Hybrid energy based long endurance aircraft

Abstract

The application relates to the field of aircraft technology, in particular to a long-distance endurance aircraft based on hybrid energy, which comprises a bottom shell, the inside of the bottom shell is provided with an azimuth adjusting assembly, and the top of the azimuth adjusting assembly is provided with a linkage steering assembly; the azimuth adjusting assembly comprises four sleeve shells, the bottoms of the four sleeve shells are fixedly connected to the bottom inner wall of the bottom shell and are arranged in a ring array, and a hollow pipe is fixedly connected between the bottom inner wall of the bottom shell and the top inner wall of the sleeve shell. The long-distance endurance aircraft based on hybrid energy can change the direction of the aircraft during flight by energizing the electromagnetic coil to make the electromagnetic coil generate electromagnetic force to adsorb the circular block on the disc to make the disc tilt, thereby changing the driving direction of the aircraft. When the electromagnetic coil generates electromagnetic force, the reaction speed is fast, the efficiency is high, the efficiency of the traditional four-axle aircraft is reduced, and the endurance of the aircraft is improved.

Description

Technical Field

[0001] This invention relates to the field of aircraft technology, specifically to a long-range endurance aircraft based on hybrid kinetic energy. Background Technology

[0002] With the rapid development of general aviation in China, various types of aircraft have emerged. Currently, these aircraft primarily rely on battery power for their own operation, limiting their ability to travel long distances and perform long-range missions. This poses a significant challenge to the practical application of aircraft over long distances. While recharging after long flights or during flights can be achieved through the power grid, off-grid charging systems are necessary for remote areas not covered by the grid. Off-grid charging systems similar to those used for car charging exist, but for aircraft, landing is susceptible to wind conditions, and ordinary charging stations cannot meet the requirements for safe and precise landing.

[0003] Existing quadcopters increase the rotation speed by increasing the power of two adjacent rotors, thereby changing the tilt angle and direction of travel. This process consumes a lot of energy and is not conducive to the flight range. In addition, the energy replenishment method of traditional quadcopters during flight is relatively simple, which is also not conducive to the flight range. To address this, we propose a long-range flight vehicle based on hybrid kinetic energy. Summary of the Invention

[0004] The purpose of this invention is to provide a long-range endurance aircraft based on hybrid kinetic energy, to solve the problems mentioned in the background art, namely, that existing quadcopters increase the rotation speed by increasing the power of two adjacent rotors to change the tilt angle and thus the direction of travel. This process consumes a lot of energy, which is detrimental to the aircraft's endurance, and the energy replenishment method of traditional quadcopters during flight is relatively singular, which is also detrimental to the aircraft's endurance. To achieve the above objective, this invention provides the following technical solution: a long-range endurance aircraft based on hybrid kinetic energy, including a base shell, an orientation adjustment component is disposed inside the base shell, and a linkage steering component is disposed on the top of the orientation adjustment component; the orientation adjustment component includes four shells, the bottoms of the four shells are fixedly connected to the bottom inner wall of the base shell and arranged in a ring array, a hollow tube is fixedly connected between the bottom inner wall of the base shell and the top inner wall of the shell, an electromagnetic coil is fixedly sleeved between the side surface of the hollow tube and the inner ring surface of the shell, and four sliding pillars are fixedly connected to the bottom inner wall of the base shell and arranged in a ring array. A limiting plate is fixedly connected to the top of the sliding column. A sliding piece is movably sleeved on the side surface of the sliding column. A spring is movably connected between the bottom of the sliding piece and the inner wall of the bottom of the bottom shell, and the spring is movably sleeved on the side surface of the sliding column. A disc is movably connected between the bottom of the limiting plate and the top of the sliding piece. The disc has four cross grooves arranged in a circular array inside. The sliding column slides through the disc via the cross grooves. A column is fixedly connected to the middle of the inner wall of the bottom of the bottom shell. A first ball is fixedly connected to the top of the column. A first movable sleeve is movably sleeved on the surface of the first ball, and the top of the first movable sleeve is fixedly connected to the middle of the bottom of the disc.

[0005] More preferably, the linkage steering assembly includes a steering column, the bottom of which is fixedly connected to the center of the top of the disk, and a limiting disc fixedly connected to the top of the steering column. An extension handle is movably sleeved on the outer side of the steering column. A groove is formed on one side of the extension handle, and the groove is located directly below the limiting disc. A triangular block is fixedly connected to the inner wall of the groove. A movable block is fixedly connected to one end of the extension handle, and a Z-shaped rod is fixedly connected to the top of the movable block. The cross groove allows the sliding column to limit the disk while sliding. The edges of the limiting disc and the sliding disc on opposite sides are arc-shaped, which facilitates sliding on the disk and prevents the limiting disc and the sliding disc from getting stuck in the cross groove, making the aircraft smoother when changing direction. The diameter of the groove is larger than the diameter of the Z-shaped rod and the steering column, so that the steering column has a sufficient deflection angle to provide force to the extension handle when changing direction, so that the extension handle rotates in the opposite direction around the steering column, ensuring that the fan blades always face the windward side and improving the wind energy conversion efficiency.

[0006] More preferably, the top of the Z-shaped rod is movably connected to a fixed plate via a bearing. A sun-tracking adjustment assembly is provided on the top of the fixed plate. The sun-tracking adjustment assembly includes twelve fixed blocks. A gas storage bladder is fixedly connected to the top of every three fixed blocks, and the four gas storage bladders are arranged in a circular array. A U-shaped tube is fixedly connected to one side of the top of each gas storage bladder. A piston is slidably connected to the interior of the section of the U-shaped tube near the fixed plate. A movable rod is fixedly connected to one side of the piston, and the other end of the movable rod extends out of the other end of the U-shaped tube. A fixed plate is fixedly connected to the other end of the movable rod. A traction rope is fixedly connected to the bottom of one side of the fixing plate. A fixing ring is fixedly sleeved on the side surface of the U-shaped tube. A swivel ring is fixedly connected to the side surface of the fixing ring, and the traction rope slides through the swivel ring. The traction rope is in a slack state by default. When the gas in the gas storage bag expands, it provides a force to tighten the traction rope, so that the two traction ropes on the same straight line are tightened. Together with the second movable sleeve and the second ball, the position of the arc-shaped solar panel is stabilized. The gas storage bag is filled with helium. Helium has a large expansion coefficient and is stable. It is also lighter than air and can offset a certain part of the weight of the aircraft.

[0007] In a further preferred embodiment, one end of each of the four traction ropes is fixedly connected to a steering rod. A second ball is fixedly connected to the bottom of the steering rod. A second movable sleeve is movably fitted onto the surface of the second ball, and the bottom of the second movable sleeve is fixedly connected to the center of the top of the fixed plate. An arc-shaped solar panel is fixedly connected to the top of the steering rod. The arc-shaped solar panel is composed of a photovoltaic film adhered to the arc-shaped plate. The lightweight and arc-shaped design can increase the area of ​​light irradiation. The second movable sleeve and the second ball can limit the rotation of the steering rod while keeping it in place, so that the steering rod rotates around the second ball without disengaging.

[0008] More preferably, four fixing rods are fixedly connected to the side surface of the bottom shell, and the fixing rods are U-shaped. The other end of the fixing rods is fixedly connected to the top shell. A transparent cover is fixedly connected to the middle of the top of the top shell. A charging coil is fixedly connected to the inner wall of the bottom of the bottom shell. The charging coil enables the aircraft to charge its built-in battery at a charging station via wireless transmission technology, thereby increasing its range.

[0009] More preferably, a reversing rod is fixedly connected to the side surface of the Z-shaped rod, and the reversing rod is located between the bottom shell and the top shell. A sleeve is fixedly connected to the other end of the reversing rod. A fixed support plate is fixedly connected to the inner annular surface of the sleeve. A generator motor is fixedly connected to the back of the fixed support plate, and the input end of the generator motor is rotatably connected through the fixed support plate. A fan blade is fixedly connected to the input end of the generator motor. Four movable slots are opened on the side surface of the bottom shell, and the four movable slots are arranged in a circular array. The four movable slots can prevent the connecting rod from being obstructed when it turns, and limit the connecting rod, thereby improving the stability of the structure.

[0010] More preferably, the top of the disk is fixedly connected to four connecting rods, and the connection point between the connecting rods and the disk is located directly above the circular block. The other end of the connecting rod passes through the interior of the bottom shell through a movable slot and extends to the exterior of the bottom shell. The other end of the connecting rod is fixedly connected to a rotor, which consists of a drive motor and blades. The rotor is powered by an internal battery to generate a reaction force that makes the aircraft float.

[0011] Compared with the prior art, the beneficial effects of the present invention are as follows:

[0012] In this invention, by installing an orientation adjustment component, the aircraft can change direction during flight by energizing an electromagnetic coil, which generates an electromagnetic force that attracts a circular block on a disk, causing the disk to tilt and thus changing the aircraft's direction. The electromagnetic coil generates an electromagnetic force with a fast response speed and high efficiency, which is lower than that of traditional quadcopters, thus increasing the aircraft's endurance.

[0013] In this invention, the installation of the linkage steering component allows the orientation adjustment component to change the position of the sleeve, generator motor, and fan blades while changing the driving direction, so that the fan blades always face the windward side, effectively converting wind energy into electrical energy and powering the aircraft, further increasing the endurance. Attached Figure Description

[0014] Figure 1 This is a three-dimensional structural diagram of the present invention;

[0015] Figure 2 This is a schematic diagram of the exploded structure of the present invention. Figure 1 ;

[0016] Figure 3 This is a schematic diagram of the exploded structure of the present invention. Figure 2 ;

[0017] Figure 4 This is a cross-sectional three-dimensional structural diagram of the present invention;

[0018] Figure 5 For the present invention Figure 4Enlarged structural diagram at point A;

[0019] Figure 6 For the present invention Figure 3 Enlarged structural diagram at point B;

[0020] Figure 7 For the present invention Figure 4 Enlarged structural diagram at point C;

[0021] Figure 8 For the present invention Figure 4 Enlarged structural diagram at point D;

[0022] Figure 9 For the present invention Figure 4 A magnified structural diagram at point E in the middle.

[0023] In the diagram: 1. Bottom shell; 2. Azimuth adjustment assembly; 3. Linkage steering assembly; 4. Fixing plate; 5. Sun-tracking adjustment assembly; 6. Movable slot; 7. Connecting rod; 8. Rotor; 9. Top shell; 10. Fixing rod; 11. Curved solar panel; 12. Transparent cover; 13. Reversing rod; 14. Sleeve; 15. Fixed support plate; 16. Fan blade; 17. Generator motor; 18. Second movable sleeve; 19. Second ball bearing; 20. Steering rod; 21. Charging coil; 201. Shell; 202. Hollow tube; 203. Electromagnetic coil; 204. Circular block; 205. Circle 206. Disc; 207. Cross groove; 208. Sliding column; 209. Spring; 210. Sliding plate; 211. Limiting plate; 212. Column; 213. First ball; 214. First movable sleeve; 305. Steering column; 306. Limiting disc; 307. Extension handle; 308. Triangular block; 309. Sliding groove; 300. Movable block; 300. Z-shaped rod; 501. Fixed block; 502. Air reservoir; 503. U-shaped tube; 504. Piston; 505. Movable rod; 506. Fixed plate; 507. Traction rope; 508. Fixed ring; 509. Cable puller. Detailed Implementation

[0024] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0025] Please see Figures 1-9This invention provides a technical solution: It includes a bottom shell 1, inside which a directional adjustment component 2 is disposed, and on top of the directional adjustment component 2 a linkage steering component 3 is disposed; the directional adjustment component 2 includes four housings 201, the bottoms of which are fixedly connected to the bottom inner wall of the bottom shell 1 and arranged in a circular array; a hollow tube 202 is fixedly connected between the bottom inner wall of the bottom shell 1 and the top inner wall of the housings 201; an electromagnetic coil 203 is fixedly sleeved between the side surface of the hollow tube 202 and the inner ring surface of the housings 201; four sliding pillars 207 are fixedly connected to the bottom inner wall of the bottom shell 1 and arranged in a circular array; a limiting piece 210 is fixedly connected to the top of each sliding pillar 207; and the side surface of each sliding pillar 207 is movable. A sliding piece 209 is fitted onto the bottom of the bottom shell 1. A spring 208 is movably connected between the bottom of the sliding piece 209 and the inner wall of the bottom of the bottom shell 1. The spring 208 is movably fitted onto the side surface of the sliding column 207. A disc 205 is movably connected between the bottom of the limiting piece 210 and the top of the sliding piece 209. The disc 205 has four cross grooves 206 arranged in a circular array inside. The sliding column 207 slides through the disc 205 through the cross grooves 206. A column 211 is fixedly connected to the middle of the inner wall of the bottom of the bottom shell 1. A first ball 212 is fixedly connected to the top of the column 211. A first movable sleeve 213 is movably fitted onto the surface of the first ball 212. The top of the first movable sleeve 213 is fixedly connected to the middle of the bottom of the disc 205.

[0026] In this embodiment, as Figure 3 , Figure 4 and Figure 5 As shown, the linkage steering assembly 3 includes a steering column 301. The bottom of the steering column 301 is fixedly connected to the center of the top of the disc 205. A limiting disc 302 is fixedly connected to the top of the steering column 301. An extension handle 303 is movably sleeved on the outer side of the steering column 301. A groove 305 is provided on one side of the inner side of the extension handle 303, and the groove 305 is located directly below the limiting disc 302. A triangular block 304 is fixedly connected to the inner wall of the groove 305. A movable block 306 is fixedly connected to one end of the extension handle 303. A Z-shaped rod 307 is fixedly connected to the top of the movable block 306. Helium is injected through the black air reservoir 502. When the gas bladder 502 is heated by sunlight, it generates pressure, which in turn provides force to the piston 504 and pulls the traction rope 507, causing the steering rod 20 to shift towards the corresponding position of the gas bladder 502, so that the curved solar panel 11 faces the sun, improving the conversion efficiency of light energy. The cross groove 206 allows the sliding column 207 to limit the disk 205 while sliding. The edges of the limiting disc 302 and the sliding disc 209 on opposite sides are curved, which facilitates sliding on the disk 205 and prevents the limiting disc 302 and the sliding disc 209 from getting stuck in the cross groove 206, making the aircraft more smooth when changing orientation.

[0027] In this embodiment, as Figure 2 , Figure 4 and Figure 7As shown, a fixed plate 4 is movably connected to the top of the Z-shaped rod 307 via a bearing. A sun-tracking adjustment assembly 5 is installed on the top of the fixed plate 4. The sun-tracking adjustment assembly 5 includes twelve fixed blocks 501. A gas storage bag 502 is fixedly connected to the top of every three fixed blocks 501, and the four gas storage bags 502 are arranged in a ring. A U-shaped tube 503 is fixedly connected to one side of the top of the gas storage bag 502. A piston 504 is slidably connected to the inside of the section of the U-shaped tube 503 near the fixed plate 4. A movable rod 505 is fixedly connected to one side of the piston 504, and the other end of the movable rod 505 extends out of the other end of the U-shaped tube 503. A fixed plate 506 is fixedly connected to the other end of the movable rod 505. A traction rope 507 is fixedly connected to the bottom of one side of the fixed plate 506. A fixing ring 508 is fixedly sleeved on the side surface of the U-shaped tube 503. A cable loop 509 is fixedly connected to the side surface of the fixing ring 508, and the traction rope 507 slides through the cable loop 509. When the aircraft needs to turn, it is controlled by a remote sensing device to turn. By energizing the electromagnetic coil 203 at the corresponding position below the disc 205, the electromagnetic coil 203 generates electromagnetic force and overcomes the force of the spring 208 to attract the iron circular block 204. This causes the disc 205 to tilt towards the energized electromagnetic coil 203. All four connecting rods 7 are connected to the disc 205, so that the connecting rods 7 tilt towards the electromagnetic coil 203 that generates electromagnetic force, thereby changing the direction of travel of the aircraft. As the aircraft changes direction, the steering column 301 at the top center of the disc 205 tilts, contacting the extension handle 303. The force from the tilting steering column 301 causes the Z-shaped rod 307 to rotate around the contact point between the steering column 301 and the extension handle 303. The diameter of the groove 305 on the extension handle 303 is larger than the diameters of the Z-shaped rod 307 and the steering column 301, ensuring that the steering column 301 has a sufficient deflection angle to rotate the extension handle 303. When the steering column 301 tilts to one side, the connection between the extension handle 303 and the Z-shaped rod 307 rotates in the opposite direction. This causes the sleeve 14 and the fan blade 16 connected to the Z-shaped rod 307 to rotate simultaneously with the aircraft's change of direction. Always facing the flight direction, a triangular block 304 is fixedly installed inside the slide 305 to provide a sufficient deflection angle when changing flight direction by 180 degrees. When the steering column 301 changes direction by 180 degrees, it contacts the inclined surface of the triangular block 304, causing the extension handle 303 to shift its position under the force and providing a certain deflection angle. This allows for a rapid change in the orientation of the fan blades 16 when quickly switching flight directions. To effectively increase the range, a photovoltaic film is adhered to the curved panel to form an arc-shaped solar panel 11. The diameter of the slide 305 is larger than the diameter of the Z-shaped rod 307 and the steering column 301, so that the steering column 301 has a sufficient deflection angle to provide force to the extension handle 303 when changing orientation.This causes the extension handle 303 to rotate in the opposite direction around the steering column 301, ensuring that the fan blades 16 always face the windward side, thus improving wind energy conversion efficiency.

[0028] In this embodiment, as Figure 2 , Figure 4 and Figure 8 As shown, one end of each of the four traction ropes 507 is fixedly connected to a steering rod 20. A second ball bearing 19 is fixedly connected to the bottom of the steering rod 20. A second movable sleeve 18 is movably fitted onto the surface of the second ball bearing 19, and the bottom of the second movable sleeve 18 is fixedly connected to the center of the top of the fixed plate 4. An arc-shaped solar panel 11 is fixedly connected to the top of the steering rod 20. The traction ropes 507 are in a slack state by default. When the gas inside the air bladder 502 expands, it provides a force to tighten the traction ropes 507, causing two traction ropes on a straight line to be tightened and cooperating with the second... The movable sleeve 18 and the second bead 19 stabilize the position of the arc-shaped solar panel 11. The air bladder 502 is filled with helium. Helium has a large expansion coefficient and is stable. It is also lighter than air and can offset some of the weight of the aircraft. The arc-shaped solar panel 11 is composed of a photovoltaic film bonded to an arc-shaped plate. The lightweight arc design can increase the area of ​​light irradiation. The second movable sleeve 18 and the second bead 19 can limit the rotation of the steering rod 20, so that the steering rod 20 rotates around the second bead 19 without disengaging.

[0029] In this embodiment, as Figure 3 , Figure 4 and Figure 5 As shown, four fixing rods 10 are fixedly connected to the side surface of the bottom shell 1, and the fixing rods 10 are U-shaped. The other end of the fixing rods 10 is fixedly connected to the top shell 9. A transparent cover 12 is fixedly connected to the middle of the top of the top shell 9. A charging coil 21 is fixedly connected to the inner wall of the bottom of the bottom shell 1. The charging coil 21 enables the aircraft to be charged at a charging station through wireless transmission technology, thereby increasing its range.

[0030] In this embodiment, as Figure 2 , Figure 4 and Figure 7 As shown, a reversing rod 13 is fixedly connected to the side surface of the Z-shaped rod 307, and the reversing rod 13 is located between the bottom shell 1 and the top shell 9. A sleeve 14 is fixedly connected to the other end of the reversing rod 13. A fixed support plate 15 is fixedly connected to the inner ring surface of the sleeve 14. A generator motor 17 is fixedly connected to the back of the fixed support plate 15, and the input end of the generator motor 17 is rotatably connected through the fixed support plate 15. A fan blade 16 is fixedly connected to the input end of the generator motor 17. Four movable slots 6 are opened on the side surface of the bottom shell 1, and the four movable slots 6 are arranged in a ring array. The four movable slots 6 can prevent the connecting rod 7 from being obstructed when it turns, and limit the connecting rod 7 to improve the stability of the structure.

[0031] In this embodiment, as Figure 1 , Figure 4 and Figure 5 As shown, four connecting rods 7 are fixedly connected to the top of the disk 205, and the connection between the connecting rods 7 and the disk 205 is located directly above the circular block 204. The other end of the connecting rod 7 passes through the interior of the bottom shell 1 through the movable slot 6 and extends to the exterior of the bottom shell 1. The other end of the connecting rod 7 is fixedly connected to a rotor 8, which consists of a drive motor and blades. The rotor 8 is powered by a built-in battery to drive the rotor 8 and generate a reaction force to make the aircraft float.

[0032] The method of use and advantages of this invention: The long-range endurance aircraft based on hybrid kinetic energy operates as follows:

[0033] like Figure 1 , Figure 2 , Figure 3 , Figure 4 , Figure 5 , Figure 6 , Figure 7 , Figure 8 and Figure 9As shown, when the aircraft needs to turn, the remote sensing device controls the aircraft to turn. By energizing the electromagnetic coil 203 located below the disc 205, the electromagnetic coil 203 generates electromagnetic force, which overcomes the force of the spring 208 and attracts the iron circular block 204. This causes the disc 205 to tilt towards the energized electromagnetic coil 203. Since all four connecting rods 7 are connected to the disc 205, they also tilt towards the electromagnetic coil 203, thus enabling the aircraft to move. As the aircraft changes direction, the steering column 301 at the top center of the disk 205 tilts. During this tilt, it contacts the extension handle 303. The force exerted by the tilting steering column 301 causes the Z-shaped rod 307 to rotate around the contact point between the steering column 301 and the extension handle 303. The diameter of the groove 305 on the extension handle 303 is larger than the diameters of the Z-shaped rod 307 and the steering column 301, ensuring that the steering column 301 has a sufficient deflection angle to rotate the extension handle 303 and thus the steering column... When 301 tilts to one side, the connection between the extension handle 303 and the Z-shaped rod 307 will rotate in the opposite direction, ensuring that the sleeve 14 and the fan blade 16 connected to the Z-shaped rod 307 always face the flight direction while the aircraft changes direction. To ensure a sufficient deflection angle when changing the flight direction by 180 degrees, a triangular block 304 is fixedly installed inside the slide 305. When the steering column 301 changes direction by 180 degrees, it contacts the inclined surface of the triangular block 304, causing the position of the extension handle 303 to shift under the force. A certain deflection angle is provided so that the orientation of the fan blade 16 can be quickly changed when the driving direction is changed rapidly. In order to effectively increase the range, a photovoltaic film is attached to the curved panel to form a curved solar panel 11. Helium is injected into the black air bladder 502 so that the air bladder 502 generates pressure when heated under the sun, thereby providing force to the piston 504 and pulling the traction rope 507 so that the steering rod 20 is offset in the direction of the corresponding air bladder 502, so that the curved solar panel 11 faces the sun and improves the conversion efficiency of light energy.

[0034] The foregoing has shown and described the basic principles, main features, and advantages of the present invention. Those skilled in the art should understand that the present invention is not limited to the above embodiments. The embodiments and descriptions in the specification are merely preferred examples and are not intended to limit the invention. Various changes and modifications can be made to the invention without departing from its spirit and scope, and all such changes and modifications fall within the scope of the present invention as claimed. The scope of protection of the present invention is defined by the appended claims and their equivalents.

Claims

1. A long-range endurance aircraft based on hybrid kinetic energy, comprising a bottom shell (1), characterized in that: The bottom shell (1) is provided with an orientation adjustment component (2) inside, and a linkage steering component (3) is provided on the top of the orientation adjustment component (2); The orientation adjustment component (2) includes four housings (201). The bottoms of the four housings (201) are fixedly connected to the bottom inner wall of the bottom shell (1) and arranged in a ring array. A hollow tube (202) is fixedly connected between the bottom inner wall of the bottom shell (1) and the top inner wall of the housing (201). An electromagnetic coil (203) is fixedly sleeved between the side surface of the hollow tube (202) and the inner ring surface of the housing (201). Four sliding pillars (207) are fixedly connected to the bottom inner wall of the bottom shell (1) and arranged in a ring array. A limiting piece (210) is fixedly connected to the top of the sliding pillar (207). A sliding plate (209) is movably sleeved on the side surface of the sliding pillar (207). The bottom of the sliding plate (209) is movably sleeved between the bottom inner wall of the bottom shell (1). A spring (208) is movably connected and the spring (208) is movably sleeved on the side surface of the slide column (207). A disc (205) is movably connected between the bottom of the limiting piece (210) and the top of the slide piece (209). The disc (205) has four cross grooves (206) inside and is arranged in a ring array. The slide column (207) slides through the disc (205) through the cross grooves (206). A column (211) is fixedly connected to the middle of the bottom inner wall of the bottom shell (1). A first ball (212) is fixedly connected to the top of the column (211). A first movable sleeve (213) is movably sleeved on the surface of the first ball (212) and the top of the first movable sleeve (213) is fixedly connected to the middle of the bottom of the disc (205).

2. The long-range endurance aircraft based on hybrid kinetic energy according to claim 1, characterized in that: The linkage steering assembly (3) includes a steering column (301), the bottom of which is fixedly connected to the middle of the top of the disc (205), a limiting disc (302) is fixedly connected to the top of the steering column (301), an extension handle (303) is movably sleeved on the outside of the steering column (301), a groove (305) is provided on one side of the inside of the extension handle (303) and the groove (305) is located directly below the limiting disc (302), a triangular block (304) is fixedly connected to the inner wall of the groove (305), a movable block (306) is fixedly connected to one end of the extension handle (303), and a Z-shaped rod (307) is fixedly connected to the top of the movable block (306).

3. A long-range endurance aircraft based on hybrid kinetic energy according to claim 2, characterized in that: The top of the Z-shaped rod (307) is movably connected to a fixed plate (4) via a bearing. The top of the fixed plate (4) is provided with a sun-tracking adjustment assembly (5). The sun-tracking adjustment assembly (5) includes twelve fixed blocks (501). The top of every three fixed blocks (501) is fixedly connected to an air reservoir (502), and the four air reservoirs (502) are arranged in a ring. A U-shaped tube (503) is fixedly connected to one side of the top of the air reservoir (502). A piston (504) is slidably connected inside the section of the U-shaped tube (503) near the fixed plate (4). The piston (504) is fixedly connected to one side of a movable rod (505), and the other end of the movable rod (505) extends out of the other end of a U-shaped tube (503). The other end of the movable rod (505) is fixedly connected to a fixing plate (506). The bottom of one side of the fixing plate (506) is fixedly connected to a traction rope (507). A fixing ring (508) is fixedly sleeved on the side surface of the U-shaped tube (503). A slewing ring (509) is fixedly connected to the side surface of the fixing ring (508), and the traction rope (507) slides through the slewing ring (509).

4. A long-range endurance aircraft based on hybrid kinetic energy according to claim 3, characterized in that: One end of each of the four traction ropes (507) is fixedly connected to a steering rod (20). The bottom of the steering rod (20) is fixedly connected to a second ball (19). The surface of the second ball (19) is movably fitted with a second movable sleeve (18), and the bottom of the second movable sleeve (18) is fixedly connected to the middle of the top of the fixed plate (4). The top of the steering rod (20) is fixedly connected to an arc-shaped solar panel (11).

5. A long-range endurance aircraft based on hybrid kinetic energy according to claim 1, characterized in that: Four fixing rods (10) are fixedly connected to the side surface of the bottom shell (1) and the fixing rods (10) are U-shaped. The other end of the fixing rods (10) is fixedly connected to the top shell (9). A transparent cover (12) is fixedly connected to the middle of the top of the top shell (9). A charging coil (21) is fixedly connected to the bottom inner wall of the bottom shell (1).

6. A long-range endurance aircraft based on hybrid kinetic energy according to claim 5, characterized in that: A reversing rod (13) is fixedly connected to the side surface of the Z-shaped rod (307), and the reversing rod (13) is located between the bottom shell (1) and the top shell (9). A sleeve (14) is fixedly connected to the other end of the reversing rod (13). A fixed support plate (15) is fixedly connected to the inner ring surface of the sleeve (14). A generator motor (17) is fixedly connected to the back of the fixed support plate (15), and the input end of the generator motor (17) is rotatably connected through the fixed support plate (15). A fan blade (16) is fixedly connected to the input end of the generator motor (17). Four movable slots (6) are opened on the side surface of the bottom shell (1), and the four movable slots (6) are arranged in a ring array.

7. A long-range endurance aircraft based on hybrid kinetic energy according to claim 1, characterized in that: The top of the disk (205) is fixedly connected to four connecting rods (7), and the connection between the connecting rods (7) and the disk (205) is located directly above the circular block (204). The other end of the connecting rod (7) passes through the interior of the bottom shell (1) through the movable groove (6) and extends to the exterior of the bottom shell (1). The other end of the connecting rod (7) is fixedly connected to a rotor (8).

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