CN113928550B - Aircraft with a plurality of aircraft body - Google Patents
Aircraft with a plurality of aircraft body Download PDFInfo
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- CN113928550B CN113928550B CN202111428620.1A CN202111428620A CN113928550B CN 113928550 B CN113928550 B CN 113928550B CN 202111428620 A CN202111428620 A CN 202111428620A CN 113928550 B CN113928550 B CN 113928550B
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- power supply
- paddle
- piezoelectric
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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
- B64C27/20—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
- B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02N—ELECTRIC MACHINES NOT OTHERWISE PROVIDED FOR
- H02N2/00—Electric machines in general using piezoelectric effect, electrostriction or magnetostriction
- H02N2/18—Electric machines in general using piezoelectric effect, electrostriction or magnetostriction producing electrical output from mechanical input, e.g. generators
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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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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- General Electrical Machinery Utilizing Piezoelectricity, Electrostriction Or Magnetostriction (AREA)
Abstract
The invention discloses an aircraft, which comprises a fuselage, a paddle cover, paddles and piezoelectric plates, wherein the fuselage is provided with a plurality of piezoelectric plates; wherein the machine body comprises an electric control assembly; the paddle cover is arranged at the top of the machine body; the blade is arranged in the blade cover, is in transmission connection with the electric control assembly and is used for rotating under the drive of the electric control assembly so as to provide power for the flight of the airframe; the piezoelectric sheet is provided with a fixed end and a free end which are arranged back to back, and the fixed end is fixed on one side of the paddle cover, which is back to the machine body, and is electrically connected with the electric control assembly. The technical scheme of the invention can improve the endurance of the aircraft.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to an aircraft.
Background
With the rapid development of aircraft technology, aircraft have completed a transition from military to civilian use. Moreover, with the continuous fusion of the aircraft technology and the security technology, the aircraft is increasingly penetrated into the security industry, and has important application in various scenes such as emergency rescue, digital city construction, smart city construction, forest fire prevention monitoring, frontier defense monitoring, military reconnaissance, police condition fire control monitoring and the like. However, the cruising ability of the aircraft is very worry, and the situation that the electric quantity is exhausted and crashes in the flying process often occurs.
Disclosure of Invention
The invention mainly aims to provide an aircraft, which aims to improve the endurance of the aircraft.
An embodiment of the present invention proposes an aircraft comprising:
the device comprises a body, a control module and a control module, wherein the body comprises an electric control assembly;
the paddle cover is arranged at the top of the machine body;
the blade is arranged in the blade cover, is in transmission connection with the electric control assembly and is used for rotating under the drive of the electric control assembly so as to provide power for the flight of the fuselage; and
the piezoelectric sheet is provided with a fixed end and a free end which are arranged back to back, and the fixed end is fixed on one side of the paddle cover, which is back to the machine body, and is electrically connected with the electric control assembly.
In an embodiment of the invention, a flow blocking blunt body is convexly arranged on a side surface of the paddle cover, which is opposite to the main body, at a central axis of the paddle cover, the fixed end is fixed on a side wall of the flow blocking blunt body, and the free end extends outwards along a radial direction of the paddle cover.
In an embodiment of the present invention, an end of the flow blocking blunt body, which is close to the paddle cover, is cylindrical, and the fixed end is fixed on a side wall of the cylindrical end of the flow blocking blunt body.
In an embodiment of the invention, the surface of the piezoelectric patch is arranged in the axial direction of the paddle cover.
In an embodiment of the present invention, the piezoelectric sheets are disposed in a plurality of piezoelectric sheets at intervals along a circumferential direction of the flow-blocking blunt body.
In an embodiment of the present invention, the electric control assembly includes a driving assembly and a power supply, wherein the power supply is electrically connected to the driving assembly, and the driving assembly is in transmission connection with the blade so as to drive the blade;
the aircraft further comprises an auxiliary power supply, wherein the auxiliary power supply is electrically connected with the driving assembly and the piezoelectric sheet, and the piezoelectric sheet is used for charging the auxiliary power supply.
In an embodiment of the invention, a mounting column is convexly arranged on the surface of one side of the paddle cover, which is opposite to the machine body, the fixed end is fixed on the side wall of the mounting column, a mounting cavity is formed in the mounting column, and the auxiliary power supply is arranged in the mounting cavity.
In an embodiment of the invention, the installation cavity is communicated with the inner cavity of the paddle cover, a power transmission wire is led out from one end of the auxiliary power supply, which faces the paddle cover, and the power transmission wire enters the inner cavity of the paddle cover, enters the machine body after bypassing the movement range of the paddle, and is electrically connected with the driving assembly.
In an embodiment of the invention, the paddle cover comprises:
the two ends of the cylinder body are opened;
the fixed ring is arranged at one end of the cylinder part, which is opposite to the machine body, and the flow blocking blunt body is convexly arranged on one side surface of the fixed ring, which is opposite to the machine body;
the connecting ribs are radially distributed between the outer side wall of the fixed ring and the inner side wall of the barrel part to connect the barrel part and the fixed ring; and
the supporting beams are radially distributed in one end of the cylinder part, which faces the machine body, the inner ends of the supporting beams are connected with each other, the outer ends of the supporting beams are connected to the inner side wall of the cylinder part, the supporting beams are connected with the machine body, and the output shaft of the driving assembly penetrates into the inner cavity of the paddle cover from the connection part of the inner ends of the supporting beams and is connected with the paddles so as to drive the paddles to rotate;
the power transmission wires penetrate into the inner cavity of the paddle cover through the middle opening of the fixing ring, are routed to the inner side wall of the cylinder body along one connecting rib, and then are routed to the machine body along one supporting beam to enter the machine body.
In an embodiment of the present invention, a plurality of fixing buckles are sequentially arranged along the routing direction, for clamping the power transmission wires, along the connecting ribs, the supporting beams and the inner side wall of the barrel; or a wire slot is formed along the wiring direction and is used for clamping the power transmission wire.
In one embodiment of the present invention, the piezoelectric sheet is a polyvinylidene fluoride piezoelectric sheet.
According to the technical scheme, the piezoelectric sheet which is electrically connected with the electric control component in the machine body is arranged on one side of the paddle cover, which is opposite to the machine body. Thus, during the flight of the aircraft, the piezoelectric sheet will swing under the action of the air flow, and the swing will deform the piezoelectric sheet (at this time, there is a compressed portion and also a stretched portion on the piezoelectric sheet 40), so as to promote the generation of the piezoelectric signal; after the piezoelectric signal is generated, it can be directed to an electronic control assembly for use as a power supply for driving the blade in rotation or for other electrical components in the aircraft. Therefore, wind energy can be captured in the flight process of the aircraft, so that power generation is realized, extra electric energy supply is realized, the rapid consumption of the power supply of the aircraft is relieved, and the cruising ability of the aircraft is improved.
Moreover, if the piezoelectric plate is placed at the position of the machine body, downward airflow generated by the blade will greatly interfere with the piezoelectric plate, thereby being unfavorable for capturing wind energy. If the piezoelectric sheet is placed around the paddle cover, the volume of the aircraft can be increased, and the probability of dangers such as winding and the like can be greatly increased. Thus, the present invention optimizes placement on top of the paddle cover, both in terms of safety and captured energy efficiency.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are required in the embodiments or the description of the prior art will be briefly described, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and other drawings may be obtained according to the structures shown in these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic structural view of an embodiment of an aircraft of the present invention;
FIG. 2 is a schematic cross-sectional view of the aircraft of FIG. 1;
fig. 3 is a schematic view of the aircraft of fig. 1 in a cross-sectional configuration from another perspective.
Reference numerals illustrate:
| reference numerals | Name of the name | Reference numerals | Name of the name |
| 100 | Aircraft with a plurality of aircraft body | 23 | Connecting rib |
| 10 | Fuselage body | 24 | Supporting beam |
| 11 | Outer casing | 30 | Blade |
| 12 | Power supply | 40 | Piezoelectric sheet |
| 13 | Circuit board | 40a | Connecting wire |
| 14 | Driving assembly | 50 | Flow-blocking blunt body |
| 20 | Paddle cover | 50a | Mounting cavity |
| 21 | Barrel part | 60 | Auxiliary power supply |
| 22 | Fixing ring | 60a | Power transmission wire |
The achievement of the objects, functional features and advantages of the present invention will be further described with reference to the accompanying drawings, in conjunction with the embodiments.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and fully with reference to the accompanying drawings, in which it is evident that the embodiments described are only some, but not all embodiments of the invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
It should be noted that all directional indicators (such as up, down, left, right, front, and rear … …) in the embodiments of the present invention are merely used to explain the relative positional relationship, movement, etc. between the components in a particular posture (as shown in the drawings), and if the particular posture is changed, the directional indicator is changed accordingly.
Furthermore, descriptions such as those referred to as "first," "second," and the like, are provided for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implying an order of magnitude of the indicated technical features in the present disclosure. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include at least one such feature. In the description of the present invention, the meaning of "a plurality", "a number" or "a plurality" is at least two, such as two, three, etc., unless specifically defined otherwise.
In the present invention, unless specifically stated and limited otherwise, the terms "connected," "affixed," and the like are to be construed broadly, and for example, "affixed" may be a fixed connection, a removable connection, or an integral body; can be mechanically or electrically connected; either directly or indirectly, through intermediaries, or both, may be in communication with each other or in interaction with each other, unless expressly defined otherwise. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art according to the specific circumstances.
In addition, the technical solutions of the embodiments of the present invention may be combined with each other, but it is necessary to be based on the fact that those skilled in the art can implement the technical solutions, and when the technical solutions are contradictory or cannot be implemented, the combination of the technical solutions should be considered as not existing, and not falling within the scope of protection claimed by the present invention.
Aiming at the technical problems reflected by the background technology, the invention provides an aircraft, and aims to improve the cruising ability of the aircraft.
The specific structure of the aircraft according to the invention will be described in the following in the specific embodiments, and by way of example of the horizontal placement of the aircraft:
as shown in fig. 1 to 3, in an embodiment of the present invention, the aircraft 100 includes:
a body 10, the body 10 comprising an electrical control assembly;
a paddle cover 20, wherein the paddle cover 20 is arranged on the top of the machine body 10;
the paddle 30 is arranged in the paddle cover 20 and is in transmission connection with the electric control assembly, and is used for rotating under the drive of the electric control assembly so as to provide power for the flight of the airframe 10; and
the piezoelectric sheet 40 is provided with a fixed end and a free end which are arranged back to back, and the fixed end is fixed on one side of the paddle cover 20, which is opposite to the body 10, and is electrically connected with the electric control assembly.
Specifically, the body 10 includes a housing 11, a power supply 12, a circuit board 13, a driving assembly 14, and the like; the power supply 12 and the circuit board 13 are both accommodated in the housing 11, and the driving assembly 14 is at least partially accommodated in the housing 11. It will be appreciated that the power supply 12, the circuit board 13, and the drive assembly 14 constitute an electrical control assembly in this embodiment; wherein the power supply 12 is electrically connected to the circuit board 13 to supply power to the electrical components (e.g., the driving assembly 14) on the aircraft 100 through the circuit board 13; the driving assembly 14 is also electrically connected to the circuit board 13, so as to obtain the electric energy provided by the power supply 12 through the circuit board 13. Of course, in other embodiments, the electrical control assembly may also include more or fewer electrical components. In addition, the body 10 may further include other components, such as a camera, a speaker, a microphone, a radar, etc., to meet the requirements of different application scenarios.
The paddle cover 20 is approximately in a disc-shaped structure (of course, in other embodiments, the outline of the cross section of the paddle cover 20 can be in other shapes, such as triangle, square, rectangle, ellipse, diamond, etc.), and has a bottom surface and a top surface which are arranged back to back, the top surface of the paddle cover 20 is provided with an air inlet which is communicated with the inner cavity of the paddle cover 20, and the bottom surface of the paddle cover 20 is provided with an air outlet which is communicated with the inner cavity of the paddle cover 20; at this time, the top of the machine body 10 is opposite to and fixedly connected with the central area of the bottom surface of the paddle cover 20, and the output shaft of the driving assembly 14 positioned at the top of the machine body 10 penetrates into the inner cavity of the paddle cover 20 from the bottom surface of the paddle cover 20; at this time, the blade 30 is also received in the interior cavity of the blade housing 20 and fixedly coupled to the output shaft of the drive assembly 14.
Thus, when the drive assembly 14 is in operation, the paddles 30 are rotated by the drive assembly 14; at this time, the air flow may flow into the inner cavity of the blade cover 20 from the air inlet at the top surface of the blade cover 20 and flow out from the air outlet at the bottom surface of the blade cover 20 after acting with the blade 30, so as to provide lifting force for the blade 30, thereby providing power for the flight of the fuselage 10. Also, it will be appreciated that when the drive assembly 14 is controlling its output shaft at an angle to vertical, the plane of rotation of the paddles 30 is no longer horizontal, but will be inclined at an angle, thereby controlling the direction of travel of the fuselage 10 in the horizontal direction.
Further, in the technical solution of this embodiment, a piezoelectric plate 40 electrically connected to the electrical control component in the machine body 10 is further disposed on a side of the paddle cover 20 facing away from the machine body 10. Thus, during the flight of the aircraft 100, the piezoelectric sheet 40 will swing under the action of the airflow, and the swing will deform the piezoelectric sheet 40 (at this time, there is a compressed portion and also a stretched portion on the piezoelectric sheet 40), so as to promote the generation of the piezoelectric signal; after generation, the piezoelectric signals may be directed to an electronic control assembly for use as a power supply for driving the rotation of the blade or other electrical components in the aircraft 100. In this way, wind energy can be captured during the flight of the aircraft 100 to realize "power generation" and additional power supply, thereby alleviating the rapid consumption of the power supply 12 of the aircraft 100 itself and improving the cruising ability of the aircraft 100.
Moreover, if the piezoelectric sheet 40 is placed at the position of the body 10, the downward airflow generated by the blade 30 will greatly interfere with the piezoelectric sheet 40, thereby adversely affecting the capture of wind energy. If the piezoelectric sheet 40 is placed around the paddle cover 20, the volume of the aircraft 100 will be increased, and the probability of risk of entanglement will be greatly increased. Thus, the present embodiment optimally places it on top of the paddle cover 20, both in terms of safety and captured energy efficiency.
In addition, the piezoelectric sheet 40 may be a flexible piezoelectric sheet such as a polyvinylidene fluoride piezoelectric sheet (also referred to as PVDF piezoelectric sheet) or a lead zirconate titanate flexible piezoelectric sheet (also referred to as PZT flexible piezoelectric sheet), so as to facilitate the oscillation thereof under the action of air flow to generate a piezoelectric signal. Also, it will be appreciated that the piezoelectric patch 40 employed in the present embodiment does not act as a sensor, but rather utilizes the property of the piezoelectric material on the other hand, i.e., acts as a transducer, to convert wind energy into electrical energy to alleviate the electrical energy "anxiety" of the aircraft 100.
As shown in fig. 1 to 3, in an embodiment of the aircraft 100 according to the present invention, a flow blocking blunt body 50 is protruded on a surface of the side of the blade cover 20 facing away from the fuselage 10 at a central axis of the blade cover 20, the fixed end is fixed on a side wall of the flow blocking blunt body 50, and the free end is extended outwards along a radial direction of the blade cover 20.
In this embodiment, the upper surface of the paddle cover 20 is convexly provided with a flow-blocking blunt body 50; the flow blocking blunt body 50 is located at the center of the blade cover 20 and is disposed coaxially with the blade cover 20 (i.e., the center axis of the flow blocking blunt body 50 coincides with the center axis of the blade cover 20). At this time, the piezoelectric sheet 40 is disposed in the radial direction of the blade cover 20, that is, the longitudinal direction of the piezoelectric sheet 40 coincides with the radial direction of the blade cover 20.
In hydrodynamics, bluff body is also called a bluff body, and refers to a bluff body, such as a cylinder, a sphere, or the like. The blunt body has a large differential pressure resistance which is even overwhelming, and the differential pressure resistance is also called shape resistance because the magnitude of the differential pressure resistance has a great relationship with the shape of the object. In other words, the bluff body is a shape that is rounded at the front and pointed at the back, smooth on the surface, and slightly shaped like a water drop, relative to the streamlined body. An object having such a shape will move in the fluid, and the fluid will follow the contour of the object, with substantially no separation and wake, and thus with minimal resistance. Whereas for bluff bodies, i.e. bluff bodies, flow separation is formed at their boundaries, the rear part generates a broad wake with vortex shedding phenomena (which may be periodic or non-periodic). It will be appreciated, therefore, that in the design of this embodiment, after the airflow passes through the bluff body 50, a karman vortex street is formed behind it; at this time, the piezoelectric patch 40 located behind the bluff body 50 swings under the influence of the karman vortex street to generate an electric current for providing additional electric power for the flight or other electronic devices of the aircraft 100. It can be appreciated that the design of the flow-blocking blunt body 50 and the utilization of karman vortex street greatly improves the efficiency of the piezoelectric patch 40 in capturing wind energy.
As shown in fig. 1 to 3, in an embodiment of the aircraft 100 according to the present invention, an end of the bluff body 50 adjacent to the paddle cover is cylindrical, and the fixed end is fixed to a sidewall of the cylindrical end of the bluff body 50. In this way, the periodic falling-off double-line vortex is formed behind the flow-blocking blunt body 50, and the periodic falling-off double-line vortex is formed, so that the piezoelectric sheet 40 can swing stably, and more wind energy can be captured under the same time and wind power.
Of course, it is understood that in other embodiments, the end of the bluff body 50 proximate the shroud may be prismatic (e.g., triangular prism, quadrangular prism), elliptical prism, etc.
Furthermore, the shape of the end of the flow blocking blunt body 50 remote from the blade cover may be appropriately set according to the actual situation, for example, the setting of the cross-sectional taper in the present embodiment.
As shown in fig. 1 to 3, in an embodiment of the aircraft 100 according to the present invention, the surface of the piezoelectric sheet 40 is disposed along the axial direction of the blade cover 20.
In this embodiment, the central axis of the paddle cover 20 is vertically arranged, the central axis of the flow blocking blunt body 50 is also vertically arranged, and the piezoelectric sheet 40 is also vertically arranged; that is, the piezoelectric sheet 40 is horizontally disposed in the longitudinal direction, and is disposed in the radial direction of the blade cover 20, and the piezoelectric sheet 40 is vertically disposed in the width direction, and is disposed in the axial direction of the blade cover 20.
It can be appreciated that the design of the "axial arrangement of the piezoelectric sheet 40 along the paddle cover 20" in combination with the cylindrical shape of the side wall of the flow blocking blunt body 50 is beneficial to obtaining karman vortex streets perpendicular to the piezoelectric sheet 40 on the plane where the vortex rotation direction is located, so that the karman vortex streets have stronger pushing action on the swinging of the piezoelectric sheet 40, and further the swinging amplitude of the piezoelectric sheet 40 is beneficial to be enhanced, so that more wind energy can be captured under the same time and wind force.
On the other hand, in the design of the present embodiment, the two opposite surfaces of the piezoelectric sheet 40 are both in a vertical state; in this way, the influence of the arrangement of the piezoelectric plates 40 on the vertical airflow circulation can be further reduced, the full action of the blades 30 and the airflow is ensured, and the power of the aircraft 100 is ensured.
As shown in fig. 1 to 3, in an embodiment of the aircraft 100 according to the present invention, a plurality of piezoelectric sheets 40 are disposed at intervals along the circumference of the bluff body 50.
In this manner, the limitations on the flight direction of the aircraft 100 when wind energy is captured by a single piezoelectric patch 40 can be alleviated; that is, the flight direction in which the aircraft 100 can capture wind energy into electric energy through the piezoelectric sheets 40 is widened, the difficulty in capturing wind energy by the aircraft 100 is reduced, and the efficiency in capturing wind energy by the aircraft 100 is improved.
In addition, in the present embodiment, four piezoelectric sheets 40 are provided, and the four piezoelectric sheets 40 are uniformly distributed in the circumferential direction of the flow-blocking blunt body 50; that is, the flow blocking blunt body 50 is provided with one piezoelectric sheet 40 every 90 ° in the circumferential direction. Of course, in other embodiments, more or fewer piezoelectric sheets 40 may be provided, and those skilled in the art may reasonably design according to actual application scenarios, which will not be described herein.
Typically, the number of piezoelectric sheets 40 does not exceed 8 sheets to avoid interference between adjacent two piezoelectric sheets 40.
As shown in fig. 1 to 3, in an embodiment of the aircraft 100 according to the present invention, the electric control assembly includes a driving assembly 14 and a power supply 12, the power supply 12 is electrically connected to the driving assembly 14, and the driving assembly 14 is drivingly connected to the blade 30 to drive the blade 30;
the aircraft 100 further includes a secondary power supply 60, where the secondary power supply 60 is electrically connected to the driving assembly 14 and to the piezoelectric sheet 40, and the piezoelectric sheet 40 is used for charging the secondary power supply 60.
It will be appreciated that under the design of the present embodiment, the aircraft 100 has two power supplies—a power supply 12 and a secondary power supply 60; wherein the power supply 12 can supply electrical energy to the drive assembly 14 and other electrical components in the aircraft 100 via the circuit board 13 to provide electrical energy for the flight power of the aircraft 100 and to provide electrical energy for the operation of the other electrical components in the aircraft 100; the secondary power supply 60 may also supply electrical power to the drive assembly 14 and other electrical components in the aircraft 100 via the circuit board 13 to provide electrical power for the flight power of the aircraft 100 and to provide electrical power for the operation of the other electrical components in the aircraft 100. Regarding the scheduling of the power supply 12 and the secondary power supply 60, this may be achieved by a controller on the circuit board 13, and one possible scheduling scheme is provided below:
when the electric quantity of the power supply 12 is not lower than the lower limit threshold value, the controller turns on the power supply 12 and turns off the auxiliary power supply 60; at this point, power is provided by power supply 12 for the flight power of aircraft 100 and for the operation of other electrical components in aircraft 100. When the electric quantity of the power supply 12 is lower than the lower limit threshold value, the controller turns off the power supply 12 and turns on the auxiliary power supply 60; at this time, the secondary power supply 60 provides power for the flight power of the aircraft 100 and provides power for the operation of other electrical components in the aircraft 100.
In addition, by rationally designing the control logic, other functions can be implemented, such as: the sub power supply 60 charges the power supply 12, etc.;
it can be appreciated that the configuration of the two power supplies not only can ensure the normal operation of the aircraft 100, but also can provide a storage place for the electric energy converted by the piezoelectric patch 40 after capturing the wind energy, thereby being beneficial to ensuring the cruising of the aircraft 100 and realizing the reasonable utilization of the electric energy.
Further, as shown in fig. 1 to 3, in an embodiment of the aircraft 100 according to the present invention, a mounting post is protruding from a surface of a side of the paddle cover 20 facing away from the fuselage 10, the fixed end is fixed on a side wall of the mounting post, a mounting cavity 50a is formed in the mounting post, and the auxiliary power supply 60 is disposed in the mounting cavity 50 a. In this embodiment, the mounting posts are served by the aforementioned flow-blocking bluff body 50.
It can be appreciated that, under the design of the present embodiment, the distance between the piezoelectric sheet 40 and the secondary power supply 60 is shortened, so that the piezoelectric signal in the piezoelectric sheet 40 can be conveniently exported and stored, the long-distance electric energy loss is avoided, and the energy efficiency level of the aircraft 100 is improved.
Note that, the electrical connection between the piezoelectric sheet 40 and the secondary power supply 60 may be achieved at least by:
as shown in fig. 1 to 3, in an embodiment of the aircraft 100 according to the present invention, the fixed end is led with a connection wire 40a, and the connection wire 40a penetrates through the sidewall of the bluff body 50 and enters the installation cavity 50a, and is electrically connected to the auxiliary power supply 60. It will be appreciated that the connecting wire 40a may be a two-core wire, the "two cores" of which communicate with the two extraction electrodes of the piezoelectric patch 40, respectively, to derive the piezoelectric signal.
On the other hand, regarding the electrical connection between the secondary power supply 60 and the driving assembly 14, at least the following manner is adopted:
as shown in fig. 1 to 3, in an embodiment of the aircraft 100 according to the present invention, the installation cavity 50a communicates with the inner cavity of the paddle cover 20, and a power transmission wire 60a is led out from one end of the secondary power supply 60 facing the paddle cover 20, where the power transmission wire 60a enters the inner cavity of the paddle cover 20 and enters the body 10 after bypassing the movement range of the paddle 30, and is electrically connected to the driving assembly 14. In this embodiment, the power transmission wire 60a is electrically connected with the circuit board 13 after entering the machine body 10, and then electrically connected with the driving assembly 14 through the electrical connection relationship between the circuit board 13 and the driving assembly 14. Of course, in other embodiments, the power transmission wire 60a may be directly electrically connected to the driving assembly 14 after entering the main body 10, or electrically connected to the driving assembly 14 through other manners.
It can be understood that the electric connection between the auxiliary power supply 60 and the driving assembly 14 is realized, the interference of the paddles 30 is avoided, the stability and reliability of the paddles 30 during operation are ensured, and the stability and reliability of the electric connection between the auxiliary power supply 60 and the driving assembly 14 are also ensured. Meanwhile, as can be appreciated, the wires are routed in the inner cavity of the paddle cover 20, so that the wires are prevented from being exposed, a certain protection effect can be achieved on the wires, and the reliability of the aircraft 100 is improved.
In addition, in order to further improve the safety of the routing of the power transmission wire 60a, ensure the stability and reliability of the blade 30 during operation, ensure the stability and reliability of the electrical connection between the auxiliary power supply 60 and the driving assembly 14, and further design the routing of the power transmission wire 60a as follows:
as shown in fig. 1 to 3, in an embodiment of the aircraft 100 according to the present invention, the blade cover 20 includes:
a cylindrical body 21, wherein both ends of the cylindrical body 21 are opened;
a fixing ring 22, wherein the fixing ring 22 is arranged at one end of the cylinder 21, which is opposite to the machine body 10, and the flow blocking blunt body 50 is convexly arranged at one side surface of the fixing ring 22, which is opposite to the machine body 10;
a plurality of connecting ribs 23, wherein the connecting ribs 23 are radially distributed between the outer side wall of the fixed ring 22 and the inner side wall of the cylinder 21 to connect the cylinder 21 and the fixed ring 22; and
the supporting beams 24 are radially distributed in one end of the cylinder 21, which faces the machine body 10, the inner ends of the supporting beams 24 are connected with each other, the outer ends of the supporting beams 24 are connected to the inner side wall of the cylinder 21, the supporting beams 24 are connected with the machine body 10, and the output shaft of the driving assembly 14 penetrates into the inner cavity of the blade cover 20 from the connection part of the inner ends of the supporting beams 24 and is connected with the blade 30 to drive the blade 30 to rotate;
the power transmission wire 60a penetrates the inner cavity of the paddle cover 20 from the middle opening of the fixing ring 22, and is routed to the inner side wall of the cylinder 21 along the connecting rib 23, and then is routed to the airframe 10 along the supporting beam 24 to enter the airframe 10.
It can be appreciated that, under the design of the present embodiment, the power transmission wire 60a is equivalent to a line running along the cavity wall of the inner cavity of the paddle cover 20, so that a good supporting effect of the cavity wall of the inner cavity of the paddle cover 20 can be obtained, thereby facilitating the stability of the power transmission wire 60a and avoiding the interference with the paddle 30.
In order to further improve stability of the power transmission wire 60a, a plurality of fixing buckles may be sequentially arranged along the routing direction for clamping the power transmission wire 60a, wherein the connecting ribs 23, the supporting beams 24 and the inner side wall of the cylinder 21 are used for routing; or, a wire slot is formed along the wire direction for clamping the power transmission wire 60a.
In order to improve the convenience of manufacturing the aircraft 100, the flow blocking blunt body 50 may be integrally formed with the blade cover 20 (e.g., an integrally formed structure by injection molding). It will be appreciated that this also facilitates the stability of the bluff body 50, and the formation and stability of the karman vortex street, thereby facilitating the swinging of the piezoelectric patch 40 under the action of the karman vortex street and the generation of piezoelectric signals.
Note that, the connection between the support beam 24 and the body 10 may be a connection between the support beam 24 and the housing 11 of the body 10, and may be realized by, for example, bonding, welding, screw connection, or snap connection.
As shown in fig. 1 to 3, in an embodiment of the aircraft 100 according to the present invention, the piezoelectric sheet 40 is a polyvinylidene fluoride piezoelectric sheet.
A polyvinylidene fluoride piezoelectric sheet (also called as PVDF piezoelectric sheet) is a piezoelectric device using a polyvinylidene fluoride piezoelectric film as a sensitive element, and when the piezoelectric device is subjected to pressure, a piezoelectric signal is generated. The design of the invention is to lead out and collect the piezoelectric signals generated by the pressed polyvinylidene fluoride piezoelectric sheet for the flying of the aircraft 100 or the use of other electric elements in the aircraft 100.
In general, a PVDF piezoelectric sheet is manufactured by encapsulating a PVDF piezoelectric film between two sheets of protective material and reserving an extraction electrode. Wherein, the protective material can be polyimide film (also called PI film), which has excellent high and low temperature resistance, electrical insulation, cohesiveness, radiation resistance, flexibility and the like; and, the PVDF piezoelectric film and the protective material can be bonded by using an adhesive such as epoxy resin.
The PVDF piezoelectric sheet has the advantages of soft texture, light weight, high sensitivity and the like; the PVDF piezoelectric sheet has excellent chemical stability, is superior to piezoelectric ceramic transducers (such as lead zirconate titanate piezoelectric ceramic transducers, also called PZT piezoelectric ceramic transducers), and can be used for a long time below 80 ℃; meanwhile, the frequency response width of the PVDF piezoelectric sheet is 0-500 MHz, and is also superior to that of a piezoelectric ceramic transducer; the elastic compliance coefficient of the PVDF piezoelectric sheet is about 30 times that of the PZT piezoelectric ceramic transducer, and the PVDF piezoelectric sheet is lighter (the relative density is only about 1/4 of that of the PZT piezoelectric ceramic transducer), can support various required complex shapes, is impact resistant and has low price.
In addition, it should be noted that the energy harvesting effect of the PVDF piezoelectric sheet is proportional to its length and inversely proportional to its width; accordingly, the PVDF piezoelectric sheet is designed in a band-like structure in each embodiment of the invention, and the length direction of the band-like structure is arranged in the radial direction of the blade cover 20.
The foregoing description is only of the preferred embodiments of the present invention and is not intended to limit the scope of the invention, and all equivalent structural changes made by the description of the present invention and the accompanying drawings or direct/indirect application in other related technical fields are included in the scope of the invention.
Claims (10)
1. An aircraft, comprising:
the device comprises a body, a control module and a control module, wherein the body comprises an electric control assembly;
the paddle cover is arranged at the top of the machine body;
the paddle is arranged in the paddle cover, is in transmission connection with the driving component of the electric control component and is used for rotating under the driving of the electric control component so as to provide power for the flight of the fuselage; and
the piezoelectric sheet is provided with a fixed end and a free end which are arranged back to back, and the fixed end is fixed on one side of the paddle cover, which is opposite to the machine body, and is electrically connected with the electric control assembly;
the side surface of the oar cover, which is back to the machine body, is convexly provided with a flow blocking blunt body at the central axis of the oar cover, the fixed end is fixed on the side wall of the flow blocking blunt body, and the free end is arranged along the radial outward extension of the oar cover.
2. The aircraft of claim 1, wherein an end of the bluff body adjacent to the shroud is cylindrical, and the fixed end is fixed to a sidewall of the cylindrical end of the bluff body.
3. The aircraft of claim 1, wherein a surface of the piezoelectric patch is disposed along an axial direction of the paddle cover.
4. The aircraft of claim 1, wherein the piezoelectric sheets are provided in a plurality of numbers, and the piezoelectric sheets are arranged at intervals along the circumferential direction of the flow-blocking blunt body.
5. The aircraft of claim 1, wherein the electrical control assembly comprises a drive assembly and a power supply, the power supply being electrically connected to the drive assembly, the drive assembly being drivingly connected to the blade to drive the blade;
the aircraft further comprises an auxiliary power supply, wherein the auxiliary power supply is electrically connected with the driving assembly and the piezoelectric sheet, and the piezoelectric sheet is used for charging the auxiliary power supply.
6. The aircraft of claim 5, wherein a mounting post is provided on a surface of the side of the paddle cover facing away from the fuselage, the fixed end is fixed to a side wall of the mounting post, a mounting cavity is formed in the mounting post, and the auxiliary power supply is arranged in the mounting cavity.
7. The aircraft of claim 6, wherein the mounting cavity is in communication with the interior cavity of the paddle cover, and wherein a power transmission wire is led out from an end of the secondary power supply facing the paddle cover, enters the interior cavity of the paddle cover and enters the fuselage after bypassing the range of motion of the paddles, and is electrically connected to the drive assembly.
8. The aircraft of claim 7, wherein the paddle cover comprises:
the two ends of the cylinder body are opened;
the fixed ring is arranged at one end of the cylinder part, which is opposite to the machine body, and the flow blocking blunt body is convexly arranged on one side surface of the fixed ring, which is opposite to the machine body;
the connecting ribs are radially distributed between the outer side wall of the fixed ring and the inner side wall of the barrel part to connect the barrel part and the fixed ring; and
the supporting beams are radially distributed in one end of the cylinder part, which faces the machine body, the inner ends of the supporting beams are connected with each other, the outer ends of the supporting beams are connected to the inner side wall of the cylinder part, the supporting beams are connected with the machine body, and the output shaft of the driving assembly penetrates into the inner cavity of the paddle cover from the connection part of the inner ends of the supporting beams and is connected with the paddles so as to drive the paddles to rotate;
the power transmission wires penetrate into the inner cavity of the paddle cover through the middle opening of the fixing ring, are routed to the inner side wall of the cylinder body along one connecting rib, and then are routed to the machine body along one supporting beam to enter the machine body.
9. The aircraft according to claim 8, wherein a plurality of fixing buckles are sequentially arranged along the routing direction and used for clamping the power transmission wires, wherein the connecting ribs, the supporting beams and the inner side wall of the barrel body are used for routing; or a wire slot is formed along the wiring direction and is used for clamping the power transmission wire.
10. The aircraft according to any one of claims 1 to 9, wherein the piezoelectric sheet is a polyvinylidene fluoride piezoelectric sheet.
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| CN202111428620.1A CN113928550B (en) | 2021-11-26 | 2021-11-26 | Aircraft with a plurality of aircraft body |
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| CN202111428620.1A CN113928550B (en) | 2021-11-26 | 2021-11-26 | Aircraft with a plurality of aircraft body |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR101667330B1 (en) * | 2015-07-17 | 2016-10-19 | 주식회사 한국카본 | Vertical take off and landing aircraft using hybrid-electric propulsion system |
| CN106385200A (en) * | 2016-10-18 | 2017-02-08 | 青岛大学 | Flexible piezoelectric generator based on Karman vortex street effect |
| CN108216602A (en) * | 2016-12-15 | 2018-06-29 | 西安仁科电子科技有限公司 | A kind of unmanned vehicle |
| CN109229359A (en) * | 2018-09-25 | 2019-01-18 | 王君钰 | A kind of coaxial dual-rotor helicopter and its flight control method |
| CN110683041A (en) * | 2019-10-24 | 2020-01-14 | 张红艳 | Disc-shaped aircraft |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20080074002A1 (en) * | 2006-09-26 | 2008-03-27 | Shashank Priya | Piezoelectric energy harvester |
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Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR101667330B1 (en) * | 2015-07-17 | 2016-10-19 | 주식회사 한국카본 | Vertical take off and landing aircraft using hybrid-electric propulsion system |
| CN106385200A (en) * | 2016-10-18 | 2017-02-08 | 青岛大学 | Flexible piezoelectric generator based on Karman vortex street effect |
| CN108216602A (en) * | 2016-12-15 | 2018-06-29 | 西安仁科电子科技有限公司 | A kind of unmanned vehicle |
| CN109229359A (en) * | 2018-09-25 | 2019-01-18 | 王君钰 | A kind of coaxial dual-rotor helicopter and its flight control method |
| CN110683041A (en) * | 2019-10-24 | 2020-01-14 | 张红艳 | Disc-shaped aircraft |
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