CN112455697A - Novel temperature control system of oil-electricity hybrid power water unmanned aerial vehicle - Google Patents
Novel temperature control system of oil-electricity hybrid power water unmanned aerial vehicle Download PDFInfo
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- CN112455697A CN112455697A CN202011442533.7A CN202011442533A CN112455697A CN 112455697 A CN112455697 A CN 112455697A CN 202011442533 A CN202011442533 A CN 202011442533A CN 112455697 A CN112455697 A CN 112455697A
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- sealed cabin
- temperature control
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- aerial vehicle
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- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 title claims abstract description 18
- 238000010438 heat treatment Methods 0.000 claims abstract description 20
- 230000035939 shock Effects 0.000 claims description 6
- 238000010586 diagram Methods 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 238000010521 absorption reaction Methods 0.000 description 2
- 230000003139 buffering effect Effects 0.000 description 2
- 239000002775 capsule Substances 0.000 description 2
- 239000007769 metal material Substances 0.000 description 2
- 238000007789 sealing Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 1
- 229920001971 elastomer Polymers 0.000 description 1
- 229920001821 foam rubber Polymers 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 229910052755 nonmetal Inorganic materials 0.000 description 1
- 239000003973 paint Substances 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
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/026—Aircraft characterised by the type or position of power plants comprising different types of power plants, e.g. combination of a piston engine and a gas-turbine
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/08—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
- B64D33/10—Radiator arrangement
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Forklifts And Lifting Vehicles (AREA)
- Electric Propulsion And Braking For Vehicles (AREA)
Abstract
The invention discloses a novel temperature control system of a hybrid power water unmanned aerial vehicle, which comprises a body assembly, a temperature control assembly and a power assembly, wherein a bottom cover of the body assembly is arranged on one side of a shell, a plurality of wings are arranged on the periphery of the shell, propellers and motors are arranged on the wings, an undercarriage is arranged on one side of the shell, a sealed cabin of the temperature control assembly is arranged in the shell, a cabin door is in sliding connection with the sealed cabin, a heating resistor, a circuit board and a temperature sensor are positioned in the sealed cabin, and the power assembly is arranged in the sealed cabin. Set up the sealed cabin through the outside at power component to set up temperature sensor in the sealed cabin and detect the temperature, thereby can open heating resistor and heat when the temperature is low, open the hatch door when the temperature is high and ventilate with the external world, thereby keep the part work under good temperature environment in the sealed cabin, make unmanned aerial vehicle can normally work under abominable temperature environment.
Description
Technical Field
The invention relates to the field of unmanned aerial vehicles, in particular to a novel temperature control system of a hybrid power water unmanned aerial vehicle.
Background
An unmanned aircraft, referred to as "drone", is an unmanned aircraft that is operated by a radio remote control device and a self-contained program control device, or is operated autonomously, either completely or intermittently, by an onboard computer.
When current unmanned aerial vehicle worked under cold environment, can cross because the temperature is low and make power supply system can not normally work to easily break down, reduce stability in use.
Disclosure of Invention
The invention aims to provide a novel temperature control system of a hybrid power water unmanned aerial vehicle, and aims to solve the problem that the existing unmanned aerial vehicle cannot normally work in a cold environment and is prone to failure.
In order to achieve the above purpose, the invention provides a novel temperature control system of a hybrid power water unmanned aerial vehicle, which comprises a fuselage assembly, a temperature control assembly and a power assembly, wherein the fuselage assembly comprises a shell, a bottom cover, wings, propellers, motors and an undercarriage, the bottom cover is fixedly connected with the shell and is positioned on one side of the shell, a plurality of wings are arranged, a plurality of wings are communicated with the shell and are positioned on the periphery of the shell, a plurality of motors are arranged, the motors are respectively fixedly connected with the wings and are positioned on one side of the wings, a plurality of propellers are arranged, the propellers are respectively fixedly connected with rotating shafts of the motors and are positioned on one side of the motors, the undercarriage is fixedly connected with the shell and is positioned on one side of the shell close to the bottom cover, the temperature control assembly comprises a sealed cabin, a cabin door, a heating resistor, a circuit board and a temperature sensor, the sealed cabin is provided with a plurality of through holes, the sealed cabin is fixedly connected with the shell and is positioned in the shell, the cabin door is slidably connected with the sealed cabin and is positioned on two sides of the sealed cabin, the heating resistor is fixedly connected with the sealed cabin and is positioned in the sealed cabin, the temperature sensor is fixedly connected with the sealed cabin and is positioned on one side of the sealed cabin, the circuit board is fixedly connected with the heating resistor and the temperature sensor and is positioned in the sealed cabin, the power assembly comprises an engine unit, a battery pack and a charging interface, the engine unit, the battery pack are fixedly connected with the sealed cabin and are positioned in the sealed cabin, and the charging interface is electrically connected with the circuit board, and through the housing.
The machine body assembly further comprises an O-shaped ring, the O-shaped ring is fixedly connected with the shell and is positioned between the shell and the bottom cover.
The fuselage assembly further comprises a filling layer, and the filling layer is fixedly connected with the wings and is positioned in the wings.
The aircraft body assembly further comprises an air cushion, and the air cushion is fixedly connected with the undercarriage and is located on one side of the undercarriage.
The power assembly further comprises an interface cover, and the interface cover is rotatably connected with the shell and is located in the charging interface.
The temperature control assembly further comprises an air cylinder and a connecting plate, the connecting plate is fixedly connected with the two cabin doors and is positioned on one side of the cabin doors, and a sliding rod of the air cylinder is fixedly connected with the connecting plate and is positioned on one side of the connecting plate.
The temperature control assembly further comprises a fan, and the fan is fixedly connected with the sealed cabin and is positioned in the sealed cabin.
The temperature control assembly further comprises a shock pad, the shock pad is fixedly connected with the sealed cabin and is positioned on one side, close to the bottom cover, of the sealed cabin.
According to the novel temperature control system of the oil-electricity hybrid power water unmanned aerial vehicle, the bottom cover is fixedly connected with the shell, the plurality of wings are communicated with the shell, the plurality of motors are respectively and fixedly connected with the plurality of wings, the plurality of propellers are respectively and fixedly connected with rotating shafts of the plurality of motors, the motors on the wings are waterproof motors and are connected with the inside of the shell through wires, the motors can be driven to drive the propellers to rotate, and the undercarriage is fixedly connected with the shell and used for supporting a main body of the unmanned aerial vehicle when the undercarriage rises and falls; the sealed cabin with casing fixed connection, the hatch door with sealed cabin sliding connection slides the hatch door can be right the through-hole carries out the switching to can communicate or interrupt with the exterior space, heating resistor with sealed cabin fixed connection can be right the sealed cabin heats, temperature sensor with sealed cabin fixed connection is used for right the temperature in the sealed cabin detects, the circuit board mainly comprises the singlechip for transmit data and electric power, engine block can produce the electric energy with the heat energy of petrol and charge, the group battery can be right the motor supplies power, the interface that charges allows the external power supply to the group battery charges. Through the outside of power component sets up the sealed cabin to set up temperature sensor in the sealed cabin and detect the temperature, thereby can open when the temperature is low heating resistor heats, opens when the temperature is high the hatch door ventilates with the external world, thereby keeps parts in the sealed cabin work under good temperature environment, thereby can normally work under abominable temperature environment, thereby solve current unmanned aerial vehicle and can not normally work and the problem that easily breaks down under cold environment.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.
Fig. 1 is a top side disassembled structure diagram of a temperature control system of a novel hybrid electric-oil hybrid power waterborne unmanned aerial vehicle of the invention;
FIG. 2 is a bottom side disassembled structure diagram of the temperature control system of the novel hybrid electric-oil hybrid power waterborne unmanned aerial vehicle of the invention;
FIG. 3 is a schematic cross-sectional view of a temperature control system of a novel hybrid electric-oil hybrid water unmanned aerial vehicle along a wing according to the invention;
FIG. 4 is a partial block diagram of the temperature control assembly of the present invention;
fig. 5 is a schematic cross-sectional view of fig. 4.
1-fuselage component, 2-temperature control component, 3-power component, 11-shell, 12-bottom cover, 13-wing, 14-propeller, 15-motor, 16-landing gear, 17-O-ring, 18-filling layer, 19-air cushion, 20-baffle, 21-sealed cabin, 22-cabin door, 23-heating resistor, 24-circuit board, 25-temperature sensor, 26-cylinder, 27-connecting board, 28-fan, 29-shock pad, 31-engine unit, 32-battery pack, 33-charging interface, 34-interface cover, 35-loading cabin, 36-heat conducting board, 211-through hole.
Detailed Description
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention.
In the description of the present invention, it is to be understood that the terms "length", "width", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on the orientations or positional relationships illustrated in the drawings, and are used merely for convenience in describing the present invention and for simplicity in description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed in a particular orientation, and be operated, and thus, are not to be construed as limiting the present invention. Further, in the description of the present invention, "a plurality" means two or more unless specifically defined otherwise.
Referring to fig. 1 to 5, the present invention provides a temperature control system for a novel hybrid power water unmanned aerial vehicle:
including fuselage subassembly 1, temperature control assembly 2 and power component 3, fuselage subassembly 1 includes casing 11, bottom 12, wing 13, screw 14, motor 15 and undercarriage 16, bottom 12 with casing 11 fixed connection, and lie in one side of casing 11, the quantity of wing 13 has a plurality ofly, and is a plurality of wing 13 with casing 11 intercommunication, and lie in around casing 11, the quantity of motor 15 has a plurality ofly, and is a plurality of motor 15 respectively with a plurality of wing 13 fixed connection, and lie in one side of wing 13, the quantity of screw 14 has a plurality ofly, and is a plurality of screw 14 respectively with a plurality of the pivot fixed connection of motor 15, and lie in one side of motor 15, undercarriage 16 with casing 11 fixed connection, and lie in casing 11 is close to one side of bottom 12, the temperature control assembly 2 comprises a sealed cabin 21, a cabin door 22, a heating resistor 23, a circuit board 24 and a temperature sensor 25, the sealed cabin 21 is provided with a plurality of through holes 211, the sealed cabin 21 is fixedly connected with the shell 11 and is positioned in the shell 11, the cabin door 22 is slidably connected with the sealed cabin 21 and is positioned at two sides of the sealed cabin 21, the heating resistor 23 is fixedly connected with the sealed cabin 21 and is positioned in the sealed cabin 21, the temperature sensor 25 is fixedly connected with the sealed cabin 21 and is positioned at one side of the sealed cabin 21, the circuit board 24 is fixedly connected with the heating resistor 23 and the temperature sensor 25 and is positioned in the sealed cabin 21, the power assembly 3 comprises an engine unit 31, a battery pack 32 and a charging interface 33, the engine unit 31 and the battery pack 32 are fixedly connected with the sealed cabin 21, and is located in the sealed cabin 21, and the charging interface 33 is electrically connected with the circuit board 24 and penetrates through the shell 11.
In this embodiment, the bottom cover 12 is fixedly connected to the housing 11 and located at one side of the housing 11, a closed cavity is formed by the bottom cover 12 and the housing 11, the number of the wings 13 is plural, the wings 13 are communicated with the housing 11 and located at the periphery of the housing 11, the number of the motors 15 is plural, the motors 15 are respectively fixedly connected to the wings 13 and located at one side of the wings 13, the number of the propellers 14 is plural, the propellers 14 are respectively fixedly connected to the rotating shafts of the motors 15 and located at one side of the motors 15, the motors 15 on the wings 13 are waterproof motors 15, and are connected to the housing 11 through wires, so that the motors 15 can be driven to drive the propellers 14 to rotate, and the landing gear 16 is fixedly connected to the housing 11, the unmanned aerial vehicle is used for supporting the unmanned aerial vehicle main body during rising and falling and has a buffering effect; the temperature control assembly 2 comprises a sealed cabin 21, a cabin door 22, a heating resistor 23, a circuit board 24 and a temperature sensor 25, the sealed cabin 21 has a plurality of through holes 211, the sealed cabin 21 is fixedly connected with the shell 11 and is positioned in the shell 11, the sealed cabin 21 is made of high-strength material, an insulating layer is arranged outside the sealed cabin, the cabin door 22 is slidably connected with the sealed cabin 21 and is positioned at two sides of the sealed cabin 21, the through holes 211 can be opened and closed by sliding the cabin door 22 so as to be communicated with or interrupted by an external space, the heating resistor 23 is fixedly connected with the sealed cabin 21 and is positioned in the sealed cabin 21 and can heat the sealed cabin 21, the temperature sensor 25 is fixedly connected with the sealed cabin 21 and is positioned at one side of the sealed cabin 21, the type of the temperature sensor 25 can be TP-100, the electric power component comprises a power component 3, an engine unit 31, a battery pack 32 and a charging interface 33, wherein the power component 3 comprises the engine unit 31, the battery pack 32 and the sealed cabin 21, the engine unit 31 and the battery pack 32 are fixedly connected and are located in the sealed cabin 21, the charging interface 33 is electrically connected with the circuit board 24 and penetrates through the shell, the engine unit 31 can generate electric energy from the heat energy of gasoline to charge, the battery pack 32 can supply power to the motor 15, and the charging interface 33 allows an external power source to charge the battery pack 32. Through the outside of power component 3 sets up sealed cabin 21 to set up temperature sensor 25 in sealed cabin 21 and detect the temperature, thereby can open when the temperature is low heating resistor 23 heats, opens when the temperature is high hatch door 22 ventilates with the external world, thereby keeps parts in the sealed cabin 21 work under good temperature environment, thereby can normally work under abominable temperature environment, thereby solve current unmanned aerial vehicle can not normally work and the problem of easily breaking down under cold environment.
Further, the body assembly 1 further includes an O-ring 17, wherein the O-ring 17 is fixedly connected to the housing 11 and is located between the housing 11 and the bottom cover 12.
In this embodiment, the O-ring 17 is disposed between the housing and the bottom cover 12, and can seal a gap between the housing and the bottom cover 12 to improve the waterproof performance of the unmanned aerial vehicle.
Further, the fuselage assembly 1 further comprises a filling layer 18, and the filling layer 18 is fixedly connected with the wing 13 and is located in the wing 13.
In this embodiment, the filling layer 18 may be foam rubber, and is placed inside the wing 13, so that rain and snow cannot enter the housing 11 through the wing 13, and the waterproof performance of the unmanned aerial vehicle is further improved.
Further, the fuselage assembly 1 further comprises an air cushion 19, and the air cushion 19 is fixedly connected with the landing gear 16 and is positioned on one side of the landing gear 16.
In this embodiment, air cushion 19 can provide certain buoyancy, can allow unmanned aerial vehicle to take off and land on water, can also play the effect of buffering when landing on land in addition, protects unmanned aerial vehicle safety to descend.
Further, the power assembly 3 further includes an interface cover 34, and the interface cover 34 is rotatably connected with the housing 11 and is located in the charging interface 33.
In the present embodiment, the interface cover 34 is disposed on one side of the charging interface 33, so that when the charging interface 33 is not used, the interface cover 34 can be pushed into the charging interface 33 to protect the charging interface 33 and prevent entry of foreign matter.
Further, the temperature control assembly 2 further comprises an air cylinder 26 and a connecting plate 27, the connecting plate 27 is fixedly connected with the two doors 22 and is located at one side of the doors 22, and a sliding rod of the air cylinder 26 is fixedly connected with the connecting plate 27 and is located at one side of the connecting plate 27.
In this embodiment, the air cylinder 26 can be connected with the circuit board 24 through a controller, so that the position of the connecting plate 27 can be automatically adjusted according to the temperature, so that the sealing degree of the sealed cabin 21 can be automatically adjusted, when the temperature in the sealed cabin 21 is too high, the cabin door 22 is opened to carry out heat convection with the outside air so as to reduce the temperature, when the temperature is too low, the cabin door 22 is closed, and the heating resistor 23 is started to heat and keep warm, so that the normal operation of the unmanned aerial vehicle can be maintained.
Further, the temperature control assembly 2 further comprises a fan 28, and the fan 28 is fixedly connected with the sealed cabin 21 and is located in the sealed cabin 21.
In this embodiment, the air inside the sealed cabin 21 can be rapidly agitated by turning on the fan 28, so that the heat generated by the heating resistor 23 can be rapidly dissipated, thereby ensuring the normal operation of the equipment.
Further, the body assembly 1 further comprises a baffle 20, wherein the baffle 20 is rotatably connected with the housing 11 and is located on one side of the housing 11 close to the charging interface 33.
In the present embodiment, the baffle 20 is disposed outside the charging interface 33, so as to block rain and snow encountered during the flight, further protect the charging interface 33, and avoid short circuit.
Further, the temperature control assembly 2 further comprises a shock absorption pad 29, and the shock absorption pad 29 is fixedly connected with the sealed cabin 21 and is located on one side of the sealed cabin 21 close to the bottom cover 12.
In the present embodiment, the shock-absorbing pad 29 is disposed between the bottom cover 12 and the capsule 21 so that the impact can be gentle at the time of landing, thereby increasing the stability of the components inside the capsule 21.
Further, the machine body assembly 1 further comprises a loading bin 35 and a heat conducting plate 36, the loading bin 35 is fixedly connected with the shell 11 and is located on one side of the shell 11 far away from the bottom cover 12, and the heat conducting plate 36 is fixedly connected with the sealed cabin 21, penetrates through the shell 11 and is located in the loading bin 35.
In this embodiment, the loading chamber 35 can be used to place other accessories such as a camera, a sensor, etc. to expand the capability of the drone, and the heat conducting plate 36 is made of a high conductivity material, so that the heat in the sealed cabin 21 can be conducted into the loading chamber 35 to keep the temperature stable.
The working principle and the using process of the invention are as follows: referring to fig. 1 and 2, after the unmanned aerial vehicle is installed, the circuit board 24 can drive the motor 15 to rotate so that the unmanned aerial vehicle flies, the temperature sensor 25 monitors the temperature in the sealed cabin 21 in real time, and when the temperature is high, the cylinder 26 is controlled to open the cabin door 22, and heat convection is performed between the through hole 211 and the external environment so as to reduce the temperature; when the temperature is low, close hatch door 22, and start heating resistor 23 heats, fan 28 can promote the radiating efficiency, then through O type ring 17 with filling layer 18 etc. can improve unmanned aerial vehicle's leakproofness for unmanned aerial vehicle is more stable in sleet weather operation, will in addition casing 11 with the screw head that bottom 12 connects can adopt sealing washer and gasket cooperation sealed, and wherein the gasket can be metal material, also can be non-metal material such as plastics, rubber, casing 11 inside and outside can also be brushed waterproof material with further improvement waterproof performance with paint.
While the invention has been described with reference to a preferred embodiment, it will be understood by those skilled in the art that various changes in form and detail may be made therein without departing from the spirit and scope of the invention as defined by the appended claims.
Claims (8)
1. A novel temperature control system of a hybrid power water unmanned aerial vehicle is characterized in that,
including fuselage subassembly, temperature control subassembly and power component, the fuselage subassembly includes casing, bottom, wing, screw, motor and undercarriage, the bottom with casing fixed connection to be located one side of casing, the quantity of wing has a plurality ofly, a plurality ofly the wing with the casing intercommunication, and be located around the casing, the quantity of motor has a plurality ofly, and a plurality ofly the motor respectively with a plurality ofly wing fixed connection, and be located one side of wing, the quantity of screw has a plurality ofly, a plurality ofly the screw respectively with a plurality of the pivot fixed connection of motor, and be located one side of motor, the undercarriage with casing fixed connection, and be located the casing is close to one side of bottom, the temperature control subassembly includes sealed cabin, hatch door, heating resistor, circuit board and temperature sensor, the sealed cabin is provided with a plurality of through holes, the sealed cabin is fixedly connected with the shell and is positioned in the shell, the cabin door is connected with the sealed cabin in a sliding mode and is positioned on two sides of the sealed cabin, the heating resistor is fixedly connected with the sealed cabin and is positioned in the sealed cabin, the temperature sensor is fixedly connected with the sealed cabin and is positioned on one side of the sealed cabin, the circuit board is fixedly connected with the heating resistor and the temperature sensor and is positioned in the sealed cabin, the power assembly comprises an engine unit, a battery pack and a charging interface, the engine unit, the battery pack is fixedly connected with the sealed cabin and is positioned in the sealed cabin, and the charging interface is electrically connected with the circuit board and penetrates through the shell.
2. The novel temperature control system of the hybrid electric-gasoline hybrid electric water unmanned aerial vehicle as claimed in claim 1,
the body assembly further comprises an O-ring, wherein the O-ring is fixedly connected with the shell and is positioned between the shell and the bottom cover.
3. The novel temperature control system of hybrid electric-oil hybrid unmanned aerial vehicle on water as claimed in claim 2,
the fuselage assembly further comprises a filling layer, and the filling layer is fixedly connected with the wings and is positioned in the wings.
4. The novel temperature control system of hybrid electric-oil hybrid unmanned aerial vehicle on water as claimed in claim 3,
the aircraft body assembly further comprises an air cushion, and the air cushion is fixedly connected with the undercarriage and is located on one side of the undercarriage.
5. The novel temperature control system of the hybrid electric-gasoline hybrid electric water unmanned aerial vehicle as claimed in claim 1,
the power assembly further comprises an interface cover, and the interface cover is rotatably connected with the shell and is positioned in the charging interface.
6. The novel temperature control system of the hybrid electric-gasoline hybrid electric water unmanned aerial vehicle as claimed in claim 1,
the temperature control assembly further comprises an air cylinder and a connecting plate, the connecting plate is fixedly connected with the two cabin doors and is positioned on one side of the cabin doors, and a sliding rod of the air cylinder is fixedly connected with the connecting plate and is positioned on one side of the connecting plate.
7. The novel temperature control system of hybrid electric-oil unmanned aerial vehicle on water as claimed in claim 6,
the temperature control assembly further comprises a fan, and the fan is fixedly connected with the sealed cabin and is positioned in the sealed cabin.
8. The novel temperature control system of hybrid electric-oil hybrid unmanned aerial vehicle on water as claimed in claim 7,
the temperature control assembly further comprises a shock pad, and the shock pad is fixedly connected with the sealed cabin and is positioned on one side, close to the bottom cover, of the sealed cabin.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011442533.7A CN112455697A (en) | 2020-12-11 | 2020-12-11 | Novel temperature control system of oil-electricity hybrid power water unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011442533.7A CN112455697A (en) | 2020-12-11 | 2020-12-11 | Novel temperature control system of oil-electricity hybrid power water unmanned aerial vehicle |
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| Publication Number | Publication Date |
|---|---|
| CN112455697A true CN112455697A (en) | 2021-03-09 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011442533.7A Withdrawn CN112455697A (en) | 2020-12-11 | 2020-12-11 | Novel temperature control system of oil-electricity hybrid power water unmanned aerial vehicle |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN104102248A (en) * | 2014-07-02 | 2014-10-15 | 北京航空航天大学 | Unmanned aerial vehicle equipment cabin temperature control system capable of utilizing heat of engine |
| CN106516129A (en) * | 2016-11-10 | 2017-03-22 | 广东容祺智能科技有限公司 | Multi-rotor unmanned aerial vehicle system capable of adapting to northern ultra-low temperature environments |
| WO2018006439A1 (en) * | 2016-07-04 | 2018-01-11 | 深圳市龙云创新航空科技有限公司 | Integrated power multi-axis unmanned aerial vehicle |
| CN109144140A (en) * | 2018-11-12 | 2019-01-04 | 象限空间（天津）科技有限公司 | A kind of small drone cabin temperature control system and method |
| CN109733620A (en) * | 2018-11-22 | 2019-05-10 | 南京航空航天大学 | A kind of hybrid power unmanned plane and its control method |
| CN110318856A (en) * | 2019-07-12 | 2019-10-11 | 青岛未来创新高新技术有限公司 | The intelligent temperature control system and its implementation of unmanned vehicle engine |
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2020
- 2020-12-11 CN CN202011442533.7A patent/CN112455697A/en not_active Withdrawn
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104102248A (en) * | 2014-07-02 | 2014-10-15 | 北京航空航天大学 | Unmanned aerial vehicle equipment cabin temperature control system capable of utilizing heat of engine |
| WO2018006439A1 (en) * | 2016-07-04 | 2018-01-11 | 深圳市龙云创新航空科技有限公司 | Integrated power multi-axis unmanned aerial vehicle |
| CN106516129A (en) * | 2016-11-10 | 2017-03-22 | 广东容祺智能科技有限公司 | Multi-rotor unmanned aerial vehicle system capable of adapting to northern ultra-low temperature environments |
| CN109144140A (en) * | 2018-11-12 | 2019-01-04 | 象限空间（天津）科技有限公司 | A kind of small drone cabin temperature control system and method |
| CN109733620A (en) * | 2018-11-22 | 2019-05-10 | 南京航空航天大学 | A kind of hybrid power unmanned plane and its control method |
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