CN206691353U

CN206691353U - A kind of multi-rotor unmanned aerial vehicle

Info

Publication number: CN206691353U
Application number: CN201720306001.8U
Authority: CN
Inventors: 卢旭升
Original assignee: Individual
Current assignee: Individual
Priority date: 2017-03-28
Filing date: 2017-03-28
Publication date: 2017-12-01
Anticipated expiration: 2027-03-28

Abstract

It the utility model is related to a kind of multi-rotor unmanned aerial vehicle, including fuselage, horn, horn foldable structure, bi-motor structure, blade and quick-disassembly structure, fuselage outer periphery is uniformly provided with multiple horns, one end of horn is by horn foldable structure hinge on fuselage, the other end of the horn is provided with bi-motor structure, there are the bi-motor structure two output shafts to be separately installed with blade, and each bi-motor structure drives two blades simultaneously；A quick-disassembly structure is mounted in the middle part of the upper/lower terminal of fuselage.The present invention/utility model layout is good, installation can fast folding or expansion horn, and be designed with can the landing gear structure of fast insert-pull be easy to carry, save parking space, main screw lift is light, and the endurance that power energy system provides is strong.

Description

A kind of multi-rotor unmanned aerial vehicle

Technical field

The utility model belongs to unmanned plane field, especially a kind of multi-rotor unmanned aerial vehicle.

Background technology

In recent years, possessed along with the gradual maturation of UAV technology, and the progress of supporting control device The feasibility of technical a variety of applications.At present, the structure of multi-rotor unmanned aerial vehicle is usually stationary structure, and agent structure is solid Fixed, space-consuming is larger, especially outgoing execution task when carry it is more inconvenient, it is inconvenient to carry.

By retrieval, do not find and the disclosed patented technology of this patent identical.

Utility model content

The purpose of this utility model is in place of overcome the deficiencies in the prior art, there is provided a kind of multi-rotor unmanned aerial vehicle, design It is scientific and reasonable, simple in construction, powerful, stable.

The utility model solves its technical problem and takes following technical scheme to realize：

A kind of multi-rotor unmanned aerial vehicle, including fuselage, horn, horn foldable structure, bi-motor structure, blade and Quick Release knot Structure, fuselage outer periphery are uniformly provided with multiple horns, and by horn foldable structure hinge on fuselage, it is special for one end of horn Sign is：The other end of the horn is provided with bi-motor structure, and there are the bi-motor structure two output shafts to be separately installed with Blade, each bi-motor structure drive two blades simultaneously；A quick-disassembly structure is mounted in the middle part of the upper/lower terminal of fuselage.

Moreover, it is symmetrically installed with retractable landing gear in fuselage lower end both sides.

Moreover, the horn is curved structure, curve bending, the horn oblique upper of installation blade one end are formed with the middle part of horn Extension, curved structure allow to reduce body volume when fuselage folds.

Moreover, the bi-motor structure includes motor mounting shell, blade mounting disc, connecting tube and motor, motor installation Shell is a rectangular cubic housing, and a blade mounting disc is symmetrically installed with the upper and lower ends of motor mounting shell, is installed in blade An output shaft hole coaxially is formed with the middle part of disk, and drive installation has a blade respectively in upper and lower two output shaft holes；In electricity A connecting tube is fixed with the middle part of one side wall of machine mounting shell, the connecting tube is used for affixed horn；It is embedding side by side in motor mounting shell Equipped with two motors.

Moreover, the horn foldable structure include horn fixed mount, horn folding rotary shaft, horn connecting tube, it is spacing hook, Limited post and depression bar, horn fixed mount are packed on fuselage, and horn fixed mount is a rectangle space frame structure, and horn is fixed The end face outer of frame is hinged with horn connecting tube by the horn folding rotary shaft of a longitudinal direction, is contacted with horn fixed mount Horn connection end surfaces be formed with two spacing hooks, be provided with horn fixed mount one with it is spacing hook position coordinate limit Position post, the both ends of limited post are individually directed regulation and are arranged in the made limit sliding chutes in horn fixed mount two side, in limited post Middle part is coated with a depression bar.

It is packed in moreover, the quick-disassembly structure includes fixed seat, dismounting seat, spacing ring and handle, fixed seat on fuselage, Fixed seat upper center is formed with mounting hole, and dismounting seat is coaxially installed with the mounting hole, and the dismounting seat upper end is formed with bolt hole use In the airborne equipment needed for connection, dismounting seat bottom is formed with coaxial spacing ring；Coaxially it is formed with a fracture in fixed seat upper end Ring, the periphery coaxial sleeve of the fracture inner ring are equipped with a fracture outer shroud, in the fixed seat on the outside of the fracture outer shroud by one with it is solid The homoaxial lock shaft of reservation is hinged with one handle, and the outer wall of the periphery close contact fracture outer shroud of the handle is simultaneously convex as one Wheel construction.

Moreover, the undercarriage includes feet bar, support bar and undercarriage connecting seat, the middle part of feet bar is vertically fixedly mounted with There is a support bar, the support bar other end is fixed with a limited location snap ring, and the limited location snap ring is fixed with a spacing locknut, in limiting lock Coaxially extension is formed with termination to the support bar of female other end, and the termination coaxial cooperation has sleeve, and sleeve pipe one end is formed with and limiting lock The screw thread that mother coordinates, the other end of sleeve pipe are hinged with a undercarriage connecting seat by swing shaft, and the undercarriage connecting seat is packed in Fuselage lower end.

The advantages of the utility model and good effect are：

1st, this unmanned plane is easy to control, swift to operate simple, lifting using push type rapid deployment and storage horn structure Operating efficiency, horn use bend pipe structure, and folding space is using rationally and specifically higher intensity, by testing bend pipe form In the case of 30mm external diameter wall thickness 1mm carbon fibre composite can monomer weigh 95kg, weight only has 65g.

2nd, this unmanned plane is not affected by the weather, and flight system and electricity are covered using the molded plastics shell of a lightweight Source system protection the influence of their not climates.

3rd, the active/standby devices system of this unmanned plane, Fast Installation detaching structure, fast quick-release are mounted in fuselage upper/lower terminal Place system drastically increases speed and flexibility.

4th, this unmanned plane uses power dual system, supports 6 rotors also to support 12 molecular dynamical systems of electricity simultaneously, It is bigger in limited wheelbase to improve power output.

5th, for the working cell of quick-replaceable the machine, versatility is realized, operation of landing gear is designed to extension and retraction system and branch Support structure uses rapid plug structure, allows to carry out diversification flight demand, while be greatly reduced the sky of equipment storage Between.

6th, this unmanned plane is the unmanned plane of a diversification, and power energy system is not used only in the range of battery, Many continuations of the journey of the machine can be improved under hybrid power energy resource system working condition with quick-replaceable hybrid power energy resource system Ability.

7th, this unmanned plane supports whole avionics systems to include (the winged control such as DJI series, APM series, PIX series), aircraft electricity Pond can install and lean to one side up and down the installation of six pieces of batteries, and application is random, the convenient demand with client of main purpose, oil electricity mixing Dynamical system is also that can install up and down, also possesses installation RTK differential GPS mounting platforms, main purpose makes user more Memberization is applied, and facilitates demand of the client to platform expansion.

Brief description of the drawings

Fig. 1 is the dimensional structure diagram of this unmanned plane；

Fig. 2 is the lateral elevational view of this unmanned plane；

Fig. 3 is the schematic top plan view of this unmanned plane deployed condition；

Fig. 4 is the schematic top plan view of this unmanned plane folded state；

Fig. 5 is bi-motor structural representation in this unmanned plane；

Fig. 6 is Fig. 5 explosive view；

Fig. 7 is horn foldable structure schematic diagram；

Fig. 8 is quick-disassembly structure schematic diagram；

Fig. 9 is Fig. 8 explosive view；

Figure 10 is undercarriage fractionation structural representation.

Above and below Figure 11 equipment carry working state structures schematic diagram (double heads up and down)；

Figure 12 is that GPS deploys design sketch；

Figure 13 is GPS folding effect figures.

Embodiment

Below in conjunction with the accompanying drawings and the utility model is described in further detail by specific embodiment, and following examples are simply retouched The property stated, be not limited, it is impossible to limit the scope of protection of the utility model with this.

A kind of multi-rotor unmanned aerial vehicle, including fuselage 6, horn 5, horn foldable structure 4, bi-motor structure 1, blade 2 and Quick-disassembly structure 9, the main body of fuselage are a regular polygon disk-like structure, installation battery and control circuit board in fuselage, outside fuselage All radial equipartitions are provided with multiple horns, and the horn shown in the present embodiment is six；One end of horn passes through horn foldable structure For hinge on fuselage, the other end of horn is provided with bi-motor structure 1, and there are the bi-motor structure two output shafts to install respectively There is blade, each bi-motor structure drives two blades simultaneously, there is provided sufficient power；Pacify in the middle part of the upper/lower terminal of fuselage Equipped with a quick-disassembly structure 9, two quick-disassembly structures are used to install head 3 or the grade airborne equipment of the hybrid power energy 7.

Undercarriage 8 is symmetrically installed with fuselage lower end both sides, the present embodiment is using demountable structure.

Aircraft battery can be with upper and lower installation and six pieces of batteries installation of leaning to one side, and application is random, shown in the present embodiment accompanying drawing Outer periphery interval is provided with six pieces of batteries 11 on fuselage.

1 to six GPS module can be installed, the fuselage upper end radial equipartition of the present embodiment is provided with three by rolling on fuselage The GPS module 10 of folded support support, referring to shown in accompanying drawing 12 to accompanying drawing 13.

Each several part concrete structure is：

Referring to shown in accompanying drawing 1 to 3, horn is curved structure, and curve bending, the machine of installation blade one end are formed with the middle part of horn Arm oblique upper extends, and curved structure allows to reduce body volume when fuselage folds, effectively prevent when laterally folded blade with Body parts position interferes influence and folded.

Referring to shown in accompanying drawing 5 to Fig. 6, bi-motor structure includes motor mounting shell 1-3, blade mounting disc 1-4, connecting tube 1- 1 and motor 1-5, motor mounting shell 1-3 are a rectangular cubic housing, are symmetrically installed with the upper and lower ends of motor mounting shell One blade mounting disc 1-4, an output shaft hole is coaxially formed with the middle part of blade mounting disc, and in upper and lower two output shaft holes Drive installation has a blade respectively；A connecting tube 1-1 is fixed with the middle part of a side wall of motor mounting shell, the connecting tube is used for Affixed horn；It is embedded with two motor 1-5 side by side in motor mounting shell, the motor mounting shell of motor lower end, which is mounted, one Location-plate 1-6 is used for the position for fixing two motors, and the output shaft of two motors is co-axially mounted corresponding upper/lower terminal two respectively Individual blade, power are strong.

Referring to shown in accompanying drawing 7, horn foldable structure includes horn fixed mount 1-3, horn folding rotary shaft 1-2, horn connection Pipe 1-1, spacing hook 1-7, limited post 1-5 and depression bar 1-4, horn fixed mount are packed on fuselage, and horn fixed mount is one Rectangle space frame structure, the end face outer of horn fixed mount are hinged with horn by the horn folding rotary shaft of a longitudinal direction Connecting tube, two spacing hooks are formed with the horn connection end surfaces contacted with horn fixed mount, are installed in horn fixed mount There is a limited post coordinated with spacing hook position, the both ends of limited post are individually directed regulation and are arranged on horn fixed mount two side In made limit sliding chutes 1-6, be coated with a depression bar in the middle part of limited post, depression bar elastic reset not in the state of by external force, The position of limited post and hook locks；It is that limited post moves in limit sliding chutes when depression bar is extruded by external force, so as to unclamp machine The hook of arm connecting tube.This structure is laterally folded using the progress of push type mechanical structure, by pressing, to operate the stretching, extension of horn Or fold.

Referring to shown in accompanying drawing 8 to Fig. 9, quick-disassembly structure includes fixed seat 9-4, dismounting seat 9-2, spacing ring 9-6 and handle 9-1, fixed seat are packed on fuselage, and fixed seat upper center is formed with mounting hole, and dismounting seat is coaxially installed with the mounting hole, should Dismounting seat upper end is formed with bolt hole and is used to connect required airborne equipment, and dismounting seat bottom is formed with coaxial spacing ring 9-6；

A fracture inner ring 9-7 is coaxially formed with fixed seat upper end, the periphery coaxial sleeve of the fracture inner ring is equipped with outside a fracture Ring 9-8, one handle 9- is hinged with the homoaxial lock shaft 9-9 of fixed seat by one in the fixed seat on the outside of the fracture outer shroud 1, the periphery of the handle is in close contact the outer wall of fracture outer shroud and turns into a cam structure, and rotating the handle can compress or put Loose fracture outer shroud and fracture inner ring, diameter is tightened up so as to lock the spacing ring inside insertion fracture inner ring, and then lock dismounting Seat；Fixed seat bottom both sides are symmetrically installed with self-locking spring slice 9-5, for locking the dismounting seat being inlaid in mounting hole, further Ensure the steadiness of connection.

Referring to shown in accompanying drawing 10, undercarriage includes feet bar 8-1, support bar 8-2 and undercarriage connecting seat 8-6, feet The middle part of bar is vertically fixed with a support bar, and the support bar other end is fixed with a limited location snap ring 8-3, and the limited location snap ring is fixed with One spacing locknut 8-4, coaxially extend in the support bar of the spacing locknut other end and be formed with termination 8-5, the termination coaxial cooperation has one Sleeve pipe 8-8, sleeve pipe one end are formed with the screw thread coordinated with spacing locknut, and the other end of sleeve pipe is hinged with together by swing shaft 8-7 Fall frame connecting seat 8-6, the undercarriage connecting seat is packed in fuselage lower end.

The fast disassembly type operation of landing gear of the present embodiment be can fast quick-detach, taken out between fuselage by sliding rail groove Fast Installation is inserted, edge has spring tongue to prevent from loosening and come off, and the power supply and signal of undercarriage are attached by contact, are made Undercarriage and fuselage are separated into the mode of two modules, one product, dismantle and easy to maintenance.

Laterally folded rear body has the locking mechanical structure for horn, the laterally folded of horn is fixed.

Unmanned plane motor cabinet can support the double two kinds of installation motor modes of upper and lower list thus to support double dynamical system System.

Lower extension plant machinery structure carries out effectiveness in vibration suppression using top plate plate by cushion rubber, is used with lower connection equipment of hanging Rapid plug structure carries out mechanical engagement, enables the compatible a variety of carry quick-replaceable effects of a machine.

The design of battery (non-label in figure) fixed structure is installed using circumference array mode, versatile replaceable major part Electrokinetic cell on the market, it can also improve the discharge performance of battery.

Blade and motor also use fast disassembly type fixed form, are easy to carry and rapid deployment.

Although disclosing embodiment of the present utility model and accompanying drawing for the purpose of illustration, those skilled in the art can be with Understand：Do not departing from the utility model and spirit and scope of the appended claims, it is various replace, change and modifications all be can Can, therefore, the scope of the utility model is not limited to embodiment and accompanying drawing disclosure of that.

Claims

1. a kind of multi-rotor unmanned aerial vehicle, including fuselage, horn, horn foldable structure, bi-motor structure, blade and Quick Release knot Structure, fuselage outer periphery are uniformly provided with multiple horns, and by horn foldable structure hinge on fuselage, it is special for one end of horn Sign is：The other end of the horn is provided with bi-motor structure, and there are the bi-motor structure two output shafts to be separately installed with Blade, each bi-motor structure drive two blades simultaneously；A quick-disassembly structure is mounted in the middle part of the upper/lower terminal of fuselage.

2. multi-rotor unmanned aerial vehicle according to claim 1, it is characterised in that：It is symmetrically installed with and can receives in fuselage lower end both sides Blow the gear down.

3. according to the multi-rotor unmanned aerial vehicle described in claim 1, it is characterised in that：The horn is curved structure, is made in the middle part of horn There are curve bending, the horn oblique upper extension of installation blade one end, curved structure allows to reduce body volume when fuselage folds.

4. according to the multi-rotor unmanned aerial vehicle described in claim 1, it is characterised in that：The bi-motor structure include motor mounting shell, Blade mounting disc, connecting tube and motor, motor mounting shell is a rectangular cubic housing, in the upper and lower ends pair of motor mounting shell Title is provided with a blade mounting disc, and an output shaft hole, and upper and lower two output are coaxially formed with the middle part of blade mounting disc Drive installation has a blade respectively in axis hole；A connecting tube is fixed with the middle part of a side wall of motor mounting shell, the connecting tube For affixed horn；It is embedded with two motors side by side in motor mounting shell.

5. according to the multi-rotor unmanned aerial vehicle described in claim 1, it is characterised in that：The horn foldable structure is fixed including horn Frame, horn folding rotary shaft, horn connecting tube, spacing hook, limited post and depression bar, horn fixed mount are packed on fuselage, machine Arm fixed mount is a rectangle space frame structure, the horn folded turning that the end face outer of horn fixed mount passes through a longitudinal direction Axle is hinged with horn connecting tube, two spacing hooks is formed with the horn connection end surfaces contacted with horn fixed mount, in horn One limited post coordinated with spacing hook position is installed, the both ends of limited post are individually directed regulation and are arranged on horn in fixed mount In the made limit sliding chutes in fixed mount two side, a depression bar is coated with the middle part of limited post.

6. according to the multi-rotor unmanned aerial vehicle described in claim 1, it is characterised in that：The quick-disassembly structure include fixed seat, dismounting seat, Spacing ring and handle, fixed seat are packed on fuselage, and fixed seat upper center is formed with mounting hole, are co-axially mounted in the mounting hole There is dismounting seat, the dismounting seat upper end is formed with bolt hole and is used to connect required airborne equipment, and dismounting seat bottom is formed with coaxial limit Position ring；A fracture inner ring is coaxially formed with fixed seat upper end, the periphery coaxial sleeve of the fracture inner ring is equipped with a fracture outer shroud, and this is disconnected One handle is hinged with the homoaxial lock shaft of fixed seat by one in fixed seat on the outside of mouth outer shroud, the periphery of the handle is tight Contiguity touches the outer wall of fracture outer shroud and turns into a cam structure.

7. according to the multi-rotor unmanned aerial vehicle described in claim 2, it is characterised in that：The undercarriage include feet bar, support bar with And undercarriage connecting seat, the middle part of feet bar are vertically fixed with a support bar, the support bar other end is fixed with a limited location snap ring, The limited location snap ring is fixed with a spacing locknut, coaxially extends in the support bar of the spacing locknut other end and is formed with termination, the termination is same Axle is combined with sleeve, and sleeve pipe one end is formed with the screw thread coordinated with spacing locknut, and the other end of sleeve pipe is hinged with by swing shaft One undercarriage connecting seat, the undercarriage connecting seat are packed in fuselage lower end.