Low-altitude manned aircraft

Abstract

The invention discloses a low-altitude manned aircraft, and relates to the technical field of manned aircrafts, the low-altitude manned aircraft comprises a cavity, the lower surface of the cavity is fixedly connected with a fixing plate, the upper surface of the cavity is provided with a flight mechanism, the flight mechanism comprises a fixing frame and a fixing box, the fixing box is fixedly connected to the outer surface of the cavity, and the fixing plate is fixedly connected to the fixing frame. The fixing frame is fixedly connected to the upper surface of the fixing box, and the flying mechanism is arranged, so that the cavity can complete take-off work under control, and the effect of flying in different directions in the air under control is achieved; an air circulation mechanism penetrates through the upper surface of the cavity, the air circulation mechanism is used for purifying air in the cavity, the air circulation mechanism comprises an exhaust pipe, the exhaust pipe penetrates through the upper surface of the cavity, and a first supporting rod is fixedly connected to the top end of the exhaust pipe; the end of the first supporting rod is fixedly connected with a stepping motor, and the effect that the aircraft can be flexibly changed to stop on the water surface and the ground is achieved.

Description

Technical Field

[0001] The present invention relates to the technical field of manned aircraft, in particular to a low-altitude manned aircraft. Background Art

[0002] As a brilliant achievement in the field of modern aviation, manned aircraft are reshaping the way humans travel and explore. From common civilian helicopters to cutting-edge electric vertical take-off and landing aircraft, they give people wings to soar into the sky with their unique design. In terms of structural design, in order to ensure flight safety and comfort, high-strength lightweight materials such as carbon fiber composite materials are used to reduce the weight of the aircraft and withstand various stresses during flight. The cockpit is equipped with an advanced avionics system, integrated with high-definition display screens, intelligent navigation and automatic driving assistance functions, allowing pilots to accurately control flight attitude, direction and route, and can calmly deal with even complex weather conditions.

[0003] Although the manned aircraft on the market have made many breakthroughs, they still have certain limitations, the most prominent of which is the difficulty in flexibly changing the state of stopping on the water and the ground. From the perspective of design and structure, the landing gear of most traditional civil helicopters and electric vertical take-off and landing aircraft is mostly fixed or only suitable for conventional land landing. If there is a need for forced landing on the water, its structure cannot effectively buffer the impact, and it lacks the design of floating and stable mooring on the water, which can easily cause the aircraft to roll over and sink, endangering the safety of the driver and passengers. Summary of the invention

[0004] To achieve the above objectives, the present invention is implemented through the following technical solutions: a low-altitude manned aircraft, comprising a chamber, a fixing plate is fixedly connected to the lower surface of the chamber, a flying mechanism is arranged on the upper surface of the chamber, the flying mechanism comprises a fixing frame and a fixing box, the fixing box is fixedly connected to the outer surface of the chamber, the fixing frame is fixedly connected to the upper surface of the fixing box, by arranging the flying mechanism, the chamber can complete the take-off work under control, and complete the effect of flying in different directions in the air under control; an air circulation mechanism is passed through the upper surface of the chamber, the air circulation mechanism is used to purify the air in the chamber, the air circulation mechanism comprises an exhaust pipe, the exhaust pipe passes through the upper surface of the chamber, the top end of the exhaust pipe is fixedly connected to a first support rod, the end of the first support rod is fixedly connected to a stepping motor, the output end of the stepping motor is installed with a rotating rod through a coupling, and the end of the rotating rod is fixedly connected to a fan blade; a landing mechanism is arranged on the lower surface of the fixed box, the landing mechanism comprises a connecting frame, the The connecting frame is fixedly connected to the outer side of the fixed box, and the bottom end of the connecting frame is fixedly connected to the limiting ring. The inner cavity of the limiting ring is rotatably connected with a rotating block, and the end of the rotating block is fixedly connected to the rotating frame. By setting an air circulation mechanism, the air in the inner cavity of the chamber can be discharged from the chamber, so that the air in the inner cavity of the chamber can be exchanged with the outside world when flying in the air. When the aircraft is flying, the chamber needs to be kept sealed to prevent external noise and airflow from quickly entering the inner cavity of the chamber, but high sealing will cause the exhaust gas in the inner cavity of the chamber to not be discharged. Therefore, it is necessary to set an air circulation mechanism, and the air circulation mechanism can control the working state of the landing mechanism. By setting a stepper motor, after connecting the power supply and turning on the switch, the rotating rod can drive the fan blades to produce a rotation effect, and the rotating rod can be controlled to rotate forward and reverse. By setting a landing mechanism, when the aircraft needs to land in the water or glide to land, the bottom of the chamber can be protected, so that the aircraft can float on the water surface or produce a moving effect on the land.

[0005] Preferably, the outer surface of the chamber is fixedly connected with a curved glass cover, the outer surface of the chamber is fixedly connected with a limiting frame, the outer surface of the limiting frame is rotatably connected with a rotating plate, the outer surface of the rotating plate is fixedly connected with a hatch cover, the hatch cover is extruded and fitted with the outer side surface of the chamber, a seat is provided on the bottom surface of the inner cavity of the chamber, and an operating table is provided on the inner wall of the chamber. By providing the curved glass cover, the pilot can observe the outside conditions through the curved glass cover when in the inner cavity of the chamber, and the curved shape can reduce air resistance. By providing the limiting frame, the rotating plate can be limited, so that the hatch cover can rotate, and the hatch cover can close the chamber. By providing the operating table, the pilot can control the aircraft.

[0006] Preferably, the outer side surface of the fixing plate is fixedly connected with a bent rod, the end of the bent rod is fixedly connected with an elastic bottom rod, the outer side surface of the fixing plate is symmetrically fixedly connected with an extrusion rod, the bottom end of the extrusion rod is fixedly connected with an extrusion block, the extrusion block is extruded and adapted to the upper surface of the elastic bottom rod, and by providing the elastic bottom rod, the elastic bottom rod can be supported by the ground when the aircraft lands, and by providing the extrusion rod and the extrusion block, the deformation tendency of the elastic bottom rod can be limited when the aircraft lands, preventing the elastic bottom rod from deforming too much and causing the chamber to contact the ground, thereby preventing the chamber from being damaged and threatening the safety of personnel.

[0007] Preferably, a first air-permeable plate passes through the outer side surface of the fixed box, a battery is arranged in the inner cavity of the fixed box, a central controller is fixedly connected to the upper surface of the fixed frame, and the central controller is connected to the battery through a wire row. By setting up a battery, the electricity required for the flight of the device can be stored, and the battery is in contact with the central controller through the wire row, so that the central controller can be connected to the circuit.

[0008] Preferably, connecting tubes are fixedly connected at the corners of the fixing frame, a wire is connected to the outer surface of the central controller, the wire runs through the connecting tube, a fixing ring is fixedly connected to the end of the connecting tube away from the central controller, a servo motor is fixedly connected to the inner wall of the fixing ring, the servo motor is connected to the central controller via a wire, a propeller is installed at the output end of the servo motor via a coupling, and the central controller and the servo motor can be connected together by setting the wire, and then under the control of the central controller, the servo motor can rotate, thereby driving the propeller at the output end to rotate, so that the aircraft can generate downward airflow, and finally the aircraft can take off and fly in the air.

[0009] Preferably, a sieve plate is fixedly connected to the bottom of the inner wall of the exhaust pipe, a limiting tube is fixedly connected to the top of the inner wall of the exhaust pipe, a second air permeable plate is slidably connected to the inner cavity of the limiting tube, a first spring is fixedly connected to the upper surface of the second air permeable plate, the top of the first spring is fixedly connected to the top of the inner wall of the limiting tube, a connecting column is fixedly connected to the lower surface of the second air permeable plate, a blocking plate is fixedly connected to the bottom of the inner wall of the exhaust pipe, a blocking ring is fixedly connected to the bottom of the inner wall of the exhaust pipe, the blocking plate is squeezed and fitted with the upper surface of the blocking ring, and by providing the sieve plate, objects in the inner cavity of the chamber can be prevented from entering the inner cavity of the exhaust pipe, and by providing the limiting tube, the second air permeable plate can be limited. , so that the second air permeable plate can produce the effect of vertical up and down movement in the inner cavity of the limiting tube. By setting the first spring, the second air permeable plate can rebound and return to its original position after the second air permeable plate moves up and down. By setting the blocking plate and the blocking ring, the air in the inner cavity of the chamber will not enter the inner cavity of the exhaust pipe when they are in contact with each other. Therefore, when the stepper motor reverses and the fan blades blow air into the inner cavity of the exhaust pipe, the blocking plate is in contact with the blocking ring, thereby preventing air from entering the inner cavity of the chamber. When the stepper motor rotates forward and the fan blades discharge the airflow in the inner cavity of the exhaust pipe, the blocking plate is kept away from the blocking ring, thereby causing convection between the air in the inner cavity of the chamber and the air outside.

[0010] Preferably, an exhaust mechanism passes through the outer side surface of the exhaust pipe, and the exhaust mechanism includes a connecting box, the connecting box passes through the outer side surface of the exhaust pipe, a third air permeable plate is fixedly connected to the inner wall of the connecting box, a sliding rod is slidably connected to the inner cavity of the third air permeable plate, a sealing plate is fixedly connected to one end of the sliding rod close to the exhaust pipe, a sealing ring is fixedly connected to the outer ring of the sealing plate, the sealing ring is extruded and fitted with the inner wall of the connecting box, and a second spring is sleeved on the outer surface of the sliding rod.

[0011] Preferably, the end of the connecting box away from the exhaust pipe is fixedly connected to a bent pipe, the end of the bent pipe is fixedly connected to a trigger mechanism, the trigger mechanism includes a connecting frame, the connecting frame is fixedly connected to the outer side surface of the fixed box, the inner wall of the connecting frame is fixedly connected to a sealing tube, the end of the bent pipe away from the exhaust pipe is fixedly connected to the top of the sealing tube, the inner cavity of the sealing tube is slidably connected to a piston, the lower surface of the piston is fixedly connected to a connecting rod, the bottom end of the connecting rod is fixedly connected to a tooth plate, the lower surface of the piston is fixedly connected to a third spring, and the bottom end of the third spring is fixedly connected to the bottom surface of the inner cavity of the sealing tube.

[0012] Preferably, a gear is fixedly connected to the side of the rotating block away from the rotating frame, and the gear is meshed with the rack of the gear plate. The gear blocks on the outer surface of the gear are only distributed on a quarter of the circumference. By arranging the gear and arranging the gear blocks only on a quarter of the circumference of the outer surface of the gear, when the gear plate moves downward, the gear will only rotate within a range of ninety degrees. The outer surface of the rotating frame is fixedly connected to a reduction mechanism, and the reduction mechanism includes a limit box, which is fixedly connected to the outer surface of the rotating frame, and a moving plate is slidably connected to the inner cavity of the limit box, and a sliding block is slidably connected to the outer surface of the moving plate. An inclined plate is fixedly connected to the end, a partition rod is fixedly connected to the inner wall of the limit box, and a fourth spring is fixedly connected between the sliding block and the opposite surface of the partition rod. By setting a deceleration mechanism, the resistance of the aircraft can be automatically increased when the aircraft lands, so that the aircraft can be quickly decelerated. By setting a limit box, the movable plate can be limited so that the movable plate can be extended and retracted. By setting an inclined plate, the inclined plate can be affected by wind force under the blowing of airflow, so that the movable plate can be unfolded, thereby increasing the resistance with the air. By setting a fourth spring, the movable plate can rebound to its original position after moving.

[0013] Preferably, the outer surface of the limit box is fixedly connected to a second support rod, and the end of the second support rod is fixedly connected to a floating mechanism, and the floating mechanism includes a first air box, the first air box is fixedly connected to the end of the second support rod, the outer surface of the first air box is fixedly connected to a third support rod, and the end of the third support rod is fixedly connected to the second air box, the outer surface of the first air box is fixedly connected to a limit frame, and a rotating column is rotatably connected to the inner cavity of the limit frame, and the end of the rotating column is fixedly connected to a roller. By setting the floating mechanism, when the aircraft needs to land on a lake or the sea, an upward buoyancy can be provided to the bottom of the aircraft, so that the aircraft can float on the water surface, and at the same time, when the aircraft needs to glide and land, the aircraft can glide stably on the ground. By setting the first air box and the second air box, and the cross-section is triangular, the buoyancy of the aircraft on the water surface can be increased while reducing the air resistance. By setting the limit frame, the rotating column can be limited so that the rotating column can drive the roller to rotate stably, so that the aircraft can slide stably on the road surface when gliding.

[0014] The present invention provides a low-altitude manned aircraft, which has the following beneficial effects:

[0015] 1. The low-altitude manned aircraft can discharge the air in the inner cavity of the chamber by setting an air circulation mechanism, so that the air in the inner cavity of the chamber can be exchanged with the outside world when flying in the air. When the aircraft is flying, the chamber needs to be kept sealed to prevent external noise and airflow from quickly entering the inner cavity of the chamber. However, high sealing will result in the exhaust gas in the inner cavity of the chamber not being discharged. Therefore, an air circulation mechanism needs to be set, and the air circulation mechanism can control the working state of the landing mechanism.

[0016] Second, the low-altitude manned aircraft can reverse the stepper motor and allow the fan blades to blow air into the inner cavity of the exhaust pipe by setting an exhaust mechanism, so that the airflow can enter the inner cavity of the connecting box. By setting a sliding rod, the sealing plate can be driven to produce a lateral movement effect. By setting a sealing plate and a sealing ring, the airflow can be blown to produce lateral movement, so that the airflow can be discharged through the gap between the connecting box and the sealing ring.

[0017] 3. The low-altitude manned aircraft can automatically increase the resistance of the aircraft when it lands by providing a deceleration mechanism, so that the aircraft can be decelerated quickly. The limit box can be provided to limit the movable plate so that the movable plate can be extended and retracted. The inclined plate can be provided so that the inclined plate is affected by the wind force under the blowing of the airflow, so that the movable plate can be unfolded, thereby increasing the resistance with the air. The fourth spring can be provided so that the movable plate can rebound to its original position after it moves.

[0018] Fourth, the low-altitude manned aircraft, by providing a floating mechanism, can provide an upward buoyancy to the bottom of the aircraft when the aircraft needs to land on a lake or the sea, thereby allowing the aircraft to float on the water surface. At the same time, when the aircraft needs to glide to land, the aircraft can glide stably on the ground.

[0019] 5. The low-altitude manned aircraft is provided with a curved glass cover, so that the pilot can observe the outside conditions through the curved glass cover when in the inner cavity of the chamber, and the curved shape can reduce air resistance. By providing a limit frame, the rotating plate can be limited, so that the hatch can rotate and the hatch can close the chamber. By providing an operating table, the pilot can control the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 This is a schematic diagram of the external structure of a low-altitude manned aircraft of the present invention;

[0021] Figure 2 A structural side view of a low-altitude manned aircraft according to the present invention;

[0022] Figure 3It is a partial structural schematic diagram of a low-altitude manned aircraft of the present invention;

[0023] Figure 4 This is a schematic diagram of the structure of the flight mechanism of the present invention;

[0024] Figure 5 It is a schematic diagram of the local structure of the flight mechanism of the present invention;

[0025] Figure 6 This is a schematic diagram of the air circulation mechanism structure of the present invention;

[0026] Figure 7 It is a schematic diagram of the cross-sectional structure of the air circulation mechanism of the present invention;

[0027] Figure 8 For the present invention Figure 6 A schematic diagram of the enlarged structure in the middle;

[0028] Fig. 9 It is a schematic diagram of the structure of the trigger mechanism of the present invention;

[0029] Fig.10 It is a schematic diagram of the structure of the landing mechanism of the present invention;

[0030] Fig.11 It is a schematic diagram of the partial structure of the landing mechanism of the present invention;

[0031] Fig.12 It is a schematic diagram of the structure of the speed reduction mechanism of the present invention;

[0032] Fig.13 It is a schematic diagram of the floating mechanism structure of the present invention.

[0033] In the figure: 1, chamber; 2, fixed plate; 3, bent rod; 4, elastic bottom rod; 5, flight mechanism; 6, air circulation mechanism; 7, landing mechanism; 8, curved glass cover; 9, extrusion rod; 10, extrusion block; 11, limit frame; 12, rotating plate; 13, hatch; 14, operating table; 15, seat; 51, fixed frame; 52, central controller; 53, fixed box; 54, first air permeable plate; 55, battery; 56, wire row; 57, wire; 58, connecting pipe; 59, fixing ring; 510, servo motor; 511, propeller; 61, exhaust pipe; 62, first support rod; 63, stepping motor; 64, fan blade; 65, rotating rod; 66, exhaust mechanism; 67, trigger mechanism; 68, sieve plate; 69, limit pipe; 610, second air permeable plate; 611, first spring; 612, connecting column; 613, blocking plate; 614, blocking ring; 661, connecting box; 662, third air permeable plate; 663, sliding rod; 664, sealing plate; 665, second spring; 666, sealing ring; 667, bent pipe; 671, connecting frame; 672, sealing pipe; 673, piston; 674, third spring; 675, connecting rod; 676, tooth plate; 71, connecting frame; 72, limiting ring; 73, rotating block; 74, gear; 75, rotating frame; 76, speed reduction mechanism; 77, second support rod; 78, floating mechanism; 761, limiting box; 762, moving plate; 763, sliding block; 764, tilting plate; 765, fourth spring; 766, partition rod; 781, first air box; 782, third support rod; 783, second air box; 784, limiting frame; 785, rotating column; 786, roller. DETAILED DESCRIPTION

[0034] The present invention is further described in detail below in conjunction with the accompanying drawings and specific embodiments. The embodiments of the present invention are provided for the purpose of illustration and description, and are not intended to be exhaustive or to limit the present invention to the disclosed forms. Many modifications and variations will be apparent to those of ordinary skill in the art. The embodiments are selected and described in order to better illustrate the principles and practical applications of the present invention, and to enable those of ordinary skill in the art to understand the present invention and thereby design various embodiments with various modifications suitable for specific uses.

[0035] The first embodiment, as Figure 1 - Figure 5As shown, the present invention provides a technical solution: a low-altitude manned aircraft, comprising a chamber 1, a fixing plate 2 is fixedly connected to the lower surface of the chamber 1, a flying mechanism 5 is arranged on the upper surface of the chamber 1, the flying mechanism 5 comprises a fixing frame 51 and a fixing box 53, the fixing box 53 is fixedly connected to the outer surface of the chamber 1, the fixing frame 51 is fixedly connected to the upper surface of the fixing box 53, by arranging the flying mechanism 5, the chamber 1 can complete the take-off work under control, and complete the effect of flying in different directions in the air under control; the upper surface of the chamber 1 is penetrated There is an air circulation mechanism 6, which is used to purify the air in the chamber 1. The air circulation mechanism 6 includes an exhaust pipe 61, and the exhaust pipe 61 passes through the upper surface of the chamber 1. The top of the exhaust pipe 61 is fixedly connected to a first support rod 62, and the end of the first support rod 62 is fixedly connected to a stepper motor 63. The output end of the stepper motor 63 is installed with a rotating rod 65 through a coupling, and the end of the rotating rod 65 is fixedly connected to a fan blade 64; the lower surface of the fixed box 53 is provided with a landing mechanism 7, and the landing mechanism 7 includes a connecting frame 7 1, the connecting frame 71 is fixedly connected to the outer side of the fixed box 53, the bottom end of the connecting frame 71 is fixedly connected to the limiting ring 72, the inner cavity of the limiting ring 72 is rotatably connected to a rotating block 73, and the end of the rotating block 73 is fixedly connected to a rotating frame 75. By setting the air circulation mechanism 6, the air in the inner cavity of the chamber 1 can be discharged from the chamber 1, so that the air in the inner cavity of the chamber 1 can be exchanged with the outside when flying in the air. When the aircraft is flying, the chamber 1 needs to be kept sealed to prevent external noise and airflow from quickly entering the inner cavity of the chamber 1, but the high-density The sealing property will cause the exhaust gas in the inner cavity of the chamber 1 to not be discharged, so it is necessary to set up an air circulation mechanism 6, and the air circulation mechanism 6 can control the working state of the landing mechanism 7. By setting up a stepper motor 63, after connecting to the power supply and turning on the switch, the rotating rod 65 can drive the fan blades 64 to produce a rotation effect, and the rotating rod 65 can be controlled to rotate forward and reverse. By setting up the landing mechanism 7, when the aircraft needs to land in the water or glide and land, the bottom of the chamber 1 can be protected, so that the aircraft can float on the water surface or produce a moving effect on the land surface.

[0036] The outer surface of the chamber 1 is fixedly connected with a curved glass cover 8, the outer surface of the chamber 1 is fixedly connected with a limiting frame 11, the outer surface of the limiting frame 11 is rotatably connected with a rotating plate 12, the outer surface of the rotating plate 12 is fixedly connected with a hatch 13, the hatch 13 is extruded and adapted with the outer side surface of the chamber 1, a seat 15 is provided on the bottom surface of the inner cavity of the chamber 1, and an operating table 14 is provided on the inner wall of the chamber 1. By providing the curved glass cover 8, the pilot can observe the outside conditions through the curved glass cover 8 when in the inner cavity of the chamber 1, and the curved shape can reduce air resistance. By providing the limiting frame 11, the rotating plate 12 can be limited, so that the hatch 13 can rotate, so that the hatch 13 can control the chamber 1 The aircraft is closed and an operating table 14 is provided so that the pilot can control the aircraft. The outer side surface of the fixing plate 2 is fixedly connected with a bending rod 3, and the end of the bending rod 3 is fixedly connected with an elastic bottom rod 4. The outer side surface of the fixing plate 2 is symmetrically fixedly connected with an extrusion rod 9, and the bottom end of the extrusion rod 9 is fixedly connected with an extrusion block 10. The extrusion block 10 is extruded and adapted with the upper surface of the elastic bottom rod 4. By providing the elastic bottom rod 4, the elastic bottom rod 4 can be supported by the ground when the aircraft lands. By providing the extrusion rod 9 and the extrusion block 10, the deformation trend of the elastic bottom rod 4 can be limited when the aircraft lands, so as to prevent the elastic bottom rod 4 from deforming too much and causing the chamber 1 to contact the ground, thereby preventing the chamber 1 from being damaged and threatening the safety of personnel.

[0037] The outer side of the fixed box 53 is penetrated by a first air permeable plate 54, and the inner cavity of the fixed box 53 is provided with a battery 55. The upper surface of the fixed frame 51 is fixedly connected with a central controller 52, and the central controller 52 is connected to the battery 55 through a wire row 56. By providing the battery 55, the power required for the flight of the device can be stored, and the battery 55 is in contact with the central controller 52 through the wire row 56, so that the central controller 52 can be connected to the circuit. The corners of the fixed frame 51 are fixedly connected with connecting pipes 58, and the outer surface of the central controller 52 is connected with a wire 57, and the wire 57 passes through the connecting pipe 58. A fixing ring 59 is fixedly connected to one end away from the central controller 52, and a servo motor 510 is fixedly connected to the inner wall of the fixing ring 59. The servo motor 510 is connected to the central controller 52 through a wire 57, and a propeller 511 is installed at the output end of the servo motor 510 through a coupling. By setting the wire 57, the central controller 52 and the servo motor 510 can be connected together, and then under the control of the central controller 52, the servo motor 510 is rotated, and then the propeller 511 at the output end is driven to rotate, so that the aircraft can generate downward airflow, and finally the aircraft can take off and fly in the air.

[0038] The second embodiment, as Figure 6 - Fig. 9 As shown, a sieve plate 68 is fixedly connected to the bottom of the inner wall of the exhaust pipe 61, a limiting tube 69 is fixedly connected to the top of the inner wall of the exhaust pipe 61, a second air-permeable plate 610 is slidably connected to the inner cavity of the limiting tube 69, a first spring 611 is fixedly connected to the upper surface of the second air-permeable plate 610, a top end of the first spring 611 is fixedly connected to the top of the inner wall of the limiting tube 69, a connecting column 612 is fixedly connected to the lower surface of the second air-permeable plate 610, a blocking plate 613 is fixedly connected to the bottom end of the connecting column 612, a blocking ring 614 is fixedly connected to the bottom of the inner wall of the exhaust pipe 61, the blocking plate 613 is squeezed and fitted with the upper surface of the blocking ring 614, by providing the sieve plate 68, objects in the inner cavity of the chamber 1 can be prevented from entering the inner cavity of the exhaust pipe 61, and by providing the limiting tube 69, the second air-permeable plate 610 can be The second air permeable plate 610 is limited so that it can produce the effect of vertical up and down movement in the inner cavity of the limiting tube 69. By setting the first spring 611, the second air permeable plate 610 can rebound and return to its original position after moving up and down. By setting the blocking plate 613 and the blocking ring 614, the air in the inner cavity of the chamber 1 will not enter the inner cavity of the exhaust pipe 61 when they are in contact with each other. Therefore, when the stepper motor 63 reverses and the fan blades 64 blow air into the inner cavity of the exhaust pipe 61, the blocking plate 613 is in contact with the blocking ring 614, so that the air will not enter the inner cavity of the chamber 1. When the stepper motor 63 rotates forward and the fan blades 64 discharge the airflow in the inner cavity of the exhaust pipe 61, the blocking plate 613 is away from the blocking ring 614, so that the air in the inner cavity of the chamber 1 and the outside air are convected.

[0039] The outer side of the exhaust pipe 61 is penetrated by an exhaust mechanism 66, and the exhaust mechanism 66 includes a connection box 661, and the connection box 661 passes through the outer side of the exhaust pipe 61. A third air permeable plate 662 is fixedly connected to the inner wall of the connection box 661, and a sliding rod 663 is slidably connected to the inner cavity of the third air permeable plate 662. The sliding rod 663 is fixedly connected to an end of the sliding rod 663 close to the exhaust pipe 61. A sealing plate 664 is fixedly connected to the outer ring of the sealing plate 664. The sealing ring 666 is pressed and adapted with the inner wall of the connection box 661. The outer surface of the sliding rod 663 is sleeved with a second spring 665. By setting the exhaust mechanism 6 6, when the stepper motor 63 is reversed and the fan blade 64 blows air into the inner cavity of the exhaust pipe 61, the airflow can enter the inner cavity of the connection box 661. By setting the sliding rod 663, the sealing plate 664 can be driven to produce a lateral movement effect. By setting the sealing plate 664 and the sealing ring 666, the airflow can be blown to produce a lateral movement, so that the airflow can be discharged through the gap between the connection box 661 and the sealing ring 666. The sealing ring 666 is made of rubber and can produce a certain deformation. When negative pressure is generated in the inner cavity of the connection box 661, the sealing ring 666 is deformed, so that the pressure in the inner cavity of the connection box 661 is restored to balance.

[0040] The end of the connection box 661 away from the exhaust pipe 61 is fixedly connected to a bend pipe 667, and the end of the bend pipe 667 is fixedly connected to a trigger mechanism 67. The trigger mechanism 67 includes a connection frame 671, and the connection frame 671 is fixedly connected to the outer side of the fixed box 53. The inner wall of the connection frame 671 is fixedly connected to a sealing tube 672. The end of the bend pipe 667 away from the exhaust pipe 61 is fixedly connected to the top of the sealing tube 672. The inner cavity of the sealing tube 672 is slidably connected to a piston 673. The lower surface of the piston 673 is fixedly connected to a connecting rod 675. The bottom end of the rod 675 is fixedly connected with a tooth plate 676, and the lower surface of the piston 673 is fixedly connected with a third spring 674. The bottom end of the third spring 674 is fixedly connected to the bottom surface of the inner cavity of the sealing tube 672. By setting the bend pipe 667, the connecting box 661 and the sealing tube 672 can be connected together. By setting the sealing tube 672, the piston 673 can be limited so that the piston 673 can move vertically up and down. When the airflow enters the inner cavity of the sealing tube 672 through the bend pipe 667, the piston 673 drives the connecting rod 675 and the tooth plate 676 to move downward.

[0041] The third embodiment, as Fig.10 - Fig.13As shown, a gear 74 is fixedly connected to the side of the rotating block 73 away from the rotating frame 75, and the gear 74 meshes with the rack of the toothed plate 676. The tooth blocks on the outer surface of the gear 74 are only distributed on a quarter of the circumference. By setting the gear 74 and setting the tooth blocks only on a quarter of the circumference of the outer surface of the gear 74, when the toothed plate 676 moves downward, the gear 74 will only rotate within a range of ninety degrees. The outer surface of the rotating frame 75 is fixedly connected to a reduction mechanism 76, and the reduction mechanism 76 includes a limit box 761, and the limit box 761 is fixedly connected to the outer surface of the rotating frame 75. A moving plate 762 is slidably connected to the inner cavity of the limit box 761, and a sliding block 763 is slidably connected to the outer surface of the moving plate 762. The end portion is fixedly connected with an inclined plate 764, the inner wall of the limit box 761 is fixedly connected with a partition rod 766, and the fourth spring 765 is fixedly connected between the sliding block 763 and the opposite surface of the partition rod 766. By setting the deceleration mechanism 76, the resistance of the aircraft can be automatically increased when the aircraft lands, so that the aircraft can be quickly decelerated. By setting the limit box 761, the movable plate 762 can be limited so that the movable plate 762 can be extended and retracted. By setting the inclined plate 764, the inclined plate 764 can be affected by the wind force under the blowing of the airflow, so that the movable plate 762 can be unfolded, thereby increasing the resistance with the air. By setting the fourth spring 765, the movable plate 762 can rebound to its original position after the movable plate 762 moves.

[0042] The outer surface of the limit box 761 is fixedly connected to the second support rod 77, and the end of the second support rod 77 is fixedly connected to the floating mechanism 78. The floating mechanism 78 includes a first air box 781, and the first air box 781 is fixedly connected to the end of the second support rod 77. The outer surface of the first air box 781 is fixedly connected to the third support rod 782, and the end of the third support rod 782 is fixedly connected to the second air box 783. The outer surface of the first air box 781 is fixedly connected to the limit frame 784, and the inner cavity of the limit frame 784 is rotatably connected to a rotating column 785, and the end of the rotating column 785 is fixedly connected to a roller 786. By setting a floating machine Structure 78 can provide an upward buoyancy to the bottom of the aircraft when the aircraft needs to land on a lake or the sea, thereby allowing the aircraft to float on the water surface. At the same time, when the aircraft needs to glide to land, the aircraft can glide stably on the ground. By providing a first air tank 781 and a second air tank 783 with a triangular cross-section, the buoyancy of the aircraft on the water surface can be increased while reducing air resistance. By providing a limit frame 784, the rotating column 785 can be limited so that the rotating column 785 can drive the roller 786 to rotate stably, thereby allowing the aircraft to glide stably on the road surface when gliding.

[0043] Working principle: When in use, the pilot enters the inner cavity of the chamber 1, then rotates the rotating plate 12 to make the hatch 13 close the outer side of the chamber 1, and then controls the operating table 14 to make the battery 55 generate current and flow to the servo motor 510 through the central controller 52 and the wire 57. After the servo motor 510 rotates, it will drive the propeller 511 to rotate, thereby generating a downward airflow. When the airflow gradually increases, the chamber 1 will gradually rise, so that the aircraft can complete the take-off work; when it is necessary to exchange the airflow in the inner cavity of the chamber 1 during the flight, the operator connects the stepper motor 63 to the power supply and controls The output end of the stepper motor 63 rotates forward, so that the fan blades 64 generate airflow and discharge the air in the inner cavity of the exhaust pipe 61. Under the influence of suction, the second air permeable plate 610 moves upward in the inner cavity of the limiting tube 69, so that the blocking plate 613 no longer blocks the blocking ring 614, and finally the air in the inner cavity of the chamber 1 can enter the inner cavity of the exhaust pipe 61 and be finally discharged, so as to achieve the effect of replacing the air in the inner cavity of the chamber 1; when it is necessary to land the aircraft vertically on the ground, the control console 14 is controlled to make the aircraft land smoothly downward. During the landing process, the elastic bottom rod 4 contacts the ground and deforms, thereby buffering the force. At the same time, the extrusion rod 9 and the extrusion block 10 will squeeze the upper surface of the elastic bottom rod 4, so as to prevent the chamber 1 from being excessively lowered and causing contact with the ground; when it is necessary to land the aircraft on the water surface or glide and land, the operator controls the stepper motor 63 to reverse, so that the fan blades 64 rotate in the opposite direction and blow the external airflow into the inner cavity of the exhaust pipe 61. During the continuous blowing process, the sealing plate 664 and the sealing ring 666 are blown and move horizontally, so that the gas enters the inner cavity of the connecting box 661 and enters the inner cavity of the sealing tube 672 through the bend 667. Under the influence of air pressure, the piston 673 drives the connecting rod 675 and the tooth plate 676 move downward, and during the movement, the gear 74 meshes with the tooth plate 676, thereby causing the rotating block 73 and the rotating frame 75 to rotate, and the limit box 761 is in a direction perpendicular to the wind direction, while the first air box 781 and the second air box 783 are parallel to the water surface. When the airflow blows towards the inclined plate 764, the inclined plate 764 is squeezed, thereby causing the moving plate 762 to stretch out, increasing the contact area with the air, thereby achieving the effect of decelerating the aircraft. When the aircraft enters the water surface, the first air box 781 and the second air box 783 will generate upward buoyancy, so that the aircraft can dock on the water surface.

[0044] Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field and related fields without creative work should fall within the scope of protection of the present invention. The structures, devices and operating methods not specifically described and explained in the present invention are implemented according to the conventional means in the field unless otherwise specified and limited.

Claims

1. A low-altitude manned aircraft, comprising a chamber (1), a fixing plate (2) being fixedly connected to the lower surface of the chamber (1), characterized in that: The upper surface of the chamber (1) is provided with a flying mechanism (5), the flying mechanism (5) comprising a fixing frame (51) and a fixing box (53), the fixing box (53) being fixedly connected to the outer surface of the chamber (1), and the fixing frame (51) being fixedly connected to the upper surface of the fixing box (53); the upper surface of the chamber (1) is penetrated by an air circulation mechanism (6), the air circulation mechanism (6) being used for purifying the air in the chamber (1), the air circulation mechanism (6) comprising an exhaust pipe (61), the exhaust pipe (61) being penetrated by the upper surface of the chamber (1), the top end of the exhaust pipe (61) being fixedly connected to a first support rod (62), the first The end of the support rod (62) is fixedly connected to a stepper motor (63), the output end of the stepper motor (63) is installed with a rotating rod (65) through a coupling, and the end of the rotating rod (65) is fixedly connected to a fan blade (64); the lower surface of the fixed box (53) is provided with a landing mechanism (7), and the landing mechanism (7) includes a connecting frame (71), the connecting frame (71) is fixedly connected to the outer side surface of the fixed box (53), the bottom end of the connecting frame (71) is fixedly connected to a limit ring (72), the inner cavity of the limit ring (72) is rotatably connected to a rotating block (73), and the end of the rotating block (73) is fixedly connected to a rotating frame (75).

2. A low altitude manned aircraft according to claim 1, characterized in that: The outer surface of the chamber (1) is fixedly connected to a curved glass cover (8), the outer surface of the chamber (1) is fixedly connected to a limiting frame (11), the outer surface of the limiting frame (11) is rotatably connected to a rotating plate (12), the outer surface of the rotating plate (12) is fixedly connected to a hatch (13), the hatch (13) is extruded and fitted with the outer side surface of the chamber (1), a seat (15) is provided on the bottom surface of the inner cavity of the chamber (1), and an operating table (14) is provided on the inner wall of the chamber (1).

3. A low altitude manned aircraft according to claim 2, characterized in that: The outer side surface of the fixing plate (2) is fixedly connected to a bent rod (3), the end of the bent rod (3) is fixedly connected to an elastic bottom rod (4), the outer side surface of the fixing plate (2) is symmetrically fixedly connected to an extrusion rod (9), the bottom end of the extrusion rod (9) is fixedly connected to an extrusion block (10), and the extrusion block (10) is extruded and adapted to the upper surface of the elastic bottom rod (4).

4. A low-altitude manned aircraft according to claim 3, characterized in that: The outer side surface of the fixed box (53) is penetrated by a first air permeable plate (54), the inner cavity of the fixed box (53) is provided with a storage battery (55), the upper surface of the fixed frame (51) is fixedly connected to a central controller (52), and the central controller (52) is connected to the storage battery (55) via a wire row (56).

5. A low altitude manned aircraft according to claim 4, characterized in that: The corners of the fixing frame (51) are fixedly connected with connecting tubes (58); the outer surface of the central controller (52) is connected with a wire (57); the wire (57) passes through the connecting tube (58); one end of the connecting tube (58) away from the central controller (52) is fixedly connected with a fixing ring (59); the inner wall of the fixing ring (59) is fixedly connected with a servo motor (510); the servo motor (510) is connected to the central controller (52) via the wire (57); and a propeller (511) is installed at the output end of the servo motor (510) via a coupling.

6. A low altitude manned aircraft according to claim 1, characterized in that: A sieve plate (68) is fixedly connected to the bottom of the inner wall of the exhaust pipe (61), a limiting tube (69) is fixedly connected to the top of the inner wall of the exhaust pipe (61), a second air-permeable plate (610) is slidably connected to the inner cavity of the limiting tube (69), a first spring (611) is fixedly connected to the upper surface of the second air-permeable plate (610), the top end of the first spring (611) is fixedly connected to the top of the inner wall of the limiting tube (69), a connecting column (612) is fixedly connected to the lower surface of the second air-permeable plate (610), a blocking plate (613) is fixedly connected to the bottom end of the connecting column (612), a blocking ring (614) is fixedly connected to the bottom of the inner wall of the exhaust pipe (61), and the blocking plate (613) is extruded and matched with the upper surface of the blocking ring (614).

7. A low altitude manned aircraft according to claim 6, characterized in that: An exhaust mechanism (66) passes through the outer side surface of the exhaust pipe (61), and the exhaust mechanism (66) includes a connecting box (661). The connecting box (661) passes through the outer side surface of the exhaust pipe (61). A third air permeable plate (662) is fixedly connected to the inner wall of the connecting box (661). A sliding rod (663) is slidably connected to the inner cavity of the third air permeable plate (662). A sealing plate (664) is fixedly connected to one end of the sliding rod (663) close to the exhaust pipe (61). A sealing ring (666) is fixedly connected to the outer ring of the sealing plate (664). The sealing ring (666) is pressed and fitted with the inner wall of the connecting box (661). A second spring (665) is sleeved on the outer surface of the sliding rod (663).

8. A low altitude manned aircraft according to claim 7, characterized in that: The end of the connection box (661) away from the exhaust pipe (61) is fixedly connected to a bent pipe (667), the end of the bent pipe (667) is fixedly connected to a trigger mechanism (67), the trigger mechanism (67) comprises a connection frame (671), the connection frame (671) is fixedly connected to the outer side surface of the fixed box (53), the inner wall of the connection frame (671) is fixedly connected to a sealing pipe (672), and the end of the bent pipe (667) away from the exhaust pipe (61) is fixedly connected to the trigger mechanism (67), and the trigger mechanism (67) comprises a connection frame (671). The connection frame (671) is fixedly connected to the outer side surface of the fixed box (53), and the inner wall of the connection frame (671) is fixedly connected to a sealing pipe (672). It is fixedly connected to the top end of the sealing tube (672), and a piston (673) is slidably connected to the inner cavity of the sealing tube (672). The lower surface of the piston (673) is fixedly connected to a connecting rod (675), and the bottom end of the connecting rod (675) is fixedly connected to a toothed plate (676). The lower surface of the piston (673) is fixedly connected to a third spring (674), and the bottom end of the third spring (674) is fixedly connected to the bottom surface of the inner cavity of the sealing tube (672).

9. A low-altitude manned aircraft according to claim 8, characterized in that: A gear (74) is fixedly connected to the side of the rotating block (73) away from the rotating frame (75), and the gear (74) is meshed with the rack of the toothed plate (676). The tooth blocks on the outer surface of the gear (74) are only distributed over a quarter of the circumference. A reduction mechanism (76) is fixedly connected to the outer surface of the rotating frame (75). The reduction mechanism (76) comprises a limit box (761). The limit box (761) is fixedly connected to the outer surface of the rotating frame (75). A moving plate (762) is slidably connected to the inner cavity of the limit box (761). The outer surface of the moving plate (762) is slidably connected to a sliding block (763). The end of the sliding block (763) is fixedly connected to an inclined plate (764). A partition rod (766) is fixedly connected to the inner wall of the limit box (761). A fourth spring (765) is fixedly connected between the opposite surfaces of the sliding block (763) and the partition rod (766).

10. A low altitude manned aircraft according to claim 9, characterized in that: The outer surface of the limit box (761) is fixedly connected to a second support rod (77), the end of the second support rod (77) is fixedly connected to a floating mechanism (78), the floating mechanism (78) comprises a first air box (781), the first air box (781) is fixedly connected to the end of the second support rod (77), the outer surface of the first air box (781) is fixedly connected to a third support rod (782), the end of the third support rod (782) is fixedly connected to the second air box (783), the outer surface of the first air box (781) is fixedly connected to a limit frame (784), the inner cavity of the limit frame (784) is rotatably connected to a rotating column (785), and the end of the rotating column (785) is fixedly connected to a roller (786).

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