High-speed helicopter

Abstract

The invention relates to the technical field of helicopters, and provides a high-speed helicopter which comprises a power mechanism, a tail rotor control mechanism, an auxiliary mechanism and a helicopter body, the power mechanism comprises an engine, the engine is installed on the top of the helicopter body, auxiliary power devices are installed on the two sides of the engine, and auxiliary batteries are installed on the two sides of the helicopter body; the top of the engine is provided with a rotor hub, the rotor hub is fixedly connected with four rotor blades which are uniformly distributed on the circumference, and through the arrangement of the structures such as the helicopter body and the auxiliary power device, when the helicopter moves forwards in the sky, the helicopter flies more smoothly through the streamline arrangement of the helicopter body; according to the technical scheme, the engine, the auxiliary power device and the auxiliary battery are arranged on the helicopter, so that the power of the helicopter is stronger, high-speed flight is achieved through the engine with higher power, the voyage is increased, and the problems of low power and poor empennage functionality in the prior art are solved through the technical scheme.

Description

Technical Field

[0001] The present invention relates to the technical field of helicopters, and specifically, to high-speed helicopters. Background Art

[0002] Currently, a helicopter is an aircraft whose lift depends entirely on one or more rotors rotating around a vertical axis. These rotors generate a reaction force by repelling the airflow downward, thereby supporting its flight in the air.

[0003] In the prior art, there is a fast helicopter with the publication number of CN104163240A. This patent relates to the field of aviation technology, especially a fast helicopter. The design of this patent aims to improve the flight speed and optimize the flight efficiency. Through a series of innovative measures, the overall performance of the helicopter has been significantly improved. Specifically, on the basis of the original helicopter, a thrust device arranged backward is added. This thrust device mainly consists of a thrust engine and a propeller. By generating thrust backward, it provides an additional forward pushing force for the helicopter. This design enables the helicopter to obtain a greater speed during flight in the air, thereby effectively shortening the flight time and reducing the flight cost.

[0004] However, when this patent is in use, in order to have a longer range, a small and weak engine is adopted on the basis of sufficient power. As a result, the reserve power is extremely low, resulting in extremely poor power under the conditions of thin oxygen at high altitudes or plateaus, which affects the speed and ceiling, and even makes it impossible to take off and land on plateaus. When this patent is in use, the tail wing can only provide propulsion assistance and cannot provide stability and lift for the helicopter. When this patent is in use, its functions are single. Summary of the Invention

[0005] The present invention provides a high-speed helicopter, which solves the problems of low power and poor functionality of the tail wing in the related art.

[0006] The technical solution of the present invention is as follows: A high-speed helicopter includes a power mechanism, a tail rotor control mechanism, an auxiliary mechanism, and a fuselage. The power mechanism includes an engine, which is installed on the top of the fuselage. Auxiliary power devices are installed on both sides of the engine. Auxiliary batteries are installed on both sides of the fuselage. A rotor hub is installed on the top of the engine. Four circumferentially distributed rotor blades are fixedly connected to the rotor hub. A rear fairing is fixedly connected to one end of the fuselage. A wake wing is installed at one end of the fuselage. Two symmetrically arranged headlamps are installed on one side of the fuselage. Two symmetrically arranged bottom lamps are installed at the bottom of the fuselage. A cargo hold is arranged at the tail of the fuselage. A front window and a sliding door are respectively slidably assembled on both sides of the fuselage. A warning lamp is installed at the bottom of the fuselage. A cockpit is arranged at the head of the fuselage. A passenger cabin is arranged in the middle of the fuselage.

[0007] As a preferred embodiment of the present invention, the tail rotor control mechanism includes a rotating motor installed inside the fuselage. The output end of the rotating motor is connected by a coupling to a coaxial rotating shaft. One end of the rotating shaft is equipped with a tail wing power box. One side of the tail wing power box is equipped with a tail wing hub. Four circumferentially evenly distributed tail wing blades are fixedly connected to the tail wing hub. The two sides of the fuselage are respectively equipped with a first hydraulic cylinder and a second hydraulic cylinder. A front landing wheel is jointly installed on the first hydraulic cylinder and the second hydraulic cylinder. A rear hydraulic cylinder is installed at the bottom of the fuselage. One end of the rear hydraulic cylinder is equipped with a rear landing wheel.

[0008] As a preferred embodiment of the present invention, the auxiliary mechanism includes two upper frames respectively fixedly connected to the two sides of the fuselage. A smoke warning device is installed at the bottom of the fuselage. A fog outlet head is installed at the bottom of the smoke warning device. A suspension box is installed at the bottom of the fuselage. A rotating motor is installed inside the suspension box. The output end of the rotating motor is connected by a coupling to a coaxial rotating shaft. Two symmetrically arranged limiting circular plates are fixedly sleeved on the outer peripheral surface of the rotating shaft. A pull rope is arranged on the outer peripheral surface of the rotating shaft. One end of the pull rope is fixedly connected to a hook. A follower shaft is rotatably installed inside the suspension box. One end of the follower shaft is fixedly connected to a reciprocating lead screw. A transmission belt is jointly installed on the outer peripheral surfaces of the rotating shaft and the follower shaft. A sliding block is movably sleeved on the outer peripheral surface of the reciprocating lead screw. A limiting plate is fixedly connected inside the suspension box.

[0009] As a preferred embodiment of the present invention, a circular hole is formed inside the fuselage. The rotating shaft is rotatably installed inside the circular hole, and the circular hole is used for the rotation of the rotating shaft.

[0010] As a preferred embodiment of the present invention, a circular groove is formed inside the suspension box. The rotating shaft is rotatably installed inside the circular groove, and the circular groove is used for the rotation of the rotating shaft.

[0011] As a preferred embodiment of the present invention, a hole groove is formed inside the suspension box body. The follower shaft is rotatably installed inside the hole groove, and the hole groove is used for the rotation of the follower shaft.

[0012] As a preferred embodiment of the present invention, a rotating groove is formed inside the suspension box body. The reciprocating lead screw is rotatably installed inside the rotating groove, and the rotating groove is used for the rotation of the reciprocating lead screw.

[0013] As a preferred embodiment of the present invention, a sliding groove is formed inside the limiting plate. The sliding block is slidably connected inside the sliding groove, and the sliding groove is used for the sliding of the sliding block.

[0014] As a preferred embodiment of the present invention, a through groove is formed inside the sliding block, and the pulling rope passes through the inside of the through groove, and the through groove is used for the pulling rope to pass through.

[0015] The working principle and beneficial effects of the present invention are as follows:

[0016] 1. Through the arrangement of structures such as the fuselage and the auxiliary power device in the present invention, when the helicopter moves forward in the sky, the streamlined setting of the fuselage makes the flight of the helicopter smoother. An engine, an auxiliary power device, and an auxiliary battery are provided on the helicopter, making the power of the helicopter stronger. A more powerful engine is used to achieve high-speed flight and increase the flight range.

[0017] 2. Through the arrangement of structures such as the rotating motor and the tail rotor blade in the present invention, when the helicopter ascends to a high altitude, the rotating motor is turned on. The rotation of the rotating motor drives the angle of the tail rotor blade to rotate, making the tail rotor blade rotate backward by 45 degrees to give the helicopter a forward thrust, improving the forward thrust of the helicopter and enhancing the functionality of the tail.

[0018] 3. Through the arrangement of structures such as the suspension box and the upper frame in the present invention, when the helicopter needs to lift the cargo and leave, the rotating motor in the suspension box is turned on, causing the hook to descend for overhauling and lifting the cargo. Upper frames are provided on both sides of the helicopter to assist personnel in boarding, improving its functionality. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] The present invention will be further described in detail below in conjunction with the drawings and specific embodiments.

[0020] Figure 1 It is a schematic diagram of the overall structure of the present invention;

[0021] Figure 2 It is a bottom view of the overall structure of the present invention;

[0022] Figure 3 It is a side view of the overall structure of the present invention;

[0023] Figure 4 It is a schematic diagram of the overall structure of the tail rotor blade of the present invention;

[0024] Figure 5 It is a schematic diagram of the internal structure of the suspension box of the present invention;

[0025] Figure 6 It is a schematic diagram of the overall structure of the smoke alarm of the present invention.

[0026] In the figure: 1. Power mechanism; 11. Body; 111. Headlight; 112. Bottom light; 113. Cargo hold; 114. Front window; 115. Sliding door; 116. Warning light; 117. Cockpit; 118. Passenger cabin; 119. Auxiliary battery; 12. Engine; 121. Auxiliary power unit; 122. Rotor hub; 123. Rotor blade; 13. Rear deflector wing; 131. Wake wing;

[0027] 2. Tail rotor control mechanism; 21. Rotating motor; 211. Rotating shaft; 212. Tail wing power box; 22. Tail wing hub; 221. Tail wing blade; 23. First hydraulic cylinder; 231. Second hydraulic cylinder; 232. Front landing wheel; 24. Rear hydraulic cylinder; 241. Rear landing wheel;

[0028] 3. Auxiliary mechanism; 31. Upper frame; 32. Suspension box; 321. Rotating motor; 322. Rotating shaft; 323. Limiting circular plate; 324. Pulling rope; 325. Hook; 326. Transmission belt; 33. Follow-up shaft; 331. Reciprocating lead screw; 332. Sliding block; 34. Limiting plate; 35. Smoke warning device; 351. Mist outlet head. Specific implementation mode

[0029] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts fall within the scope of protection of the present invention.

[0030] Embodiment 1

[0031] As Figures 1 to 6As shown in the figure, this embodiment proposes a high-speed helicopter, which includes a power mechanism 1, a tail rotor control mechanism 2, an auxiliary mechanism 3, and a fuselage 11. The power mechanism 1 includes an engine 12, which is installed on the top of the fuselage 11. Auxiliary power devices 121 are installed on both sides of the engine 12. Auxiliary batteries 119 are installed on both sides of the fuselage 11. A rotor hub 122 is installed on the top of the engine 12. Four circumferentially evenly distributed rotor blades 123 are fixedly connected to the rotor hub 122. A rear fairing wing 13 is fixedly connected to one end of the fuselage 11. A wake wing 131 is installed at one end of the fuselage 11. Two symmetrically arranged headlamps 111 are installed on one side of the fuselage 11. Two symmetrically arranged bottom lamps 112 are installed at the bottom of the fuselage 11. A cargo hold 113 is provided at the tail of the fuselage 11. A front window 114 and a sliding door 115 are respectively slidably assembled on both sides of the fuselage 11. A warning lamp 116 is installed at the bottom of the fuselage 11. A cockpit 117 is provided at the head of the fuselage 11. A passenger cabin 118 is provided in the middle of the fuselage 11. Through the settings of structures such as the fuselage 11 and the auxiliary power device 121, when the helicopter moves forward in the sky, the streamlined setting of the fuselage 11 makes the helicopter fly more smoothly. The engine 12, the auxiliary power device 121, and the auxiliary battery 119 are provided on the helicopter, making the power of the helicopter stronger. With a larger power engine, high-speed flight is achieved, and the range is increased.

[0032] In this embodiment, there are headlamps 111 and bottom lamps 112 at the front and bottom of the fuselage 11 for lighting when the helicopter is used at night. There is a warning lamp 116 at the bottom of the fuselage 11 for warning at night. A cockpit 117, a passenger cabin 118, and a cargo hold 113 are provided inside the fuselage 11. The cockpit 117 is used to control the helicopter. The passenger cabin 118 is used for passengers. The cargo hold 113 is used to place goods. There are a front window 114 and a sliding door 115 on both sides of the fuselage 11. The front window 114 and the sliding door 115 are used to protect personnel during helicopter flight. There are a rear fairing wing 13 and a wake wing 131 at the tail of the fuselage 11. The fuselage 11 is designed in a streamlined shape, which conforms to aerodynamics. When moving forward and cooperating with the rear fairing wing 13 and the wake wing 131, it can move forward better. The engine 12, the auxiliary battery 119, and the auxiliary power mechanism 1 are provided on the fuselage 11, making the power of the rotor blades 123 stronger when the rotor hub 122 rotates. With a larger power engine, high-speed flight is achieved, and the range is increased. And by disconnecting the power of the rotor blades 123 at high altitude, the shock wave generated by the side of the rotor blades 123 rotating forward approaching supersonic speed brings huge resistance to flight, avoiding power loss.

[0033] Embodiment 2

[0034] As Figures 1 to 4As shown in the figure, based on the same concept as in the above Embodiment 1, this embodiment also proposes that the tail rotor control mechanism 2 includes a rotating motor 21. The rotating motor 21 is installed inside the fuselage 11. The output end of the rotating motor 21 is connected by a coupling to a coaxial rotating shaft 211. One end of the rotating shaft 211 is installed with a tail wing power box 212. One side of the tail wing power box 212 is installed with a tail wing hub 22. Four circumferentially evenly distributed tail wing blades 221 are fixedly connected to the tail wing hub 22. A first hydraulic cylinder 23 and a second hydraulic cylinder 231 are respectively installed on both sides of the fuselage 11. A front landing wheel 232 is jointly installed on the first hydraulic cylinder 23 and the second hydraulic cylinder 231. A rear hydraulic cylinder 24 is installed at the bottom of the fuselage 11. One end of the rear hydraulic cylinder 24 is installed with a rear landing wheel 241. Through the setting of structures such as the rotating motor 21 and the tail wing blades 221, when the helicopter ascends to a high altitude, the rotating motor 21 is turned on. The rotating motor 21 starts to drive the angle of the tail wing blades 221 to rotate, making the tail wing blades 221 rotate backward by 45 degrees to give the helicopter a forward thrust, improving the forward thrust of the helicopter and enhancing the functionality of the tail wing.

[0035] As Figures 1 to 4 shown, a circular hole is opened inside the fuselage 11, and the rotating shaft 211 is rotatably installed inside the circular hole.

[0036] In this embodiment, there are a first hydraulic cylinder 23, a second hydraulic cylinder 231 and a rear hydraulic cylinder 24 at the bottom of the fuselage 11. The activation of the first hydraulic cylinder 23 and the second hydraulic cylinder 231 causes the front landing wheel 232 to descend, and the activation of the rear hydraulic cylinder 24 causes the rear landing wheel 241 to descend. The descent of the front landing wheel 232 and the rear landing wheel 241 assists in the descent of the helicopter. When the helicopter ascends to a high altitude, the rotating motor 21 is turned on. The rotating motor 21 starts to drive the rotating shaft 211 to rotate. The rotation of the rotating shaft 211 causes the angle of the tail wing power box 212 to rotate, thereby causing the angle of the tail wing blades 221 to rotate, making the tail wing blades 221 rotate backward by 45 degrees to give the helicopter a forward thrust, improving the forward thrust of the helicopter.

[0037] Embodiment 3

[0038] As Figures 1 to 4As shown in the figure, based on the same concept as in the above-mentioned Embodiment 1, this embodiment also proposes that the auxiliary mechanism 3 includes two upper frames 31, which are respectively fixedly connected to both sides of the fuselage 11. A smoke warning device 35 is installed at the bottom of the fuselage 11, and a mist outlet 351 is installed at the bottom of the smoke warning device 35. A suspension box 32 is installed at the bottom of the fuselage 11. A rotating motor 321 is installed inside the suspension box 32. The output end of the rotating motor 321 is connected by a coupling to a coaxial rotating shaft 322. Two symmetrically arranged limiting circular plates 323 are fixedly sleeved on the outer peripheral surface of the rotating shaft 322. A pull rope 324 is arranged on the outer peripheral surface of the rotating shaft 322. One end of the pull rope 324 is fixedly connected to a hook 325. A follower shaft 33 is rotatably installed inside the suspension box 32. One end of the follower shaft 33 is fixedly connected to a reciprocating lead screw 331. A transmission belt 326 is jointly installed on the outer peripheral surfaces of the rotating shaft 322 and the follower shaft 33. A sliding block 332 is movably sleeved on the outer peripheral surface of the reciprocating lead screw 331. A limiting plate 34 is fixedly connected inside the suspension box 32. Through the settings of structures such as the suspension box 32 and the upper frame 31, when the helicopter needs to drive the goods away, the rotating motor 321 inside the suspension box 32 is turned on, so that the hook 325 descends to overhaul and hoist the goods. The upper frames 31 are arranged on both sides of the helicopter, which can provide assistance when personnel board the plane and improve its functionality.

[0039] As Figure 5 shown, a circular groove is opened inside the suspension box 32, and the rotating shaft 322 is rotatably installed inside the circular groove.

[0040] As Figure 5 shown, a hole groove is opened inside the suspension box 32 body, and the follower shaft 33 is rotatably installed inside the hole groove.

[0041] As Figure 5 shown, a rotating groove is opened inside the suspension box 32 body, and the reciprocating lead screw 331 is rotatably installed inside the rotating groove.

[0042] As Figure 5 shown, a through groove is opened inside the sliding block 332, and the pull rope 324 passes through the inside of the through groove.

[0043] In this embodiment, a smoke warning device 35 is installed at the bottom of the airframe 11. There is a mist outlet 351 on the smoke warning device 35. When the helicopter fails, the smoke warning device 35 is turned on, so that smoke is ejected from the mist outlet 351, facilitating the outside world to timely understand the failure of the helicopter. An upper airframe 31 is provided on the airframe. When personnel board the helicopter, they can enter the interior of the airframe 11 through the upper airframe 31. When the equipment needs to lift goods, the helicopter takes off first, and then the rotation motor 321 is turned on. The rotation of the rotation motor 321 drives the rotation of the rotation shaft 322. The rotation of the rotation shaft 322 causes the pulling rope 324 to descend. The descent of the pulling rope 324 causes the hook 325 to descend. At this time, the personnel can hook the hook 325 to the goods. While the pulling rope 324 is descending and retracting, the rotation of the rotation shaft 322 drives the rotation of the follower shaft 33 through the transmission belt 326. The rotation of the follower shaft 33 drives the rotation of the reciprocating lead screw 331. The rotation of the reciprocating lead screw 331 causes the sliding block 332 to slide. When the sliding block 332 slides, it controls the lowering and retracting positions of the pulling rope 324. When the sliding block 332 slides, the limit plate 34 limits it to prevent the pulling rope 324 from getting disordered, improving the functionality of the helicopter.

[0044] The above are only the preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principles of the present invention shall be included in the protection scope of the present invention.

Claims

1. High-speed helicopter, characterized in that, It includes a power mechanism (1), a tail rotor control mechanism (2), an auxiliary mechanism (3) and a fuselage (11). The power mechanism (1) includes an engine (12). The engine (12) is installed on the top of the fuselage (11). Auxiliary power devices (121) are installed on both sides of the engine (12). Auxiliary batteries (119) are installed on both sides of the fuselage (11). A rotor hub (122) is installed on the top of the engine (12). Four rotors (123) evenly distributed in a circle are fixedly connected to the rotor hub (122). A rear fairing (13) is fixedly connected to one end of the fuselage (11). A wake wing (131) is installed at one end of the fuselage (11). Two symmetrically arranged headlamps (111) are installed on one side of the fuselage (11). Two symmetrically arranged bottom lamps (112) are installed at the bottom of the fuselage (11). A cargo hold (113) is provided at the tail of the fuselage (11). A front window (114) and a sliding door (115) are respectively slidably assembled on both sides of the fuselage (11). A warning lamp (116) is installed at the bottom of the fuselage (11). A cockpit (117) is provided at the head of the fuselage (11). A passenger cabin (118) is provided in the middle of the fuselage (11).

2. The high-speed helicopter according to claim 1, characterized in that, The tail rotor control mechanism (2) includes a rotating motor (21). The rotating motor (21) is installed inside the fuselage (11). The output end of the rotating motor (21) is connected by a coupling to a coaxial rotating shaft (211). A tail wing power box (212) is installed at one end of the rotating shaft (211). A tail wing hub (22) is installed on one side of the tail wing power box (212). Four tail wing blades (221) evenly distributed in a circle are fixedly connected to the tail wing hub (22). A first hydraulic cylinder (23) and a second hydraulic cylinder (231) are respectively installed on both sides of the fuselage (11). A front landing wheel (232) is jointly installed on the first hydraulic cylinder (23) and the second hydraulic cylinder (231). A rear hydraulic cylinder (24) is installed at the bottom of the fuselage (11). A rear landing wheel (241) is installed at one end of the rear hydraulic cylinder (24).

3. The high-speed helicopter according to claim 1, wherein, The auxiliary mechanism (3) includes two upper machine frames (31), the two upper machine frames (31) are respectively fixedly connected to both sides of the machine body (11), a smoke warning device (35) is installed at the bottom of the machine body (11), a fog outlet head (351) is installed at the bottom of the smoke warning device (35), a suspension box (32) is installed at the bottom of the machine body (11), a rotation motor (321) is installed inside the suspension box (32), the output end of the rotation motor (321) is connected by a coupling to a rotation shaft (322) arranged coaxially, two symmetrically arranged limiting circular plates (323) are fixedly sleeved on the outer peripheral surface of the rotation shaft (322), a pulling rope (324) is arranged on the outer peripheral surface of the rotation shaft (322), one end of the pulling rope (324) is fixedly connected to a hook (325), a follower shaft (33) is rotatably installed inside the suspension box (32), one end of the follower shaft (33) is fixedly connected to a reciprocating lead screw (331), a transmission belt (326) is commonly installed on the outer peripheral surfaces of the rotation shaft (322) and the follower shaft (33), a sliding block (332) is movably sleeved on the outer peripheral surface of the reciprocating lead screw (331), and a limiting plate (34) is fixedly connected inside the suspension box (32).

4. The high-speed helicopter according to claim 2, wherein, A circular hole is formed inside the machine body (11), and the rotating shaft (211) is rotatably installed inside the circular hole.

5. The high-speed helicopter according to claim 3, wherein, A circular groove is formed inside the suspension box (32), and the rotation shaft (322) is rotatably installed inside the circular groove.

6. The high-speed helicopter according to claim 3, characterized in that, A hole groove is formed inside the body of the suspension box (32), and the follower shaft (33) is rotatably installed inside the hole groove.

7. The high-speed helicopter according to claim 3, characterized in that, A rotating groove is formed inside the body of the suspension box (32), and the reciprocating lead screw (331) is rotatably installed inside the rotating groove.

8. The high-speed helicopter according to claim 3, characterized in that, A sliding groove is formed inside the limiting plate (34), and the sliding block (332) is slidably connected inside the sliding groove.

9. The high-speed helicopter according to claim 3, characterized in that, A through groove is formed inside the sliding block (332), and the pulling rope (324) passes through the inside of the through groove.

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