CN211494452U - Rotor unmanned aerial vehicle thermal management system verts and rotor unmanned aerial vehicle verts - Google Patents
Rotor unmanned aerial vehicle thermal management system verts and rotor unmanned aerial vehicle verts Download PDFInfo
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- CN211494452U CN211494452U CN201921996544.2U CN201921996544U CN211494452U CN 211494452 U CN211494452 U CN 211494452U CN 201921996544 U CN201921996544 U CN 201921996544U CN 211494452 U CN211494452 U CN 211494452U
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Abstract
The application discloses a thermal management system of a tilt rotor unmanned aerial vehicle and the tilt rotor unmanned aerial vehicle, wherein wings of the tilt rotor unmanned aerial vehicle comprise fixed wings positioned above a vehicle body, tilt rotors rotatably fixed at two ends of the fixed wings and rotors rotatably fixed on the top surfaces of the tilt rotors; the thermal management system comprises a heat dissipation structure arranged on the top surface of the tilt rotor and below the rotor; the pipeline structure of the heat dissipation structure is connected into an engine of the unmanned aerial vehicle through the inside of the wing. According to the application, under two working modes of the tilt rotor unmanned aerial vehicle, the heat dissipation structure has excellent heat dissipation performance, and the design requirement for improving the heat dissipation performance of the tilt rotor unmanned aerial vehicle on the premise of not improving the weight of the tilt rotor unmanned aerial vehicle is met; the heat dispersion of rotor unmanned aerial vehicle that inclines has been improved.
Description
Technical Field
The present disclosure generally relates to the field of unmanned aerial vehicle technology, and in particular, to a thermal management system for a tilt rotor unmanned aerial vehicle and a tilt rotor unmanned aerial vehicle.
Background
The working modes of the tilt rotor unmanned aerial vehicle comprise a fixed wing mode and a helicopter mode, and the two working modes have higher requirements on a thermal management system, particularly in the helicopter mode; meanwhile, the tilting rotor unmanned aerial vehicle has very high requirement on weight; therefore, the design requirements for improving the heat dissipation effect and the weight of the tilt rotor unmanned aerial vehicle by increasing the size of the heat dissipation structure are mutually contradictory. Need a design that can improve rotor unmanned aerial vehicle heat dispersion that verts under the prerequisite that does not improve rotor unmanned aerial vehicle's that verts weight urgently.
Disclosure of Invention
In view of the above-mentioned defect or not enough among the prior art, it is desirable to provide a rotor unmanned aerial vehicle thermal management system and a rotor unmanned aerial vehicle that verts that can improve rotor unmanned aerial vehicle heat dispersion that verts under the prerequisite that does not improve rotor unmanned aerial vehicle's weight that verts.
In a first aspect, the application provides a thermal management system for a tilt rotor unmanned aerial vehicle, wherein wings of the tilt rotor unmanned aerial vehicle comprise a fixed wing positioned above a vehicle body, tilt rotors rotatably fixed at two ends of the fixed wing, and rotors rotatably fixed on top surfaces of the tilt rotors; the thermal management system includes a heat dissipating structure disposed on a top surface of the tilt rotor and below the rotor; the pipeline structure of the heat dissipation structure is connected into an engine of the unmanned aerial vehicle through the inside of the wing.
According to the technical scheme provided by the embodiment of the application, the heat dissipation structure comprises a lubricating oil radiator, an intercooler and a cooling liquid radiator; the lubricating oil radiator and the intercooler are fixed on the tilt rotor wing on one side of the fixed wing; the cooling liquid radiator is fixed on the tilt wing at the other side of the fixed wing.
According to the technical scheme that this application embodiment provided, heat radiation structure passes through the bolt fastening in tilt rotor's top surface.
According to the technical scheme provided by the embodiment of the application, an adjusting cavity positioned below the heat dissipation structure is arranged in the tilt rotor; the top of the adjusting cavity is provided with a through groove communicated with the outside, the length direction of the through groove extends along a first direction, and the first direction is parallel to the length direction of the fixed wing; the through groove is positioned on one side of the heat dissipation structure in the flight direction;
the vertical side wall of the adjusting cavity is rotatably connected with a first rotating shaft which is horizontally arranged and is vertical to the first direction; a supporting plate positioned in the adjusting cavity is fixed on the first rotating shaft at a position corresponding to the through groove; when the first rotating shaft rotates, the supporting plate rotates out of the adjusting cavity, is positioned on one side of the flight direction of the heat dissipation structure, is in contact with the side wall of the heat dissipation structure and is used for supporting the heat dissipation structure;
and a driving mechanism for controlling the first rotating shaft to rotate is arranged in the adjusting cavity.
According to the technical scheme provided by the embodiment of the application, the driving mechanism comprises a second rotating shaft which is vertically and rotatably arranged on the bottom surface of the adjusting cavity;
the surfaces of the first rotating shaft and the second rotating shaft are provided with spiral grooves; the surface of the first rotating shaft and the surface of the second rotating shaft are fixedly connected with adjusting ropes; the two ends of the adjusting rope are respectively wound in the spiral groove for a plurality of circles;
the bottom surface of the adjusting cavity is provided with a semi-circle sliding groove around the second rotating shaft; the connecting lines at the two ends of the sliding chute are parallel to the first rotating shaft; a counterweight ball is slidably clamped in the sliding groove; the top surface of the counterweight ball extends out of the bottom surface of the adjusting cavity and is connected with the outer wall of the second rotating shaft through a pull rope;
the bottom surface of the sliding groove gradually becomes lower from one end close to the through groove to one end far away from the through groove.
In a second aspect, the application provides a rotor unmanned aerial vehicle verts, unmanned aerial vehicle is equipped with above-mentioned arbitrary thermal management system.
According to the technical scheme, the heat dissipation structure of the tilt rotor unmanned aerial vehicle is designed on the surface of the tilt rotor and is positioned below the tilt rotor, so that when the tilt rotor unmanned aerial vehicle is in a helicopter mode, the heat dissipation structure is in a horizontal position, and the cooling of the heat dissipation structure can be accelerated by utilizing air flow below the tilt rotor unmanned aerial vehicle; when rotor unmanned aerial vehicle verts is in the stationary vane mode, the rotor that verts rotates 90 degrees for install at its surface heat radiation structure and be in vertical position, the air current that flying speed brought before usable this moment accelerates the cooling to heat radiation structure. Thus, under two working modes of the tilt rotor unmanned aerial vehicle, the heat dissipation structure has excellent heat dissipation performance, and the design requirement for improving the heat dissipation performance of the tilt rotor unmanned aerial vehicle on the premise of not improving the weight of the tilt rotor unmanned aerial vehicle is met; the heat dispersion of rotor unmanned aerial vehicle that inclines has been improved.
According to the technical scheme that provides of this application preferred embodiment, as unmanned aerial vehicle heat radiation structure's lubricating oil radiator, intercooler and coolant liquid radiator, according to three's weight ratio, evenly set up on the tilt rotor of unmanned aerial vehicle both sides, guaranteed whole unmanned aerial vehicle's weight balance.
According to the technical scheme that provides of this application preferred embodiment, adjust the chamber through the design and can bear the backup pad of adjusting the intracavity and roll out for when unmanned aerial vehicle is in the stationary vane mode, the backup pad can be followed and is adjusted the intracavity and stretch out, is used for from bottom sprag live heat radiation structure, for heat radiation structure provides reinforcing protective structure at the stationary vane mode, has improved unmanned aerial vehicle's flight safety.
Drawings
Other features, objects and advantages of the present application will become more apparent upon reading of the following detailed description of non-limiting embodiments thereof, made with reference to the accompanying drawings in which:
fig. 1 is a schematic structural diagram of an unmanned aerial vehicle in a helicopter mode according to an embodiment of the present application;
fig. 2 is a schematic structural diagram of an unmanned aerial vehicle in a fixed-wing mode according to an embodiment of the present application;
FIG. 3 is a schematic structural view of the interior of a tilt rotor according to a second embodiment of the present invention;
100 fixed wings; 200 tilt rotors; 300 rotor wings; 400 a heat dissipation structure; 410 a lubricating oil radiator; 420 intercooler; 430 a coolant radiator; 421 an adjustment chamber; 422 through grooves; 423 a first rotating shaft; 424 support plates; 500 a drive mechanism; 510 a second rotating shaft; 520 adjusting the rope; 530 a chute; 540 weight-balancing balls; 550 pulling the rope.
Detailed Description
The present application will be described in further detail with reference to the following drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the relevant invention and not restrictive of the invention. It should be noted that, for convenience of description, only the portions related to the present invention are shown in the drawings.
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present application will be described in detail below with reference to the embodiments with reference to the attached drawings.
Example one
Please refer to fig. 1 and fig. 2, which are schematic structural diagrams of a drone applied to a thermal management system of a tilt rotor drone provided in the present application, wherein a wing of the tilt rotor drone includes a fixed wing 100 located above a fuselage, tilt rotors 200 rotatably fixed at two ends of the fixed wing 100, and a rotor 300 rotatably fixed on a top surface of the tilt rotor 200; the thermal management system comprises a heat dissipation structure 400 disposed on the top surface of the tilt rotor 200 and below the rotor 300; the pipeline structure of the heat dissipation structure 400 is connected to the inside of the engine of the unmanned aerial vehicle through the inside of the wing.
The tilt rotor unmanned aerial vehicle has two working modes, wherein one mode is a helicopter mode, and is shown in fig. 2; one is the fixed-wing mode, as shown in FIG. 1;
in the helicopter mode, as shown in fig. 2, the tilt wing 200 is flush with the plane of the fixed wing 100, and the tilt wing 200 forms an integral whole with the fixed wing 100, and in the fixed wing mode, the tilt wing 200 is perpendicular to the plane of the fixed wing 100, i.e., the state shown in fig. 2. When the tilt rotor unmanned aerial vehicle is in a helicopter mode, the heat dissipation structure 400 is in a horizontal position, and at the moment, the cooling of the heat dissipation structure can be accelerated by utilizing airflow below the rotor 300; when rotor unmanned aerial vehicle verts is in the fixed wing mode, as shown in fig. 2, the rotor that verts rotates 90 degrees for install at its surface heat radiation structure 400 in vertical position, the air current that the speed brought before the usable this moment of flying accelerates the cooling to heat radiation structure 400. Thus, under two working modes of the tilt rotor unmanned aerial vehicle, the heat dissipation structure 400 has excellent heat dissipation performance, and the design requirement for improving the heat dissipation performance of the tilt rotor unmanned aerial vehicle on the premise of not improving the weight of the tilt rotor unmanned aerial vehicle is met; the heat dispersion of rotor unmanned aerial vehicle that inclines has been improved.
Heat dissipation structure 400 of tiltrotor drone includes oil radiator 410, intercooler 420, and coolant radiator 430; wherein the sum of the weights of the oil radiator 410 and the intercooler 20 is substantially matched with the weight of the coolant radiator 430, and thus the oil radiator 410 and the intercooler 420 are fixed to the tilt rotor 200 on the side of the stationary wing 100; the coolant radiator 430 is fixed to the tilt wing 200 at the other side of the stationary wing 100. Thus, the weight of the two sides of the fixed wing 100 is approximately equal, and a small weight difference can be coordinated by the weight difference of the mounting bases of the two-side heat dissipation structures 400; so that the overall weight of the unmanned aerial vehicle is kept balanced.
Wherein, the bases of the oil radiator 410, the intercooler 420 and the coolant radiator 430 are all fixed on the top surface of the tilt rotor 200 by bolts; because the wings of the unmanned aerial vehicle, including the fixed wing 410, the tilt rotor 420 and the rotor 430, are all provided with hollow cavities; the lubricating oil radiator 410, the intercooler 420 and the coolant radiator 430 are all connected with an inlet pipe and an outlet pipe, and the inlet pipe and the outlet pipe pass through the cavity of the wing and then enter the engine of the fuselage and are respectively connected with the corresponding components.
For example, the lubricating oil of the engine enters the inlet of the lubricating oil radiator from the lubricating oil inlet pipe, flows out of the outlet of the lubricating oil radiator and returns to the engine after being cooled by the lubricating oil radiator, and the lubricating oil is effectively radiated in the lubricating oil radiator; high-temperature air after turbocharging of the engine enters an intercooler, and enters an engine air box after the intercooler effectively dissipates heat; the cooling liquid of the engine enters the inlet of the cooling liquid radiator from the cooling liquid inlet pipe, flows out of the outlet of the cooling liquid radiator and returns to the engine after being cooled by the cooling liquid radiator, and the cooling liquid is effectively radiated in the cooling liquid radiator.
Example two
On the basis of the first embodiment, as shown in fig. 3, an adjusting cavity 421 located below the heat dissipation structure 400 is provided in the tilt rotor 420; the top of the adjusting cavity 421 is provided with a through groove 422 communicated with the outside, the length direction of the through groove 422 extends along a first direction, and the first direction is parallel to the length direction of the fixed wing 410; the through groove 422 is positioned at one side of the heat dissipation structure in the flight direction;
a first rotating shaft 423 which is horizontally arranged and is perpendicular to the first direction is rotatably connected to a vertical side wall of the adjusting cavity 421; a supporting plate 424 positioned in the adjusting cavity 421 is fixed on the first rotating shaft 423 at a position corresponding to the through groove 422; when the first rotating shaft 423 rotates, the supporting plate 424 rotates out of the adjusting cavity 421 and is located at one side of the flight direction of the heat dissipation structure 400, and contacts with the sidewall of the heat dissipation structure 400, so as to support the heat dissipation structure 400;
a driving mechanism 500 for controlling the rotation of the first rotating shaft 423 is provided in the adjustment chamber 421.
When the wings of the unmanned aerial vehicle rotate from the helicopter mode to the fixed wing mode, the driving mechanism 500 drives the first rotating shaft 423 to rotate in the direction of an arrow 1 in the figure, the first rotating shaft 423 drives the supporting plate 424 to rotate, so that the supporting plate 424 rotates out of the through groove 422, and when the first rotating shaft 423 rotates 180 degrees, the supporting plate 424 is located at the position shown in fig. 2; at the moment, the supporting plate is positioned below the heat dissipation mechanism and is in contact with the side face of the heat dissipation structure, so that a supporting effect can be provided for the heat dissipation structure, and the supporting protection can be provided for the heat dissipation structure under the mode of the fixed wing.
Preferably, the side wall of the rotating hole of the adjusting cavity, into which the first rotating shaft is inserted, is provided with a limiting protrusion, which can limit the maximum rotating angle of the first rotating shaft along the direction of the arrow 1; so that its maximum rotation angle remains 180 degrees.
An embodiment of the driving mechanism 500 is optionally driven by a motor, and in a preferred embodiment of the driving mechanism, the driving mechanism 500 includes a second rotating shaft 510 vertically and rotatably disposed at the bottom surface of the adjusting cavity;
the surfaces of the first rotating shaft 423 and the second rotating shaft 510 are provided with spiral grooves; the surface of the first rotating shaft and the surface of the second rotating shaft 510 are fixedly connected with adjusting ropes 520; the two ends of the adjusting rope 520 are respectively coiled in the spiral groove for a plurality of circles;
the bottom surface of the adjusting cavity 421 is provided with a half-circle sliding groove 530 around the second rotating shaft 510; the connecting line of the two ends of the sliding chute is parallel to the first rotating shaft 423; a counterweight ball 540 is slidably clamped in the chute 530; the top surface of the counterweight ball 540 extends out of the bottom surface of the adjustment cavity 421 and is connected with the outer wall of the second rotating shaft 510 through a pull rope 550;
the bottom surface of the sliding groove 530 is gradually lowered from one end close to the through groove 422 to one end far away from the through groove 422.
When the tilt wing is horizontally maintained, the weight ball slides from the high end to the low end of the sliding slot 530 under the action of gravity, and drives the second rotating shaft 510 to rotate 180 degrees.
When the tilt wing rotates from the horizontal state to the vertical state, the counterweight ball 540 moves from the lower end to the upper end of the chute 530 under the action of gravity to drive the second rotating shaft 510 to rotate clockwise, and the adjusting rope 520 is tightened and wound on the surface of the second rotating shaft 510 along with the rotation of the second rotating shaft 510, so that the first rotating shaft 423 is pulled to rotate clockwise; in this embodiment, the diameters of the first rotating shaft and the second rotating shaft are the same, and when the first rotating shaft 423 rotates 180 degrees under the pulling of the weight ball 540, the first rotating shaft 423 also rotates 180 degrees clockwise, so that the supporting plate 424 rotates to the position of fig. 2, and provides a support for the heat dissipation structure 400.
When the tilt wing rotates from the vertical state to the horizontal state, the counterweight ball slides from the high end to the low end of the chute 530 under the action of gravity, and drives the second rotating shaft 510 to rotate 180 degrees counterclockwise; the adjusting rope 520 then drives the first rotating shaft to rotate 180 degrees counterclockwise, so that the supporting plate is reset to return to the through groove.
In the preferred embodiment of the driving mechanism, the gravity and the inclined sliding groove are matched, the gravity of the counterweight ball is used for driving the supporting plate to extend or retract, and the driving mechanism is of a pure physical structure, stable in structure and low in cost.
EXAMPLE III
The embodiment provides a tilt rotor unmanned aerial vehicle adopting the thermal management system of the first embodiment, and the structure of the tilt rotor unmanned aerial vehicle is shown in fig. 1.
The above description is only a preferred embodiment of the application and is illustrative of the principles of the technology employed. It will be appreciated by a person skilled in the art that the scope of the invention as referred to in the present application is not limited to the embodiments with a specific combination of the above-mentioned features, but also covers other embodiments with any combination of the above-mentioned features or their equivalents without departing from the inventive concept. For example, the above features may be replaced with (but not limited to) features having similar functions disclosed in the present application.
Claims (6)
1. A thermal management system of a tilt rotor unmanned aerial vehicle is disclosed, wherein wings of the tilt rotor unmanned aerial vehicle comprise fixed wings positioned above a vehicle body, tilt rotors rotatably fixed at two ends of the fixed wings, and rotors rotatably fixed on the top surfaces of the tilt rotors; wherein the thermal management system comprises a heat dissipation structure disposed on a top surface of the tilt rotor and below the rotor; the pipeline structure of the heat dissipation structure is connected into an engine of the unmanned aerial vehicle through the inside of the wing.
2. The tilt-rotor unmanned aerial vehicle thermal management system of claim 1, wherein the heat dissipation structure comprises a lubricant heat sink, an intercooler, and a coolant heat sink; the lubricating oil radiator and the intercooler are fixed on the tilt rotor wing on one side of the fixed wing; the cooling liquid radiator is fixed on the tilt wing at the other side of the fixed wing.
3. The tilt rotor unmanned aerial vehicle thermal management system of claim 1, wherein the heat dissipation structure is bolted to the top surface of the tilt rotor.
4. The tilt rotor unmanned aerial vehicle thermal management system of claim 3, wherein a tuning cavity is provided in the tilt rotor below the heat dissipating structure; the top of the adjusting cavity is provided with a through groove communicated with the outside, the length direction of the through groove extends along a first direction, and the first direction is parallel to the length direction of the fixed wing; the through groove is positioned on one side of the heat dissipation structure in the flight direction;
the vertical side wall of the adjusting cavity is rotatably connected with a first rotating shaft which is horizontally arranged and is vertical to the first direction; a supporting plate positioned in the adjusting cavity is fixed on the first rotating shaft at a position corresponding to the through groove; when the first rotating shaft rotates, the supporting plate rotates out of the adjusting cavity, is positioned on one side of the flight direction of the heat dissipation structure, is in contact with the side wall of the heat dissipation structure and is used for supporting the heat dissipation structure;
and a driving mechanism for controlling the first rotating shaft to rotate is arranged in the adjusting cavity.
5. The tilt-rotor drone thermal management system of claim 4, wherein the drive mechanism includes a second shaft vertically rotatably disposed at a bottom surface of the adjustment cavity;
the surfaces of the first rotating shaft and the second rotating shaft are provided with spiral grooves; the surface of the first rotating shaft and the surface of the second rotating shaft are fixedly connected with adjusting ropes; the two ends of the adjusting rope are respectively wound in the spiral groove for a plurality of circles;
the bottom surface of the adjusting cavity is provided with a semi-circle sliding groove around the second rotating shaft; the connecting lines at the two ends of the sliding chute are parallel to the first rotating shaft; a counterweight ball is slidably clamped in the sliding groove; the top surface of the counterweight ball extends out of the bottom surface of the adjusting cavity and is connected with the outer wall of the second rotating shaft through a pull rope;
the bottom surface of the sliding groove gradually becomes lower from one end close to the through groove to one end far away from the through groove.
6. A tilt rotor unmanned aerial vehicle, the unmanned aerial vehicle comprising a thermal management system according to any of claims 1 to 5.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921996544.2U CN211494452U (en) | 2019-11-19 | 2019-11-19 | Rotor unmanned aerial vehicle thermal management system verts and rotor unmanned aerial vehicle verts |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921996544.2U CN211494452U (en) | 2019-11-19 | 2019-11-19 | Rotor unmanned aerial vehicle thermal management system verts and rotor unmanned aerial vehicle verts |
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| Publication Number | Publication Date |
|---|---|
| CN211494452U true CN211494452U (en) | 2020-09-15 |
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| CN201921996544.2U Active CN211494452U (en) | 2019-11-19 | 2019-11-19 | Rotor unmanned aerial vehicle thermal management system verts and rotor unmanned aerial vehicle verts |
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