CN110352162A - Unmanned plane and its casing - Google Patents
Unmanned plane and its casing Download PDFInfo
- Publication number
- CN110352162A CN110352162A CN201880014411.2A CN201880014411A CN110352162A CN 110352162 A CN110352162 A CN 110352162A CN 201880014411 A CN201880014411 A CN 201880014411A CN 110352162 A CN110352162 A CN 110352162A
- Authority
- CN
- China
- Prior art keywords
- casing
- unmanned plane
- inlet channel
- side wall
- wind inlet
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Withdrawn
Links
- 230000008676 import Effects 0.000 claims abstract description 4
- 230000004580 weight loss Effects 0.000 claims description 4
- 230000000694 effects Effects 0.000 abstract description 4
- 238000001816 cooling Methods 0.000 abstract description 3
- 239000003570 air Substances 0.000 description 28
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 6
- 230000005611 electricity Effects 0.000 description 5
- 230000001681 protective effect Effects 0.000 description 5
- 230000008901 benefit Effects 0.000 description 3
- 239000003292 glue Substances 0.000 description 3
- 238000009423 ventilation Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 239000002360 explosive Substances 0.000 description 2
- 230000010354 integration Effects 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 230000009466 transformation Effects 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 239000012080 ambient air Substances 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000005672 electromagnetic field Effects 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000004033 plastic Substances 0.000 description 1
- 229920003023 plastic Polymers 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U20/00—Constructional aspects of UAVs
- B64U20/90—Cooling
- B64U20/96—Cooling using air
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U20/00—Constructional aspects of UAVs
- B64U20/70—Constructional aspects of the UAV body
-
- 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
- B64U30/29—Constructional aspects of rotors or rotor supports; Arrangements thereof
- B64U30/291—Detachable rotors or rotor supports
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Cooling Or The Like Of Electrical Apparatus (AREA)
Abstract
A kind of unmanned plane and casing (1), casing (1) is built-in with the heater element (5) of unmanned plane, it is provided on casing (1) wind inlet channel (8), the paddle wind that wind inlet channel (8) is used to generate when rotating propeller (3) imports in casing (1)；The bottom of casing (1) is equipped with air outlet, and air outlet exports casing (1) for that will carry out the paddle wind after hot transmitting with heater element (5)；Wherein, air outlet is arranged to be used at least one through-hole (131) matched with the radiator (7) of heater element (5).The technical solution is by being arranged wind inlet channel (8) on casing (1), and air outlet is set in the bottom of casing (1), paddle wind so as to generate when rotating propeller (3) is imported into casing (1), then casing (1) is flowed out from air outlet with after heater element (5) the progress heat exchange in casing (1), and then is embodied as the effect of heater element (5) radiating and cooling.
Description
The present embodiments relate to a kind of unmanned plane and its casings, belong to unmanned vehicle technical field.
UAV is the not manned vehicle using radio robot and the presetting apparatus provided for oneself manipulation referred to as " unmanned plane " (" UAV ").Unmanned plane can be generally divided into: unmanned fixed wing aircraft, unmanned VTOL aircraft, unmanned airship, unmanned helicopter, unmanned multi-rotor aerocraft, unmanned parasol etc..
With the situation of selling well of unmanned plane, consumer is more and more for the demand of unmanned plane function, in order to bring better experience to client, present unmanned plane compared to several years ago, even for the unmanned plane produced a few months ago, can all increase many functions of improving user experiences, and/or improve flight safety.In order to realize these functions, inevitably in fuselage interior using the power consumption of more electronic components or increase electronic component, to meet the needs of new function.
But, although the power consumption for increasing electronic component or increase electronic component can increase the function of unmanned plane, and/or improve the safety of unmanned plane, but fuselage interior is also inevitably made to generate more heats, if cannot in time eliminate these heats, it just very likely will lead to unmanned plane and break down.
Summary of the invention
The embodiment of the present invention provides a kind of unmanned plane and its casing, to solve above or other potential problems of the existing technology.
According to an embodiment of the invention, providing a kind of casing of unmanned plane, the casing is built-in with the heater element of the unmanned plane, and wind inlet channel is provided on the casing, and the paddle wind that the wind inlet channel is used to generate when rotating the propeller imports in the casing；The bottom of the casing is equipped with air outlet, and the air outlet is used to carry out the paddle wind after hot transmitting with the heater element and exports the casing；Wherein, the air outlet is arranged to be used at least one through-hole matched with the radiator of the heater element.
Casing as described above, comprising: side wall, lid close the lower cover of upper cover and lid conjunction at the lower ending opening of side wall at the upper end opening of side wall；
The through-hole opened up on the lower lid includes at least one of strip-shaped hole, square hole, circular hole, windowing.
Casing as described above, wherein the strip-shaped hole extends along the length direction of the radiator.
Casing as described above, wherein the wind inlet channel includes: the through slot opened up on the side wall, and the deflector being arranged on the side wall or the lower lid；The deflector extends from the through slot toward the oblique upper far from the casing.
Casing as described above, wherein the wind inlet channel includes: the through slot opened up on the lower lid, and the deflector being arranged on the lower lid；The deflector extends from the through slot toward the oblique upper far from the casing.
Casing as described above, wherein the wind inlet channel includes: the through slot opened up on the cover, and the deflector being arranged on the upper cover, the side wall or the lower lid；The deflector extends from the through slot toward the oblique upper far from the casing.
Casing as described above, wherein the inner surface of the deflector towards the through slot is cambered surface.
Casing as described above, wherein the integral piece that the upper cover and the side wall are integrally formed, alternatively, the integral piece that the lower cover and the side wall are integrally formed.
Casing as described above, wherein the propeller rotation is formed with Plane of rotation, and the wind inlet channel is located in the Plane of rotation in the orthographic projection on the Plane of rotation.
Casing as described above, wherein the wind inlet channel is positioned close to the position of the front end of the casing.
According to an embodiment of the invention, providing a kind of unmanned plane, comprising: said machine casing, the heater element being mounted in the casing, propeller and the horn for connecting the casing and the propeller.
Unmanned plane as described above, wherein radiator is additionally provided between the heater element and the bottom of the casing, the radiator is fixed on the bottom of the electronic component.
Unmanned plane as described above, wherein the bottom of the radiator is provided with multiple heat radiating fins.
Unmanned plane as described above, wherein the horn includes: first support arm and second support arm, and has angle between the first support arm and second support arm；The first end of the first end of the first support arm and the second support arm is connect with the propeller, and the second end of the second end of the first support arm and the second support arm is connect with the casing respectively.
Unmanned plane as described above, wherein offer weight loss groove in the first support arm and second support arm.
Unmanned plane as described above, wherein the wind inlet channel of the casing is between the first support arm and second support arm.
According to the technical solution of the present embodiment, wind inlet channel is set on the side wall of the casing of unmanned plane and offers air outlet in the bottom of casing, in the accommodating chamber that the air for being formed by the top flow direction lower section of Plane of rotation from the rotation of the blade of propeller enters casing through the wind inlet channel, then hot transmitting is carried out with the electronic component installed in casing, finally accommodating chamber is flowed out from the air outlet of bottom of shell, to reduce the temperature of electronic component, so that the temperature of electronic component is able to maintain that within the temperature of normal work, then electronic component is capable of the work of normal table.
The advantages of additional aspect of the invention, will be set forth in part in the description, and partially will become apparent from the description below, or practice through the invention is recognized.
By referring to accompanying drawing described in detail below, the above and other objects, features and advantages of the embodiment of the present invention will become more clearly understood from.In the accompanying drawings, by by example and it is unrestricted in a manner of multiple embodiments of the invention are illustrated, in which:
Fig. 1 is the structural schematic diagram of unmanned plane provided in an embodiment of the present invention；
Fig. 2 is the explosive view of unmanned plane in Fig. 1；
Fig. 3 is the cross-sectional view of unmanned plane in Fig. 1；
Fig. 4 is the top view of radiator in Fig. 1；
Fig. 5 is the left view of radiator in Fig. 1；
Fig. 6 is the bottom view of radiator in Fig. 1；
Fig. 7 is the top view of lower cover in Fig. 1；
Fig. 8 is the left view of lower cover in Fig. 1；
Fig. 9 is the bottom view of lower cover in Fig. 1；
In figure:
1, casing；11, upper cover；12, side wall；
12a, front side wall；12b, rear wall；12c, left side wall；
12d, right side wall；13, lower cover；131, through-hole；
132, the first bolt hole；2, horn；21, first support arm；
22, second support arm；23, weight loss groove；3, propeller；
4, protective cover；5, heater element；6, electromagnetic shielding plate；
7, radiator；71, heat radiating fin；72, the second bolt hole；
8, wind inlet channel；81, through slot；82, deflector.
The embodiment of the present invention is described below in detail, examples of the embodiments are shown in the accompanying drawings, and in which the same or similar labels are throughly indicated same or similar element or elements with the same or similar functions.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to be used to explain the present invention, and be not considered as limiting the invention.
Fig. 1 is the structural schematic diagram of unmanned plane provided in this embodiment, and Fig. 2 is the explosive view of unmanned plane in Fig. 1；Fig. 3 is the cross-sectional view of unmanned plane in Fig. 1.As shown in Figure 1 to Figure 3, the unmanned plane of the present embodiment includes: fuselage, horn 2, Power Component and foot prop.In order to make those skilled in the art be better understood by the technical solution and its advantage of the present embodiment, the structure of unmanned plane is introduced according to the sequence of Power Component, horn 2, fuselage and foot prop below.
Referring to figs. 1 to Fig. 3, Power Component includes: propeller 3, motor (not shown) and electricity adjust (not shown).Propeller 3 is driven by a motor rotation, so that rising, advance, the rotation etc. for unmanned plane provide power.Propeller 3 has blade and propeller hub, the output shaft of propeller hub and motor is fixed, blade is mounted on propeller hub, when the output shaft of motor drives propeller hub rotation, the blade being mounted on propeller hub also follows rotation to form Plane of rotation, to which the air around propeller 3 to be guided to the lower section of Plane of rotation, namely downward paddle wind is formed, to provide lift for unmanned plane.Electricity calls to control motor work, it is electrically connected with the flight control circuit board that will be described below, with control signal control motor starting/stopping, revolving speed, the steering etc. issued according to flight control circuit board, and then control the heading and flying speed of unmanned plane.
Further, propeller 3 can have multiple, to form multi-rotor unmanned aerial vehicle as shown in Figure 1 to Figure 3.Specifically, this multiple propeller 3 be distributed across in the form of radial fuselage surrounding namely multiple propellers 3 be arranged at intervals on fuselage casing 1 outer edge.For example, the quadrotor drone shown in Fig. 1 to Fig. 3 includes there are four propeller 3, this four propellers 3 are symmetrical arranged about the transversal line and longitudinal axis of unmanned plane.
Optionally; referring to figs. 1 to Fig. 3; the protective cover 4 for protecting propeller 3 can be equipped in the present embodiment, protective cover 4 can be connect by such as snap fit with horn, the sector structure for being specially connected to the one end of horn 2 far from fuselage and extending toward separate ground direction.It is appreciated that protective cover 4 can also be fixedly connected with other components of casing 1 and extend toward far from ground direction, and the structure of protective cover 4 is also not limited to sector structure in some other embodiment.
Horn 2 is used to connect propeller 3 and fuselage.Specifically, horn 2 can be the single hollow rod piece being fabricated to by metal, plastics or carbon fibre material, certainly, in other embodiment, horn 2 is also possible to the either solid rod piece of plate structure.Propeller 3 is fixed on the one end of horn 2 far from fuselage, and the other end of horn 2 is then fixed with the casing 1 for the fuselage that will be described below.Optionally, propeller 3 is detachable or is rotatably mounted on the one end of horn 2 far from fuselage, to facilitate storage and the transport of unmanned plane.Similarly, the other end of horn 2 similarly can be detachable or be rotatably connect with the casing of fuselage 1, to improve the convenience in the storage or transport of unmanned plane.
Specifically, horn 2 can be rectilinear form, or be also possible to polygonal shape.For example, the horn 2 of Fig. 1 to Fig. 3 includes first support arm 21 and second support arm 22, there is angle between the two support arms and form triangular structure between fuselage, to improve the stability of unmanned plane.With continued reference to Fig. 1 and Fig. 2, the first end of first support arm 21 and the first end of second support arm 22 are fixed, and propeller 3 is fixed on the link position of the two；The second end of first support arm 21 and the second end of second support arm 22 are fixed with the casing 1 of fuselage described below respectively.In other words, first support arm 21 and second support arm 22 extend from the link position of the two toward different directions with fixed with the casing 1 of fuselage, to form 2 structure of horn of triangle.Optionally, weight loss groove 23 is offered in first support arm 21 and second support arm 22, to mitigate the weight of unmanned plane, to improve flying height and the cruise duration of unmanned plane.
In addition, being can be seen that from Fig. 1 to Fig. 3 when unmanned plane is multi-rotor unmanned aerial vehicle comprising have multiple horns 2, these 2 scattering devices of horn and radial extend outward in the surrounding of the fuselage of unmanned plane.The number of Power Component is identical as the number of horn 2, and each propeller 3 is installed in the one of one end of horn 2 far from fuselage, for example, can open up mounting hole far from one end of fuselage in horn 2 and motor mount is arranged in mounting hole.The motor of Power Component is fixed in mounting base, and the propeller hub of propeller 3 is fixed on the output shaft of motor.Electricity is adjusted and can be integrated with motor, or electricity is adjusted and be may be mounted in the cavity of horn 2.
Fuselage is the main part of unmanned plane comprising: casing 1 and the heater element 5 being placed in casing 1.Specifically, the heater element 5 being placed in casing 1 can be unmanned plane to realize disposable type, any type of electronic component or integration module in the be installed to casing 1 of the functions such as flight, shooting, location navigation.For example, flight control circuit board, GPS positioning module, Beidou positioning module, gyroscope, wireless receiving module, the image transmission/reception module being electrically connected with the camera on holder etc. can be installed in casing 1.
Since calorific value of the calorific value compared to the unmanned plane that produces or developed before of the electronic component that is mounted or integrated into casing 1 perhaps more and more present unmanned planes of quantity of integration module increases very much.In order to enable unmanned plane to work normally, these heats for being necessarily required to distribute heater element 5 are lost to as early as possible outside casing 1, to drop to the temperature in casing 1 within the temperature range that heater element 5 can work normally.Based on this, present embodiments provide a kind of improved casing 1, it is provided with wind inlet channel 8 on casing 1, it is introduced into casing 1 so that the propeller 3 in the Power Component that will be described below is rotated generated paddle wind, to make these paddle wind and heater element 5 carry out hot transmitting, then the air outlet set by the bottom of casing 1 exports casing 1 to these paddle wind again, to play the purpose for reducing temperature in casing 1.Wherein, air outlet is at least one through-hole 131 of configuration in 1 bottom of casing, this at least one through-hole 131 is matched with the radiator 7 for the heater element 5 that will be described below.
Further, since unmanned plane is generally in higher airflight, the temperature of surrounding air is all relatively low, therefore, after the air of these low temperature is imported into casing 1, the radiating and cooling effect to heater element 5 can also be improved, and not will increase the noise of unmanned plane also.
Casing 1 is generally made into as round, ellipse, rectangle or other geometries.Those skilled in the art should understand that, the wind inlet channel 8 being described below can be set on the casing 1 of arbitrary shape, but it is more succinct in order to describe, below by for the round rectangle casing 1 shown by Fig. 1 into Fig. 3, casing 1 and its wind inlet channel 8 and the air outlet that 1 bottom of casing is arranged in are illustrated.Those skilled in the art should understand that; on the basis of following embodiments; it can be by the way that corresponding wind inlet channel 8 and air outlet be arranged after direct or simple transformation on the casing 1 of other shapes; so as to the radiating and cooling to 1 internal heating element 5 of casing, these are still belonged to the scope of protection of the present invention directly or through the unmanned plane and its casing 1 of simple transformation.
With continued reference to Fig. 1 to Fig. 3, casing 1 includes: upper cover 11, side wall 12 and lower cover 13.Side wall 12 has upper end opening and lower ending opening, and the lid of upper cover 11 closes at upper end opening, and the lid of lower cover 13 closes at lower ending opening, so that upper cover 11, side wall 12 and lower cover 13 enclose one for accommodating the accommodating chamber of above-mentioned heater element 5.
It please see Figure 1, specifically, side wall 12 includes positioned at the front side wall 12a of front end, the rear wall 12b being oppositely arranged with front side wall 12a, the left side wall 12c fixed with the left side of front side wall 12a and rear wall 12b and the right side wall 12d fixed with the right side of front side wall 12a and rear wall 12b.A wind inlet channel 8 is each provided in the front end of left side wall 12c and right side wall 12d, left side wind inlet channel 8 favours left side wall 12c, right side wind inlet channel 8 favours right side wall 12d, and left side wind inlet channel 8 and right side wind inlet channel 8 extend toward the oblique upper far from the casing 1, to make the air inlet of left side wind inlet channel 8 and right side wind inlet channel 8 towards the flow direction of paddle wind caused by propeller 3, so that paddle wind is imported into casing 1.
It is understood that, the paddle wind caused by wind inlet channel 8 needs to rotate on propeller 3 is imported into casing 1, therefore, the air inlet of wind inlet channel 8 should rotate the height for being formed by Plane of rotation lower than propeller 3, this height for also complying with the propeller 3 of unmanned plane is generally both configured to the existing design theory higher than 1 upper cover 11 of casing.Certainly, if the height lower than upper cover 11 that propeller 3 is arranged, only need the position for slightly adjusting wind inlet channel 8 that the purpose imported the paddle wind of propeller 3 in casing 1 can be realized at this time.
For Fig. 3, the air inlet of left side wind inlet channel 8 is lower than the height of upper left side propeller 3 (calling the first propeller in the following text), and specifically, the blade rotation for being less than the first propeller 3 is formed by Plane of rotation；The air inlet of right side wind inlet channel 8 is lower than the height of upper right side propeller 3 (calling the second propeller in the following text), and specifically, the blade rotation for being less than the second propeller 3 is formed by Plane of rotation.
Optionally, wind inlet channel 8 or right side wind inlet channel 8 on the left of can also being only arranged on casing 1.
Again optionally, right side wind inlet channel 8 can be set in the rear end of right side wall 12d, right air path is also positioned close to the position of lower right propeller (calling third propeller in the following text), or left side wind inlet channel 8 is arranged in the rear end of left side wall 12c, left side wind inlet channel 8 is also positioned close to the position of lower left propeller (calling quadruple screw propeller in the following text).
Also optionally, in the case where guaranteeing 1 intensity of casing, any number of wind inlet channel 8 can be set on left side wall 12c, right side wall 12d.
In addition, this multiple wind inlet channel 8 can perhaps transversal line be symmetrical or symmetrical about the longitudinal axis of fuselage and transversal line simultaneously relative to the longitudinal axis of fuselage when being provided with multiple wind inlet channels 8 on the left side wall 12c of casing 1 and right side wall 12d.It is each provided with a wind inlet channel 8 (left side wind inlet channel 8 and right side wind inlet channel 8) in the front end of the left side wall 12c of casing 1 and the front end of right side wall 12d for example, showing in Fig. 3, the two wind inlet channels 8 are symmetrical about the longitudinal axis of fuselage.
After unmanned plane takes off, propeller 3 of the scattering device around fuselage rotates, it flows to blade and rotates air below the Plane of rotation to be formed out of, wind inlet channel 8 enters casing 1 accommodating chamber, one or more air outlet opened up after exchanging heat with heater element 5 from lower cover 13 flows out fuselage, to take the heat that heater element 5 issues out of fuselage, to reduce the temperature in casing 1, guarantee that heater element 5 is capable of the work of normal table.
With continued reference to Fig. 3, the casing 1 of the present embodiment offers right through slot 81 in the bottom of right side wall 12d, the right through slot 81 has the notch towards 13 direction of lower cover, the right edge of lower cover 13 has extended to form right deflector 82 toward upper right side, in other words, the right edge of lower cover 13 has extended to form right deflector 82 toward 3 direction of the second propeller positioned at upper right side.The right deflector 82 and tool right through slot 81 jaggy enclose right side wind inlet channel 8.
It can be understood that, in other embodiment, right through slot 81 can also be not arranged in the bottom of right side wall 12d, but the middle section between the top and bottom of right side wall 12d is set, at this time, right through slot 81 does not have notch, namely, top, bottom end, the front-end and back-end of right through slot 81 are closed, right deflector 82 is then formed on right side wall 12d or lower cover 13, specially extends to form the right deflector 82 from the right edge of the bottom surface of right through slot 81 or lower cover 13 toward upper right side.
In some other embodiment, right through slot 81 can also be arranged on lower cover 13, and also right deflector 82 is arranged on lower cover 13 at this time.For example, can open up right through slot 81 in the right edge of lower cover 13, and the right deflector 82 extended toward upper right side is set on lower cover 13.Alternatively, right through slot 81 can also be arranged in upper cover 11, right deflector 82 be can be set on upper cover 11, side wall 12 or lower cover 13 at this time.For example, the right edge in upper cover 11 opens up right through slot 81, and the deflector 82 extended toward oblique top is set in upper cover 11.
In the present embodiment, the integral piece that right deflector 82 can be integrally formed with upper cover 11, side wall 12 or lower cover 13；Alternatively, the right deflector 82 can be individual component, pass through the fixation of conventional fixed form modes such as (such as) being bonded, be bolted or be clamped and upper cover 11, side wall 12 or lower cover 13.
Further, the shape of right deflector 82 towards the inner surface of right through slot 81 can be arbitrary.For example, the inner surface of right deflector 82 includes the first plane and the second plane to link together.Obtuse angle is formed between first plane and the second plane, to make right side wind inlet channel 8 that there is biggish incoming air area, improves intake volume to improve radiating efficiency.It can be with rounding off, to reduce windage when air flows through wind inlet channel 8, to reduce the influence to unmanned plane during flying efficiency between first plane and the second plane.For another example, the inner surface of right deflector 82 is cambered surface, flows through the windage of wind inlet channel 8 to further decrease air, to improve air intake efficiency and reduce the influence for unmanned plane during flying efficiency.
Optionally, in order to improve the air inlet ability for improving right side wind inlet channel 8, right side wind inlet channel 8 is formed by the orthographic projection on Plane of rotation in the blade of the second propeller 3 and is located in the Plane of rotation.
It should be noted that right through slot 81 along right side wall 12d length direction extend distance can radiating efficiency, the structural strength of casing 1 and the influence for flight efficiency according to actual needs be configured, be not specifically limited herein.
Similarly, in the present embodiment, the structure of left side wind inlet channel 8 is identical as the structure of right side wind inlet channel 8.Certainly; in other embodiments; the structure of left side wind inlet channel 8 and right side wind inlet channel 8 can also have fraction of variation; such as; the left through slot 81 and left deflector 82 of left side wind inlet channel 8 are arranged at the top of left side wall 12c and the middle section of bottom end; the bottom of right side wall 12d is arranged in the right through slot 81 of right side wind inlet channel 8, right deflector 82 is formed in the right edge of lower cover 13, it should be appreciated by those skilled in the art that these simple replacements all belong to the scope of protection of the present invention.
Furthermore, it should be understood that, although the upper cover 11 introduced in above-described embodiment, side wall 12 and lower cover 13 are individual three components, but upper cover 11 and side wall 12 can also be formed into integral piece by being integrally formed to form integral piece or pass through to be integrally formed by lower cover 13 and side wall 12, and make substantive change without the structure to wind inlet channel 8.
Further, in order to improve the heat transfer effect of heater element 5 and air, radiator 7 is additionally provided between heater element 5 and lower cover 13, which is fixed on the bottom of heater element 5 by heat-conducting glue or other modes.
Fig. 4 is the top view of radiator 7 in Fig. 1；Fig. 5 is the left view of radiator 7 in Fig. 1；Fig. 6 is the bottom view of radiator 7 in Fig. 1.As shown in Figures 4 to 6, radiator 7 can be made as metal made of plate structure, be bonded in the lower part of heater element 5 by heat-conducting glue, the heat that heater element 5 generates is transmitted on radiator 7 by heat-conducting glue.
When work, unmanned plane starting, propeller 3 rotates, air is formed by the top of plane toward flowing underneath to form paddle wind from the rotation of the blade of propeller 3, it enters through wind inlet channel 8 in the accommodating chamber of casing 1, is then blown over from the bottom surface of radiator 7, to carry out heat exchange with radiator 7, the air inlet outflow casing 1 finally opened up from lower cover 13 again, to take the heat of heater element 5 outside casing 1 to.
Optionally, the bottom of radiator 7 is formed with one or more heat radiating fin 71, to improve 7 base area of radiator, to improve radiating efficiency.Again optionally, the second bolt hole 72 is additionally provided on radiator 7, so as to by bolt that radiator 7 and casing 1 or heater element 5 (such as flight control circuit board) is fixed, to improve the bonding strength of radiator 7.
Further, electromagnetic field when in order to avoid the work of heater element 5 to other heater elements 5 of unmanned plane (such as the electricity of Power Component adjust or the motor and holder of motor, holder on the camera installed) generate electromagnetic interference, electromagnetic shielding plate 6 is additionally provided between radiator 7 and heater element 5.
Fig. 7 is the top view of lower cover 13 in Fig. 1；Fig. 8 is the left view of lower cover 13 in Fig. 1；Fig. 9 is the bottom view of lower cover 13 in Fig. 1.As shown in Figure 7 to 9, lower cover 13 offers multiple elongate holes as ventilation hole 131 along the length direction of radiator 7, this multiple elongate holes is arranged in parallel, to improve air-out effect, then improves radiating efficiency.Meanwhile this multiple elongate holes can extend along the direction of radiator 7, to cooperate the structure of the heat radiating fin 71 of 7 bottom of radiator, so that heat radiating fin 71 may be exposed by elongate holes, directly contact with cool ambient air, to improve radiating efficiency.
It is understood that, ventilation hole 131 is in addition to for above explained elongate holes and spread pattern, it can also be one of square hole, circular hole, windowing or design in combination, shape, size, density and the spread pattern of ventilation hole 131 can be with designs, radiator 7 can be cooperated to radiate heater element 5, be not specifically limited herein.
Optionally, multiple first bolts hole 132 are offered on lower cover 13, lower cover 13 are fixed on the heater element 5 in accommodating chamber by bolt, such as lower cover 13 is fixed with flight control circuit board again, to improve the stability of flight control circuit board, its shaking is avoided.
Foot prop be used for unmanned plane land when be supported on ground perhaps ground ordered goods to avoid casing 1 and the ground holder that perhaps ground ordered goods are contacted to protect casing 1 or 1 bottom of casing to be installed.Wherein, foot prop can be fixed with the lower cover 13 of casing 1, can also be set to the lower section of horn 2, can also be that the lower section cooperation of the lower cover 13 and horn 2 of casing 1 is equipped with foot prop, the buffer structure which can form for such as soft rubber material.
Finally, it should be noted that embodiment of above is merely illustrative of the technical solution of the present invention, rather than it is limited；Although referring to aforementioned embodiments to inventions have been detailed description, but those skilled in the art should understand that: it can still modify to technical solution documented by aforementioned embodiments, or equivalent substitution of some or all of the technical features；And these are modified or replaceed, the range for embodiment of the present invention technical solution that it does not separate the essence of the corresponding technical solution.
Claims (25)
- A kind of casing of unmanned plane, the casing are built-in with the heater element of the unmanned plane, which is characterized in thatWind inlet channel is provided on the casing, the paddle wind that the wind inlet channel is used to generate when rotating the propeller imports in the casing；The bottom of the casing is equipped with air outlet, and the air outlet is used to carry out the paddle wind after hot transmitting with the heater element and exports the casing；Wherein, the air outlet is arranged to be used at least one through-hole matched with the radiator of the heater element.
- Casing according to claim 1, which is characterized in that the casing includes: the lower cover of upper cover and lid conjunction at the lower ending opening of side wall of side wall, lid conjunction at the upper end opening of side wall；The through-hole opened up on the lower lid includes at least one of strip-shaped hole, square hole, circular hole, windowing.
- Casing according to claim 2, which is characterized in that the strip-shaped hole extends along the length direction of the radiator.
- Casing according to claim 2, which is characterized in that the wind inlet channel includes: the through slot opened up on the side wall, and the deflector being arranged on the side wall or the lower lid；The deflector extends from the through slot toward the oblique upper far from the casing.
- Casing according to claim 2, which is characterized in that the wind inlet channel includes: the through slot opened up on the lower lid, and the deflector being arranged on the lower lid；The deflector extends from the through slot toward the oblique upper far from the casing.
- Casing according to claim 2, which is characterized in that the wind inlet channel includes: the through slot opened up on the cover, and the deflector being arranged on the upper cover, the side wall or the lower lid；The deflector extends from the through slot toward the oblique upper far from the casing.
- The casing according to any one of claim 4 to 6, which is characterized in that the inner surface of the deflector towards the through slot is cambered surface.
- The casing according to any one of claim 2 to 6, which is characterized in that the integral piece that the upper cover and the side wall are integrally formed, alternatively, the integral piece that the lower cover and the side wall are integrally formed.
- Casing according to any one of claim 1 to 6, which is characterized in that the propeller rotation is formed with Plane of rotation, and the wind inlet channel is located in the Plane of rotation in the orthographic projection on the Plane of rotation.
- Casing according to any one of claim 1 to 6, which is characterized in that the wind inlet channel is positioned close to the position of the front end of the casing.
- A kind of unmanned plane, which is characterized in that the horn including casing, the heater element being mounted in the casing, propeller and the connection casing and the propeller；Wind inlet channel is provided on the casing, the paddle wind that the wind inlet channel is used to generate when rotating the propeller imports in the casing；The bottom of the casing is equipped with air outlet, and the air outlet is used to carry out the paddle wind after hot transmitting with the heater element and exports the casing；Wherein, the air outlet is arranged to be used at least one through-hole matched with the radiator of the heater element.
- Unmanned plane according to claim 11, which is characterized in that the casing includes: the lower cover of upper cover and lid conjunction at the lower ending opening of side wall of side wall, lid conjunction at the upper end opening of side wall；The through-hole opened up on the lower lid includes at least one of strip-shaped hole, square hole, circular hole, windowing.
- Unmanned plane according to claim 12, which is characterized in that the strip-shaped hole extends along the length direction of the radiator.
- Unmanned plane according to claim 12, which is characterized in that the wind inlet channel includes: the through slot opened up on the side wall, and the deflector being arranged on the side wall or the lower lid；The deflector extends from the through slot toward the oblique upper far from the casing.
- Unmanned plane according to claim 12, which is characterized in that the wind inlet channel includes: the through slot opened up on the lower lid, and the deflector being arranged on the lower lid；The deflector extends from the through slot toward the oblique upper far from the casing.
- Unmanned plane according to claim 12, which is characterized in that the wind inlet channel includes: the through slot opened up on the cover, and the deflector being arranged on the upper cover, the side wall or the lower lid；The deflector extends from the through slot toward the oblique upper far from the casing.
- Unmanned plane described in any one of 4 to 16 according to claim 1, which is characterized in that the inner surface of the deflector towards the through slot is cambered surface.
- Unmanned plane described in any one of 2 to 16 according to claim 1, which is characterized in that the integral piece that the upper cover and the side wall are integrally formed, alternatively, the integral piece that the lower cover and the side wall are integrally formed.
- Unmanned plane described in any one of 1 to 16 according to claim 1, which is characterized in that the propeller rotation is formed with Plane of rotation, and the wind inlet channel is located in the Plane of rotation in the orthographic projection on the Plane of rotation.
- Unmanned plane described in any one of 1 to 16 according to claim 1, which is characterized in that the wind inlet channel is positioned close to the position of the front end of the casing.
- Unmanned plane according to claim 11, which is characterized in that radiator is additionally provided between the heater element and the bottom of the casing, the radiator is fixed on the bottom of the electronic component.
- Unmanned plane according to claim 21, which is characterized in that the bottom of the radiator is provided with multiple heat radiating fins.
- Unmanned plane according to claim 11, which is characterized in that the horn includes: first support arm and second support arm, and has angle between the first support arm and second support arm；The first end of the first end of the first support arm and the second support arm is connect with the propeller,The second end of the second end of the first support arm and the second support arm is connect with the casing respectively.
- Unmanned plane according to claim 23, which is characterized in that offer weight loss groove in the first support arm and second support arm.
- Unmanned plane according to claim 23, which is characterized in that the wind inlet channel of the casing is between the first support arm and second support arm.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820017883.0U CN207843295U (en) | 2018-01-05 | 2018-01-05 | Unmanned plane and its casing |
| CN2018200178830 | 2018-01-05 | ||
| PCT/CN2018/106253 WO2019134399A1 (en) | 2018-01-05 | 2018-09-18 | Unmanned aerial vehicle and casing thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110352162A true CN110352162A (en) | 2019-10-18 |
Family
ID=63417399
Family Applications (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201820017883.0U Expired - Fee Related CN207843295U (en) | 2018-01-05 | 2018-01-05 | Unmanned plane and its casing |
| CN201880014411.2A Withdrawn CN110352162A (en) | 2018-01-05 | 2018-09-18 | Unmanned plane and its casing |
Family Applications Before (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201820017883.0U Expired - Fee Related CN207843295U (en) | 2018-01-05 | 2018-01-05 | Unmanned plane and its casing |
Country Status (2)
| Country | Link |
|---|---|
| CN (2) | CN207843295U (en) |
| WO (1) | WO2019134399A1 (en) |
Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN207843295U (en) * | 2018-01-05 | 2018-09-11 | 深圳市大疆创新科技有限公司 | Unmanned plane and its casing |
| CN109050952A (en) * | 2018-09-30 | 2018-12-21 | 广州科易光电技术有限公司 | The unmanned machine head of lightweight with external radiator |
| CN109720558A (en) * | 2019-02-19 | 2019-05-07 | 深圳市翔农创新科技有限公司 | The unmanned plane of layout is adjusted based on electricity |
| CN110341940B (en) * | 2019-08-06 | 2023-01-10 | 中咨数据有限公司 | Stably-moving wind-resistant rescue unmanned aerial vehicle |
| WO2023178688A1 (en) * | 2022-03-25 | 2023-09-28 | 深圳市大疆创新科技有限公司 | Unmanned aerial vehicle |
| CN114571931B (en) * | 2022-04-24 | 2022-08-26 | 浙江大学 | Amphibious unmanned aerial vehicle |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2016172947A1 (en) * | 2015-04-30 | 2016-11-03 | 深圳市大疆创新科技有限公司 | Thermal management system and thermal management method, and unmanned aerial vehicle for application of the thermal management system |
| US20170225574A1 (en) * | 2016-02-10 | 2017-08-10 | Qualcomm Incorporated | Structures for charging a multicopter |
| CN106672225A (en) * | 2016-12-27 | 2017-05-17 | 昆山优尼电能运动科技有限公司 | Cooling air path system of unmanned aerial vehicle |
| CN207843295U (en) * | 2018-01-05 | 2018-09-11 | 深圳市大疆创新科技有限公司 | Unmanned plane and its casing |
-
2018
- 2018-01-05 CN CN201820017883.0U patent/CN207843295U/en not_active Expired - Fee Related
- 2018-09-18 WO PCT/CN2018/106253 patent/WO2019134399A1/en active Application Filing
- 2018-09-18 CN CN201880014411.2A patent/CN110352162A/en not_active Withdrawn
Also Published As
| Publication number | Publication date |
|---|---|
| CN207843295U (en) | 2018-09-11 |
| WO2019134399A1 (en) | 2019-07-11 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN110352162A (en) | Unmanned plane and its casing | |
| WO2019140658A1 (en) | Heat dissipation structure, heat dissipation method and device, unmanned aerial vehicle and readable storage medium | |
| US10093418B2 (en) | Unmanned aerial vehicle | |
| CN207978230U (en) | A kind of radiator structure and unmanned plane | |
| WO2019140660A1 (en) | Fuselage and unmanned aerial vehicle comprising same | |
| US8310117B2 (en) | Electric propulsion system useful in jet-type model airplanes and UAVs | |
| JP2017535478A (en) | Unmanned aerial vehicle | |
| CN110382356A (en) | The Power Component and unmanned plane of unmanned plane | |
| CN208868303U (en) | Radiator structure and unmanned vehicle | |
| CN215590991U (en) | Flying body and power device | |
| WO2021129352A1 (en) | Unmanned aerial vehicle base station | |
| JPWO2019225607A1 (en) | Aircraft and frame of air vehicle | |
| CN110313226A (en) | Radiating subassembly, heat radiation module and unmanned vehicle | |
| CN207773456U (en) | Unmanned plane | |
| WO2019119903A1 (en) | Unmanned aerial vehicle | |
| US11220329B2 (en) | Ducted rotor stators | |
| CN207369504U (en) | Radiator structure, camera and mobile platform | |
| CN106081093A (en) | A kind of double oar unmanned plane | |
| CN210882606U (en) | Unmanned plane | |
| CN208597234U (en) | Radiating subassembly, heat radiation module and unmanned vehicle | |
| WO2021056194A1 (en) | Unmanned aerial vehicle | |
| WO2021044388A1 (en) | A drone | |
| CN217864729U (en) | Heat dissipation mechanism that unmanned aerial vehicle horn was used | |
| CN207450213U (en) | The rack construction and aircraft of aircraft | |
| WO2023178688A1 (en) | Unmanned aerial vehicle |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| WW01 | Invention patent application withdrawn after publication |
Application publication date: 20191018 |
|
| WW01 | Invention patent application withdrawn after publication |