CN212172552U - Centrifugal clutch type hybrid power propulsion device of vertical take-off and landing fixed wing unmanned aerial vehicle - Google Patents
Centrifugal clutch type hybrid power propulsion device of vertical take-off and landing fixed wing unmanned aerial vehicle Download PDFInfo
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- CN212172552U CN212172552U CN202020685204.4U CN202020685204U CN212172552U CN 212172552 U CN212172552 U CN 212172552U CN 202020685204 U CN202020685204 U CN 202020685204U CN 212172552 U CN212172552 U CN 212172552U
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Abstract
The utility model discloses a VTOL fixed wing unmanned aerial vehicle centrifugation separation and reunion formula hybrid propulsion unit, including power unit and screw, power unit includes: the centrifugal; the output shaft of the engine is connected with a centrifugal throwing block through a connecting sleeve, and the centrifugal throwing block is positioned in a cover body of a clutch outer cover of the generator. The utility model discloses a power advancing device has higher security and reliability, can effectively solve VTOL fixed wing unmanned aerial vehicle and cruise various problems that the flight in-process engine fault brought, avoids unmanned aerial vehicle to lose the power of advancing and the flight accident that causes.
Description
Technical Field
The utility model relates to an unmanned aerial vehicle power supply device field specifically is a vertical take-off and landing fixed wing is centrifugal separation and reunion formula hybrid propulsion device for unmanned aerial vehicle.
Background
With the continuous maturity of the theory systems related to the unmanned aerial vehicle field such as stator information technology, communication technology, aircraft design, unmanned aerial vehicle has obtained rapid development and perfect in recent years. The flight chess represented by the unmanned aerial vehicle is widely used in various industries, and is generally applied to various fields such as agriculture, breeding industry, express transportation, disaster relief, surveying and mapping and the like at present.
In the numerous classifications of unmanned aerial vehicles, the VTOL fixed wing unmanned aerial vehicle receives numerous users 'hotmelt because of having fused advantages such as the fixed wing unmanned aerial vehicle's voyage is far away, duration is long, fast and convenient take off and land, from this VTOL fixed wing unmanned aerial vehicle uses comparatively generally and has also obtained certain development in recent years at present. However, the vertical take-off and landing fixed wing unmanned aerial vehicle has the following problems in the use process: during the process of cruising and flying of the vertical take-off and landing fixed wing unmanned aerial vehicle, if the engine is flamed out due to some unexpected reasons, the unmanned aerial vehicle often loses the advancing power and causes a flight accident, and thus great economic loss is caused.
The invention patent with application number 2014103392669 discloses a double-engine four-shaft four-propeller unmanned aerial vehicle, which comprises a body, a power transmission device and a propeller assembly; the power transmission device is fixed on the machine body and connected with the propeller assembly, and the propeller assembly comprises a steering engine, a propeller clamp, a variable pitch control arm, a variable pitch sliding block, a variable pitch rod, a variable pitch propeller and a propeller clamp base; each propeller clamp base is provided with two propeller clamps, the two propeller clamps are symmetrically arranged left and right along the section of the center of the propeller clamp base, the propeller clamps rotate along the shaft of the propeller clamp base, the propeller clamps are hinged with one end of a variable-pitch rod through a hinge chain and freely rotate by taking a hinge hole as a circle center, a variable-pitch sliding block is sleeved on the propeller rotation input shaft, moves up and down along the axis of the propeller rotation input shaft and is rigidly connected with the other end of the variable-pitch rod to drive the variable-pitch rod to move up and down and further drive the propeller clamps to rotate along the shaft of the propeller clamp base, one end of a variable-pitch control arm is connected with the variable-pitch sliding block, and the other end of the variable-pitch control arm is connected with a steering engine to drive the variable-pitch sliding block to move; the power transmission device comprises a first engine, a second engine, an upper input gear, a lower input gear, an upper output gear, a lower output gear, a central shaft and a gearbox; the first engine drives the upper input gear, the second engine drives the lower input gear, the upper input gear and the lower input gear are overlapped up and down and coaxial with the central shaft, the upper output gear is meshed with the upper input gear, the lower output gear is meshed with the lower input gear, and the upper output gear and the lower output gear are connected with the propeller rotation input shaft of the propeller assembly through the gearbox. When one engine fails, the attitude of the airplane can be basically maintained by improving the power of the other engine, the safe landing is realized, and the reliability is high. But the power system cannot be applied to the fixed-wing unmanned plane for vertical take-off and landing.
Disclosure of Invention
For solving the deficiencies of the prior art, the utility model aims to provide a: the centrifugal clutch type hybrid power propulsion device is suitable for the vertical take-off and landing fixed wing unmanned aerial vehicle.
In order to solve the above problem, the technical scheme of the utility model is so realized:
the utility model provides a VTOL fixed wing unmanned aerial vehicle centrifugation separation and reunion formula hybrid propulsion unit, includes power unit and screw, power unit includes: the centrifugal pump comprises a battery, an engine, a generator, a clutch outer cover, a connecting sleeve and a centrifugal throwing block, wherein the battery is connected with the generator through a wire, the clutch outer cover is connected with one end of a generator rotor, and the propeller is fixedly connected with the other end of the generator rotor; the output shaft of the engine is connected with a centrifugal throwing block through a connecting sleeve, and the centrifugal throwing block is positioned in a cover body of a clutch outer cover of the generator.
Preferably, the engine and the generator are coaxially arranged right below the propeller, so that even if the engine fails, the body is still in a reliable balance state under the action of the gravity center, and the flying attitude is not influenced.
Preferably, a plurality of mounting holes are formed in the engine, an engine support rod is mounted in the mounting holes, and the engine support rod is fixedly connected with a stator of the generator.
More preferably, the number of the mounting holes is 4, and the mounting holes are vertically arranged on the peripheral wall of the engine shell at equal intervals and correspond to the position of the generator rotor.
Still preferably, the electric energy output end of the generator is connected with a battery, the battery is a lithium battery, and the output end of the battery is provided with an anti-ignition plug with the model number AS 150.
More preferably, the aforementioned engine is an aircraft engine.
Still further preferably, a connecting hole for connecting an output shaft of the engine is formed in the center of the connecting sleeve, a pair of symmetrically arranged connecting caps are arranged on two sides of the connecting hole, and the connecting caps are fixedly connected with the centrifugal thrower.
Still further preferably, the centrifugal throwing block comprises a first throwing block and a second throwing block which are identical in structure, a through hole is formed in each of the first throwing block and the second throwing block, a spring is connected between the two through holes, and mounting structures matched with the connecting caps are formed on the first throwing block and the second throwing block respectively.
Still further preferably, when the centrifugal thrower is in a contracted state, the spring is in an original length, and when the engine rotates at a high speed, the centrifugal thrower is opened due to the centrifugal force, and the spring is in an extended state.
The utility model has the advantages that:
(1) in the hybrid propulsion device of the utility model, the engine and the generator are coaxially stacked under the propeller, so that the center of gravity of the whole power system is positioned on the central line of the propeller, and when the engine breaks down, the flying posture of the unmanned aerial vehicle is not influenced at all, thereby having higher safety and reliability;
(2) the utility model discloses a hybrid propulsion device is centrifugal separation and reunion formula driving system, and when the unmanned aerial vehicle initial state of taking off, when the engine was in the idle state, the centrifugation flail piece was in the shrink state, did not contact with the inner wall of clutch dustcoat, supplied power through the battery this moment, and the operating condition of generator becomes the motor, and output mechanical energy provides the thrust that advances in the flight process for the screw, can make unmanned aerial vehicle's start-up faster like this, and real-time response nature is better;
(3) when unmanned aerial vehicle when the flight cruises, the engine is in middle and high speed operation, the first flail block and the second flail block that lead to centrifugal flail block owing to the effect of centrifugal force are in open detached state under the high-speed rotatory condition, transmit mechanical energy and charge for the battery on the generator rotor when providing power for the screw, and in case the engine trouble, the battery can be at once for the generator anti-charging, become the operating condition of generator once more the motor, can effectively solve the fixed wing unmanned aerial vehicle of VTOL and cruise various problems that the flight in-process engine trouble brought cruises, avoid unmanned aerial vehicle to lose the power that gos forward and the flight accident that causes.
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 these drawings without creative efforts.
Fig. 1 is a schematic perspective view of a centrifugal clutch type hybrid propulsion unit of a vertical take-off and landing fixed wing drone according to an embodiment of the present invention;
FIG. 2 is an exploded view of the embodiment of FIG. 1;
FIG. 3 is an exploded view of the embodiment of FIG. 1 from another perspective;
FIG. 4 is a front view of the embodiment shown in FIG. 1;
FIG. 5 is a top view of the embodiment shown in FIG. 1;
fig. 6 is a partially enlarged schematic view of fig. 2.
The meaning of the reference symbols in the figures: 1. the centrifugal.
Detailed Description
The present invention will be described in detail with reference to the accompanying drawings and specific embodiments.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are used merely for convenience of description and for simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be construed as limiting the present invention. Furthermore, the terms "first" and "second" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
Please refer to fig. 1 to 5, the propulsion device of the present invention is suitable for a vertical take-off and landing fixed wing drone, including a power mechanism and a propeller 11, wherein the power mechanism adopts a centrifugal clutch type hybrid power mode, including: the centrifugal pump comprises a battery 12, an engine 1, a generator 9, a clutch housing 7, a connecting sleeve 5 and a centrifugal throwing block 6, wherein the battery 12 is preferably a lithium battery and is connected with the generator 9 through a wire, namely, an electric energy output end of the generator 9 is connected with the battery 12, the specific connection mode is that a V + terminal of an electric energy output terminal of the generator 9 is connected with a positive electrode of the battery 12, and a V-terminal of the electric energy output terminal of the generator 9 is connected with a negative electrode of the battery 12. To improve safety, the output of the battery 12 is provided with an anti-sparking plug of type AS 150.
It should be noted that the engine 1 and the generator 9 are coaxially installed right below the propeller 11, so that even if the engine 1 fails, the body is still in a reliable balance state under the action of the center of gravity, and the flight attitude is not affected.
As shown in fig. 1 and 2, the clutch housing 7 is connected to one end of the generator rotor 10, and the propeller 11 is fixedly connected to the other end of the generator rotor 10; an output shaft 4 of the engine 1 is connected with a centrifugal throw block 6 through a connecting sleeve 5, and the centrifugal throw block 6 is positioned in a cover body of a clutch outer cover 7 of a generator 9. Therefore, in the process of cruising and flying of the vertical take-off and landing fixed wing, the engine 1 provides power in a normal medium-high speed running state and simultaneously charges the battery 12, and in an idling state or when the engine 1 fails and stops working to cause the unmanned aerial vehicle to lose forward power, the battery 12 provides electric energy to the generator 9 in time, so that the generator 9 is in a motor working state to drive the propeller 11 to continuously provide forward thrust.
In order to assemble the engine 1 and the generator 9 into an integral power propulsion device with a compact structure, a plurality of mounting holes 2 are formed on the engine 1, an engine support rod 3 is mounted in each mounting hole 2, and the engine support rod 3 is fixedly connected with a stator 8 of the generator 9. Preferably, the number of the mounting holes 2 is 4, and the mounting holes are vertically arranged on the peripheral wall of the casing of the engine 1 at equal intervals and at positions corresponding to the generator rotor 10.
Specifically, as shown in fig. 6, a connection hole 501 for connecting the output shaft 4 of the engine 1 is formed in the center of the connection sleeve 5, a pair of symmetrically arranged connection caps 502 are disposed on both sides of the connection hole 501, and the connection caps 502 are fixedly connected with the centrifugal thrower 6. The centrifugal throwing block 6 comprises a first throwing block 601 and a second throwing block 602 which have identical structures, a through hole 603 is formed in each of the first throwing block and the second throwing block, a spring 604 is connected between the two through holes 603, and mounting structures matched with the connecting cap 502 are formed on the first throwing block 601 and the second throwing block 602 respectively.
When the centrifugal swing block 6 is in a contracted state, the spring 604 is in the original length; . When the engine 1 of the unmanned aerial vehicle runs at a medium-high speed, the centrifugal throwing block 6 is separated and opened under the action of centrifugal force, the first throwing block 601 and the second throwing block 602 are tightly attached to the inner wall of the clutch outer cover 7, and the spring 604 is in an extending state at the moment.
The utility model discloses a propulsion unit's theory of operation does: when the engine 1 is in an idling state, the centrifugal thrower 6 is in a contracted state and is not in contact with the inner wall of the clutch outer cover 7, power is supplied through the battery 12 at the moment, the working state of the generator 9 is changed into a motor, and mechanical energy is output to provide forward thrust for the propeller 11 in the flying process; when the engine 1 is in a medium-high speed running state, under the condition of high-speed rotation, the centrifugal throwing block 6 is in contact with the inner wall surface of the clutch outer cover 7 under the action of centrifugal force to transmit torque, the transmitted torque is transmitted to the generator rotor 10 through the clutch outer cover 7, the generator rotor 10 drives the propeller 11 to rotate, the engine 1 directly provides forward thrust required by the unmanned aerial vehicle, and the generator 9 is in a power generation working state and charges the battery 12 at the same time.
To sum up, the utility model discloses a hybrid propulsion unit is applicable to VTOL fixed wing unmanned aerial vehicle, has higher security and reliability, adopts the two dynamical systems of centrifugal separation and reunion formula of engine 1 and generator 9 for make unmanned aerial vehicle's start-up faster, real-time response nature is better, can effectively solve VTOL fixed wing unmanned aerial vehicle at the various problems that the flight in-process engine 1 trouble of cruising brought, avoid unmanned aerial vehicle to lose the flight accident that advances power and cause.
In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art.
In the description herein, references to the description of the term "one embodiment," "some embodiments," "an example," "a specific example," or "some examples," etc., mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, the schematic representations of the terms used above do not necessarily refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.
The foregoing illustrates and describes the principles, general features, and advantages of the present invention. It should be understood by those skilled in the art that the above embodiments do not limit the present invention in any way, and all technical solutions obtained by adopting equivalent replacement or equivalent transformation fall within the protection scope of the present invention.
Claims (9)
1. The utility model provides a VTOL fixed wing unmanned aerial vehicle centrifugation separation and reunion formula hybrid advancing device, includes power unit and screw, its characterized in that, power unit includes: the centrifugal pump comprises a battery, an engine, a generator, a clutch outer cover, a connecting sleeve and a centrifugal throwing block, wherein the battery is connected with the generator through a wire, the clutch outer cover is connected with one end of a generator rotor, and the propeller is fixedly connected with the other end of the generator rotor; the output shaft of the engine is connected with a centrifugal throwing block through a connecting sleeve, and the centrifugal throwing block is positioned in a cover body of a clutch outer cover of the generator.
2. The vertical take-off and landing fixed wing drone centrifugal clutch type hybrid propulsion device according to claim 1, characterized in that the engine and generator are mounted coaxially right under the propeller.
3. The centrifugal clutch type hybrid propulsion device for VTOL fixed wing UAVs according to claim 1, wherein the engine is formed with a plurality of mounting holes, and the mounting holes are internally provided with engine support rods, and the engine support rods are fixedly connected with the stator of the generator.
4. The centrifugal clutch type hybrid propulsion device for VTOL fixed wing UAVs according to claim 3, wherein the number of said mounting holes is 4, and the mounting holes are vertically arranged on the peripheral wall of the engine housing at equal intervals and corresponding to the rotor of the generator.
5. The centrifugal clutch type hybrid propulsion device for VTOL fixed wing UAVs according to claim 1, wherein the power output end of the generator is connected with a battery, the battery is a lithium battery, and the output end of the battery is provided with an anti-sparking plug with model AS 150.
6. The vertical take-off and landing fixed wing drone centrifugal clutch type hybrid propulsion device according to claim 1, wherein the engine is an aircraft engine.
7. The centrifugal clutch type hybrid propulsion device of the VTOL fixed wing UAV (unmanned aerial vehicle) according to any one of claims 1-6, wherein a connecting hole for connecting an engine output shaft is formed at the center of the connecting sleeve, a pair of symmetrically arranged connecting caps are arranged at two sides of the connecting hole, and the connecting caps are fixedly connected with the centrifugal thrower.
8. The vertical take-off and landing fixed wing unmanned aerial vehicle centrifugal clutch type hybrid propulsion device of claim 7, wherein the centrifugal throwing block comprises a first throwing block and a second throwing block which are identical in structure, a through hole is formed in each throwing block, a spring is connected between the two through holes, and mounting structures matched with the connecting caps are formed on the first throwing block and the second throwing block respectively.
9. The vertical take-off and landing fixed wing drone centrifugal clutch type hybrid propulsion device of claim 8, wherein the spring is at original length when the centrifugal flail block is in a contracted state.
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113074050A (en) * | 2021-04-08 | 2021-07-06 | 安徽砺德特种动力科技有限公司 | Electric injection engine and engine for unmanned aerial vehicle |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113074050A (en) * | 2021-04-08 | 2021-07-06 | 安徽砺德特种动力科技有限公司 | Electric injection engine and engine for unmanned aerial vehicle |
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