CN209776802U - Self-generating water-spraying aircraft - Google Patents
Self-generating water-spraying aircraft Download PDFInfo
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- CN209776802U CN209776802U CN201822266911.5U CN201822266911U CN209776802U CN 209776802 U CN209776802 U CN 209776802U CN 201822266911 U CN201822266911 U CN 201822266911U CN 209776802 U CN209776802 U CN 209776802U
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Abstract
The utility model relates to an aircraft especially relates to a from electricity generation water spray aircraft, including aircraft main part, inlet tube and hydrodynamic force electricity generation subassembly, the aircraft main part is equipped with water inlet and water jet, the inlet tube with the water inlet is connected, hydrodynamic force electricity generation unit mount is in on the inlet tube, and with the inlet tube intercommunication, hydrodynamic force electricity generation subassembly with aircraft main part electricity is connected, is used for doing the aircraft main part provides power. Because rivers in the inlet tube flow at a high speed always, have very big kinetic energy, utilize the backward flow in the inlet tube to drive the electricity generation subassembly electricity generation, and will generate electricity and supply the aircraft main part to use, provide power for the flight of aircraft main part, external power source has been avoided to this scheme, realize that water spray aircraft self electricity generation supplies self to use, reduce water spray aircraft's weight, and as long as this internal water supply of looks aircraft, the electricity generation subassembly can generate electricity always, guarantees water spray aircraft's long-time continuation of the journey.
Description
Technical Field
The utility model relates to an aircraft especially relates to a from electricity generation water spray aircraft.
Background
The control every single move that water spray aircraft can be fine, driftage and roll attitude, water spray aircraft bottom is through soft inlet tube connection water pump, water in the inlet tube flows at high speed always, water spray aircraft can realize the rotation of relative water inlet hose as required, water spray aircraft system mainly provides power through the aquatic of placing or the water pump on ground, but also have the steering wheel on the aircraft body, the system of the needs power supply of circuit board, these systems are not big to the demand of electric quantity, but must have power supply system.
The hydrodynamic unmanned aerial vehicle in the prior art adopts a method of directly connecting a power supply system of a water surface or ground water pump to a water spraying aircraft to realize power supply of an aircraft system, the method increases the burden of the aircraft (the aircraft flies high, the line can be very long), the effective load of the aircraft is reduced, and if the aircraft rotates, an electric wire can be wound, so that large-angle spinning of the aircraft cannot be realized, and the function of the aircraft is limited.
Wiring to the aircraft is not a good solution, and another solution is to supply power by batteries, but battery power has a timed charging problem. If the battery capacity is large, the aircraft can continuously fly for a long time, but the weight is heavy, so that the effective load of the aircraft is reduced; if the battery capacity is small, the aircraft has a short duration of flight and cannot continue flying for a long period of time.
SUMMERY OF THE UTILITY MODEL
The utility model provides a self-generating water spray aircraft to solve the problem that water spray aircraft is big in weight and can't last journey for a long time.
In order to solve the problem, the embodiment of the utility model provides a from electricity generation water spray aircraft, including aircraft main part, inlet tube and hydrodynamic force power generation subassembly, the aircraft main part is equipped with water inlet and water jet, the inlet tube with the water inlet is connected, hydrodynamic force power generation unit mount is in on the inlet tube, and with the inlet tube intercommunication, hydrodynamic force power generation subassembly with aircraft main part electricity is connected, is used for doing the aircraft main part provides power.
Optionally, the hydrodynamic force power generation assembly includes a stator and a rotor, one end of the rotor is disposed on the water flow path and is configured to rotate under the action of water flow, and the other end of the rotor is rotatably disposed in the stator.
Optionally, still include connecting pipe and installation sleeve, the one end of connecting pipe with the water inlet of aircraft main part is connected, the other end with advance water piping connection, the telescopic axis of installation with the axis of connecting pipe is perpendicular, just the telescopic lateral wall of installation with the lateral wall intercommunication of connecting pipe, the rotor is followed the telescopic axial setting of installation, just the one end of rotor is rotatable set up in the installation sleeve, the other end set up in the stator.
Optionally, one end of the mounting sleeve is closed, the other end of the mounting sleeve is open, one end of the stator is closed, the other end of the stator is open, the open end of the mounting sleeve is connected with the open end of the stator, and the mounting space of the rotor is jointly constructed.
optionally, two ends of the rotor are respectively rotatably connected with the closed end of the mounting sleeve and the closed end of the stator.
Optionally, two ends of the rotor are respectively connected with the closed end of the mounting sleeve and the closed end of the stator through bearings.
Optionally, the rotor includes a blade segment, the blade segment is provided with a plurality of thrust blades along a circumferential direction, and the blade segment is rotatably disposed in the mounting sleeve.
Optionally, the shape of the thrust blade is an arc, and the bending direction of the thrust blade is opposite to the rotation direction of the rotor.
Optionally, the thrust vane extends into the connecting pipe from a communication position between the side wall of the mounting sleeve and the side wall of the water inlet pipe.
Optionally, the rotor includes a magnet segment, the stator is provided with an induction coil, and the magnet segment is rotatably disposed in the stator.
Above-mentioned scheme has increased the electricity generation subassembly in water spray aircraft's inlet tube department, because rivers in the inlet tube flow at a high speed always, have very big kinetic energy, utilize the backward flow in the inlet tube to drive the electricity generation subassembly electricity generation, and supply the aircraft main part with the electricity generation and use, flight for the aircraft main part provides power, external power source has been avoided to this scheme, realize water spray aircraft self electricity generation and supply self to use, reduce water spray aircraft's weight, and as long as this internal water supply of looks aircraft, the electricity generation subassembly can generate electricity always, guarantee water spray aircraft's long-time continuation of the journey.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings required to be used in the description of the embodiments of the present invention will be briefly introduced below, and 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 inventive labor.
Fig. 1 is a schematic structural diagram of a self-generating water-jet aircraft according to an embodiment of the present invention;
Fig. 2 is a perspective view of a power generation assembly according to an embodiment of the present invention;
Fig. 3 is a schematic view of another perspective of a power generation assembly according to an embodiment of the present invention;
Fig. 4 is an exploded view of a power generation assembly according to an embodiment of the present invention.
In the figure, 1: an aircraft body 1; 2: a power generation assembly; 3: a water inlet pipe; 4: a connecting pipe; 5: installing a sleeve; 201: a stator; 202: a rotor; 202 a: a blade segment; 202 b: a magnet segment; 202 c: and a thrust blade.
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 some, not all, of the embodiments of the present invention. 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.
as shown in fig. 1 to 4, the embodiment of the utility model provides a from electricity generation water spray aircraft, including aircraft main part 1, inlet tube 3 and hydrodynamic force power generation subassembly 2, aircraft main part 1 is equipped with water inlet and water jet, inlet tube 3 is connected with the water inlet, hydrodynamic force power generation subassembly 2 is installed on inlet tube 3, and communicate with inlet tube 3, hydrodynamic force power generation subassembly 2 is connected with aircraft main part 1 electricity, be used for providing power for aircraft main part 1, it is concrete, be equipped with rechargeable battery in the aircraft main part 1, power generation subassembly 2 is connected with rechargeable battery, the electricity generation will be stored in rechargeable battery. This embodiment has increased electricity generation subassembly 2 in water spray aircraft's inlet tube 3 department, because rivers in the inlet tube 3 flow at a high speed always, have very big kinetic energy, utilize the backward flow in the inlet tube 3 to drive electricity generation subassembly 2 electricity generation, and supply aircraft main part 1 use with the electricity generation, flight for aircraft main part 1 provides power, external power source has been avoided to this scheme, realize water spray aircraft self electricity generation and supply self to use, reduce water spray aircraft's weight, and as long as this internal water supply of looks aircraft, electricity generation subassembly 2 can generate electricity always, guarantee water spray aircraft's long-time continuation of the journey.
Further, the hydrodynamic force power generation assembly 2 includes a stator 201 and a rotor 202, one end of the rotor 202 is arranged on the water flow path and is used for rotating under the action of water flow, the other end of the rotor 202 is rotatably arranged in the stator 201, and the rotor 202 rotates under the driving of the water flow, so that the rotor 202 and the stator 201 rotate relatively to generate power.
Further, this aircraft still includes connecting pipe 4 and installation sleeve 5, the one end of connecting pipe 4 is connected with the water inlet of aircraft main part 1, the other end and inlet tube 3 are connected, in this embodiment, the one end of connecting pipe 4 cup joints with the water inlet of aircraft main part 1, and adopt the sealing washer sealed, the other end is equipped with the screw thread, inlet tube 3 includes the hose, the hose cover is on the screw thread section of connecting pipe 4, can realize being connected of connecting pipe 4 and inlet tube 3, can realize the sealed of kneck again, the axis of installation sleeve 5 is perpendicular with the axis of connecting pipe 4, and the lateral wall of installation sleeve 5 and the lateral wall of connecting pipe 4 intercommunication, rotor 202 sets up along the axial of installation sleeve 5, and rotor 202's one end is rotatable to be set up in installation sleeve 5, the. The power generation module 2 is mounted on the water flow path by the connecting pipe 4 and the mounting sleeve 5, and the kinetic energy of the water flow is converted into electric energy for the aircraft body 1 to use.
Further, one end of the mounting sleeve 5 is closed, the other end is opened, one end of the stator 201 is closed, the other end is opened, the mounting sleeve 5 and the stator 201 are coaxially arranged, the opened end of the mounting sleeve 5 is connected with the opened end of the stator 201, and the mounting space of the rotor 202 is jointly constructed. The rotor 202 is sealed in the installation space, so that the influence from the outside is avoided, and the flying stability of the whole water spraying aircraft is ensured.
further, both ends of the rotor 202 are rotatably connected to the closed end of the mounting sleeve 5 and the closed end of the stator 201, respectively. In the present embodiment, both ends of the rotor 202 are connected to the closed end of the mounting sleeve 5 and the closed end of the stator 201 by bearings, respectively.
Further, the rotor 202 includes a blade segment 202a, the blade segment 202a is provided with a plurality of thrust blades 202c along the circumferential direction, and the blade segment 202a is rotatably disposed in the mounting sleeve 5. When water flows through the rotor 202, the blades are driven by the power of the water flow to drive the rotor 202 to rotate, so as to realize power generation,
Further, the shape of the thrust blade 202c is arc-shaped, and the bending direction of the thrust blade 202c is opposite to the rotation direction of the rotor 202. The thrust blades 202c are arranged in an arc shape and bent in a direction opposite to the rotation direction of the rotor 202, and this is provided for the purpose that the thrust blades 202c are more easily forced to rotate the rotor 202.
Further, the thrust vanes 202c extend from the communication between the side wall of the mounting sleeve 5 and the side wall of the water inlet pipe 3 into the connecting pipe 4, that is, the thrust vanes 202c are located on the water flow path.
Further, the rotor 202 includes a magnet segment 202b, the stator 201 is provided with an induction coil, and the magnet segment 202b is rotatably disposed in the stator 201. When the magnet segments 202b rotate in the stator 201, the induction coil cuts the magnetic induction lines to generate electricity.
To sum up, the utility model provides a from electricity generation water spray aircraft, including aircraft main part, inlet tube and hydrodynamic force electricity generation subassembly, the aircraft main part is equipped with water inlet and water jet, and the inlet tube is connected with the water inlet, and hydrodynamic force electricity generation unit mount is on the inlet tube to with the inlet tube intercommunication, the hydrodynamic force electricity generation subassembly is connected with the aircraft main part electricity, is used for providing power for the aircraft main part, and is concrete, is equipped with rechargeable battery in the aircraft main part, and the electricity generation subassembly is connected with rechargeable battery, and the electricity generation will be stored in rechargeable battery. This embodiment has increased the electricity generation subassembly in water spray aircraft's inlet tube department, because rivers in the inlet tube flow at a high speed always, very big kinetic energy has, the backward flow that utilizes in the inlet tube drives the electricity generation subassembly electricity generation, and supply the aircraft main part with the electricity generation and use, flight for the aircraft main part provides power, external power source has been avoided to this scheme, realize water spray aircraft self electricity generation and supply self to use, reduce water spray aircraft's weight, and as long as this internal water supply of looks aircraft, the electricity generation subassembly can generate electricity always, guarantee water spray aircraft's long-time continuation of the journey.
The above embodiments are only specific embodiments of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art can easily think of changes or substitutions within the technical scope of the present invention, and all should be covered within the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (10)
1. The utility model provides a from electricity generation water spray aircraft, its characterized in that, includes aircraft main part, inlet tube and hydrodynamic force electricity generation subassembly, the aircraft main part is equipped with water inlet and water jet, the inlet tube with the water inlet is connected, hydrodynamic force electricity generation unit mount is in on the inlet tube, and with the inlet tube intercommunication, hydrodynamic force electricity generation subassembly with the aircraft main part electricity is connected, is used for doing the aircraft main part provides power.
2. The self-generating water jet aircraft according to claim 1, wherein the water power generating assembly comprises a stator and a rotor, one end of the rotor is disposed on the water flow path for rotation under the action of water flow, and the other end of the rotor is rotatably disposed in the stator.
3. The self-generating water spraying aircraft according to claim 2, further comprising a connecting pipe and a mounting sleeve, wherein one end of the connecting pipe is connected with the water inlet of the aircraft body, the other end of the connecting pipe is connected with the water inlet pipe, the axis of the mounting sleeve is perpendicular to the axis of the connecting pipe, the side wall of the mounting sleeve is communicated with the side wall of the connecting pipe, the rotor is arranged along the axial direction of the mounting sleeve, one end of the rotor is rotatably arranged in the mounting sleeve, and the other end of the rotor is arranged in the stator.
4. The self-generating water-spraying aircraft according to claim 3, wherein one end of the mounting sleeve is closed, the other end of the mounting sleeve is open, one end of the stator is closed, the other end of the stator is open, and the open end of the mounting sleeve is connected with the open end of the stator to jointly form the mounting space of the rotor.
5. The self-generating water-spraying aircraft according to claim 4, wherein two ends of the rotor are rotatably connected with the closed end of the mounting sleeve and the closed end of the stator respectively.
6. The self-generating water-spraying aircraft according to claim 5, wherein two ends of the rotor are respectively connected with the closed end of the mounting sleeve and the closed end of the stator through bearings.
7. The self-generating water-spraying aircraft according to claim 3, wherein the rotor comprises a blade section, the blade section is provided with a plurality of thrust blades along the circumferential direction, and the blade section is rotatably arranged in the mounting sleeve.
8. The self-generating water-spraying aircraft according to claim 7, wherein the thrust blades are arc-shaped, and the bending direction of the thrust blades is opposite to the rotation direction of the rotor.
9. the self-generating water jet aircraft of claim 7, wherein the thrust blades extend into the connecting pipe from a communication between the side wall of the mounting sleeve and the side wall of the water inlet pipe.
10. The self-generating water-spraying aircraft according to claim 8, wherein the rotor comprises a magnet section, the stator is provided with an induction coil, and the magnet section is rotatably arranged in the stator.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822266911.5U CN209776802U (en) | 2018-12-29 | 2018-12-29 | Self-generating water-spraying aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822266911.5U CN209776802U (en) | 2018-12-29 | 2018-12-29 | Self-generating water-spraying aircraft |
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| Publication Number | Publication Date |
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| CN209776802U true CN209776802U (en) | 2019-12-13 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201822266911.5U Active CN209776802U (en) | 2018-12-29 | 2018-12-29 | Self-generating water-spraying aircraft |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GR1010314B (en) * | 2021-09-17 | 2022-09-30 | Κωνσταντινος Θεοφανη Μαδενιδης | Unmanned firefighting device - method for the firefighting and restriction of forest fires |
-
2018
- 2018-12-29 CN CN201822266911.5U patent/CN209776802U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GR1010314B (en) * | 2021-09-17 | 2022-09-30 | Κωνσταντινος Θεοφανη Μαδενιδης | Unmanned firefighting device - method for the firefighting and restriction of forest fires |
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