阅读说明：本技术 一种节能型混合动力无人机 (Energy-saving hybrid unmanned aerial vehicle ) 是由 李洁 于 2020-06-06 设计创作，主要内容包括：本发明公开了一种节能型混合动力无人机,包括复合翼无人机,所述复合翼无人机内设有气瓶固定机构,所述气瓶固定机构一侧设有摆动除霜机构,所述摆动除霜机构一侧设有排气转换机构。本发明的有益效果是,可以有效防止液态氢瓶外表面结霜的现象,间接达到减重的效果,通过利用氢动能发动机的热量可以提高清除结霜的效果,同时可以间接提高液态氢瓶的温度,从而适当增加瓶内的压力,增大排出量。(The invention discloses an energy-saving hybrid power unmanned aerial vehicle which comprises a composite wing unmanned aerial vehicle, wherein a gas cylinder fixing mechanism is arranged in the composite wing unmanned aerial vehicle, a swing defrosting mechanism is arranged on one side of the gas cylinder fixing mechanism, and an exhaust conversion mechanism is arranged on one side of the swing defrosting mechanism. The invention has the advantages that the invention can effectively prevent the frosting phenomenon on the outer surface of the liquid hydrogen bottle, indirectly achieve the effect of weight reduction, improve the effect of removing the frosting by utilizing the heat of the hydrogen kinetic energy engine, and simultaneously indirectly improve the temperature of the liquid hydrogen bottle, thereby properly increasing the pressure in the bottle and increasing the discharge amount.)

1. An energy-saving hybrid power unmanned aerial vehicle comprises a composite wing unmanned aerial vehicle (1), and is characterized in that a gas cylinder fixing mechanism is arranged in the composite wing unmanned aerial vehicle (1), a swing defrosting mechanism is arranged on one side of the gas cylinder fixing mechanism, and an exhaust conversion mechanism is arranged on one side of the swing defrosting mechanism;

the gas cylinder fixing mechanism comprises a gas cylinder storage box (2) at the lower end of a composite wing unmanned aerial vehicle (1), rectangular pipes (3) are installed on two sides of the gas cylinder storage box (2), sliding blocks (4) are installed on the inner rings of the rectangular pipes (3), the sliding blocks (4) are in sliding connection with the rectangular pipes (3), T-shaped clamping grooves (5) are installed on one sides of the sliding blocks (4), sliding rails (6) are installed on two sides of the gas cylinder storage box (2), the sliding rails (6) are fixedly connected with the composite wing unmanned aerial vehicle (1), T-shaped connecting rods (7) are installed at the upper ends of the sliding rails (6), triangular blocks (8) are installed at one ends of the T-shaped connecting rods (7), fixing strips (9) are installed on one sides of the triangular blocks (8), the fixing strips (9) correspond to the positions of the T-shaped clamping grooves (5), connecting, the upper end of the side surface of the gas cylinder storage box (2) is provided with a first circular through hole (12), a reciprocating lead screw (11) penetrates through the first circular through hole (12), a first vertical bearing (13) is installed on one side of the gas cylinder storage box (2), the first vertical bearing (13) is fixedly connected with the composite wing unmanned aerial vehicle (1), a rotating block (14) is installed on the inner ring of the first vertical bearing (13), a first threaded hole (15) meshed with the reciprocating lead screw (11) is formed in the side surface of the rotating block (14), and one end of the rotating block (14) is provided with a first transmission gear (16); a first through hole (17) is formed in one side of the T-shaped connecting rod (7), a sliding rod (18) is installed in the first through hole (17), a circular baffle (19) is installed at one end of the sliding rod (18), a rectangular baffle (20) is installed at the other end of the sliding rod (18), an extension spring (21) is installed between the rectangular baffle (20) and the T-shaped connecting rod (7), a second threaded hole (22) is formed in the side surface of the gas cylinder storage box (2), and a fastening bolt (23) is installed on the inner ring of the second threaded hole (22); a stepping motor (24) is installed on one side of the gas cylinder storage box (2), the stepping motor (24) is fixedly connected with the composite wing unmanned aerial vehicle (1), a first output shaft (25) is installed at one end of the stepping motor (24), a second output shaft (26) is installed at the other end of the second stepping motor (24), and a first one-way gear (27) meshed with the first transmission gear (16) is installed at one end of the first output shaft (25);

the swing defrosting mechanism comprises a circular through hole II (28) at the lower end of the side surface of the gas cylinder storage box (2), a roller bearing I (29) is installed on one side of the circular through hole II (28), a limiting block (30) is installed on the inner ring of the roller bearing I (29), a hollow pipe (31) is installed on the inner ring of the roller bearing I (29), a limiting groove (32) is formed in the side surface of the hollow pipe (31), the limiting groove (32) corresponds to the limiting block (30), an electromagnet ring I (33) is installed at one end of the hollow pipe (31), a bevel gear I (34) is installed on the outer ring of the electromagnet ring I (33), an electromagnet ring II (35) is installed on one side of the gas cylinder storage box (2), the electromagnet ring II (35) is fixedly connected with the composite wing unmanned aerial vehicle (1), the electromagnet ring II (35) corresponds to the electromagnet ring I (33), and a torsion, an arc-shaped hollow bar (37) is mounted at the other end of the hollow tube (31), one end of the arc-shaped hollow bar (37) is in a state of being communicated with the hollow tube (31), an air outlet hole (38) is formed in the side surface of the arc-shaped hollow bar (37), a cleaning brush (39) is mounted on one side of the air outlet hole (38), a fixing shaft (40) is mounted on the side surface of the gas cylinder storage box (2), a roller bearing II (41) is mounted at one end of the fixing shaft (40), a bevel gear II (42) is mounted on the outer surface of the roller bearing II (41), and a belt pulley I (43; a second unidirectional gear (44) is installed on one side of the first unidirectional gear (27), a second belt pulley (45) is installed on the side surface of the second unidirectional gear (44), and a transmission belt (46) is installed in front of the second belt pulley (45) and the first belt pulley (43);

the exhaust conversion mechanism comprises a hydrogen fuel engine (47) at one end of the composite wing unmanned aerial vehicle (1), an exhaust pipe (48) is installed at one end of the hydrogen fuel engine (47), a rectangular box (49) is installed at one end of the exhaust pipe (48), the exhaust pipe (48) and the rectangular box (49) are in an intercommunicating state, the lower end of the rectangular box (49) is fixedly connected with the composite wing unmanned aerial vehicle (1), a first branch pipe (50) is installed on the side surface of the rectangular box (49), a second branch pipe (51) is installed on the side surface of the rectangular box (49), a rectangular strip (52) is installed on the inner surface of the rectangular box (49), a trapezoidal block (53) is installed in the rectangular box (49), a strip-shaped groove (54) is formed in the side surface of the trapezoidal block (53), the strip-shaped groove (54) corresponds to the position of the rectangular strip (52), a third through hole (, a circular strip (57) is installed in the sliding seal ring (56), one end of the circular strip (57) is fixedly connected with the trapezoidal block (53), a T-shaped groove (58) is installed at the lower end of the circular strip (57), the lower end of the T-shaped groove (58) is fixedly connected with the composite wing unmanned aerial vehicle (1), a rack groove (58) is formed in the upper end of the circular strip (57), a sliding rack (59) is installed in the rack groove (58), and compression springs (60) are installed at two ends of the sliding rack (59); one end of the second output shaft (26) is provided with a common gear (61) which is meshed with the sliding rack (59).

2. An energy-saving hybrid unmanned aerial vehicle as claimed in claim 1, characterized in that, a rubber pad (62) is installed on one side of the sliding block (4).

3. An energy-saving hybrid unmanned aerial vehicle according to claim 1, wherein the lower surface of the composite wing unmanned aerial vehicle (1) is provided with a rectangular opening (63).

4. The energy-saving hybrid unmanned aerial vehicle of claim 1, wherein one end of the branch pipe I (50) is provided with a rubber pipe I (64), and one end of the rubber pipe I (64) is fixedly connected with the hollow pipe (31) and is in an intercommunicated state.

5. The energy-saving hybrid unmanned aerial vehicle as claimed in claim 1, wherein a circular partition plate (65) is installed in the composite wing unmanned aerial vehicle (1), two circular partition plates (65) are provided, a hydrogen fuel cell (66) is installed on one side of the circular partition plate (65), a gas distribution valve (67) is installed on the other side of the circular partition plate (65), a fixed pipe (68) is installed at one end of the gas distribution valve (67), and a first sealing valve (69) is installed at one end of the fixed pipe (68).

6. The energy-saving hybrid unmanned aerial vehicle as claimed in claim 5, wherein a first gas pipe (70) is installed between the gas distribution valve (67) and the hydrogen fuel cell (66), and a second gas pipe (71) is installed between the gas distribution valve (67) and the hydrogen fuel engine (47).

7. The energy-saving hybrid unmanned aerial vehicle as claimed in claim 1, wherein a hydrogen fuel bottle (72) is disposed in the gas bottle storage box (2), and a second sealing valve (73) is mounted at an output end of the hydrogen fuel bottle (72).

Technical Field

The invention relates to the technical field of hydrogen kinetic energy unmanned aerial vehicles, in particular to an energy-saving hybrid power unmanned aerial vehicle.

Background

Hydrogen power unmanned aerial vehicle is the unmanned aircraft who adopts liquid hydrogen power, and hydrogen power unmanned aerial vehicle has pioneering unmanned aerial vehicle, will open a brand-new data acquisition and communication market. The 'ghost eye' is a model for changing the idea into reality, is a crystal of a rapid prototyping project, adopts a series of advanced technologies, and can be used for executing information collection, reconnaissance and survey tasks; the composite wing unmanned aerial vehicle is a combination of a fixed wing and a rotor wing, the composite wing unmanned aerial vehicle can be more suitable for complex working conditions, different working states are provided during high-speed flight and suspension, the unmanned aerial vehicle can be kept in stable and flexible working conditions under general conditions by a plurality of rotor wings, but the composite wing unmanned aerial vehicle is inconvenient to use a traditional mechanical connecting rod for transmission due to the arrangement of the plurality of rotor wings, the rotor wings are generally powered by electric power, only one power propeller behind the fixed wing unmanned aerial vehicle is arranged, and the composite wing unmanned aerial vehicle can be driven by a single power source, so that the device is provided with two power sources;

the hydrogen power unmanned aerial vehicle needs liquid hydrogen to provide continuous energy, when the unmanned aerial vehicle works, the gasification speed of the output end of the liquid hydrogen bottle is increased, and liquid gasification needs to absorb heat, so that the frosting phenomenon can be generated near the output end of the liquid hydrogen bottle, and if the frosting phenomenon is not cleaned in time, the weight of the unmanned aerial vehicle is increased, and the energy consumption is increased; no matter be liquid hydrogen bottle or natural gas bottle can not guarantee stable strength output when pressure is lower, but still have more energy this moment in the bottle, if can the maximize with gaseous abundant release in the bottle, can effectively improve hydrogen power unmanned aerial vehicle's continuation of the journey.

Disclosure of Invention

Aiming at the defects, the invention provides an energy-saving hybrid power unmanned aerial vehicle to solve the problem.

In order to achieve the purpose, the invention adopts the following technical scheme:

an energy-saving hybrid power unmanned aerial vehicle comprises a composite wing unmanned aerial vehicle, wherein a gas cylinder fixing mechanism is arranged in the composite wing unmanned aerial vehicle, a swing defrosting mechanism is arranged on one side of the gas cylinder fixing mechanism, and an exhaust conversion mechanism is arranged on one side of the swing defrosting mechanism;

the gas cylinder fixing mechanism comprises a gas cylinder storage box at the lower end of the composite wing unmanned aerial vehicle, rectangular pipes are mounted on two sides of the gas cylinder storage box, sliding blocks are mounted on inner rings of the rectangular pipes and are connected with the rectangular pipes in a sliding mode, T-shaped clamping grooves are mounted on one sides of the sliding blocks, sliding rails are mounted on two sides of the gas cylinder storage box and are fixedly connected with the composite wing unmanned aerial vehicle, T-shaped connecting rods are mounted at the upper ends of the sliding rails, triangular blocks are mounted at one ends of the T-shaped connecting rods, fixing strips are mounted on one sides of the triangular blocks and correspond to the T-shaped clamping grooves in position, connecting rods are mounted at one ends of the T-shaped connecting rods, reciprocating lead screws are mounted in the centers of the side surfaces of the connecting rods, circular through holes I are formed in the, a first threaded hole meshed with the reciprocating screw rod is formed in the side surface of the rotating block, and a first transmission gear is mounted at one end of the rotating block; a first through hole is formed in one side of the T-shaped connecting rod, a sliding rod is installed in the first through hole, a circular baffle is installed at one end of the sliding rod, a rectangular baffle is installed at the other end of the sliding rod, an extension spring is installed between the rectangular baffle and the T-shaped connecting rod, a second threaded hole is formed in the side surface of the gas cylinder storage box, and a fastening bolt is installed on the inner ring of the second threaded hole; a stepping motor is installed on one side of the gas cylinder storage box and fixedly connected with the composite wing unmanned aerial vehicle, a first output shaft is installed at one end of the stepping motor, a second output shaft is installed at the other end of the stepping motor, and a first one-way gear meshed with the first transmission gear is installed at one end of the first output shaft;

the swing defrosting mechanism comprises a circular through hole II at the lower end of the side surface of the gas cylinder storage box, a roller bearing I is arranged on one side of the circular through hole II, a limiting block is arranged on the inner ring of the roller bearing I, a hollow tube is arranged on the inner ring of the roller bearing I, a limiting groove is formed in the side surface of the hollow tube and corresponds to the limiting block in position, an electromagnet ring I is arranged at one end of the hollow tube, a bevel gear I is arranged on the outer ring of the electromagnet ring I, an electromagnet ring II is arranged on one side of the gas cylinder storage box and is fixedly connected with the composite wing unmanned aerial vehicle, the electromagnet ring II corresponds to the electromagnet ring I in position, a torsion spring is arranged between the hollow tube and the side surface of the gas cylinder storage box, an arc hollow strip is arranged at the other end of the hollow, a fixed shaft is arranged on the side surface of the gas cylinder storage box, a roller bearing II is arranged at one end of the fixed shaft, a bevel gear II is arranged on the outer surface of the roller bearing II, and a belt pulley I is arranged on one side of the bevel gear II; a second one-way gear is mounted on one side of the first one-way gear, a second belt pulley is mounted on the surface of the two sides of the one-way gear, and a transmission belt is mounted in front of the second belt pulley and the first belt pulley;

the exhaust conversion mechanism comprises a hydrogen fuel engine at one end of the composite wing unmanned aerial vehicle, an exhaust pipe is mounted at one end of the hydrogen fuel engine, a rectangular box is mounted at one end of the exhaust pipe, the exhaust pipe and the rectangular box are in an intercommunicating state, the lower end of the rectangular box is fixedly connected with the composite wing unmanned aerial vehicle, a first branch pipe is mounted on the side surface of the rectangular box, a second branch pipe is mounted on the side surface of the rectangular box, a rectangular strip is mounted on the inner surface of the rectangular box, a trapezoidal block is mounted in the rectangular box, a strip-shaped groove is formed in the side surface of the trapezoidal block, the strip-shaped groove corresponds to the position of the rectangular strip, a third through hole is formed in the side surface of the rectangular box, a sliding sealing ring is mounted in the inner circle of the third through hole, a circular strip is mounted in the sliding sealing ring, compression springs are arranged at two ends of the sliding rack; and one end of the output shaft is provided with a common gear which is meshed with the sliding rack.

Furthermore, a rubber pad is installed on one side of the sliding block.

Further, the lower surface of the composite wing unmanned aerial vehicle is provided with a rectangular opening.

Furthermore, a first rubber pipe is installed at one end of the branch pipe, and one end of the first rubber pipe is fixedly connected with the hollow pipe and is in an intercommunicated state.

Furthermore, two circular partition plates are arranged in the composite wing unmanned aerial vehicle, a hydrogen fuel cell is arranged on one side of each circular partition plate, a gas distribution valve is arranged on the other side of each circular partition plate, a fixing pipe is arranged at one end of each gas distribution valve, and a first sealing valve is arranged at one end of each fixing pipe.

Furthermore, a first gas conveying pipe is arranged between the gas distribution valve and the hydrogen fuel cell, and a second gas conveying pipe is arranged between the gas distribution valve and the hydrogen fuel engine.

Further, a hydrogen fuel bottle is arranged in the gas bottle storage box, and a sealing valve II is installed at the output end of the hydrogen fuel bottle.

The invention has the beneficial effects that: the phenomenon that the surface of the liquid hydrogen bottle frosts can be effectively prevented, the weight losing effect is indirectly achieved, the frosting clearing effect can be improved through the heat of the hydrogen kinetic energy engine, meanwhile, the temperature of the liquid hydrogen bottle can be indirectly improved, and therefore the pressure in the bottle is properly increased, and the discharge amount is increased.

Drawings

Fig. 1 is a schematic structural diagram of an energy-saving hybrid unmanned aerial vehicle according to the invention;

FIG. 2 is an enlarged schematic view of via three;

FIG. 3 is a schematic view of a gas cylinder securing mechanism;

FIG. 4 is a schematic cross-sectional view of a gas cylinder securing mechanism;

FIG. 5 is a schematic cross-sectional view of a circular bar;

FIG. 6 is an enlarged schematic view of a rectangular box;

FIG. 7 is a side view schematic of a trapezoidal block;

FIG. 8 is a partial schematic view of a hollow tube;

FIG. 9 is a schematic view of the oscillating defrost mechanism;

FIG. 10 is a schematic side view of an arcuate hollow bar;

FIG. 11 is an enlarged schematic view of a roller bearing I;

FIG. 12 is a schematic view of bevel gear two;

in the figure, 1, a compound wing unmanned plane; 2. a gas cylinder storage tank; 3. a rectangular tube; 4. a slider; 5. a T-shaped clamping groove; 6. a slide rail; 7. a T-shaped connecting rod; 8. a triangular block; 9. a fixing strip; 10. a connecting rod; 11. a reciprocating screw; 12. a first circular through hole; 13. a first vertical bearing; 14. rotating the block; 15. a first threaded hole; 16. a first transmission gear; 17. a first through hole; 18. a slide bar; 19. a circular baffle; 20. a rectangular baffle plate; 21. an extension spring; 22. a second threaded hole; 23. fastening a bolt; 24. a stepping motor; 25. a first output shaft; 26. a second output shaft; 27. a one-way gear I; 28. a second circular through hole; 29. a roller bearing I; 30. a limiting block; 31. a hollow tube; 32. a limiting groove; 33. a first electromagnet ring; 34. a first bevel gear; 35. a second electromagnet ring; 36. a torsion spring; 37. an arc-shaped hollow bar; 38. an air outlet; 39. cleaning the brush; 40. a fixed shaft; 41. a roller bearing II; 42. a second bevel gear; 43. a first belt pulley; 44. a second one-way gear; 45. a second belt pulley; 46. a transmission belt; 47. a hydrogen-fueled engine; 48. an exhaust pipe; 49. a rectangular box; 50. dividing a pipe into a first pipe; 51. dividing a pipe into two pipes; 52. a rectangular strip; 53. a trapezoidal block; 54. a strip-shaped groove; 55. a third through hole; 56. sliding the seal ring; 57. a circular strip; 58. a T-shaped slot; 59. a sliding rack; 60. a compression spring; 61. a common gear; 62. a rubber pad; 63. a rectangular opening; 64. a first rubber pipe; 65. a circular separator plate; 66. a hydrogen fuel cell; 67. a gas distribution valve; 68. a fixed tube; 69. a first sealing valve; 70. a first gas transmission pipe; 71. a second gas conveying pipe; 72. a hydrogen fuel bottle; 73. and a second sealing valve.

Detailed Description

The invention is described in detail with reference to the accompanying drawings, and as shown in fig. 1-12, an energy-saving hybrid unmanned aerial vehicle comprises a composite wing unmanned aerial vehicle 1, wherein a gas cylinder fixing mechanism is arranged in the composite wing unmanned aerial vehicle 1, a swing defrosting mechanism is arranged on one side of the gas cylinder fixing mechanism, and an exhaust switching mechanism is arranged on one side of the swing defrosting mechanism;

the gas cylinder fixing mechanism comprises a gas cylinder storage box 2 at the lower end of the composite wing unmanned aerial vehicle 1, rectangular pipes 3 are mounted on two sides of the gas cylinder storage box 2, sliding blocks 4 are mounted on inner rings of the rectangular pipes 3, the sliding blocks 4 are in sliding connection with the rectangular pipes 3, T-shaped clamping grooves 5 are mounted on one sides of the sliding blocks 4, sliding rails 6 are mounted on two sides of the gas cylinder storage box 2, the sliding rails 6 are fixedly connected with the composite wing unmanned aerial vehicle 1, T-shaped connecting rods 7 are mounted at the upper ends of the sliding rails 6, triangular blocks 8 are mounted at one ends of the T-shaped connecting rods 7, fixing strips 9 correspond to the T-shaped clamping grooves 5 in position, connecting rods 10 are mounted at one ends of the T-shaped connecting rods 7, reciprocating lead screws 11 are mounted at the centers of the side surfaces of the connecting rods 10, circular through holes, the vertical bearing I13 is fixedly connected with the composite wing unmanned aerial vehicle 1, a rotating block 14 is installed on the inner ring of the vertical bearing I13, a threaded hole I15 meshed with the reciprocating screw rod 11 is formed in the side surface of the rotating block 14, and a transmission gear I16 is installed at one end of the rotating block 14; one side of the T-shaped connecting rod 7 is provided with a first through hole 17, a sliding rod 18 is installed in the first through hole 17, one end of the sliding rod 18 is provided with a circular baffle 19, the other end of the sliding rod 18 is provided with a rectangular baffle 20, an extension spring 21 is installed between the rectangular baffle 20 and the T-shaped connecting rod 7, the side surface of the gas cylinder storage box 2 is provided with a second threaded hole 22, and an inner ring of the second threaded hole 22 is provided with a fastening bolt 23; a stepping motor 24 is installed on one side of the gas cylinder storage box 2, the stepping motor 24 is fixedly connected with the compound wing unmanned aerial vehicle 1, a first output shaft 25 is installed at one end of the stepping motor 24, a second output shaft 26 is installed at the other end of the stepping motor 24, and a first one-way gear 27 meshed with the first transmission gear 16 is installed at one end of the first output shaft 25;

the swing defrosting mechanism comprises a circular through hole II 28 at the lower end of the side surface of the gas cylinder storage box 2, a roller bearing I29 is arranged at one side of the circular through hole II 28, a limiting block 30 is arranged at the inner ring of the roller bearing I29, a hollow pipe 31 is arranged at the inner ring of the roller bearing I29, a limiting groove 32 is formed in the side surface of the hollow pipe 31, the limiting groove 32 corresponds to the limiting block 30 in position, an electromagnet ring I33 is arranged at one end of the hollow pipe 31, a bevel gear I34 is arranged at the outer ring of the electromagnet ring I33, an electromagnet ring II 35 is arranged at one side of the gas cylinder storage box 2, the electromagnet ring II 35 is fixedly connected with the composite wing unmanned aerial vehicle 1, the electromagnet ring II 35 corresponds to the electromagnet ring I33 in position, a torsion spring 36 is arranged between the hollow pipe 31 and the side surface, an air outlet 38 is formed in the side surface of the arc-shaped hollow bar 37, a cleaning brush 39 is mounted on one side of the air outlet 38, a fixed shaft 40 is mounted on the side surface of the gas cylinder storage box 2, a second roller bearing 41 is mounted at one end of the fixed shaft 40, a second bevel gear 42 is mounted on the outer surface of the second roller bearing 41, and a first belt pulley 43 is mounted on one side of the second bevel gear 42; a second one-way gear 44 is arranged on one side of the first one-way gear 27, a second belt pulley 45 is arranged on the side surface of the second one-way gear 44, and a transmission belt 46 is arranged in front of the second belt pulley 45 and the first belt pulley 43;

the exhaust conversion mechanism comprises a hydrogen fuel engine 47 at one end of the composite wing unmanned aerial vehicle 1, an exhaust pipe 48 is mounted at one end of the hydrogen fuel engine 47, a rectangular box 49 is mounted at one end of the exhaust pipe 48, the exhaust pipe 48 and the rectangular box 49 are in an intercommunicating state, the lower end of the rectangular box 49 is fixedly connected with the composite wing unmanned aerial vehicle 1, a first branch pipe 50 is mounted on the side surface of the rectangular box 49, a second branch pipe 51 is mounted on the side surface of the rectangular box 49, a rectangular strip 52 is mounted on the inner surface of the rectangular box 49, a trapezoidal block 53 is mounted in the rectangular box 49, a strip-shaped groove 54 is formed in the side surface of the trapezoidal block 53, the strip-shaped groove 54 corresponds to the position of the rectangular strip 52, a third through hole 55 is formed in the side surface of the rectangular box 49, a sliding seal ring 56 is mounted on, the lower end of the T-shaped groove 58 is fixedly connected with the composite wing unmanned aerial vehicle 1, the upper end of the circular strip 57 is provided with a rack groove 58, a sliding rack 59 is arranged in the rack groove 58, and two ends of the sliding rack 59 are provided with compression springs 60; one end of the second output shaft 26 is provided with a common gear 61 which is meshed with the sliding rack 59.

The rubber pad 62 is installed on one side of the sliding block 4, and the sliding block 4 can be effectively prevented from being in rigid contact with the hydrogen fuel bottle 72 by the action of the rubber pad 62, and the friction force between the sliding block and the hydrogen fuel bottle 72 can be increased.

The lower surface of the composite wing unmanned aerial vehicle 1 is provided with a rectangular opening 63.

One end of the first branch pipe 50 is provided with a first rubber pipe 64, and one end of the first rubber pipe 64 is fixedly connected with the hollow pipe 31 and is in a communicated state.

The compound wing unmanned aerial vehicle 1 is internally provided with two circular partition plates 65, one side of each circular partition plate 65 is provided with a hydrogen fuel cell 66, the other side of each circular partition plate 65 is provided with a gas distribution valve 67, one end of each gas distribution valve 67 is provided with a fixed pipe 68, and one end of each fixed pipe 68 is provided with a first sealing valve 69.

A first gas pipe 70 is arranged between the gas distribution valve 67 and the hydrogen fuel cell 66, and a second gas pipe 71 is arranged between the gas distribution valve 67 and the hydrogen fuel engine 47.

A hydrogen fuel bottle 72 is arranged in the gas bottle storage box 2, and a sealing valve II 73 is arranged at the output end of the hydrogen fuel bottle 72.

In this embodiment, the electrical appliance of the device is controlled by an external controller, the hollow tube 31 is in a double-layer closed structure (as shown in fig. 8), one half of the bevel gear 42 has a toothed groove, the other half has no toothed groove (as shown in fig. 12), the device is provided with two sets of power systems, the hydrogen fuel engine 47 directly provides power for the propeller of the fixed wing unmanned aerial vehicle, the hydrogen fuel cell 66 provides kinetic energy for the smaller rotor wing, no matter the hydrogen fuel engine 47 or the hydrogen fuel cell 66 requires hydrogen as fuel, by butting the sealing valve II 73 at one end of the hydrogen fuel bottle 72 with the sealing valve I69, the hydrogen gas in the hydrogen fuel bottle 72 can be delivered into the gas distribution valve 67 through the fixed pipe 68, selectively outputting the gas to the hydrogen fuel cell 6 through a gas transmission pipe one 70 or outputting the gas to the hydrogen fuel engine 47 through a gas transmission pipe two 71 by controlling the operation of the gas distribution valve 67;

when a hydrogen fuel bottle 72 needs to be installed, the composite wing unmanned aerial vehicle 1 is fixed, the hydrogen fuel bottle 72 is lifted into the gas bottle storage box 2 through a tool or manually, the upper end of the hydrogen fuel bottle 72 is enabled to be abutted against the upper end of the gas bottle storage box 2, the height of the hydrogen fuel bottle 72 is determined at the moment, the controller controls the stepping motor 24 to rotate forwards and rotate for a specified number of turns, the stepping motor 24 rotates forwards to drive the one-way gear I27 to transmit to the one-way gear I16, the one-way gear II 44 does not transmit, the transmission gear I16 rotates to drive the rotating block 14 to rotate, the rotating block 14 rotates to drive the reciprocating lead screw 11 to move towards the left side, the reciprocating lead screw 11 moves to simultaneously drive the connecting rod 10 and the T-shaped connecting rod 7 to synchronously move, and the T-shaped connecting rod 7 moves to; at this time, the extension spring 21 is in a contracted state, so that the circular baffle plate 19 is firstly contacted with the hydrogen fuel bottle 72, the extension spring 21 is gradually lengthened as the sliding rod 18 slides leftwards, the pressure of the circular baffle plate 19 on the hydrogen fuel bottle 72 is gradually increased, when the pressure is high enough, the hydrogen fuel bottle 72 can be loosened by a hand, the extension spring 21 is gradually lengthened, the sliding block 4 is pushed by the fixing strip 9, the sliding block 4 gradually clamps the hydrogen fuel bottle 72 (as shown in fig. 4), after the fixing, the fastening bolt 23 is manually screwed, so that one end of the fastening bolt 23 abuts against the hydrogen fuel bottle 72, the pressure between the sealing valve two 73 and the sealing valve one 69 is indirectly increased, and the sealing valve two 73 is communicated with the sealing valve one 69; after the gas cylinder storage box is fixed, the gas cylinder storage box 2 and the rectangular opening 63 are sealed by a wind shield manually; when the hydrogen fuel bottle 72 needs to be released, the controller controls the stepping motor 24 to rotate forward again for a specified number of turns, and the T-shaped connecting rod 7 can move rightwards by utilizing the characteristic of the reciprocating lead screw 11, so that the reverse operation is realized, and the purpose of releasing is achieved;

when the stepping motor 24 rotates forwards, the stepping motor 24 drives the common gear 61 to rotate continuously, and by utilizing the characteristic of the sliding rack 59, when the sliding rack 59 slides to the top, the sliding rack 59 can compress the compression spring 60, so that the sliding rack 59 and the common gear 61 are separated intermittently, the common gear 61 idles, when the stepping motor 24 rotates forwards, the position of the trapezoidal block 53 is not influenced, after taking off for a certain time, the output end of the hydrogen fuel bottle 72 can generate a frosting phenomenon, then the controller controls the stepping motor 24 to rotate backwards, the first reverse-rotation unidirectional gear 27 of the stepping motor 24 does not transmit, and the second unidirectional gear 44 and the common gear 61 are driven to transmit; when the stepping motor 24 rotates reversely, the controller controls the electromagnet ring two 35 and the electromagnet ring one 33 to be electrified (the polarities of the electromagnet ring two 35 and the electromagnet ring one 33 are opposite), the electromagnet ring two 35 pushes the electromagnet ring one 33 to move rightwards, the bevel gear one 34 is driven to be attached to the bevel gear two 42, meanwhile, the cleaning brush 39 is driven to be attached to one end of the hydrogen fuel bottle 72, the rotation of the second one-way gear 44 drives the second one-way gear 44 to rotate, the rotation of the second one-way gear 44 drives the second belt pulley 45 to rotate, the second belt pulley 45 drives the first belt pulley 43 below through the transmission belt 46 to rotate, the first belt pulley 43 drives the second bevel gear 42 and the first bevel gear 34 to rotate, and by utilizing the half-tooth characteristic of the second bevel gear 42, when the second bevel gear 42 is engaged with the first bevel gear 34, the arc-shaped hollow bar 37 rotates forward by a certain angle, when the second bevel gear 42 is separated from the first bevel gear 34, the arc-shaped hollow bar 37 is reset by the elasticity of the torsion spring 36;

the common gear 61 is reversely rotated to enable the common gear 61 to be continuously meshed with the sliding rack 59, the sliding rack 59 is driven to slide to one side by the rotation of the common gear 61, the circular strip 57 is driven to slide by the sliding rack 59, the trapezoidal block 53 is indirectly driven to slide, so that the heat which is directly discharged into the atmosphere through the branch pipe II 51 is directly discharged into the atmosphere through the branch pipe I50, the rubber pipe I64 and the arc-shaped hollow strip 37 and finally discharged through the air outlet 38, the heating purpose is achieved, and the defrosting effect is better and obvious; when the sliding rack 59 slides up again, the common gear 61 is separated from the sliding rack 59 again, the continuous reverse rotation of the common gear 61 will not drive the sliding rack 59 to move, and the trapezoidal block 53 is reset again when the stepping motor 24 rotates forward, that is, releases the hydrogen fuel bottle 72.

The technical solutions described above only represent the preferred technical solutions of the present invention, and some possible modifications to some parts of the technical solutions by those skilled in the art all represent the principles of the present invention, and fall within the protection scope of the present invention.