Unmanned helicopter

Abstract

The invention relates to the field of unmanned aerial vehicles, and discloses an unmanned helicopter which comprises a rack, a power system and an undercarriage, the two ends of two front vertical rods and the two ends of two rear vertical rods of the rack are connected with upper longitudinal rods and lower longitudinal rods respectively, the front portions of the front vertical rods form front portions, the rear portions of the rear vertical rods form rear portions, and middle portions are formed between the front vertical rods and the rear vertical rods; an engine, a speed reducer, a horizontal transmission shaft, a reversing mechanism and a rotor wing in the power system are sequentially connected, the engine and the speed reducer are located in the middle of the rack, and a front oil tank and a rear oil tank are connected with the engine and located on the front portion and the rear portion of the rack respectively. The tilting mechanism is connected with the engine and used for enabling the engine to tilt so as to achieve tensioning and separation and reunion of the engine and a speed reducer belt, and then connection and separation and reunion of the engine and the rotor wings are achieved. The rear end of the engine is rotatably connected to the two lower longitudinal rods through a tilting frame, and the front end of the engine is fixed to the rack through a tilting mechanism. The unmanned helicopter fuselage frame is simple, reliable, compact in overall structure and reasonable in layout.

Description

Technical Field

[0001] The invention relates to the field of unmanned aerial vehicles, in particular to an unmanned helicopter. Background Art

[0002] Unmanned helicopters have the characteristics of vertical take-off and landing, fixed-point hovering, and precise recovery. They have low requirements for take-off and landing sites, good environmental adaptability and flexibility, and can be widely used in tasks such as supply, first aid, and transportation. Among them, tandem twin-rotor unmanned helicopters are becoming more and more popular due to their compact structure, large load capacity, and high safety.

[0003] However, there are still some problems with the overall structure of unmanned helicopters, such as complex structure, difficult assembly and disassembly, low reliability of the fuselage frame, unreasonable layout of major components, etc. Summary of the invention

[0004] The invention provides an unmanned helicopter with a simple and reliable fuselage frame and a reasonable layout of main parts.

[0005] To achieve the above object, the technical solution of the present invention is as follows:

[0006] An unmanned helicopter comprises a frame, a power system and a landing gear, wherein the frame comprises two upper longitudinal bars, a plurality of upper cross bars, two lower longitudinal bars, a plurality of lower cross bars, two front oblique bars, two front vertical bars, two rear oblique bars and two rear vertical bars, wherein the two upper longitudinal bars, a plurality of upper cross bars, two lower longitudinal bars, a plurality of lower cross bars, two front oblique bars and two rear oblique bars constitute the overall structure of the frame, the two front vertical bars and the two rear vertical bars are respectively connected at both ends to the upper longitudinal bars and the lower longitudinal bars, the front of the front vertical bars forms the front part, the rear of the rear vertical bars forms the rear part, and the middle part is formed between the front vertical bars and the rear vertical bars; the power system comprises an engine, a reducer, a horizontal transmission The engine, reducer, horizontal transmission shaft, reversing mechanism and rotor are connected in sequence; the engine and reducer are located in the middle of the frame; the front fuel tank and the rear fuel tank are both connected to the engine and are respectively located at the front and rear of the frame; the tilting mechanism is connected to the engine to tilt the engine, so as to achieve the tension and clutch of the engine and the reducer belt, and then achieve the connection and clutch of the engine and the rotor; the rear end of the engine is rotatably connected to the two lower longitudinal rods through the tilting frame, and the front end is fixed to the frame through the tilting mechanism; the landing gear is fixed to the frame.

[0007] Among them, the reducer is a belt transmission mechanism, including a driving wheel, a driven wheel, and a belt. The driving wheel is located in front of the engine, and the driving wheel axle that cooperates with the driving wheel is rigidly connected to the engine. The driven wheel is fixed to two upper longitudinal rods. A four-claw aviation aluminum part is fixed to the front end of the engine, and the far end of the driving wheel axle is concentrically fixed to the engine output end through the four-claw aviation aluminum part.

[0008] Among them, the tilting mechanism is located in front of the driving wheel, and includes an electric push rod and an up and down moving mechanism. One end of the up and down moving mechanism is connected to the electric push rod, and the other end is connected to a four-claw aviation aluminum part, so that the electric push rod drives the front end of the engine to move up and down through the up and down moving mechanism and the four-claw aviation aluminum part to achieve tilting.

[0009] Among them, an upper cross bar is provided between the two upper longitudinal bars at the position of the front vertical bar, the electric push rod is fixed on the upper cross bar, and the up and down moving mechanism has a pivotally connected fixed part and a movable part, the fixed part is fixed on the two upper longitudinal bars, and the two ends of the movable part are respectively connected to the electric push rod and the four-claw aviation aluminum part.

[0010] The tilting mechanism further comprises two rollers, which are respectively located on the two outer sides of the belt and connected to the electric push rod through a linkage structure, so that when the electric push rod moves downward, the rollers also squeeze the belt inward.

[0011] Among them, the front fuel tank and the rear fuel tank include an outer side surface and an inner side surface, and the outer side surface and the inner side surface are V-shaped; each side of the front and rear of the frame includes an outer fixing rod and an inner fixing rod, and the outer fixing rod and the inner fixing rod are V-shaped, and the front fuel tank and the rear fuel tank are supported on the outer fixing rod and the inner fixing rod; the front fuel tank and the rear fuel tank are fixed to the outer fixing rod and the inner fixing rod by strongly tightening flat belts.

[0012] Wherein, the power system also includes an intercooler for dissipating heat from the engine, and the intercooler is installed on the rear vertical rod.

[0013] It also includes an electric control board, which is located in front of the two front vertical rods and fixed on the two front vertical rods.

[0014] Among them, the rotor includes a front rotor and a rear rotor, and the reversing mechanism includes a front reversing mechanism and a rear reversing mechanism, which are respectively fixed to the front end and the rear end of the upper longitudinal rod; the two ends of the horizontal transmission shaft are respectively connected to the front reversing mechanism and the rear reversing mechanism, and the 12V and 24V generators are respectively integrated and installed on the main input shaft of the reversing mechanism and driven by the horizontal transmission shaft.

[0015] A bearing is fixed on the upper rear portion of the upper longitudinal rod, and the horizontal transmission shaft is fixed in the bearing and connected to the two upper longitudinal rods through the bearing.

[0016] The landing gear includes two skid tubes, two connecting beams respectively connected to the front and rear ends of the skid tubes, each connecting beam includes an upper connecting portion and a lower connecting portion formed by extending downward from the two ends of the upper connecting portion, the upper connecting portion is connected to the lower cross bar of the frame through a connecting mechanism, the connecting mechanism includes an upper connecting piece, a middle connecting piece, and a lower connecting piece, the upper end of the upper connecting piece is provided with a flat surface for matching with the fixing bolts, and the lower end is provided with a first lower arc surface depression matching with the lower surface of the lower cross bar of the frame; the upper end of the middle connecting piece is provided with a first lower arc surface depression matching with the lower surface of the lower cross bar of the frame The lower surface of the cross bar cooperates with the first upper arc surface depression, and the lower end is provided with a second lower arc surface depression that cooperates with the upper surface of the upper connecting part; the upper end of the lower connecting piece is provided with a second upper arc surface depression that cooperates with the lower surface of the upper connecting part, and the lower end is provided with a flat surface for the nut to cooperate with; the upper connecting piece, the middle connecting piece, and the lower connecting piece are all provided with through holes that pass through the upper connecting piece, the lower cross bar of the frame, the middle connecting piece, the upper connecting part of the landing gear, and the through holes of the lower connecting piece from top to bottom, and are screwed with the nut to fix the landing gear to the frame.

[0017] The beneficial effects of the present invention are as follows: the unmanned helicopter of the present invention has a power system and a landing gear reasonably fixedly mounted on a frame, so that the fuselage frame is simple and reliable, the overall structure is compact, and the layout is reasonable. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 The figure is a three-dimensional diagram of an unmanned helicopter according to an embodiment of the present invention.

[0019] Figure 2 for Figure 1 A stereoscopic image of the unmanned helicopter from another angle is shown.

[0020] Figure 3 for Figure 1 A front view of the unmanned helicopter is shown.

[0021] Figure 4 for Figure 1 A perspective view of the frame of the unmanned helicopter shown.

[0022] Figure 5 for Figure 1 A three-dimensional diagram of the power system in the unmanned helicopter shown.

[0023] Figure 6 for Figure 5 A three-dimensional view of the power system from another angle.

[0024] Figure 7 for Figure 5 A three-dimensional diagram of the power system shown from another angle.

[0025] Figure 8 for Figure 5 A three-dimensional diagram of the power system shown from another angle.

[0026] Fig. 9 for Figure 1 Schematic diagram of the reversing mechanism and rotor in the unmanned helicopter shown.

[0027] Fig.10 for Figure 1 A three-dimensional diagram of the connection mechanism in the unmanned helicopter shown. DETAILED DESCRIPTION

[0028] The present invention will be further described below in conjunction with the accompanying drawings and examples.

[0029] like Figures 1 to 10 As shown, in this embodiment, the unmanned helicopter mainly includes a frame, a power system, and a landing gear.

[0030] like Figure 4 As shown, in this embodiment, the frame mainly includes two upper longitudinal bars 11, multiple upper cross bars 12, two lower longitudinal bars 13, multiple lower cross bars 14, two front oblique bars 15, two front vertical bars 16, two rear oblique bars 17, and two rear vertical bars 18. Among them, the two upper longitudinal bars 11, multiple upper cross bars 12, two lower longitudinal bars 13, multiple lower cross bars 14, two front oblique bars 15, and two rear oblique bars 17 constitute the overall structure of the frame. The two front vertical bars 16 and the two rear vertical bars 18 are connected to the upper longitudinal bars 11 and the lower longitudinal bars 13 at both ends, the front of the front vertical bars 16 forms the front part, the rear of the rear vertical bars 18 forms the rear part, and the middle part is formed between the front vertical bars 16 and the rear vertical bars 18. The upper cross bar 12 and the lower cross bar 14 are respectively arranged at the position of the front vertical bar 16 between the two upper longitudinal bars 11 and the lower longitudinal bars 13 to form a rectangular frame. Each side of the front and rear of the frame includes an external fixing rod 19 and an internal fixing rod 20, and the external fixing rod 19 and the internal fixing rod 20 are V-shaped. The upper end of each external fixing rod 19 is connected to the upper longitudinal rod 11, and an upper cross bar 12, a lower cross bar 14 and a vertical rod are arranged at the upper end of the external fixing rod 19 to form a rectangular frame. The upper cross bar 12, the lower cross bar 14 and the vertical rod are also arranged at both ends of the frame to form a rectangular frame. The rod-shaped members are connected and fixed by welding. The fuselage frame has a simple structure and is reliably fixed.

[0031] like Figures 1 to 3 As shown, the power system includes an engine 31, a reducer 32, a horizontal transmission shaft 33, a reversing mechanism 34, a rotor 35, a front fuel tank 36, a rear fuel tank 37, and a tilting mechanism 38. The engine 31, the reducer 32, the horizontal transmission shaft 33, the reversing mechanism 34, and the rotor 35 are connected in sequence, so that the engine 31 drives the rotor 35 to rotate through the reducer 32, the horizontal transmission shaft 33, and the reversing mechanism 34. The engine 31 and the reducer 32 are located in the middle of the frame, and the front fuel tank 36 and the rear fuel tank 37 are both connected to the engine 31, and are respectively located at the front and rear of the frame.

[0032] like Figures 5 to 8As shown, in this embodiment, the reducer 32 is a belt transmission mechanism, including a driving wheel 321, a driven wheel 322, and a belt 323. The driving wheel 321 is located in front of the engine 31, and the driving wheel 321 axle matched with the driving wheel 321 is rigidly connected to the engine 31. The driven wheel 322 is fixed to two upper longitudinal rods 11, and a four-claw aviation aluminum part 39 is fixed to the front end of the engine 31. The distal end of the driving wheel 321 shaft is concentrically fixed to the output end of the engine 31 through the four-claw aviation aluminum part 39.

[0033] In this embodiment, the tilt mechanism 38 is connected to the engine 31 to tilt the engine 31, so as to achieve the tension and clutch of the engine 31 and the belt 323 of the reducer 32, and then achieve the connection and clutch of the engine 31 and the rotor 35. The rear end of the engine 31 is rotatably connected to the two lower longitudinal rods 13 through the tilt frame 40, and the front end is fixed to the frame through the tilt mechanism 38.

[0034] The tilt mechanism 38 is located in front of the driving wheel 321, and includes an electric push rod 381 and an up-and-down moving mechanism 382. One end of the up-and-down moving mechanism 382 is connected to the electric push rod 381, and the other end is connected to the four-claw aviation aluminum part 39, so that the electric push rod 381 drives the front end of the engine 31 to move up and down through the up-and-down moving mechanism 382 and the four-claw aviation aluminum part 39 to achieve tilting. Among them, the electric push rod 381 is fixed on the upper cross bar 12 at the position of the front vertical bar 16, and the up-and-down moving mechanism 382 has a fixed part 3821 and a movable part 3822 pivoted by a pivot 3823. The fixed part 3821 is fixed on the two upper longitudinal bars 11, and the movable part 3822 connects the electric push rod 381 and the four-claw aviation aluminum part 39. The movable part 3822 is provided with multiple movable structures to provide a certain degree of freedom of movement so that the engine can deflect within a certain range. The tilting mechanism 38 further includes two rollers 383 , which are respectively located on the two outer sides of the belt 323 and connected to the electric push rod 381 through a linkage structure 384 , so that when the electric push rod 381 moves downward, the rollers 383 also press the belt 323 inward.

[0035] In this embodiment, the front fuel tank 36 and the rear fuel tank 37 include an outer side surface and an inner side surface, and the outer side surface and the inner side surface are V-shaped. The front fuel tank 36 and the rear fuel tank 37 are supported on the outer fixing rod 19 and the inner fixing rod 20, and are fixed to the outer fixing rod 19 and the inner fixing rod 20 by tightening the flat belt 5 (such as Figure 3 , only the strong tightening flat belt that fixes the rear fuel tank 37 is drawn).

[0036] In this embodiment, the power system further includes an intercooler 41 for cooling the engine 31. The intercooler 41 is mounted on the rear vertical rod 18 (eg, Figure 7 The rear part of the upper longitudinal rod 11 is also fixed with a bearing 42 at the top, and the horizontal transmission shaft 33 is fixed in the bearing 42 and connected to the two upper longitudinal rods 11 (such as Figure 3The unmanned helicopter further comprises an electric control panel 6, which is located in front of the two front vertical rods 16 and is fixed on the two front vertical rods 16 (such as Figure 2 ).

[0037] In this embodiment, the rotor 35 includes a front rotor and a rear rotor, and the reversing mechanism 34 includes a front reversing mechanism and a rear reversing mechanism, which are respectively fixed to the front end and the rear end of the upper longitudinal rod 11. The two ends of the horizontal transmission shaft 33 are respectively connected to the front reversing mechanism and the rear reversing mechanism. The 12V and 24V generators 7 are respectively integrated and installed on the main input shaft of the reversing mechanism 34, and are driven by the horizontal transmission shaft 33 (such as Fig. 9 ).

[0038] In this embodiment, the landing gear is fixed to the frame. The landing gear is a skid type, including two skid tubes 81 and two connecting beams 82 respectively connected to the front and rear ends of the skid tubes 81. Each connecting beam 82 includes an upper connecting portion 821 and a lower connecting portion 822 (such as Figure 4 ), the upper connecting portion 821 is connected to the lower cross bar 14 of the frame through a connecting mechanism. Fig.10 As shown, the connection mechanism includes an upper connection member 91, a middle connection member 92, and a lower connection member 93. The upper end of the upper connection member 91 is provided with a flat surface for matching with the fixing bolt 94, and the lower end is provided with a first lower arc surface depression 911 matching with the lower surface of the lower cross bar 14 of the frame. The upper end of the middle connection member 92 is provided with a first upper arc surface depression 921 matching with the lower surface of the lower cross bar 14 of the frame, and the lower end is provided with a second lower arc surface depression 922 matching with the upper surface of the upper connection part 821. The upper end of the lower connection member 93 is provided with a second upper arc surface depression 931 matching with the lower surface of the upper connection part 821, and the lower end is provided with a flat surface for matching with the nut. The upper connecting member 91, the middle connecting member 92 and the lower connecting member 93 are all provided with through holes which penetrate in the vertical direction, so that the fixing bolts 94 can pass through the through holes of the upper connecting member 91, the lower cross bar 14 of the frame, the middle connecting member 92, the upper connecting part 821 of the landing gear and the lower connecting member 93 from top to bottom, and be screwed with nuts to fix the landing gear to the frame.

Claims

1. An unmanned helicopter, characterized in that: The invention comprises a frame, a power system and a landing gear, wherein the frame comprises two upper longitudinal bars, a plurality of upper cross bars, two lower longitudinal bars, a plurality of lower cross bars, two front oblique bars, two front vertical bars, two rear oblique bars and two rear vertical bars, wherein the two upper longitudinal bars, a plurality of upper cross bars, two lower longitudinal bars, a plurality of lower cross bars, two front oblique bars and two rear oblique bars constitute the overall structure of the frame, the two front vertical bars and the two rear vertical bars are respectively connected to the upper longitudinal bars and the lower longitudinal bars at both ends, the front of the front vertical bars forms the front part, the rear of the rear vertical bars forms the rear part, and the middle part is formed between the front vertical bars and the rear vertical bars; the power system comprises an engine, a reducer, a horizontal transmission shaft, a converter The engine, reducer, horizontal transmission shaft, reversing mechanism and rotor are connected in sequence, the engine and reducer are located in the middle of the frame, the front fuel tank and the rear fuel tank are both connected to the engine, and are respectively located at the front and rear of the frame; the tilting mechanism is connected to the engine to tilt the engine, so as to achieve the tension and clutch of the engine and the reducer belt, and then achieve the connection and clutch of the engine and the rotor; the rear end of the engine is rotatably connected to the two lower longitudinal rods through the tilting frame, and the front end is fixed to the frame through the tilting mechanism; the landing gear is fixed to the frame.

2. The unmanned helicopter according to claim 1, characterized in that: The reducer is a belt transmission mechanism, including a driving wheel, a driven wheel, and a belt. The driving wheel is located in front of the engine, and the driving wheel axle that cooperates with the driving wheel is rigidly connected to the engine. The driven wheel is fixed to two upper longitudinal rods. A four-claw aviation aluminum part is fixed to the front end of the engine, and the far end of the driving wheel axle is concentrically fixed to the engine output end through the four-claw aviation aluminum part.

3. The unmanned helicopter according to claim 2, characterized in that: The tilting mechanism is located in front of the driving wheel, and includes an electric push rod and an up and down moving mechanism. One end of the up and down moving mechanism is connected to the electric push rod, and the other end is connected to a four-claw aviation aluminum part, so that the electric push rod drives the front end of the engine to move up and down through the up and down moving mechanism and the four-claw aviation aluminum part to achieve tilting.

4. The unmanned helicopter according to claim 3, characterized in that: An upper cross bar is provided between the two upper longitudinal bars at the position of the front vertical bar, the electric push rod is fixed on the upper cross bar, and the up and down moving mechanism has a fixed part and a movable part pivotally connected to each other, the fixed part is fixed on the two upper longitudinal bars, and the two ends of the movable part are respectively connected to the electric push rod and the four-claw aviation aluminum part.

5. The unmanned helicopter according to claim 3, characterized in that: The tilting mechanism also includes two rollers, which are respectively located at two outer sides of the belt and connected to the electric push rod through a linkage structure, so that when the electric push rod moves downward, the rollers also squeeze the belt inward.

6. The unmanned helicopter according to claim 1, characterized in that: The front fuel tank and the rear fuel tank include an outer side surface and an inner side surface, and the outer side surface and the inner side surface are V-shaped; each side of the front and rear of the frame includes an outer fixing rod and an inner fixing rod, and the outer fixing rod and the inner fixing rod are V-shaped, and the front fuel tank and the rear fuel tank are supported on the outer fixing rod and the inner fixing rod; the front fuel tank and the rear fuel tank are fixed to the outer fixing rod and the inner fixing rod by strongly tightening flat belts.

7. The unmanned helicopter according to claim 1, characterized in that: The power system also includes an intercooler for dissipating heat from the engine, and the intercooler is mounted on the rear vertical rod.

8. The unmanned helicopter according to claim 1, characterized in that: It also includes an electric control board, which is located in front of the two front vertical rods and fixed on the two front vertical rods.

9. The unmanned helicopter according to claim 1, characterized in that: The rotor includes a front rotor and a rear rotor, and the reversing mechanism includes a front reversing mechanism and a rear reversing mechanism, which are respectively fixed to the front end and the rear end of the upper longitudinal rod; the two ends of the horizontal transmission shaft are respectively connected to the front reversing mechanism and the rear reversing mechanism, and 12V and 24V generators are respectively integrated and installed on the main input shaft of the reversing mechanism and driven by the horizontal transmission shaft; a bearing is also fixed on the upper rear part of the upper longitudinal rod, and the horizontal transmission shaft is fixed in the bearing and connected to the two upper longitudinal rods through the bearing.

10. The unmanned helicopter according to claim 1, characterized in that: The landing gear comprises two skid tubes, two connecting beams respectively connected to the front and rear ends of the skid tubes, each connecting beam comprises an upper connecting portion and a lower connecting portion formed by extending downward from the two ends of the upper connecting portion, the upper connecting portion is connected to the lower cross bar of the frame through a connecting mechanism, the connecting mechanism comprises an upper connecting piece, a middle connecting piece, and a lower connecting piece, the upper end of the upper connecting piece is provided with a flat surface for matching with a fixing bolt, and the lower end is provided with a first lower arc surface depression matching with the lower surface of the lower cross bar of the frame; the upper end of the middle connecting piece is provided with a first lower arc surface depression matching with the lower surface of the lower cross bar of the frame The lower surface is matched with the first upper arc surface depression, and the lower end is provided with a second lower arc surface depression matched with the upper surface of the upper connecting part; the upper end of the lower connecting piece is provided with a second upper arc surface depression matched with the lower surface of the upper connecting part, and the lower end is provided with a flat surface for the nut to cooperate with; the upper connecting piece, the middle connecting piece and the lower connecting piece are all provided with through holes that pass through the upper connecting piece, the lower cross bar of the frame, the middle connecting piece, the upper connecting part of the landing gear, and the through holes of the lower connecting piece from top to bottom, and are screwed with the nut to fix the landing gear to the frame.

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