CN112498686B - Microminiature coaxial double-oar unmanned aerial vehicle - Google Patents
Microminiature coaxial double-oar unmanned aerial vehicle Download PDFInfo
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- CN112498686B CN112498686B CN202011540180.4A CN202011540180A CN112498686B CN 112498686 B CN112498686 B CN 112498686B CN 202011540180 A CN202011540180 A CN 202011540180A CN 112498686 B CN112498686 B CN 112498686B
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- aerial vehicle
- unmanned aerial
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- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims description 9
- 238000013016 damping Methods 0.000 claims description 9
- 230000003068 static effect Effects 0.000 claims description 7
- 241000227287 Elliottia pyroliflora Species 0.000 claims description 3
- 238000010248 power generation Methods 0.000 claims 1
- 238000005516 engineering process Methods 0.000 abstract description 7
- 230000035939 shock Effects 0.000 abstract description 7
- 238000010521 absorption reaction Methods 0.000 abstract description 6
- 238000000034 method Methods 0.000 abstract description 5
- 238000010586 diagram Methods 0.000 description 5
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 4
- 229910052802 copper Inorganic materials 0.000 description 4
- 239000010949 copper Substances 0.000 description 4
- 238000009434 installation Methods 0.000 description 4
- 238000006073 displacement reaction Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 125000004122 cyclic group Chemical group 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 230000000737 periodic effect Effects 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
-
- 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
- B64C27/10—Helicopters with two or more rotors arranged coaxially
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/12—Rotor drives
- B64C27/14—Direct drive between power plant and rotor hub
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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
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/20—Rotors; Rotor supports
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Arrangement Or Mounting Of Propulsion Units For Vehicles (AREA)
Abstract
The invention provides a miniature coaxial double-oar unmanned aerial vehicle, which comprises a main shaft, a motor, a battery, a period torque changing mechanism, a total distance changing mechanism and a shock absorption hanging frame mechanism, wherein the motor, a power supply system, the period torque changing mechanism, the total distance changing mechanism and the shock absorption hanging frame mechanism are all arranged on the main shaft, a main shaft positioning hole I, a main shaft positioning hole II, a main shaft line passing hole III, a limiting groove I and a limiting groove II are arranged on the main shaft, the miniature coaxial double-oar unmanned aerial vehicle can reduce the transverse width of the miniature coaxial double-oar unmanned aerial vehicle, so that the resistance of air borne by the miniature coaxial double-oar unmanned aerial vehicle in the flying process is reduced, the flying speed of the miniature coaxial double-oar unmanned aerial vehicle is improved, and the miniature coaxial double-oar unmanned aerial vehicle has the outstanding characteristics of small volume, difficulty in being found, good concealment, light weight, low cost, strong function, convenience in carrying, simplicity in operation and the like, can realize lifting, follow-flying and high dynamic attack, and is convenient to construct a novel combat system based on miniature high-integration technology of miniature unmanned aerial vehicle technology and airborne equipment.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicle equipment, in particular to a microminiature coaxial double-oar unmanned aerial vehicle.
Background
The unmanned aerial vehicle has the characteristics of simple operation and use and capability of meeting the use under various environments, and is increasingly applied to the industries of military, industry, social life and the like, wherein the coaxial double-oar unmanned aerial vehicle has better air property and lower energy consumption, is popular, the invention patent with the patent application number of CN202010104669.0 discloses a vector coaxial double-oar unmanned aerial vehicle, and the existing coaxial double-oar unmanned aerial vehicle basically has the advantages of simple operation, high flying speed, high flying flexibility, long flying distance, long service life and the like, can meet the use requirements of entertainment, business, agriculture, military and the like, but for the existing coaxial double-oar unmanned aerial vehicle, on one hand, the existing unmanned aerial vehicle has larger volume, is easy to be found, is unfavorable for concealment, has large weight and is unfavorable for carrying, and is unfavorable for large-scale combat use, and on the other hand, has slower flying speed, and needs personnel to lift the unmanned aerial vehicle after supporting or by means of a platform, and is unfavorable for flexible use.
Disclosure of Invention
Aiming at the defects of the prior art, the invention aims to provide a microminiature coaxial double-oar unmanned aerial vehicle so as to solve the problems in the prior art.
In order to achieve the above object, the present invention is realized by the following technical scheme: the miniature coaxial double-oar unmanned aerial vehicle comprises a main shaft, a motor, a battery, a period distance-changing mechanism, a total distance-changing mechanism and a shock absorption hanging frame mechanism, wherein the motor, a power supply system, the period distance-changing mechanism, the total distance-changing mechanism and the shock absorption hanging frame mechanism are all arranged on the main shaft, a first main shaft positioning hole, a second main shaft positioning hole, a main shaft wire passing hole, a third main shaft positioning hole, a first limit groove and a second limit groove are arranged on the main shaft, a propeller hub mounting threaded hole is arranged on the motor, a propeller hub is arranged at the top and the bottom of the motor, the propeller hub is arranged on the threaded hole through a rotating shaft, One side of the propeller hub is provided with a propeller and a lower propeller, the propeller and the lower propeller are all installed on the propeller hub through blade mounting holes, the bottom of a battery is provided with a battery quick-release fixing piece, a battery connecting fixing piece is welded on the battery quick-release fixing piece, a battery connecting fixing piece positioning hole and a fixing hole are formed in the battery connecting fixing piece, a battery fixing end is installed on the battery, a chute is formed in the battery fixing end, a slideway is integrally formed in the battery quick-release fixing piece, the chute is matched with the slideway, a lock hole is formed in the battery quick-release fixing piece, a clamping groove is formed in the inner side of the battery fixing end, the clamping groove is connected with the lock hole through a locking bolt, the utility model discloses a steering engine, including battery quick detach mounting, cycle displacement mechanism, locking bolt, steering wheel, horizontal pole and tilting tray guide piece, the cycle displacement mechanism includes upper portion and lower part, upper portion includes steering wheel support and steering wheel, the steering wheel is installed on last steering wheel support, go up steering wheel support locking in the outside side of main shaft spacing groove two, go up steering wheel support and pass through the bolt and install on main shaft locating hole two, steering wheel rocking arm is installed to the bottom of steering wheel, install horizontal pole and tilting tray guide piece on the last steering wheel support, the tilting tray guide piece is installed in the bottom of horizontal pole, the guide slot has been seted up on the tilting tray guide piece, the lower part includes tilting tray movable tray, tilting tray quiet dish, The steering engine rocker arm is provided with a first ball head, the tilting disk movable disk is provided with a second ball head and a third ball head, the first ball head is connected with the second ball head and the third ball head through a second connecting rod respectively, one side of the third ball head is provided with an extension section, one end of the extension section is clamped at the inner side of a guide groove, a rotor hub at the top of the motor is connected with a tilting disk static disk through a first connecting rod, the total variable pitch mechanism comprises a lower-layer movable disk, a sliding shaft sleeve, a variable pitch shifting fork, a shifting fork front rotating shaft and a shifting fork connecting rod, the sliding shaft sleeve is sleeved on the outer side of a main shaft, a rotor hub at the bottom of the motor is connected with the lower-layer movable disk through a torque arm, and the damping hanging rack mechanism comprises a base support frame, The base support is arranged at the bottom of the lower-layer movable disc, the base support is fixedly connected with a main shaft positioning hole on a main shaft through a positioning hole, a lower steering engine connecting rod is arranged at the bottom of the base support, a connecting rod mounting hole is formed in the base support, a shifting fork connecting rod is arranged at the top of the base support, the base support is connected with the hanger through the damping ball, a flight control device is arranged at the bottom of the base support, the flight control device is arranged on the hanger through a bolt, a mounting hole is formed in the hanger, and the flight control device is arranged at the bottom of the hanger through a bolt.
As a preferred embodiment of the present invention, the battery is connected to the motor by a wire, which is arranged inside the spindle through the spindle via hole.
As a preferred embodiment of the present invention, the fixing holes are disposed at both sides of the battery connection fixing member positioning hole, the fixing hole is fixed with the upper limit groove one by a bolt, and the battery connection fixing member positioning hole is mounted on the main shaft positioning hole one by a bolt.
As a preferable implementation mode of the invention, the lower movable disk is arranged at the bottom of the motor, a copper sleeve bearing mounting section is integrally formed on the sliding shaft sleeve, and the lower movable disk is mounted on the copper sleeve bearing mounting section through a bearing.
As a preferred implementation mode of the invention, the battery is provided with a battery fixing end, the battery fixing end is provided with a chute, the battery quick-release fixing piece is integrally formed with a slideway, and the chute is matched with the slideway.
As a preferable implementation mode of the invention, the thin-wall bearing and the knuckle bearing are both sleeved on the outer side of the main shaft, the knuckle bearing is arranged on the top of the thin-wall bearing, the movable disc of the tilting disk is sleeved on the outer side of the knuckle bearing, and the static disc of the tilting disk is sleeved on the outer side of the thin-wall bearing.
As a preferred implementation mode of the invention, one end of the variable-pitch shifting fork is provided with a shifting fork threaded hole, the sliding shaft sleeve is provided with a through hole, and the shifting fork threaded hole is connected with the through hole through a shifting fork front rotating shaft.
As a preferred embodiment of the invention, the front rotating shaft of the shifting fork comprises a polish rod part and a threaded part, wherein the threaded part is matched with the threaded hole of the shifting fork, and the polish rod part is clamped at the inner side of the through hole.
As a preferred implementation mode of the invention, the middle part of the variable-pitch shifting fork is arranged on a shifting fork connecting rod through a rotating shaft, the bottom of the base bracket is provided with a lower steering engine connecting rod, and the other end of the variable-pitch shifting fork is connected with the lower steering engine connecting rod through a connecting rod III.
As a preferred embodiment of the invention, the bottom of the base bracket is provided with a lower steering engine, and the lower steering engine is arranged on the base bracket through a steering engine mounting hole.
Compared with the prior art, the invention has the beneficial effects that:
1. when the miniature coaxial double-oar unmanned aerial vehicle is used, all parts of the unmanned aerial vehicle are connected in series through one main shaft, the whole unmanned aerial vehicle is distributed through the main shaft, so that the transverse width of the unmanned aerial vehicle is reduced, the resistance of air received by the unmanned aerial vehicle in the flying process is reduced, the flying speed of the unmanned aerial vehicle is improved, and the unmanned aerial vehicle has the outstanding characteristics of small size, difficulty in finding out, good concealment, light weight, low cost, strong function, convenience in carrying, simplicity in operation and the like.
2. When the miniature coaxial double-oar unmanned aerial vehicle is used, the miniature coaxial double-oar design is adopted, two pairs of rotary wings are coaxially installed and reversely rotated, through battery driving, vertical lifting, flying following and high dynamic attack are realized, a novel combat system based on miniature highly integrated technology of miniature unmanned aerial vehicle technology and airborne equipment is constructed, the miniature unmanned aerial vehicle has vertical lifting capability, and can be hidden during combat, and after the miniature unmanned aerial vehicle is controlled to take off by personnel, target unfolding search or other tasks are performed.
Drawings
FIG. 1 is a schematic diagram of a portable coaxial double-oar unmanned aerial vehicle;
Fig. 2 is a schematic diagram of a main shaft structure of a portable coaxial double-oar unmanned aerial vehicle according to the present invention;
FIG. 3 is a schematic view of a portable coaxial double-paddle unmanned aerial vehicle motor of the present invention;
FIG. 4 is a schematic illustration of a portable coaxial dual-propeller unmanned hub assembly in accordance with the present invention;
FIG. 5 is a schematic diagram of an assembly of a portable coaxial dual-paddle unmanned aerial vehicle battery mounting mechanism according to the present invention;
FIG. 6 is an assembly schematic diagram of a portable coaxial dual-propeller unmanned aerial vehicle cyclic pitch-varying mechanism according to the present invention;
FIG. 7 is an assembly schematic diagram of a variable collective pitch mechanism of a portable coaxial double-oar unmanned aerial vehicle of the present invention;
FIG. 8 is a schematic view of a lower movable disk of a portable coaxial double-oar unmanned aerial vehicle;
FIG. 9 is a schematic view of a sliding sleeve of a portable coaxial dual-paddle unmanned aerial vehicle according to the present invention;
FIG. 10 is a schematic view of a front shaft of a fork of a portable coaxial dual-propeller unmanned aerial vehicle;
FIG. 11 is a schematic view of a portable coaxial double-oar unmanned aerial vehicle range shift fork according to the present invention;
FIG. 12 is a schematic illustration of a portable coaxial dual-paddle unmanned aerial vehicle fork linkage;
FIG. 13 is a schematic view of a shock absorbing pylon mechanism of a portable coaxial dual-oar unmanned aerial vehicle according to the present invention;
FIG. 14 is a schematic view of a portable coaxial double-oar unmanned aerial vehicle base support of the present invention;
FIG. 15 is a schematic view of a portable coaxial dual-paddle unmanned aerial vehicle pylon according to the present invention;
FIG. 16 is a schematic view of a portable coaxial dual-paddle unmanned aerial vehicle battery of the present invention;
In the figure: 1. a first main shaft positioning hole; 2. a main shaft positioning hole II; 3. a spindle wire passing hole; 4. a main shaft positioning hole III; 5. a first limit groove; 6. a limiting groove II; 7. a motor; 8. the propeller hub is provided with a threaded hole; 9. a hub; 10. a first connecting rod; 11. blade mounting holes; 12. a rotation shaft; 13. locking the bolt; 14. clamping springs; 15. a spring; 16. a battery quick-release fixing piece; 17. a lock hole; 18. a slideway; 19. a battery connection fixing member; 20. a battery connecting fixing piece positioning hole; 21. a fixing hole; 22. an upper steering engine bracket; 23. steering engine; 24. steering engine rocker arm; 25. mounting a cross bar; 26. a swashplate guide; 27. a guide groove; 28. a tilting plate movable plate; 29. a tilting disk stationary disk; 30. a knuckle bearing; 31. a thin-wall bearing; 32. a second connecting rod; 33. a ball head I; 34. a second ball head; 35. a ball head III; 36. an extension section; 37. a propeller; 38. a lower propeller; 39. a lower movable disk; 40. a sliding sleeve; 41. a front rotating shaft of the shifting fork; 42. a variable-pitch shifting fork; 43. a fork connecting rod; 44. a connecting rod III; 45. a lower steering engine connecting rod; 46. a base bracket; 47. a torque arm; 48. a polish rod portion; 49. a threaded portion; 50. a copper bush bearing mounting section; 51. a through hole; 52. positioning holes; 53. a lower steering engine mounting hole; 54. a shifting fork threaded hole; 55. a battery; 56. a clamping groove; 57. a chute; 58. a battery fixing end; 59. a hanging rack; 60. a lower steering engine; 61. a shock-absorbing ball; 62. and (5) flight control.
Detailed Description
The invention is further described in connection with the following detailed description, in order to make the technical means, the creation characteristics, the achievement of the purpose and the effect of the invention easy to understand.
Referring to fig. 1 to 16, the present invention provides a technical solution: the miniature coaxial double-oar unmanned aerial vehicle comprises a main shaft, a motor 7, a battery 55, a period distance-changing mechanism, a total distance-changing mechanism and a shock absorption hanging frame mechanism, wherein the motor 7, a power supply system, the period distance-changing mechanism, the total distance-changing mechanism and the shock absorption hanging frame mechanism are all arranged on the main shaft, a main shaft positioning hole I1, a main shaft positioning hole II 2, a main shaft wire passing hole 3, a main shaft positioning hole III 4, a limiting groove I5 and a limiting groove II 6 are arranged on the main shaft, a propeller hub installation threaded hole 8 is arranged on the motor 7, a propeller hub 9 is arranged at the top and the bottom of the motor 7, the propeller hub 9 is arranged on the threaded hole 8 through a rotating shaft 12, a propeller 37 and a lower propeller 38 are arranged on one side of the propeller hub 9, the propeller 37 and the lower propeller 38 are both arranged on the propeller hub 9 through a blade mounting hole 11, a battery quick-release fixing piece 16 is arranged at the bottom of a battery 55, a battery connecting fixing piece 19 is welded on the battery quick-release fixing piece 16, a battery connecting fixing piece positioning hole 20 and a fixing hole 21 are formed in the battery connecting fixing piece 19, a battery fixing end 58 is arranged on the battery 55, a chute 57 is formed in the battery fixing end 58, a slideway 18 is integrally formed on the battery quick-release fixing piece 16, the chute 57 is matched with the slideway 18, The battery quick-release fixing piece 16 is provided with a lock hole 17, the inner side of the battery fixing end 58 is provided with a clamping groove 56, the clamping groove 56 is connected with the lock hole 17 through a locking bolt 13, two ends of the locking bolt 13 are fixed on the battery quick-release fixing piece 16 through a spring 15 and a clamp spring 14, the periodic distance-changing mechanism comprises an upper part and a lower part, the upper part comprises an upper steering engine bracket 22 and a steering engine 23, the steering engine 23 is arranged on the upper steering engine bracket 22, the upper steering engine bracket 22 is locked on the outer side of a main shaft limiting groove II 6, the upper steering engine bracket 22 is arranged on a main shaft positioning hole II 2 through a bolt, the steering engine rocker arm 24 is arranged at the bottom of the steering engine 23, The upper steering engine bracket 22 is provided with a cross rod 25 and a swashplate guide piece 26, the swashplate guide piece 26 is arranged at the bottom of the cross rod 25, the swashplate guide piece 26 is provided with a guide groove 27, the lower part comprises a swashplate movable disc 28, a swashplate static disc 29, a thin-wall bearing 31 and a knuckle bearing 30, the steering engine rocker 24 is provided with a ball head one 33, the swashplate movable disc 28 is provided with a ball head two 34 and a ball head three 35, the ball head one 33 is respectively connected with the ball head two 34 and the ball head three 35 through a connecting rod two 32, one side of the ball head three 35 is provided with an extension section 36, one end of the extension section 36 is clamped at the inner side of the guide groove 27, The hub 9 at the top of the motor 7 is connected with the tilting disk static disk 29 through a first connecting rod 10, the variable-total-distance mechanism comprises a lower-layer dynamic disk 39, a sliding shaft sleeve 40, a variable-distance shifting fork 42, a shifting fork front rotating shaft 41 and a shifting fork connecting rod 43, the sliding shaft sleeve 40 is sleeved on the outer side of a main shaft, the hub 9 at the bottom of the motor 7 is connected with the lower-layer dynamic disk 39 through a torque arm 47, the damping hanging frame mechanism comprises a base bracket 46, a hanging frame 59 and a damping ball 61, the base bracket 46 is arranged at the bottom of the lower-layer dynamic disk 39, the base bracket 46 is fixedly connected with a main shaft positioning hole three 4 on the main shaft through a positioning hole 52, The bottom of base support 46 is installed down steering wheel connecting rod 45, base support 46 is provided with connecting rod mounting hole 64, and shift fork connecting rod 43 is installed at the top of base support 46, base support 46 passes through shock-absorbing ball 61 and is connected with stores pylon 59, the bottom of base support 46 is provided with flies to control 64, fly to control 64 and install on stores pylon 59 through the bolt, set up the mounting hole on stores pylon 59, fly to control 62 is installed through the bolt to the bottom of stores pylon 59, and this miniature coaxial double-oar unmanned aerial vehicle adopts miniature coaxial double-oar design, and two pairs of rotor coaxial installation, counter-rotating realize hanging up and down through battery-powered, through battery-operated, with flying and high dynamic attack, construct the novel combat system of miniature highly integrated technology based on miniature unmanned aerial vehicle technique and airborne equipment, miniature unmanned aerial vehicle can be when combat, hide it back, take off and carry out and expand searching or other tasks to the target through personnel control its take off.
As a preferred embodiment of the present invention, the battery 55 is connected to the motor 7 through a wire, and the wire is arranged on the inner side of the spindle through the spindle wire through hole 3, so that the arrangement of the motor is facilitated, and the safety of the wire is ensured 1.
As a preferred embodiment of the present invention, the fixing holes 21 are disposed at both sides of the battery connection fixing member positioning hole 20, the fixing holes 21 are fixed to the upper limit groove 1 by bolts, and the battery connection fixing member positioning hole 20 is mounted to the main shaft positioning hole 1 by bolts.
As a preferred embodiment of the present invention, the lower moving disc 39 is disposed at the bottom of the motor 7, the sliding shaft sleeve 40 is integrally formed with a copper sleeve bearing mounting section 50, and the lower moving disc 39 is mounted on the copper sleeve bearing mounting section 50 through a bearing.
As a preferred embodiment of the present invention, the battery 55 is provided with the battery fixing end 58, the battery fixing end 58 is provided with the chute 57, the battery quick-release fixing member 16 is integrally formed with the chute 18, the chute 57 is matched with the chute 18, the battery fixing end 58 and the chute 18 on the battery quick-release fixing member 16 can be combined in a scribing and inserting manner to complete the installation, and the locking bolt 13 is inserted into the clamping groove 56 on the battery fixing end 58, so that the battery installation and fixing can be completed quickly.
As a preferred embodiment of the present invention, the thin-walled bearing 31 and the knuckle bearing 30 are both sleeved on the outer side of the main shaft, the knuckle bearing 30 is disposed on the top of the thin-walled bearing 31, the movable tilting disk 28 is sleeved on the outer side of the knuckle bearing 30, and the stationary tilting disk 29 is sleeved on the outer side of the thin-walled bearing 31.
As a preferred embodiment of the present invention, a shift fork threaded hole 54 is formed at one end of the shift fork 42, a through hole 51 is formed in the sliding sleeve 40, and the shift fork threaded hole 54 is connected to the through hole 51 through the front shift fork shaft 41.
As a preferred embodiment of the present invention, the fork front rotary shaft 41 includes a polish rod portion 48 and a threaded portion 49, the threaded portion 49 is engaged with the fork threaded hole 54, and the polish rod portion 48 is caught inside the through hole 51.
As a preferred embodiment of the present invention, the middle part of the pitch shift fork 42 is mounted on the fork link 43 through a rotating shaft, the bottom of the base bracket 46 is mounted with the lower steering engine link 45, and the other end of the pitch shift fork 42 is connected with the lower steering engine link 45 through a third link 44.
As a preferred embodiment of the present invention, the bottom of the base support 46 is provided with the lower steering engine 60, the lower steering engine 60 is mounted on the base support 46 through the steering engine mounting hole 53, the unmanned aerial vehicle connects all parts in series through a main shaft, and the unmanned aerial vehicle is integrally laid out through the main shaft, so that the transverse width of the unmanned aerial vehicle is reduced, the resistance of the air received by the unmanned aerial vehicle in the flying process is reduced, the flying speed of the unmanned aerial vehicle is improved, and the unmanned aerial vehicle has the outstanding characteristics of small size, difficulty in finding, good concealment, light weight, low cost, strong function, convenience in carrying, simplicity in operation and the like. The miniature coaxial double-oar unmanned aerial vehicle supplies electric energy to all electric equipment through a battery 55, adopts a miniature coaxial double-oar design, is coaxially installed and reversely rotated by two pairs of rotary wings, realizes vertical take-off and landing, fly following and high dynamic attack through battery driving, builds a novel combat system based on miniature highly integrated technology of miniature unmanned aerial vehicle technology and airborne equipment, has vertical take-off and landing capability, can hide the miniature unmanned aerial vehicle during combat, and can control take-off of the miniature unmanned aerial vehicle to carry out target unfolding search or other tasks by personnel after the miniature unmanned aerial vehicle is hidden, and when the miniature coaxial double-oar unmanned aerial vehicle is used, all parts are connected in series through a main shaft, the whole unmanned aerial vehicle is distributed through the main shaft, so that the transverse width of the miniature unmanned aerial vehicle is reduced, the resistance of air received in the flying process is reduced, the flying speed of the miniature unmanned aerial vehicle is improved, and the miniature coaxial double-oar unmanned aerial vehicle has the outstanding characteristics of small size, difficulty in being found, good concealment, light weight, low cost, strong function, convenience in carrying, simplicity in operation and the like
While the fundamental and principal features of the invention and advantages of the invention have been shown and described, it will be apparent to those skilled in the art that the invention is not limited to the details of the foregoing exemplary embodiments, but may be embodied in other specific forms without departing from the spirit or essential characteristics thereof. The present embodiments are, therefore, to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.
Furthermore, it should be understood that although the present disclosure describes embodiments, not every embodiment is provided with a separate embodiment, and that this description is provided for clarity only, and that the disclosure is not limited to the embodiments described in detail below, and that the embodiments described in the examples may be combined as appropriate to form other embodiments that will be apparent to those skilled in the art.
Claims (7)
1. The utility model provides a coaxial double oar unmanned aerial vehicle of microminiature which characterized in that: comprises a main shaft, a motor (7), a battery (55), a period distance changing mechanism, a total distance changing mechanism and a damping hanging frame mechanism, wherein the motor (7), a power supply system, the period distance changing mechanism, the total distance changing mechanism and the damping hanging frame mechanism are all arranged on the main shaft, a first main shaft positioning hole (1), a second main shaft positioning hole (2), a main shaft wire passing hole (3), a third main shaft positioning hole (4), a first limit groove (5) and a second limit groove (6) are arranged on the main shaft, a screw hole (8) for installing a propeller hub is arranged on the motor (7), a propeller hub (9) is arranged at the top and the bottom of the motor (7), The utility model discloses a solar energy power generation device, including a rotor hub (9), a battery fixing end (58) and a battery, wherein the rotor hub (9) is arranged on a threaded hole (8) through a rotating shaft (12), a screw (37) and a lower screw (38) are arranged on one side of the rotor hub (9), the screw (37) and the lower screw (38) are arranged on the rotor hub (9) through a blade mounting hole (11), a battery quick-release fixing piece (16) is arranged at the bottom of the battery (55), a battery connecting fixing piece (19) is welded on the battery quick-release fixing piece (16), a battery connecting fixing piece positioning hole (20) and a fixing hole (21) are arranged on the battery connecting fixing piece (19), The battery fixing end (58) is provided with a chute (57), the battery quick-release fixing piece (16) is integrally formed with a slide way (18), the chute (57) is matched with the slide way (18), the battery quick-release fixing piece (16) is provided with a lock hole (17), the inner side of the battery fixing end (58) is provided with a clamping groove (56), the clamping groove (56) is connected with the lock hole (17) through a locking bolt (13), two ends of the locking bolt (13) are fixed on the battery quick-release fixing piece (16) through a spring (15) and a clamp spring (14), the cycle variable-pitch mechanism comprises an upper part and a lower part, the upper part comprises an upper steering engine support (22) and a steering engine (23), the steering engine (23) is arranged on the upper steering engine support (22), the upper steering engine support (22) is locked at the outer side of a main shaft limiting groove II (6), the upper steering engine support (22) is arranged on a main shaft positioning hole II (2) through bolts, a steering engine rocker arm (24) is arranged at the bottom of the steering engine (23), a cross rod (25) and a swashplate guide piece (26) are arranged on the upper steering engine support (22), the swashplate guide piece (26) is arranged at the bottom of the cross rod (25), a guide groove (27) is formed in the swashplate guide piece (26), The lower part comprises a tilting disk movable disk (28), a tilting disk static disk (29), a thin-wall bearing (31) and a joint bearing (30), a first ball head (33) is arranged on the steering engine rocker arm (24), a second ball head (34) and a third ball head (35) are arranged on the tilting disk movable disk (28), the first ball head (33) is respectively connected with the second ball head (34) and the third ball head (35) through a second connecting rod (32), an extension section (36) is arranged on one side of the third ball head (35), one end of the extension section (36) is clamped at the inner side of the guide groove (27), a paddle hub (9) at the top of the motor (7) is connected with the tilting disk static disk (29) through the first connecting rod (10), The variable total distance mechanism comprises a lower layer movable disc (39), a sliding shaft sleeve (40), a variable distance shifting fork (42), a shifting fork front rotating shaft (41) and a shifting fork connecting rod (43), wherein the sliding shaft sleeve (40) is sleeved on the outer side of a main shaft, a paddle hub (9) at the bottom of a motor (7) is connected with the lower layer movable disc (39) through a torque arm (47), the damping hanging frame mechanism comprises a base bracket (46), a hanging frame (59) and a damping ball (61), the base bracket (46) is arranged at the bottom of the lower layer movable disc (39), the base bracket (46) is fixedly connected with a main shaft positioning hole III (4) on the main shaft through a positioning hole (52), The bottom of the base support (46) is provided with a lower steering engine connecting rod (45), the base support (46) is provided with a connecting rod mounting hole (64), the top of the base support (46) is provided with a shifting fork connecting rod (43), the base support (46) is connected with a hanging frame (59) through a damping ball (61), the bottom of the base support (46) is provided with a flight control (65), the flight control (65) is mounted on the hanging frame (59) through a bolt, the hanging frame (59) is provided with a mounting hole, the bottom of the hanging frame (59) is provided with the flight control (65) through a bolt, a battery (55) is connected with a motor (7) through an electric wire, The electric wires penetrate through the spindle wire passing holes (3) to be arranged on the inner side of the spindle, the fixing holes (21) are formed in two sides of the battery connection fixing piece locating holes (20), the fixing holes (21) are fixed with the upper limiting grooves (5) through bolts, and the battery connection fixing piece locating holes (20) are arranged on the spindle locating holes (1) through bolts.
2. The microminiature coaxial double-paddle unmanned aerial vehicle of claim 1, wherein: the lower movable disc (39) is arranged at the bottom of the motor (7), the copper bush bearing mounting section (50) is integrally formed on the sliding shaft sleeve (40), and the lower movable disc (39) is mounted on the copper bush bearing mounting section (50) through a bearing.
3. The microminiature coaxial double-paddle unmanned aerial vehicle of claim 1, wherein: the thin-wall bearing (31) and the knuckle bearing (30) are both sleeved on the outer side of the main shaft, the knuckle bearing (30) is arranged at the top of the thin-wall bearing (31), the tilting disk moving disk (28) is sleeved on the outer side of the knuckle bearing (30), and the tilting disk static disk (29) is sleeved on the outer side of the thin-wall bearing (31).
4. The microminiature coaxial double-paddle unmanned aerial vehicle of claim 1, wherein: one end of the variable-pitch shifting fork (42) is provided with a shifting fork threaded hole (54), the sliding shaft sleeve (40) is provided with a through hole (51), and the shifting fork threaded hole (54) is connected with the through hole (51) through a shifting fork front rotating shaft (41).
5. The microminiature coaxial double-paddle unmanned aerial vehicle of claim 4, wherein: the front rotating shaft (41) of the shifting fork comprises a polish rod part (48) and a threaded part (49), the threaded part (49) is matched with a threaded hole (54) of the shifting fork, and the polish rod part (48) is clamped at the inner side of the through hole (51).
6. The microminiature coaxial double-paddle unmanned aerial vehicle of claim 1, wherein: the middle part of the variable-pitch shifting fork (42) is arranged on a shifting fork connecting rod (43) through a rotating shaft, a lower steering engine connecting rod (45) is arranged at the bottom of the base support (46), and the other end of the variable-pitch shifting fork (42) is connected with the lower steering engine connecting rod (45) through a connecting rod III (44).
7. The microminiature coaxial double-paddle unmanned aerial vehicle of claim 1, wherein: the bottom of base support (46) is provided with lower steering wheel (60), lower steering wheel (60) are installed on base support (46) through steering wheel mounting hole (53).
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| CN202011540180.4A CN112498686B (en) | 2020-12-23 | 2020-12-23 | Microminiature coaxial double-oar unmanned aerial vehicle |
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| CN112498686B true CN112498686B (en) | 2024-10-01 |
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| US9434471B2 (en) * | 2005-04-14 | 2016-09-06 | Paul E Arlton | Rotary wing vehicle |
| WO2008140851A2 (en) * | 2007-02-28 | 2008-11-20 | Lawrence John M | Dual rotor vertical takeoff and landing rotorcraft |
| CN205293082U (en) * | 2015-12-14 | 2016-06-08 | 深圳市沈氏彤创航天模型有限公司 | Coaxial unmanned aerial vehicle's assembly structure |
| CN108557070B (en) * | 2018-04-12 | 2019-05-03 | 北京理工大学 | A kind of small-sized coaxial dual-rotor helicopter |
| CN210526851U (en) * | 2019-08-30 | 2020-05-15 | 祖亚军 | Variable-pitch drive assembly for an aircraft |
| CN110626495A (en) * | 2019-08-30 | 2019-12-31 | 祖亚军 | Small coaxial double-rotor type unmanned aerial vehicle |
| CN211033009U (en) * | 2019-09-30 | 2020-07-17 | 北京交通大学 | Small coaxial dual-rotor unmanned aerial vehicle |
| CN212047876U (en) * | 2020-02-17 | 2020-12-01 | 华南机械制造有限公司 | Single-shaft double-propeller unmanned aerial vehicle |
| CN111332462B (en) * | 2020-02-24 | 2021-08-03 | 北京理工大学 | Portable small-sized cylinder type coaxial reverse-propeller three-blade rotor type unmanned aerial vehicle |
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