Horizontal omni-directional movement jet-propelled helicopter

Abstract

The invention relates to the technical field of aircrafts, in particular to a horizontal omni-directional movement jet helicopter. Comprising a fuselage, a left wing, a right wing, a vertical wing, a left lower vertical stabilizer, a right lower vertical stabilizer, a left turboshaft engine, a right turboshaft engine, a single-shaft turbojet engine, a gas collection chamber on a shell of the turbojet engine, a left front lift fan, a left rear lift fan, a right front lift fan, a right rear lift fan, a right front lift nozzle and a right rear lift nozzle, a left front lifting force spraying pipe, a left rear lifting force spraying pipe, a left front horizontal spraying pipe, a left rear horizontal spraying pipe, a front left horizontal spraying pipe, a front right horizontal spraying pipe, a right front horizontal spraying pipe, a right rear horizontal spraying pipe, a rear right horizontal spraying pipe and a rear left horizontal spraying pipe. The horizontal omni-directional motion jet-propelled helicopter not only inherits the advantages of vertical lifting and front-back and left-right lateral flight of the helicopter, but also overcomes the defect that the stability of the helicopter is not better than that of a fixed-wing aircraft, and has the advantages of high flight speed and stable flight of the fixed-wing aircraft.

Description

Technical Field

[0001] This invention relates to the field of aircraft technology, specifically to a horizontal omnidirectional jet helicopter. Background Technology

[0002] Existing helicopters fly by using a horizontally rotating rotor to provide lift and thrust, and some use a tail rotor to maintain heading. They are characterized by vertical takeoff and landing, hovering, stopping, and forward, backward, or lateral flight. This is achieved by tilting the main rotor's plane of rotation in the desired direction. While helicopters offer high flight flexibility, allowing for vertical takeoff and landing, hovering, and forward, backward, and lateral flight, they also have disadvantages such as relatively slow speed and lower stability compared to fixed-wing aircraft. Furthermore, they suffer from speed limitations, tip stall, vortex ring effects, blade flapping, and ground resonance.

[0003] To address the aforementioned issues, we propose an improvement: a horizontally omnidirectional jet helicopter. Summary of the Invention

[0004] To solve the above-mentioned technical problems, the present invention provides the following technical solution:

[0005] This invention provides a horizontally omnidirectional jet helicopter, comprising a fuselage, a left wing, a right wing, a vertical wing, a lower left vertical stabilizer, a lower right vertical stabilizer, a left turboshaft engine, a right turboshaft engine, a single-shaft turbojet engine, an air intake chamber on the turbojet engine casing, a left front lift fan, a left rear lift fan, a right front lift fan, a right rear lift fan, a right front lift nozzle, a right rear lift nozzle, a left front lift nozzle, a left rear lift nozzle, a left front horizontal nozzle, a left rear horizontal nozzle, a front left horizontal nozzle, a front right horizontal nozzle, a right front horizontal nozzle, a right rear horizontal nozzle, a rear right horizontal nozzle, and a rear left horizontal nozzle. The left wing and the right wing are fixedly connected to the left and right sides of the fuselage, respectively. The vertical wing is fixedly connected to the upper rear side of the fuselage. The lower left vertical stabilizer and the lower right vertical stabilizer are symmetrically fixedly connected to the lower part of the fuselage.

[0006] A left turboshaft engine and a right turboshaft engine are symmetrically fixedly mounted on the upper rear part of the fuselage. A single-shaft turbojet engine is fixedly mounted at the tail of the fuselage. A left front lift fan, a left rear lift fan, a right front lift fan, and a right rear lift fan are symmetrically mounted on the lower part of the fuselage. A right front lift nozzle, a right rear lift nozzle, a left front lift nozzle, and a left rear lift nozzle are symmetrically mounted on the front and rear sides of the lower part of the fuselage. A left front horizontal nozzle, a left rear horizontal nozzle, a front left horizontal nozzle, a front right horizontal nozzle, a right front horizontal nozzle, a right rear horizontal nozzle, a rear right horizontal nozzle, and a rear left horizontal nozzle are symmetrically mounted around the fuselage.

[0007] As a preferred embodiment of the present invention, the single-shaft turbojet engine is connected to the left turboshaft engine via a bevel gear connecting the turboshaft engine drive shaft and the upper left drive shaft, and the single-shaft turbojet engine is connected to the right turboshaft engine via a bevel gear connecting the turboshaft engine drive shaft and the upper right drive shaft.

[0008] As a preferred embodiment of the present invention, the output shaft of the single-shaft turbojet engine is coaxially and fixedly connected to a bevel gear that connects to the lift fan drive shaft. The bevel gear that connects to the lift fan drive shaft meshes with two driven bevel gears. The left center drive shaft and the right center drive shaft are coaxially and fixedly connected to the two driven bevel gears respectively. The left center drive shaft is driven by a left reducer and a left rear drive shaft through a bevel gear set. The output shaft of the left reducer is coaxially and fixedly connected to a left front drive shaft. The left front drive shaft and the left rear drive shaft are driven by a left front lift fan and a left rear lift fan respectively through a bevel gear set.

[0009] The right center drive shaft is connected to the right reducer and the right rear drive shaft via a bevel gear set. The output shaft of the right reducer is coaxially fixedly connected to the right front drive shaft. The right front drive shaft and the right rear drive shaft are respectively connected to the right front lift fan and the right rear lift fan via bevel gear sets.

[0010] As a preferred embodiment of the present invention, the single-shaft turbojet engine has an air collection chamber on its rear outer casing. The air collection chamber on the turbojet engine casing is connected to the left front lift nozzle and the left rear lift nozzle through the left lift nozzle air supply pipe. The air collection chamber on the turbojet engine casing is connected to the right front lift nozzle and the right rear lift nozzle through the right lift nozzle air supply pipe.

[0011] The gas collection chamber on the turbojet engine casing is connected to the left front horizontal nozzle and the front left horizontal nozzle through the left front horizontal nozzle gas supply pipe. The gas collection chamber on the turbojet engine casing is connected to the left rear horizontal nozzle and the rear left horizontal nozzle through the left rear horizontal nozzle gas supply pipe. The gas collection chamber on the turbojet engine casing is connected to the front right horizontal nozzle and the right front horizontal nozzle through the right front horizontal nozzle gas supply pipe. The gas collection chamber on the turbojet engine casing is connected to the right rear horizontal nozzle and the rear right horizontal nozzle through the right rear horizontal nozzle gas supply pipe.

[0012] As a preferred technical solution of the present invention, the gas collection chamber on the casing of the turbojet engine is fixedly connected with a partition plate between the right lift nozzle and the horizontal nozzle gas collection chamber, a partition plate between the left lift nozzle and the horizontal nozzle gas collection chamber, and a partition plate between the left and right lift nozzle gas collection chambers. The partition plate divides the gas collection chamber into three parts: the gas collection chamber connected to the left lift nozzle gas supply pipe, the gas collection chamber connected to the right lift nozzle gas supply pipe, and the gas collection chamber connected to the horizontal nozzle gas supply pipe.

[0013] The turbojet engine casing has an air inlet on the left front horizontal nozzle air supply pipe, an air inlet on the right front horizontal nozzle air supply pipe, an air inlet on the right lift nozzle air supply pipe, and an air inlet on the left lift nozzle air supply pipe on the air collection chamber.

[0014] As a preferred embodiment of the present invention, the single-shaft turbojet engine includes a combustion chamber and a compressor. The compressor outlet is divided into two parts by an annular gas distribution ring with a wedge-shaped cross-section: a one-third inner ring combustion chamber gas inlet and a two-thirds outer ring gas collecting chamber gas inlet. The one-third inner ring combustion chamber gas inlet is connected to the combustion chamber, and the two-thirds outer ring gas collecting chamber gas inlet is connected to the gas collecting chambers connected to the left lift nozzle gas supply pipe, the right lift nozzle gas supply pipe, and the horizontal nozzle gas supply pipe.

[0015] As a preferred embodiment of the present invention, the right front lift nozzle, right rear lift nozzle, left front lift nozzle and left rear lift nozzle are respectively located directly below the left front lift fan, left rear lift fan, right front lift fan and right rear lift fan.

[0016] As a preferred technical solution of the present invention, the right front lift nozzle, the right rear lift nozzle, the left front lift nozzle and the left rear lift nozzle are respectively connected to the right front air supply pipe end pipe, the right rear air supply pipe end pipe, the left front air supply pipe end pipe and the left rear air supply pipe end pipe.

[0017] The right front gas pipeline, right rear gas pipeline, left front gas pipeline, and left rear gas pipeline are respectively connected to the right front lift nozzle end pipe distribution pipe, right rear lift nozzle end pipe distribution pipe, left front lift nozzle end pipe distribution pipe, and left rear lift nozzle end pipe distribution pipe.

[0018] The right front lift nozzle end pipe air distribution pipe, the right rear lift nozzle end pipe air distribution pipe, the left front lift nozzle end pipe air distribution pipe, and the left rear lift nozzle end pipe air distribution pipe are respectively equipped with right front air distribution pipe exhaust valve, right rear air distribution pipe exhaust valve, left front air distribution pipe exhaust valve, and left rear air distribution pipe exhaust valve.

[0019] As a preferred embodiment of the present invention, a gas flow regulating valve for the right lift nozzle gas pipeline and a gas flow regulating valve for the left lift nozzle gas pipeline are respectively installed on the right rear gas pipeline end pipe and the left rear gas pipeline end pipe.

[0020] As a preferred embodiment of the present invention, the upper part of the fuselage is provided with a turbojet engine air intake.

[0021] The beneficial effects of this invention are: this horizontal omnidirectional jet helicopter inherits the advantages of helicopters, which can take off and land vertically and fly forward, backward, left, right and sideways, while overcoming the disadvantage of its instability being inferior to that of fixed-wing aircraft. It has the advantages of fixed-wing aircraft, such as high flight speed and stable flight. Attached Figure Description

[0022] The accompanying drawings are provided to further illustrate the invention and form part of the specification. They are used in conjunction with embodiments of the invention to explain the invention and do not constitute a limitation thereof. In the drawings:

[0023] Figure 1 This is a top view of a horizontally omnidirectional jet helicopter according to the present invention;

[0024] Figure 2 This is a front view of a horizontally omnidirectional jet helicopter according to the present invention;

[0025] Figure 3 This is a bottom view of a horizontally omnidirectional jet helicopter according to the present invention;

[0026] Figure 4 This is a rear view of a horizontally omnidirectional jet helicopter according to the present invention.

[0027] Figure 5 This is a schematic diagram of the connection between the lift fan and the turbojet engine of a horizontally omnidirectional jet helicopter according to the present invention.

[0028] Figure 6 This invention relates to a horizontally omnidirectional jet helicopter. Figure 1 Sectional view at point AA;

[0029] Figure 7 This is a schematic diagram of the connection between the horizontal nozzle and air supply pipe of a horizontally omnidirectional jet helicopter and the turbojet engine according to the present invention.

[0030] Figure 8 This is a side view of a horizontally omnidirectional jet helicopter according to the present invention;

[0031] Figure 9 This is a schematic diagram of the connection between the aircraft lift nozzle and air supply pipe of a horizontal omnidirectional jet helicopter and the turbojet engine according to the present invention.

[0032] Figure 10 This invention relates to a horizontally omnidirectional jet helicopter. Figure 3 Cross-sectional view of the BB lift nozzle and lift fan;

[0033] Figure 11This is a schematic cross-sectional view of the turbojet engine of a horizontally omnidirectional jet helicopter according to the present invention.

[0034] Figure 12 This invention relates to a horizontally omnidirectional jet helicopter. Figure 11 CC section view in the middle;

[0035] Figure 13 This invention relates to a horizontally omnidirectional jet helicopter. Figure 11 A magnified view of point A in the figure;

[0036] Figure 14 This is a block diagram of a horizontal signal generation device for a horizontally omnidirectional jet helicopter according to the present invention.

[0037] Figure 15 This is a block diagram of the aircraft control system of a horizontal omnidirectional jet helicopter according to the present invention.

[0038] In the diagram: 1. Fuselage; 2. Left wing; 3. Right wing; 4. Vertical wing; 5. Lower left vertical stabilizer; 6. Lower right vertical stabilizer; 7. Left front lift fan; 8. Left rear lift fan; 9. Right front lift fan; 10. Right rear lift fan; 11. Left front horizontal nozzle; 12. Left rear horizontal nozzle; 13. Front left horizontal nozzle; 14. Front right horizontal nozzle; 15. Right front horizontal nozzle; 16. Right rear horizontal nozzle; 17. Rear right horizontal nozzle; 18. Rear left horizontal nozzle; 19. Left turboshaft engine; 20. Right turboshaft engine; 21. Single-shaft turbojet engine; 22. Upper left driveshaft; 23. Upper right driveshaft; 24. Right front lift nozzle; 25. Right rear lift nozzle; 26. Left front lift nozzle; 27. 1. Left rear lift nozzle; 28. Right front air supply pipe end pipe; 29. ​​Right rear air supply pipe end pipe; 30. Left front air supply pipe end pipe; 31. Left rear air supply pipe end pipe; 32. Left reducer; 33. Right reducer; 34. Left front drive shaft; 35. Left rear drive shaft; 36. Right front drive shaft; 37. Right rear drive shaft; 38. Left center drive shaft; 39. Right center drive shaft; 40. Left front horizontal nozzle air supply pipe; 41. Left rear horizontal nozzle air supply pipe; 42. Right front horizontal nozzle air supply pipe; 43. Right rear horizontal nozzle air supply pipe; 44. Right front lift nozzle end pipe air distribution pipe; 45. Right rear lift nozzle end pipe air distribution pipe; 46. Left front lift nozzle end pipe air distribution pipe; 4 7. Left rear lift nozzle end pipe gas distribution pipe; 48. Right front gas distribution pipe exhaust valve; 49. Right rear gas distribution pipe exhaust valve; 50. Left front gas distribution pipe exhaust valve; 51. Left rear gas distribution pipe exhaust valve; 52. Right lift nozzle gas supply pipe; 53. Left lift nozzle gas supply pipe; 54. Right lift nozzle gas supply pipe end pipe gas flow regulating valve; 55. Left lift nozzle gas supply pipe end pipe gas flow regulating valve; 56. Turbojet engine air inlet; 57. Bevel gear connecting to lift fan drive shaft; 58. Bevel gear connecting to turboshaft engine drive shaft; 59. Combustion chamber; 60. Compressor; 61. Gas collection chamber on turbojet engine casing; 62. Gas collection chamber connected to left lift nozzle gas supply pipe; 63. The gas collection chamber connected to the right lift nozzle's gas supply pipe; 64. The gas collection chamber connected to the horizontal nozzle's gas supply pipe; 65. The air inlet of the left front horizontal nozzle's gas supply pipe on the gas collection chamber; 66. The air inlet of the right front horizontal nozzle's gas supply pipe on the gas collection chamber; 67. The air inlet of the right lift nozzle's gas supply pipe on the gas collection chamber; 68. The air inlet of the left lift nozzle's gas supply pipe on the gas collection chamber; 69. The partition between the right lift nozzle and the horizontal nozzle's gas collection chamber; 70. The partition between the left lift nozzle and the horizontal nozzle's gas collection chamber; 71. The partition between the left and right lift nozzle's gas collection chambers; 72. The gas inlet of the one-third inner ring combustion chamber; 73. The gas inlet of the two-thirds outer ring gas collection chamber; 74. A wedge-shaped annular gas distribution ring. Detailed Implementation

[0039] The preferred embodiments of the present invention will be described below with reference to the accompanying drawings. It should be understood that the preferred embodiments described herein are for illustration and explanation only and are not intended to limit the present invention.

[0040] Example: Figure 1 - Figure 15 As shown, a horizontally omnidirectional jet helicopter includes a fuselage 1, a left wing 2, a right wing 3, a vertical wing 4, a lower left vertical stabilizer 5, a lower right vertical stabilizer 6, a left turboshaft engine 19, a right turboshaft engine 20, a single-shaft turbojet engine 21, an air intake chamber 61 on the turbojet engine casing, a left front lift fan 7, a left rear lift fan 8, a right front lift fan 9, a right rear lift fan 10, a right front lift nozzle 24, a right rear lift nozzle 25, and a left front lift nozzle 26. 6. Left rear lift nozzle 27, left front horizontal nozzle 11, left rear horizontal nozzle 12, front left horizontal nozzle 13, front right horizontal nozzle 14, right front horizontal nozzle 15, right rear horizontal nozzle 16, rear right horizontal nozzle 17, rear left horizontal nozzle 18. Left wing 2 and right wing 3 are fixedly connected to the left and right sides of the fuselage 1 respectively. Vertical wing 4 is fixedly connected to the upper rear side of the fuselage 1. Left lower vertical stabilizer 5 and right lower vertical stabilizer 6 are symmetrically fixedly connected to the lower part of the fuselage 1.

[0041] A left turboshaft engine 19 and a right turboshaft engine 20 are symmetrically fixedly mounted on the upper rear part of the fuselage 1. A single-shaft turbojet engine 21 is fixedly mounted on the tail of the fuselage 1. A left front lift fan 7, a left rear lift fan 8, a right front lift fan 9, and a right rear lift fan 10 are symmetrically mounted on the lower part of the fuselage 1. A right front lift nozzle 24, a right rear lift nozzle 25, a left front lift nozzle 26, and a left rear lift nozzle 27 are symmetrically mounted on the front and rear sides of the lower part of the fuselage 1. A left front horizontal nozzle 11, a left rear horizontal nozzle 12, a front left horizontal nozzle 13, a front right horizontal nozzle 14, a right front horizontal nozzle 15, a right rear horizontal nozzle 16, a rear right horizontal nozzle 17, and a rear left horizontal nozzle 18 are symmetrically mounted around the fuselage 1.

[0042] The single-shaft turbojet engine 21 is connected to the left turboshaft engine 19 via a bevel gear 58 that connects to the drive shaft of the turboshaft engine and the upper left drive shaft 22. The single-shaft turbojet engine 21 is connected to the right turboshaft engine 20 via a bevel gear 58 that connects to the drive shaft of the turboshaft engine and the upper right drive shaft 23.

[0043] The output shaft of the single-shaft turbojet engine 21 is coaxially and fixedly connected to a bevel gear 57 that connects to the lift fan drive shaft. The bevel gear 57 that connects to the lift fan drive shaft meshes with two driven bevel gears. The left center drive shaft 38 and the right center drive shaft 39 are coaxially and fixedly connected to the two driven bevel gears respectively. The left center drive shaft 38 is connected to the left reducer 32 and the left rear drive shaft 35 through a bevel gear set. The output shaft of the left reducer 32 is coaxially and fixedly connected to the left front drive shaft 34. The left front drive shaft 34 and the left rear drive shaft 35 are connected to the left front lift fan 7 and the left rear lift fan 8 respectively through bevel gear sets.

[0044] The right center drive shaft 39 is connected to the right reducer 33 and the right rear drive shaft 37 via a bevel gear set. The output shaft of the right reducer 33 is coaxially fixedly connected to the right front drive shaft 36. The right front drive shaft 36 and the right rear drive shaft 37 are respectively connected to the right front lift fan 9 and the right rear lift fan 10 via bevel gear sets.

[0045] The single-shaft turbojet engine 21 has an air collection chamber 61 on its rear casing. The air collection chamber 61 is connected to the left front lift nozzle 26 and the left rear lift nozzle 27 through the left lift nozzle air supply pipe 53. The air collection chamber 61 is also connected to the right front lift nozzle 24 and the right rear lift nozzle 25 through the right lift nozzle air supply pipe 52.

[0046] The gas collection chamber 61 on the turbojet engine casing is connected to the left front horizontal nozzle 11 and the front left horizontal nozzle 13 through the left front horizontal nozzle gas supply pipe 40. The gas collection chamber 61 on the turbojet engine casing is connected to the left rear horizontal nozzle 12 and the rear left horizontal nozzle 18 through the left rear horizontal nozzle gas supply pipe 41. The gas collection chamber 61 on the turbojet engine casing is connected to the front right horizontal nozzle 14 and the right front horizontal nozzle 15 through the right front horizontal nozzle gas supply pipe 42. The gas collection chamber 61 on the turbojet engine casing is connected to the right rear horizontal nozzle 16 and the rear right horizontal nozzle 17 through the right rear horizontal nozzle gas supply pipe 43.

[0047] The gas collection chamber 61 on the turbojet engine casing is internally fixedly connected to a partition plate 69 between the right lift nozzle and the horizontal nozzle gas collection chamber, a partition plate 70 between the left lift nozzle and the horizontal nozzle gas collection chamber, and a partition plate 71 between the left and right lift nozzle gas collection chambers. The partition plate divides the gas collection chamber 62 connected to the left lift nozzle gas supply pipe, the gas collection chamber 63 connected to the right lift nozzle gas supply pipe, and the gas collection chamber 64 connected to the horizontal nozzle gas supply pipe.

[0048] The gas chamber 61 on the casing of the turbojet engine has an air inlet 65 for the left front horizontal nozzle air supply pipe, an air inlet 66 for the right front horizontal nozzle air supply pipe, an air inlet 67 for the right lift nozzle air supply pipe, and an air inlet 68 for the left lift nozzle air supply pipe.

[0049] The single-shaft turbojet engine 21 includes a combustion chamber 59 and a compressor 60. The compressor 60 outlet is divided into two parts by an annular gas distribution ring 74 with a wedge-shaped cross-section: an inner one-third combustion chamber gas inlet 72 and an outer two-thirds gas collection chamber gas inlet 73. The inner one-third combustion chamber gas inlet 72 is connected to the combustion chamber 59, and the outer two-thirds gas collection chamber gas inlet 73 is connected to the gas collection chamber 62 connected to the left lift nozzle gas supply pipe, the gas collection chamber 63 connected to the right lift nozzle gas supply pipe, and the gas collection chamber 64 connected to the horizontal nozzle gas supply pipe.

[0050] The right front lift nozzle 24, right rear lift nozzle 25, left front lift nozzle 26 and left rear lift nozzle 27 are located directly below the left front lift fan 7, left rear lift fan 8, right front lift fan 9 and right rear lift fan 10, respectively.

[0051] The right front lift nozzle 24, right rear lift nozzle 25, left front lift nozzle 26 and left rear lift nozzle 27 are respectively connected to the right front air supply pipeline end pipe 28, right rear air supply pipeline end pipe 29, left front air supply pipeline end pipe 30 and left rear air supply pipeline end pipe 31.

[0052] The right front gas pipeline end pipe 28, the right rear gas pipeline end pipe 29, the left front gas pipeline end pipe 30, and the left rear gas pipeline end pipe 31 are respectively connected to the right front lift nozzle end pipe distribution pipe 44, the right rear lift nozzle end pipe distribution pipe 45, the left front lift nozzle end pipe distribution pipe 46, and the left rear lift nozzle end pipe distribution pipe 47.

[0053] The right front lift nozzle end pipe air distribution pipe 44, the right rear lift nozzle end pipe air distribution pipe 45, the left front lift nozzle end pipe air distribution pipe 46, and the left rear lift nozzle end pipe air distribution pipe 47 are respectively equipped with the right front air distribution pipe exhaust valve 48, the right rear air distribution pipe exhaust valve 49, the left front air distribution pipe exhaust valve 50, and the left rear air distribution pipe exhaust valve 51.

[0054] The right rear gas pipeline end pipe 29 and the left rear gas pipeline end pipe 31 are respectively equipped with a right lift nozzle gas pipeline end pipe gas flow regulating valve 54 and a left lift nozzle gas pipeline end pipe gas flow regulating valve 55.

[0055] The upper part of the fuselage 1 is provided with a turbojet engine air intake 56.

[0056] The cross-sectional area of ​​each of the right lift nozzle air supply pipe 52, left lift nozzle air supply pipe 53, left front horizontal nozzle air supply pipe 40, left rear horizontal nozzle air supply pipe 41, right front horizontal nozzle air supply pipe 42, and right rear horizontal nozzle air supply pipe 43 is one-quarter of the total area of ​​the air intake of the gas collection chamber 61 on the turbojet engine casing. The total area of ​​the air intakes of the gas collection chamber 62 connected to the left lift nozzle air supply pipe, the gas collection chamber 63 connected to the right lift nozzle air supply pipe, and the gas collection chamber 64 connected to the horizontal nozzle air supply pipe is two-thirds of the outer ring area of ​​the circular ring swept by the last stage blade of the compressor 60, which is twice the cross-sectional area of ​​each of the right lift nozzle air supply pipe 52, left lift nozzle air supply pipe 53, left front horizontal nozzle air supply pipe 40, left rear horizontal nozzle air supply pipe 41, right front horizontal nozzle air supply pipe 42, and right rear horizontal nozzle air supply pipe 43.

[0057] The left front lift fan 7, left rear lift fan 8, right front lift fan 9, and right rear lift fan 10 are ducted fans. Since the aircraft is lighter in the front and heavier in the rear, a left reduction gear 32 and a right reduction gear 33 are provided on the left front drive shaft 34 and right front drive shaft 36 leading to the left front lift fan 7 and the right front lift fan 9, respectively, to reduce the speed of the left front lift fan 7 and the right front lift fan 9, so that the aircraft can maintain balance.

[0058] The function of the right front lift nozzle 24, right rear lift nozzle 25, and left front lift nozzle 26, and the left rear lift nozzle 27, is to generate auxiliary lift. The magnitude of the lift generated by the right front lift nozzle 24, right rear lift nozzle 25, and left front lift nozzle 26, and the left rear lift nozzle 27, is used to adjust the balance and level of the aircraft. During flight, the exhaust valves of the gas distribution pipes of the right front lift nozzle 24, right rear lift nozzle 25, and left front lift nozzle 26 are in the middle position. When one side is higher than the other, such as the left side, the exhaust valves of the gas distribution pipes of the left front lift nozzle 26 and left rear lift nozzle 27 on the higher side open wider, exhausting gas into the duct through the exhaust port on the sidewall of the duct, thus reducing the amount of gas entering the left front lift nozzle 26 and left rear lift nozzle 27, which will cause the left side to lower. The opposite is true for the lower side.

[0059] Once the aircraft is balanced, if the front position is too high, adjust the exhaust valves on the gas distribution pipes of the right front lift nozzle 24 and the left front lift nozzle 26 to open them wider. This reduces the amount of gas entering the right front lift nozzle 24 and the left front lift nozzle 26, lowering the front position, and vice versa for the rear position.

[0060] When the aircraft flies to the left, the right front horizontal nozzle 15 and the right rear horizontal nozzle 16 open, the front right horizontal nozzle 14 and the right rear horizontal nozzle 16 close, the front left horizontal nozzle 13 and the rear left horizontal nozzle open, and the left front horizontal nozzle 11 and the left rear horizontal nozzle 12 close. If the aircraft flies forward, the rear left horizontal nozzle 18 and the rear right horizontal nozzle 17 open, the left rear horizontal nozzle and the right rear horizontal nozzle 16 close, the left front horizontal nozzle 11 and the left rear horizontal nozzle 15 open, and the front left horizontal nozzle 13 and the front right horizontal nozzle 14 close. At this time, the combustion chamber 59 of the single-shaft turbojet engine 21 can be ignited, and high-temperature and high-pressure gases are ejected one after another to make the aircraft fly forward.

[0061] When the aircraft is rotating, the left front horizontal nozzle 11, the front right horizontal nozzle 14, the right rear horizontal nozzle 16, and the rear left horizontal nozzle 18 are opened, while the other horizontal nozzles are closed, and the aircraft rotates.

[0062] It should be noted that the left wing 2 and right wing 3 of the aircraft do not generate lift. The vertical wing 4, the lower left vertical stabilizer 5, and the lower right vertical stabilizer 6 work together to ensure the stability of the aircraft's forward flight.

[0063] The generation of the aircraft's level signal consists of a level bubble, a camera, a leveling computer, and a gyroscope. The level bubble generates a level signal, and the camera images the level bubble. The leveling computer calculates the position of the level bubble. When the level bubble is centered, the leveling computer determines that the aircraft is level, and at this point, it locks the gyroscope's data signal. If the gyroscope signal changes, it indicates that the aircraft is not level. At this point, the lift from each lift nozzle is adjusted, and the leveling computer re-determines the position of the level bubble to restore the aircraft to level. Once the aircraft is level, the data signal from gyroscope 1 is locked again. Determining the position of the level bubble 101 also simultaneously determines which side of the aircraft is higher or lower.

[0064] The aircraft's control system includes a central computer, a leveling computer, an execution computer, pedals, a control stick, a radio altimeter, and a north navigation signal receiver. The central computer periodically scans data from other computers, sensors, and equipment. If it detects a leveling computer signal that the aircraft is not level, it sends a signal to the execution computer. The execution computer then sends adjustment signals to the exhaust valves in the lift nozzle distribution pipes and the lift nozzle flow control valves, adjusting their opening positions to further adjust the lift generated by each lift nozzle, thereby adjusting the aircraft's level and balance. If it detects changes in the control stick or pedals, it sends a signal to the execution computer, which then sends signals to each leveling nozzle to adjust their opening and closing, thereby adjusting the aircraft's forward, backward, left, and right movements and rotation. When changes in signal data from the BeiDou navigation signal receiver and radio altimeter are detected, indicating aircraft ascent or descent, the central computer sends a signal to the execution computer. The execution computer then sends adjustment signals to the throttle of each turboshaft engine, adjusting its magnitude and thus the aircraft's ascent or descent. The BeiDou navigation signal receiver provides the central computer with movement signals indicating the aircraft's forward, backward, left, and right ascent or descent, allowing the central computer to make decisions and further adjust the thrust of each horizontal and vertical thrust nozzle, the throttle of each turboshaft engine, and the aircraft's attitude. If the data signals from all computers and devices remain unchanged, the central computer does not send signals to the execution computer, and the aircraft remains hovered.

[0065] Finally, it should be noted that the above descriptions are merely preferred embodiments of the present invention and are not intended to limit the present invention. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments or make equivalent substitutions for some of the technical features. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A horizontally omnidirectional jet helicopter, comprising a fuselage (1), a left wing (2), a right wing (3), a vertical wing (4), a lower left vertical stabilizer (5), a lower right vertical stabilizer (6), a left turboshaft engine (19), a right turboshaft engine (20), a single-shaft turbojet engine (21), an air chamber (61) on the turbojet engine casing, a left front lift fan (7), a left rear lift fan (8), a right front lift fan (9), a right rear lift fan (10), a right front lift nozzle (24), a right rear lift nozzle (25), a left front lift nozzle (26), a left rear lift nozzle (27), a left front horizontal nozzle (11), a left rear horizontal nozzle (12), a front left horizontal nozzle (13), a front right horizontal nozzle (14), a right front horizontal nozzle (15), a right rear horizontal nozzle (16), a rear right horizontal nozzle (17), and a rear left horizontal nozzle (18), characterized in that, The left wing (2) and right wing (3) are fixedly connected to the left and right sides of the fuselage (1), respectively. A vertical wing (4) is fixedly connected to the upper rear side of the fuselage (1), and a lower left vertical stabilizer (5) and a lower right vertical stabilizer (6) are symmetrically fixedly connected to the lower part of the fuselage (1). A left turboshaft engine (19) and a right turboshaft engine (20) are symmetrically fixedly installed on the upper rear part of the fuselage (1). A single-shaft turbojet engine (21) is fixedly installed at the tail of the fuselage (1). A left front lift fan (7), a left rear lift fan (8), a right front lift fan (9), and a right rear lift fan (10) are symmetrically installed on the lower part of the fuselage (1). A right front lift nozzle (24), a right rear lift nozzle (25), a left front lift nozzle (26), and a left rear lift nozzle (27) are symmetrically installed on the front and rear sides of the lower part of the fuselage (1). A left front horizontal nozzle (11), a left rear horizontal nozzle (12), a front left horizontal nozzle (13), a front right horizontal nozzle (14), a right front horizontal nozzle (15), a right rear horizontal nozzle (16), a rear right horizontal nozzle (17), and a rear left horizontal nozzle (18) are symmetrically installed around the fuselage (1).

2. The horizontal omnidirectional jet helicopter according to claim 1, characterized in that, The single-shaft turbojet engine (21) is connected to the left turboshaft engine (19) via a bevel gear (58) connecting the turboshaft engine drive shaft and the upper left drive shaft (22). The single-shaft turbojet engine (21) is connected to the right turboshaft engine (20) via a bevel gear (58) connecting the turboshaft engine drive shaft and the upper right drive shaft (23).

3. A horizontally omnidirectional jet helicopter according to claim 1, characterized in that, The output shaft of the single-shaft turbojet engine (21) is coaxially fixedly connected to a bevel gear (57) that connects to the lift fan drive shaft. The bevel gear (57) that connects to the lift fan drive shaft meshes with two driven bevel gears. The left middle drive shaft (38) and the right middle drive shaft (39) are coaxially fixedly connected to the two driven bevel gears respectively. The left middle drive shaft (38) is connected to the left reducer (32) and the left rear drive shaft (35) through a bevel gear set. The output shaft of the left reducer (32) is coaxially fixedly connected to the left front drive shaft (34). The left front drive shaft (34) and the left rear drive shaft (35) are connected to the left front lift fan (7) and the left rear lift fan (8) respectively through a bevel gear set. The right middle drive shaft (39) is connected to the right reducer (33) and the right rear drive shaft (37) via a bevel gear set. The output shaft of the right reducer (33) is coaxially fixedly connected to the right front drive shaft (36). The right front drive shaft (36) and the right rear drive shaft (37) are respectively connected to the right front lift fan (9) and the right rear lift fan (10) via bevel gear sets.

4. A horizontally omnidirectional jet helicopter according to claim 1, characterized in that, The single-shaft turbojet engine (21) has an air collection chamber (61) on the rear outer shell of the turbojet engine housing. The air collection chamber (61) on the turbojet engine housing is connected to the left front lift nozzle (26) and the left rear lift nozzle (27) through the left lift nozzle air supply pipe (53). The air collection chamber (61) on the turbojet engine housing is connected to the right front lift nozzle (24) and the right rear lift nozzle (25) through the right lift nozzle air supply pipe (52). The gas collection chamber (61) on the turbojet engine casing is connected to the left front horizontal nozzle (11) and the front left horizontal nozzle (13) through the left front horizontal nozzle gas supply pipe (40). The gas collection chamber (61) on the turbojet engine casing is connected to the left rear horizontal nozzle (12) and the rear left horizontal nozzle (18) through the left rear horizontal nozzle gas supply pipe (41). The gas collection chamber (61) on the turbojet engine casing is connected to the front right horizontal nozzle (14) and the right front horizontal nozzle (15) through the right front horizontal nozzle gas supply pipe (42). The gas collection chamber (61) on the turbojet engine casing is connected to the right rear horizontal nozzle (16) and the rear right horizontal nozzle (17) through the right rear horizontal nozzle gas supply pipe (43).

5. A horizontally omnidirectional jet helicopter according to claim 1, characterized in that, The gas collection chamber (61) on the turbojet engine housing is fixedly connected to a partition plate (69) between the right lift nozzle and the horizontal nozzle gas collection chamber, a partition plate (70) between the left lift nozzle and the horizontal nozzle gas collection chamber, and a partition plate (71) between the left and right lift nozzle gas collection chambers. The partition plate divides the gas collection chamber (62) connected to the left lift nozzle gas supply pipe, the gas collection chamber (63) connected to the right lift nozzle gas supply pipe, and the gas collection chamber (64) connected to the horizontal nozzle gas supply pipe. The turbojet engine casing has an air inlet (65) for the left front horizontal nozzle air supply pipe, an air inlet (66) for the right front horizontal nozzle air supply pipe, an air inlet (67) for the right lift nozzle air supply pipe, and an air inlet (68) for the left lift nozzle air supply pipe on the air collection chamber (61).

6. A horizontally omnidirectional jet helicopter according to claim 1, characterized in that, The single-shaft turbojet engine (21) includes a combustion chamber (59) and a compressor (60). The compressor (60) outlet is divided into two parts by a wedge-shaped annular gas distribution ring (74): a one-third inner ring combustion chamber gas inlet (72) and a two-thirds outer ring gas collection chamber gas inlet (73). The one-third inner ring combustion chamber gas inlet (72) is connected to the combustion chamber (59). The two-thirds outer ring gas collection chamber gas inlet (73) is connected to the gas collection chamber (62) connected to the left lift nozzle gas supply pipe, the gas collection chamber (63) connected to the right lift nozzle gas supply pipe, and the gas collection chamber (64) connected to the horizontal nozzle gas supply pipe.

7. A horizontally omnidirectional jet helicopter according to claim 1, characterized in that, The right front lift nozzle (24), right rear lift nozzle (25), left front lift nozzle (26) and left rear lift nozzle (27) are located directly below the left front lift fan (7), left rear lift fan (8), right front lift fan (9) and right rear lift fan (10), respectively.

8. A horizontally omnidirectional jet helicopter according to claim 1, characterized in that, The right front lift nozzle (24), right rear lift nozzle (25), left front lift nozzle (26) and left rear lift nozzle (27) are respectively connected to the right front gas pipeline end pipe (28), right rear gas pipeline end pipe (29), left front gas pipeline end pipe (30) and left rear gas pipeline end pipe (31); The right front gas pipeline end pipe (28), right rear gas pipeline end pipe (29), left front gas pipeline end pipe (30), and left rear gas pipeline end pipe (31) are respectively connected to the right front lift nozzle end pipe distribution pipe (44), right rear lift nozzle end pipe distribution pipe (45), left front lift nozzle end pipe distribution pipe (46), and left rear lift nozzle end pipe distribution pipe (47). The right front lift nozzle end pipe air distribution pipe (44), right rear lift nozzle end pipe air distribution pipe (45), left front lift nozzle end pipe air distribution pipe (46), and left rear lift nozzle end pipe air distribution pipe (47) are respectively equipped with a right front air distribution pipe exhaust valve (48), a right rear air distribution pipe exhaust valve (49), a left front air distribution pipe exhaust valve (50), and a left rear air distribution pipe exhaust valve (51).

9. A horizontally omnidirectional jet helicopter according to claim 1, characterized in that, The right rear gas pipeline end pipe (29) and the left rear gas pipeline end pipe (31) are respectively equipped with a right lift nozzle gas pipeline end pipe gas flow regulating valve (54) and a left lift nozzle gas pipeline end pipe gas flow regulating valve (55).

10. A horizontally omnidirectional jet helicopter according to claim 1, characterized in that, The upper part of the fuselage (1) is provided with a turbojet engine air intake (56).

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