CN112810811B - Double-rotor unmanned aerial vehicle - Google Patents
Double-rotor unmanned aerial vehicle Download PDFInfo
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- CN112810811B CN112810811B CN202110069727.5A CN202110069727A CN112810811B CN 112810811 B CN112810811 B CN 112810811B CN 202110069727 A CN202110069727 A CN 202110069727A CN 112810811 B CN112810811 B CN 112810811B
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- 230000009977 dual effect Effects 0.000 claims description 14
- 230000009467 reduction Effects 0.000 claims description 14
- 238000003860 storage Methods 0.000 claims description 8
- 238000010248 power generation Methods 0.000 claims description 7
- 230000005540 biological transmission Effects 0.000 claims description 3
- 238000009826 distribution Methods 0.000 abstract description 3
- 238000000034 method Methods 0.000 description 7
- 230000005611 electricity Effects 0.000 description 4
- 230000009471 action Effects 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 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 2
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
- B64C27/10—Helicopters with two or more rotors arranged coaxially
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/20—Rotorcraft characterised by having shrouded rotors, e.g. flying platforms
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- 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
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- 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
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The embodiment of the application relates to a double-rotor unmanned aerial vehicle, which comprises: the double-rotor type air conditioner comprises a machine body, two coaxial double-rotors, fixed wings, tilting duct fans and a hybrid power system, wherein the coaxial double-rotors are arranged at the top of the machine body, the two tilting duct fans are symmetrically arranged at two sides of the machine body through the fixed wings, the hybrid power system is arranged inside the machine body and is connected with the coaxial double-rotors and the tilting duct fans so as to drive the coaxial double-rotors and the tilting duct fans, and the tilting duct fans can rotate around the machine body under the driving of the hybrid power system. The coaxial double-rotor wing and the ducted fan can be adjusted according to actual conditions so as to finish vertical take-off, landing and horizontal flight of the unmanned aerial vehicle, reduce flight resistance of an airplane, improve range of the unmanned aerial vehicle, drive the coaxial double-rotor wing and the ducted fan by adopting the hybrid power system, enable power distribution to be more reasonable, reduce oil consumption, improve navigational speed of the unmanned aerial vehicle and increase range and navigational time of the unmanned aerial vehicle.
Description
Technical Field
The application relates to the technical field of aircraft manufacturing, in particular to a double-rotor unmanned aerial vehicle.
Background
The vertical take-off and landing aircraft is hardly limited by a field, can take off and land on any level ground, can be deployed at a position closer to a battlefield, is convenient and quick for transporting personnel and materials, and greatly improves the efficiency of combined delivery; and the probability of being hit by enemy is greatly reduced because the device is not limited by the field.
Currently, vertical takeoff and landing aircraft are mainly divided into two main categories: rotorcraft and fixed wing aircraft. A typical representative of gyroplanes is various helicopters owned by the major military countries of the world. Such as the united states apaqi helicopter, the komanqi helicopter, the dried transshipment helicopter, the new generation of high speed helicopters S-97, etc., the russian kaseries helicopter, etc., the chinese helicopter, etc.
However, the maximum take-off weight of the helicopter is directly limited by the power of an engine at present, and after the vertical take-off is turned to be flat, the power requirement is further improved due to the increase of resistance, the oil consumption is increased, the range of the helicopter is greatly influenced, and the striking capability of the helicopter on a deep target is weaker.
Disclosure of Invention
The embodiment of the application provides a double-rotor unmanned aerial vehicle, which aims to solve the problem of smaller range of the existing rotorcraft.
The embodiment of the application provides a fan with a tilting duct and a hybrid power system, which comprises a machine body, coaxial double rotors, fixed wings and a rotating shaft;
the coaxial double rotor wings are arranged at the top of the fuselage;
the two tilting duct fans are symmetrically arranged on two sides of the machine body through the fixed wings;
the hybrid power system is arranged in the fuselage and is connected with the coaxial double-rotor wing and the tilting duct fan so as to drive the coaxial double-rotor wing and the tilting duct fan;
the tilting duct fan can rotate around the machine body under the drive of the hybrid power system.
Optionally, the tilting ducted fan comprises a tilting mechanism and a ducted fan;
the ducted fan is connected with the fixed wing through a tilting mechanism, and one end, far away from the ducted fan, of the fixed wing is connected with the machine body;
the hybrid power system is respectively connected with the tilting mechanism and the ducted fan.
Optionally, the hybrid power system comprises a multiple parallel operation speed reduction system and an electric propulsion system;
the multiple parallel operation speed reducing system is connected with the electric propulsion system;
the multiple parallel operation speed reducing system is connected with the coaxial double rotor wings;
the electric propulsion system is connected with the ducted fan;
the tilting mechanism is connected with the multiple parallel operation speed reducing system and/or the electric propulsion system.
Optionally, the multiple parallel operation speed reducing system comprises an engine and a speed reducing mechanism;
the number of the engines is N, the output shaft of each engine is in transmission connection with the speed reducing mechanism, and the speed reducing mechanism is connected with the coaxial double rotor wings and the tilting duct fan, wherein N is a positive integer not smaller than 2.
Optionally, the multiple parallel operation speed reducing system further comprises a plurality of starting and generating integrated motors, and each engine is connected with one starting and generating integrated motor;
the electric propulsion system comprises a storage battery and a power module;
the storage battery is electrically connected with the power module, and the power module is connected with the tilting duct fan and the starting and power generation integrated motor.
Optionally, the coaxial dual rotors comprise an upper rotor, a lower rotor, an outer rotor shaft, and an inner rotor shaft;
the outer rotary wing shaft is sleeved outside the inner rotary wing shaft;
the upper rotor wing is connected with the inner rotor wing shaft, and the lower rotor wing is connected with the outer rotor wing shaft.
Optionally, the reduction mechanism includes an upper aspect gear and a lower aspect gear;
the upper and lower gear teeth are mounted vertically coaxially facing the tooth surface;
the outer rotor shaft passes through the middle part of the upper aspect gear and is fixedly connected with the upper aspect gear;
the inner rotor shaft passes through the middle part of the lower aspect gear and is fixedly connected with the lower aspect gear;
and a power input cylindrical gear is connected to an output shaft of each engine, and the power input cylindrical gear is arranged between the upper aspect gear and the lower aspect gear and is meshed with the upper aspect gear and the lower aspect gear for driving.
Optionally, the rear ends of the two sides of the fuselage are symmetrically connected with horizontal tails.
Optionally, a vertical tail is connected to one end of the horizontal tail far away from the fuselage.
Optionally, the bottom of the fuselage is provided with landing gear mechanisms.
According to the double-rotor unmanned aerial vehicle provided by the application, in the first aspect, the coaxial double-rotor is arranged at the top of the fuselage, the two tilting duct fans are symmetrically arranged at two sides of the fuselage through the fixed wings, the hybrid power system is arranged inside the fuselage, and the hybrid power system is connected with the coaxial double-rotor and the tilting duct fans so as to drive the coaxial double-rotor and the tilting duct fans, the tilting duct fans can rotate around the fuselage under the driving of the hybrid power system, wherein the two tilting duct fans are symmetrically arranged at two sides of the fuselage through the fixed wings, and can rotate around the fuselage under the driving of the hybrid power system, when the unmanned aerial vehicle needs to take off vertically, the tilting duct fans can realize tilting under the driving of the hybrid power system so that the tilting duct fans are in the vertical direction, and further under the driving of the hybrid power, so that the tilting duct fans provide upward thrust to reduce the paddle area of the coaxial double-rotor, thereby reducing the rotating radius and the flight resistance of the coaxial double-rotor, when the unmanned aerial vehicle needs to fly horizontally, the tilting duct fans can realize the driving of the tilting duct fans under the hybrid power system, and the unmanned aerial vehicle can realize the tilting in the horizontal direction, and the unmanned aerial vehicle can realize the horizontal driving of the tilting duct fans under the horizontal direction.
In a second aspect, the hybrid power system is connected with the coaxial double-rotor wing and the tilting duct fan, and the coaxial double-rotor wing and the tilting duct fan are driven by the hybrid power system, so that power distribution is more reasonable, oil consumption is reduced, range and endurance of an aircraft are improved, in addition, the tilting duct fan is symmetrically arranged on two sides of the aircraft body through fixed wings, and the fixed wings can provide partial lifting force when the unmanned aerial vehicle flies horizontally, so that power consumption of the unmanned aerial vehicle is reduced, and horizontal flying speed of the unmanned aerial vehicle is improved.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings that are needed in the description of the embodiments of the present application will be briefly described below, it being obvious that the drawings in the following description are only some embodiments of the present application, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
Fig. 1 is a schematic side view of a dual rotor unmanned aerial vehicle according to an embodiment of the present application;
fig. 2 is a schematic diagram of a hybrid power system of a dual-rotor unmanned aerial vehicle according to an embodiment of the present application;
fig. 3 is a schematic top view of a dual rotor unmanned aerial vehicle according to an embodiment of the present application;
fig. 4 is a schematic front view of a dual-rotor unmanned aerial vehicle according to an embodiment of the present application;
fig. 5 is a schematic side view of a dual-rotor unmanned aerial vehicle in a vertical take-off and landing state according to an embodiment of the present application;
fig. 6 is a schematic diagram of a speed reducing mechanism of a dual-rotor unmanned aerial vehicle according to an embodiment of the present application.
Reference numerals illustrate:
1-fuselage, 2-coaxial twin rotors, 21-upper rotors, 22-lower rotors, 23-inner rotor shafts, 24-outer rotor shafts, 3-tilting ducted fans, 4-fixed wings, 5-hybrid power systems, 51-multiple parallel operation speed reduction systems, 511-engines, 5111-engine output shafts, 5112-power input cylindrical gears, 512-speed reduction mechanisms, 5121-upper aspect gears, 5122-lower aspect gears, 513-start power generation integrated motors, 52-electric propulsion systems, 521-storage batteries, 522-power modules, 6-horizontal tails, 7-vertical tails and 8-landing gear mechanisms.
Detailed Description
The following description of the embodiments of the present application will be made clearly and fully with reference to the accompanying drawings, in which it is evident that the embodiments described are some, but not all embodiments of the application. All other embodiments, which can be made by those skilled in the art based on the embodiments of the application without making any inventive effort, are intended to be within the scope of the application.
In the related art, the vertical takeoff and landing aircraft is mainly divided into two main categories: rotorcraft and fixed wing aircraft. A typical representative of gyroplanes is various helicopters owned by the major military countries of the world. Such as the united states apaqi helicopter, the komanqi helicopter, the dried transshipment helicopter, the new generation of high speed helicopters S-97, etc., the russian kaseries helicopter, etc., the chinese helicopter, etc.
However, the maximum take-off weight of the existing helicopter is directly limited by the power of an engine, and after the vertical take-off is turned to be flat, the power requirement is further improved due to the increase of resistance, the oil consumption is increased, the range of the helicopter is greatly influenced, and the striking capability of the helicopter on a deep target is weaker.
In view of the above, the application creatively provides a double-rotor unmanned aerial vehicle, which aims to solve the problem of smaller range of the existing rotorcraft.
Referring to fig. 1 and fig. 2, fig. 1 is a schematic side view of a dual-rotor unmanned aerial vehicle according to an embodiment of the present application, and fig. 2 is a schematic hybrid power system of a dual-rotor unmanned aerial vehicle according to an embodiment of the present application. As shown in fig. 1 and 2, the dual-rotor unmanned aerial vehicle comprises a body 1, a coaxial dual-rotor 2, a fixed wing 4, a tilting duct fan 3 and a hybrid power system 5;
the coaxial double rotor wing 2 is arranged at the top of the fuselage 1;
the two tilting duct fans 3 are symmetrically arranged on two sides of the machine body 1 through the fixed wings 4;
the hybrid power system 5 is arranged inside the machine body 1, and the hybrid power system 5 is connected with the coaxial double-rotor wing 2 and the tilting duct fan 3 to drive the coaxial double-rotor wing 2 and the tilting duct fan 3;
the tilting duct fan 3 can rotate around the main body 1 under the drive of the hybrid system 5.
In this embodiment, two tilting ducted fans 3 are symmetrically disposed on two sides of the fuselage 1 through fixed wings 4, and the tilting ducted fans 3 can rotate around the fuselage 1 under the driving of the hybrid power system 5, when the unmanned aerial vehicle needs to take off vertically, the tilting ducted fans 3 can tilt under the driving of the hybrid power system 5, so that the tilting ducted fans 3 are in the vertical direction, and then under the driving of the hybrid power, the upward thrust is provided, so as to reduce the pitch disk area of the coaxial dual rotor 2, thereby reducing the rotation radius and the flight resistance of the coaxial dual rotor 2, when the unmanned aerial vehicle needs to fly horizontally, the tilting ducted fans 3 can tilt under the driving of the hybrid power system 5, so that the tilting ducted fans 3 can provide the horizontal thrust under the driving of the hybrid power system 5, and thereby accelerating the forward flying speed of the unmanned aerial vehicle.
The hybrid power system 5 is connected with the coaxial double rotor wing 2 and the tilting duct fan 3, the coaxial double rotor wing 2 and the tilting duct fan 3 are driven by the hybrid power system 5, so that power distribution can be more reasonable, oil consumption can be reduced, range and endurance of an airplane are improved, in addition, the tilting duct fan 3 is symmetrically arranged on two sides of the airplane body 1 through the fixed wings 4, and the fixed wings 4 can provide partial lifting force when the unmanned aerial vehicle horizontally flies, so that power consumption of the unmanned aerial vehicle is reduced, horizontal flying speed of the unmanned aerial vehicle is improved, wherein the fixed wings 4 on each side can be 2 or more and can be specifically set according to actual requirements, and the unmanned aerial vehicle is not particularly limited.
Based on the dual-rotor unmanned aerial vehicle, the application provides the following specific embodiment examples, and the examples can be arbitrarily combined on the premise of not contradicting each other to form a new dual-rotor unmanned aerial vehicle. It should be understood that, for the new double rotor unmanned aerial vehicle formed by any combination of examples, it is within the scope of the present application.
Referring to fig. 1 to 5, fig. 3 is a schematic top view of a dual-rotor unmanned aerial vehicle according to an embodiment of the present application, fig. 4 is a schematic front view of a dual-rotor unmanned aerial vehicle according to an embodiment of the present application, and fig. 5 is a schematic side view of a vertical take-off and landing state of a dual-rotor unmanned aerial vehicle according to an embodiment of the present application, in which, in a possible implementation manner, the tilting ducted fan 3 includes a tilting mechanism and a ducted fan;
the ducted fan is connected with the fixed wing 4 through a tilting mechanism, and one end, far away from the ducted fan, of the fixed wing 4 is connected with the machine body 1;
the hybrid power system 5 is connected to the tilting mechanism and the ducted fan, respectively.
In this embodiment, the tilting ducted fan 3 includes a tilting mechanism and a ducted fan, where the ducted fan is connected to the fixed wing 4 through the tilting mechanism, one end of the fixed wing 4 away from the ducted fan is connected to the fuselage 1, the hybrid system 5 is connected to the tilting mechanism and the ducted fan respectively, the hybrid system 5 can drive the tilting mechanism, so that the tilting mechanism drives the ducted fan to rotate, where when the ducted fan flies horizontally, the central axis of the ducted fan is parallel to the central axis of the unmanned aerial vehicle, the ducted fan can rotate under the drive of the hybrid system 5, so as to provide forward thrust, and when the unmanned aerial vehicle needs to lift vertically, the hybrid system 5 can drive the tilting mechanism, so that the tilting mechanism drives the ducted fan to tilt from the horizontal direction to the vertical direction, at this time, the ducted fan can provide upward thrust under the drive of the hybrid system 5, so as to cooperate with the coaxial double rotor 2 to realize vertical lifting of the unmanned aerial vehicle.
In one possible embodiment, the hybrid system 5 includes a multiple parallel operation speed reduction system 51 and an electric propulsion system 52;
the multiple parallel operation speed reducing system 51 is connected with the electric propulsion system 52;
the multiple parallel operation speed reducing system 51 is connected with the coaxial double rotor wing 2;
the electric propulsion system 52 is connected with the ducted fan;
the tilting mechanism is connected to the multiple parallel operation deceleration system 51 and/or the electric propulsion system 52.
In the present embodiment, the hybrid system 5 includes a multiple parallel operation speed reduction system 51 and an electric propulsion system 52, wherein the multiple parallel operation speed reduction system 51 is connected with the electric propulsion system 52 so as to enable the cooperative use of the engine 511 and the motor and the energy recovery, the multiple parallel operation speed reduction system 51 is connected with the coaxial twin-rotor 2 so as to enable the hybrid power of the engine 511 and the motor to be used for driving the coaxial twin-rotor 2, and the electric propulsion system 52 is connected with the ducted fan, wherein the electric propulsion system 52 provides electric energy so as to enable the ducted fan to operate by driving the ducted fan by the electric energy so as to enable the ducted fan to provide thrust.
The tilting mechanism is connected to the multiple parallel operation speed reduction system 51 and/or the electric propulsion system 52, i.e. the tilting mechanism may be connected to the multiple parallel operation speed reduction system 51 so as to drive the tilting mechanism by the engine 511, for example, the tilting mechanism may include a bearing and a tilting shaft, the bearing is disposed in the fixed wing 4, the tilting shaft passes through the bearing, one end of the tilting shaft is in driving connection with the multiple parallel operation speed reduction system 51, the other end of the tilting shaft is connected to the ducted fan so as to drive the tilting shaft to rotate by the multiple parallel operation speed reduction system 51, and further drive the ducted fan to rotate, the tilting mechanism may also be connected to the electric propulsion system 52 so as to drive the tilting mechanism to rotate by the electric power supplied by the battery, for example, the tilting mechanism may include a servo motor disposed in the fixed wing 4, an output shaft of the servo motor is connected to the ducted fan, the electric propulsion system 52 drives the servo motor to operate, and further drive the ducted fan to rotate by an output shaft of the servo motor, and in addition, the tilting mechanism may further include a limiter may be connected to the multiple parallel operation speed reduction system 51 or the electric propulsion system 52 so as to drive the ducted fan to rotate by the electric motor to a horizontal position or a vertical position of the ducted fan to avoid the rotation of the ducted fan from being fixed to the horizontal position or the vertical position of the body 1.
In one possible embodiment, the multiple parallel operation deceleration system 51 includes an engine 511 and a deceleration mechanism 512;
the number of the engines 511 is N, the output shaft 5111 of each engine is in transmission connection with the speed reducing mechanism 512, and the speed reducing mechanism 512 is connected with the coaxial double rotor wing 2 and the tilting duct fan 3, wherein N is a positive integer not less than 2.
In this embodiment, the multiple parallel operation speed reducing system 51 includes an engine 511 and a speed reducing mechanism 512, where the number of the engines 511 is N, and the output shaft 5111 of each engine is in driving connection with the speed reducing mechanism 512, and the speed reducing mechanism 512 is connected with the coaxial twin rotors 2 and the tilting duct fans 3, where N is a positive integer not less than 2, that is, the number of the engines 511 may be 2 or more, and the output shafts 5111 of the multiple engines are in driving connection with the speed reducing mechanism 512, so as to be capable of simultaneously providing output power to drive the coaxial twin rotors 2 to increase the navigational speed of the aircraft.
In a possible embodiment, the multiple parallel operation speed reducing system 51 further includes a plurality of start-up and power-generation integrated motors 513, and each of the motors 511 is connected to one of the start-up and power-generation integrated motors 513;
the electric propulsion system 52 includes a battery 521 and a power module 522;
the battery 521 is electrically connected to the power module 522, and the power module 522 is connected to the tilting duct fan 3 and the integrated starter-generator motor 513.
In this embodiment, the multiple-parallel operation speed reducing system 51 further includes a plurality of integrated motors 513 for starting and generating electricity, each motor 511 is connected to one integrated motor 513 for starting and generating electricity, the integrated motors 513 for starting the motors 511 can generate electricity under the rotation of the motors 511 to charge the storage battery 521, the electric propulsion system 52 includes the storage battery 521 and a power module 522, wherein the storage battery 521 is electrically connected to the power module 522, the power module 522 is connected to the tilting duct fan 3 and the integrated motors 513 for starting and generating electricity, the electric energy of the storage battery 521 reaches the motor of the duct fan through the power module 522 to drive the motor of the duct fan to work, so that the duct fan works to provide thrust, and the power module 522 can reasonably distribute the power of the multiple-parallel operation speed reducing system 51 and the electric propulsion system 52 to achieve the purpose of saving energy.
In one possible embodiment, the coaxial twin rotor 2 comprises an upper rotor 21, a lower rotor 22, an outer rotor shaft 24 and an inner rotor shaft 23;
the outer rotor shaft 24 is sleeved outside the inner rotor shaft 23;
the upper rotor 21 is connected to the inner rotor shaft 23, and the lower rotor 22 is connected to the outer rotor shaft 24.
In the present embodiment, the coaxial twin rotor 2 includes an upper rotor 21, a lower rotor 22, an outer rotor shaft 24, and an inner rotor shaft 23, wherein the outer rotor shaft 24 is sleeved outside the inner rotor shaft 23, the upper rotor 21 is connected with the inner rotor shaft 23, the lower rotor 22 is connected with the outer rotor shaft 24 so that the upper rotor 21 rotates together with the inner rotor shaft 23, the lower rotor 22 rotates together with the outer rotor shaft 24, and the upper rotor 21 and the lower rotor 22 are separately rotatable.
Referring to fig. 1 to 6, fig. 6 is a schematic view of a speed reducing mechanism 512 of a dual rotor unmanned aerial vehicle according to an embodiment of the present application, and in a possible implementation, the speed reducing mechanism 512 includes an upper aspect gear 5121 and a lower aspect gear 5122;
the upper face gear 5121 and the lower face gear 5122 are vertically and coaxially mounted tooth-to-tooth;
the outer rotor shaft 24 passes through the middle of the upper gear 5121 and is fixedly connected with the upper gear 5121;
the inner rotor shaft 23 passes through the middle of the lower aspect gear 5122 and is fixedly connected with the lower aspect gear 5122;
a power input spur gear 5112 is connected to the output shaft 5111 of each of the engines, and the power input spur gear 5112 is disposed between the upper and lower spur gears 5121 and 5122 and is engaged with and driven by the upper and lower spur gears 5121 and 5122.
In this embodiment, the speed reducing mechanism 512 includes an upper gear 5121 and a lower gear 5122, the teeth of the upper gear 5121 and the lower gear 5122 are vertically and coaxially installed facing the tooth surface, the outer rotor shaft 24 passes through the middle of the upper gear 5121 and is fixedly connected with the upper gear 5121, the inner rotor shaft 23 passes through the middle of the lower gear 5122 and is fixedly connected with the lower gear 5122, and the upper gear 5121 and the lower gear 5122 can rotate relatively, so that the outer rotor shaft 24 can be driven to rotate by the upper gear 5121, and the inner rotor shaft 23 can be driven to rotate by the lower gear 5122. A power input spur gear 5112 is connected to the output shaft 5111 of each engine, and the power input spur gear 5112 is disposed between the upper and lower aspect gears 5121 and 5122 and is in meshed driving with the upper and lower aspect gears 5121 and 5122, so that the output shaft 5111 of the engine can rotate the upper and lower aspect gears 5121 and 5122 in opposite directions through the power input spur gear 5112 to rotate the upper and lower rotary wings 21 and 22 in opposite directions.
In a possible embodiment, the rear ends of both sides of the fuselage 1 are symmetrically connected with the horizontal tail 6.
In the present embodiment, the horizontal rear wing 6 can improve the balance performance of the unmanned aerial vehicle.
In a possible embodiment, a vertical tail 7 is connected to the horizontal tail 6 at the end remote from the fuselage 1.
In this embodiment, the vertical tail 7 can assist steering of the unmanned aerial vehicle, so as to improve the maneuvering performance of the unmanned aerial vehicle.
In a possible embodiment, the bottom of the fuselage 1 is provided with landing gear mechanisms 8.
In this embodiment, the bottom of the fuselage 1 is provided with the landing gear mechanism 8 to facilitate the support of the fuselage 1 when the unmanned aerial vehicle is lifted, avoiding the damage caused by the fuselage 1 contacting the ground.
In a possible implementation manner, the unmanned aerial vehicle further comprises a scanning imaging and communication radar system, a fire control system and a flight control system, wherein the scanning imaging and communication radar system, the fire control system and the flight control system are all arranged in the unmanned aerial vehicle 1 so as to improve the practical performance of the unmanned aerial vehicle.
It should be understood that while the description of the application has described preferred embodiments of the application, additional variations and modifications in those embodiments may occur to those skilled in the art once they learn of the basic inventive concepts. It is therefore intended that the following claims be interpreted as including the preferred embodiment and all such alterations and modifications as fall within the scope of the embodiments of the application.
Finally, it is further 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 terminal 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 terminal. 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 terminal device comprising the element.
The above description of the present application provides a dual rotor unmanned aerial vehicle, and specific examples are applied to illustrate the principles and embodiments of the present application, where the above examples are only used to help understand the method and core ideas of the present application; meanwhile, as those skilled in the art will have variations in the specific embodiments and application scope in accordance with the ideas of the present application, the present description should not be construed as limiting the present application in view of the above.
Claims (8)
1. The double-rotor unmanned aerial vehicle is characterized by comprising a fuselage (1), coaxial double rotors (2), fixed wings (4), a tilting ducted fan (3) and a hybrid power system (5);
the coaxial double rotor wing (2) is arranged at the top of the machine body (1);
the two tilting duct fans (3) are symmetrically arranged at two sides of the machine body (1) through the fixed wings (4);
the hybrid power system (5) is arranged inside the machine body (1), and the hybrid power system (5) is connected with the coaxial double-rotor wing (2) and the tilting duct fan (3) so as to drive the coaxial double-rotor wing (2) and the tilting duct fan (3);
the tilting duct fan (3) can rotate around the machine body (1) under the drive of the hybrid power system (5);
the hybrid power system (5) comprises a multiple parallel operation speed reducing system (51) and an electric propulsion system (52), the multiple parallel operation speed reducing system (51) comprises engines (511) and speed reducing mechanisms (512), the number of the engines (511) is N, N is a positive integer not less than 2, an output shaft (5111) of the engines (511) is in transmission connection with the speed reducing mechanisms (512), and the speed reducing mechanisms (512) are connected with the coaxial double rotor wings (2); the multiple-parallel operation speed reducing system (51) further comprises a plurality of starting and power generation integrated motors (513), and each engine (511) is connected with one starting and power generation integrated motor (513); the electric propulsion system (52) includes a battery (521) and a power module (522); the storage battery (521) is electrically connected with the power module (522), and the power module (522) is connected with the tilting duct fan (3) and the starting and power generation integrated motor (513).
2. The dual rotor unmanned aerial vehicle of claim 1, wherein,
the tilting ducted fan (3) comprises a tilting mechanism and a ducted fan;
the ducted fan is connected with the fixed wing (4) through a tilting mechanism, and one end, far away from the ducted fan, of the fixed wing (4) is connected with the machine body (1);
the hybrid power system (5) is respectively connected with the tilting mechanism and the ducted fan.
3. The dual rotor drone of claim 2, wherein,
the multiple parallel operation speed reducing system (51) is connected with the electric propulsion system (52);
the multiple parallel operation speed reducing system (51) is connected with the coaxial double rotor wing (2);
the electric propulsion system (52) is connected with the ducted fan;
the tilting mechanism is connected with the multiple parallel operation speed reducing system (51) and/or the electric propulsion system (52).
4. The dual rotor unmanned aerial vehicle of claim 1, wherein,
the coaxial double-rotor (2) comprises an upper rotor (21), a lower rotor (22), an outer rotor shaft (24) and an inner rotor shaft (23);
the outer rotary wing shaft (24) is sleeved outside the inner rotary wing shaft (23);
the upper rotor (21) is connected with the inner rotor shaft (23), and the lower rotor (22) is connected with the outer rotor shaft (24).
5. The dual rotor unmanned aerial vehicle of claim 4, wherein,
the reduction mechanism (512) includes an upper aspect gear (5121) and a lower aspect gear (5122);
the upper face gear (5121) and the lower face gear (5122) are vertically and coaxially mounted tooth-to-tooth;
the outer rotary wing shaft (24) passes through the middle part of the upper aspect gear (5121) and is fixedly connected with the upper aspect gear (5121);
the inner rotor shaft (23) passes through the middle part of the lower aspect gear (5122) and is fixedly connected with the lower aspect gear (5122);
a power input cylindrical gear (5112) is connected to an output shaft (5111) of each engine, and the power input cylindrical gear (5112) is arranged between the upper aspect gear (5121) and the lower aspect gear (5122) and is in meshed driving with the upper aspect gear (5121) and the lower aspect gear (5122).
6. The dual rotor unmanned aerial vehicle of claim 1, wherein,
the rear ends of the two sides of the machine body (1) are symmetrically connected with horizontal tail wings (6).
7. The dual rotor drone of claim 6, wherein,
one end, far away from the machine body (1), of the horizontal tail wing (6) is connected with a vertical tail (7).
8. The dual rotor unmanned aerial vehicle of claim 1, wherein,
the bottom of the machine body (1) is provided with a landing gear mechanism (8).
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| WO2022260634A1 (en) * | 2021-06-07 | 2022-12-15 | Ali Turan | Differential gearbox with output shafts that are on the same side and rotate in reverse directions |
| CN115352643A (en) * | 2022-08-08 | 2022-11-18 | 北京科技大学 | Multi-parallel-engine coaxial dual-rotor helicopter power assembly based on single-plane gear pair |
| CN115200648B (en) * | 2022-09-14 | 2022-11-29 | 四川省亚通工程咨询有限公司 | Bridge state monitoring system and method based on unmanned aerial vehicle |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102211663A (en) * | 2011-05-11 | 2011-10-12 | 王略 | Gear tilting type coaxial machine |
| CN107856488A (en) * | 2017-11-16 | 2018-03-30 | 四川省特种设备检验研究院 | It is a kind of can VTOL plug-in hybrid hovercar power drive system |
| CN108528734A (en) * | 2017-03-02 | 2018-09-14 | 贝尔直升机德事隆公司 | Hybrid propulsion drivetrain system for tiltrotor aircraft |
| WO2019184869A1 (en) * | 2018-03-28 | 2019-10-03 | 刘保伸 | Multi-purpose helicopter having dual compartment structure, electronic omni-directional rotor assembly, and application thereof |
| CN111483590A (en) * | 2020-05-26 | 2020-08-04 | 清华大学 | Coaxial contra-rotating dual-rotor speed reduction transmission structure |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20170267338A1 (en) * | 2014-10-01 | 2017-09-21 | Sikorsky Aircraft Corporation | Acoustic signature variation of aircraft utilizing a clutch |
| US11148799B2 (en) * | 2018-11-26 | 2021-10-19 | Textron Innovations Inc. | Tilting duct compound helicopter |
-
2021
- 2021-01-19 CN CN202110069727.5A patent/CN112810811B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102211663A (en) * | 2011-05-11 | 2011-10-12 | 王略 | Gear tilting type coaxial machine |
| CN108528734A (en) * | 2017-03-02 | 2018-09-14 | 贝尔直升机德事隆公司 | Hybrid propulsion drivetrain system for tiltrotor aircraft |
| CN107856488A (en) * | 2017-11-16 | 2018-03-30 | 四川省特种设备检验研究院 | It is a kind of can VTOL plug-in hybrid hovercar power drive system |
| WO2019184869A1 (en) * | 2018-03-28 | 2019-10-03 | 刘保伸 | Multi-purpose helicopter having dual compartment structure, electronic omni-directional rotor assembly, and application thereof |
| CN111483590A (en) * | 2020-05-26 | 2020-08-04 | 清华大学 | Coaxial contra-rotating dual-rotor speed reduction transmission structure |
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