CN113247259A - Tandem wing device and tandem wing aircraft - Google Patents
Tandem wing device and tandem wing aircraft Download PDFInfo
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- CN113247259A CN113247259A CN202110047401.2A CN202110047401A CN113247259A CN 113247259 A CN113247259 A CN 113247259A CN 202110047401 A CN202110047401 A CN 202110047401A CN 113247259 A CN113247259 A CN 113247259A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/08—Aircraft not otherwise provided for having multiple wings
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C23/00—Influencing air flow over aircraft surfaces, not otherwise provided for
- B64C23/005—Influencing air flow over aircraft surfaces, not otherwise provided for by other means not covered by groups B64C23/02 - B64C23/08, e.g. by electric charges, magnetic panels, piezoelectric elements, static charges or ultrasounds
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
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Abstract
The invention discloses a tandem wing device and a tandem wing aircraft, wherein the tandem wing device comprises: the device comprises an annular motion device and a plurality of wings arranged on the annular motion device; the annular motion device can actively perform annular cyclic motion; several wings can move circularly with the annular moving device, so that the wings obtain lift force or simultaneously obtain lift force and thrust force. The tandem wing device aircraft has the advantages of simple structure, no closed ring formed by multiple wings, small interference among the wings, large lift-drag ratio, no annular duct with a large windward section, small flight resistance, and capability of superposing the running speed of the aircraft and the circulating motion speed of the wings so as to obtain larger lift force during low-speed flight.
Description
Technical Field
The present invention relates to aircraft, and more particularly to a tandem wing apparatus and a tandem wing aircraft.
Background
Fixed wing aircraft, helicopters, multi-rotor aircraft are common aircraft. The fixed wing aircraft has a large wing lift-drag ratio, but generally has one or two main wings, the lift area is small, large lift is difficult to provide at low speed, and the fixed wing aircraft cannot vertically take off and land; the wing cannot provide forward power by itself, an additional propeller is needed to provide the forward power, the propelling power of the propeller is lost, and the energy utilization efficiency is low. The helicopter and the multi-rotor aircraft can take off and land vertically but have small lift-drag ratio and low energy utilization efficiency.
Chinese patent publication No. CN201710222033.4 discloses a novel electromagnetic-driven tandem wing aircraft, which includes a plurality of tandem wings in a large duct, the tandem wings form a closed ring surface, the tandem wings are suspended on an electromagnetic track, and the tandem wings rotate circularly to provide lift force for the aircraft. Although the aircraft can also take off and land vertically, the magnetic suspension structure of the aircraft is complex, the requirement on manufacturing is high, and the cost is high; according to a karman-plus-Boolean transportation efficiency diagram, the lift-drag ratio of the existing helicopter is about 4, and the multiple wings of the electromagnetic drive tandem wing aircraft form a closed ring, so that the interference among the wings is large, the lift force is reduced and the resistance is increased, the lift-drag ratio is less than 4, and the energy consumption is high; the culvert has a large windward section and large in-flight resistance; the lift force is proportional to the square of the speed of the wing, and the flight speed of the tandem wing aircraft and the cyclic operation speed of the wing cannot be superposed, so that the lift force cannot be further increased. The novel electromagnetic drive tandem wing aircraft operation tandem wing device can not provide thrust, needs other propellers, and the propeller has not only increased the aircraft area of facing the wind, has increased the resistance moreover, and power loss has in addition reduced energy utilization.
Disclosure of Invention
In view of the above technical problems, the present invention provides a novel tandem wing apparatus and a tandem wing aircraft.
In order to achieve the technical purpose, the invention adopts the technical scheme that:
a tandem wing apparatus, comprising:
the device comprises an annular motion device and a plurality of wings arranged on the annular motion device;
the annular motion device can circularly move;
the plurality of wings can circularly move along with the annular moving device, so that the tandem wing device obtains lift force or simultaneously obtains lift force and thrust force.
The endless moving device includes:
an annular conveying unit and at least two rotating wheels;
the annular conveying unit is wound on the rotating wheel to form an annular motion structure;
and a plurality of wing fixing pieces for fixing the wings are fixedly arranged on the annular conveying unit.
The tandem wing device frame is fixedly connected with the machine body through a connecting piece and is rotatably connected with the rotating wheel through a bearing.
The tandem wing device frame is provided with a track parallel to the conveying direction of the annular conveying unit through a track connecting piece, one surface of the wing fixing piece is fixed with the annular conveying unit, and the other surface of the wing fixing piece is fixedly connected with the wing;
the left and right bilateral symmetry of wing mounting is equipped with the orientation two engaging lugs that the track direction extends the setting, be equipped with on the engaging lug be used for with track rolling contact's gyro wheel.
The annular conveying unit is an annular conveying belt, an annular conveying chain or an annular conveying rope.
And wing end baffles for limiting the circumferential flow of the wing tip and weakening the downward washing flow to obtain a larger lift-drag ratio are arranged at two ends of the wing.
The annular motion device is an annular linear motor device, an annular track is used as a stator, a plurality of rotors are arranged around the annular track, and each rotor is fixedly connected with a wing.
A wing partition board is arranged between the upper square wing positioned above the annular motion device and the lower square wing positioned below the annular motion device and close to the upper wing, the bottom of the wing partition board is fixedly connected with the tandem wing device frame through a partition board bracket, and the upper surface of the wing partition board has a parallel spacing distance from the lower surface of the upper square wing;
or a wing partition plate is arranged above the upper wing above the annular motion device, the bottom of the wing partition plate is fixedly connected with the tandem wing device frame through a partition plate bracket, and the lower surface of the wing partition plate is spaced from the upper surface of the upper square wing in parallel;
or a wing partition plate is arranged between a lower wing positioned below the annular motion device and an upper wing positioned above the annular motion device and close to the lower wing, the wing partition plate is fixedly connected with the tandem wing device frame through a partition plate bracket, and the lower surface of the wing partition plate is parallel to the upper surface of the lower wing at a spacing distance;
or the wing partition plates are arranged below the lower wings and fixedly connected with the tandem wing device frame through the partition plate brackets, and the upper surfaces of the wing partition plates are spaced from the lower surfaces of the lower wings in parallel at intervals.
The invention further discloses a tandem wing aircraft, which comprises an aircraft body and one or more tandem wing devices arranged on the aircraft body;
the aircraft also comprises a propeller which is arranged on the aircraft body and used for providing part or all of the flight power of the aircraft.
Compared with a novel electromagnetic drive serial wing aircraft, the serial wing device and the serial wing aircraft have the following beneficial effects:
firstly, according to a Karman-Gabulier transportation efficiency diagram, the lift-drag ratio of the conventional fixed wing transport plane is about 18, although the front wing and the rear wing have some interference, the front wing and the rear wing move in a translation mode relative to the air like the fixed wing, and the aspect ratio can be larger by adding the multi-wing, so that the high lift-drag ratio similar to that of the fixed wing transport plane can be obtained, and the resistance in flight can be reduced.
Second, the upper wing and the lower wing in the tandem wing device of the present invention are two vertical rows with different heights, and do not form a closed loop, so that the interference is greatly reduced, and a large lift-drag ratio can be obtained.
And thirdly, the aircraft is not provided with a large windward section annular duct, and the flight resistance is small.
And fourthly, the speed of the wing relative to the air is equal to the speed of the annular motion of the tandem wing device plus the flying speed of the aircraft, the lift force of the aircraft is in direct proportion to the square of the speed, and the invention can obtain larger lift force at smaller flying speed.
The invention can realize that a forward lift force component is generated when the wings provide lift force by setting the head-tail height difference of the tandem wings or in other ways, thereby providing the propulsive force when the aircraft flies, reducing the propeller resistance of an additional propeller and improving the energy utilization efficiency.
The invention does not need a complex magnetic suspension device, has simple structure, relatively convenient manufacture and low cost.
Drawings
FIG. 1 is a schematic structural view of a tandem wing apparatus embodiment 1 of the present invention;
wherein, 1 is a tandem wing device frame; 2 is a conveying belt; 3 is a belt wheel; 4 is a wing fixing piece; 5 is a wing;
FIG. 2 is a front view of a tandem wing apparatus embodiment 1 of the present invention;
FIG. 3 is a front view of a tandem wing apparatus embodiment 2 of the present invention;
FIG. 4 is a schematic structural view of a tandem wing apparatus embodiment 3 of the present invention;
wherein 6 is a baffle bracket; 7 is a wing end baffle plate;
FIG. 5 is a schematic structural view of a tandem wing apparatus embodiment 4 of the present invention;
wherein 8 is a wing clapboard; 9 is a clapboard bracket;
FIG. 6 is a schematic view of the vertical placement of the wing partitions;
FIG. 7 is a schematic structural view of a tandem wing apparatus embodiment 5 of the present invention;
FIG. 8 is a schematic structural view of a tandem wing apparatus embodiment 6 of the present invention;
FIG. 9 is a schematic view of the speed at which the wing travels down;
FIG. 10 is a schematic view of the geometry of a toroidal motion device;
FIG. 11 is a schematic structural view of a tandem wing apparatus embodiment 7 of the present invention;
FIG. 12 is a front view of a tandem wing apparatus embodiment 7 of the present invention;
wherein, 10 is a roller; 11 is a track; 12 is a track connecting piece;
FIG. 13 is a schematic structural view of a tandem wing aircraft of the present invention;
FIG. 14 is a front view of the tandem wing aircraft of the present invention in flight.
Detailed Description
The tandem wing apparatus and the tandem wing aircraft according to the present invention will be described in further detail with reference to the drawings and specific embodiments.
Example 1
Fig. 1 is a schematic structural view of a tandem wing apparatus according to embodiment 1 of the present invention.
Fig. 2 is a front view of the tandem wing apparatus of the present invention according to embodiment 1.
Comprises a tandem wing device frame 1, a conveying belt 2, a belt wheel 3, a wing fixing piece 4, a wing 5 and a driving device. The wing fixing piece 4 fixes a wing 5 on the conveying belt 2, the driving device drives the belt wheel 3 to rotate so as to drive the conveying belt 2 to rotate, and the wing 5 fixed on the conveying belt 2 and the conveying belt 2 move circularly together.
For the sake of convenience of explanation, an example will now be given. Assuming that the air flow rate is zero, the right side in fig. 2 is the flying direction, and the direction is the forward direction and the reverse direction, the aircraft flies at 20m/s, the conveyor belt rotates counterclockwise at 30m/s, the lower wing moves in the forward direction, and the upper wing moves in the reverse direction (in the present invention, the upper wing moves to the upper side and the lower wing moves to the lower side), at this time, the speed of the lower wing relative to the air is the aircraft running speed plus the wing circulating movement speed is 50m/s, at this time, the lower wing speed is far greater than the flying speed and the wing circulating movement speed, the lift force is proportional to the square of the speed, and the lift force is larger when the speed is larger. The speed of the upper wing relative to the air is the speed of the cyclic motion of the wing minus the flying speed of the aircraft and is-10 m/s; the upper wing generates a downward direction of lift, which is collectively referred to herein as negative lift; the negative lift is also proportional to the square of the speed, and is small because the upper wing has a low speed of travel relative to the air. The upper square wing and the lower square wing form two longitudinal rows with a certain distance, and do not form a closed ring, so that the interference is greatly reduced. The operation of the wing is mobile, not the rotation of the helicopter, and the lift-drag ratio is large. The tandem wing device does not have an annular duct with a large windward section, and has small flight resistance. The wheel may of course also be a driving wheel which can be actively rotated.
In order to further reduce the inter-wing interference, the invention may provide that the vertical height of each wing is different, i.e. that each wing is in a set of parallel planes at different heights.
Example 2
Fig. 3 is a front view of a second embodiment of the present invention.
The difference of the first embodiment is that the conveyer belt rotates clockwise, the speed of the upper wing relative to the air is the absolute value of the running speed of the aircraft plus the absolute value of the circulating motion speed of the upper wing, and the upper wing obtains a speed relative to the air which is larger than the circulating running speed and the flying speed, so that a larger lift force is obtained; the lower wing obtains a smaller negative lift.
Example 3
Fig. 4 shows a perspective view of a third embodiment of the invention.
Unlike the first embodiment, the two ends of the wing are respectively provided with a wing end baffle 7 to limit the flow around the wing tip, so that the downwash flow is weakened to obtain a larger lift-drag ratio. One end of the wing end baffle bracket 6 is fixedly connected with the tandem wing device frame 1, and the other end is connected with the wing end baffle 7.
Example 4
Fig. 5 shows a perspective view of a fourth embodiment of the present invention.
The difference with the first embodiment is that a wing partition plate 8 is arranged below the upper wing, the wing partition plate 8 is fixedly connected with the tandem wing device frame 1 through a partition plate support 9, the distance between the wing partition plate 8 and the upper wing is small, so that the lower part of the upper wing is the wing partition plate when the upper wing operates, the lower surface of the upper wing generates negative pressure, the upper surface of the wing partition plate 8 also generates negative pressure, the negative pressures generated by the two surfaces are offset, the negative lift force is further reduced, meanwhile, the arrangement of the wing partition plate 8 also can reduce the wing tip streaming of the upper wing and the lower wing, and the resistance when the wings move is reduced. Of course the wing spacers 8 can also be placed above the upper wing. The tandem wing aircraft can vertically take off due to the arrangement of the wing partition plates, when the tandem wing device is static on the ground, the tandem wings start to circularly move, the wings generate larger lift force when moving to the lower part, the negative lift force can be greatly weakened due to the fact that the tandem wings are close to the wing partition plates when moving to the upper part, along with the acceleration of the circular movement speed, the lift force generated by the tandem wings is increased until the lift force is equal to or exceeds the gravity of the aircraft, the tandem wing aircraft vertically takes off from the ground, the circular movement speed is reduced when landing, the lift force is reduced, and the aircraft falls to the ground. The baffle can produce adverse effect to the lift of below wing, also can set up the wing baffle and divide into two from the centre, and wing baffle support be rotatable coupling, have the pivot on the wing baffle, have the pivot cover on the wing baffle support, take off the back wing baffle and rotate and place perpendicularly as shown in figure 6. Of course, after the two wings take off, the wing partition plate can also move towards the wing tip direction, so that a gap which is slightly smaller than the span length is formed in the middle of the tandem wing device, and the adverse interference of the wing partition plate on the lower wing can also be reduced. Of course, to reduce the adverse effect of the wing baffle on the lift of the underlying wing, the wing baffle may also be made narrower in width in the spanwise direction, or slotted in the middle of the wing baffle.
When the upper wing provides the lift force, a wing partition plate is arranged close to the lower wing or below the lower wing in the annular movement device and between the lower wing and the upper wing; optionally, no wing baffles are provided.
Example 5
Fig. 7 shows a perspective view of a fifth embodiment of the present invention.
In order to ensure that the tandem wing device obtains better transverse stability or further reduce the interference between an upper wing and a lower wing, the invention arranges the wings to be a left wing and a right wing, an included angle is formed between the two wings, and a downward dihedral angle is formed when the wings run to the lower part; it is of course also possible to provide for the wing to be dihedral when running down. When the wing has a reverse angle, the arranged wing partition board is V-shaped or inverted V-shaped. It is of course also possible to provide the wings with a sweep angle to increase lateral stability.
Example 6
Fig. 8 shows a sixth embodiment of the present invention, which is a tandem wing apparatus with a lower head direction and a higher tail direction. The speed diagram of a wing moving to the lower part is shown in fig. 9, assuming that the air flow rate is zero, the right side in fig. 9 is the flight direction, and the positive direction is the positive direction, because the circular motion device in the nose direction is low, the wing moves obliquely downwards in the direction of the speed V2 of the lower part, the motion speed of the aircraft is V1, and the motion speed of the aircraft relative to the air is the combined speed of V1 and V2, so that the air has an oblique upward speed to the wing, the lift force can generate a forward component force, the component force can counteract the resistance of the aircraft in operation, and the component force for further increasing the lift force can provide the whole propelling force of the aircraft. Of course, the method of the present invention for making the wing generate the forward component of the lift force is not limited to making the wing device have a low front and a high back, but can also be implemented by changing the shape of the circular motion device, such as the geometric schematic diagram of the circular motion device shown in fig. 10, where the wing moves obliquely downward in the speed direction of the downward motion, and the lift force generates a forward component.
Example 7
In the embodiment 6, as shown in fig. 11 and 12, in order to prevent the wing from moving upwards too much vertically against the conveyor belt when providing a large lifting force, the wing fixing member 4 is provided with a roller 10, the wing mounting frame 1 is provided with a rail 11, and the rail 11 and the wing mounting frame 1 are fixed together by a rail connecting member 12, so that the lifting force of the wing 5 acts on the rail 11 through the roller 10, thereby limiting the upward or downward movement of the wing 5 and ensuring the smooth operation of the wing 5.
Example 8
Fig. 13 and 14 show an embodiment 7, in which the number of the tandem wing devices is four, the wing partition plates 8 are arranged below the upper wings of the tandem wing devices, the four tandem wing devices are fixed on a frame 13, and each tandem wing device is provided with a set of power system to adjust the balance of the aircraft according to the difference of the circular movement speed. The aircraft is static on the ground, the tandem wing devices circularly move, the aircraft takes off and is separated from the ground along with the increase of the movement speed, the right side direction in the figure 14 is taken as the flight direction of the aircraft, the speed of the front two tandem wings is reduced, the speed of the rear two tandem wings is increased, the aircraft generates a pitching operation to enable the front part to be low and the rear part to be high, and therefore the wings generate a forward component force to overcome air resistance to fly forwards; when the speed needs to be reduced, the speed of the front two tandem wings is increased, the speed of the rear two tandem wings is reduced, the front of the aircraft is raised by one pitching, and the rear of the aircraft is reduced, so that the speed of reducing the propelling force is reduced.
The number of the tandem wings on the aircraft can be flexibly set according to requirements, and 1, 2, 3, 5 and the like can be arranged.
As other embodiments of the present invention, the tandem wing apparatus of the present invention is not limited to the conveyor belt apparatus; can be a chain and chain wheel device, and wings are fixed on the chain and move circularly along with the chain; or can be a steel wire rope, a steel wire rope wheel device, and wings are fixed on the steel wire rope and move circularly along with the steel wire rope; or an annular linear motor device (the linear motor is bent into an annular shape), the annular track is used as a stator, a plurality of rotors are arranged around the annular track, an upper wing is fixed on each rotor, and the wings move annularly along with the rotors.
The stability of the present invention can be set with reference to the stability of existing aircraft, such as horizontal tail, vertical tail, etc. The steering of the invention can refer to the steering rudder device of the existing fixed wing aircraft.
The present invention has been described in connection with the preferred embodiments, but the present invention is not limited to the embodiments disclosed above, and is intended to cover various modifications, equivalent combinations, which are made in accordance with the spirit of the present invention.
Claims (10)
1. A tandem wing apparatus, characterized by: the method comprises the following steps:
the device comprises an annular motion device and a plurality of wings arranged on the annular motion device;
the annular motion device can circularly move;
the plurality of wings can circularly move along with the annular moving device, so that the tandem wing device obtains lift force or simultaneously obtains lift force and thrust force.
2. The tandem wing arrangement of claim 1, wherein said circular motion arrangement comprises:
an annular conveying unit and at least two rotating wheels;
the annular conveying unit is wound on the rotating wheel to form an annular motion structure;
and a plurality of wing fixing pieces for fixing the wings are fixedly arranged on the annular conveying unit.
3. The tandem wing device according to claim 2, further comprising a tandem wing device frame, wherein the tandem wing device frame is fixedly connected with the machine body through a connecting piece, and the tandem wing device frame is rotatably connected with the rotating wheel through a bearing.
4. The tandem wing device according to claim 3, wherein the tandem wing device frame is provided with a rail arranged parallel to the conveying direction of the annular conveying unit through a rail connecting member, one surface of the wing fixing member is fixed to the annular conveying unit, and the other surface of the wing fixing member is fixedly connected to the wing;
the left and right bilateral symmetry of wing mounting is equipped with the orientation two engaging lugs that the track direction extends the setting, be equipped with on the engaging lug be used for with track rolling contact's gyro wheel.
5. The tandem wing apparatus according to claim 2, wherein the endless conveyor unit is an endless conveyor belt, an endless conveyor chain, or an endless conveyor rope.
6. The tandem wing apparatus according to claim 2, wherein both ends of the wing are provided with wing end baffles for restricting the tip-around flow and attenuating the downwash flow to obtain a large lift-drag ratio.
7. The tandem wing apparatus according to claim 1, wherein the endless moving means is an endless linear motor apparatus, the endless track is a stator, and a plurality of rotors are disposed around the endless track, each rotor having a wing fixedly attached thereto.
8. The tandem wing arrangement of claim 1, wherein a wing spacer is disposed adjacent the upper wing between the upper wing above the endless moving device and the lower wing below the endless moving device, the bottom of the wing spacer being fixedly connected to the tandem wing arrangement frame by a spacer bracket, the upper surface of the wing spacer being spaced parallel to the lower surface of the upper wing;
or a wing partition plate is arranged above the upper wing above the annular motion device, the bottom of the wing partition plate is fixedly connected with the tandem wing device frame through a partition plate bracket, and the lower surface of the wing partition plate is spaced from the upper surface of the upper square wing in parallel;
or a wing partition plate is arranged between a lower wing positioned below the annular motion device and an upper wing positioned above the annular motion device and close to the lower wing, the wing partition plate is fixedly connected with the tandem wing device frame through a partition plate bracket, and the lower surface of the wing partition plate is parallel to the upper surface of the lower wing at a spacing distance;
or the wing partition plates are arranged below the lower wings and fixedly connected with the tandem wing device frame through the partition plate brackets, and the upper surfaces of the wing partition plates are spaced from the lower surfaces of the lower wings in parallel at intervals.
9. A tandem wing aircraft comprising an aircraft body and one or more tandem wing apparatus as claimed in any one of claims 1 to 8 provided on the aircraft body.
10. The tandem wing aircraft of claim 9, further comprising a propeller disposed on the aircraft body for providing some or all of the flight power of the aircraft.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010040836X | 2020-01-15 | ||
| CN202010040836.XA CN111152926A (en) | 2020-01-15 | 2020-01-15 | Tandem wing device and tandem wing aircraft |
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| Publication Number | Publication Date |
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| CN113247259A true CN113247259A (en) | 2021-08-13 |
| CN113247259B CN113247259B (en) | 2022-11-18 |
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| CN202010040836.XA Pending CN111152926A (en) | 2020-01-15 | 2020-01-15 | Tandem wing device and tandem wing aircraft |
| CN202110047401.2A Active CN113247259B (en) | 2020-01-15 | 2021-01-14 | Tandem wing device and tandem wing aircraft |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202010040836.XA Pending CN111152926A (en) | 2020-01-15 | 2020-01-15 | Tandem wing device and tandem wing aircraft |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114476067A (en) * | 2020-10-23 | 2022-05-13 | 符海玉 | Tandem rotor wing device and tandem wing aircraft |
| CN114476068A (en) * | 2020-10-27 | 2022-05-13 | 符海玉 | Double-layer tandem wing device and double-layer tandem wing aircraft |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101056795A (en) * | 2004-10-26 | 2007-10-17 | 朴南洙 | Acceleration system for link belt-mounted ship |
| KR20100009971U (en) * | 2009-04-02 | 2010-10-12 | 김병만 | A propelling equipment |
| CN104071319A (en) * | 2013-03-26 | 2014-10-01 | 孟杰 | Propelling method using reverse power wing and relevant tool system thereof |
-
2020
- 2020-01-15 CN CN202010040836.XA patent/CN111152926A/en active Pending
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2021
- 2021-01-14 CN CN202110047401.2A patent/CN113247259B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101056795A (en) * | 2004-10-26 | 2007-10-17 | 朴南洙 | Acceleration system for link belt-mounted ship |
| US20080214070A1 (en) * | 2004-10-26 | 2008-09-04 | Nam Soo Park | Acceleration System For Link Belt-Mounted Ship |
| KR20100009971U (en) * | 2009-04-02 | 2010-10-12 | 김병만 | A propelling equipment |
| CN104071319A (en) * | 2013-03-26 | 2014-10-01 | 孟杰 | Propelling method using reverse power wing and relevant tool system thereof |
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|---|---|
| CN113247259B (en) | 2022-11-18 |
| CN111152926A (en) | 2020-05-15 |
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