A lift wing-shaped disc-type vertical take-off and landing aircraft

Abstract

The present invention discloses a lift wing type disc type vertical take-off and landing aircraft, which relates to the field of vertical take-off and landing aircraft, including a fuselage, an engine, a cockpit, an installation box and a landing gear, wherein the engine is arranged on the side of the fuselage, and a cockpit is arranged below the fuselage, an installation box is arranged on the rear side of the cockpit, and a landing gear is arranged on the outside of the cockpit, a battery box is arranged inside the installation box, and a conductive module is arranged above the battery box and inside the installation box, and the left side of the installation box is designed in an open structure so that the battery box can slide out. The lift wing type disc type vertical take-off and landing aircraft adopts 8 ducted propeller brushless motor engines embedded in the edge of the upper wing, and the 8 ducted engines have uniform power distribution and high redundancy. When an engine fails such as stopping, the aircraft has sufficient time to make an emergency landing or return, and the ducted engines embedded in the wings can effectively avoid the danger and accident of people or objects being mixed into the engine propeller blades.

Description

Technical Field

[0001] The invention relates to the technical field of vertical take-off and landing flight, in particular to a lift wing-shaped disc-type vertical take-off and landing aircraft. Background Art

[0002] Prior art 1 (publication number CN115402509B, Chinese patent published on February 3, 2023) A vertical take-off and landing aircraft, comprising: a fuselage for accommodating power batteries and mission loads; a main wing, fixedly connected to the tail of the fuselage; a front canard, spaced apart from the main wing and fixedly connected to the front of the fuselage; a connecting rod, one end of which is fixedly connected to the front canard and the other end is fixedly connected to the main wing, and can bear the load; a horizontal lift unit, fixedly connected to the connecting rod and driven by the connecting rod to the main wing and the front canard; an inclined power unit, located behind the main wing and fixedly arranged at the end of the connecting rod, the inclined power unit is arranged at a fixed angle to provide thrust and auxiliary lift. The vertical take-off and landing aircraft avoids the process of installing a tilting mechanism in the prior art, reduces production costs, simplifies the structure, and is easier to produce and use; and avoids the failure of the tilting mechanism and the unstable connection between the tilting mechanism and the aircraft when the tilting mechanism is used, thereby improving the reliability and stability of the aircraft; Prior art 2 (publication number CN216332748U, a Chinese patent published on April 19, 2022) An electric vertical take-off and landing manned aircraft, comprising a lower wing installed at the front lower end of the fuselage, motor fairings at both ends of the lower wing, and two front rotors installed above the fairings; an upper wing is installed at the rear upper end of the fuselage, vertical tails are installed at both ends of the upper wing, and a rear rotor is installed on the top of the vertical tail; the rotor diameter of the rear rotor is larger than that of the front rotor, and the front rotor and the rear rotor are symmetrical on the left and right; the application realizes that all power systems of the entire machine are provided by electric energy, and has the same advantages as helicopters, such as vertical take-off and landing and low requirements for take-off and landing, which has great advantages in short-distance transportation.

[0003] Current vertical take-off and landing aircraft, when using pure electric drive, generally need to carry heavy batteries to power them. However, in the event of an accidental fall or collision, the battery will accelerate the aircraft's descent. At the same time, the battery is also prone to fire and other disasters after a collision, increasing the possibility of secondary risks after the fall. Summary of the invention

[0004] The purpose of the present invention is to provide a lift-wing-shaped disc-type vertical take-off and landing aircraft to solve the problem raised in the above background technology that the current vertical take-off and landing aircraft generally needs to carry heavy batteries to supply energy when using pure electric drive, but in the event of an accidental fall or collision, the battery will accelerate the falling speed of the aircraft, and the battery is also prone to fire and other disasters after a collision.

[0005] To achieve the above-mentioned purpose, the present invention provides the following technical solutions: a lift-wing-type disc-type vertical take-off and landing aircraft, comprising a fuselage, an engine, a cockpit, an installation box and a landing gear, wherein the engine is arranged on the side of the fuselage, and the cockpit is installed below the fuselage, the installation box is arranged on the rear side of the cockpit, and the landing gear is arranged on the outside of the cockpit, a battery box is arranged inside the installation box, and conductive modules are arranged above the battery box and inside the installation box, and the left side of the installation box is designed in an open structure so that the battery box can slide out, a mounting base is arranged below the battery box, and a detachable connection is formed between the mounting base and the mounting box, and the mounting base is removed to take out the battery box from the bottom of the installation box, and a baffle is arranged on the left side of the installation box to provide a lift for the battery box. For shielding, a first parachute bag is arranged inside the battery box, and a first parachute opener for controlling the first parachute bag is arranged on the right side of the battery box, and a first control head is connected to the right side of the first parachute opener, an automatic control mechanism is arranged on the right side of the first control head to control the operation of the first parachute opener, a push plate is arranged inside the installation box, and the push plate is located on the right side of the battery box, and a second spring is fixed on the right side of the push plate to provide a left thrust for the push plate, a driving block is fixed on the right side of the push plate, and a limiting mechanism is arranged on the outer side of the driving block to provide a limiting effect on the movement of the driving block, a control shaft is fixed on the front side of the baffle to control the movement of the baffle, and the control shaft is rotatably installed inside the installation box, and a rotation control mechanism is arranged at the end of the control shaft.

[0006] To further optimize the technical solution, the engine is distributed in eight groups on the edge of the fuselage, wing blades are provided on the outside of the fuselage, and the fuselage is designed in a butterfly-shaped structure.

[0007] To further optimize the technical solution, the automatic control mechanism includes a first connector, a guide frame and a pulling mechanism;

[0008] A first connecting head, fixed on the right side of the first control head;

[0009] The guide frame is fixed inside the installation box, and the upper and lower ends of the guide frame are designed as through structures, and an up and down sliding structure is formed between the guide frame and the first connector;

[0010] The pulling mechanism is arranged on the outside of the first connecting head.

[0011] To further optimize the technical solution, the pulling mechanism includes a movable block, a first spring and an extrusion groove;

[0012] The movable block is arranged inside the first connector and between the first connector to form a forward and backward sliding structure, and the left side of the movable block is designed to be inclined;

[0013] A first spring, arranged at the inner end of the movable block to provide thrust for the movable block;

[0014] The extrusion groove is arranged inside the guide frame, and the outer end of the movable block is located inside the extrusion groove.

[0015] To further optimize the technical solution, a storage cavity is provided on the outer side of the push plate, and the second spring is provided inside the storage cavity.

[0016] To further optimize the technical solution, a second parachute bag is arranged above the body, a second parachute opener is arranged inside the installation box, a second control head is connected below the second parachute opener, and a second connecting head is fixed below the second control head, the second connecting head is located above the driving block, and a fourth spring is arranged on the outside of the second connecting head to provide downward thrust for the second connecting head.

[0017] To further optimize the technical solution, the limiting mechanism includes a limiting groove, a limiting block, a third spring, a first control rope and a control plate;

[0018] A limit groove is provided below the driving block;

[0019] A limit block is arranged below the limit slot and between the limit slots to form a snap-fit ​​structure, and an up-and-down sliding structure is formed between the limit block and the installation box;

[0020] A third spring is used to fix the lower part of the limit block;

[0021] A first control rope is fixed below the limit block;

[0022] The control panel is fixed on the right end of the first control rope, and a left-right sliding structure is formed between the control panel and the installation box.

[0023] To further optimize the technical solution, the rotation control mechanism includes a first gear, a transmission plate, a drive rod and an operating mechanism;

[0024] A first gear, fixed to the right end of the control shaft;

[0025] A transmission plate is arranged at the rear side of the first gear, and a meshing connection is formed between the transmission plate and the first gear, and an up-and-down sliding structure is formed between the transmission plate and the mounting box;

[0026] A driving rod passes through the transmission plate and forms a threaded connection between the transmission plates, and a rotational connection is formed between the driving rod and the mounting box;

[0027] The operating mechanism is connected to the driving rod to operate the rotation of the driving rod.

[0028] Further optimizing the technical solution, the operating mechanism includes a second gear, a connecting plate, a second control rope and a fifth spring;

[0029] a second gear fixed to the surface of the driving rod;

[0030] A connecting plate is arranged on the outer side of the second gear and is meshed with the second gear, and a left-right sliding structure is formed between the connecting plate and the mounting box, and the connecting plate is located on the left side of the control panel;

[0031] a second control rope, fixed to the right side of the connecting plate, the end of the second control rope being connected to the cockpit;

[0032] The fifth spring is arranged on the right side of the connecting plate to provide thrust for the connecting plate.

[0033] Compared with the prior art, the present invention has the following beneficial effects:

[0034] (1) This aircraft uses a total of 8 ducted propeller brushless motor engines embedded in the edge of the upper wing. The 8 ducted engines have uniform power distribution and high redundancy. When an engine fails, the aircraft has sufficient time to make an emergency landing or return. The ducted engines embedded in the wings can effectively avoid the danger and accident of people or objects being entangled in the engine propeller blades. The engines are installed on the edge of the wings, and the larger lever arm increases the operating capacity.

[0035] (2) The wings of this aircraft are designed to be disc-shaped. First, the circular shape of the wings can be deformed in the event of an accidental fall, effectively absorbing the impact energy, protecting the integrity of the aircraft and fuselage, and protecting the occupants.

[0036] (3) The battery box and installation box of the aircraft are detachable. In the event of an accident, the battery box can be urgently sent out from the installation box to separate the battery box and the aircraft, thereby avoiding the risk of battery box explosion to the cockpit. At the same time, the detached battery box can be slowly lowered by the first parachute pack to improve its safety.

[0037] (4) The second parachute pack can provide a slow-descent effect for the aircraft body, and after the battery box is pushed out, the second parachute opener automatically works to control the opening of the second parachute pack, thereby improving the overall safety of the aircraft.

[0038] (5) The movement of the baffle can release the limiting effect on the battery box, and the movement of the baffle can be controlled by pulling the second control rope, and the second control rope is automatically released after pulling the limiting effect on the push plate, so that the battery is pushed out and the parachute bag is opened synchronously. BRIEF DESCRIPTION OF THE DRAWINGS

[0039] Figure 1 It is a schematic diagram of the three-dimensional structure of the present invention;

[0040] Figure 2 It is a bottom view structural schematic diagram of the present invention;

[0041] Figure 3It is a side view structural schematic diagram of the present invention;

[0042] Figure 4 This is a bottom view of the structure of the installation box of the present invention;

[0043] Figure 5 This is a schematic diagram of the three-dimensional structure of the battery box of the present invention;

[0044] Figure 6 This is a schematic diagram of the main cross-sectional structure of the installation box of the present invention;

[0045] Figure 7 It is a schematic diagram of the top-sectional structure of the guide frame of the present invention;

[0046] Figure 8 This is a schematic diagram of the main cross-sectional structure of the control shaft of the present invention;

[0047] Fig. 9 It is a schematic diagram of the side sectional structure of the first gear of the present invention;

[0048] Fig.10 This is a schematic diagram of the top view of the second gear structure of the present invention.

[0049] In the figure: 1, fuselage; 2, engine; 3, cockpit; 4, installation box; 5, landing gear; 6, wing blade; 7, battery box; 8, installation base; 9, baffle; 10, control shaft; 11, conductive module; 12, first parachute bag; 13, first parachute opener; 14, first control head; 15, first connector; 16, guide frame; 17, movable block; 18, first spring; 19, extrusion groove; 20, push plate; 21, drive block; 2 2. Second spring; 23. Storage cavity; 24. Limiting groove; 25. Limiting block; 26. Third spring; 27. First control rope; 28. Control board; 29. ​​Second parachute bag; 30. Second parachute opener; 31. Second control head; 32. Second connecting head; 33. Fourth spring; 34. First gear; 35. Transmission plate; 36. Drive rod; 37. Second gear; 38. Connecting plate; 39. Second control rope; 40. Fifth spring. DETAILED DESCRIPTION

[0050] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0051] See also Figure 1-Figure 10The present invention provides the following technical solution: a lift-wing-shaped disc-type vertical take-off and landing aircraft, comprising a body 1, an engine 2, a cockpit 3, a mounting box 4 and a landing gear 5, wherein the engine 2 is arranged on the side of the body 1, and the cockpit 3 is installed below the body 1, the mounting box 4 is arranged on the rear side of the cockpit 3, and the landing gear 5 is arranged on the outside of the cockpit 3;

[0052] Embodiment 1: The present invention provides the following technical solution, which discloses that a battery box 7 is arranged inside the installation box 4, a conductive module 11 is arranged above the battery box 7 and inside the installation box 4, and the left side of the installation box 4 is designed in an open structure so that the battery box 7 can slide out, a mounting base plate 8 is arranged below the battery box 7, and a detachable connection is formed between the mounting base plate 8 and the installation box 4, the mounting base plate 8 is removed to take the battery box 7 out from the bottom of the installation box 4, a baffle 9 is arranged on the left side of the installation box 4 to provide shielding for the battery box 7, a first parachute pack 12 is arranged inside the battery box 7, and a first parachute opener 13 for controlling the first parachute pack 12 is arranged on the right side of the battery box 7, and a first control head 14 is connected to the right side of the first parachute opener 13, and the first control An automatic control mechanism is provided on the right side of the head 14 to control the operation of the first parachute opener 13, a push plate 20 is provided inside the installation box 4, and the push plate 20 is located on the right side of the battery box 7, and a second spring 22 is fixed to the right side of the push plate 20 to provide a left thrust for the push plate 20, a driving block 21 is fixed to the right side of the push plate 20, and a limiting mechanism is provided on the outer side of the driving block 21 to provide a limiting effect on the movement of the driving block 21, a control shaft 10 is fixed on the front side of the baffle 9 to control the movement of the baffle 9, and the control shaft 10 is rotatably installed inside the installation box 4, and a rotation control mechanism is provided at the end of the control shaft 10, eight groups of engines 2 are distributed on the edge of the fuselage 1, and a wing knife 6 is provided on the outer side of the fuselage 1, and the fuselage 1 is designed in a butterfly shape.

[0053] This aircraft uses a total of 8 ducted propeller brushless motor engines 2 embedded in the edge of the upper wing. The 8 ducted engines 2 have uniform power distribution and high redundancy. When an engine 2 stops or fails, the aircraft has sufficient time to make an emergency landing or return. The ducted engines 2 embedded in the wing can effectively avoid the danger and accident of people or objects being mixed into the propeller blades of the engine 2. The engine 2 is installed on the edge of the wing, and the larger force arm increases the operating capacity. When the aircraft takes off and lands vertically, the 8 engines 2 provide all the lift. When climbing or descending with a slope, the duct tilting provides lift and thrust at the same time. When flying horizontally, it provides thrust and a small amount of lift. All attitude controls of this aircraft, including pitch, yaw, roll, etc., are achieved by the engine 2 through the adjustment of the speed and angle. Among them, the pitch attitude is controlled by the front and rear 4 engines 2, and the front two engines 2 provide the main lift during flight. The two engines 2 on the left and right sides can realize the U-turn of the aircraft around the geometric center or a U-turn with a small turning radius by reverse deflection, and can also realize the yaw of the aircraft by deflection in the same direction but at different deflection angles.

[0054] The wings of the fuselage 1 of this aircraft are designed to be disc-shaped. First, the circular shape of the wing can be deformed to effectively absorb the impact energy in the event of an accidental fall, protect the integrity of the fuselage, and protect the occupants. Second, the wing between the fuselage 1 and the left and right engines is designed as a low-speed asymmetric SD7032 airfoil. This airfoil geometry is relatively simple, has a large maximum lift coefficient and a low drag coefficient, and performs well under low Reynolds numbers. The wing area is about 6.5 square meters, which provides the main lift for the aircraft in the level flight cruise phase, effectively improves the aerodynamic performance of the aircraft, reduces energy consumption and take-off weight, and increases the range. Third, the circular wing can evenly distribute the engine 2. When a single engine 2 fails, it can reduce its impact on the stability of the aircraft, and the aircraft has ample time to return or make an emergency landing.

[0055] In order to prevent the airflow on the wing surface from flowing into the duct of the engine 2, or the exhaust of the duct from affecting the airflow below, the wing is provided with wing blades 6 to improve the aerodynamic performance.

[0056] The aircraft landing gear 5 adopts a retractable front three-point layout, and the landing gear 5 structure is a solid spring type, and the landing gear can be retracted during cruising flight. The spring-type landing gear 5 can absorb impact force during take-off and landing, improve the take-off and landing quality, and in addition, when the descent rate is large or an accidental fall occurs, it can effectively resist impact deformation and protect the occupants.

[0057] This aircraft design has designed a low-speed lift airfoil with an effective wing area of ​​6.5 square meters, which can provide lift for the entire aircraft after reaching the cruising speed, greatly improving the aerodynamic efficiency of the aircraft. Secondly, the vertical ducted propeller engine 2 and the curved surface of the disc-shaped wing can effectively form a Coanda effect, which can increase lift during vertical takeoff and landing. The specific lift and drag estimates are as follows:

[0058] The wing installation angle of attack is designed to be 2.47 degrees. The lift coefficient C of the SD7032 airfoil at this angle of attack L =0.686, resistance coefficient C D =0.0183. Lift:

[0059] L=1 / 2ρv 2 SC L =7190N=734KG

[0060] Resistance caused by lifting:

[0061] L=1 / 2ρv 2 SC D =192N=19.6KG

[0062] The total resistance, i.e. the sum of pressure difference resistance, friction resistance and lift resistance, is estimated at a maximum of 40KG.

[0063] For manned vertical take-off and landing flying cars or aircraft, if the number of lift engines 2 is small, as long as one engine 2 fails, the aircraft will find it difficult to redistribute the power balance, or it will need to be equipped with engines 2 with a large power margin to achieve power balance. If any two engines 2 fail, a serious disaster will occur. Compared with such aircraft, 8 engines 2 increase the safety margin. If any 1-2 engines fail, the aircraft can easily balance the lift, achieve return or forced landing, and avoid serious disasters.

[0064] Embodiment 2: On the basis of embodiment 1, an automatic control mechanism is disclosed, which includes a first connecting head 15, a guide frame 16 and a pulling mechanism. The first connecting head 15 is fixed on the right side of the first control head 14. The guide frame 16 is fixed inside the installation box 4, and the upper and lower ends of the guide frame 16 are designed as a through structure, and an up and down sliding structure is formed between the guide frame 16 and the first connecting head 15. The pulling mechanism is arranged on the outside of the first connecting head 15. The pulling mechanism includes a movable block 17, a first spring 18 and an extrusion groove 19. The movable block 17 is arranged inside the first connecting head 15 and between the first connecting head 15 to form a front and back sliding structure, and the left side of the movable block 17 is designed as an inclined structure. The first spring 18 is arranged at the inner end of the movable block 17 to provide thrust for the movable block 17. The extrusion groove 19 is opened inside the guide frame 16, and the outer end of the movable block 17 is located inside the extrusion groove 19.

[0065] The battery box 7 in the installation box 4 transmits electricity through the conductive module 11. When the battery box 7 is removed normally, the installation base plate 8 is removed, the battery box 7 is removed vertically, and the first connecting head 15 slides out of the guide frame 16 without triggering the first parachute opener 13. When an accident occurs and the battery box 7 needs to be separated, the baffle 9 is controlled to move, and the limit of the driving block 21 is released at the same time, so that the push plate 20 pushes the battery box 7 to move under the action of the second spring 22, and pushes it out of the installation box 4. At the same time, the movable block 17 on the outer side of the first connecting head 15 is positioned by the extrusion groove 19 to pull the first control head 14 to move, triggering the first parachute opener 13. After the first control head 14 reaches the maximum pull-out distance, the battery box 7 continues to move. The first connecting head 15 is pulled so that the movable block 17 is squeezed by the extrusion groove 19 to move, so that the movable block 17 is separated from the connection with the extrusion groove 19, and the battery box 7 falls off. After the battery box 7 falls off, the first parachute bag 12 on the battery box 7 opens, so that it can land safely.

[0066] Embodiment 3: Based on the embodiment 1, a storage chamber 23 is provided on the outer side of the push plate 20, a second spring 22 is provided inside the storage chamber 23, a second parachute bag 29 is provided above the body 1, a second parachute opener 30 is provided inside the installation box 4, and a second control head 31 is connected below the second parachute opener 30, and a second connecting head 32 is fixed below the second control head 31, the second connecting head 32 is located above the driving block 21, and a fourth spring 33 is provided on the outer side of the second connecting head 32 to provide a downward thrust for the second connecting head 32, and the limit The mechanism includes a limit groove 24, a limit block 25, a third spring 26, a first control rope 27 and a control plate 28. The limit groove 24 is opened below the driving block 21. The limit block 25 is arranged below the limit groove 24 and between the limit groove 24 to form a snap-fit ​​structure, and an up-and-down sliding structure is formed between the limit block 25 and the installation box 4. The third spring 26 is fixed below the limit block 25. The first control rope 27 is fixed below the limit block 25. The control plate 28 is fixed at the right end of the first control rope 27, and a left-right sliding structure is formed between the control plate 28 and the installation box 4. The rotation control mechanism includes a first gear 34, a transmission plate 35, a drive rod 36 and an operating mechanism. The first gear 34 is fixed to the right end of the control shaft 10. The transmission plate 35 is arranged at the rear side of the first gear 34, and the transmission plate 35 and the first gear 34 are meshed and connected, and the transmission plate 35 and the installation box 4 form an up and down sliding structure. The drive rod 36 penetrates the transmission plate 35 and the transmission plate 35 is threadedly connected, and the drive rod 36 and the installation box 4 are rotatably connected. The operating mechanism is connected to the drive rod 36 to operate the rotation of the drive rod 36. The operating mechanism It includes a second gear 37, a connecting plate 38, a second control rope 39 and a fifth spring 40. The second gear 37 is fixed on the surface of the driving rod 36. The connecting plate 38 is arranged on the outer side of the second gear 37 and forms a meshing connection between the second gear 37. A left-right sliding structure is formed between the connecting plate 38 and the mounting box 4. The connecting plate 38 is located on the left side of the control plate 28. The second control rope 39 is fixed on the right side of the connecting plate 38. The end of the second control rope 39 is connected to the cockpit 3. The fifth spring 40 is arranged on the right side of the connecting plate 38 to provide thrust for the connecting plate 38.

[0067] The second control rope 39 is connected to the cockpit 3. In an emergency, the second control rope 39 can be pulled to pull the connecting plate 38 to move. The connecting plate 38 drives the driving rod 36 to rotate through the engagement between the connecting plate 38 and the second gear 37. The driving rod 36 drives the transmission plate 35 to move. The transmission plate 35 drives the control shaft 10 to rotate through the engagement with the first gear 34, so that the baffle 9 moves. At the same time, after the connecting plate 38 moves, the control plate 28 can be pushed to move, so that the control plate 28 pulls the limit block 25 to move through the first control rope 27, releases the connection between the limit block 25 and the limit groove 24, and makes the second spring 22 push the battery box 7 to move outward. At the same time, after the driving block 21 moves, the supporting force on the second connecting head 32 disappears, and the second connecting head 32 will drive the second control head 31 to move, triggering the second parachute opener 30 to open the second parachute bag 29, providing landing buffer protection for the aircraft.

[0068] The contents not described in detail in this specification belong to the prior art known to professional and technical personnel in this field.

[0069] Although the present invention has been described in detail with reference to the aforementioned embodiments, it is still possible for those skilled in the art to modify the technical solutions described in the aforementioned embodiments, or to make equivalent substitutions for some of the technical features therein. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A lift-wing-shaped disc-type vertical take-off and landing aircraft, comprising a body (1), an engine (2), a cockpit (3), a mounting box (4) and a landing gear (5), wherein the engine (2) is arranged on the side of the body (1), the cockpit (3) is installed below the body (1), the mounting box (4) is arranged at the rear side of the cockpit (3), and the landing gear (5) is arranged on the outside of the cockpit (3); Features: A battery box (7) is arranged inside the installation box (4), and a conductive module (11) is arranged above the battery box (7) and inside the installation box (4), and the left side of the installation box (4) is designed in an open structure so that the battery box (7) can slide out, and a mounting base plate (8) is arranged below the battery box (7), and the mounting base plate (8) and the installation box (4) are detachably connected, and the mounting base plate (8) is removed to remove the battery box (7) from the bottom of the installation box (4), and a baffle is arranged on the left side of the installation box (4). (9), providing a shield for the battery box (7), wherein a first parachute bag (12) is arranged inside the battery box (7), and a first parachute opener (13) for controlling the first parachute bag (12) is arranged on the right side of the battery box (7), and a first control head (14) is connected to the right side of the first parachute opener (13), and an automatic control mechanism is arranged on the right side of the first control head (14) for controlling the operation of the first parachute opener (13), and a push plate (20) is arranged inside the installation box (4), and the push plate (20) is located at the battery box (7). The right side of the box (7) is fixed with a second spring (22) on the right side of the push plate (20) to provide a leftward thrust for the push plate (20); a driving block (21) is fixed on the right side of the push plate (20); a limiting mechanism is arranged on the outer side of the driving block (21) to provide a limiting effect on the movement of the driving block (21); a control shaft (10) is fixed on the front side of the baffle (9) to control the movement of the baffle (9); the control shaft (10) is rotatably mounted inside the mounting box (4); and a limit mechanism is arranged at the end of the control shaft (10) A rotation control mechanism, wherein a second parachute bag (29) is arranged above the body (1), a second parachute opener (30) is arranged inside the installation box (4), a second control head (31) is connected below the second parachute opener (30), and a second connecting head (32) is fixed below the second control head (31), the second connecting head (32) is located above the driving block (21), and a fourth spring (33) is arranged outside the second connecting head (32) to provide downward thrust for the second connecting head (32).

2. A lift-wing-shaped disc-type vertical take-off and landing aircraft according to claim 1, characterized in that: The engine (2) has eight groups distributed on the edge of the body (1), and wing blades (6) are arranged on the outside of the body (1), and the body (1) is designed in a disc-shaped structure.

3. A lift-wing-shaped disc-type vertical take-off and landing aircraft according to claim 1, characterized in that: The automatic control mechanism comprises a first connecting head (15), a guide frame (16) and a pulling mechanism; A first connecting head (15) fixed on the right side of the first control head (14); A guide frame (16) is fixed inside the installation box (4), and the upper and lower ends of the guide frame (16) are designed as through-type structures, and an up-and-down sliding structure is formed between the guide frame (16) and the first connector (15); The pulling mechanism is arranged on the outside of the first connecting head (15).

4. A lift-wing-shaped disc-type vertical take-off and landing aircraft according to claim 3, characterized in that: The pulling mechanism comprises a movable block (17), a first spring (18) and an extrusion groove (19); The movable block (17) is arranged inside the first connector (15) and between the first connector (15) to form a forward and backward sliding structure, and the left side of the movable block (17) is designed to be inclined; A first spring (18), arranged at the inner end of the movable block (17) to provide a thrust for the movable block (17); The extrusion groove (19) is opened inside the guide frame (16), and the outer end of the movable block (17) is located inside the extrusion groove (19).

5. The lift-wing-shaped disc-type vertical take-off and landing aircraft according to claim 1, characterized in that: A receiving cavity (23) is provided on the outer side of the push plate (20), and the second spring (22) is arranged inside the receiving cavity (23).

6. The lift-wing-shaped disc-type vertical take-off and landing aircraft according to claim 1, characterized in that: The limiting mechanism comprises a limiting groove (24), a limiting block (25), a third spring (26), a first control rope (27) and a control plate (28); A limit groove (24) is provided below the driving block (21); A limit block (25) is arranged below the limit slot (24) and between the limit slot (24) to form a snap-fit ​​structure, and an up-and-down sliding structure is formed between the limit block (25) and the installation box (4); A third spring (26) is fixed below the limit block (25); A first control rope (27) is fixed below the limit block (25); The control panel (28) is fixed to the right end of the first control rope (27), and a left-right sliding structure is formed between the control panel (28) and the installation box (4).

7. A lift-wing-shaped disc-type vertical take-off and landing aircraft according to claim 6, characterized in that: The rotation control mechanism comprises a first gear (34), a transmission plate (35), a drive rod (36) and an operating mechanism; A first gear (34) is fixed to the right end of the control shaft (10); A transmission plate (35) is arranged on the rear side of the first gear (34), and a meshing connection is formed between the transmission plate (35) and the first gear (34), and an up-and-down sliding structure is formed between the transmission plate (35) and the mounting box (4); A driving rod (36) passes through the transmission plate (35) and forms a threaded connection between the transmission plate (35), and a rotational connection is formed between the driving rod (36) and the mounting box (4); The operating mechanism is connected to the driving rod (36) to operate the rotation of the driving rod (36).

8. The lift-wing-shaped disc-type vertical take-off and landing aircraft according to claim 7, characterized in that: The operating mechanism comprises a second gear (37), a connecting plate (38), a second control rope (39) and a fifth spring (40); A second gear (37) is fixed on the surface of the driving rod (36); A connecting plate (38) is arranged on the outside of the second gear (37) and is meshed with the second gear (37), and a left-right sliding structure is formed between the connecting plate (38) and the mounting box (4), and the connecting plate (38) is located on the left side of the control panel (28); A second control rope (39) is fixed to the right side of the connecting plate (38), and an end of the second control rope (39) is connected to the cockpit (3); A fifth spring (40) is arranged on the right side of the connecting plate (38) to provide a thrust for the connecting plate (38).

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