CN118665746B - Assembled heat abstractor for unmanned helicopter - Google Patents
Assembled heat abstractor for unmanned helicopter Download PDFInfo
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- CN118665746B CN118665746B CN202411003096.7A CN202411003096A CN118665746B CN 118665746 B CN118665746 B CN 118665746B CN 202411003096 A CN202411003096 A CN 202411003096A CN 118665746 B CN118665746 B CN 118665746B
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- unmanned helicopter
- air inlet
- guide
- guide plates
- inlet cover
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- 238000001816 cooling Methods 0.000 claims description 30
- 238000010438 heat treatment Methods 0.000 claims description 13
- 230000007246 mechanism Effects 0.000 claims description 7
- 238000009423 ventilation Methods 0.000 claims description 7
- 230000000149 penetrating effect Effects 0.000 claims description 5
- 230000005855 radiation Effects 0.000 claims 1
- 230000017525 heat dissipation Effects 0.000 description 59
- 238000000034 method Methods 0.000 description 13
- 230000008569 process Effects 0.000 description 6
- 230000005540 biological transmission Effects 0.000 description 5
- 230000000694 effects Effects 0.000 description 5
- 230000009471 action Effects 0.000 description 4
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 4
- 230000007547 defect Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 238000005265 energy consumption Methods 0.000 description 3
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 description 2
- 230000002411 adverse Effects 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 229910052744 lithium Inorganic materials 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 239000004519 grease Substances 0.000 description 1
- 230000020169 heat generation Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 229920001296 polysiloxane Polymers 0.000 description 1
- 238000007493 shaping process Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U20/00—Constructional aspects of UAVs
- B64U20/90—Cooling
- B64U20/92—Cooling of avionics
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U20/00—Constructional aspects of UAVs
- B64U20/90—Cooling
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U20/00—Constructional aspects of UAVs
- B64U20/90—Cooling
- B64U20/94—Cooling of rotors or rotor motors
-
- 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
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
Abstract
The invention relates to the technical field of unmanned aerial vehicles, in particular to an assembled heat dissipating device for an unmanned helicopter, which comprises an air inlet cover, wherein the air inlet cover is detachably arranged in the unmanned helicopter, the bottom of the air inlet cover extends out to the lower part of the unmanned helicopter, the air inlet cover is of a cuboid hollow non-cover structure, an air inlet is formed in the bottom of the air inlet cover and faces the head of the unmanned helicopter, an air outlet is formed in the bottom of the air inlet cover and faces the tail of the unmanned helicopter, and the air inlet and the air outlet are both positioned below the unmanned helicopter.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicles, in particular to an assembled heat radiator for an unmanned helicopter.
Background
Nowadays, with the continuous development of unmanned helicopter technology in China, unmanned helicopters are widely applied to the fields of agriculture, meteorology, topographic exploration, military science and the like. In the prior art, unmanned helicopters generally include mechanisms such as a nacelle, a fuselage, landing gear, a power unit, a transmission, a power supply system, and a rotor system. The power device generally adopts an electric motor, and the electric motor transmits torsion to the rotor wing system through the transmission device and is used for controlling the rotor wing system to work, so that the flying direction and the flying speed of the unmanned helicopter are controlled. The power supply system generally adopts a rechargeable lithium battery for supplying power to the power device and various electronic components in the machine body.
In the prior art, in the flying process of the unmanned helicopter, heat is generated by the motor, the battery and electronic components in the fuselage, so that the temperature in the fuselage is increased, and the high-temperature environment is one of important factors affecting the operation of electronic products, therefore, the heat dissipation effect of the unmanned helicopter directly affects the quality and safety performance of the products. At present, aiming at the problem of heat dissipation of an unmanned helicopter, the traditional mode mainly reduces the temperature by improving the heat dissipation efficiency of a motor, a lithium battery and electronic components and optimizing the air flow design in the helicopter body. However, these methods often have certain disadvantages, for example, the conventional heat dissipation method mainly depends on increasing the heat dissipation area or using a fan to perform forced cooling, and increasing the heat dissipation area can certainly increase the dead weight of the aircraft, and using a fan can increase the energy consumption of the aircraft and affect the cruising ability of the aircraft.
Besides the traditional heat dissipation mode, in the prior art, a heat dissipation structure for an unmanned helicopter is provided in a patent with publication number CN209427043U, and the technical scheme of the patent comprises a heat dissipation fan, a heat dissipation water tank, a rubber tube, a main propeller shaft, a main propeller wheel and other structures. This technical scheme passes through main oar axle and main oar wheel transmission to be connected, and passes through main oar wheel transmission with main oar axle and radiator fan and be connected for the engine is when carrying out power transmission to unmanned helicopter, can drive radiator fan through self mechanical structure and rotate, helps the radiator tank to dispel the heat fast after absorbing the engine heat through the rubber tube. According to the technical scheme, the cooling fan is driven to rotate through the rotation of the propeller, and an additional power source is not needed to be provided, so that the cooling efficiency of the aircraft can be improved under the condition that the energy consumption of the aircraft is not increased, and the defect of a traditional cooling mode is overcome.
However, the above heat dissipation method only can dissipate heat for a power source or a single component in the aircraft, so that the electronic components and the power supply system in the aircraft cannot obtain a good heat dissipation effect, and in addition, the above method also can increase the rotation resistance of the main propeller shaft, which may have a defect of affecting the flight stability. In order to overcome various defects of the existing unmanned helicopter heat dissipation mode, an assembly type heat dissipation device for an unmanned helicopter is provided.
Disclosure of Invention
The invention aims to provide an assembled heat radiator for an unmanned helicopter, which is used for solving the problems in the background technology.
The invention is realized by the following technical scheme that the assembled heat dissipating device for the unmanned helicopter comprises an air inlet cover, an air inlet cover and an air outlet, wherein the air inlet cover is detachably arranged in the unmanned helicopter, the bottom of the air inlet cover extends out to the lower part of the unmanned helicopter, the air inlet cover is of a cuboid hollow non-cover structure, an air inlet is formed in the bottom of the air inlet cover and faces to the head of the unmanned helicopter, an air outlet is formed in the bottom of the air inlet cover and faces to the tail of the unmanned helicopter, and the air inlet and the air outlet are both positioned below the unmanned helicopter;
The cooling plate is positioned in the air inlet cover and fixedly connected with the air inlet cover, a plurality of cooling fins are formed on the bottom surface of the cooling plate in a protruding mode, the arrangement direction of the cooling fins is consistent with the length direction of the air inlet cover, a square-tube-shaped motor bin is arranged on the top surface of the cooling plate and used for accommodating a motor of an unmanned helicopter, and cooling fins are uniformly arranged on the outer surface of the motor bin;
The battery compartment, battery compartment integrated into one piece set up in the upper surface of heating panel, the afterbody of unmanned helicopter is run through to the open end of battery compartment, the open end detachable of battery compartment is connected with the battery lid, the battery lid with unmanned helicopter's afterbody surface parallel and level.
Optionally, the lower surface of heating panel just is close to one side left and right sides both ends symmetry of air intake and is equipped with first guide plate, the air intake is located between two first guide plates, the lower surface of heating panel just is located still to be equipped with a plurality of second guide plates between two first guide plates, the direction of arranging of second guide plate and first guide plate is unanimous with the length direction of heating panel.
Optionally, two mounting holes are formed in the surface of the heat dissipation plate and located between the two first guide plates in a penetrating mode, a rotating shaft is arranged in the two mounting holes in a rotating mode, a guide disc is arranged at the bottom end of the rotating shaft, a plurality of guide plates are uniformly arranged on the bottom face of the guide disc, the length directions of the guide plates are consistent, and a guide air channel is formed between two adjacent guide plates.
Optionally, the vent has been seted up to the left and right sides symmetry that just is located two water conservancy diversion dishes on the surface of heating panel, the lower surface of heating panel just is located vent position department and is equipped with the kuppe, works as the guide vane with the length direction of heating panel is unanimous, the kuppe is located the side of guide vane, works as the guide vane keeps 45 contained angles with the length direction of heating panel, and the water conservancy diversion wind channel that is located water conservancy diversion dish edge position aims at the kuppe.
Optionally, the top of rotation axis stretches out to the top of heating panel and fixed cover is equipped with driven gear, the top of heating panel still is equipped with the actuating mechanism that is used for controlling two driven gear rotations, actuating mechanism includes electric putter and two-sided rack, electric putter fixed set up in on the heating panel, electric putter's expansion end with two-sided rack fixed connection, two-sided rack stretches into between two driven gear, and two driven gear all with two-sided rack meshing sets up.
Optionally, a temperature sensor and a controller are further arranged in the air inlet cover, a signal output end of the temperature sensor is connected with the controller, and a signal output end of the controller is connected with the electric push rod.
Optionally, a plurality of the second guide plates are all aligned and distributed near one end of the air inlet, a plurality of the other ends of the second guide plates all extend to a position close to the guide plate, and the bottom ends of the second guide plates are attached to the bottom surface of the air inlet cover.
Optionally, the surface of battery cover runs through and has seted up a plurality of exhaust holes, the inside intercommunication of exhaust hole and unmanned helicopter.
Optionally, the mounting hole is in a shape of a step hole with a small upper part and a large lower part, the diameter of the guide disc is identical with the diameter of the bottom of the mounting hole, the guide disc is positioned in the mounting hole, and the bottom surface of the guide disc is flush with the lower surface of the heat dissipation plate.
Optionally, the top surface protrusion shaping of battery compartment has a plurality of conducting strips, the direction of arranging of conducting strip with the length direction of heating panel is unanimous.
Compared with the prior art, the invention provides the assembled heat dissipation device for the unmanned helicopter, which has the following beneficial effects:
1. According to the invention, through a unique air inlet cover design, natural heat dissipation by utilizing air flow in the flight process is realized, the cooling effect of the cooling plate is effectively improved, and secondly, the motor and the battery are arranged above the cooling plate, so that the heat dissipation efficiency of the power source and the power supply system of the aircraft can be fully improved on the premise of not increasing the flight energy consumption of the aircraft.
2. When the guide vane is inclined with the second guide vane, one part of air flow can pass below the heat dissipation plate, and the other part of air flow can enter the machine body, so that the air flow direction can be controlled according to specific conditions, and heat dissipation can be carried out on a power source, a power supply system and electronic components in the machine body.
3. When the guide vane is kept perpendicular to the second guide vane, the guide vane can prevent air flow from passing below the heat dissipation plate, so that the air flow is prevented from dissipating heat and reducing temperature of the internal elements of the unmanned helicopter, the internal temperature of the helicopter body can be maintained when the unmanned helicopter works in cold seasons or high-altitude areas, and adverse effects of low-temperature weather on a power supply system are weakened.
4. The heat radiator is detachably connected to the bottom of the unmanned helicopter, so that the battery is convenient to detach and mount, and in addition, the opening end of the battery compartment penetrates through the tail of the unmanned helicopter, so that the battery can be taken out without detaching the heat radiator, and the maintenance or replacement of the battery is facilitated.
Drawings
FIG. 1 is a schematic view of the unmanned helicopter of the present invention;
FIG. 2 is a schematic diagram of a heat dissipating device according to the present invention;
FIG. 3 is a schematic diagram of a heat dissipating plate according to the present invention;
FIG. 4 shows a heat dissipating plate according to the present invention a back side schematic;
FIG. 5 shows a heat dissipating plate according to the present invention a schematic diagram of another state of the back;
FIG. 6 shows the present invention a top view of the back of the heat dissipation plate;
FIG. 7 shows a heat dissipating plate according to the present invention a back side another state top view;
FIG. 8 is a cross-sectional view of a heat dissipating device according to the present invention;
FIG. 9 is a schematic view of the structure of the air intake cover of the present invention;
FIG. 10 is a schematic view of a rotating shaft structure according to the present invention;
fig. 11 is a schematic view of the battery cover structure of the present invention.
In the figure, 100 parts of unmanned helicopter, 200 parts of air inlet cover, 201 parts of air inlet, 202 parts of air outlet, 300 parts of heat dissipation plate, 301 parts of heat dissipation plate, 302 parts of motor bin, 303 parts of heat dissipation fin, 304 parts of first guide plate, 305 parts of second guide plate, 306 parts of mounting hole, 307 parts of rotating shaft, 308 parts of guide plate, 309 parts of guide plate, 310 parts of guide plate, ventilation opening, 311 parts of guide plate, 312 parts of guide cover, driven gear, 313 parts of electric push rod, 314 parts of double-sided rack, 400 parts of battery bin, 401 parts of battery cover, 402 parts of exhaust hole, 403 parts of heat conduction plate, 500 parts of controller, 501 parts of temperature sensor.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
Referring to fig. 1-11, an assembled heat dissipating device for an unmanned helicopter includes an air intake cover 200, a heat dissipating plate 300 and a battery compartment 400, wherein the air intake cover 200 is detachably mounted inside the unmanned helicopter 100, the bottom of the air intake cover 200 extends out to the lower side of the unmanned helicopter 100, the air intake cover 200 is of a cuboid hollow non-cover structure, an air intake 201 is disposed at the bottom of the air intake cover 200 and facing the head of the unmanned helicopter 100, an air outlet 202 is disposed at the bottom of the air intake cover 200 and facing the tail of the unmanned helicopter 100, and both the air intake 201 and the air outlet 202 are disposed below the unmanned helicopter 100. When the unmanned helicopter 100 is in flight, the air inlet 201 faces forward and the air outlet 202 faces backward, so that air flow can enter the air inlet cover 200 through the air inlet 201 and then be discharged through the air outlet 202.
Further, the heat dissipation plate 300 is located inside the air intake cover 200 and fixedly connected with the air intake cover 200, a plurality of heat dissipation fins 301 are formed on the bottom surface of the heat dissipation plate 300 in a protruding mode, as shown in fig. 4, the arrangement direction of the heat dissipation fins 301 is consistent with the length direction of the air intake cover 200, a square-tube-shaped motor bin 302 is arranged on the top surface of the heat dissipation plate 300, the motor bin 302 is used for accommodating a motor of the unmanned helicopter 100, heat dissipation fins 303 are uniformly arranged on the outer surface of the motor bin 302, the heat dissipation plate 300 is made of aluminum alloy materials and has good heat conductivity, and the motor bin 302 and the heat dissipation plate 300 are of an integrated structure. When the motor is placed inside the motor compartment 302, the side surfaces and the bottom surface of the motor should be coated with heat conductive silicone grease for better heat conduction, so that the heat generated by the motor can be better transferred to the heat dissipation plate 300.
Further, the battery compartment 400 is integrally formed on the upper surface of the heat dissipation plate 300, the open end of the battery compartment 400 penetrates through the tail of the unmanned helicopter 100, and the open end of the battery compartment 400 is detachably connected with the battery cover 401, as shown in fig. 2, the battery cover 401 is flush with the outer surface of the tail of the unmanned helicopter 100. The battery compartment 400 is composed of four surfaces of a left side wall, a right side wall, an upper end surface and a front end surface, the battery compartment 400 and the heat dissipation plate 300 jointly enclose a space for accommodating a battery, and the front end surface of the battery compartment 400 is provided with two conductive electric shocks for corresponding positive and negative poles of the battery.
In addition, the tail of the unmanned helicopter 100 has a through hole, not shown in the drawing, into which the open end of the battery compartment 400 is inserted, and when the battery cover 401 is covered on the open end of the battery compartment 400, the battery cover 401 is also embedded in the through hole, and the outer surface of the battery cover 401 is flush with the outer surface of the tail of the unmanned helicopter 100, and meanwhile, the battery cover 401 and the battery compartment 400 are fixedly connected by a clamping connection or a bolt.
It should be noted that, during the flight of the unmanned helicopter 100, the heat generated by the motor and the battery is transferred to the heat dissipation plate 300, and the air flow enters from the air inlet 201 and is discharged from the air outlet 202, so that the air flow can take away the heat on the heat dissipation plate 300, thereby slowing down the heat generating efficiency of the motor and the battery.
On the other hand, the lower surface of the heat dissipation plate 300 and the left and right ends of one side close to the air inlet 201 are symmetrically provided with first guide plates 304, as shown in fig. 4, the air inlet 201 is located between two first guide plates 304, the lower surface of the heat dissipation plate 300 and located between two first guide plates 304 are also provided with a plurality of second guide plates 305, and the arrangement directions of the second guide plates 305 and the first guide plates 304 are consistent with the length direction of the heat dissipation plate 300. In addition, the bottom ends of the first guide plate 304 and the second guide plate 305 are both attached to the inner bottom surface of the air inlet cover 200, and one end of the first guide plate 304 is attached to the front end surface of the air inlet cover 200, so that the air flow is prevented from leaking from below the guide plates, and the air flow is ensured to completely pass through the gap between the first guide plate 304 and the second guide plate 305.
Further, two mounting holes 306 are formed in the surface of the heat dissipation plate 300 and located between the two first guide plates 304 in a penetrating manner, as shown in fig. 5, a rotating shaft 307 is rotatably disposed in the two mounting holes 306, a guide plate 308 is disposed at the bottom end of the rotating shaft 307, a plurality of guide plates 309 are uniformly disposed on the bottom surface of the guide plate 308, the length directions of the guide plates 309 are consistent, a guide air channel is formed between two adjacent guide plates 309, and the bottom surface of the guide plate 308 is flush with the lower surface of the heat dissipation plate 300. Specifically, the mounting hole 306 is in a stepped hole shape with a small top and a large bottom, the rotating shaft 307 is rotatably connected in the mounting hole 306 through a bearing, and the diameter of the guide disc 308 is identical to that of the lower end of the mounting hole 306, and in addition, as shown in fig. 6, the distance between the far ends of the two guide discs 308 is identical to that between the two first guide plates 304.
In addition, it should be noted that the ends of the second deflectors 305 near the air inlet 201 are aligned, the other ends of the second deflectors 305 extend to a position near the air guide plate 308, and the distance between the second deflectors 305 and the air guide plate 308 is not more than 1 cm, so that the lengths of the second deflectors 305 are different, and when the lengths of the deflectors 309 are consistent with the length direction of the second deflectors 305, the air flow flowing through the second deflectors 305 can completely enter the air guide duct. In addition, the guide vane 309 and the inner bottom surface of the air intake cover 200 have only a slight gap, so that the air flow is prevented from passing under the guide vane 309.
Further, the surface of the heat dissipation plate 300 and the left and right sides of the two flow guide plates 308 are symmetrically provided with ventilation openings 310, the lower surface of the heat dissipation plate 300 and the position of the ventilation openings 310 are provided with flow guide covers 311, as shown in fig. 5, when the length direction of the flow guide plates 309 is consistent with that of the heat dissipation plate 300, the flow guide covers 311 are positioned on the side surfaces of the flow guide plates 309, and when the length direction of the flow guide plates 309 and the length direction of the heat dissipation plate 300 keep 45 degrees included angle, the flow guide air channels positioned at the edge parts of the flow guide plates 308 can be aligned with the flow guide covers 311, as shown in fig. 6. Specifically, the number of ventilation openings 310 is two, the height of the air guide sleeve 311 is equal to that of the air guide sleeve 309, and one surface of the air guide sleeve 311, which faces the air guide sleeve 308, is in an inclined surface shape, when part of the air guide channels are aligned to the air guide sleeve 311, air flow can pass through the ventilation openings 310 and enter the upper part of the heat dissipation plate 300 through the action of the air guide sleeve 311, so that heat in the unmanned helicopter 100 can be taken away.
In addition, the top of the rotation shaft 307 extends to the upper side of the heat dissipation plate 300 and is fixedly sleeved with a driven gear 312, a driving mechanism for controlling the rotation of the two driven gears 312 is further arranged above the heat dissipation plate 300, the driving mechanism comprises an electric push rod 313 and a double-sided rack 314, the electric push rod 313 is fixedly arranged on the heat dissipation plate 300, the movable end of the electric push rod 313 is fixedly connected with the double-sided rack 314, the double-sided rack 314 extends into the space between the two driven gears 312, and the two driven gears 312 are meshed with the double-sided rack 314. Therefore, the electric push rod 313 can directly control the front-back sliding of the double-sided rack 314, so as to indirectly control the relative rotation of the two guide plates 308, and adjust the direction of the guide plates 309.
Specifically, the air intake cover 200 is further provided with a temperature sensor 501 and a controller 500, a signal output end of the temperature sensor 501 is connected with the controller 500, and a signal output end of the controller 500 is connected with the electric push rod 313. The surface of the battery cover 401 is provided with a plurality of exhaust holes 402 in a penetrating manner, as shown in fig. 8, the exhaust holes 402 are communicated with the inside of the unmanned helicopter 100, the exhaust holes 402 are used for exhausting air in the unmanned helicopter 100, the upper surface of the battery compartment 400 is also provided with a plurality of heat conducting fins 403 in a protruding manner, and the arrangement direction of the heat conducting fins 403 is consistent with the length direction of the heat dissipation plate 300.
When the temperature of the air inside the unmanned helicopter 100 is higher than the high temperature threshold set by the temperature sensor 501, the temperature sensor 501 transmits a signal to the controller 500, and the controller 500 controls the electric push rod 313 to act, so that the air deflector 309 and the length direction of the second air deflector 305 keep an included angle of 45 ° and a part of the air enters the upper part of the heat dissipation plate 300, thereby helping to take away the heat of the internal elements of the unmanned helicopter 100.
It should be noted that, when the temperature sensor 501 is further set with a low temperature threshold, and the temperature of the air inside the unmanned helicopter 100 is lower than the set low temperature threshold, the controller 500 will control the electric push rod 313 to act, so that the air deflector 309 is kept perpendicular to the second air deflector 305, as shown in fig. 7, and at this time, the air deflector 309 will obstruct the outside air from entering below the heat dissipating plate 300.
In summary, in the practical application process of the embodiment, in the initial state, the length direction of the guide vane 309 is consistent with the length direction of the second guide vane 305, and at this time, the guide vane 309 does not affect the airflow flowing under the heat dissipation plate 300, and the air enters from the air inlet 201 and is exhausted from the air outlet 202, so as to cool the heat dissipation plate 300, thereby slowing down the heat generation efficiency of the motor and the battery. When the unmanned helicopter 100 continuously increases in flight time, the electronic components in the unmanned helicopter 100 also generate heat and continuously increase the heat in the unmanned helicopter 100, when the temperature exceeds the threshold value of the temperature sensor 501, the controller 500 controls the electric push rod 313 to act, so that the air deflector 309 rotates 45 degrees, at this time, a part of the air flow entering the inside of the air inlet cover 200 continues to flow below the heat dissipation plate 300, and another part of the air flow enters the above of the heat dissipation plate 300 through the air vent 310 and is discharged from the air vent 402, so as to take away the heat in the unmanned helicopter 100.
In addition, when the unmanned helicopter 100 flies in a cold season or when the unmanned helicopter 100 flies to a higher altitude area, the low temperature tends to affect the battery-powered stability and the battery endurance due to the low ambient temperature, so in this case, when the temperature is lower than the low temperature threshold of the temperature sensor 501, the controller 500 may control the diaphragm 308 to rotate 90 °, as shown in fig. 7, and the diaphragm 309 may obstruct the external air from entering the lower side of the heat dissipation plate 300, so that adverse effects of the low temperature environment on the battery-powered system can be avoided.
It is noted that relational terms such as first and second, and the like are used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Moreover, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising one does not exclude the presence of other like elements in a process, method, article, or apparatus that comprises an element.
Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made therein without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (5)
1. An assembled heat sink for an unmanned helicopter, comprising:
The air inlet cover (200), the inside in unmanned helicopter (100) is detachably installed to air inlet cover (200), and the bottom of air inlet cover (200) stretches out to the below of unmanned helicopter (100), air inlet cover (200) are cuboid cavity no lid structure, the bottom of air inlet cover (200) and the one side towards unmanned helicopter (100) head are equipped with air intake (201), the bottom of air inlet cover (200) and the one side towards unmanned helicopter (100) afterbody are equipped with air outlet (202), air intake (201) and air outlet (202) are all located the below of unmanned helicopter (100);
The cooling device comprises a cooling plate (300), wherein the cooling plate (300) is positioned in an air inlet cover (200) and is fixedly connected with the air inlet cover (200), a plurality of cooling fins (301) are formed on the bottom surface of the cooling plate (300) in a protruding mode, the arrangement direction of the cooling fins (301) is consistent with the length direction of the air inlet cover (200), a square-tube-shaped motor bin (302) is arranged on the top surface of the cooling plate (300), the motor bin (302) is used for accommodating a motor of an unmanned helicopter (100), and cooling fins (303) are uniformly arranged on the outer surface of the motor bin (302);
The battery compartment (400), battery compartment (400) integrated into one piece set up in the upper surface of heating panel (300), the afterbody of unmanned helicopter (100) is run through to the open end of battery compartment (400), the open end of battery compartment (400) is detachably connected with battery lid (401), battery lid (401) with unmanned helicopter (100) afterbody surface parallel and level;
The cooling plate comprises a cooling plate body and is characterized in that first guide plates (304) are symmetrically arranged at the left end and the right end of the lower surface of the cooling plate body, which are close to one side of an air inlet (201), the air inlet (201) is positioned between the two first guide plates (304), a plurality of second guide plates (305) are further arranged on the lower surface of the cooling plate body and between the two first guide plates (304), and the arrangement directions of the second guide plates (305) and the first guide plates (304) are consistent with the length direction of the cooling plate body (300);
Two mounting holes (306) are formed in the surface of the heat radiation plate (300) and located between the two first guide plates (304) in a penetrating manner, a rotating shaft (307) is arranged in the two mounting holes (306) in a rotating manner, a guide disc (308) is arranged at the bottom end of the rotating shaft (307), a plurality of guide sheets (309) are uniformly arranged on the bottom surface of the guide disc (308), the length directions of the guide sheets (309) are consistent, and a guide air channel is formed between two adjacent guide sheets (309);
The surface of the cooling plate (300) and the left and right sides of the two guide plates (308) are symmetrically provided with ventilation openings (310), the lower surface of the cooling plate (300) and the position of the ventilation openings (310) are provided with guide covers (311), when the guide plates (309) are consistent with the length direction of the cooling plate (300), the guide covers (311) are positioned on the side surfaces of the guide plates (309), and when the guide plates (309) keep an included angle of 45 degrees with the length direction of the cooling plate (300), the guide air channels positioned at the edge parts of the guide plates (308) are aligned with the guide covers (311);
The top of the rotating shaft (307) extends to the upper side of the radiating plate (300) and is fixedly sleeved with a driven gear (312), a driving mechanism for controlling the rotation of the two driven gears (312) is further arranged above the radiating plate (300), the driving mechanism comprises an electric push rod (313) and a double-sided rack (314), the electric push rod (313) is fixedly arranged on the radiating plate (300), the movable end of the electric push rod (313) is fixedly connected with the double-sided rack (314), the double-sided rack (314) extends into the space between the two driven gears (312), and the two driven gears (312) are meshed with the double-sided rack (314);
The inside of air inlet cover (200) still is equipped with temperature sensor (501) and controller (500), the signal output part of temperature sensor (501) with controller (500) are connected, the signal output part of controller (500) with electric putter (313) are connected.
2. The assembly type heat dissipating device for the unmanned helicopter of claim 1, wherein one ends of the second deflectors (305) close to the air inlet (201) are aligned, the other ends of the second deflectors (305) extend to a position close to the deflector (308), and the bottom ends of the second deflectors (305) are attached to the bottom surface of the air inlet cover (200).
3. The assembled heat dissipating device for the unmanned helicopter of claim 1, wherein the surface of the battery cover (401) is provided with a plurality of vent holes (402) in a penetrating manner, and the vent holes (402) are communicated with the inside of the unmanned helicopter (100).
4. The assembled heat dissipating device for the unmanned helicopter of claim 1, wherein the mounting hole (306) is in a stepped hole shape with a smaller upper part and a larger lower part, the diameter of the deflector plate (308) is matched with the bottom diameter of the mounting hole (306), the deflector plate (308) is positioned in the mounting hole (306), and the bottom surface of the deflector plate (308) is flush with the lower surface of the heat dissipating plate (300).
5. The assembled heat dissipating device for the unmanned helicopter according to claim 1, wherein the top surface of the battery compartment (400) is formed with a plurality of heat conducting fins (403) in a protruding manner, and the arrangement direction of the heat conducting fins (403) is consistent with the length direction of the heat dissipating plate (300).
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| CN105253311B (en) * | 2015-09-28 | 2017-08-08 | 易瓦特科技股份公司 | Depopulated helicopter |
| CN205022880U (en) * | 2015-09-28 | 2016-02-10 | 湖北易瓦特科技股份有限公司 | Unmanned helicopter of formula is directly gone into to air current |
| CN108882614B (en) * | 2017-05-09 | 2023-11-17 | 昆山合朗航空科技有限公司 | Unmanned vehicles wind path cooling system |
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