An unmanned helicopter

Abstract

This invention relates to the field of unmanned aerial vehicles (UAVs) and discloses an unmanned helicopter, including a frame, a power system, and landing gear. The frame has two front vertical members and two rear vertical members, each connected to an upper longitudinal member and a lower longitudinal member, respectively. The front vertical members form a front section, the rear vertical members form a rear section, and the area between the front and rear vertical members forms a middle section. The power system consists of an engine, a reducer, a horizontal drive shaft, a reversing mechanism, and a rotor, connected sequentially. The engine and reducer are located in the middle of the frame. The front and rear fuel tanks are both connected to the engine and are located at the front and rear of the frame, respectively. A tilting mechanism connects to the engine and tilts it to achieve tensioning and disengagement of the engine and reducer belts, thereby connecting and disengaging the engine and rotor. The rear end of the engine is rotatably connected to the two lower longitudinal members via a tilting bracket, and the front end is fixed to the frame via the tilting mechanism. This unmanned helicopter has a simple and reliable fuselage frame, a compact overall structure, and a reasonable layout.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicles (UAVs), and in particular to an unmanned helicopter. Background Technology

[0002] Unmanned helicopters are characterized by vertical takeoff and landing, hovering, and precise recovery. They have low requirements for takeoff and landing sites, good environmental adaptability and flexibility, and can be widely used in missions such as resupply, emergency rescue, and transportation. Among them, tandem rotor unmanned helicopters are increasingly favored due to their compact structure, large payload, and high safety.

[0003] However, the overall structure of unmanned helicopters still has some problems, such as complex structure, difficulty in assembly and disassembly, low reliability of fuselage frame, and unreasonable layout of major components. Summary of the Invention

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

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

[0006] An unmanned helicopter includes a frame, a power system, and landing gear. The frame includes two upper longitudinal struts, multiple upper transverse struts, two lower longitudinal struts, multiple lower transverse struts, two front diagonal struts, two front vertical struts, two rear diagonal struts, and two rear vertical struts. The two upper longitudinal struts, multiple upper transverse struts, two lower longitudinal struts, multiple lower transverse struts, two front diagonal struts, and two rear diagonal struts constitute the overall structure of the frame. The two front vertical struts and two rear vertical struts are respectively connected to the upper and lower longitudinal struts at both ends. The front of the front vertical struts forms the front section, the rear of the rear vertical struts forms the rear section, and the middle section is formed between the front and rear vertical struts. The power system includes an engine, a reducer, and a horizontal transmission. The engine, reducer, horizontal drive shaft, reversing mechanism, and rotor are connected in sequence. The engine and reducer are located in the middle of the frame. The front and rear oil tanks are both connected to the engine and are located at the front and rear of the frame, respectively. The tilting mechanism is connected to the engine to tilt it, thereby tightening and disengaging the belts of the engine and reducer, and thus connecting and disengaging the engine and rotor. The rear end of the engine is rotatably connected to two lower longitudinal rods via a tilting bracket, and the front end is fixed to the frame via the tilting mechanism. The landing gear is fixed to the frame.

[0007] The reducer is a belt drive mechanism, including a drive pulley, a driven pulley, and a belt. The drive pulley is located in front of the engine, and the drive pulley axle that cooperates with the drive pulley is rigidly connected to the engine. The driven pulley is fixed to two upper longitudinal rods. A four-jaw aerospace aluminum part is fixed to the front end of the engine. The far end of the drive pulley axle is concentrically fixed to the engine output end through the four-jaw aerospace aluminum part.

[0008] The tilting mechanism is located in front of the drive wheel and includes an electric push rod and a vertical moving mechanism. One end of the vertical moving mechanism is connected to the electric push rod, and the other end is connected to a four-jaw aerospace aluminum component. The electric push rod drives the front end of the engine to move up and down through the vertical moving mechanism and the four-jaw aerospace aluminum component to achieve tilting.

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

[0010] The tilting mechanism also includes two rollers, which are located on the outer sides of the belt and connected to an electric actuator through a linkage structure. When the electric actuator moves downward, the rollers also squeeze the belt inward.

[0011] The front and rear oil tanks each have an outer and an inner side, which are V-shaped. Each side of the front and rear of the frame includes an outer and an inner fixing rod, which are V-shaped. The front and rear oil tanks are supported on the outer and inner fixing rods. The front and rear oil tanks are secured to the outer and inner fixing rods by strong tightening flat straps.

[0012] The power system also includes an intercooler for cooling the engine, which is mounted on the rear strut.

[0013] It also includes an electronic control board, which is located in front of the two front vertical bars and fixed to the two front vertical bars.

[0014] 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 fixed to the front end and the rear end of the upper longitudinal rod, respectively. The two ends of the horizontal drive shaft are respectively connected to the front reversing mechanism and the rear reversing mechanism. The main input shaft of the reversing mechanism integrates and installs 12V and 24V generators, which are driven by the horizontal drive shaft.

[0015] The upper longitudinal rod has a bearing fixed at its rear, 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 and two connecting beams connected to the front and rear ends of the skid tubes respectively. Each connecting beam includes an upper connecting part and a lower connecting part extending downward from both ends of the upper connecting part. The upper connecting part is connected to the lower crossbar of the frame via a connecting mechanism. The connecting mechanism includes an upper connecting member, a middle connecting member, and a lower connecting member. The upper connecting member has a flat surface at its upper end for mounting bolts, and a first lower arc-shaped recess at its lower end that mates with the lower surface of the frame's lower crossbar. The middle connecting member has a recess at its upper end that mates with the lower surface of the frame's lower crossbar. The lower surface of the crossbar has a first upper arc-shaped recess that mates with it, and the lower end has a second lower arc-shaped recess that mates with the upper surface of the upper connecting part; the upper end of the lower connector has a second upper arc-shaped recess that mates with the lower surface of the upper connecting part, and the lower end has a flat surface for the nut to mate with it; the upper connector, the middle connector, and the lower connector all have through holes that extend vertically, so that the fixing bolts can pass through the through holes of the upper connector, the lower crossbar of the frame, the middle connector, the upper connecting part of the landing gear, and the lower connector from top to bottom, and be screwed with nuts to fix the landing gear to the frame.

[0017] The beneficial effects of the present invention are: by reasonably fixing the power system and landing gear on the frame, the unmanned helicopter of the present invention makes the fuselage frame simple and reliable, the overall structure compact and the layout reasonable. Attached Figure Description

[0018] Figure 1 This is a perspective view of an unmanned helicopter according to an embodiment of the present invention.

[0019] Figure 2 for Figure 1 The image shown is a 3D view of the unmanned helicopter from another angle.

[0020] Figure 3 for Figure 1 The image shows the front view of the unmanned helicopter.

[0021] Figure 4 for Figure 1 The image shows a 3D view of the frame of the unmanned helicopter.

[0022] Figure 5 for Figure 1 The diagram shows a 3D view of the power system in the unmanned helicopter.

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

[0024] Figure 7 for Figure 5 The diagram shows another perspective of the power system.

[0025] Figure 8 for Figure 5 The diagram shows another perspective of the power system.

[0026] Figure 9 for Figure 1 The diagram shows the reversing mechanism and rotor of the unmanned helicopter.

[0027] Figure 10 for Figure 1 A 3D view of the connecting mechanism in the unmanned helicopter shown. Detailed Implementation

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

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

[0030] like Figure 4 As shown, in this embodiment, the frame mainly includes two upper longitudinal bars 11, multiple upper horizontal bars 12, two lower longitudinal bars 13, multiple lower horizontal bars 14, two front diagonal bars 15, two front vertical bars 16, two rear diagonal bars 17, and two rear vertical bars 18. The two upper longitudinal bars 11, multiple upper horizontal bars 12, two lower longitudinal bars 13, multiple lower horizontal bars 14, two front diagonal bars 15, and two rear diagonal bars 17 constitute the overall structure of the frame. The two front vertical bars 16 and two rear vertical bars 18 are connected at both ends to the upper longitudinal bars 11 and the lower longitudinal bars 13, respectively. The front of the front vertical bar 16 forms the front section, and the rear of the rear vertical bar 18 forms the rear section, with the middle section formed between the front vertical bars 16 and the rear vertical bars 18. Upper horizontal bars 12 and lower horizontal bars 14 are respectively provided at the position of the front vertical bars 16 between the two upper longitudinal bars 11 and the lower longitudinal bars 13, forming a rectangular frame. Each side of the front and rear sections of the frame includes an outer fixing rod 19 and an inner fixing rod 20, which are V-shaped. The upper ends of each outer fixing rod 19 are connected to an upper longitudinal rod 11. An upper horizontal rod 12, a lower horizontal rod 14, and a vertical rod are located at the upper ends of the outer fixing rod 19, forming a rectangular frame. Upper horizontal rods 12, lower horizontal rods 14, and vertical rods are also provided at both ends of the frame, forming rectangular frames. All rods are connected and fixed by welding. The frame structure is both simple and reliably fixed.

[0031] like Figures 1 to 3 As shown, the power system includes an engine 31, a reducer 32, a horizontal drive 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, reducer 32, horizontal drive shaft 33, reversing mechanism 34, and rotor 35 are connected sequentially, enabling the engine 31 to drive the rotor 35 to rotate via the reducer 32, horizontal drive shaft 33, and reversing mechanism 34. The engine 31 and reducer 32 are located in the middle of the frame, while the front fuel tank 36 and rear fuel tank 37 are both connected to the engine 31 and are located at the front and rear of the frame, respectively.

[0032] like Figures 5 to 8As shown, in this embodiment, the reducer 32 is a belt drive mechanism, including a drive pulley 321, a driven pulley 322, and a belt 323. The drive pulley 321 is located in front of the engine 31. The axle of the drive pulley 321, which cooperates with the drive pulley 321, is rigidly connected to the engine 31. The driven pulley 322 is fixed to two upper longitudinal rods 11. A four-jaw aerospace aluminum part 39 is fixed at the front end of the engine 31. The far end of the drive pulley 321 shaft is concentrically fixed to the output end of the engine 31 through the four-jaw aerospace aluminum part 39.

[0033] In this embodiment, the tilting mechanism 38 is connected to the engine 31 to tilt the engine 31, thereby achieving tensioning and disengagement of the belt 323 between the engine 31 and the reducer 32, and thus achieving connection and disengagement between the engine 31 and the rotor 35. The rear end of the engine 31 is rotatably connected to two lower longitudinal rods 13 via the tilting frame 40, and the front end is fixed to the frame via the tilting mechanism 38.

[0034] The tilting mechanism 38 is located in front of the drive wheel 321 and includes an electric actuator 381 and a vertical movement mechanism 382. One end of the vertical movement mechanism 382 is connected to the electric actuator 381, and the other end is connected to a four-jaw aerospace aluminum component 39. This allows the electric actuator 381 to drive the front end of the engine 31 to move up and down through the vertical movement mechanism 382 and the four-jaw aerospace aluminum component 39, thus achieving tilting. The electric actuator 381 is fixed to the upper horizontal bar 12 at the position of the front vertical bar 16. The vertical movement mechanism 382 has a fixed component 3821 and a movable component 3822 pivotally connected by a pivot 3823. The fixed component 3821 is fixed to two upper vertical bars 11, and the movable component 3822 connects the electric actuator 381 and the four-jaw aerospace aluminum component 39. The movable component 3822 has multiple movable structures to provide a certain degree of freedom of movement, allowing the engine to deflect within a certain range. The tilting mechanism 38 also includes two rollers 383, which are located on the outer sides of the belt 323 respectively. They are connected to the electric push rod 381 through the linkage structure 384. When the electric push rod 381 moves downward, the rollers 383 also squeeze the belt 323 inward.

[0035] In this embodiment, the front fuel tank 36 and the rear fuel tank 37 include outer and inner sides, which 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 secured to the outer fixing rod 19 and the inner fixing rod 20 by a strong tightening flat strap 5 (e.g., ...). Figure 3 Only the strong tightening flat strap of the fixed fuel tank 37 was drawn.

[0036] In this embodiment, the power system also includes an intercooler 41 for cooling the engine 31, and the intercooler 41 is mounted on the rear vertical strut 18 (e.g., Figure 7 The upper longitudinal rod 11 is further fixed with a bearing 42 at its rear. The horizontal drive shaft 33 is fixed in the bearing 42 and connected to the two upper longitudinal rods 11 via the bearing 42 (e.g., ...). Figure 3The unmanned helicopter also includes an electronic control board 6, which is located in front of the two front vertical masts 16 and fixed to the two front vertical masts 16 (e.g., Figure 2 ).

[0037] In this embodiment, the rotor 35 includes a front rotor and a rear rotor, and the commutation mechanism 34 includes a front commutation mechanism and a rear commutation 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 drive shaft 33 are respectively connected to the front commutation mechanism and the rear commutation mechanism. A 12V and a 24V generator 7 are integrated and installed on the main input shaft of the commutation mechanism 34, and are driven by the horizontal drive shaft 33 (e.g., ...). Figure 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 (e.g., extending downwards from both ends of the upper connecting portion 821) formed by the upper connecting portion 821. Figure 4 The upper connecting part 821 is connected to the lower crossbar 14 of the frame via a connecting mechanism. For example... Figure 10 As shown, the connecting mechanism includes an upper connecting member 91, a middle connecting member 92, and a lower connecting member 93. The upper connecting member 91 has a flat surface at its upper end for engaging with a fixing bolt 94, and a first lower arc-shaped recess 911 at its lower end for engaging with the lower surface of the lower crossbar 14 of the frame. The middle connecting member 92 has a first upper arc-shaped recess 921 at its upper end for engaging with the lower surface of the lower crossbar 14 of the frame, and a second lower arc-shaped recess 922 at its lower end for engaging with the upper surface of the upper connecting part 821. The lower connecting member 93 has a second upper arc-shaped recess 931 at its upper end for engaging with the lower surface of the upper connecting part 821, and a flat surface at its lower end for engaging with a nut. The upper connector 91, the middle connector 92, and the lower connector 93 are all provided with through holes that extend vertically, so that the fixing bolt 94 can pass through the through holes of the upper connector 91, the lower crossbar 14 of the frame, the middle connector 92, the upper connecting part 821 of the landing gear, and the lower connector 93 from top to bottom, and be screwed with a nut to fix the landing gear to the frame.

Claims

1. An unmanned helicopter, characterized in that, The system includes a frame, a power system, and landing gear. The frame comprises two upper longitudinal bars, multiple upper transverse bars, two lower longitudinal bars, multiple lower transverse bars, two front diagonal bars, two front vertical bars, two rear diagonal bars, and two rear vertical bars. The two upper longitudinal bars, multiple upper transverse bars, two lower longitudinal bars, multiple lower transverse bars, two front diagonal bars, and two rear diagonal bars constitute the overall structure of the frame. The two front vertical bars and two rear vertical bars are connected to the upper and lower longitudinal bars at their respective ends. The front of the front vertical bars forms the front section, and the rear of the rear vertical bars forms the rear section. The front vertical bars and the rear vertical bars... The vertical bars form a central section; the power system includes an engine, a reducer, a horizontal drive shaft, a reversing mechanism, a rotor, a front oil tank, a rear oil tank, and a tilting mechanism. The engine, reducer, horizontal drive shaft, reversing mechanism, and rotor are connected sequentially. The engine and reducer are located in the middle of the frame. The front and rear oil tanks are both connected to the engine and are located at the front and rear of the frame, respectively. The tilting mechanism is connected to the engine to tilt it, thereby achieving tensioning and disengagement of the engine and reducer belts, and thus realizing… The connection and clutch between the engine and rotor are described. The rear end of the engine is rotatably connected to two lower longitudinal rods via a tilting bracket, and the front end is fixed to the frame via a tilting mechanism. The landing gear is fixed to the frame. The reducer is a belt drive mechanism, including a drive pulley, a driven pulley, and a belt. The drive pulley is located in front of the engine, and the drive pulley axle, which cooperates with the drive pulley, is rigidly connected to the engine. The driven pulley is fixed to two upper longitudinal rods. A four-jaw aero-aluminum component is fixed to the front end of the engine. The distal end of the drive pulley axle is concentrically fixed to the engine output end via the four-jaw aero-aluminum component. The tilting mechanism is located in front of the drive pulley and includes an electric actuator and a vertical movement mechanism. One end of the vertical movement mechanism is connected to the electric actuator, and the other end is connected to the four-jaw aero-aluminum component, so that the electric actuator drives the front end of the engine to move up and down through the vertical movement mechanism and the four-jaw aero-aluminum component to achieve tilting. The tilting mechanism also includes two rollers, which are located on the outer sides of the belt and are connected to the electric actuator through a linkage structure. When the electric actuator moves downward, the rollers also squeeze the belt inward.

2. The unmanned helicopter as described in claim 1, characterized in that, An upper horizontal bar is provided between the two upper vertical bars at the position of the front vertical bar. The electric push rod is fixed on the upper horizontal bar. The up-down moving mechanism has a fixed part and a movable part that are pivotally connected. The fixed part is fixed on the two upper vertical bars, and the two ends of the movable part are respectively connected to the electric push rod and the four-jaw aerospace aluminum parts.

3. The unmanned helicopter as described in claim 1, characterized in that, The front and rear oil tanks include outer and inner sides, which are V-shaped. Each side of the front and rear of the frame includes an outer fixing rod and an inner fixing rod, which are V-shaped. The front and rear oil tanks are supported on the outer and inner fixing rods. The front and rear oil tanks are fixed to the outer and inner fixing rods by strong tightening flat straps.

4. The unmanned helicopter as described in claim 1, characterized in that, The powertrain also includes an intercooler for cooling the engine, which is mounted on the rear strut.

5. The unmanned helicopter as described in claim 1, characterized in that, It also includes an electronic control board, which is located in front of the two front vertical bars and fixed to the two front vertical bars.

6. The unmanned helicopter as described in claim 1, characterized in that, The rotor includes a front rotor and a rear rotor. The reversing mechanism includes a front reversing mechanism and a rear reversing mechanism, which are fixed to the front end and rear end of the upper longitudinal rod, respectively. The two ends of the horizontal drive shaft are connected to the front reversing mechanism and the rear reversing mechanism, respectively. A 12V and a 24V generator are integrated and installed on the main input shaft of the reversing mechanism and driven by the horizontal drive shaft. The rear of the upper longitudinal rod is also fixed with a bearing. The horizontal drive shaft is fixed in the bearing and connected to the two upper longitudinal rods through the bearing.

7. The unmanned helicopter as described in claim 1, characterized in that, The landing gear includes two skid tubes and two connecting beams respectively connected to the front and rear ends of the skid tubes. Each connecting beam includes an upper connecting part and a lower connecting part extending downward from both ends of the upper connecting part. The upper connecting part is connected to the lower crossbar of the frame via a connecting mechanism. The connecting mechanism includes an upper connecting member, a middle connecting member, and a lower connecting member. The upper end of the upper connecting member has a flat surface for fixing bolts, and the lower end has a first lower arc-shaped recess that mates with the lower surface of the lower crossbar of the frame. The upper end of the middle connecting member has a recess that mates with the lower crossbar of the frame. The lower surface has a first upper arc-shaped recess that mates with the upper part, and a second lower arc-shaped recess that mates with the upper surface of the upper connecting part at the lower end; the upper end of the lower connecting part has a second upper arc-shaped recess that mates with the lower surface of the upper connecting part, and a flat surface at the lower end for the nut to mate with; the upper connecting part, the middle connecting part, and the lower connecting part all have through holes that extend vertically, so that the fixing bolts can pass through the through holes of the upper connecting part, the lower crossbar of the frame, the middle connecting part, the upper connecting part of the landing gear, and the lower connecting part from top to bottom, and be screwed with nuts to fix the landing gear to the frame.

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