Floating mechanism of aircraft

Abstract

The utility model is applicable to the field of aircrafts, and provides a floating mechanism of an aircraft and the aircraft, the floating mechanism comprises a main floating unit arranged at the bottom of the aircraft, and balance floating units arranged at the bottom of the aircraft and around the main floating unit. The utility model aims to solve the technical problem that an aircraft in the prior art cannot take off, land and float-stop on water.

Description

Technical Field

[0001] The utility model belongs to the field of aircrafts, and particularly relates to a floating mechanism of an aircraft. Background Art

[0002] At present, multi-rotor aircrafts or compound-wing aircrafts on the market can only take off and land on land, and there is no aircraft that can take off and land on water yet. However, in various application environments of such aircrafts, water applications play an important role, and taking off and landing on water can greatly expand the application scenarios of aircrafts in such environments. Therefore, there is still a technical gap in the takeoff and landing of vertical takeoff and landing aircrafts on water.

[0003] Generally, vertical takeoff and landing aircrafts will adopt skid-type landing gears, or bracket-type landing gears evolved from skid-type landing gears. This type of landing gear cannot achieve takeoff and landing on water. To solve this shortcoming, by using its own appearance and structural characteristics, a method of combining a central floating hemisphere with evenly distributed balance floating balls on the outside is adopted to achieve the function of takeoff and landing on water in addition to takeoff and landing on land. Summary of the Utility Model

[0004] The purpose of the utility model is to provide a floating mechanism of an aircraft, aiming to solve the technical problem that the existing aircrafts cannot achieve takeoff, landing and floating on water.

[0005] The utility model is realized as follows: A floating mechanism of an aircraft, the floating mechanism includes a main floating unit arranged at the bottom of the aircraft, and a balance floating unit arranged at the bottom of the aircraft and surrounding the main floating unit.

[0006] A further technical solution of the utility model is: The main floating unit includes a floating body with a hollow structure; the main floating unit further includes a plurality of partition plates arranged inside the floating body and crisscrossed horizontally and vertically, and a sealing cover covering the floating body; the balance floating unit includes a floating ball retracting and extending part, and balance floating balls arranged on the floating ball retracting and extending part.

[0007] A further technical solution of the utility model is: The floating ball retracting and extending part includes a connecting rod with one end hinged to the aircraft through a rotating shaft, a connecting rod with one end hinged to the other end of the connecting rod through a rotating shaft, a one-way joint rocker with one end hinged to the connecting rod through a rotating shaft, a rocker operating arm with the middle part rigidly connected to the other end of the one-way joint rocker through a rocker rotating shaft, a servo arm with both ends hinged to both ends of the rocker operating arm through a ball head push-pull rod, and a servo arranged on the aircraft and the output shaft of which is connected to the middle part of the servo arm; or the balance floating unit includes a floating ball support rod arranged at the bottom of the aircraft, and balance floating balls arranged on the floating ball support rod.

[0008] A further technical solution of the present utility model is that the main floating unit is hemispherical; there are at least three balance floating units; the connecting rod, the link rod and the one-way joint rocker are "I"-shaped rods or "H"-shaped rods.

[0009] Another object of the present utility model is to provide an aircraft, and the aircraft includes the floating mechanism described above.

[0010] Another object of the present utility model is to provide an aircraft, and the aircraft includes the floating mechanism described above, and further includes a seat arranged in the middle of the aircraft.

[0011] A further technical solution of the present utility model is that the aircraft further includes a cockpit cover arranged on the aircraft and covering the seat.

[0012] Another object of the present utility model is to provide an aircraft, and the aircraft includes the floating mechanism described above, and further includes a land support part arranged at the bottom of the aircraft.

[0013] Another object of the present utility model is to provide an aircraft, and the aircraft includes the floating mechanism described above, and further includes a land support part arranged at the bottom of the aircraft and a seat arranged in the middle of the aircraft.

[0014] A further technical solution of the present utility model is that the aircraft further includes a cockpit cover arranged on the aircraft and covering the seat.

[0015] The beneficial effects of the present utility model are as follows: This floating mechanism enables the aircraft to take off, land and float on water through the cooperation of the main floating unit and the balance floating unit, filling the gap that the aircraft cannot take off, land and float on water. By arranging a land support part at the bottom of the aircraft, the aircraft can take off and land on both water and land, perfectly combining water takeoff and landing with land takeoff and landing, realizing amphibious compatibility on the same aircraft. In addition, a seat can be arranged on the aircraft to turn the aircraft into a manned aircraft, and a cockpit cover is arranged to protect the passengers. The floating mechanism also has good stability, flexible layout, simple structure, mature forming and assembly processes, is easy to implement, has a long service life and low failure rate. Description of the Drawings

[0016] Figure 1 is an installation explosion diagram of a floating mechanism of an aircraft provided by an embodiment of the present utility model;

[0017] Figure 2 is a cross-sectional view of the main floating unit of a floating mechanism of an aircraft provided by an embodiment of the present utility model;

[0018] Figure 3It is a structural diagram of a balance floating unit of a floating mechanism of an aircraft provided by an embodiment of the present utility model;

[0019] Figure 4 It is a classic position structural diagram of a balance floating unit of a floating mechanism of an aircraft provided by an embodiment of the present utility model;

[0020] Figure 5 It is a fully retracted state diagram of a balance floating unit of a floating mechanism of an aircraft provided by an embodiment of the present utility model;

[0021] Figure 6 It is a semi-expanded state diagram of a balance floating unit of a floating mechanism of an aircraft provided by an embodiment of the present utility model;

[0022] Figure 7 It is a fully expanded state diagram of a balance floating unit of a floating mechanism of an aircraft provided by an embodiment of the present utility model;

[0023] Figure 8 It is a structure of an aircraft provided by an embodiment of the present utility model Figure 1 ;

[0024] Figure 9 It is a structure of an aircraft provided by an embodiment of the present utility model Figure 2 ;

[0025] Figure 10 It is a structure of an aircraft provided by an embodiment of the present utility model Figure 3 ;

[0026] Figure 11 It is a structure of an aircraft provided by an embodiment of the present utility model Figure 4 ;

[0027] Figure 12 It is a structure of an aircraft provided by an embodiment of the present utility model Figure 5 ;

[0028] Figure 13 It is a structure of an aircraft provided by an embodiment of the present utility model Figure 6 。 Detailed implementation manners

[0029] Reference signs: 1 - main floating unit; 2 - balance floating unit; 3 - floating body; 4 - partition board; 5 - sealing cover; 6 - floating ball retracting and releasing part; 7 - balance floating ball; 8 - connecting rod; 9 - connecting link; 10 - one-way joint rocker; 11 - rocker operating arm; 12 - servo arm; 13 - servo; 14 - ball head push-pull rod; 15 - seat; 16 - cockpit cover; 17 - land support part; 18 - bottom plate; 19 - aircraft.

[0030] Such as Figure 1As shown in FIGS. -7, the floating mechanism of an aircraft provided by the present utility model includes a main floating unit 1 disposed at the bottom of the aircraft 19, and a balance floating unit 2 disposed at the bottom of the aircraft 19 and surrounding the main floating unit 1. Through the cooperation of the main floating unit 1 and the balance floating unit 2, the aircraft 19 can take off, land and float on water, filling the gap that the aircraft 19 cannot take off, land and float on water. The role of the main floating unit 1 is to provide sufficient buoyancy for the aircraft 19, so that the aircraft 19 will not sink into the water due to its own weight, while the balance floating unit 2 plays a role in maintaining the balance of the aircraft 19 after landing on water, so that the aircraft 19 will not tilt due to unstable center of gravity.

[0031] As Figure 2 shown, the main floating unit 1 is hemispherical. The main floating unit 1 includes a floating body 3 with a hollow structure, several partition plates 4 arranged horizontally and vertically inside the floating body 3, and a sealing cover 5 covering the floating body 4. The overall shape of the main floating unit 1 is hemispherical to ensure good balance on water, and it is rigidly connected to the bottom plate 18 of the aircraft 19 by bolts or screws. The main floating unit 1 is made of high-toughness plastic material. The floating body 3 with a hollow structure has several partition plates 4 arranged horizontally and vertically to divide its interior into several sealed compartments to enhance rigidity and strength. As the main buoyancy-providing component, the size and the height position of the waterline of the main floating unit 1 depend on the take-off weight of the aircraft 19. Through calculation, it is easy to calculate the required drainage volume. After obtaining the drainage volume, the height position of the waterline on the main floating unit 1 can be easily calculated. The sealing cover 5 is provided to ensure the sealing performance of the main floating unit 1.

[0032] For the balance floating unit 2, there are two options. One is the retractable type, and the other is the fixed type. Which specific method to adopt can be set according to requirements. The balance floating unit 2 has at least three and is evenly arranged under the housing surrounding the main floating unit 1 to ensure the horizontal stability of the aircraft 19 floating on the water surface. Moreover, the balance floating unit 2 can also be set according to the configuration of the aircraft 19. For example, if the aircraft 19 is a six-axis one, six are configured; if it is an eight-axis one, eight are configured, and so on.

[0033] As Figure 3As shown in Figs. -7, the structure of the retractable balance floating unit 2 is as follows: It includes a floating ball retracting and extending part 6, and a balance floating ball 7 arranged on the floating ball retracting and extending part 6. The floating ball retracting and extending part 6 includes a connecting rod 8 whose one end is hinged to the aircraft 19 through a rotating shaft, a connecting rod 9 whose one end is hinged to the other end of the connecting rod 8 through a rotating shaft, a one-way joint rocker 10 whose one end is hinged to the connecting rod 9, a rocker operating arm 11 whose middle part is rigidly connected to the other end of the one-way joint rocker 10 through a rocker rotating shaft, a servo arm 12 whose two ends are hinged to the two ends of the rocker operating arm 11 through a ball head push-pull rod 14, and a servo 13 arranged on the aircraft 19 and whose output shaft is connected to the middle part of the servo arm 12. The balance floating unit 2 generates power through the servo 13, making the output shaft drive the servo arm 12 to rotate forward and backward. At the same time, a parallelogram structure is formed by the servo arm 12, the ball head push-pull rods 14 on both sides, and the rocker operating arm 11. The four vertices of the parallelogram are four rotating pairs. The forward and backward rotation of the servo arm 12 transfers the power to the rocker operating arm 11 through the formed parallelogram structure, thereby realizing the rotation of the rocker operating arm 11 on the one-way joint rocker 10, and further driving the connecting rod 9 to drive the connecting rod frame 8 to rotate along the rotating shaft hinged to the aircraft 19. Since the balance floating ball 7 is fixed at the distal end of the connecting rod 8, the retracting and extending action of the balance floating ball 7 is realized. In addition, the one-way joint rocker 10 also plays a limiting role, only allowing the connecting rod 9 to rotate within a certain angle range. When it is collinear with the connecting rod 9, it will stop rotating, playing a protective role.

[0034] As Figure 4 As shown in Figs. -7, under the control of the floating ball retracting and extending part 6, the retractable balance floating unit 2 can be in multiple positions. The two most typical positions are the first position of the fully retracted balance floating ball 7 and the third position of the fully extended balance floating ball 7. The second position of the balance floating ball 7 is an intermediate position. The lengths of the various rods of the floating ball retracting and extending part 6 can be calculated according to the actual requirements of the height position of the balance floating ball 7, that is, the height position of the balance floating ball 7 can be adjusted by adjusting the lengths of the various rods, so that the aircraft 19 is at the best height during takeoff, landing, and floating on water.

[0035] The connecting rod 8, the connecting rod 9, and the one-way joint rocker 10 are "I"-shaped rods or "H"-shaped rods, which are specifically selected according to requirements. The "I"-shaped rod is lighter in weight and has general strength in horizontal torsional and bending resistance, while the "H"-shaped rod is heavier in weight, but it has stronger horizontal torsional and bending resistance.

[0036] The structure of the fixed balance floating unit 2 is as follows: It includes a floating ball support rod (not shown in the figure) arranged at the bottom of the aircraft 19, and a balance floating ball 7 arranged on the floating ball support rod. This structure is relatively simple. The floating ball support rod is rigidly connected to the bottom of the aircraft 19 and can be connected at various angles. Then, the balance floating ball 7 can be fixed on the floating ball support rod. The length of the floating ball support rod is calculated and determined according to the weight of the aircraft and the depth of the waterline, so that the aircraft 19 takes off, lands, and floats at the optimal height on the water.

[0037] As Figure 13 shown, an aircraft, the aircraft 19 includes the floating mechanism described above. By installing the floating mechanism on the aircraft, the aircraft 19 can take off, land, and float on the water. It can also be equipped with a lighting system for advertising, performances, emergency search and rescue, etc.

[0038] As Figure 8 、 9 、12 shown, an aircraft, the aircraft 19 includes the floating mechanism described above, and also includes a seat 15 arranged at the central part of the aircraft 19, and a cockpit cover 16 arranged on the aircraft 19 and covering the seat 15. By installing the floating mechanism on the aircraft 19, the aircraft can take off, land, and float on the water. A seat 15 can also be installed on the aircraft 19 to make the aircraft 19 a waterborne manned aircraft, realizing waterborne manned takeoff, landing, and floating. And by installing the cockpit cover 16 to protect the internal personnel. The seat 15 is installed on the bottom plate 18 of the aircraft 19. Equipping the seat 15 can be used for sightseeing, transportation, emergency rescue, etc. It can also be equipped with a lighting system for advertising, performances, emergency search and rescue, etc.

[0039] As Figure 10 shown, an aircraft, the aircraft 19 includes the floating mechanism described above, and also includes a land support part 17 arranged at the bottom of the aircraft. By installing the floating mechanism on the aircraft 19, the aircraft 19 can take off, land, and float on the water. By installing the land support part 17, the aircraft 19 can further take off, land, and land on land, thus realizing the amphibious use of the aircraft 19 on water and land. The land support part 17 can be a support leg or a support frame. It can also be equipped with a lighting system for advertising, performances, emergency search and rescue, etc.

[0040] As Figure 11As shown in the figure, an aircraft, the aircraft 19 includes the floating mechanism described above, and also includes a land support part 17 arranged at the bottom of the aircraft, a seat 15 arranged at the central part of the aircraft 19, and a cockpit cover 16 arranged on the aircraft 19 and covering the seat 15. By installing a floating mechanism on the aircraft 19, the aircraft 19 can take off, land and float on water. By installing the land support part 17, the aircraft 19 can further take off, land and touch down on land, thus realizing the amphibious use of the aircraft 19 on water and land. The land support part 17 can be a support leg or a support frame. A seat 15 can also be installed on the aircraft 19 to make the aircraft 19 an amphibious manned aircraft, realizing amphibious manned use. And by installing the cockpit cover 16 to protect the personnel inside. The seat 15 is installed on the bottom plate 18 of the aircraft 19. Equipping with the seat 15 can be used for sightseeing, transportation, emergency rescue, etc. A lighting system can also be equipped for advertising, performance, emergency search and rescue, etc.

[0041] This floating mechanism realizes that the aircraft can take off, land and float on water through the cooperation of the main floating unit and the balance floating unit, filling the blank that the aircraft cannot take off, land and float on water. By arranging a land support part at the bottom of the aircraft, the amphibious take-off and landing of the aircraft on water and land are realized, making the take-off and landing on water and the take-off and landing on land perfectly combined, and realizing the amphibious compatibility on the same aircraft. In addition, a seat can be arranged on the aircraft to turn the aircraft into a manned aircraft, and a cockpit cover is arranged to protect the passengers. The floating mechanism also has good stability, flexible layout, simple structure, mature forming and assembly processes, is easy to realize, has a long service life and a low failure rate.

[0042] The above are only the preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A floating mechanism for an aircraft, characterized in that, The floating mechanism includes a main floating unit disposed at the bottom of the aircraft, and balance floating units disposed at the bottom of the aircraft and around the main floating unit; the main floating unit includes a floating body with a hollow structure; the main floating unit further includes a plurality of partition plates disposed inside the floating body and crisscrossed horizontally and vertically, and a sealing cover covering the floating body; the balance floating unit includes a floating ball retracting and extending part, and balance floating balls disposed on the floating ball retracting and extending part.

2. The floating mechanism according to claim 1, characterized in that, The floating ball retracting and extending part includes a connecting rod with one end hinged to the aircraft through a rotating shaft, a connecting rod with one end hinged to the other end of the connecting rod through a rotating shaft, a one-way joint rocker with one end hinged to the connecting rod, a rocker operating arm rigidly connected to the other end of the one-way joint rocker through a rocker rotating shaft in the middle, a servo arm with both ends hinged to both ends of the rocker operating arm through a ball head push-pull rod, and a servo disposed on the aircraft and having an output shaft connected to the middle of the servo arm; or the balance floating unit includes a floating ball support rod disposed at the bottom of the aircraft, and balance floating balls disposed on the floating ball support rod.

3. The floating mechanism according to claim 2, characterized in that, The main floating unit is hemispherical; there are at least three balance floating units; the connecting rod, the connecting rod and the one-way joint rocker are "I"-shaped rods or "H"-shaped rods.

4. An aircraft, characterized in that, The aircraft includes the floating mechanism according to any one of claims 1-3.

5. An aircraft, characterized in that, The aircraft includes the floating mechanism according to any one of claims 1-3, and further includes a seat disposed at the central part of the aircraft.

6. The aircraft according to claim 5, wherein The aircraft further includes a cockpit cover disposed on the aircraft and covering the seat.

7. An aircraft, characterized in that, The aircraft includes the floating mechanism according to any one of claims 1-3, and further includes a land support part disposed at the bottom of the aircraft.

8. An aircraft, characterized in that, The aircraft includes the floating mechanism according to any one of claims 1-3, and further includes a land support part disposed at the bottom of the aircraft, and a seat disposed at the central part of the aircraft.

9. The aircraft according to claim 8, characterized in that, The aircraft further includes a cockpit cover disposed on the aircraft and covering the seat.

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