CN209479968U - More rotor flying platforms - Google Patents

Abstract

A kind of more rotor flying platforms, including rotor seat, carbon pipe, platform assembly composition, its dynamical system includes driving cell apparatus, motor, propeller, the lower end of the platform assembly is fixed with lateral fast plate, the fast plate is provided with fast socket, and Quick Release assembly is fixed on fast plate by fast bolt by the fast socket；Vibration-absorptive material is placed in carbon pipe, the battery compartment in cell apparatus is provided with for guaranteeing battery work in the low-temperature protection device of normal temperature environment.Its advantage is that due to having used Quick-disassembling mechanism so that general purpose vehicle saves many time when replacing mission payload, realize it is quick, easily replace mission payload；Battery uses low-temperature protection device, so that still can work normally when flying platform rises to low-temperature region；After placing vibration-absorptive material inside carbon pipe, the vibration of Z axis is effectively reduced, has a smooth flight.

Description

More rotor flying platforms

Technical field

The utility model relates to air vehicle technique field, in particular to a kind of more rotor flying platforms.

Background technique

Multi-rotor unmanned aerial vehicle has that structure is simple, easy to operate, can VTOL, the advantages that strong flexibility, stability is good, It is widely applied in the specialized neck such as aeroplane photography, geographical mapping, agricultural plant protection, power-line patrolling, environmental monitoring.

But so many multi-rotor unmanned aerial vehicle is all used using a machine one mostly.When certain multi-rotor unmanned aerial vehicle is completed When after one task as gone to execute new different tasks again, needs to spend many manpowers, or original equipment is processed, change It makes, takes time and effort.

Utility model content

The purpose of this utility model is just to provide a kind of a tractor serves several purposes, using Quick-disassembling mechanism, the different equipment of quick-replaceable, It realizes a tractor serves several purposes, more rotor flying platforms of a variety of applications of multi-rotor unmanned aerial vehicle industry can be met.

The solution of the utility model is such that

A kind of more rotor flying platforms, including rotor seat, carbon pipe, platform assembly composition, dynamical system include driving electricity Pool device, motor, propeller, the lower end of the platform assembly are fixed with lateral fast plate, and the fast plate is provided with fast insert Quick Release assembly is fixed on fast plate by fast bolt by key seat, the fast socket.

More specific technical solution is also: vibration-absorptive material is placed in the carbon pipe.

Further: it is Flexible decoupling material that vibration-absorptive material is placed in the carbon pipe.

Further: it is sponge that vibration-absorptive material is placed in the carbon pipe.

Further: the battery compartment in the cell apparatus is provided with for guaranteeing battery work in normal temperature environment Low-temperature protection device.

Further: the low-temperature protection device is included in battery compartment peripheral wall setting thermal insulation material.

Further: the low-temperature protection device includes carrying out heating mechanism to battery.

The utility model has the advantages that:

1, due to having used Quick-disassembling mechanism, when so that general purpose vehicle saving many when replacing mission payload Between, realize it is quick, easily replace mission payload；

2, battery uses low-temperature protection device, so that still can work normally when flying platform rises to low-temperature region；

3, after placing vibration-absorptive material inside carbon pipe, the vibration of Z axis is effectively reduced, has a smooth flight.

Detailed description of the invention

Fig. 1 is the structural schematic diagram of the utility model.

Fig. 2 is the left view of Fig. 1.

Fig. 3 is the top view of Fig. 1.

Fig. 4 is the structural schematic diagram of Quick-disassembling mechanism.

Fig. 5 is the left view of Fig. 4.

Fig. 6 is the top view of Fig. 4.

Fig. 7 is the structural schematic diagram of fast bolt assembly 7.

Fig. 8 is the left view of Fig. 7.

Fig. 9 is the top view of Fig. 7.

Unit number in attached drawing are as follows: rotor seat 1, carbon pipe 2, platform assembly 3, Quick Release assembly 4, attachment base 5, fast plate 6, Fast bolt assembly 7, fast socket 8, fast bolt 9.

Specific embodiment

As shown in Figure 1, 2, 3, the utility model includes rotor seat 1, carbon pipe 2, the composition of platform assembly 3, dynamical system packet Driving cell apparatus, motor, propeller are included, the lower end of the platform assembly 3 is fixed with lateral fast plate 6, and fast plate 6 passes through 5 connecting platform assembly 3 of attachment base, the fast plate 6 are provided with fast socket 8, and the fast socket 8 will be fast by fast bolt 9 It tears assembly 4 open and is fixed on fast plate 6, to meet the quick-replaceable demand of a variety of airborne equipments.

Based on the requirement for flying platform, the design parameter target of flying platform is determined.Use tetra- axis eight of X8( Rotor) type, motor number 8, select 5008 KV338 brushless motor of Crazy Motor, cabinet size600mm, empty machine Weight is 3000g, maximum take-off weight 6000g.

Match 15*55 carbon fiber spiral paddle；Electric current under maximum pull is 13.1A, then electron speed regulator has selected win 30A Mini electricity is adjusted, to satisfy the use demand；

When fully loaded, the flight time keeps 30min to need battery capacity very big, and battery capacity on the market is by multiple pipe System, especially can strictly limit battery capacity, so the large capacity that cell production companies generally produce during air transportation Battery capacity is 10000mAh, 16000mAh, so in a fully loaded state, should use double cell combination that can just meet the requirements.

In fuselage design, quadrotor drone is 565.76mm in the minimum wheel base dimension for installing 15 cun of propellers.For Convenient for the determination of carbon length of tube size and tolerance, take 580mm wheelbase as design size；

According to above-mentioned data, body shown in Fig. 1,2,3 is obtained.

Flight control system selects DJI N3 flight control system.This, which flies control, the advanced software algorithm of DJI, takes into account aircraft Stability and mobility；Double IMU Redundancy Designs improve and fly control stability.

Remote controler selects happy enlightening AT9s remote controler.The remote controler steering engine output stability is 0.5us, using DSSS&FHSS Double spread spectrums are mixed, remote control distance is about 1000 meters, is satisfied the use demand.

Since the shock momentum of aircraft Z-direction is maximum, so, the glissando of Z axis has been carried out in horn, central plate, The similar vibration-absorptive material of some such as sponges is added in carbon pipe 2, it is possible to reduce the vibration of horn, in the present embodiment, carbon pipe 2 is adopted Use carbon fiber pipe.

Since temperature is affected to poly-lithium battery, after lower than 20 DEG C, battery power is decreased obviously, therefore, Battery compartment in the cell apparatus of the utility model is provided with for guaranteeing that battery work is protected in the low temperature of normal temperature environment Protection unit achieves good effect using simply heat preservation is carried out to battery in battery compartment peripheral wall setting thermal insulation material.

In some more specifically environment, it can also guarantee that battery is normal using the heating mechanism heated to battery It uses.

When the utility model for carry LED illumination module when, be configured by following demand: 1. have it is higher bright Degree；2. waterproof, wind resistance；3. can under higher vibration environment LED module the operation is stable；4. good heat dissipation performance；5. Brightness is adjustable；6. there is a pitch axis freedom degree.Wherein: the chip of wick produces 35mil, rated power 30W, maximum electricity using platform It flows up to 4A, luminous flux maximum is up to 4000lm；Lens use 56.8mm lens, because the power of integrated LED lamp group is larger, only Good cooling effect can't be reached using radiator fin, so installing fan additional on radiator fin, improve heat dissipation effect, and Installing fan additional in lamps and lanterns can not only effective temperature-reducing, moreover it is possible to play the effect for eliminating lamps and lanterns water mist.

When the utility model is used, selected carrying equipment need to be only installed on Quick Release assembly 4, such as: LED illumination module For night search and rescue, shooting at night light filling；Installation manipulator high altitude operation etc., and by available airborne equipment unified interface, in fact Now quick, modular conversion.This is the primary trial of unmanned plane application innovation.

After equipment mounted is fixed on Quick Release assembly 4, Quick Release assembly 4 is installed on by fast plate 6 by fast bolt 9, Install carry out using；When use finishes, Quick Release assembly 4 need to only be unloaded by fast bolt 9, so that it may which replacement is carried and set It is standby, it is very easy to use.

Claims (7)

1. a kind of more rotor flying platforms, including rotor seat (1), carbon pipe (2), platform assembly (3) form, dynamical system includes Drive cell apparatus, motor, propeller, it is characterised in that: the lower end of the platform assembly (3) is fixed with lateral fast plate (6), the fast plate (6) is provided with fast socket (8), and the fast socket (8) passes through fast bolt (9) for Quick Release assembly (4) It is fixed on fast plate (6).

2. more rotor flying platforms according to claim 1, it is characterised in that: place vibration-absorptive material in the carbon pipe (2).

3. more rotor flying platforms according to claim 2, it is characterised in that: place vibration-absorptive material in the carbon pipe (2) For Flexible decoupling material.

4. more rotor flying platforms according to claim 3, it is characterised in that: place vibration-absorptive material in the carbon pipe (2) For sponge.

5. more rotor flying platforms according to claim 1, it is characterised in that: the battery compartment setting in the cell apparatus Have for guaranteeing battery work in the low-temperature protection device of normal temperature environment.

6. more rotor flying platforms according to claim 5, it is characterised in that: the low-temperature protection device is included in battery Thermal insulation material is arranged in storehouse peripheral wall.

7. more rotor flying platforms according to claim 5, it is characterised in that: the low-temperature protection device includes to battery Carry out heating mechanism.