CN111846255A - Four-rotor intelligent unmanned aerial vehicle - Google Patents
Four-rotor intelligent unmanned aerial vehicle Download PDFInfo
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- CN111846255A CN111846255A CN202010731072.9A CN202010731072A CN111846255A CN 111846255 A CN111846255 A CN 111846255A CN 202010731072 A CN202010731072 A CN 202010731072A CN 111846255 A CN111846255 A CN 111846255A
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- 239000003921 oil Substances 0.000 description 69
- 239000000295 fuel oil Substances 0.000 description 35
- 238000000034 method Methods 0.000 description 11
- 230000008569 process Effects 0.000 description 9
- 230000001105 regulatory effect Effects 0.000 description 9
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 6
- 230000009471 action Effects 0.000 description 5
- 238000006243 chemical reaction Methods 0.000 description 5
- 235000017166 Bambusa arundinacea Nutrition 0.000 description 3
- 235000017491 Bambusa tulda Nutrition 0.000 description 3
- 241001330002 Bambuseae Species 0.000 description 3
- 235000015334 Phyllostachys viridis Nutrition 0.000 description 3
- 239000011425 bamboo Substances 0.000 description 3
- 239000002828 fuel tank Substances 0.000 description 2
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- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
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- 238000004140 cleaning Methods 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D37/00—Arrangements in connection with fuel supply for power plant
- B64D37/02—Tanks
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/54—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D37/00—Arrangements in connection with fuel supply for power plant
- B64D37/02—Tanks
- B64D37/06—Constructional adaptations thereof
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
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- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Remote Sensing (AREA)
- Loading And Unloading Of Fuel Tanks Or Ships (AREA)
Abstract
The invention relates to the technical field of rotary wing type unmanned aerial vehicles, and discloses a four-rotary wing type intelligent unmanned aerial vehicle which comprises a vehicle body, wherein two connecting rods are fixedly connected to the left side and the right side of the vehicle body, the two connecting rods positioned on the same side of the vehicle body form a group, and the two groups of connecting rods are mutually symmetrical by taking the center line of the vehicle body in the vertical direction as a symmetry axis. This four rotor formula intelligence unmanned aerial vehicle, be provided with oil transportation device and annular piece through the inside at the oil tank, oil liquid level float process down when fuel consumption in the oil tank, the annular piece all pastes with the ring that floats and float in fluid surface lapse, effectively avoided when wing formula intelligence unmanned aerial vehicle carries out necessary flight mode, cause fluid to vibrate in the oil tank inside and cause the stability of unmanned aerial vehicle flight, effectively improve the stability of wing formula intelligence unmanned aerial vehicle flight, the top through annular piece and oil through hole is protruding form, and annular piece and oil tank inner wall in close contact with, the time and the cost of ponding have been saved to sink in the staff washs the fuel.
Description
Technical Field
The invention relates to the technical field of rotary wing type unmanned aerial vehicles, in particular to a four-rotary wing type intelligent unmanned aerial vehicle.
Background
Four rotor unmanned aerial vehicle can take off and land perpendicularly, with four rotors as power device's unmanned vehicles, because space free rigid body has six degrees of freedom, consequently under unmanned aerial vehicle's rigid body hypothesis, we need just be enough to confirm unmanned aerial vehicle's position and gesture completely with six variables, four rotor unmanned aerial vehicle is a four input six output, nonlinearity, the under-actuated system of strong coupling, it is through four rotors realize advancing and stopping, the relativity of utilizationforce, when four rotors promote air, the air also can reverse promotion four rotors, then play take off and the effect of descending.
The existing four-rotor unmanned aerial vehicle is divided into two modes of adjusting lift force, one mode is adjusted through variable rotating speed, but the corresponding response speed is slow, the other mode is adjusted through variable pitch, although the response speed is high, the mechanical structure for adjusting the pitch is complex, the weight of the four-rotor unmanned aerial vehicle is increased, the load capacity of the four-rotor unmanned aerial vehicle is reduced, and the rotor adjusting structure of the existing four-rotor unmanned aerial vehicle is straight, so that when the four-rotor unmanned aerial vehicle moves transversely, the resistance of air on the rotor adjusting structure is relatively large, and the effect of adjusting the lift force is further influenced; when the fuel oil in the fuel oil tank is consumed, a gap exists between the fuel oil in the fuel oil tank and an inner cavity of the fuel oil tank, when the rotor unmanned aerial vehicle performs necessary flying action in the flying process, the fuel oil in the fuel oil tank can shake, the stability of the four-rotor unmanned aerial vehicle is reduced due to the reaction force of the fuel oil and the fuel oil tank, and when the fuel oil in the fuel oil tank is consumed, the gap between the fuel oil and the top of the inner cavity of the fuel oil tank is increased, namely the content of air in the fuel oil tank is increased, then the moisture contained in the air is contacted with the inner wall of the fuel oil tank and is condensed on the wall of the fuel oil tank, and then the moisture content is accumulated and slides into the fuel oil, because the density of the water is greater than that of the fuel oil, the water is sunk to the bottom of the fuel oil tank, the fuel oil tank is required to be cleaned regularly, and, therefore, the four-rotor intelligent unmanned aerial vehicle is provided.
Disclosure of Invention
The invention provides a four-rotor type intelligent unmanned aerial vehicle, which has the advantages of effectively improving the flying stability of the four-rotor type intelligent unmanned aerial vehicle, saving the time and cost for cleaning deposited water in fuel oil by workers and improving the reaction efficiency of the four-rotor type intelligent unmanned aerial vehicle for adjusting lift force, and solves the problems that the existing four-rotor type intelligent unmanned aerial vehicle is complicated in mechanical structure for adjusting a propeller pitch, the weight of the four-rotor type intelligent unmanned aerial vehicle is increased, the load capacity of the four-rotor type intelligent unmanned aerial vehicle is reduced, and the existing rotor wing adjusting structure of the four-rotor type intelligent unmanned aerial vehicle is straight, so that when the four-rotor type intelligent unmanned aerial vehicle moves transversely, the rotor wing adjusting structure is relatively large in resistance of air, and the effect of adjusting the lift force is influenced; and for the oil tank carried by the existing oil-dynamic and oil-electric hybrid four-rotor unmanned aerial vehicle, when the fuel oil in the oil tank is consumed, a gap exists between fuel oil in the oil tank and an inner cavity of the oil tank, when the rotor unmanned aerial vehicle carries out necessary flying action in the flying process, the fuel oil in the oil tank of the four-rotor unmanned aerial vehicle can shake, the stability of the four-rotor unmanned aerial vehicle is reduced due to the reaction force between the fuel oil and the oil tank, and when the fuel oil in the oil tank is consumed, the gap between the fuel oil and the top of the inner cavity of the oil tank is increased, namely, the content of the air in the oil tank is increased, then the moisture contained in the air is condensed on the wall of the oil tank when touching the inner wall of the oil tank and then slides into the fuel along with the gathering of the moisture content, because the density of water is greater than that of fuel oil, which in turn causes water to sink and float at the bottom of the fuel tank, the fuel tank needs to be cleaned periodically, increasing the maintenance time and cost for the user.
In order to achieve the above purpose, the invention provides the following technical scheme to realize: a four-rotor intelligent unmanned aerial vehicle comprises a vehicle body, wherein two connecting rods are fixedly connected to the left side and the right side of the vehicle body, the two connecting rods positioned on the same side of the vehicle body are in a group, the two groups of connecting rods are mutually symmetrical by taking a central line of the vertical direction of the vehicle body as a symmetrical axis, a vertical block is arranged at the top of each connecting rod, an oil tank is fixedly arranged in the vehicle body, an oil transportation device is arranged in the middle of the bottom of an inner cavity of the oil tank and comprises a communicating pipe, an annular block is movably sleeved on the outer surface of the communicating pipe, the top of the annular block is convex, the outer surface of the annular block is movably connected with the inner surface of the oil tank, an annular floating plate is movably connected to the top of the annular block on the outer surface of the communicating pipe, the bottom of the annular floating plate is fixedly connected, the inside of the floating ring is provided with an oil through hole.
Optionally, the bottom of communicating pipe link up with the bottom of oil tank inner chamber mutually, the quantity of oil tank is two, two the oil tank uses the central line of the vertical direction of fuselage as the symmetry axis mutual symmetry, the top fixedly connected with of fuselage advances oil pipe, advance oil pipe's bottom and run through fuselage and oil tank in proper order and link up mutually with the top of communicating pipe, advance oil pipe's bottom and set up two bifurcated pipes, advance oil pipe's shape and be down "Y" form, advance two base pipes of oil pipe and link up mutually with the top that corresponds two inside communicating pipes of oil tank.
Optionally, a motor is fixedly mounted on the left side of the upper surface of the connecting rod, a vertical block is arranged at the top of the connecting rod, the bottom end of the vertical block is fixedly connected with an output shaft of the motor, a variable pitch driving device is fixedly connected to the top of the vertical block, and a regulating device is fixedly connected to the left side and the right side of the variable pitch driving device.
Optionally, the regulation and control device comprises a rectangular plate, the inside of the rectangular plate is in threaded connection with the right side of the pitch-variable driving device through a bolt, a U-shaped fixing plate is sleeved in the inside of the rectangular plate in a movable mode, the left side of the U-shaped fixing plate is in contact with the right side of the pitch-variable driving device, a rebound strip is sleeved in the inside of the rectangular plate in a movable mode, and the left end of the rebound strip is fixedly connected with the top of the right side of the pitch-variable driving device.
Optionally, the right end of the rebound strip is fixedly connected with the bottom of the left side of a U-shaped fixed plate inside the rectangular plate, the right side of the U-shaped fixed plate penetrates through the rectangular plate and extends to the outer side of the rectangular plate, the inside of the U-shaped fixed plate is connected with the wing through a bolt thread, and the front side of the U-shaped fixed plate is fixedly connected with a distance adjusting device through an annular sleeve.
Optionally, the roll adjustment device is including the regulation and control crown plate, the internal surface of regulation and control crown plate and the surface looks joint of perpendicular piece, the equal fixedly connected with transfer line in the left and right sides of regulation and control crown plate, two the top of transfer line cup joints with the positive middle part activity of two annular cover respectively, the horizontal groove has been seted up at the positive middle part of regulation and control crown plate, the joint piece has been cup jointed in the inside activity of regulation and control crown plate horizontal groove.
Optionally, the front surface of the clamping block penetrates through the regulation ring plate and extends to the outer side of the regulation ring plate, a linkage rod is movably sleeved on the outer surface of the clamping block, the top of the linkage rod is fixedly connected with the bottom of the variable pitch driving device through a fixed cylinder, the fixed cylinder and the linkage rod are shaped like an inward-concave arc, and the distance from the connecting point of the linkage rod and the fixed cylinder to the vertical block is two fifths of the distance length from the bottom end of the linkage rod to the vertical block.
The invention provides a four-rotor intelligent unmanned aerial vehicle, which has the following beneficial effects:
1. this four rotor formula intelligence unmanned aerial vehicle, be provided with oil transportation device and annular piece through the inside at the oil tank, oil liquid level float process down when fuel consumption in the oil tank, the annular piece all pastes with the ring that floats and float in fluid surface lapse, effectively avoided when wing formula intelligence unmanned aerial vehicle carries out necessary flight mode, cause fluid to vibrate in the oil tank inside and cause the stability of unmanned aerial vehicle flight, effectively improve the stability of wing formula intelligence unmanned aerial vehicle flight, the top through annular piece and oil through hole is protruding form simultaneously, and annular piece and oil tank inner wall in close contact with, avoid aqueous vapor in the air to mix in the fuel, the time and the cost of ponding sink in the staff's washing fuel have been saved.
2. This four rotor formula intelligence unmanned aerial vehicle, through perpendicular piece, the cooperation between roll adjustment device and the regulation and control device, and the shape of fixed section of thick bamboo and trace is the arc form to the indent, swing joint between the two, be convenient for then simplify the process of adjusting wing pitch, and because of fixed section of thick bamboo and trace are to one side indent of perpendicular piece, when the process of adjusting wing pitch, reduce blockking of air current between fixed section of thick bamboo and the trace, improve four rotor formula intelligence unmanned aerial vehicle and adjust the reaction efficiency of lift.
Drawings
FIG. 1 is a schematic front view of the present invention;
FIG. 2 is an enlarged schematic view of an airfoil according to the present invention;
FIG. 3 is an enlarged view of the structure at A in the present invention;
FIG. 4 is an enlarged view of the structure at B in FIG. 2;
FIG. 5 is a schematic side view of a pitch drive apparatus according to the present invention;
fig. 6 is a schematic side view of the control ring plate of fig. 5.
In the figure: 1. a body; 2. a connecting rod; 3. a vertical block; 4. an annular sleeve; 5. a distance adjusting device; 51. a regulating ring plate; 52. a transmission rod; 53. a linkage rod; 54. a fixed cylinder; 55. a clamping block; 6. an airfoil; 7. a regulating device; 71. a rectangular plate; 72. a resilient strip; 73. a U-shaped fixing plate; 8. an oil inlet pipe; 9. an oil tank; 10. an oil transfer device; 101. a communicating pipe; 102. an annular floating plate; 103. a floating ring; 104. an oil through hole; 11. a ring block; 12. a pitch drive device.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Referring to fig. 1-6, a four-rotor intelligent unmanned aerial vehicle comprises a body 1, two connecting rods 2 are fixedly connected to the left and right sides of the body 1, the two connecting rods 2 located on the same side of the body 1 are a group, the two groups of connecting rods 2 are mutually symmetrical with the center line of the body 1 in the vertical direction as a symmetry axis, a vertical block 3 is arranged at the top of each connecting rod 2, an oil tank 9 is fixedly installed inside the body 1, an oil transportation device 10 is arranged in the middle of the bottom of the inner cavity of the oil tank 9, the oil transportation device 10 comprises a communicating pipe 101, an annular block 11 is movably sleeved on the outer surface of the communicating pipe 101, the top of the annular block 11 is convex, the outer surface of the annular block 11 is movably connected with the inner surface of the oil tank 9, an annular floating plate 102 is movably connected to the top of the annular block 11 on the outer surface of the communicating pipe 101, and the bottom of the annular, communicating pipe 101's inside movable mounting has floating ring 103, floating ring 103's inside has been seted up oil through hole 104, is protruding form through the top of annular piece 11 and oil through hole 104, and annular piece 11 and oil tank inner wall in close contact with, avoids the aqueous vapor in the air to mix in the fuel, has saved time and the cost that the staff washed the ponding that sinks in the fuel.
Wherein, the bottom of the communicating pipe 101 is communicated with the bottom of the inner cavity of the oil tank 9, the number of the oil tanks 9 is two, the two oil tanks 9 are mutually symmetrical by taking the central line of the vertical direction of the body 1 as a symmetrical axis, the top of the body 1 is fixedly connected with an oil inlet pipe 8, the bottom of the oil inlet pipe 8 sequentially penetrates through the body 1 and the oil tanks 9 and is communicated with the top of the communicating pipe 101, the bottom of the oil inlet pipe 8 is provided with two branch pipes, the shape of the oil inlet pipe 8 is inverted Y-shaped, the two bottom pipes of the oil inlet pipe 8 are communicated with the top of the communicating pipe 101 corresponding to the inside of the two oil tanks 9, when fuel oil in the oil tank is consumed, the oil level floats downwards, the annular block 11 and the floating ring 103 are attached to float on the surface of the oil and slide downwards, thereby effectively avoiding the stability of the unmanned aerial vehicle caused by the oscillation of the oil inside the oil tanks when the, effectively improve the stability of wing formula intelligence unmanned aerial vehicle flight.
The left side of the upper surface of the connecting rod 2 is fixedly provided with a motor, the top of the connecting rod 2 is provided with a vertical block 3, the bottom end of the vertical block 3 is fixedly connected with an output shaft of the motor, the top of the vertical block 3 is fixedly connected with a variable pitch driving device 12, and the left side and the right side of the variable pitch driving device 12 are both fixedly connected with a regulating device 7, so that the process of regulating the pitch of the wing 6 is facilitated, the identity of the regulating device is kept, and the deviation in the regulating process is avoided.
The regulation and control device 7 comprises a rectangular plate 71, the inside of the rectangular plate 71 is in threaded connection with the right side of the variable pitch driving device 12 through bolts, a U-shaped fixing plate 73 is movably sleeved inside the rectangular plate 71, the left side of the U-shaped fixing plate 73 is in contact with the right side of the variable pitch driving device 12, a rebound strip 72 is movably sleeved inside the U-shaped fixing plate 73, the left end of the rebound strip 72 is fixedly connected with the top of the right side of the variable pitch driving device 12, and the rebound strip 72 is used for regulating and controlling the pitch of the wing 6 to the original position again after the lift force regulation time is completed.
Wherein, the right-hand member of bounce strip 72 and the left side bottom fixed connection who is located the inside U-shaped fixed plate 73 of rectangular plate 71, the right side of U-shaped fixed plate 73 runs through rectangular plate 71 and extends to the outside of rectangular plate 71, there is wing 6 inside of U-shaped fixed plate 73 through bolt threaded connection, 4 fixedly connected with roll adjustment device 5 are passed through to the front of U-shaped fixed plate 73, are convenient for protect the arm of wing 6 through U-shaped fixed plate 73, and the corner of U-shaped fixed plate 73 sets up the arc angle to one hundred twenty degrees, are favorable to reducing the resistance of air current to U-shaped fixed plate 73.
Wherein, roll adjustment device 5 is including regulation and control ring plate 51, the internal surface of regulation and control ring plate 51 and the surface looks joint of perpendicular piece 3, the equal fixedly connected with transfer line 52 in both sides about regulation and control ring plate 51, two the top of transfer line 52 is cup jointed with two annular cover 4 positive middle part activities respectively, the transverse groove has been seted up at the positive middle part of regulation and control ring plate 51, the inside activity in regulation and control ring plate 51 transverse groove has cup jointed joint piece 55, utilizes the inside swing joint of joint piece 55 and transverse groove, is convenient for through the position of adjusting trace 53, prevents to take place the contact between regulation and control ring plate 51 and the trace 53, and restriction regulation and control ring plate 51 horizontal direction takes place to remove simultaneously, has improved its accuracy nature of adjusting the pitch.
Wherein the front surface of the clamping block 55 penetrates through the regulating ring plate 51 and extends to the outer side of the regulating ring plate 51, the outer surface of the clamping block 55 is movably sleeved with a linkage rod 53, the top of the linkage rod 53 is fixedly connected with the bottom of the variable pitch driving device 12 through a fixed cylinder 54, the shape of the fixed cylinder 54 and the linkage rod 53 is an inward concave arc shape, the distance from the connecting point of the linkage rod 53 and the fixed cylinder 54 to the vertical block 3 is two fifths of the distance from the bottom end of the linkage rod 53 to the vertical block 3, the shape of the fixed cylinder 54 and the linkage rod 53 is an inward concave arc shape, the two are movably connected, so that the process of adjusting the pitch of the wing 6 is simplified, and because the fixed cylinder 54 and the linkage rod 53 are concave towards one side of the vertical block 3, when the pitch of the wing 6 is adjusted, the blockage of airflow between the fixed cylinder 54 and the linkage rod 53 is reduced, and the reaction efficiency of the four-rotor intelligent unmanned aerial vehicle for adjusting the lift force is improved.
Working steps, firstly, a worker opens an oil cover at the top of an oil inlet pipe 8, fuel oil flows into two corresponding oil tanks 9 through the oil inlet pipe 8, the fuel oil flows into the communicating pipe 101 and passes through the oil through hole 104 on the floating ring 103 to slide into the oil tanks 9, because the fuel oil flows into the oil tanks 9 through the bottom of the oil tanks 9, then the annular block 11 is driven to float upwards along with the rising of the liquid level of the fuel oil, at the moment, the space formed by the annular block 11 and the oil tanks 9 is filled with the fuel oil, the contact between water vapor in the air and the fuel oil is prevented, the shape of the fixed cylinder 54 and the linkage rod 53 is an inward concave arc shape, the fixed cylinder 54 and the linkage rod are movably connected with each other, then, the process of adjusting the pitch of the wing 6 is simplified, the fixed cylinder 54 and the linkage rod 53 are concave towards one side of the vertical block 3, when the pitch adjusting device 5 is driven by the vertical block 3, the blocking of the airflow between the fixed cylinder 54 and the linkage 53 is reduced, and the efficiency of adjusting the lift force is improved.
It is noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (7)
1. The utility model provides a four rotor formula intelligent unmanned aerial vehicle, includes fuselage (1), its characterized in that: the left side and the right side of the machine body (1) are fixedly connected with two connecting rods (2), the two connecting rods (2) which are positioned on the same side of the machine body (1) are a group, the two connecting rods (2) are two groups of mutually symmetrical by taking the central line of the vertical direction of the machine body (1) as the symmetrical axis, the top of each connecting rod (2) is provided with a vertical block (3), the inside of the machine body (1) is fixedly provided with an oil tank (9), the middle of the bottom of the inner cavity of the oil tank (9) is provided with an oil conveying device (10), the oil conveying device (10) comprises a communicating pipe (101), the outer surface of the communicating pipe (101) is movably sleeved with an annular block (11), the top of the annular block (11) is convex, the outer surface of the annular block (11) is movably connected with the inner surface of the oil tank (9), the outer surface of the communicating pipe (101), the bottom of the annular floating plate (102) is fixedly connected with the top of the annular block (11), a floating ring (103) is movably mounted inside the communicating pipe (101), and an oil through hole (104) is formed inside the floating ring (103).
2. The quad-rotor intelligent drone of claim 1, characterized in that: the bottom of communicating pipe (101) link up mutually with the bottom of oil tank (9) inner chamber, the quantity of oil tank (9) is two, two oil tank (9) use the central line of fuselage (1) vertical direction as the symmetry axis mutual symmetry, the top fixedly connected with of fuselage (1) advances oil pipe (8), the bottom that advances oil pipe (8) runs through fuselage (1) and oil tank (9) in proper order and link up mutually with the top of communicating pipe (101), the bottom that advances oil pipe (8) sets up two Y forked pipes, the shape that advances oil pipe (8) is down "Y" form, two bottom pipes that advance oil pipe (8) link up mutually with the top that corresponds two inside communicating pipe (101) of oil tank (9).
3. The quad-rotor intelligent drone of claim 1, characterized in that: the left side fixed mounting of connecting rod (2) upper surface has the motor, the top of connecting rod (2) is provided with perpendicular piece (3), the bottom of perpendicular piece (3) and the output shaft fixed connection of motor, the top fixedly connected with of perpendicular piece (3) becomes oar drive arrangement (12), the equal fixedly connected with regulation and control device (7) of the left and right sides that becomes oar drive arrangement (12).
4. The quad-rotor intelligent drone of claim 3, characterized in that: the adjusting and controlling device (7) is characterized by comprising a rectangular plate (71), the inside of the rectangular plate (71) is in threaded connection with the right side of the variable pitch driving device (12) through bolts, a U-shaped fixing plate (73) is sleeved in the inside of the rectangular plate (71), the left side of the U-shaped fixing plate (73) is in contact with the right side of the variable pitch driving device (12), a rebound strip (72) is sleeved in the inside of the rectangular plate (71) through the U-shaped fixing plate (73), and the left end of the rebound strip (72) is fixedly connected with the top of the right side of the variable pitch driving device (12).
5. The quad-rotor intelligent drone of claim 4, characterized in that: the right-hand member of resilience strip (72) and the left side bottom fixed connection who is located inside U-shaped fixed plate (73) of rectangular plate (71), the right side of U-shaped fixed plate (73) runs through rectangular plate (71) and extends to the outside of rectangular plate (71), there are wing (6) in the inside of U-shaped fixed plate (73) through bolt threaded connection, there is roll adjustment device (5) in the front of U-shaped fixed plate (73) through annular cover (4) fixedly connected with.
6. The quad-rotor intelligent drone of claim 5, characterized in that: roll adjustment device (5) are including regulation and control crown plate (51), the internal surface of regulation and control crown plate (51) and the surface looks joint of perpendicular piece (3), the equal fixedly connected with transfer line (52) of the left and right sides of regulation and control crown plate (51), two the top of transfer line (52) cup joints with two annular cover (4) positive middle part activities respectively, the horizontal groove has been seted up at the positive middle part of regulation and control crown plate (51), joint piece (55) have been cup jointed in the inside activity of regulation and control crown plate (51) horizontal groove.
7. The quad-rotor intelligent drone of claim 6, wherein: the front of the clamping block (55) penetrates through the regulation and control annular plate (51) and extends to the outer side of the regulation and control annular plate (51), a linkage rod (53) is movably sleeved on the outer surface of the clamping block (55), the top of the linkage rod (53) is fixedly connected with the bottom of the variable-pitch driving device (12) through a fixed cylinder (54), the fixed cylinder (54) and the linkage rod (53) are in an inwards-concave arc shape, and the distance from the connecting point of the linkage rod (53) and the fixed cylinder (54) to the vertical block (3) is two fifths of the distance between the bottom end of the linkage rod (53) and the vertical block (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN202010731072.9A CN111846255A (en) | 2020-07-27 | 2020-07-27 | Four-rotor intelligent unmanned aerial vehicle |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202010731072.9A CN111846255A (en) | 2020-07-27 | 2020-07-27 | Four-rotor intelligent unmanned aerial vehicle |
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| CN111846255A true CN111846255A (en) | 2020-10-30 |
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| CN202010731072.9A Pending CN111846255A (en) | 2020-07-27 | 2020-07-27 | Four-rotor intelligent unmanned aerial vehicle |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
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| CN114384933A (en) * | 2022-01-14 | 2022-04-22 | 广东电网能源发展有限公司 | Overhead line unmanned aerial vehicle electrified water washing control system and method and storage medium |
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