specification and practice of the embodiments disclosed herein. It is intended that the specification and examples be considered as example only and not to limit the scope of the present disclosure, with a true scope and spirit of the invention being indicated by the following claims. Variations or equivalents derived from the disclosed embodiments also fall within the scope of the present disclosure.
Claims (17)
1. An unmanned aerial vehicle comprising:
a camera assembly;
a heat generating device; and
a heat dissipation structure including:
a housing configured to receive the heat generating device, the housing including a first air inlet and a first air outlet, the first air inlet and the camera assembly being located at a same side of the housing, and the camera assembly being disposed at a front portion of the housing;
a heat dissipation device disposed in the housing and including a plurality of heat dissipation fins disposed in parallel with one another, a heat dissipation air channel being formed between two adjacent heat dissipation fins, the heat dissipation air channel including a second air inlet and a second air outlet, and the second air outlet being connected with the first air outlet; and
a heat dissipation fan disposed inside the housing and configured to provide a heat dissipation air flow to an inside space of the housing, the heat dissipation fan including a third air inlet and a third air outlet, the third air inlet being connected with the first air inlet, and the third air outlet being connected with the second air inlet.
2. The unmanned aerial vehicle of claim 1 , wherein the first air inlet and the camera assembly are located at a lower side of the housing.
3. The unmanned aerial vehicle of claim 1 , wherein the housing includes a first housing and a second housing together forming a receiving space, the receiving space being configured to receive the heat generating device, the heat dissipation device, and the heat dissipation fan.
4. The unmanned aerial vehicle of claim 3 , wherein the heat dissipation device is fully accommodated in the receiving space.
5. The unmanned aerial vehicle of claim 3 , wherein the first air inlet and the camera assembly are located at a lower side of the second housing.
6. The unmanned aerial vehicle of claim 1 , wherein the heat dissipation fan includes a first fan housing and a second fan housing enclosing the first fan housing.
7. The unmanned aerial vehicle of claim 6 , wherein the first fan housing includes an alloy housing and the second fan housing includes a plastic housing.
8. The unmanned aerial vehicle of claim 1 , wherein the heat dissipation device includes an alloy heat dissipation device.
9. The unmanned aerial vehicle of claim 1 , wherein:
the heat dissipation air channel includes a first air channel and a second air channel;
each of the heat dissipation fins includes a first fin portion and a second fin portion, the first fin portion and the second fin portion being slantly disposed; and
two first fin portions of two adjacent heat dissipation fins form the first air channel, and two second fin portions of the two adjacent heat dissipation fins form the second air channel.
10. The unmanned aerial vehicle of claim 9 , wherein:
the heat dissipation air channel further includes a third air channel located between the first air channel and the second air channel;
each of the heat dissipation fins further includes an arc-shaped transition portion connecting the first fin portion and the second fin portion; and
two arc-shaped transition portions of the two adjacent heat dissipation fins form the third air channel.
11. The unmanned aerial vehicle of claim 1 , wherein:
the housing further includes two air outlet groups, each of the two air outlet groups includes at least one first air outlet, and the two air outlet groups are disposed on two opposing sides of the housing.
12. The unmanned aerial vehicle of claim 1 , wherein:
the plurality of heat dissipation fins include two heat dissipation fin groups; and
heat dissipation air channels of the two heat dissipation fin groups are symmetrically disposed relative to the housing.
13. The unmanned aerial vehicle of claim 1 , further comprising:
a shielding cover disposed between the heat generating device and the heat dissipation device.
14. The unmanned aerial vehicle of claim 13 , wherein the shielding cover includes a copper alloy shielding cover.
15. The unmanned aerial vehicle of claim 13 , wherein heat conducting gels are provided between the shielding cover and the heat generating device and between the shielding cover and the heat dissipation device.
16. The unmanned aerial vehicle of claim 1 , wherein wind blocking foams are disposed between the heat dissipation fan and the housing and between the heat dissipation device and the housing.
17. The unmanned aerial vehicle of claim 16 , wherein:
one of the wind blocking foams is disposed right above the third air outlet and between the heat dissipation fan and the housing.
Priority Applications (1)
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US17/457,697 US20220089271A1 (en) | 2017-05-19 | 2021-12-06 | Unmanned aerial vehicle and heat dissipation structure |
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CN201720560892.X | 2017-05-19 | ||
CN201720560892.XU CN206865924U (en) | 2017-05-19 | 2017-05-19 | Unmanned plane and radiator structure |
PCT/CN2017/090972 WO2018209771A1 (en) | 2017-05-19 | 2017-06-30 | Unmanned aerial vehicle and heat dissipation structure |
US16/687,258 US11192622B2 (en) | 2017-05-19 | 2019-11-18 | Unmanned aerial vehicle and heat dissipation structure |
US17/457,697 US20220089271A1 (en) | 2017-05-19 | 2021-12-06 | Unmanned aerial vehicle and heat dissipation structure |
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CN (2) | CN206865924U (en) |
WO (1) | WO2018209771A1 (en) |
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Also Published As
Publication number | Publication date |
---|---|
CN109892030A (en) | 2019-06-14 |
CN206865924U (en) | 2018-01-09 |
CN109892030B (en) | 2021-10-22 |
WO2018209771A1 (en) | 2018-11-22 |
US20200102061A1 (en) | 2020-04-02 |
US11192622B2 (en) | 2021-12-07 |
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