Floating aircraft with wind resistance reducing function

Abstract

The invention discloses a floating aircraft with a wind resistance reducing function, and relates to the technical field of floating aircrafts. Comprising a floating assembly, a passenger compartment, a cockpit, a vector driving device, a power coupling shaft, a dynamic balance assembly, a cable cage assembly and a pipe ring, the floating assembly adopts an air bag structure in a dish-shaped sharp edge shape, a traditional empennage is removed, an acute angle design is adopted at the edge of an oblate air bag, the wind resistance of the floating aircraft is reduced in all directions, and airflow interference is reduced. The flying stability of the floating aircraft is improved by utilizing multiple groups of vector propellers, and multi-directional adjustment in the thrust direction is realized through deflection of the first vector ring and the second vector ring, so that the functions of lifting and turning of the aircraft are achieved. When the attitude of the floating aircraft is inclined, the control system judges the inclination position and the inclination angle of the floating aircraft according to the position and the size of the piezoelectric ceramic electric signal, so that judgment of attitude information of the floating aircraft is completed, and assistance is provided for attitude adjustment.

Description

Technical Field

[0001] The present invention relates to the technical field of floating aircraft, in particular to a floating aircraft with the function of reducing wind resistance. Background Art

[0002] Aerial vehicles are characterized by stable high-altitude hovering and flexible maneuverability. They offer advantages such as low energy consumption and operating costs, while also providing passengers with a safe and comfortable flight experience. They are widely used in environmental monitoring, meteorological data collection, communications relay, military reconnaissance, advertising, and scientific research. They also show significant potential in emergency rescue, tourism, and regional transportation. Equipped with advanced equipment, these vehicles enable real-time information transmission and regional coverage, playing a key role in disaster warning, border monitoring, and complex terrain exploration.

[0003] However, traditional hovercraft are susceptible to meteorological conditions such as wind speed and airflow during flight. Due to their high ratio of wind resistance to power, the aircraft is large, making steering difficult and significantly limiting maneuverability. Furthermore, traditionally designed aircraft have high side wind resistance, and their tail is easily affected by the wind, often failing to successfully perform missions under unfavorable wind direction and speed conditions. At low speeds, directional control achieved through vertical and horizontal tails is limited in effectiveness and may even negatively impact flight control due to tail displacement caused by wind. Furthermore, attitude tilt caused by uneven passenger weight distribution or other external interference is difficult to effectively adjust. Summary of the Invention

[0004] The purpose of the present invention is to provide a floating aircraft with the function of reducing wind resistance, so as to solve the problems raised in the prior art.

[0005] To achieve the above-mentioned objectives, the present invention provides the following technical solutions: a floating aircraft with the function of reducing wind resistance, comprising a floating assembly, a cable cage assembly installed in the floating assembly, a pipe ring installed on the floating assembly, a tension net installed between the pipe ring and the cable cage assembly, a power coupling shaft provided at the center of the cable cage assembly, vector drive devices rotatably installed at both ends of the power coupling shaft, a passenger cabin installed on the power coupling shaft, a dynamic balancing assembly installed at the bottom of the passenger cabin, and a cockpit installed on the power coupling shaft.

[0006] The cockpit houses a control system for the entire aerostat. The tension net, comprised of several cables and chains, supports the primary load and disperses pressure to prevent concentrated sinking on the airbag surface. The cable cage assembly connects and supports the aerostat.

[0007] Furthermore, the vector drive device includes an electric swivel, which is installed on the power coupling shaft. The first vector ring is symmetrically installed on both sides of the electric swivel, the second vector ring is rotatably installed on the first vector ring, the steering motor is installed on the first vector ring, the steering motor output shaft is horizontally arranged, the steering motor output shaft passes through the first vector ring and is connected to the second vector ring, the vector propeller is rotatably installed on the second vector ring, the drive motor is installed on the second vector ring, and the drive motor output shaft is connected to the vector propeller.

[0008] The two sets of vector drive devices contain a total of four sets of vector propellers, one above the other. The electric swivel is used to drive the entire set of vector drive devices to rotate around the power coupling shaft, and the output shaft of the steering motor can drive the second vector ring to rotate around the horizontal axis within the first vector ring. When the airborne aircraft flies horizontally, the steering motor drives the vector propeller on the second vector ring to deflect horizontally, and the drive motor drives the vector propeller to rotate and generate horizontal thrust, thereby driving the airborne aircraft to move horizontally. By driving the vector drive device to deflect by the electric swivel, the direction of the horizontal thrust can be adjusted to achieve the purpose of changing direction.

[0009] When the airborne vehicle rises, the steering motor drives the vector propeller on the second vector ring to deflect downward, causing the vector propeller to generate downward thrust, and the aircraft rises under the reaction of the thrust.

[0010] When the hovercraft descends, the steering motor drives the vector propeller upward, and the vector propeller generates an upward thrust. Under the reaction of the thrust, the aircraft descends.

[0011] Furthermore, the dynamic balancing assembly includes a balancing gear ring and a liquid regulator. The liquid regulator is installed at the bottom of the passenger compartment, the balancing gear ring is installed at the bottom of the passenger compartment, a connecting rod is installed on one side of the liquid regulator, and a connecting hard pipe is connected to the other side of the liquid regulator. One end of the connecting hard pipe is connected to a balancer, and the balancer is engaged with the balancing gear ring for transmission. A counterweight block is installed at one end of the connecting rod, and a counterweight gear is rotatably installed on the counterweight block. The counterweight gear is engaged with the balancing gear ring for transmission, and a balancing assistant is installed in the power connecting shaft. The balancing assistant is located at the bottom of the liquid regulator.

[0012] The counterweight and counterweight gear are used to balance the weight of the balancer, so that the weight at both ends of the dynamic balance assembly is balanced in the initial state. The connecting tube and the connecting rod are both made of rigid materials and have the same weight.

[0013] Furthermore, the liquid regulator includes a liquid regulating box, which is installed at the bottom of the passenger compartment. An electric telescopic rod is installed in the liquid regulating box, and a hydraulic disc is installed on the output shaft of the electric telescopic rod. The hydraulic disc is slidably installed in the liquid regulating box. A liquid storage chamber is provided between the hydraulic disc and the bottom of the liquid regulating box. The liquid storage chamber is filled with high-density liquid. The liquid storage chamber is connected to the connecting hard pipe. A linkage ring is rotatably installed on the liquid regulating box, and the linkage ring is connected to the connecting hard pipe. An electric valve is provided at the connection between the linkage ring and the connecting hard pipe.

[0014] A sealing element is provided between the linkage ring and the liquid regulating box.

[0015] Furthermore, the balancer includes a balancing shell, a balancing motor is installed in the balancing shell, a rotating gear is installed on the output shaft of the balancing motor, the rotating gear is engaged with the balancing gear ring for transmission, an elastic airbag is installed at the bottom end of the balancing shell, and the balancing shell is connected to the connecting hard pipe.

[0016] After receiving the tilt signal from the airborne vehicle, the control system activates the balancing motor. The output shaft of the balancing motor drives the rotating gear, which in turn drives the balancer to rotate around the balancing gear. The balancer, via the connecting tube, drives the interlocking ring, which, via the connecting rod, drives the counterweight. Together, the counterweight gear on the counterweight rotates around the balancing gear ring. This process continues until the counterweight rotates to the down position, at which point the balancer is in the up position. The control system activates the electric valve and the electric telescopic rod. The rod's output shaft drives the hydraulic disc downward, forcing a high-density liquid through the connecting tube into the balancer's elastic airbag. The airbag, filled with high-density liquid, expands until the weight in the up position and the weight in the down position are balanced. The airborne vehicle is then returned to its normal position, achieving dynamic balance adjustment.

[0017] Furthermore, the balancing assistant includes an auxiliary shell, which can be installed with an auxiliary rope, a hanging ball is installed at the bottom end of the auxiliary rope, a number of transmission piston rods are slidably installed in the auxiliary shell, an arc plate is installed at one end of the transmission piston rod, and the several arc plates form a circular ring, a number of piezoelectric ceramics are installed in the auxiliary shell, a number of conductive plates are slidably installed in the auxiliary shell, the conductive plates are fitted with the piezoelectric ceramics, a compression chamber is provided between the conductive plates and the transmission piston rod, and the compression chamber is filled with a compressed medium.

[0018] When the airborne vehicle tilts due to gravity imbalance or other external forces, the balance assistant tilts along with the airborne vehicle, and the hanging ball remains vertical due to the influence of gravity. The other components in the auxiliary shell are relatively tilted with the hanging ball. At this time, the hanging ball will contact the arc plate in the sinking position. The greater the tilt angle, the greater the pressure of the hanging ball on the arc plate. After the arc plate is squeezed by the hanging ball, it drives the transmission piston rod to squeeze the compressed medium in the compression chamber. After the compressed medium is pressurized, the pressure in the compression chamber increases, and the pressure acts on the conductive plate. The conductive plate transmits the pressure to the piezoelectric ceramic. The piezoelectric ceramic generates an electrical signal under pressure. The control system determines the tilt position and tilt angle of the airborne vehicle based on the position and size of the electrical signal.

[0019] Furthermore, the floating component is made of an airbag, which has a dish-shaped sharp edge.

[0020] The dished sharp-edge design eliminates the traditional tail wing and adopts a sharp-angle design on the edge of the oblate airbag to reduce the airbag wind resistance and airflow interference in all directions.

[0021] Compared with the prior art, the present invention has the following beneficial effects: The aerostat utilizes a sharp-edged, disc-shaped airbag structure, eliminating traditional tail fins and employing sharp angles on the edges of the oblate airbag. This reduces wind resistance and airflow disturbances in all directions. Multiple sets of vector propellers enhance the aerostat's flight stability. Deflection of the first and second vector rings allows for multi-directional adjustment of thrust direction, enabling the aerostat to ascend, descend, and change direction.

[0022] 2. When the attitude of the airborne vehicle is tilted, the hanging ball will squeeze the arc plate in the sinking position. The arc plate will convert the squeezing into pressure on the compression medium. The conductive sheet will transmit the pressure to the piezoelectric ceramic. The control system will determine the tilt position and tilt angle of the airborne vehicle based on the position and size of the piezoelectric ceramic electrical signal, thereby completing the judgment of the attitude information of the airborne vehicle and providing assistance for attitude adjustment.

[0023] 3. Use the balancing motor to move the balancer to the upward position. By injecting high-density liquid into the balancer to change the weight of the balancer, gravity compensation is performed on the upward position, so that the attitude of the floating aircraft returns to the right position and the purpose of dynamic balance adjustment is achieved. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 It is an overall three-dimensional diagram of the floating aircraft of the present invention; Figure 2 A perspective view of the floating aircraft of the present invention; Figure 3 is a perspective view of the vector drive device of the present invention; Figure 4is a perspective view of the dynamic balancing assembly of the present invention; Figure 5 is a perspective view of the liquid regulator of the present invention; Figure 6 is a perspective view of the balancer of the present invention; Figure 7 For the present invention Figure 5 A partial enlarged view of area A in the middle; Figure 8 is a three-dimensional diagram of the balance aid of the present invention; Figure 9 For the present invention Figure 8 A partial enlarged view of area B in the middle.

[0025] In the figure: 1. Float assembly; 2. Passenger cabin; 3. Cockpit; 4. Vector drive device; 5. Power coupling shaft; 6. Dynamic balancing assembly; 7. Cable cage assembly; 8. Pipe ring; 41. Electric swivel; 42. First vector ring; 43. Second vector ring; 44. Steering motor; 45. Drive motor; 46. Vector propeller; 61. Balance gear ring; 62. Connecting hard pipe; 63. Balancer; 64. Counterweight; 65. Counterweight gear; 66. Liquid regulator; 67. Connecting rod; 68, balancing assistant; 661, liquid regulating box; 662, connecting ring; 663, hydraulic disc; 664, electric telescopic rod; 665, liquid storage chamber; 631, balancing shell; 632, balancing motor; 633, rotating gear; 634, elastic airbag; 681, auxiliary shell; 682, auxiliary rope; 683, hanging ball; 684, curved plate; 685, transmission piston rod; 686, piezoelectric ceramic; 687, conductive plate; 688, compression chamber. DETAILED DESCRIPTION

[0026] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0027] like Figures 1-9 As shown, the present invention provides a technical solution for a floating aircraft with a wind resistance reduction function: it includes a floating component 1, a cable cage component 7 is installed in the floating component 1, a pipe ring 8 is installed on the floating component 1, a tension net is installed between the pipe ring 8 and the cable cage component 7, a power coupling shaft 5 is provided at the center of the cable cage component 7, vector drive devices 4 are rotatably installed at both ends of the power coupling shaft 5, a passenger cabin 2 is installed on the power coupling shaft 5, a dynamic balance component 6 is installed at the bottom end of the passenger cabin 2, and a cockpit 3 is installed on the power coupling shaft 5.

[0028] The cockpit 3 houses a control system for controlling the entire aerostat. A tension net, comprised of several cables and chains, supports the primary load and distributes pressure to prevent concentrated sinking on the airbag surface. A cable cage assembly 7 connects and supports the aerostat.

[0029] The vector drive device 4 includes an electric swivel 41, which is installed on the power coupling shaft 5. A first vector ring 42 is symmetrically installed on both sides of the electric swivel 41. A second vector ring 43 is rotatably installed on the first vector ring 42. A steering motor 44 is installed on the first vector ring 42. The output shaft of the steering motor 44 is horizontally arranged. The output shaft of the steering motor 44 passes through the first vector ring 42 and is connected to the second vector ring 43. A vector propeller 46 is rotatably installed on the second vector ring 43. A drive motor 45 is installed on the second vector ring 43, and the output shaft of the drive motor 45 is connected to the vector propeller 46.

[0030] The two sets of vector drive devices 4 include a total of four sets of vector propellers 46 in the upper and lower parts. The electric swivel 41 is used to drive the entire set of vector drive devices 4 to rotate around the power coupling shaft 5. The output shaft of the steering motor 44 can drive the second vector ring 43 to rotate around the horizontal axis within the first vector ring 42. The dynamic balancing assembly 6 includes a balancing gear ring 61 and a liquid regulator 66. The liquid regulator 66 is installed at the bottom end of the passenger compartment 2. The balancing gear ring 61 is installed at the bottom end of the passenger compartment 2. A connecting rod 67 is installed on one side of the liquid regulator 66. The other side of the liquid regulator 66 is connected to a connecting hard pipe 62. One end of the connecting hard pipe 62 is connected to a balancer 63. The balancer 63 is engaged with the balancing gear ring 61 for transmission. A counterweight block 64 is installed at one end of the connecting rod 67. A counterweight gear 65 is rotatably installed on the counterweight block 64. The counterweight gear 65 is engaged with the balancing gear ring 61 for transmission. A balancing assistant 68 is installed in the power connecting shaft 5. The balancing assistant 68 is located at the bottom end of the liquid regulator 66.

[0031] The counterweight block 64 and the counterweight gear 65 are used to balance the weight of the balancer 63, so that the weight of both ends of the dynamic balance assembly 6 is balanced in the initial state. The connecting hard pipe 62 and the connecting rod 67 are both made of rigid materials and have the same weight.

[0032] The liquid regulator 66 includes a liquid regulating tank 661, which is mounted at the bottom of the passenger compartment 2. An electric telescopic rod 664 is mounted within the liquid regulating tank 661. A hydraulic disc 663 is mounted on the output shaft of the electric telescopic rod 664. The hydraulic disc 663 is slidably mounted within the liquid regulating tank 661. A liquid storage chamber 665 is located between the hydraulic disc 663 and the bottom of the liquid regulating tank 661. The liquid storage chamber 665 is filled with a high-density liquid and communicates with the connecting rigid tube 62. A linkage ring 662 is rotatably mounted on the liquid regulating tank 661 and connected to the connecting rigid tube 62. An electric valve is installed at the junction of the linkage ring 662 and the connecting rigid tube 62. A seal is provided between the linkage ring 662 and the liquid regulating tank 661.

[0033] The balancer 63 includes a balancing shell 631, in which a balancing motor 632 is installed. A rotating gear 633 is installed on the output shaft of the balancing motor 632. The rotating gear 633 is engaged with the balancing gear ring 61 for transmission. An elastic airbag 634 is installed at the bottom end of the balancing shell 631, and the balancing shell 631 is connected to the connecting hard tube 62.

[0034] The balancing assistant 68 includes an auxiliary shell 681, which can be installed with an auxiliary rope 682, and a hanging ball 683 is installed at the bottom end of the auxiliary rope 682. A number of transmission piston rods 685 are slidably installed in the auxiliary shell 681, and an arc plate 684 is installed at one end of the transmission piston rod 685. The arc plates 684 form a circular ring. A number of piezoelectric ceramics 686 are installed in the auxiliary shell 681, and a number of conductive plates 687 are slidably installed in the auxiliary shell 681. The conductive plates 687 are fitted with the piezoelectric ceramics 686. A compression chamber 688 is provided between the conductive plate 687 and the transmission piston rod 685, and the compression chamber 688 is filled with a compressed medium.

[0035] The floating component 1 is made of an airbag with a sharp-edged disc shape. The disc-shaped sharp-edged shape eliminates the traditional tail and adopts a sharp angle design on the edge of the oblate airbag to reduce the airbag's wind resistance and airflow interference in all directions.

[0036] The present invention operates as follows: When the airborne vehicle is flying horizontally, the steering motor 44 drives the vector propeller 46 on the second vector ring 43 to deflect horizontally. The drive motor 45 rotates the vector propeller 46 and generates horizontal thrust, thereby driving the airborne vehicle to move horizontally. The electric swivel 41 drives the vector drive device 4 to deflect, adjusting the direction of the horizontal thrust to achieve the purpose of changing direction. When the airborne vehicle ascends, the steering motor 44 drives the vector propeller 46 on the second vector ring 43 to deflect downward, causing the vector propeller 46 to generate downward thrust, and the thrust reaction causes the airborne vehicle to ascend. When the airborne vehicle descends, the steering motor 44 drives the vector propeller 46 upward, causing the vector propeller 46 to generate upward thrust, and the thrust reaction causes the airborne vehicle to descend.

[0037] When the airborne vehicle tilts due to gravity imbalance or other external forces, the balance assistant 68 tilts along with the airborne vehicle, and the hanging ball 683 remains vertical due to the influence of gravity. The other components in the auxiliary shell 681 are relatively tilted with the hanging ball 683. At this time, the hanging ball 683 will contact the arc plate 684 in the sunken position. The greater the tilt angle, the greater the pressure of the hanging ball 683 on the arc plate 684. After the arc plate 684 is squeezed by the hanging ball 683, it drives the transmission piston rod 685 to squeeze the compressed medium in the compression chamber 688. After the compressed medium is pressurized, the pressure in the compression chamber 688 increases, and the pressure acts on the conductive sheet 687. The conductive sheet 687 transmits the pressure to the piezoelectric ceramic 686. The piezoelectric ceramic 686 generates an electrical signal under pressure. The control system determines the tilt position and tilt angle of the airborne vehicle based on the position and size of the electrical signal.

[0038] After receiving the tilt signal from the airborne vehicle, the control system activates the balancing motor 632. The output shaft of the balancing motor 632 drives the rotating gear 633 to rotate. The rotating gear 633 drives the balancer 63 to rotate around the balancing gear. The balancer 63 drives the interlocking ring 662 via the connecting rigid tube 62 to rotate. The interlocking ring 662 drives the counterweight 64 via the interlocking rod 67 to rotate. The counterweight gear 65 on the counterweight 64 rotates around the balancing gear ring 61. When the counterweight 64 rotates to the sunken position and the balancer 63 is in the tilted position, the control system activates the electric valve and the electric telescopic rod 664. The output shaft of the electric telescopic rod 664 drives the hydraulic disc 663 downward, pressing a high-density liquid through the connecting rigid tube 62 into the elastic airbag 634 of the balancer 63. The elastic airbag 634 is filled with the high-density liquid and expands until the weight in the tilted position and the weight in the sunken position reach equilibrium. The airborne vehicle is then returned to its normal position, achieving the purpose of dynamic balance adjustment.

[0039] It will be apparent to those skilled in the art that the present invention is not limited to the details of the exemplary embodiments described above and that the invention can be embodied in other specific forms without departing from the spirit or essential characteristics of the invention. Therefore, the embodiments should be considered in all respects as illustrative and non-restrictive, and the scope of the invention is defined by the appended claims, not the foregoing description, and all variations within the meaning and range of equivalents of the claims are intended to be included therein. Any reference sign in a claim should not be construed as limiting the claim to which it relates.

Claims

1. A floating aircraft with a wind resistance reduction function, characterized by: The floating aircraft comprises a floating component (1), a cable cage component (7) is installed in the floating component (1), a pipe ring (8) is installed on the floating component (1), a tension net is installed between the pipe ring (8) and the cable cage component (7), a power coupling shaft (5) is provided at the center of the cable cage component (7), vector drive devices (4) are rotatably installed at both ends of the power coupling shaft (5), a passenger cabin (2) is installed on the power coupling shaft (5), a dynamic balancing component (6) is installed at the bottom end of the passenger cabin (2), and a cockpit (3) is installed on the power coupling shaft (5).

2. The floating aircraft with wind resistance reduction function according to claim 1, characterized in that: The vector drive device (4) includes an electric swivel (41), the electric swivel (41) is mounted on a power coupling shaft (5), a first vector ring (42) is symmetrically mounted on both sides of the electric swivel (41), a second vector ring (43) is rotatably mounted on the first vector ring (42), a steering motor (44) is mounted on the first vector ring (42), an output shaft of the steering motor (44) is horizontally arranged, the output shaft of the steering motor (44) passes through the first vector ring (42) and is connected to the second vector ring (43), a vector propeller (46) is rotatably mounted on the second vector ring (43), a drive motor (45) is mounted on the second vector ring (43), and an output shaft of the drive motor (45) is connected to the vector propeller (46).

3. The floating aircraft with wind resistance reduction function according to claim 1, characterized in that: The dynamic balancing assembly (6) includes a balancing gear ring (61) and a liquid regulator (66), wherein the liquid regulator (66) is mounted at the bottom end of the passenger compartment (2), and the balancing gear ring (61) is mounted at the bottom end of the passenger compartment (2). A connecting rod (67) is mounted on one side of the liquid regulator (66), and a connecting hard pipe (62) is connected to the other side of the liquid regulator (66). One end of the connecting hard pipe (62) is connected to a balancer (63), and the balancer (63) is meshed with the balancing gear ring (61) for transmission. A counterweight block (64) is mounted on one end of the connecting rod (67), and a counterweight gear (65) is rotatably mounted on the counterweight block (64). The counterweight gear (65) is meshed with the balancing gear ring (61) for transmission. A balancing auxiliary device (68) is mounted in the power coupling shaft (5), and the balancing auxiliary device (68) is located at the bottom end of the liquid regulator (66).

4. The floating aircraft with wind resistance reduction function according to claim 5, characterized in that: The liquid regulator (66) includes a liquid regulating box (661), the liquid regulating box (661) is installed at the bottom end of the passenger compartment (2), an electric telescopic rod (664) is installed in the liquid regulating box (661), a hydraulic disc (663) is installed on the output shaft of the electric telescopic rod (664), the hydraulic disc (663) is slidably installed in the liquid regulating box (661), a liquid storage chamber (665) is provided between the hydraulic disc (663) and the bottom end of the liquid regulating box (661), the liquid storage chamber (665) is filled with high-density liquid, the liquid storage chamber (665) is communicated with the connecting hard pipe (62), a linking ring (662) is rotatably installed on the liquid regulating box (661), the linking ring (662) is connected to the connecting hard pipe (62), and an electric valve is provided at the connection between the linking ring (662) and the connecting hard pipe (62).

5. The floating aircraft with wind resistance reduction function according to claim 5, characterized in that: The balancer (63) includes a balancing housing (631), a balancing motor (632) is installed in the balancing housing (631), a rotating gear (633) is installed on the output shaft of the balancing motor (632), the rotating gear (633) is meshed with the balancing gear ring (61) for transmission, an elastic airbag (634) is installed at the bottom end of the balancing housing (631), and the balancing housing (631) is connected to the connecting hard pipe (62).

6. The floating aircraft with wind resistance reduction function according to claim 5, characterized in that: The balancing assistant (68) includes an auxiliary shell (681), the auxiliary shell (681) can be installed with an auxiliary rope (682), the bottom end of the auxiliary rope (682) is installed with a hanging ball (683), a plurality of transmission piston rods (685) are slidably installed in the auxiliary shell (681), one end of the transmission piston rod (685) is installed with an arc plate (684), and a plurality of the arc plates (684) form a ring, a plurality of piezoelectric ceramics (686) are installed in the auxiliary shell (681), a plurality of conductive plates (687) are slidably installed in the auxiliary shell (681), the conductive plates (687) are fitted with the piezoelectric ceramics (686), a compression chamber (688) is provided between the conductive plate (687) and the transmission piston rod (685), and the compression chamber (688) is filled with a compressed medium.

7. The floating aircraft with wind resistance reduction function according to claim 1, characterized in that: The floating component (1) is made of an airbag, and the airbag is in a dish-shaped sharp-edge shape.

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