CN210310866U - Take propeller type, folding, five rotor unmanned vehicles of oil-electricity hybrid - Google Patents
Take propeller type, folding, five rotor unmanned vehicles of oil-electricity hybrid Download PDFInfo
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- CN210310866U CN210310866U CN201920783809.4U CN201920783809U CN210310866U CN 210310866 U CN210310866 U CN 210310866U CN 201920783809 U CN201920783809 U CN 201920783809U CN 210310866 U CN210310866 U CN 210310866U
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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
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- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/60—Other road transportation technologies with climate change mitigation effect
- Y02T10/7072—Electromobility specific charging systems or methods for batteries, ultracapacitors, supercapacitors or double-layer capacitors
Abstract
The utility model relates to the technical field of aviation, in particular to a five-rotor unmanned aerial vehicle with tail rotor, folding and oil-electricity hybrid power, which comprises a five-rotor unmanned aerial vehicle frame and an oil-electricity hybrid power system; the hybrid power system of oil electricity installs in five rotor unmanned vehicles frames, five rotor unmanned vehicles frames include framework undercarriage, first electric rotor bracing piece, electricity generation transmission system mounting bracket and compound bracing piece, hybrid power system of oil electricity includes electric rotor, horizontal bar piston engine, power battery, electricity generation belt drive system and main rotor, and electric rotor and main rotor all install in five rotor unmanned vehicles frames and by installing the horizontal bar piston engine drive in five rotor unmanned vehicles frames through the piston engine mounting bracket and rotate. The utility model relates to a novelty can effectively increase rotor type aircraft time of navigating through generator and the power battery that sets up, improves the power system reliability, the effectual oil consumption that has reduced simultaneously.
Description
Technical Field
The utility model relates to the technical field of aviation, specifically a take propeller type, folding, five rotor unmanned vehicles of oil-electricity hybrid.
Background
An unmanned aerial vehicle, also known as an unmanned plane and abbreviated as "unmanned aerial vehicle", and abbreviated as "UAV", is an unmanned aerial vehicle operated by a radio remote control device and a self-contained program control device, or autonomously operated by an onboard computer, either completely or intermittently.
With the rapid development of aviation science and technology, the technical development of the rotor type unmanned aerial vehicle is mature, and although the types of the rotor type unmanned aerial vehicle are very many, the further popularization and the use of the application industrial rotor type unmanned aerial vehicle with higher practical value are limited due to the problems of low flight aerodynamic efficiency and short technical plate of a power system. The utility model provides a take removable folding five rotor unmanned vehicles of oil-electricity hybrid of tail-rotor formula, problem more than can fine solution.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide a take propeller type, folding, five rotor unmanned vehicles of oil-electricity hybrid to solve the problem that proposes among the above-mentioned background art.
In order to achieve the above object, the utility model provides a following technical scheme:
a five-rotor unmanned aerial vehicle with a tail rotor type, folding and oil-electricity hybrid power comprises a five-rotor unmanned aerial vehicle frame and an oil-electricity hybrid power system; the oil-electricity hybrid power system is arranged on a five-rotor unmanned aerial vehicle frame, the five-rotor unmanned aerial vehicle frame plays an effective supporting role, the five-rotor unmanned aerial vehicle frame comprises a framework type undercarriage, a first electric rotor support rod, a power generation transmission system mounting frame and a composite support rod, the first electric rotor support rod is provided with three groups and is circumferentially arranged on the power generation transmission system mounting frame together with the composite support rod, the framework type undercarriage is arranged at the lower end of the power generation transmission system mounting frame through a plug engine mounting frame, the oil-electricity hybrid power system comprises an electric rotor, a single-bar piston engine, a power battery, a power generation belt transmission system and a main rotor, the electric rotor and the main rotor are both arranged on the five-rotor unmanned aerial vehicle frame and are driven to rotate by the single-bar piston engine arranged on the five-rotor unmanned aerial vehicle frame through the piston engine, the horizontal bar piston engine is connected with the power battery electricity installed on the plug engine mounting frame, and the power battery is still connected with the generator electricity, the generator is connected with the rotation shaft of the main rotor through the power generation belt transmission system.
As a further aspect of the present invention: and the horizontal bar piston engine is also electrically connected with a voltage stabilizing rectifier.
As a further aspect of the present invention: and the first electric rotor wing supporting rod and the composite supporting rod are respectively provided with an electric rotor wing.
As a further aspect of the present invention: first electronic rotor bracing piece includes end dead lever and folding rod, and the one end side of end dead lever is connected through folding pivot and folding rod rotation, and the side that folding pivot was kept away from to fixed pole passes through set screw and folding rod fixed connection.
As a further aspect of the present invention: the electric rotor wing comprises a motor base, a brushless direct current motor and a rotor wing, the rotor wing is installed on an output shaft of the brushless direct current motor, the brushless direct current motor is fixedly connected with the folding rod through the motor base, and the brushless direct current motor is electrically connected with the power battery through an electric regulation.
As a further aspect of the present invention: the compound bracing piece includes electronic rotor bracing piece of second, hexagonal pole and electronic tail-rotor, and the one end of the electronic rotor bracing piece of second is fixed on the electricity generation transmission system mounting bracket, and the other end is pegged graft with hexagonal pole, and electronic tail-rotor is installed and is kept away from the one end and the setting of perpendicular to hexagonal pole of the electronic rotor bracing piece of second at hexagonal pole.
As a further aspect of the present invention: the electric tail rotor comprises a tail rotor, a tail rotor motor and a tail rotor motor base, the tail rotor motor is installed on the hexagonal rod through the tail rotor motor base, and an output shaft of the tail rotor motor base is fixedly connected with the tail rotor.
Compared with the prior art, the beneficial effects of the utility model are that: the utility model has novel design, can effectively increase the navigation time of the rotor type aircraft through the arranged generator and the power battery, improves the reliability of a power system, and simultaneously effectively reduces the oil consumption; the load can be effectively increased according to the operation condition.
Drawings
Fig. 1 is a schematic structural diagram of a five-rotor unmanned aerial vehicle with a tail rotor, a folding structure and a hybrid power of oil and electricity.
Fig. 2 is another schematic structural diagram of the five-rotor unmanned aerial vehicle with the tail rotor, the folding and the oil-electricity hybrid power.
Fig. 3 is another schematic structural diagram of a five-rotor unmanned aerial vehicle with a tail rotor, a folding structure and a hybrid power of oil and electricity.
Fig. 4 is a schematic structural view of a first electric rotor support rod in a five-rotor unmanned aerial vehicle with a tail rotor, a folding structure and a hybrid power of oil and electricity.
Fig. 5 is a schematic structural diagram of a composite support rod in a five-rotor unmanned aerial vehicle with a tail rotor, a folding structure and a hybrid power of oil and electricity.
Fig. 6 is a schematic view of a folded state of three first electric rotor support rods of a five-rotor unmanned aerial vehicle with a tail rotor, a folding structure and a hybrid power of oil and electricity.
Fig. 7 is a schematic diagram of a fully folded state of a five-rotor unmanned aerial vehicle with a tail rotor, a folding state and a hybrid power of oil and electricity.
Fig. 8 is a schematic diagram of a fully folded state (with a detachable tail rotor) of the five-rotor unmanned aerial vehicle with a tail rotor, a folding type and a hybrid power of oil and electricity.
In the figure: 1. the five-rotor unmanned aerial vehicle comprises a five-rotor unmanned aerial vehicle frame, 2. a gasoline-electric hybrid power system, 1-1. a framework type undercarriage, 1-2. a piston engine mounting rack, 1-3. a first electric rotor support rod, 1-4. a power generation transmission system mounting rack, 1-5. a composite support rod, 2-1. an electric rotor, 2-2. a voltage stabilizing rectifier, 2-3. a single-rod piston engine, 2-4. a power battery, 2-5. a power generator, 2-6. an electric tail rotor, 2-7. a power generation belt transmission system, 2-8. a main rotor, 1-3-1. an end fixing rod, 1-3-2. a fixing screw, 1-3-3. a folding rotating shaft, 1-3-4. a folding rod, 1-3-5. an electric regulator, 1-3-6 motor seats, 1-3-7 brushless direct current motors, 1-3-8 rotors, 1-5-1 second electric rotor supporting rods, 1-5-2 hexagonal rods, 1-5-3 tail rotors, 1-5-4 tail rotor motors and 1-5-5 tail rotor motor seats.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
Example one
Referring to fig. 1 to 8, in an embodiment of the present invention, a five-rotor unmanned aerial vehicle with a tail rotor, a foldable structure, and a hybrid power system includes a five-rotor unmanned aerial vehicle frame 1 and a hybrid power system 2; the oil-electricity hybrid power system 2 is installed on a five-rotor unmanned aerial vehicle frame 1, the five-rotor unmanned aerial vehicle frame 1 plays an effective bearing role, the five-rotor unmanned aerial vehicle frame 1 comprises a framework type undercarriage 1-1, first electric rotor supporting rods 1-3, a power generation transmission system installation frame 1-4 and composite supporting rods 1-5, the first electric rotor supporting rods 1-3 are provided with three groups and are circumferentially installed on the power generation transmission system installation frame 1-4 together with the composite supporting rods 1-5, the framework type undercarriage 1-1 is installed at the lower end of the power generation transmission system installation frame 1-4 through a plug engine installation frame 1-2, the oil-electricity hybrid power system 2 comprises electric rotors 2-1, a single-bar piston engine 2-3, power batteries 2-4, a power supply system and a power supply system, The power generation belt transmission system 2-7 and the main rotor 2-8, the electric rotor 2-1 and the main rotor 2-8 are both arranged on the five-rotor unmanned aerial vehicle frame 1 and driven to rotate by a horizontal bar piston engine 2-3 arranged on the five-rotor unmanned aerial vehicle frame 1 through a piston engine mounting frame 1-2, the horizontal bar piston engine 2-3 is electrically connected with a power battery 2-4 arranged on the plug engine mounting frame 1-2, the power battery 2-4 is also electrically connected with a power generator 2-5, the power generator 2-5 is rotationally connected with a rotating shaft of the main rotor 2-8 through the power generation belt transmission system 2-7, the power generator 2-5 is driven to generate power through the power generation belt transmission system 2-7 when the main rotor 2-8 rotates, the power generation is stored in the power battery 2-4, the electric power storage is realized, so that the aircraft power battery 2-4 can be detachably and independently charged, the power battery 2-4 can be charged through the aircraft generator 2-5 under the condition of medium and low load, and the navigation time of the rotor wing aircraft is effectively prolonged.
It should be noted that the power battery 2-4 of the oil-electric hybrid power system 2 can realize two modes of disassembly charging and on-board power generation charging, and the battery capacity of the power battery must ensure that the horizontal bar piston engine 2-3 stops in the air and can continuously fly for more than 3min by virtue of the electric lift force under the condition of full power and the condition that the load of an aircraft is generally loaded.
Preferably, the horizontal bar piston engine 2-3 is also electrically connected with a voltage stabilizing rectifier 2-2, so that the stability of the current of the power battery 2-4 entering the horizontal bar piston engine 2-3 is ensured, and the flying stability of the aircraft is further improved.
Further, the first electric rotor wing supporting rod 1-3 and the composite supporting rod 1-5 are respectively provided with an electric rotor wing 2-1 for providing power during takeoff.
Specifically, the first electric rotor wing supporting rod 1-3 comprises an end fixing rod 1-3-1 and a folding rod 1-3-4, the side edge of one end of the end fixing rod 1-3-1 is rotatably connected with the folding rod 1-3-4 through a folding rotating shaft 1-3-3, and the side edge of the end fixing rod 1-3-1 far away from the folding rotating shaft 1-3-3 is fixedly connected with the folding rod 1-3-4 through a fixing screw 1-3-2, so that the folding and unfolding of the end fixing rod 1-3-1 and the folding rod 1-3-4 can be realized.
Still further, the electric rotor 2-1 comprises a motor base 1-3-6, a brushless direct current motor 1-3-7 and a rotor 1-3-8, the rotor 1-3-8 is mounted on an output shaft of the brushless direct current motor 1-3-7, the brushless direct current motor 1-3-7 is fixedly connected with the folding rod 1-3-4 through the motor base 1-3-6, the brushless direct current motor 1-3-7 is electrically connected with the power battery 2-4 through an electric regulator 1-3-5, and the rotor 1-3-8 is driven to rotate when the brushless direct current motor 1-3-7 works.
Example two
The utility model discloses still explain 1-5 in the concrete implementation in-process in detail, it is specific, compound bracing piece 1-5 includes second electronic rotor bracing piece 1-5-1, hexagonal pole 1-5-2 and electronic tail rotor 2-6, and the one end of second electronic rotor bracing piece 1-5-1 is fixed on electricity generation transmission system mounting bracket 1-4, and the other end pegs graft with hexagonal pole 1-5-2, and electronic tail rotor 2-6 is installed and is kept away from the one end of second electronic rotor bracing piece 1-5-1 and perpendicular to hexagonal pole 1-5-2 setting at hexagonal pole 1-5-2.
Specifically, the electric tail rotor 2-6 comprises a tail rotor 1-5-3, a tail rotor motor 1-5-4 and a tail rotor motor base 1-5-5, the tail rotor motor 1-5-4 is installed on the hexagonal rod 1-5-2 through the tail rotor motor base 1-5-5, an output shaft of the tail rotor motor base 1-5-5 is fixedly connected with the tail rotor 1-5-3, and the tail rotor motor base 1-5-5 drives the tail rotor 1-5-3 to rotate so as to achieve the steering effect.
It is obvious to a person skilled in the art that the invention is not restricted to details of the above-described exemplary embodiments, but that it can be implemented in other specific forms without departing from the spirit or essential characteristics of the invention. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.
Furthermore, it should be understood that although the present description refers to embodiments, not every embodiment may contain only a single embodiment, and such description is for clarity only, and those skilled in the art should integrate the description, and the embodiments may be combined as appropriate to form other embodiments understood by those skilled in the art.
Claims (7)
1. A five-rotor unmanned aerial vehicle with a tail rotor type, folding and oil-electricity hybrid power comprises a five-rotor unmanned aerial vehicle frame (1) and an oil-electricity hybrid power system (2); the oil-electricity hybrid power system (2) is arranged on the five-rotor unmanned aerial vehicle frame (1) and is characterized in that,
the five-rotor unmanned aerial vehicle frame (1) comprises a framework type undercarriage (1-1), first electric rotor supporting rods (1-3), a power generation transmission system mounting frame (1-4) and composite supporting rods (1-5), wherein three groups of the first electric rotor supporting rods (1-3) are arranged and circumferentially mounted on the power generation transmission system mounting frame (1-4) together with the composite supporting rods (1-5), and the framework type undercarriage (1-1) is mounted at the lower end of the power generation transmission system mounting frame (1-4) through a plug engine mounting frame (1-2);
oil-electricity hybrid power system (2) include electronic rotor (2-1), horizontal bar piston engine (2-3), power battery (2-4), electricity generation belt transmission system (2-7) and main rotor (2-8), electronic rotor (2-1) and main rotor (2-8) all install on five rotor unmanned vehicles frame (1) and by installing horizontal bar piston engine (2-3) drive rotation at five rotor unmanned vehicles frame (1) through piston engine mounting bracket (1-2), horizontal bar piston engine (2-3) are connected with power battery (2-4) electricity of installing on stopper engine mounting bracket (1-2), and power battery (2-4) still are connected with generator (2-5) electricity, generator (2-5) are through electricity generation belt transmission system (2-7) and main rotor (2-4) -8) is rotationally connected.
2. The tailed, folded, hybrid-electric-oil five-rotor unmanned aerial vehicle of claim 1, wherein a voltage regulator rectifier (2-2) is electrically connected to the horizontal rod piston engine (2-3).
3. The tailed, folded, hybrid-electric-gasoline five-rotor unmanned aerial vehicle of claim 1, wherein the first electric rotor support rod (1-3) and the composite support rod (1-5) are respectively provided with an electric rotor (2-1).
4. The tailed, folded, hybrid-electric-oil-and-electric-hybrid unmanned aerial vehicle as claimed in claim 3, wherein the first electric rotor support rod (1-3) comprises an end fixing rod (1-3-1) and a folding rod (1-3-4), one end side of the end fixing rod (1-3-1) is rotatably connected with the folding rod (1-3-4) through a folding rotating shaft (1-3-3), and the side of the end fixing rod (1-3-1) far away from the folding rotating shaft (1-3-3) is fixedly connected with the folding rod (1-3-4) through a fixing screw (1-3-2).
5. The unmanned aircraft with the tail rotor type, the folding function and the oil-electric hybrid power is characterized in that the electric rotor (2-1) comprises a motor base (1-3-6), a brushless direct current motor (1-3-7) and a rotor (1-3-8), the rotor (1-3-8) is installed on an output shaft of the brushless direct current motor (1-3-7), the brushless direct current motor (1-3-7) is fixedly connected with the folding rod (1-3-4) through the motor base (1-3-6), and the brushless direct current motor (1-3-7) is electrically connected with a power battery (2-4) through an electric regulator (1-3-5).
6. The tailed, folded, hybrid-electric-gasoline five-rotor unmanned aerial vehicle according to claim 1, wherein the composite support rods (1-5) comprise second electric rotor support rods (1-5-1), hexagonal rods (1-5-2) and electric tailrotors (2-6), one end of each second electric rotor support rod (1-5-1) is fixed on the power generation transmission system mounting frame (1-4), the other end of each second electric rotor support rod is connected with the hexagonal rod (1-5-2) in an inserting mode, and the electric tailrotors (2-6) are installed at one ends, far away from the second electric rotor support rods (1-5-1), of the hexagonal rods (1-5-2) and are arranged perpendicular to the hexagonal rods (1-5-2).
7. The unmanned aircraft with the tail rotor, the folding function and the hybrid power of oil and electricity, as claimed in claim 6, wherein the electric tail rotor (2-6) comprises a tail rotor (1-5-3), a tail rotor motor (1-5-4) and a tail rotor motor base (1-5-5), the tail rotor motor (1-5-4) is mounted on the hexagonal rod (1-5-2) through the tail rotor motor base (1-5-5), and the output shaft of the tail rotor motor base (1-5-5) is fixedly connected with the tail rotor (1-5-3).
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920783809.4U CN210310866U (en) | 2019-05-28 | 2019-05-28 | Take propeller type, folding, five rotor unmanned vehicles of oil-electricity hybrid |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201920783809.4U CN210310866U (en) | 2019-05-28 | 2019-05-28 | Take propeller type, folding, five rotor unmanned vehicles of oil-electricity hybrid |
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| CN210310866U true CN210310866U (en) | 2020-04-14 |
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| CN201920783809.4U Active CN210310866U (en) | 2019-05-28 | 2019-05-28 | Take propeller type, folding, five rotor unmanned vehicles of oil-electricity hybrid |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110077582A (en) * | 2019-05-28 | 2019-08-02 | 江苏航空职业技术学院 | A kind of magnetic tape trailer paddle, folding, five rotor unmanned aircraft of oil electric mixed dynamic |
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2019
- 2019-05-28 CN CN201920783809.4U patent/CN210310866U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110077582A (en) * | 2019-05-28 | 2019-08-02 | 江苏航空职业技术学院 | A kind of magnetic tape trailer paddle, folding, five rotor unmanned aircraft of oil electric mixed dynamic |
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