CN210191812U - Rotorcraft convenient to transition is flexible - Google Patents
Rotorcraft convenient to transition is flexible Download PDFInfo
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- CN210191812U CN210191812U CN201921003736.9U CN201921003736U CN210191812U CN 210191812 U CN210191812 U CN 210191812U CN 201921003736 U CN201921003736 U CN 201921003736U CN 210191812 U CN210191812 U CN 210191812U
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- bottom plate
- gyroplane
- fuselage
- main part
- base plate
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Abstract
The utility model relates to a gyroplane technical field discloses a gyroplane convenient to transition is flexible, including the gyroplane main part, the gyroplane main part includes the rotor piece, and the fixed first bottom plate that supports the gyroplane main part that is equipped with in one side that the rotor piece was kept away from to the gyroplane main part, one side that the gyroplane main part was kept away from to first bottom plate is rotated relatively and is equipped with the second bottom plate, is equipped with in the second bottom plate and drives first bottom plate pivoted power unit, and one side that first bottom plate was kept away from to the second bottom plate is equipped with positive tricycle running. The utility model discloses a gyroplane that has solved current positive tricycle running gear when the more level and smooth road surface of road conditions is high-speed, the characteristics of poor stability.
Description
Technical Field
The utility model relates to a gyroplane technical field, in particular to gyroplane convenient to transition is flexible.
Background
The gyroplane is an 'aircraft' which uses an unpowered rotor to provide lift force and is heavier than air, and the propulsion device provides thrust to advance, and the propulsion device comprises a propeller and an air jet. The air flow blows the rotor wing to generate lift force when the aircraft advances, the aircraft cannot vertically take off or hover, initial power is always provided for the rotor wing when the aircraft takes off, the lift force of the rotor wing is increased, approximately vertical landing can be performed by means of the rotor wing, the structure of the rotor wing becomes complex, and the speed improvement is limited.
The existing gyroplane is designed into a positive three-wheel traveling mechanism (an independent wheel is arranged at the front end of the bottom side of a gyroplane main body, and two collinear wheels are arranged at the rear end of the bottom side of the gyroplane), when the gyroplane is transferred, the positive three-wheel traveling mechanism rotates to drive the gyroplane main body to move.
SUMMERY OF THE UTILITY MODEL
Based on above problem, the utility model provides a gyroplane convenient to transition is flexible has solved current positive tricycle running gear's gyroplane and when the more level and smooth road surface of road conditions was gone at a high speed, poor stability's characteristics.
For solving the above technical problem, the utility model discloses a technical scheme as follows:
the utility model provides a gyroplane convenient to transition is flexible, includes the gyroplane main part, and the gyroplane main part includes rotor plate, and one side that rotor plate was kept away from to the gyroplane main part is fixed to be equipped with the first bottom plate that supports the gyroplane main part, and one side that rotor plate main part was kept away from to first bottom plate rotates relatively and is equipped with the second bottom plate, is equipped with in the second bottom plate to drive first bottom plate pivoted power unit, and one side that first bottom plate was kept away from to the second bottom plate is equipped with positive tricycle running.
The utility model discloses a principle and effect: the rotorcraft is in a first transition mode, when the rotorcraft runs on a road with complicated road conditions, the positive three-wheel traveling mechanism drives the second bottom plate to move, the second bottom plate drives the first bottom plate to move, the first bottom plate drives the rotorcraft main body to rotate, in the moving process, the moving mode of the rotorcraft main body is a positive three-wheel moving mode, the positive three-wheel moving mode has the advantages of being convenient to guide and easy to avoid obstacles (gullies and small obstacles), the rotorcraft runs in a second transition mode, when the rotorcraft runs on a road with smoother road conditions, the power supply of the power mechanism is switched on, the power mechanism drives the first bottom plate to rotate on the upper side of the second bottom plate, when the front side and the back side of the rotorcraft main body are adjusted oppositely, the power supply of the power mechanism is switched off, the positive three-wheel traveling mechanism is converted into a reverse three-wheel traveling mechanism, and when the reverse three, first bottom plate drives the gyroplane main part and rotates, at above-mentioned in-process, changes the moving mode of gyroplane main part into the tricycle moving mechanism that falls, and the gyroplane main part has the good advantage of stability when carrying out high-speed the removal.
As a preferred mode, the main body of the rotor wing comprises a main body, and further comprises an engine and a battery which are arranged in the main body, wherein a rotor wing sheet in transmission connection with the engine is arranged on the upper side of the main body, a propeller in transmission connection with the engine is arranged on the tail side of the main body, and a horizontal tail is arranged on the tail side of the main body.
As a preferred mode, the right three-wheel traveling mechanism comprises two common wheels and an electric wheel, the two common wheels are arranged on the same side of the machine body in the moving direction, and the electric wheel is connected with a battery inside the machine body.
As a preferred mode, the middle part of the lower side of the first bottom plate is connected with one end of an annular clamping table, and the other end of the annular clamping table is clamped with the second bottom plate.
As a preferred mode, the middle part of the lower side of the first bottom plate is connected with one end of a rotating shaft, the other end of the rotating shaft is positioned in the second bottom plate, the power mechanism comprises a first gear arranged at the tail end of the rotating shaft in the second bottom plate and a motor connected with a battery in the second bottom plate, and an output shaft of the motor is connected with a second gear meshed with the first gear through oil.
As an optimal mode, the middle part of the lower side of the first base plate is provided with an annular limiting groove, the annular limiting groove is composed of a plurality of hemispherical grooves, the second base plate is provided with a lifting groove opposite to the hemispherical grooves, a hemispherical fixture block which is in lifting fit clamping connection with the lifting groove is arranged in the lifting groove, the hemispherical fixture block is connected with the hemispherical grooves, and one side, away from the hemispherical grooves, of the hemispherical fixture block is connected with the bottom side of the lifting groove through a spring in a compression state.
Compared with the prior art, the beneficial effects of the utility model are that:
(1) the utility model discloses a gyroplane that has solved current positive tricycle running gear when the more level and smooth road surface of road conditions is high-speed, the characteristics of poor stability.
(2) The utility model discloses a rotor main body includes the fuselage, still includes engine, the battery that sets up in the fuselage, and the fuselage upside is equipped with the rotor blade who is connected with engine drive, and the fuselage caudal side is equipped with the screw of being connected with engine drive, and the fuselage caudal side is equipped with the horizontal tail. The inside oil tank that is equipped with the engine intercommunication of fuselage, the oil tank is to the engine fuel feeding, and the engine operation, engine drive screw, tail-rotor rotate, reach the utility model discloses the purpose of taking off.
(3) The utility model discloses a positive tricycle running gear includes two ordinary wheels, an electronic round, and two ordinary round settings are in fuselage moving direction's homonymy, and electronic round is connected with the inside battery of fuselage. The design of electronic round, when the power of switch-on battery and electronic round, the electronic round of positive tricycle running gear can initiatively provide power, drives gyroplane main part and removes, need not to provide extra power.
(4) The utility model discloses a middle part of first bottom plate downside is connected with the one end of annular ka tai, the other end and the second bottom plate joint of annular ka tai. First bottom plate passes through annular ka tai joint with the second bottom plate, makes the relative rotation of first bottom plate, second bottom plate in same plane, when having avoided the relative movement of first bottom plate, second bottom plate, influences the utility model discloses a stability.
(5) The utility model discloses a middle part of first bottom plate downside is connected with the one end of pivot, and inside the other end of pivot was located the second bottom plate, power unit still included the motor of being connected with the battery in the second bottom plate including setting up the first gear at pivot end in the second bottom plate, connected oil and first gear engagement's second gear on the output shaft of motor. The pivot passes through the bearing with the second bottom plate and is connected, and the battery supplies power to the motor, and the motor rotates and drives second gear revolve, and first gear drives first gear revolve, and first gear drives the pivot and rotates, and the pivot drives first bottom plate and rotates, reaches the exchange of rotor main body front and back side, and this in-process has the advantage that the automaticity is strong.
(6) The utility model discloses a middle part of first bottom plate downside is equipped with annular spacing groove, and annular spacing groove comprises a plurality of hemisphere grooves, is equipped with on the second bottom plate with the relative lift groove of hemisphere groove, the lift inslot be equipped with rather than the hemisphere fixture block of lift cooperation joint, hemisphere fixture block meets with hemisphere groove, and one side that hemisphere groove was kept away from to the hemisphere fixture block is through the spring coupling that is in compression state with lift tank bottom side. The quantity of half spherical groove is the even number, when first bottom plate and second bottom plate rotate relatively, first bottom plate extrusion hemisphere fixture block, make first hemisphere fixture block indent lift inslot, when first bottom plate rotated a definite position with the second bottom plate (the offside half spherical groove of initial hemisphere groove), the spring promotes the removal of hemisphere fixture block, make the hemisphere fixture block fall into half spherical inslot, in first bottom plate and second bottom plate certain torque force of relative pivoted, the relative rotation of first bottom plate and second bottom plate has been prevented to the hemisphere fixture block, reach first bottom plate, second bottom plate relative position's is fixed.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a schematic partial cross-sectional view of the first base plate of FIG. 1 interfacing with a second base plate;
FIG. 3 is a bottom view of FIG. 1;
FIG. 4 is a bottom view of the first base plate of FIG. 1;
FIG. 5 is a schematic structural view of the main body of the rotor blade of FIG. 1;
the labels in the figure are: the rotary wing aircraft comprises an aircraft body 1, a first base plate 2, a second base plate 3, an electric wheel 4, a common wheel 5, a battery 6, a horizontal tail 7, an engine 8, a propeller 9, a rotary wing plate 10, an annular limiting groove 11, an annular clamping table 12, a hemispherical groove 13, a rotating shaft 14, a first gear 15, a second gear 16, a motor 17, a hemispherical clamping block 18, a spring 19, a lifting groove 20 and a rotary wing aircraft body 21.
Detailed Description
The present invention will be further described with reference to the accompanying drawings. Embodiments of the present invention include, but are not limited to, the following examples.
Example 1:
the utility model provides a gyroplane convenient to transition is flexible, including gyroplane main part 21, gyroplane main part 21 includes rotor blade 10, one side that rotor blade 10 was kept away from to gyroplane main part 21 is fixed to be equipped with and supports first bottom plate 2 of gyroplane main part 21, one side that first bottom plate 2 kept away from gyroplane main part 21 rotates relatively and is equipped with second bottom plate 3, be equipped with in the second bottom plate 3 and drive 2 pivoted power unit of first bottom plate, one side that first bottom plate 2 was kept away from to second bottom plate 3 is equipped with positive tricycle running gear.
The utility model discloses a principle and effect: the rotorcraft is in a first transition mode, when the rotorcraft runs on a road with complex road conditions, the positive three-wheel traveling mechanism drives the second bottom plate 3 to move, the second bottom plate 3 drives the first bottom plate 2 to move, the first bottom plate 2 drives the rotorcraft main body 21 to rotate, in the moving process, the moving mode of the rotorcraft main body 21 is a positive three-wheel moving mode, the positive three-wheel moving mode has the advantages of being convenient to guide and easy to avoid obstacles (gullies and small obstacles), the rotorcraft in a second transition mode is characterized in that when the rotorcraft runs on a road with smooth road conditions, the power supply of the power mechanism is connected, the power mechanism drives the first bottom plate 2 to rotate on the upper side of the second bottom plate 3, when the front side and the back side of the rotorcraft main body 21 are adjusted oppositely, the power supply of the power mechanism is disconnected, at the moment, the positive three-wheel traveling mechanism is changed into a, second bottom plate 3 drives first bottom plate 2 and removes, and first bottom plate 2 drives gyroplane main part 21 and rotates, at above-mentioned in-process, changes gyroplane main part 21's mobile mode into the tricycle moving mechanism that reverses, and gyroplane main part 21 has the good advantage of stability when carrying out high-speed the removal.
Example 2:
the embodiment is further optimized on the basis of the embodiment 1, and specifically comprises the following steps:
the gyroplane main body 21 comprises a fuselage 1, and further comprises an engine 8 and a battery 6 which are arranged in the fuselage 1, wherein the upper side of the fuselage 1 is provided with a rotor blade 10 in transmission connection with the engine 8, the tail side of the fuselage 1 is provided with a propeller 9 in transmission connection with the engine 8, and the tail side of the fuselage 1 is provided with a horizontal tail 7. The inside oil tank that is equipped with engine 8 intercommunication of fuselage 1, the oil tank is to the fuel feeding of engine 8, and engine 8 operation, engine 8 drive screw 9, the tail-rotor rotates, reach the utility model discloses the purpose of taking off.
As a preferable mode, the right three-wheel traveling mechanism includes two common wheels 5 and one electric wheel 4, the two common wheels 5 are arranged on the same side of the moving direction of the body 1, and the electric wheel 4 is connected with a battery 6 inside the body 1. The design of electric wheel 4, when the power of switch-on battery 6 and electric wheel 4, electric wheel 4 of positive tricycle running gear can initiatively provide power, drives gyroplane main part 21 and removes, need not to provide extra power.
As a preferable mode, the middle part of the lower side of the first bottom plate 2 is connected with one end of an annular clamping table 12, and the other end of the annular clamping table 12 is clamped with the second bottom plate 3. First bottom plate 2 and second bottom plate 3 pass through annular card platform 12 joints, make the relative rotation of first bottom plate 2, second bottom plate 3 in same plane, when having avoided the relative movement of first bottom plate 2, second bottom plate 3, influence the utility model discloses a stability.
As a preferable mode, the middle part of the lower side of the first base plate 2 is connected with one end of a rotating shaft 14, the other end of the rotating shaft 14 is located inside the second base plate 3, the power mechanism comprises a first gear 15 arranged at the end of the rotating shaft 14 in the second base plate 3, and further comprises a motor 17 connected with the battery 6 in the second base plate 3, and an output shaft of the motor 17 is connected with a second gear 16 in which oil is meshed with the first gear 15. The rotating shaft 14 is connected with the second bottom plate 3 through a bearing, the battery 6 supplies power to the motor 17, the motor 17 rotates to drive the second gear 16 to rotate, the second gear 16 drives the first gear 15 to rotate, the first gear 15 drives the rotating shaft 14 to rotate, the rotating shaft 14 drives the first bottom plate 2 to rotate, the front side and the rear side of the gyroplane main body 21 are exchanged, and the gyroplane main body exchange device has the advantage of high automation capability.
As a preferable mode, an annular limiting groove 11 is arranged in the middle of the lower side of the first base plate 2, the annular limiting groove 11 is composed of a plurality of hemispherical grooves 13, a lifting groove 20 opposite to the hemispherical grooves 13 is arranged on the second base plate 3, a hemispherical fixture block 18 which is in lifting fit and clamping connection with the lifting groove 20 is arranged in the lifting groove 20, the hemispherical fixture block 18 is connected with the hemispherical grooves 13, and one side, far away from the hemispherical grooves 13, of the hemispherical fixture block 18 is connected with the bottom side of the lifting groove 20 through a spring 19 in a compression state. The quantity of semicircular groove is the even number, when first bottom plate 2 rotated with second bottom plate 3 relatively, hemisphere fixture block 18 was extruded to first bottom plate 2, make first hemisphere fixture block 18 compress into lift groove 20, when first bottom plate 2 rotated a certain position with second bottom plate 3 (the opposite side hemisphere groove 13 of initial hemisphere groove 13), spring 19 promoted hemisphere fixture block 18 and removed, make hemisphere fixture block 18 fall into hemisphere groove 13, in first bottom plate 2 and the certain torque force of second bottom plate 3 relative rotation, hemisphere fixture block 18 has prevented the relative rotation of first bottom plate 2 with second bottom plate 3, reach first bottom plate 2, the fixed of second bottom plate 3 relative position.
The other parts of this embodiment are the same as embodiment 1, and are not described herein again.
The embodiment of the present invention is the above. The specific parameters in the above embodiments and examples are only for the purpose of clearly showing the verification process of the present invention, and are not used to limit the patent protection scope of the present invention, which is still subject to the claims, and all the equivalent structural changes made by using the contents of the specification and the drawings of the present invention should be included in the protection scope of the present invention.
Claims (6)
1. The utility model provides a gyroplane convenient to transition is flexible, includes gyroplane main part (21), gyroplane main part (21) is including rotor piece (10), its characterized in that, one side that rotor piece (10) were kept away from in gyroplane main part (21) is fixed and is equipped with first bottom plate (2) that support gyroplane main part (21), one side relative rotation that rotor piece (21) were kept away from in first bottom plate (2) is equipped with second bottom plate (3), be equipped with in second bottom plate (3) and drive first bottom plate (2) pivoted power unit, one side that first bottom plate (2) were kept away from in second bottom plate (3) is equipped with positive tricycle running gear.
2. The gyroplane convenient to transition maneuver according to claim 1, wherein the gyroplane body (21) comprises a fuselage (1), and further comprises an engine (8) and a battery (6) arranged in the fuselage (1), the upper side of the fuselage (1) is provided with a rotor blade (10) in transmission connection with the engine (8), the tail side of the fuselage (1) is provided with a propeller (9) in transmission connection with the engine (8), and the tail side of the fuselage (1) is provided with a horizontal tail (7).
3. A rotorcraft for facilitating transition maneuvers according to claim 1, wherein the positive three-wheeled chassis comprises two common wheels (5) and one electric wheel (4), and the two common wheels (5) are arranged on the same side of the fuselage (1) in the moving direction, and the electric wheel (4) is connected to a battery (6) inside the fuselage (1).
4. A rotorcraft convenient to transition maneuver according to claim 1, wherein the middle of the lower side of the first base plate (2) is connected with one end of an annular clamping table (12), and the other end of the annular clamping table (12) is clamped with the second base plate (3).
5. A rotorcraft convenient to transition maneuver according to claim 1 or 2, wherein the middle of the lower side of the first base plate (2) is connected with one end of a rotating shaft (14), the other end of the rotating shaft (14) is located inside the second base plate (3), the power mechanism comprises a first gear (15) arranged at the end of the rotating shaft (14) in the second base plate (3), and further comprises a motor (17) connected with the battery (6) in the second base plate (3), and the output shaft of the motor (17) is connected with a second gear (16) with oil engaged with the first gear (15).
6. The rotorcraft convenient to transition maneuver according to claim 1, wherein the lower side of the first base plate (2) is provided with an annular limiting groove (11) in the middle, the annular limiting groove (11) is composed of a plurality of hemispherical grooves (13), the second base plate (3) is provided with a lifting groove (20) opposite to the hemispherical grooves (13), the lifting groove (20) is internally provided with a hemispherical fixture block (18) which is in lifting fit clamping connection with the lifting groove, the hemispherical fixture block (18) is connected with the hemispherical grooves (13), and one side of the hemispherical fixture block (18) away from the hemispherical grooves (13) is connected with the bottom side of the lifting groove (20) through a spring (19) in a compression state.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921003736.9U CN210191812U (en) | 2019-06-28 | 2019-06-28 | Rotorcraft convenient to transition is flexible |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921003736.9U CN210191812U (en) | 2019-06-28 | 2019-06-28 | Rotorcraft convenient to transition is flexible |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN210191812U true CN210191812U (en) | 2020-03-27 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201921003736.9U Active CN210191812U (en) | 2019-06-28 | 2019-06-28 | Rotorcraft convenient to transition is flexible |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN210191812U (en) |
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2019
- 2019-06-28 CN CN201921003736.9U patent/CN210191812U/en active Active
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