CN221067697U - Anti-tipping amphibious aircraft - Google Patents
Anti-tipping amphibious aircraft Download PDFInfo
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- CN221067697U CN221067697U CN202322792946.3U CN202322792946U CN221067697U CN 221067697 U CN221067697 U CN 221067697U CN 202322792946 U CN202322792946 U CN 202322792946U CN 221067697 U CN221067697 U CN 221067697U
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- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 abstract description 24
- 230000002035 prolonged effect Effects 0.000 abstract description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000007664 blowing Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
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Abstract
The utility model discloses an anti-tipping amphibious aircraft, which comprises an aircraft body, wherein wing plates are symmetrically arranged on the aircraft body, air bags are symmetrically arranged on one side, close to the wing plates, of the aircraft body, the air bags are distributed below the wing plates on the corresponding side, a rotating wing seat is arranged at one end, far away from the aircraft body, of the wing plates, a wing fan capable of lifting along the rotating wing seat is arranged on the rotating wing seat, and a transversely arranged impeller structure is arranged at the bottom of the rotating wing seat. According to the utility model, the two side wing fans can be moved upwards, so that the distance between the side wing fans and the water surface is increased when the aircraft body falls on the water surface, water drops generated when equipment falls on the side wing fans are prevented from splashing, the stability of the side wing fans during operation is ensured, the occurrence of a tipping phenomenon is prevented, and the service life of the equipment during operation is prolonged. When the aircraft is required to run on the water surface, the impeller structure is arranged towards the tail of the aircraft body, so that the forward movement of the aircraft body can be realized after the impeller structure is started.
Description
Technical Field
The utility model relates to the technical field of aircrafts, in particular to an anti-tipping amphibious aircraft.
Background
Aircraft have become commonplace in people's daily lives, such as in agriculture, rescue, and business. Most aircraft are not specially protected due to their water resistance and can cause electrical shorts once they encounter rain or fall into the water. At present, amphibious aircrafts exist, and water surface landing and water surface take-off can be realized.
An amphibious aircraft as in patent publication number CN204586397U, which has the technical scheme key points that: the wing fan comprises a machine body, a machine head, a wing, a front wheel mounting frame, a front wheel, a wing fan power motor, a wing fan adjusting motor, a wing main gear, a wing slave gear, a rear wheel, a rear wing fan power motor, a rear wing fan adjusting motor, a rear wing main gear, a rear wing slave gear, two air bags, a camera, a control system and a battery, wherein the wing, the front wheel mounting frame, the front wheel, the wing fan power motor, the wing fan adjusting motor, the wing main gear and the wing slave gear are all two. The amphibious aircraft has the advantages that amphibious aircraft can be realized, photographing detection and the like can be achieved, the structure is simple, and the cost is low.
However, when the aircraft is in use, the wing fans provide partial power for the aircraft, when the aircraft descends, water surface can form water drops due to impact force generated when the aircraft descends, and the water drops splash on the two wing fans of the aircraft, so that the flying stability is influenced, the occurrence of short circuit is easy to cause, and the service life of equipment is influenced.
Disclosure of utility model
The utility model aims to solve the defects in the prior art and provides an anti-tipping amphibious aircraft.
In order to achieve the above purpose, the present utility model adopts the following technical scheme:
The utility model provides an amphibious aircraft of anti-tipping, includes the aircraft organism, the symmetry is provided with the pterygoid lamina on the aircraft organism, one side symmetry that is close to the pterygoid lamina on the aircraft organism is provided with the gasbag, the gasbag distributes in the below of the pterygoid lamina of corresponding side, the one end that the aircraft organism was kept away from to the pterygoid lamina is equipped with the rotation wing seat, be equipped with the flank fan that can go up and down along the rotation wing seat on the rotation wing seat, the bottom of rotation wing seat is equipped with the impeller structure of transverse arrangement.
As a further description of the above technical solution, the rotating wing seat can rotate within 90 degrees relative to the wing plate, and two extreme positions of the rotating wing seat are parallel to and perpendicular to the length direction of the wing plate respectively.
As a further description of the above technical solution, a rotary driving motor is fixed at one end of the wing plate far away from the aircraft body, and an output shaft of the rotary driving motor penetrates through the wing plate and is connected with the rotary wing seat.
As further description of the technical scheme, the side extending plates are connected to the rotating wing seats, electric push rods which are vertically arranged are arranged on the side extending plates, piston rods of the electric push rods are connected with lifting plates, and the side wing fans are fixed on the lifting plates.
As a further description of the above technical solution, the wing fan is fixed to the lift plate by an annular plate.
As a further description of the above technical solution, a sliding groove is provided on a side wall of the rotating wing seat, and the lifting plate slides in the sliding groove.
The utility model has the following beneficial effects:
1. According to the utility model, through the adjustable protection, the two side wing fans can be moved upwards, so that the distance between the side wing fans and the water surface is increased when the aircraft body falls on the water surface, water drops generated when equipment falls on the side wing fans are prevented from splashing, the stability of the side wing fans during operation is ensured, the occurrence of a tipping phenomenon is prevented, and the service life of the equipment during operation is prolonged.
2. When the aircraft runs on the water surface, the impeller structure can be arranged towards the tail of the aircraft body, so that the aircraft body can move forwards after the impeller structure is started.
Drawings
FIG. 1 is a schematic perspective view of one side of an aircraft body according to the present utility model;
FIG. 2 is a schematic view of a part of the structure of FIG. 1;
Fig. 3 is a schematic structural view of the lift plate of the present utility model.
Legend description: 1. an aircraft body; 2. a wing plate; 3. an air bag; 4. rotating the wing seat; 5. a rotary drive motor; 6. an impeller structure; 7. a sliding groove; 8. an electric push rod; 9. pulling up the plate; 10. a side extension plate; 11. a wing fan; 12. an annular plate; 13. a circular air duct; 14. and a connection hole.
Detailed Description
The following description of the embodiments of the present utility model will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present utility model, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.
Referring to fig. 1-3, an anti-tipping amphibious aircraft comprises an aircraft body 1, wing plates 2 are symmetrically arranged on the aircraft body 1, air bags 3 are symmetrically arranged on one side, close to the wing plates 2, of the aircraft body 1, the air bags 3 are distributed below the wing plates 2 on the corresponding side, one end, far away from the aircraft body 1, of the wing plates 2 is provided with a rotary wing seat 4, the rotary wing seat 4 is provided with a wing fan 11 capable of lifting along the rotary wing seat 4, and the bottom of the rotary wing seat 4 is provided with a transversely arranged impeller structure 6.
The wing plate 2 according to the utility model is based on a laterally symmetrical structural arrangement of the aircraft body 1, so that the structure on the left and right sides of the aircraft body 1 is symmetrical, and only one side of the aircraft body 1 is shown in fig. 1.
The impeller structure 6 is used for realizing the movement of the water surface by means of the rotation of the impeller structure 6 after falling on the water surface; the steering as to the water surface is achieved by means of the differential speed of the two impeller structures 6. The use of the air-bag 3 thus ensures a certain float force after landing on the water surface.
As shown in fig. 1 and fig. 2, the rotary wing seat 4 can rotate within 90 degrees relative to the wing plate 2, and two extreme positions of the rotary wing seat 4 after rotation are respectively parallel to and perpendicular to the length direction of the wing plate 2. The rotary wing seat 4 of the present utility model has two states, the first one is parallel to the length direction of the wing plate 2, and the state is used for flying in the air; the second is perpendicular to the length direction of the wing plate 2, and is used when the ship is sailing on the water surface.
Specifically, one end of the wing plate 2 far away from the aircraft body 1 is fixed with a rotary driving motor 5, and an output shaft of the rotary driving motor 5 penetrates through the wing plate 2 and then is connected with the rotary wing seat 4.
As shown in fig. 2, the rotating wing seat 4 is connected with a side extension plate 10, an electric push rod 8 arranged vertically is installed on the side extension plate 10, a piston rod of the electric push rod 8 is connected with a lifting plate 9, and the side wing fan 11 is fixed on the lifting plate 9. The electric push rod 8 drives the lifting plate 9 to move, so that the upper and lower positions of the wing fans 11 relative to the aircraft body 1 can be adjusted, the height of the wing fans 11 from the water surface can be adjusted before the wing fans fall on the water surface, the water drops caused by air blowing can be prevented from splashing onto the wing fans 11, the stability during falling is improved, and the phenomenon of tipping is avoided.
The side wing fan 11 is fixed on the lifting plate 9 through an annular plate 12, a plurality of connecting holes 14 distributed along the periphery of the circular air duct 13 are formed in the lifting plate 9, and the annular plate 12 passes through the connecting holes 14 through bolts and is connected with the side wing fan 11. The direct bearing contact surface of the bolt of the utility model is landed on the annular plate 12, thereby minimizing damage to the lift plate 9.
In order to facilitate the guiding of the lifting plate 9 in the vertical sliding manner, as shown in fig. 2, a sliding groove 7 is provided on the side wall of the rotating wing seat 4, and the lifting plate 9 slides in the sliding groove 7.
The axial direction of the impeller structure 6 is parallel to the length direction of the lifting plate 9, so that the impeller structure 6 is in a non-working state as shown in fig. 2 when flying in normal air, and can follow the rotation of the rotary wing seat 4 after falling onto the water surface, the axial direction of the impeller structure 6 faces the tail of the aircraft body 1, and the aircraft body 1 can be driven to move forwards by means of the rotation of the impeller structure 6.
Specifically, as shown in fig. 3, the lifting plate 9 is provided with a circular air duct 13, and the side wing fans 11 are coaxially installed at the circular air duct 13.
Finally, it should be noted that: the foregoing description is only illustrative of the preferred embodiments of the present utility model, and although the present utility model has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that modifications may be made to the embodiments described, or equivalents may be substituted for elements thereof, and any modifications, equivalents, improvements or changes may be made without departing from the spirit and principles of the present utility model.
Claims (9)
1. An anti-roll-over amphibious aircraft comprising an aircraft body (1), characterized in that: the wing plate structure is characterized in that wing plates (2) are symmetrically arranged on the aircraft body (1), one end, away from the aircraft body (1), of each wing plate (2) is provided with a rotary wing seat (4), each rotary wing seat (4) is provided with a wing fan (11) capable of lifting along the rotary wing seat (4), and the bottom of each rotary wing seat (4) is provided with a transversely arranged impeller structure (6).
2. An anti-roll-over amphibious aircraft according to claim 1, wherein: the rotating wing seat (4) can rotate within a range of 90 degrees relative to the wing plate (2), and two limit positions of the rotating wing seat (4) after rotation are respectively parallel to and perpendicular to the length direction of the wing plate (2).
3. An anti-roll-over amphibious aircraft according to claim 1, wherein: one end of the wing plate (2) far away from the aircraft body (1) is fixed with a rotary driving motor (5), and an output shaft of the rotary driving motor (5) penetrates through the wing plate (2) and then is connected with the rotary wing seat (4).
4. An anti-roll-over amphibious aircraft according to claim 1, wherein: the rotating wing seat (4) is connected with an electric push rod (8), a piston rod of the electric push rod (8) is connected with a lifting plate (9), and the flank fan (11) is fixed on the lifting plate (9).
5. An anti-roll-over amphibious aircraft according to claim 4, wherein: the flank fans (11) are fixed on the lifting plate (9) through annular plates (12).
6. An anti-roll-over amphibious aircraft according to claim 4, wherein: the side wall of the rotating wing seat (4) is provided with a sliding groove (7), and the lifting plate (9) slides in the sliding groove (7).
7. An anti-roll-over amphibious aircraft according to claim 4, wherein: the axial direction of the impeller structure (6) is parallel to the length direction of the lifting plate (9).
8. An anti-roll-over amphibious aircraft according to claim 5, wherein: the lifting plate (9) is provided with a circular air duct (13), and the side wing fans (11) are coaxially arranged at the circular air duct (13).
9. An anti-roll-over amphibious aircraft according to claim 8, wherein: the lifting plate (9) is provided with a plurality of connecting holes (14) distributed along the periphery of the circular air duct (13), and the annular plate (12) passes through the connecting holes (14) through bolts and is connected with the side wing fans (11).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322792946.3U CN221067697U (en) | 2023-10-17 | 2023-10-17 | Anti-tipping amphibious aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322792946.3U CN221067697U (en) | 2023-10-17 | 2023-10-17 | Anti-tipping amphibious aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN221067697U true CN221067697U (en) | 2024-06-04 |
Family
ID=91251191
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202322792946.3U Active CN221067697U (en) | 2023-10-17 | 2023-10-17 | Anti-tipping amphibious aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN221067697U (en) |
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2023
- 2023-10-17 CN CN202322792946.3U patent/CN221067697U/en active Active
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