CN117734984A - Electric-control heat dissipation rectifying device and aircraft - Google Patents
Electric-control heat dissipation rectifying device and aircraft Download PDFInfo
- Publication number
- CN117734984A CN117734984A CN202311462837.3A CN202311462837A CN117734984A CN 117734984 A CN117734984 A CN 117734984A CN 202311462837 A CN202311462837 A CN 202311462837A CN 117734984 A CN117734984 A CN 117734984A
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- heat dissipation
- fairing
- power arm
- electric
- fins
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- 230000017525 heat dissipation Effects 0.000 title claims abstract description 128
- 239000004677 Nylon Substances 0.000 claims description 5
- 229920001778 nylon Polymers 0.000 claims description 5
- 239000002184 metal Substances 0.000 claims description 3
- 230000005855 radiation Effects 0.000 abstract description 5
- 230000001105 regulatory effect Effects 0.000 abstract description 2
- 230000000694 effects Effects 0.000 description 9
- 230000005611 electricity Effects 0.000 description 6
- 238000009434 installation Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 238000011900 installation process Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 238000005266 casting Methods 0.000 description 1
- 230000001276 controlling effect Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
Abstract
The invention provides an electric-regulation heat-dissipation rectifying device and an aircraft, wherein the device comprises an electric regulator arranged on an external power arm, heat-dissipation fins arranged on the outer side of the electric regulator, and a first fairing and a second fairing which are respectively positioned on two sides of the heat-dissipation fins; the first fairing and the second fairing are installed and fixed on the power arm and are matched with the radiating fins to form a streamline structure. The invention can reduce the air resistance of the radiating fins while realizing electrically-regulated heat radiation.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to an electrically-regulated heat dissipation rectifying device and an aircraft.
Background
Currently, unmanned aircraft, abbreviated as "unmanned aerial vehicle", english abbreviated as "UAV", is mainly unmanned aircraft, which is operated by a radio remote control device and a self-contained program control device, or aircraft, which is operated autonomously, either entirely or intermittently, by an on-board computer.
In the existing unmanned aerial vehicle structure, in order to reduce the flight resistance of power arm, can generally with unmanned aerial vehicle's electricity transfer heat radiation structure setting in the inside of power arm, this structure although can reduce air resistance, nevertheless has certain requirement to the inner space of power arm, in addition because heat radiation structure setting in the inside of power arm, also can influence the radiating effect that the electricity was transferred for the electricity is transferred heat radiation structure and can't compromise heat dissipation and drag reduction.
Therefore, there is a need for an electrically-controlled heat dissipation and rectification device that can reduce the resistance to the power arm while ensuring the electrically-controlled heat dissipation and overcoming the limitations of the installation location.
Disclosure of Invention
In view of the above problems, the present invention is to provide an electrically-controlled heat dissipation rectifying device and an aircraft, so as to solve the problems of the existing electrically-controlled installation method that the internal space of the power arm is required, and the heat dissipation effect of the electrically-controlled heat dissipation is poor.
The invention provides an electric-regulation heat-dissipation rectifying device, which comprises an electric regulator arranged on a power arm, heat-dissipation fins arranged on the outer side of the electric regulator, and a first rectifying cover and a second rectifying cover which are respectively positioned on two sides of the heat-dissipation fins; the first fairing and the second fairing are installed and fixed on the power arm and are matched with the radiating fins to form a streamline structure.
In addition, the optional technical scheme is that the radiating fins are vertically distributed, and the distribution direction of the radiating fins is vertical to the extending direction of the power arm; the outer sides of the radiating fins are provided with radiating baffles, and the arrangement direction of the radiating baffles is consistent with the extension direction of the power arms.
In addition, the optional technical scheme is that in the direction perpendicular to the power arm, the air flow conducts vertically through gaps among the radiating fins.
In addition, an alternative technical scheme is that the heat dissipation baffle is fixed on the outer side of the heat dissipation fin through rivets.
In addition, the optional technical scheme is that the first fairing, the second fairing and the heat dissipation baffle are of an integrated structure.
In addition, the optional technical scheme is that one end of the first fairing is a rectangular opening matched with the shape of the radiating fin, and the other end is a bullet-shaped streamline structure; the second cowling has the same structure as the first cowling.
Furthermore, an alternative solution is that the first fairing is fixed to the power arm by at least two L-shaped connectors; one fixing surface of the L-shaped connecting piece is fixedly connected with the shell of the power arm through a screw, and the other fixing surface is fixedly connected with the side wall of the first fairing through a screw; and the radian of the other fixing surface is consistent with that of the side wall of the first fairing.
In addition, the optional technical scheme is that the first fairing and the second fairing are nylon pieces; the heat dissipation baffle is a metal piece.
In addition, the alternative technical scheme is that the heat dissipation baffle is of a plane structure or a streamline structure.
On the other hand, the invention also provides an aircraft, which comprises 4 power arms, 4 cantilevers arranged on each power arm and propellers respectively positioned at the end parts of the 4 power arms; wherein, 4 electric heat dissipation and rectification devices are respectively arranged on each power arm, and the electric heat dissipation and rectification devices are as described above.
By utilizing the electric-tuning heat dissipation rectifying device and the aircraft, the electric-tuning heat dissipation fins are arranged outside the power arms, the first fairing and the second fairing are respectively arranged on two sides of the heat dissipation fins, the first fairing and the second fairing are fixedly arranged on the power arms and are matched with the heat dissipation fins to form a streamline appearance structure, the occupation of the electric-tuning heat dissipation structure on the inner space of the power arms can be effectively reduced, the power arms can be made to be smaller in size, the heat dissipation effect of the electric tuning can be improved, the air resistance of the electric-tuning heat dissipation fins is reduced, and the integral flying performance of the aircraft is improved.
To the accomplishment of the foregoing and related ends, one or more aspects of the invention comprise the features hereinafter fully described. The following description and the annexed drawings set forth in detail certain illustrative aspects of the invention. These aspects are indicative, however, of but a few of the various ways in which the principles of the invention may be employed. Furthermore, the invention is intended to include all such aspects and their equivalents.
Drawings
Other objects and attainments together with a more complete understanding of the invention will become apparent and appreciated by referring to the following description taken in conjunction with the accompanying drawings. In the drawings:
FIG. 1 is a perspective view of an electrically tunable heat dissipation and rectification device in accordance with an embodiment of the present invention;
FIG. 2 is a top view of an electrically tunable heat dissipation and rectification device in accordance with an embodiment of the present invention;
FIG. 3 is a side view of an electrically tunable heat dissipation and rectification device in accordance with an embodiment of the present invention;
FIG. 4 is an enlarged view of a portion A of FIG. 1;
FIG. 5 is a partial top view of an electrically tunable heat dissipation and rectification device in accordance with an embodiment of the present invention;
fig. 6 is a partial side view of an electrically tunable heat dissipation and rectification device in accordance with an embodiment of the present invention.
The labels in the figures are as follows: the power arm 1, the electric-regulation heat dissipation rectifying device 31, the electric-regulation heat dissipation rectifying device 32, the electric-regulation heat dissipation rectifying device 33, the electric-regulation heat dissipation rectifying device 34, the heat dissipation fins 4, the first rectifying cover 51, the second rectifying cover 52, the heat dissipation baffle 6 and the L-shaped connecting piece 7.
The same reference numerals will be used throughout the drawings to refer to similar or corresponding features or functions.
Detailed Description
The details of one or more embodiments of the invention will be apparent from the description of the embodiments of the invention set forth in the accompanying drawings, which are incorporated in the description of the invention. All other embodiments, which can be obtained by modification without inventive effort by a person skilled in the art based on the embodiments of the present invention, are also within the scope of protection of the present invention.
The terminology used in the following embodiments is for the purpose of describing or illustrating particular embodiments only and is not intended to be limiting of the scope of the present invention. Furthermore, as used in this specification, the singular forms such as "a," "an," "the," and "the" are intended to include the plural forms such as "one or more" unless the context clearly indicates to the contrary. It should also be understood that when terms such as "one or more," "at least one," "more," and the like are used in the detailed description of the invention, it is intended to include one, two, and at least three.
In addition, when terms such as "in one embodiment," "in some embodiments," "in one or more embodiments," etc. are used in the specification of the present invention, it is intended that one or more embodiments of the present invention may include specific technical features described in connection with the embodiment. Thus, appearances of the phrases "in one embodiment," "in some embodiments," "in one or more embodiments," or "in other embodiments" in various places throughout this specification are not necessarily all referring to the same embodiment, but may also refer to the same embodiment, or different embodiments, unless the specific features described in the embodiments are used alone or in combination.
It should be understood that when sequential terms such as "first", "second", etc. are used in the following description of the present invention to describe various elements, these sequential terms should only be used to distinguish one element from another element, and should not be interpreted as meaning that the terms such as "first", "second", etc. are intended to indicate a primary and secondary relationship, precedence relationship, etc. The first element may be referred to as a second element, and the second element may be referred to as the first element, without departing from the scope of the invention.
In the description of the present invention, it should be understood that the terms "center," "longitudinal," "transverse," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," "circumferential," etc. as indicated below, are based on the orientation or positional relationship shown in the drawings, merely for convenience of description and to simplify the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as limiting the content or structure of the present invention.
The electric power adjusting device aims at solving the problems that the existing electric power adjusting installation mode has requirements on the inner space of a power arm, the electric power adjusting heat dissipation effect is poor, and the like. The invention provides an electric-tuning heat dissipation rectifying device and an aircraft, wherein heat dissipation equipment of an electric tuning is arranged outside a power arm, and fairing structures are respectively arranged at two sides of a heat dissipation fin, so that the fairings and the heat dissipation fins are matched to form a streamline structure.
In order to describe the structure of the electrically-controlled heat dissipation rectifying device and the aircraft in detail, the following detailed description of the embodiments of the present invention will be given with reference to the accompanying drawings.
Fig. 1 to 4 show a three-dimensional structure, a top view structure, a side view structure and a partially enlarged structure of an electrically-controlled heat dissipation rectifying device according to an embodiment of the present invention, respectively.
As shown in fig. 1 to 4 together, the electrically-controlled heat dissipation rectifying device according to the embodiment of the present invention includes an electric control provided on a power arm 1, heat dissipation fins 4 provided outside the electric control, and first and second fairings 51 and 52 respectively provided on both sides of the heat dissipation fins 4; the first fairing 51 and the second fairing 52 are installed and fixed on the power arm 1 and cooperate with the radiating fins 4 to form a streamline structure, so that not only can the electric adjustment on the outer side of the power arm 1 be reduced and the resistance of the radiating fins 4 be reduced, but also the radiating effect of the radiating fins 4 can be improved, the occupation of the radiating fins on the inner space of the power arm 1 can be reduced, and the improvement design of the structure of the power arm 1 is facilitated.
Specifically, the radiating fins 4 located on the outer side of the electric regulator can be vertically distributed, the distribution direction of the radiating fins 4 is perpendicular to the extending direction of the power arm 1, meanwhile, the radiating baffle 6 can be arranged on the outermost side of the radiating fins 4, the arrangement direction of the radiating baffle 6 is consistent with the extending direction of the power arm 1, the local structure of the radiating fins 4 is shielded by the radiating baffle 6, the positions located on the upper side and the lower side of the radiating baffle 6 are open structures, air flow can be vertically conducted in the direction perpendicular to the power arm 1 through gaps among the radiating fins 4, the air flow is known to be non-conducting in the transverse direction perpendicular to the radiating fins 4, the radiating baffle 6 is matched with the first fairing 51 and the second fairing 52 to form a streamline structure, the horizontal air flow can smoothly bypass, flow separation and vortex are formed, the resistance of the device before cruising is reduced, and meanwhile, the vertical air flow can freely pass through the radiating fins 4, and therefore the radiating effect on the electric regulator is effectively improved.
It should be noted that, the heat dissipation fin 4 may be disposed outside the power arm 1, the heat dissipation surface area of the electric adjustment is increased by the heat dissipation fin 4, and the heat dissipation baffle 6 is disposed on one side, so that the air flow vertically flowing through the heat dissipation fin 4 is fast, the heat dissipation effect is improved, and the electric adjustment disposed inside the heat dissipation fin 4 may be disposed inside the power arm 1 or disposed outside the power arm 1 together with the heat dissipation fin 4, and may be specifically adjusted according to the design requirement.
In one embodiment of the present invention, since the structure of the heat dissipation fin 4 is rectangular, one end of the first fairing 51 may be provided with a rectangular opening adapted to the shape of the heat dissipation fin 4, and the other end is a bullet-shaped streamline structure, correspondingly, the structures of the second fairing 52 and the first fairing 51 are the same, and the structures are symmetrically distributed about the heat dissipation fin 4, so that the first fairing 51, the heat dissipation baffle 6 outside the heat dissipation fin 4 and the second fairing 52 form a shuttle-shaped streamline structure; in addition, the heat dissipation baffle 6 can be set to be of a planar structure or a streamline structure, namely, the heat dissipation baffle 6 can be set to be of a flat plate structure attached to the heat dissipation fins 4, and can also be set to be of an arc shape, and the outer end face of the heat dissipation fins 4 can also be set to be of an arc structure corresponding to the heat dissipation baffle 6, so that the heat dissipation baffle 6 can be attached to the heat dissipation fins 4 all the time for positioning, the bearing capacity of the heat dissipation baffle to wind power is increased, and the occurrence of bulge deformation energy is prevented.
Fig. 5 and 6 respectively show a partially schematic structure of an electrically-controlled heat dissipation rectifying device according to an embodiment of the present invention with the second fairing removed.
As shown in fig. 1 to 6 together, in the installation process of the heat dissipation baffle 6, the first fairing 51 and the second fairing 52, the electric-control heat dissipation rectifying device of the invention can adopt structural members such as bolts or rivets to position corresponding components on the heat dissipation fins 4 and the shells of the power arms 1; taking the fixing manner of the first fairing 51 as an example (the fixing manner of the second fairing 52 and the first fairing 51 are the same), it can be fixed on the power arm 1 through at least two L-shaped connectors 7; each L-shaped connecting piece 7 comprises two mutually perpendicular fixing surfaces, wherein one fixing surface is fixedly connected with the shell of the power arm 1 through a screw, and the other fixing surface is fixedly connected with the side wall of the first fairing 51 through a screw; and the radian of the other fixing surface is consistent with that of the side wall of the first fairing 51, so that the other fixing surface can be attached to the inner side wall of the first fairing 51, and finally the first fairing 51 is fixedly connected with the L-shaped connecting piece 7 through bolts or rivets.
It should be noted that, the heat dissipation baffle 6 may be locked on the heat dissipation fins 4 by a screw or a bolt alone, or, to simplify the assembly process, the heat dissipation baffle 6 and the first fairing 51 and the second fairing 52 may be provided as an integrally formed structure, that is, the heat dissipation baffle 6, the first fairing 51 and the second fairing 52 may be formed as an integrally formed structure by casting or stamping, etc., and in the installation process, the heat dissipation baffle 6 and the first fairing 51 and the second fairing 52 may be directly covered on the outer sides of the heat dissipation fins 4 and then integrally fixed by a connecting piece.
In another embodiment of the present invention, four electrically-controlled heat dissipation and rectification devices may be disposed on one power arm, including electrically-controlled heat dissipation and rectification device 31, electrically-controlled heat dissipation and rectification device 32, electrically-controlled heat dissipation and rectification device 33, and electrically-controlled heat dissipation and rectification device 34, but the present invention is not limited to this specific structure, and the number of electrically-controlled heat dissipation and rectification devices may be adjusted according to the length of the power arm and the design requirement during the application process.
In order to reduce the weight of the fairing, the first fairing 51 and the second fairing 52 can be made of light materials such as nylon, i.e. the first fairing 51 and the second fairing 52 can be made of nylon pieces; the heat dissipation baffle 6, which can dissipate heat and reduce air resistance, can be made of light materials such as metal pieces or nylon pieces. The first fairing 51, the second fairing 52 and the heat dissipation baffle 6 may be assembled separately, or the heat dissipation baffle 6 is assembled with the first fairing 51 and the second fairing 52 first, and then the formed assembly is mounted with the heat dissipation fins 4 and the housing of the power arm 1, so as to ensure the position consistency between the two fairings and the heat dissipation fins; alternatively, the first cowling 51, the second cowling 52, and the heat radiation baffle 6 may be integrally assembled after being integrally formed.
Correspondingly to the electric-regulation heat-dissipation rectifying device, the invention also provides an aircraft, which comprises 4 power arms, 4 cantilevers arranged on each power arm and propellers respectively positioned at the end parts of the 4 power arms; wherein, be provided with 4 electricity on every power arm respectively and transfer heat dissipation fairing, and one side of every power arm sets up two electricity respectively and transfers heat dissipation fairing, and the position that is located 4 electricity on same power arm transfers heat dissipation fairing staggers each other and distributes to be symmetrical about the center of power arm.
Specifically, the electric power conditioner in the aircraft is called an electronic speed regulator, is used for supplying power to the motor and controlling the rotating speed of the motor to complete specified speed and action, is a bridge for connecting the motor in a fly-controlled manner, and is divided into brushless electric power conditioner and brush electric power conditioner, and corresponds to the brushless motor and the brush motor respectively. The motor of the aircraft is connected with the propeller, the motor only works in the low-speed and take-off and landing stages of the equipment, the motor does not work in the cruising stage of the equipment, and the heat dissipation effect can be not considered at the moment, so that the resistance is minimum, and the electric-control heat dissipation rectifying device can be arranged below the propeller, so that the downward wind of the vertical take-off and landing propeller vertically passes through the heat dissipation fins, the extra heat dissipation fan is saved, and the heat dissipation effect is improved.
It should be noted that, the embodiments of the aircraft may refer to the descriptions in the embodiments of the electrically-controlled heat dissipation and rectification device, and are not described herein in detail.
According to the electric-tuning heat dissipation rectifying device and the aircraft, the electric-tuning heat dissipation fins are arranged outside the power arms, and the heat dissipation baffle plates and the fairing structures positioned on the two sides are arranged on the heat dissipation fins, so that the fairings, the heat dissipation baffle plates and the heat dissipation fins are matched to form a streamline structure.
An electrically tunable heat dissipation and rectification device and an aircraft according to the present invention are described above by way of example with reference to the accompanying drawings. However, it will be appreciated by those skilled in the art that various modifications may be made to the electrically tunable heat dissipation and rectification device and aircraft as set forth above without departing from the teachings of the present invention. Accordingly, the scope of the invention should be determined from the following claims.
Claims (10)
1. The electric-regulation heat-dissipation rectifying device is characterized by comprising an electric regulator arranged on a power arm, heat-dissipation fins arranged on the outer side of the electric regulator, and a first rectifying cover and a second rectifying cover which are respectively positioned on two sides of the heat-dissipation fins; wherein,
the first fairing and the second fairing are fixedly arranged on the power arm and are matched with the radiating fins to form a streamline structure.
2. The electrically tunable heat dissipation and rectification device of claim 1, wherein,
the radiating fins are vertically distributed, and the distribution direction of the radiating fins is vertical to the extending direction of the power arm;
the outer sides of the radiating fins are provided with radiating baffles, and the arrangement direction of the radiating baffles is consistent with the extension direction of the power arms.
3. The electrically tunable heat dissipation and rectification device of claim 2, wherein,
and in the direction perpendicular to the power arm, the air flow is vertically conducted through gaps among the radiating fins.
4. The electrically tunable heat dissipation and rectification device of claim 2, wherein,
the heat dissipation baffle is fixed on the outer side of the heat dissipation fin through rivets.
5. The electrically tunable heat dissipation and rectification device of claim 2, wherein,
the first fairing, the second fairing and the heat dissipation baffle are of an integrated structure.
6. The electrically tunable heat dissipation and rectification device of claim 1, wherein,
one end of the first fairing is a rectangular opening matched with the shape of the radiating fin, and the other end of the first fairing is a bullet-shaped streamline structure; and, in addition, the processing unit,
the second fairing is identical to the first fairing in structure.
7. The electrically tunable heat dissipation and rectification device of claim 1, wherein,
the first fairing is fixed on the power arm through at least two L-shaped connecting pieces;
one fixing surface of the L-shaped connecting piece is fixedly connected with the shell of the power arm through a screw, and the other fixing surface is fixedly connected with the side wall of the first fairing through a screw;
and the radian of the other fixing surface is consistent with the radian of the side wall of the first fairing.
8. The electrically tunable heat dissipation and rectification device of claim 2, wherein,
the first fairing and the second fairing are nylon pieces;
the heat dissipation baffle is a metal piece.
9. The electrically tunable heat dissipation and rectification device of claim 2, wherein,
the heat dissipation baffle is of a plane structure or a streamline structure.
10. An aircraft, comprising 4 power arms, 4 cantilevers arranged on each power arm and propellers respectively positioned at the end parts of the 4 power arms; wherein,
4 electrically-controlled heat dissipation and rectification devices are respectively arranged on each power arm, and the electrically-controlled heat dissipation and rectification devices are as claimed in any one of claims 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311462837.3A CN117734984A (en) | 2023-11-03 | 2023-11-03 | Electric-control heat dissipation rectifying device and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311462837.3A CN117734984A (en) | 2023-11-03 | 2023-11-03 | Electric-control heat dissipation rectifying device and aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117734984A true CN117734984A (en) | 2024-03-22 |
Family
ID=90251600
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311462837.3A Pending CN117734984A (en) | 2023-11-03 | 2023-11-03 | Electric-control heat dissipation rectifying device and aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117734984A (en) |
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2023
- 2023-11-03 CN CN202311462837.3A patent/CN117734984A/en active Pending
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