Vertical offset aircraft

Abstract

The invention discloses a vertical offset aircraft, and relates to the technical field of aircrafts, the vertical offset aircraft comprises a shell, the shell is arc-shaped, a first wind gathering barrel, a controller, an offset box, a set of engines, a cockpit and hidden driving wheels are arranged in the shell, a power assembly is arranged in the first wind gathering barrel and is used for realizing lifting of the aircraft, and the controller is arranged in the first wind gathering barrel. The controller is arranged at the tail of the interior of the offset box, the offset box is arranged on the lower portion of the interior of the shell and arranged on the outer side of the bottom of the first air gathering barrel in a penetrating mode, an offset power source electricity storage box, a connecting assembly and a transmission assembly are arranged in the offset box, and the connecting assembly is used for guaranteeing the moving stability of the offset power source electricity storage box. According to the device, the gravity center of the aircraft can be inclined through the arrangement of the internal structure of the offset box, and the advancing, retreating and steering state adjustment of the aircraft is achieved.

Description

Technical Field

[0001] This invention relates to the field of aircraft technology, specifically to vertical offset aircraft. Background Technology

[0002] Aircraft come in many different types and can perform a variety of tasks such as reconnaissance, surveillance, search and rescue, identification, tracking, and navigation. Aircraft are divided into unmanned and manned types.

[0003] Specifically, the disc-shaped aircraft is described below. It includes a cockpit, a fixed base, a landing gear, wheels, an engine, and a control system. An annular groove is formed at the connection between the cockpit and the fixed base. The inner ring of the disc-shaped shell fits into this groove. Two rotors are symmetrically arranged on the disc-shaped shell, and the rotors are connected to a rotor switch control device. The engine is connected to a transfer case via a clutch. The first output shaft of the transfer case is connected to the disc-shaped shell drive shaft via a bevel gear set. The drive gear at the upper end of the disc-shaped shell drive shaft meshes with the internal gears on the inner ring of the disc-shaped shell. The second output shaft of the transfer case is connected to the propeller shaft via a three-section constant velocity universal joint. The propeller shaft is fixed to the propeller. A rotatable disc is provided on the inner wall of the fixed base. The bearing seat fixed to the edge of the disc is fitted onto the propeller shaft. The disc is connected to the disc control lever in the cockpit via a connecting rod. The disc-shaped aircraft is a tailless, rudderless unconventional aircraft in which the fuselage is the wing and the wing is the fuselage. Its control method adopts a composite control method that combines variable mass moment control and thrust vector control to achieve flight control of the disc-shaped aircraft.

[0004] During the use of the butterfly-shaped aircraft, it was found that if the propulsion blades of the aircraft collide with objects in external space during operation, it will cause damage to the aircraft. In addition, how to easily implement the offset process of the aircraft during flight has become an urgent problem to be solved by people in this field. Summary of the Invention

[0005] The purpose of this invention is to provide a vertical offset aircraft that solves the problems mentioned in the background art by improving the blade position and setting the offset box and its internal structure.

[0006] To solve the above-mentioned technical problems, the present invention provides the following technical solution:

[0007] Vertical offset aircraft, including:

[0008] The hull, which is arc-shaped, is used to reduce air resistance experienced by the aircraft during flight; it has:

[0009] The first wind concentrator is located inside the shell. The top of the first wind concentrator is provided with an air inlet grille. The air inlet grille is spherical and can block objects around the aircraft when it is in flight to prevent large objects from entering the first wind concentrator and interfering with the normal flight of the aircraft.

[0010] The power unit, located inside the first wind-gathering duct, is used to achieve the take-off and landing of the aircraft and prevent the propeller blades from hitting objects, thus avoiding loss of personnel and the aircraft; the power unit includes:

[0011] The first motor bracket is located slightly below the air inlet of the first air concentrator;

[0012] The second motor bracket is located slightly above the middle of the inner wall of the first air-collecting duct. Both the second motor bracket and the first motor bracket are fixedly connected to the inner wall of the first air-collecting duct.

[0013] The first thruster motor is fixedly mounted in the lower middle of the first motor bracket;

[0014] The first thruster blade is fixedly connected to the output end of the first thruster motor;

[0015] The second thruster blade is located above the second motor bracket;

[0016] The second thruster motor is fixedly connected to the lower middle of the second motor bracket. The output end of the second thruster motor is fixedly connected to the second thruster blade. The first thruster motor and the second thruster motor form a forward and reverse rotation thruster. By controlling the rotation speed of the output ends of the first thruster motor and the second thruster motor, the ascent, descent or hovering state of the aircraft can be changed.

[0017] The controller is located at the rear of the offset box.

[0018] An offset box is located inside the lower part of the housing and extends through the bottom outer side of the first wind-gathering tube. The offset box contains an offset power storage box, a connecting component, and a transmission component. The connecting component is used to ensure the stability of the offset power storage box's movement, and the transmission component is used to realize the movement of the offset power storage box.

[0019] The transmission assembly includes:

[0020] The internal gear track is bolted to the outer wall of the first wind-gathering duct, and the internal gear track is internally connected to a traveling gear.

[0021] An offset motor is fixed inside the offset power storage box. The output end of the offset motor is fixedly connected to a motor gear. The motor gear is meshed with a speed conversion gear. The other side of the speed conversion gear is meshed with a drive gear.

[0022] The gear bracket is fixed in the middle of the outer wall of the offset motor and provides support for the connection between the drive gear and the speed conversion gear.

[0023] The traveling gear and the drive gear are coaxially arranged. When the drive gear rotates, it drives the traveling gear to rotate synchronously, thereby causing the offset power storage box to move. The gear bracket is provided with an I-beam guide wheel near the lower side of the inner gear track, which contacts the outer wall of the inner gear track to improve the stability of the offset power storage box movement.

[0024] The connection component includes:

[0025] A hanging rail is installed on the top outer side inside the offset box, and a cable tray and several hanging wheels are installed below the hanging rail;

[0026] A limit wheel is provided on the upper surface of the offset power storage box. The limit wheel is slidably connected to the hanging rail. A limit block is provided above the controller. The limit block is the end position and is used to prevent the offset power storage box from interfering and colliding when it is offset.

[0027] The movable blocking block is also set on the top of the offset power storage box, and is located on the same circumference as the hanging wheel. It is used to block the hanging wheel from moving when the offset power storage box moves, so that it does not exceed the offset power storage box.

[0028] The offset box driven wheel is located on the lower surface of the offset power storage box. A slide rail is provided on the inner bottom surface of the offset box, and the offset box driven wheel is slidably connected to the slide rail. Four sets of offset box driven wheels are provided.

[0029] A set of engines is located at the tail of the aircraft and is connected to the thruster motor and the offset power storage tank, respectively.

[0030] The cockpit is located directly in front of the first wind-gathering duct, and an outward-opening hatch is provided at the lower front of the cockpit;

[0031] A concealed drive wheel is located on the lower front side of the offset box, and two concealed driven wheels are provided on both sides of the concealed drive wheel at 120 degrees.

[0032] The power supply control system is located inside the aircraft. It includes the flight control system, the peripheral imaging system, and the offset box control system. When using unmanned remote control, the offset box control system is connected to the flight operating system.

[0033] Preferably, the first motor bracket and the second motor bracket are configured with a cross-shaped elliptical inner cavity.

[0034] Preferably, the offset power storage box is equipped with an energy storage battery or other energy storage power source.

[0035] Preferably, a first limit switch is provided on the side of the offset power storage box closer to the controller, and a second limit switch is provided on the side of the offset power storage box away from the controller. A set of buffer blocks is also provided on one side of the second limit switch. When the two offset power storage boxes move forward and are about to contact each other, the buffer blocks contact and buffer to prevent collision between the two boxes.

[0036] Preferably, the output end of the first thruster motor is fixedly connected to a drive shaft, and the upper end of the drive shaft is connected to a reversing gear set, which is composed of several drive gears. The output end of the reversing gear set is fixedly connected to the second thruster blade, and the forward and reverse rotation of the second thruster blade and the first thruster blade is realized by a motor.

[0037] Preferably, the cable tray is configured as a telescopic flexible cable tray, which is provided with a main line and a secondary control line. The power supply in the offset power storage box is connected to the controller for power supply through the telescopic flexible cable tray.

[0038] Preferably, the cable tray is configured as a ceiling-mounted cable tray, a telescopic contact rod is provided between the movable blocking block and the limiting wheel, the bottom of the telescopic contact rod is bolted to the top of the offset power storage box, a compression spring or spring sheet is provided inside the telescopic contact rod, and a movable contact is fixed to the top of the telescopic contact rod, which is slidably connected to the cable tray.

[0039] Preferably, a steering fine-tuning thruster is provided on the lower rear side of the shell, installed inside the arc-shaped lower rear part of the aircraft. The steering fine-tuning thruster includes a second wind concentrator, with air inlets and outlets on both sides conforming to the arc shape of the outer shape. A rotary motor is provided on the right side of the second wind concentrator. The output end of the rotary motor passes through the second wind concentrator and is fixedly connected to a spindle. A third motor bracket is fixedly connected to one side of the spindle. A third thruster motor is fixedly connected to the third motor bracket. A third thruster blade is fixedly connected to the output end of the third thruster motor. When the rotary motor is started, its output end will drive the third thruster blade to rotate, achieving the effect of torque fine-tuning.

[0040] Preferably, a hemispherical driving observation window is provided above the cockpit, and the cockpit is equipped with a manual and automatic tilt-adjustable control console and a 45-degree vertical tilt-adjustable seat.

[0041] Preferably, the transmission components are replaced, and a first offset box motor is provided below the first thruster motor. The output end of the first offset box motor is fixedly connected to a first motor shaft. A first connecting arm is fixed to the left side wall of the first motor shaft. The other end of the first connecting arm is fixedly connected to the left offset power storage box. A second offset box motor is provided at the bottom of the offset box. The output end of the second offset box motor is fixedly connected to a second motor shaft. A plane bearing is provided between the second motor shaft and the first motor shaft. A ball bearing is provided at the top of the second motor shaft. A second connecting arm is fixedly connected to the right outer wall of the second motor shaft. The other end of the second connecting arm is fixedly connected to the right offset power storage box. A first sliding component is provided at the top of the left offset power storage box, and a second sliding component is provided at the top of the right offset power storage box, thereby ensuring the orderly movement of the offset power storage boxes within the offset box. A first moving contact and a second moving contact are respectively provided at the top of the left and right offset power storage boxes. The movement of the two sets of offset power storage boxes is realized by controlling the operation of the first offset box motor and the second offset box motor. The first sliding component and the second sliding component are both composed of T-shaped hanging rails and track wheels.

[0042] Compared with the prior art, the beneficial effects achieved by the present invention are:

[0043] By setting up a first wind concentrator and first and second propeller blades inside, and by controlling the output speed of the first and second propeller motors, the state of the aircraft's ascent, descent, or hovering can be changed. In addition, the propeller motors and blades are set inside the wind concentrator, so that the propeller blades will not hit objects, and there will be no loss of personnel or aircraft.

[0044] By setting up two sets of offset power storage boxes, as well as connecting components and transmission components, the aircraft's center of gravity is tilted by adjusting the movement of the offset power storage boxes on the internal gear track, thus achieving the effects of forward, backward and turning. By adding or removing some functions, the aircraft can achieve manned or unmanned remote control flight modes.

[0045] Equipped with a steering fine-tuning thruster, it plays a role in fine-tuning torque during normal flight, and rotates forward and backward according to different turning directions when turning. Attached Figure Description

[0046] 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:

[0047] Figure 1 This is a schematic diagram of the overall structure of the present invention;

[0048] Figure 2 This is a half-sectional schematic diagram of the first air-concentrating duct of the present invention;

[0049] Figure 3 This is a schematic diagram of the internal structure of the offset box of the present invention;

[0050] Figure 4 This is the present invention. Figure 3 Enlarged schematic diagram of region A;

[0051] Figure 5 This is a schematic diagram of a half-section of the offset power supply storage box of the present invention;

[0052] Figure 6 This is a schematic diagram of the main structure of the offset box of the present invention;

[0053] Figure 7 This is a top view of the offset power supply storage box of the present invention;

[0054] Figure 8 This is a schematic diagram of the initial position of the offset power supply storage box of the present invention;

[0055] Figure 9 This is a schematic diagram of the state of the offset power storage tank when the aircraft tilts forward according to the present invention;

[0056] Figure 10 This is a schematic diagram of the steering fine-tuning thruster structure of the present invention;

[0057] Figure 11 This is a schematic diagram of the structure of Embodiment 3 of the present invention;

[0058] Figure 12 This is a schematic diagram of the structure of Embodiment 4 of the present invention;

[0059] In the diagram: 1. Shell; 2. Air intake grille; 3. Cockpit; 4. Door; 5. Concealed drive wheel; 6. Concealed driven wheel; 7. First air duct; 71. First motor bracket; 72. First thruster motor; 73. First thruster blade; 74. Second motor bracket; 75. Second thruster motor; 76. Second thruster blade; 77. Drive shaft; 78. Reversing gear set; 8. Steering fine-tuning thruster; 81. Rotary motor; 82. Second air duct; 83. Third thruster motor; 84. Third motor bracket; 85. Spindle; 9. Offset power supply storage box; 10. Controller; 11. Internal gear track; 12. Slide rail; 13. Offset box; 14. Hanging wheel; 15. Telescopic flexible cable. ; 16. Limiting block; 17. Hanging rail; 18. Moving blocking block; 19. Limiting wheel; 20. Telescopic contact rod; 21. First limit switch; 22. Traveling gear; 23. I-beam guide wheel; 24. Offset motor; 25. Gear bracket; 26. Drive gear; 27. Gear conversion gear; 28. Motor gear; 30. Offset box driven wheel; 31. Buffer block; 32. Second limit switch; 33. First offset box motor; 331. First motor shaft; 332. First connecting arm; 333. First sliding assembly; 334. First moving contact; 34. Second offset box motor; 341. Second motor shaft; 342. Second connecting arm; 343. Second sliding assembly; 344. Second moving contact. Detailed Implementation

[0060] The following detailed, non-limiting description of the technical solution of the present invention, in conjunction with preferred embodiments and accompanying drawings, is provided. Obviously, the described embodiments are merely some, not all, of the embodiments of the present invention. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without inventive effort are within the scope of protection of the present invention.

[0061] Example 1

[0062] Please see Figure 1-9 The present invention provides a technical solution: a vertical offset aircraft, including a shell 1, the outer surface of which is arc-shaped to reduce air resistance during flight. A first wind concentrator 7 is fixedly installed through the middle of the shell 1. A power component is installed inside the first wind concentrator 7 to realize the take-off and landing of the aircraft. An air inlet grille 2 is bolted to the top of the first wind concentrator 7. The air inlet grille 2 is spherical and acts as a barrier to block objects around the aircraft when in flight, so as to prevent large objects from entering the first wind concentrator 7 and interfering with the normal flight of the aircraft.

[0063] refer to Figure 2The power assembly includes a first motor bracket 71 and a second motor bracket 74. The first motor bracket 71 and the second motor bracket 74 are fixedly connected to the inner wall of the first air concentrator 7 to provide support. The first motor bracket 71 is located slightly below the air inlet of the first air concentrator 7, and the second motor bracket 74 is located slightly above the middle of the inner wall of the first air concentrator 7.

[0064] A first thruster motor 72 is fixedly connected to the lower center of the first motor bracket 71, and a first thruster blade 73 is fixedly connected to the output end of the first thruster motor 72. A second thruster motor 75 is fixedly connected to the lower center of the second motor bracket 74, and a second thruster blade 76 is fixedly connected to the output end of the second thruster motor 75. This constitutes two sets of thrusters. The first thruster motor 72 and the second thruster motor 75 form a forward and reverse rotation thruster. The first motor bracket 71 and the second motor bracket 74 are set with a cross-shaped elliptical inner cavity. By controlling the rotational speed of the output ends of the first thruster motor 72 and the second thruster motor 75, the ascent, descent, or hovering state of the aircraft can be changed.

[0065] In addition, the propeller motor and blades are located inside the wind concentrator, which will prevent the propeller blades from hitting objects and causing loss of personnel or aircraft.

[0066] refer to Figure 3-5 An offset box 13 is provided inside the lower part of the housing 1. The offset box 13 is provided through the bottom outer side of the first wind concentrator 7. The offset box 13 contains an offset power storage box 9, a connecting component and a transmission component. The connecting component is used to ensure the movement stability of the offset power storage box 9, and the transmission component is used to realize the movement of the offset power storage box 9. The offset power storage box 9 contains an energy storage battery or other energy storage power source.

[0067] Specifically, the transmission assembly includes an internal gear track 11 bolted to the outer wall of the first wind-gathering duct 7, a traveling gear 22 meshing with the inside of the internal gear track 11, an offset motor 24 bolted to the inside of the offset power storage box 9, the offset motor 24 being configured as a reduction motor, a motor gear 28 fixedly connected to the output end of the offset motor 24, a speed conversion gear 27 meshing with the motor gear 28, a drive gear 26 meshing with the other side of the speed conversion gear 27, a gear bracket 25 fixedly connected in the middle of the outer wall of the offset motor 24, serving as a connection and support for the drive gear 26 and the speed conversion gear 27, the traveling gear 22 and the drive gear 26 being coaxially arranged, when the drive gear 26 rotates, it drives the traveling gear 22 to rotate synchronously, thereby causing the offset power storage box 9 to move;

[0068] A set of track wheel shafts is connected to the bearing on the lower surface of the gear bracket 25 near the internal gear track 11. I-beam guide wheels 23 are fixed on the surface of the track wheel shafts and contact the outer wall of the internal gear track 11 to improve the stability of the movement of the offset power storage box 9.

[0069] refer to Figure 6-9 The connecting components include a hanging rail 17 located on the top outer side inside the offset box 9, a cable tray and several hanging wheels 14 located below the hanging rail 17, the cable tray being divided into telescopic flexible cable trays 15 and ceiling-mounted fixed cable trays; a controller 10 is located at the rear of the interior of the offset box 13, between the two offset power storage boxes 9, a limit wheel 19 is provided on the upper surface of the offset power storage box 9, the limit wheel 19 is slidably connected to the hanging rail 17, and a limit block 16 is provided above the controller 10 to prevent the offset power storage boxes 9 from interfering and colliding during offset;

[0070] The top of the offset power storage box 9 is also provided with a moving blocking block 18, which is located on the same circumference as the hanging wheel 14. It is used to block the hanging wheel 14 from moving when the offset power storage box 9 moves, so that it does not exceed the offset power storage box 9.

[0071] When the hanging wheel 14 is equipped with a telescopic flexible cord 15, the telescopic flexible cord 15 is equipped with a main line and a secondary control line. When the remote control is used, the receiver and controller 10 can be installed in the offset power storage box 9, the secondary line is cancelled, and the power in the offset power storage box 9 is connected to the controller 10 and the main power supply through the telescopic flexible cord 15.

[0072] When the cable tray is set as a ceiling-mounted cable tray, a telescopic contact rod 20 is provided between the moving blocking block 18 and the limiting wheel 19. The bottom bolt of the telescopic contact rod 20 is fixed to the top of the offset power storage box 9. A compression spring is provided inside the telescopic contact rod 20. A moving contact is fixed to the top of the telescopic contact rod 20 and is slidably connected to the cable tray. When the ceiling-mounted cable tray is energized, the limiting wheel 19 also has the function of controlling the upper and lower limits of the offset power storage box 9 and is installed in the middle of the top surface of the offset power storage box 9.

[0073] The above two methods are used to achieve the energizing effect of the busbar.

[0074] The bottom surface of the offset box 13 is provided with a slide rail 12, and the lower surface of the offset power storage box 9 is provided with an offset box driven wheel 30. The offset box driven wheel 30 is slidably connected to the slide rail 12, and there are four sets of offset box driven wheels 30.

[0075] By adjusting the movement of the offset power storage box 9 on the internal gear track 11, the center of gravity of the aircraft is tilted, thereby achieving the effects of forward movement, backward movement, and turning.

[0076] A first limit switch 21 is provided on the side of the offset power storage box 9 closest to the controller 10. The first limit switch 21 is closed with the limit block 16. A second limit switch 32 is provided on the side of the offset power storage box 9 furthest from the controller 10. The second limit switch 32 is closed with another second limit switch 32. A set of buffer blocks 31 is also provided on one side of the second limit switch 32, as shown in Figure b. When the two offset power storage boxes 9 move forward and are about to contact each other, the buffer blocks 31 contact and buffer to prevent the two boxes from colliding.

[0077] The aircraft cabin is equipped with a set of engines located at the tail of the aircraft, which are connected to the thruster motor and the offset power storage tank 9 to ensure sufficient power supply.

[0078] The cockpit 3 is located directly in front of the first wind-gathering duct 7. A hemispherical driving observation window is located above the cockpit 3. The cockpit 3 is equipped with a manual and automatic tilt control console and a 45-degree vertical tilt seat. An outward-opening hatch 4 is located at the lower front of the cockpit 3. The number of hatches 4 can be set according to the requirements.

[0079] A hidden drive wheel 5 is provided on the lower front side of the offset box 13, and two hidden driven wheels 6 are provided on both sides of the hidden drive wheel 5 at 120 degrees.

[0080] The aircraft is also equipped with a power supply control system, which includes a flight control system, a peripheral imaging system, and a offset box control system. When using unmanned remote control, the offset box control system is connected to the flight control system. Lighting and other systems are distributed according to actual needs.

[0081] This aircraft can achieve manned or unmanned remote-controlled flight modes by adding or removing some functions.

[0082] In addition, the movement of the offset power storage box 9 can be achieved by using a geared motor connected to the offset power storage box 9 via an arm under the first air duct 7, which is not shown in the figure.

[0083] Example 2

[0084] refer to Figure 1 and Figure 10Based on Embodiment 1, the following structure is added: A steering fine-tuning thruster 8 is provided on the lower rear side of the shell 1. During normal flight, it plays a role in fine-tuning torque. When turning, it rotates forward and backward according to different turning directions. The steering fine-tuning thruster 8 includes a second wind concentrator 82. A rotary motor 81 is provided on the right side of the second wind concentrator 82. The rotary motor 81 can be set as a unidirectional rotary motor. It can rotate 180 degrees to realize torque fine-tuning and steering propulsion. The output end of the rotary motor 81 passes through the second wind concentrator 82 and is fixedly connected to a spindle 85. A third motor bracket 84 is fixedly connected to one side of the spindle 85. A third thruster motor 83 is fixedly connected to the third motor bracket 84. A third thruster blade is fixedly connected to the output end of the third thruster motor 83. When the rotary motor 81 is started, its output end will drive the third thruster blade to rotate, realizing the effect of torque fine-tuning.

[0085] The steering fine-tuning thruster 8 is installed inside the arc-shaped lower rear section of the aircraft. The air inlets and outlets on both sides of the second wind concentrator 82 are consistent with the arc shape of the exterior. The first thruster motor 72 and the second thruster motor 75 shown in the normal diagram are in a forward and reverse rotation scheme. The 180-degree flip steering fine-tuning thruster 8 is shown as a backup embodiment. Figure 10 The number 81 indicates the position of the rotary motor 81.

[0086] Example 3

[0087] refer to Figure 11 Based on Embodiment 2, the second thruster motor 75 is replaced by a drive shaft 77 and a reversing gear set 78. The lower end of the drive shaft 77 is fixedly connected to the output end of the first thruster motor 72, and the upper end of the drive shaft 77 is connected to the input end of the reversing gear set 78. The reversing gear set 78 is composed of several transmission gears, and the output end of the reversing gear set 78 is fixedly connected to the second thruster blade 76. In this way, the forward and reverse rotation of the second thruster blade 76 and the first thruster blade 73 is realized through a single motor setup.

[0088] Therefore, one or more propeller motors can be set to achieve forward and reverse rotation of the blades, and the blade model can refer to the blade specifications used in propeller-type propellers currently used in the aviation field.

[0089] Example 4

[0090] refer to Figure 12The transmission components in Embodiment 1 are replaced. Specifically, a first offset box motor 33 is provided below the first thruster motor 72. The output end of the first offset box motor 33 is fixedly connected to a first motor shaft 331. A first connecting arm 332 is fixedly fixed to the left side wall of the first motor shaft 331. The other end of the first connecting arm 332 is fixedly connected to the left offset power storage box 9. A second offset box motor 34 is provided at the bottom of the offset box 13. The output end of the second offset box motor 34 is fixedly connected to a second motor shaft 341. A plane bearing is provided between the second motor shaft 341 and the first motor shaft 331. A ball bearing is provided at the top of the second motor shaft 341. A second connecting arm 332 is fixedly connected to the right outer wall of the second motor shaft 341. The other end of the connecting arm 342 is fixedly connected to the right offset power storage box 9. The top of the left offset power storage box 9 is provided with a first sliding component 333, and the top of the right offset power storage box 9 is provided with a second sliding component 343, thereby ensuring the orderly movement of the offset power storage box 9 within the offset box 13. In addition, the tops of the left and right offset power storage boxes 9 are respectively provided with a first moving contact 334 and a second moving contact 344. With the above structural settings, the movement of the two sets of offset power storage boxes 9 can be realized by controlling the operation of the first offset box motor 33 and the second offset box motor 34. As an alternative, the center of gravity of the aircraft is tilted, realizing the forward, backward and turning effects of the aircraft.

[0091] It should be noted that both the first sliding component 333 and the second sliding component 343 are composed of T-shaped hanging rails and track wheels.

[0092] In the description of this invention, it should be understood that the terms "upper", "lower", "front", "rear", "left", "right", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this invention, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this invention.

[0093] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features, and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A vertical offset aircraft, characterized in that: include: The shell (1) is set in an arc shape to reduce the air resistance experienced by the aircraft during flight; have: The first wind concentrator (7) is located inside the shell (1). The top of the first wind concentrator (7) is provided with an air inlet grille (2). The air inlet grille (2) is spherical. When in flight, it blocks objects around the aircraft to prevent large objects from entering the first wind concentrator (7) and interfering with the normal flight of the aircraft. The power assembly, located inside the first wind-gathering duct (7), is used to achieve the take-off and landing of the aircraft and prevent the propeller blades from hitting objects, thus avoiding loss of personnel and the aircraft; the power assembly includes: The first motor bracket (71) is located slightly below the air inlet of the first air concentrator (7); The second motor bracket (74) is located slightly above the middle of the inner wall of the first air-collecting duct (7). Both the second motor bracket (74) and the first motor bracket (71) are fixedly connected to the inner wall of the first air-collecting duct (7). The first thruster motor (72) is fixedly mounted in the lower middle of the first motor bracket (71); The first thruster blade (73) is fixedly connected to the output end of the first thruster motor (72); The second thruster blade (76) is positioned above the second motor bracket (74); The second thruster motor (75) is fixedly connected to the lower middle of the second motor bracket (74). The output end of the second thruster motor (75) is fixedly connected to the second thruster blade (76). The first thruster motor (72) and the second thruster motor (75) form a forward and reverse rotation thruster. By controlling the rotation speed of the output ends of the first thruster motor (72) and the second thruster motor (75), the ascent, descent or levitation state of the aircraft can be changed. The controller (10) is located at the rear of the offset box (13); The offset box (13) is located inside the lower part of the housing (1) and extends through the bottom outer side of the first wind-gathering tube (7). The offset box (13) contains an offset power storage box (9), a connecting component, and a transmission component. The connecting component is used to ensure the movement stability of the offset power storage box (9), and the transmission component is used to realize the movement of the offset power storage box (9). The transmission assembly includes: The internal gear track (11) is bolted to the outer wall of the first wind-gathering tube (7), and the internal gear track (11) is internally connected to a traveling gear (22); An offset motor (24) is fixed inside the offset power storage box (9). The output end of the offset motor (24) is fixedly connected to a motor gear (28). The motor gear (28) is meshed with a speed conversion gear (27). The other side of the speed conversion gear (27) is meshed with a drive gear (26). The gear bracket (25) is fixed in the middle of the outer wall of the offset motor (24) and provides support for the connection of the drive gear (26) and the speed conversion gear (27). The traveling gear (22) and the driving gear (26) are coaxially arranged. When the driving gear (26) rotates, it drives the traveling gear (22) to rotate synchronously, thereby causing the offset power storage box (9) to move. The gear bracket (25) is provided with an I-beam guide wheel (23) on the lower side near the inner gear track (11), which contacts the outer wall of the inner gear track (11) to improve the stability of the movement of the offset power storage box (9). The connection component includes: A hanging rail (17) is set on the top outer side inside the offset box (13), and a cable tray and several hanging wheels (14) are set below the hanging rail (17); A limiting wheel (19) is provided on the upper surface of the offset power storage box (9). The limiting wheel (19) is slidably connected to the hanging rail (17). A limiting block (16) is provided above the controller (10). The limiting block (16) is the end position and is used to prevent the offset power storage box (9) from interfering and colliding when it is offset. The moving blocking block (18) is also set on the top of the offset power storage box (9) and is located on the same circumference as the hanging wheel (14). It is used to block the hanging wheel (14) so ​​that it does not exceed the offset power storage box (9) when the offset power storage box (9) moves. The offset box driven wheel (30) is located on the lower surface of the offset power storage box (9). The bottom surface of the offset box (13) is provided with a slide rail (12). The offset box driven wheel (30) is slidably connected to the slide rail (12), and four sets of offset box driven wheels (30) are provided. A set of engines is located at the tail of the aircraft and is connected to the power supply of the thruster motor and the offset power storage box (9); The cockpit (3) is located directly in front of the first wind duct (7), and an outward-opening hatch (4) is provided at the lower front of the cockpit (3); A hidden drive wheel (5) is located on the lower front side of the offset box (13). Two hidden driven wheels (6) are provided on both sides of the hidden drive wheel (5) after 120 degrees. The power supply control system is located inside the aircraft. It includes the flight control system, the peripheral imaging system, and the offset box control system. When using unmanned remote control, the offset box control system is connected to the flight operating system.

2. The vertical offset aircraft according to claim 1, characterized in that: The first motor bracket (71) and the second motor bracket (74) are configured with a cross-shaped elliptical inner cavity.

3. The vertical offset aircraft according to claim 1, characterized in that: The offset power storage box (9) is equipped with an energy storage battery or other energy storage power source.

4. The vertical offset aircraft according to claim 1, characterized in that: The offset power storage box (9) is provided with a first limit switch (21) on the side closer to the controller (10), and a second limit switch (32) is provided on the side of the offset power storage box (9) away from the controller (10). A set of buffer blocks (31) is also provided on one side of the second limit switch (32). When the two offset power storage boxes (9) move forward and are about to contact each other, the buffer blocks (31) contact and buffer to prevent the two boxes from colliding.

5. The vertical offset aircraft according to claim 1, characterized in that: The output end of the first thruster motor (72) is fixedly connected to a drive shaft (77), and the upper end of the drive shaft (77) is connected to a reversing gear set (78). The reversing gear set (78) is composed of several drive gears, and the output end of the reversing gear set (78) is fixedly connected to the second thruster blade (76). The forward and reverse rotation of the second thruster blade (76) and the first thruster blade (73) is realized by a motor.

6. The vertical offset aircraft according to claim 1, characterized in that: The cable tray is configured as a telescopic flexible cable tray (15), which is equipped with a main line and a secondary control line. The power supply in the offset power storage box (9) is connected to the controller (10) for power supply through the telescopic flexible cable tray (15).

7. The vertical offset aircraft according to claim 1, characterized in that: The cable tray is set as a ceiling-mounted cable tray. A telescopic contact rod (20) is provided between the movable blocking block (18) and the limiting wheel (19). The bottom bolt of the telescopic contact rod (20) is fixed to the top of the offset power storage box (9). A compression spring or spring sheet is provided inside the telescopic contact rod (20). A movable contact is fixed to the top of the telescopic contact rod (20) and is slidably connected to the cable tray.

8. The vertical offset aircraft according to claim 1, characterized in that: A steering fine-tuning thruster (8) is provided on the lower rear side of the shell (1), installed in the arc shape of the lower rear part of the aircraft. The steering fine-tuning thruster (8) includes a second wind concentrator (82), with air inlets and outlets on both sides consistent with the arc shape of the outer shape. A rotary motor (81) is provided on the right side of the second wind concentrator (82). The output end of the rotary motor (81) passes through the second wind concentrator (82) and is fixedly connected to a spindle (85). A third motor bracket (84) is fixedly connected to one side of the spindle (85). A third thruster motor (83) is fixedly connected to the third motor bracket (84). A third thruster blade is fixedly connected to the output end of the third thruster motor (83). When the rotary motor (81) is started, its output end will drive the third thruster blade to rotate, thereby achieving the effect of torque fine-tuning.

9. The vertical offset aircraft according to claim 1, characterized in that: The cockpit (3) is equipped with a hemispherical driving observation window above it, and the cockpit (3) is equipped with a manual and automatic tilt control console and a 45-degree vertical tilt seat.

10. The vertical offset aircraft according to claim 1, characterized in that: Replace the transmission components. A first offset box motor (33) is installed below the first thruster motor (72). The output end of the first offset box motor (33) is fixedly connected to a first motor shaft (331). A first connecting arm (332) is fixedly installed on the left side wall of the first motor shaft (331). The other end of the first connecting arm (332) is fixedly connected to the left offset power storage box (9). A second offset box motor (34) is installed at the bottom of the offset box (13). The output end of the second offset box motor (34) is fixedly connected to a second motor shaft (341). A plane bearing is installed between the second motor shaft (341) and the first motor shaft (331). A ball bearing is installed on the top of the second motor shaft (341). A second ball bearing is fixedly installed on the right outer wall of the second motor shaft (341). The connecting arm (342) is fixedly connected to the right offset power storage box (9) at the other end. The top of the left offset power storage box (9) is provided with a first sliding component (333), and the top of the right offset power storage box (9) is provided with a second sliding component (343), thereby ensuring the orderly movement of the offset power storage box (9) in the offset box (13). The tops of the left and right offset power storage boxes (9) are respectively provided with a first moving contact (334) and a second moving contact (344). The movement of the two sets of offset power storage boxes (9) is realized by controlling the operation of the first offset box motor (33) and the second offset box motor (34). The first sliding component (333) and the second sliding component (343) are both composed of T-shaped hanging rails and track wheels.

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