CN207045724U - Rotor craft - Google Patents

Abstract

The utility model embodiment discloses a kind of rotor craft, including：Aircraft body, several rotor drivers and duct.Several described rotor drivers are connected on the aircraft body, and several described rotor crafts are arranged around the aircraft body in dispersion shape；The duct is equipped with several described rotor drivers, is connected with each other between adjacent duct.By setting duct on rotor driver, the blade tip position of blade is set to be limited by duct, impact noise is reduced, and induced drag is reduced, and improves the efficiency of propeller.Simultaneously because the ring of duct includes effect, make that rotor craft is compact-sized, aerodynamic noise reduces.When rotor driver is rotated, the vibration in horizontal direction and vertical direction can be produced, seriously affect the stability of rotary-wing flight, the interconnection of adjacent duct can be offset to the vibration of horizontal direction between duct, while the duct being connected with each other can slow down the vibration of duct in the vertical direction.

Description

Rotor craft

Technical field

The utility model embodiment is related to aircraft field, especially a kind of rotor craft.

Background technology

Rotor craft in recent years progressively turn into aviation academia research focus, it have VTOL, hovering, The features such as strong environmental adaptability, have a extensive future.Electronic rotor craft is limited to battery capacity and load in the prior art Ghost image rings, and can not carry out long-time, remote and heavy－duty aerial mission, to make up the deficiency of electronic rotor craft, oil Dynamic rotor craft is paid close attention to by more and more people.

In the prior art, rotor craft uses lift generating means of the free spiral rotation oar as aircraft, specifically, Rotor craft is provided with rotor horn, and rotor horn end is provided with the blade being driven by high-speed motor or engine, oar Leaf produces lift when rotating, drive rotor craft lift-off.

But the inventor of the invention has found under study for action, because the Kinematic Decomposition of propeller is horizontal movement and rotation Transhipment is dynamic, and for blade because high speed circular motion makes speed highest at blade tip, induced drag is bigger, and producing impact to external air flow makes It is big into noise, and this can cause free spiral rotation oar dynamic efficiency low；The horn of free spiral rotation oar is due to being cantilever beam structure bar Part, being easily deformed under pneumatic action at blade tip causes efficiency further to deteriorate, and limitation propeller carries out high-speed motion, equally It is the key for limiting rotary-wing flight speed.

Utility model content

The utility model embodiment is more soared mainly solving the technical problems that providing a kind of raising propeller efficiency and having The rotor craft of scanning frequency degree.

In order to solve the above technical problems, the technical scheme that the embodiment that the utility model is created uses is：There is provided one Kind rotor craft, including：

Aircraft body；

Several rotor drivers, several described rotor drivers are connected on the aircraft body, and it is described several Rotor craft is arranged around the aircraft body in dispersion shape；

Duct, the duct is equipped with several described rotor drivers, is connected with each other between adjacent duct.

Alternatively, the duct includes：

Duct circle；

Duct retainer ring, the duct Fixing shrink ring are interference fitted on the duct circle and with the duct circle；

The duct retainer ring is arranged on the rotor driver.

Alternatively, seamlessly transit to form arc end between one end of the cross section of the duct circle and two side walls, it is described Linear transitions between the end points of the duct circle cross section other end and wherein a side wall, put down between the end points and another side wall Slip over and cross.

Alternatively, the rotor craft also includes：

Parachute bucket, the parachute bucket are arranged on the aircraft body, and landing is provided with the parachute bucket Umbrella and swelling gasbag, the swelling gasbag is arranged on the parachute bottom of the barrel, between the swelling gasbag and the parachute Provided with dividing plate, the umbrella rope of the parachute is connected on the aircraft body；

Gas cylinder, the gas cylinder are arranged on the aircraft body, and the gas cylinder passes through control valve It is connected with the swelling gasbag, so that the parachute is ejected the landing by the swelling gasbag when control valve is opened Umbrella bucket.

Alternatively, several described rotor drivers include：Several rotor horns；

Attachment means wherein are connected between any one rotor horn at least one rotor horn adjacent thereto, so that Triangle stress is formed between any one described rotor horn at least one rotor horn adjacent thereto and the attachment means Structure.

Alternatively, the rotor craft also includes：

Engine, the engine are arranged on the aircraft body, the engine by transmission device with it is described Several rotor drivers connect；

Several fuel tanks, several fuel tanks rule are distributed on the aircraft body, several described fuel tanks It is connected by oil pipe with the engine, answers fuel altogether to the engine jointly.

Alternatively, the rotor craft also includes medicine-chest, and the medicine-chest includes：

Casing, the hollow formation cavity volume of box house；

Insulating course, the cavity volume is interior to be provided with some insulating courses, and some insulating courses are in the direction of growing crosswise of the casing On by the cavity volume be divided into several it is anti-swing liquid space, the insulating course is configured to flow-guiding structure, the flow-guiding structure Center offers liquid-leaking nozzle, so that the anti-liquid one-way flowing swung in liquid space.

Alternatively, the rotor craft also includes：

Enclosed hood, at least part structure of the engine are located in the enclosed hood, the enclosed hood at least one set phase To surface on offer gas channel so that the airhood in formed cross-ventilation；

Airflow speed increasing device, the airflow speed increasing device is arranged in the gas channel, by cutting and promoting air Move in one direction, the air in the gas channel is formed positive and negative pressure difference, the air described in speedup in gas channel Convection velocity.

Alternatively, the engine is provided with bent axle, and the airflow speed increasing device is provided with rotating shaft, the bent axle with it is described Rotating shaft is connected by transmission device, and described transmission device one end is connected on the bent axle of the engine, the transmission device The other end is connected in the rotating shaft of the airflow speed increasing device, and the bent axle drives the airflow speed increasing by the transmission device Device.

Alternatively, the rotor craft also includes：

Undercarriage, the undercarriage are connected to the aircraft body bottom.

Alternatively, the rotor driver also includes variable propeller pitch device, and the variable propeller pitch device includes：

Carrier member；

Actuator, the actuator are arranged in the carrier member, are produced after applying predeterminated voltage along default circumferential paths The driving force of rotation；

Bridgeware, the bridgeware are connected on the actuator, are followed the rotation of the actuator and are moved, and by institute State the driving force that actuator rotates along default circumferential paths and be converted to linear motion；

Rotary shaft, described rotary shaft one end are arranged in the carrier member, and the other end of the rotary shaft is hanging, the rotation Swing device one end is rotatablely connected with the hanging one end of the rotary shaft；

Displacement piece, the displacement piece is sleeved in the rotary shaft and is connected with the bridgeware, with the bridgeware edge The rotary shaft is moved along a straight line, and the displacement piece rotates with the position that the tumbler contacts with the rotary shaft；

Roll-setting gear, described roll-setting gear one end are connected in the displacement piece, the other end of the roll-setting gear and institute The side wall connection of rotor driver is stated, the roll-setting gear drives the rotor driver phase when being moved along a straight line with the displacement piece Rotated for the rotary shaft.

Alternatively, the actuator includes：Steering wheel and rocking arm；

The steering wheel be arranged on the carrier member backwards to the rotary shaft side surface on, the steering wheel be provided with it is defeated Shaft；

The one end is connected on the output shaft, and the other end of the rocking arm is located at the default axial path On, the rocking arm is connected positioned at one end of the circumferential paths with the bridgeware rotating shaft, and the output shaft of the steering wheel drives The rocking arm is rotated along the default circumferential paths.

The beneficial effect of the utility model embodiment is：By setting duct on rotor driver, make the blade tip position of blade Put and limited by duct, impact noise is reduced, and induced drag is reduced, and the efficiency of propeller is improved, in same power consumption Under, the isolated propeller of the more same diameter of rotor driver provided with duct, bigger thrust can be produced.Simultaneously because the ring of duct Effect is included, makes that rotor craft is compact-sized, aerodynamic noise reduces.When rotor driver is rotated, can produce horizontal direction and Vibration on vertical direction, the stability of rotary-wing flight is seriously affected, adjacent duct, which is connected with each other, to offset The vibration of horizontal direction between duct, while the duct being connected with each other can slow down the vibration of duct in the vertical direction.

Brief description of the drawings

, below will be to needed for embodiment description in order to illustrate more clearly of the technical scheme in the embodiment of the utility model The accompanying drawing to be used is briefly described, it should be apparent that, drawings in the following description are only some realities of the present utility model Example is applied, for those skilled in the art, on the premise of not paying creative work, can also be obtained according to these accompanying drawings Other accompanying drawings.

Fig. 1 is the utility model embodiment rotor craft structural representation；

Fig. 2 is the concrete structure schematic diagram of the utility model embodiment parachute bucket；

Fig. 3 is that the utility model embodiment rotor craft parachute uses schematic diagram；

Fig. 4 is the utility model embodiment medicine-chest vertical direction cross-sectional view；

Fig. 5 is the first embodiment structural representation of the utility model embodiment engine heat dissipating device；

Fig. 6 is second of embodiment structural representation of the utility model embodiment engine heat dissipating device；

Fig. 7 is the utility model embodiment pitch mechanism schematic diagram；

Fig. 8 is the concrete structure schematic diagram of the utility model embodiment actuator rocking arm；

Fig. 9 is the concrete structure schematic diagram of the utility model embodiment actuator steering wheel；

Figure 10 is the utility model embodiment pitch-variable system transverse direction face sectional view；

Figure 11 is the structural representation of the utility model embodiment displacement piece displacement outer shroud；

Figure 12 is the structural representation of the utility model embodiment displacement piece displacement inner ring；

Figure 13 is the utility model embodiment rotor driver with rotating spindle combine structure schematic diagram；

Figure 14 is the utility model embodiment propeller hub structural representation；

Figure 15 is the utility model embodiment oar clamping structure schematic diagram；

Figure 16 is a kind of structural representation of embodiment in the utility model embodiment duct cross section.

Description of reference numerals：1st, aircraft body；11st, engine；111st, gas channel；112nd, enclosed hood；113rd, air-flow Speeder；114th, fan；115th, transmission device；2nd, rotor driver；21st, blade；22nd, carrier member；23rd, actuator；231st, shake Arm；232nd, steering wheel；24th, bridgeware；241st, connecting rod；242nd, lever；243rd, connector；25th, rotary shaft；251st, propeller hub；252nd, it is solid Determine screw；253rd, standing screw；26th, displacement piece；261st, displacement outer shroud；262nd, displacement inner ring；271st, oar presss from both sides；272nd, oar branch is adjusted Frame；28th, roll-setting gear；281st, pull bar；3rd, parachute bucket；31st, gas cylinder；32nd, control valve；33rd, parachute；4th, duct； 5th, fuel tank；6th, medicine-chest；61st, insulating course；62nd, liquid-leaking nozzle；63rd, prevent swinging liquid space；64th, check valve.

Embodiment

For the ease of understanding the utility model, below in conjunction with the accompanying drawings and specific embodiment, the utility model is carried out more detailed Thin explanation.It should be noted that when element is expressed " being fixed on " another element, it can be directly in another element Above or therebetween there may be one or more elements placed in the middle.When an element is expressed " connection " another element, it can To be directly to another element or there may be one or more elements placed in the middle therebetween.This specification is used Term " vertical ", " horizontal ", "left", "right" and similar statement for illustrative purposes only.

Unless otherwise defined, technology all used in this specification and scientific terminology are with belonging to skill of the present utility model The implication that the technical staff in art field is generally understood that is identical.In art used in the description of the present utility model in this specification Language is intended merely to describe the purpose of specific embodiment, is not intended to limit the utility model.Term used in this specification "and/or" includes the arbitrary and all combination of one or more related Listed Items.

Embodiment 1

Referring to Fig. 1, Fig. 1 is the present embodiment rotor craft structural representation.

As shown in figure 1, a kind of rotor craft, including：Aircraft body 1, several rotor drivers 2 and duct 4.It is some Individual rotor driver 2 is connected on aircraft body 1, and several rotor crafts are arranged around aircraft body 1 in dispersion shape；If Duct 4 is equipped with dry rotor driver 2, is connected with each other between adjacent duct 4.

Above-mentioned embodiment makes the blade tip position of blade 21 by duct 4 by setting duct 4 on rotor driver 2 Limitation, impact noise are reduced, and induced drag is reduced, and the efficiency of propeller are improved, under same power consumption, provided with duct 4 2 more same diameter of rotor driver isolated propeller, bigger thrust can be produced.Simultaneously because the ring of duct 4 includes effect, make Rotor craft is compact-sized, aerodynamic noise reduces.When rotor driver 2 is rotated, horizontal direction and vertical direction can be produced On vibration, seriously affect the stability of rotary-wing flight, adjacent duct 4 is connected with each other can offset duct 4 it Between horizontal direction vibration, while the duct 4 being connected with each other can slow down the vibration of the in the vertical direction of duct 4.

Specifically, in the present embodiment, aircraft body 1 is (not identify) group by upper body plate (not identifying) and lower body plate Into, it is hollow between upper body plate and lower body plate, connected between upper body plate and lower body plate by copper post (not identifying).Upper machine Body forms corner star with lower body plate, but the concrete shape of upper body plate and lower body plate is not limited to be configured to corner Star, according to the difference of concrete application scene, the shape of upper body plate and lower body plate can also be (being not limited to)：Hexagon or Octagonal, the standard of selection are the quantity of rotor craft horn.

Rotor driver 2 includes rotor horn.Rotor horn one end is connected in the side wall of aircraft body 1, and the other end hangs It is empty.The difference according to rotor horn of rotor craft, can be divided into and (be not limited to) quadrotor, six rotorcraft, Eight-rotary wing aircraft etc., according to the difference of concrete application scene, the rotor horn of rotor craft can choose at random it is applicable, But the horn of the rotor craft in present embodiment is not limited to even number, in some selective embodiments, more rotors The rotor horn of aircraft can be odd number.

Rotor driver 2 also includes blade 21, and blade 21 is arranged on the end of gyroplane arm sling dead end, and blade 21 passes through connection Motor or conveyer in rotor horn end are driven.

The number of duct 4 is identical with the number of rotor horn in present embodiment, and duct 4 passes through screw or the side of welding Formula is fixed on rotor horn, and the ring of duct 4 is included on blade 21, makes to leave certain space between blade 21 and duct 4.

In some selective embodiments, connect between any one rotor horn at least one rotor horn adjacent thereto Attachment means are connected to, so as to be formed between any one rotor horn at least one rotor horn adjacent thereto and attachment means Triangle force structure.Present embodiment makes adjacent rotor horn with being connected dress by setting attachment means between rotor horn Triangle force structure is formed between putting, on the one hand can strengthen the stability between rotor horn, on the other hand, two neighboring rotation The wing transmits the opposite mechanical shock of both direction to attachment means simultaneously, it is carried out cancelling out each other for power in attachment means, The mechanical shock that rotor horn is subject to is reduced, reaches the purpose of rotor horn damping.Wherein, attachment means are specially to connect Bar.

In some selective embodiments, multi-rotor aerocraft horn shock-damping structure includes：Four rotor horns and two Attachment means, it is in mutually diagonal triangle force structure that two attachment means form two between four rotor horns, two companies Connection device is parallel to each other.

In some selective embodiments, multi-rotor aerocraft horn shock-damping structure includes：Four rotor horns and three Attachment means, three attachment means form three triangle force structures, three triangle force structures between four rotor horns Surround half frame shape.

In some selective embodiments, multi-rotor aerocraft horn shock-damping structure includes：Four rotor horns and four Attachment means, four attachment means form four triangle force structures, three triangle force structures between four rotor horns Surround quadrangle.

Rotor craft is in flight course, and due to the emergency of burst, rotor craft can lose power suddenly Or signal out of hand, now, rotor craft often does the movement of falling object, and the shock with ground can damage rotor and fly Row device.

Duct includes：Duct circle (not identifying) and duct retainer ring (not identifying), the duct Fixing shrink ring is mounted in described It is interference fitted on duct circle and with the duct circle；The duct retainer ring is arranged on the rotor driver.

Figure 16 is referred to, is a kind of structural representation of embodiment in the present embodiment duct cross section.

As shown in figure 16, in some selective embodiments, one end of the cross section of the duct circle and two side walls it Between seamlessly transit to form arc end, linear transitions between the end points of the duct circle cross section other end and wherein a side wall, Seamlessly transitted between the end points and another side wall, so that the other end of duct circle forms broken line end.Point C-B and K-L is straight Line segment, point C-K are arc end, and B-A is straightway, and A-L is camber line end, and the faces that represent of A-G are towards blade.The culvert being constructed so as to Road can lower the induced drag of blade blade tip opening position to greatest extent, and produce lift to greatest extent, improve rotor Operating efficiency.

Referring to Fig. 2, Fig. 2 is the concrete structure schematic diagram of the present embodiment parachute bucket；Referring to Fig. 3, Fig. 3 is this implementation Example rotor craft parachute uses schematic diagram.

As shown in Figures 2 and 3, in order to solve the above technical problems, in some selective embodiments, rotor craft also wraps Include：Parachute bucket 3 and gas cylinder 31.Parachute bucket 3 is arranged on aircraft body 1, and parachute is provided with parachute bucket 3 33 and swelling gasbag, swelling gasbag be arranged on the bottom of parachute bucket 3, dividing plate, parachute are provided between swelling gasbag and parachute Umbrella rope be connected on aircraft body 1；Gas cylinder 31 is arranged on aircraft body 1, and gas cylinder 31 passes through control valve Door 32 is connected with swelling gasbag, so that parachute is ejected parachute bucket 3 by swelling gasbag when control valve 32 is opened.

In some selective embodiments, rotor craft also includes：Horizontal velocity detection means (not shown), vertical speed Spend detection means (not shown), elevation carrection sensor (not shown) and control device (not shown).Wherein, horizontal velocity detects Device, vertical speed detector, elevation carrection sensor and control valve 32 are connected with control device.

Specifically, horizontal velocity detection means and vertical speed detector are tachogenerator, and control device is rotation The winged control chip of rotor aircraft.In application scenes, horizontal velocity detection means, detecting rotor craft in level Do not have movement velocity on direction, and vertical speed detector detects that the speed of falling of rotor craft reaches default pendant When falling threshold velocity, control device control control valve 32 is opened, and gas cylinder 31 is inflated swelling gasbag, release landing Umbrella, protection rotor craft preserve from.In other selective embodiments, in order to farthest protect rotor flying The safety of device, opening opportunity of parachute need the height of fall according to where aircraft to be calculated, when detecting that rotor flies The speed of row device have been above falling threshold value when, elevation carrection sensor detect rotor craft height, so as to control device Control parachute to be opened in appropriate height and position, farthest protect rotor craft.

In some selective embodiments, rotor craft also includes：Engine 11 and several fuel tanks 5.Wherein, send out Motivation 11 is arranged on aircraft body 1, and engine 11 is connected by transmission device 115 with several rotor drivers 2；Several The rule of fuel tank 5 is distributed on aircraft body 1, and several fuel tanks 5 are connected by oil pipe with engine 11, jointly to starting Machine 11 answers fuel altogether, and multiple mailboxes are symmetrically distributed in.In present embodiment, by setting multiple oil on aircraft body 1 Case 5, make load distribution on aircraft body 1 more uniformly, multiple fuel tanks 5 carry out fuel feeding to engine 11 simultaneously, avoid When single fuel tank 5 carries out fuel feeding, because the fuel of fuel tank 5 produces fluctuation, rotor craft gravity center shift is caused, in turn results in rotation The unstable situation of rotor aircraft flight.

Specifically, rotor craft includes four fuel tanks 5, and four fuel tanks 5 are symmetrically distributed in four of aircraft body 1 In orientation.

Referring to Fig. 4, Fig. 4 is the present embodiment medicine-chest vertical direction cross-sectional view.

As shown in figure 4, rotor craft includes well：Medicine-chest 6, including：Casing and insulating course 61.Wherein, in box house Sky forms cavity volume；Cavity volume is divided into several by volume on the direction of growing crosswise of casing to be prevented swinging liquid space 63, insulating course 61 Flow-guiding structure is configured to, the center of flow-guiding structure offers liquid-leaking nozzle 62, so that the anti-liquid one-way flowing swung in liquid space 63. Above-mentioned embodiment is split by setting up several insulating courses 61 along the side of growing crosswise of casing, by casing on its direction of growing crosswise Prevent swinging liquid space 63 for several, each anti-height for swinging liquid space 63 is much smaller than the height of casing, when aircraft fluctuates only There is the anti-liquid level swung in liquid space 63 in half-full state to be fluctuated, other are in, and full up or full dummy status is anti-to swing liquid air Between center of gravity in 63 do not change, influence during liquid fluctuating to casing gravity center shift is minimized with this, and then make medicine Influence of the case 6 to aircraft also minimizes.Insulating course 61 is arranged to flow-guiding structure simultaneously, and set in the middle part of flow-guiding structure Liquid-leaking nozzle 62 is put, can effectively preventing the anti-liquid swung in liquid space 63 of lower floor from flowing into, upper strata is anti-to swing in liquid space 63, enters one The reduction of step is anti-to swing the liquid fluctuating phenomenon of liquid space 63, and low anti-the problem of swinging 63 hydrops of liquid space.

In some selective embodiments, anti-oscillating liquid medicine-chest 6 also includes：Check valve 64；Check valve 64 is arranged on Lou In fluid apertures 62, check valve 64 limits the adjacent anti-liquid swung in liquid space 63 and carries out one-way flow along under the perpendicular length direction of casing. Check valve 64 makes liquid to prevent that swinging liquid space 63 is flowed to lower floor along leakage mouth from the anti-liquid space 63 that swings in upper strata, and can not Liquid is enough set inversely to prevent that swinging liquid space 63 flows to upper strata from the anti-liquid space 63 that swings of lower floor.Effectively liquid is limited shaking Occurs the possibility of reverse flow in journey, influence when further reducing liquid fluctuating to casing gravity center shift.This embodiment party In formula, check valve 64 can select (being not limited to)：Spring, gravity type or plastic partition membrane one-way valve 64.

Referring to Fig. 5, Fig. 5 is the first embodiment structural representation of the present embodiment engine heat dissipating device.

As shown in figure 5, in some selective embodiments, rotor craft also includes：Enclosed hood 112 and airflow speed increasing dress Put 113.Wherein, at least part structure of engine 11 is located in enclosed hood 112, at least one set of relative surface of enclosed hood 112 On offer gas channel 111 so that airhood in formed cross-ventilation；Airflow speed increasing device 113 is arranged on gas channel 111 It is interior, by cutting and promoting air to move in one direction, the air in gas channel 111 is formed positive and negative pressure difference, speedup Cross-ventilation speed in gas channel 111.Airflow speed increasing device 113 is specially fan 114.In engine in present embodiment Enclosed hood 112 is added on 11, at least part part of engine 11 is arranged in enclosed hood 112, and in enclosed hood 112 two Gas channel 111 is opened up on relative surface, airflow speed increasing device 113 is set in gas channel 111, can speed up gas channel Flow rate of gas in 111, quickly engine 11 is radiated.And because airflow speed increasing device 113 is arranged on enclosed hood In 112, according to air quantity air exchanging rate formula：N=N*Q/V, wherein n represent rate of ventilation in the unit interval, and N represents radiator fan 114 quantity, Q represent the air quantity of separate unit fan 114, V representation space volumes, it can be seen that the number of fan 114 and type is being determined Number, and in the case of the fixation of the air quantity of separate unit fan 114, spatial volume is smaller, and the speed of ventilation is faster, and temperature control responds Faster, the efficiency of radiating is also higher.

Specifically, engine 11 is provided with heat abstractor, and heat abstractor is distributed on the cylinder head outer wall of engine 11, this reality Apply in mode, heat abstractor specifically refers to fin, and fin is the main thermal component of the cylinder head of engine 11, and engine 11 is right Outer scattering heat is mainly with fin progress is crossed, and therefore, the red enclosed hood 112 of present embodiment is located at the cylinder head of engine 11 On, namely cover sets and on the fin of engine 11, but engine 11 is arranged at the part not limited to this in enclosed hood 112, In some selective embodiments, the entirety of engine 11 can be arranged in enclosed hood 112.

Enclosed hood 112 is made up of carbon plate of the connected mode of Tenon, and the material that enclosed hood 112 is made is not limited to This, according to the difference of concrete application scene, the material of enclosed hood 112, which is made, to be：Plastics, metal or metal alloy etc.. The mode that is made of enclosed hood 112 is also not limited to Tenon, and according to the difference of concrete application scene, the mode of enclosed hood 112 is made Can also be：Integral casting forming, 3D printing shaping or gluing shaping.

It is pointed out that the enclosed hood 112 in the present embodiment is only to surround a part in the surrounding of engine 11 and open The confined space put, closed be wrapped to form of engine 11 is not completely cut off into space in literal meaning.

Referring to Fig. 6, Fig. 6 is second of embodiment structural representation of the present embodiment engine heat dissipating device.

As shown in fig. 6, in some selective embodiments, engine 11 is provided with bent axle；At least part of engine 11 Structure is located in enclosed hood 112, and enclosed hood 112 offers gas channel 111 at least one set of relative surface, so that airhood Interior formation cross-ventilation；Fan 114 is provided with rotating shaft, and fan 114 is arranged in gas channel 111, cuts and promotes by rotating Air moves in one direction, the air in gas channel 111 is formed positive and negative pressure difference, the sky in speedup gas channel 111 Gas convection velocity；The one end of transmission device 115 is connected on the bent axle of engine 11, and the other end of transmission device 115 is connected to wind In the rotating shaft of fan 114, bent axle drives fan 114 to rotate by tumbler.Above-mentioned embodiment on engine 11 by adding If enclosed hood 112, at least part part of engine 11 is set to be arranged in enclosed hood 112, and relative in enclosed hood 112 two Gas channel 111 is opened up on surface, fan 114 is set in gas channel 111, can speed up the gas stream in gas channel 111 Dynamic speed, quickly radiates to engine 11.And because fan 114 is arranged in enclosed hood 112, spatial volume is smaller, changes The speed of gas is faster, and temperature control responds faster, and the efficiency of radiating is also higher.Meanwhile transmission device is passed through by engine 11 115 drive fans 114 are operated, and without being driven fan 114 by motor and battery, engine 11 has been simplified with this The weight of heat abstractor, the electricity for making to store in battery are used to drive multi-rotor aerocraft to fly, and extend multi-rotor aerocraft Flying distance.Concentration radiating is carried out to the cylinder head of engine 11, not only realizes the high efficiency and heat radiation to engine 11, meanwhile, Due to only carrying out concentration radiating to cylinder head part, the heat dissipation region that fan 114 is directed to, which declines to a great extent, makes the chi of the blade 21 of fan 114 Very little reduction, the load of engine 11 is then reduced, effectively raise the load of aircraft.

In some selective embodiments, rotor craft also includes：Undercarriage (not shown), undercarriage are connected to flight The bottom of device body 1.Undercarriage is a kind of protection device of multi-rotor aerocraft, for being prevented when multi-rotor aerocraft is rising and falling The rotor or body of rotor horn directly contact with ground, cause the damage of rotor craft.Or the more rotor flyings of protection Fallen when device occurs unexpected in flight course ground when impulsive force.

Referring to Fig. 7, Fig. 7 is the present embodiment pitch mechanism schematic diagram.

As shown in fig. 7, in some selective embodiments, rotor driver 2 includes：Carrier member 22, actuator 23, bridgeware 24th, rotary shaft 25, displacement piece 26 and roll-setting gear 28.Wherein, carrier member 22 is connected to rotor horn end.Actuator 23 is set The driving force rotated along default circumferential paths is produced after predeterminated voltage in carrier member 22, is applied；Bridgeware 24 is connected to driving On part 23, follow the rotation of actuator 23 and move, and the driving force that actuator 23 is rotated along default circumferential paths is converted to Linear motion；The one end of rotary shaft 25 is arranged in carrier member 22, and the other end of rotary shaft 25 is hanging, and the one end of rotor driver 2 is with turning The hanging one end rotation connection of moving axis 25；Displacement piece 26 is sleeved in rotary shaft 25 and is connected with bridgeware 24, with bridgeware 24 Moved along a straight line along rotary shaft 25, and the position that displacement piece 26 contacts with tumbler rotates with rotary shaft 25；Roll-setting gear 28 One end is connected in displacement piece 26, and the other end of roll-setting gear 28 is connected with the side wall of rotor driver 2, and roll-setting gear 28 is with displacement Rotor driver 2 is driven to be rotated relative to rotary shaft 25 when part 26 is moved along a straight line.By the way that actuator 23 is placed on into load The surface of body part 22, and the rotary power of actuator 23 is converted to by linear motion by bridgeware 24, then turned by being sleeved on The linear motion of bridgeware 24 is transferred on the roll-setting gear 28 being connected with rotor driver 2 by the displacement piece 26 on moving axis 25, by It can either be rotated in displacement piece 26 with rotary shaft 25, and can is enough to be moved along a straight line with bridgeware 24, therefore can be in rotor driver 2 Feather adjustment is carried out in the state of rotation, because the transmission of the driving force to actuator 23 is passed by rigid structure Pass, therefore, it is possible to make the motion of actuator 23 sensitivity for carrying out, adding pitch-variable system synchronous with feather adjustment, improve Control accuracy.

Specifically, specifically, carrier member 22 is to be arranged on the rotor arm (not shown) end of rotor craft, for carrying Rotor motor (not shown), rotary shaft 25 and rotor.In present embodiment, carrier member 22 is configured to half field pattern structure, carrier Part 22 is fixed by screws in rotor arm end.The concrete structure of carrier member 22 is not limited to this, according to concrete application scene Difference, the structure of carrier member 22 can be circular (being not limited to), ellipse or polygon etc..

Fig. 8, Fig. 9 are referred to, Fig. 8 is the concrete structure schematic diagram of the present embodiment actuator rocking arm；Fig. 9 drives for the present embodiment The concrete structure schematic diagram of moving part steering wheel.

As shown in Figure 8 and Figure 9, actuator 23 includes：Steering wheel 232 and rocking arm 231；Steering wheel 232 is arranged on carrier member 22 On the surface of the side of rotary shaft 25, steering wheel 232 is provided with output shaft；The one end of rocking arm 231 is connected on output shaft, rocking arm 231 other end is located in default axial path, and rocking arm 231 connects positioned at one end of circumferential paths and the rotating shaft of bridgeware 24 Connect, the output shaft band motion rocker arm 231 of steering wheel 232 is rotated along default circumferential paths.

Referring to Fig. 10, Figure 10 is the present embodiment pitch-variable system transverse direction face sectional view.

As shown in Figure 10, bridgeware 24 includes：Connecting rod 241, lever 242 and connector 243, the one end of connecting rod 241 and rocking arm 231 are located at one end rotating shaft connection of circumferential paths, and the other end of connecting rod 241 stretches out displacement aperture, and connecting rod 241 turns with rocking arm 231 It is dynamic to be moved along a straight line along displacement aperture.One end bearing pin of lever 242 is connected to bearing part surface, the other end and connecting rod of lever 242 241 rotating shafts are connected, and lever 242 is driven along bearing pin by connecting rod 241 and rotated；One end rotating shaft of connector 243 is connected to lever On 242, the other end of connector 243 is connected with displacement piece 26, and connector 243 is done with the rotation of lever 242 in vertical direction Linear motion.

In some selective embodiments, to ensure the uniformity for the stress of displacement piece 26 being connected with bridgeware 24, carrying Two levers 242 are set on body part 22, and two levers 242 are fixed in carrier member 22 by bearing pin, and two levers 242 are symmetrical Place, two levers 242 are linked together with one end that connecting rod 241 is connected by connecting shaft, the loop configuration suit of connecting rod 241 In the centre position of connecting shaft.When connecting rod 241 moves, two levers 242 are synchronous to do movement in a curve around by the center of circle of bearing pin.

Connector 243 is specially field shape connecting plate, and one end of connecting plate is connected to the centre position of lever 242, connecting plate The other end be fixedly connected with displacement piece 26, the centre position of lever 242 offers axis hole (not identifying), connecting plate and lever The position of 242 connections forms jack-post (not identifying), and jack-post is rotatably coupled in axis hole.In some selective embodiments, Miniature bearing is connected with jack-post, outer ring and the axis hole of miniature bearing are interference fitted.Connecting plate is fixedly connected with displacement piece 26, thick stick When bar 242 does arcuate movement with connecting rod 241, connecting plate drives displacement piece 26 to move along a straight line.

Figure 11 and Figure 12 are referred to, Figure 11 is the structural representation of displacement piece displacement outer shroud；Figure 12 is in displacement piece displacement The structural representation of ring.

As is illustrated by figs. 11 and 12, displacement piece 26 includes：(figure is not for displacement outer shroud 261, displacement inner ring 262, pitch bearing Show) it is sleeved on rotary shaft 25 with sleeve (not shown), displacement outer shroud 261, displacement inner ring 262 with pitch bearing and holds；Connection Part 243 is fixedly connected on displacement outer shroud 261, and displacement outer shroud 261 moves along a straight line with connector 243 along rotary shaft 25；Displacement Bearing is arranged on inside displacement outer shroud 261, and is interference fitted with displacement outer shroud 261, and pitch bearing does straight line with displacement outer shroud 261 Motion；Displacement inner ring 262 is arranged inside pitch bearing, and is interference fitted with the inner ring of pitch bearing, and roll-setting gear 28 connects In displacement inner ring 262, displacement inner ring 262 moves along a straight line with pitch bearing.Sleeve set is in rotary shaft 25, and the one of sleeve End is connected in displacement inner ring 262, and the other end of sleeve is connected with roll-setting gear 28, and sleeve rotates with rotary shaft 25, and covariant Moved along a straight line away from inner ring 262 along the direction of rotary shaft 25.

Figure 13 and Figure 14 are referred to, Figure 13 is the present embodiment rotor driver with rotating spindle combine structure schematic diagram；Figure 14 is The present embodiment propeller hub structural representation.

As shown in Figure 13 and Figure 14, the hanging one end end of rotary shaft 25 is provided with propeller hub 251, is opened up in the side wall of propeller hub 251 Fixing threaded hole 252, standing screw 253 is installed in fixing threaded hole 252, rotor driver 2 is rotatably coupled to standing screw 253 On.

Propeller hub 251 is integrally fixed at the part that 25 hanging one end of rotary shaft is used to fix rotor driver 2, and propeller hub 251 passes through spiral shell Nail is fixed on the hanging one end of rotary shaft 25, can synchronize high-speed rotation with rotary shaft 25.251 two relative sides of propeller hub Two fixing threaded holes being located along the same line 252 are offered on wall, standing screw 253 is installed in fixing threaded hole 252, it is fixed The one end of screw rod 253 is inserted into the other end in fixing threaded hole 252 and stretched out outside fixing threaded hole 252.Rotor driver 2 is rotatably coupled to Standing screw 253 stretches out one end of fixing threaded hole 252.

Rotor driver includes：Oar folder 271.Mounting hole is offered on oar folder 271, mounting hole is interior at least provided with a roll adjustment axle Hold, mounting hole is set on standing screw 253, and roll adjustment bearing rotates around standing screw 253；Oar presss from both sides 271 side walls and is provided with tune oar Support 272, oar support 272 is adjusted to be connected with roll-setting gear 28.

Figure 15 is referred to, Figure 15 is the present embodiment oar clamping structure schematic diagram.

As shown in figure 15, oar folder 271 is used for the device of fixed blades 21, and 271 one end of oar folder offer U-clamp groove and (do not marked Know), mounting hole (not shown) is opened up on the other end, U-clamp groove is used to install blade 21, and mounting hole is used for the installation of oar folder 271 , it is necessary to which explanation is that the position that standing screw 253 stretches out fixing threaded hole 252 is slide bar on standing screw 253, set in mounting hole There is a roll adjustment bearing, in some selective embodiments, mounting hole can be provided with two roll adjustment bearings.Roll adjustment bearing inner race is set with In one end of standing screw 253, one end that standing screw 253 is connected with oar folder 271 is provided with nut, and the diameter of nut is more than roll adjustment The internal diameter of bearing, oar folder 271 is set to be rotated around standing screw 253.Oar, which presss from both sides protuberance formation in 271 side walls, sizes mixing support, Oar support 272 is adjusted to be connected with displacement inner ring 262 by roll-setting gear 28.The setting of roll adjustment bearing can consolidate oar 271 movings of folder Determine screw rod 253 and rotate more light, reduce the resistance of rotation.

Roll-setting gear 28 includes：Pull bar 281；The one end of pull bar 281 is connected with displacement inner ring 262, the other end of pull bar 281 with The rotating shaft connection of oar support 272 is adjusted, oar folder 271 is driven when pull bar 281 moves along a straight line with displacement inner ring 262 around standing screw 253 Rotated.One end that displacement inner ring 262 is connected with pull bar 281 is provided with U-shaped link slot, and the both sides of link slot open up mounting hole (not shown), the both ends of pull bar 281 are equipped with the connection collar (not identifying), and pull bar 281 is connected the connection of one end with displacement inner ring 262 After collar insertion U-shaped link slot, itself and displacement inner ring 262 are fixed with being connected the screw of the collar by inserting mounting hole, sized mixing Support realizes that rotating shaft connects again by the connection collar of screw and the other end of pull bar 281.In some selective embodiments, draw Bar 281, which is connected with support of sizing mixing in the connection collar of one end, is provided with miniature bearing, to reduce friction when rotating, ensures what is rotated Fluency.

Displacement inner ring 262 with lever 242 rotation along rotary shaft move up and down when, drive pull bar 281 synchronize movement, Due to being connected with support of sizing mixing by rotating shaft when pull bar 281 moves, therefore oar folder 271 can be driven around 253 turns of standing screw It is dynamic, realize that the relative angle of blade 21 on oar folder 271 is published in instalments in regulation with this, have the function that feather.

It should be noted that preferably implementation of the present utility model is given in specification of the present utility model and its accompanying drawing Example, still, the utility model can be realized by many different forms, however it is not limited to the implementation described by this specification Example, these embodiments are not as the extra limitation to the utility model content, there is provided the purpose of these embodiments is made to this reality With the understanding more thorough and comprehensive of new disclosure.Also, above-mentioned each technical characteristic continues to be mutually combined, formed not upper The various embodiments that face is enumerated, it is accordingly to be regarded as the scope of the utility model specification record；Further, to ordinary skill For personnel, it can according to the above description be improved or be converted, and all these modifications and variations should all belong to this practicality newly The protection domain of type appended claims.

Claims (9)

1. A kind of 1. rotor craft, it is characterised in that including：

   Aircraft body；

   Several rotor drivers, several described rotor drivers are connected on the aircraft body, and several described rotors Aircraft is arranged around the aircraft body in dispersion shape；

   Duct, the duct is equipped with several described rotor drivers, is connected with each other between adjacent duct；

   Parachute bucket, the parachute bucket are arranged on the aircraft body, be provided with the parachute bucket parachute and Swelling gasbag, the swelling gasbag are arranged on the parachute bottom of the barrel, are provided between the swelling gasbag and the parachute Dividing plate, the umbrella rope of the parachute are connected on the aircraft body；

   Gas cylinder, the gas cylinder are arranged on the aircraft body, and the gas cylinder passes through control valve and institute Swelling gasbag connection is stated, so that the parachute is ejected the parachute by the swelling gasbag when control valve is opened Bucket.
2. 2. rotor craft according to claim 1, it is characterised in that the duct includes：

   Duct circle；

   Duct retainer ring, the duct Fixing shrink ring are interference fitted on the duct circle and with the duct circle；

   The duct retainer ring is arranged on the rotor driver.
3. 3. rotor craft according to claim 2, it is characterised in that one end of the cross section of the duct circle and two Seamlessly transit to form arc end between side wall, it is linear between the end points of the duct circle cross section other end and wherein a side wall Transition, seamlessly transitted between the end points and another side wall.
4. 4. rotor craft according to claim 1, it is characterised in that several described rotor drivers include：Several Rotor horn；

   Attachment means wherein are connected between any one rotor horn at least one rotor horn adjacent thereto, so that described Triangle force structure is formed between any one rotor horn at least one rotor horn adjacent thereto and the attachment means.
5. 5. rotor craft according to claim 1, it is characterised in that the rotor craft also includes：

   Engine, the engine are arranged on the aircraft body, the engine by transmission device with it is described some Individual rotor driver connection；

   Several fuel tanks, several fuel tanks rule are distributed on the aircraft body, and several described fuel tanks are logical Cross oil pipe to be connected with the engine, answer fuel altogether to the engine jointly.
6. 6. rotor craft according to claim 1, it is characterised in that the rotor craft also includes medicine-chest, described Medicine-chest includes：

   Casing, the hollow formation cavity volume of box house；

   Insulating course, the cavity volume is interior to be provided with some insulating courses, and some insulating courses will on the direction of growing crosswise of the casing The cavity volume, which is divided into several, to be prevented swinging liquid space, and the insulating course is configured to flow-guiding structure, the center of the flow-guiding structure Liquid-leaking nozzle is offered, so that the anti-liquid one-way flowing swung in liquid space.
7. 7. rotor craft according to claim 5, it is characterised in that the rotor craft also includes：

   Enclosed hood, at least part structure of the engine are located in the enclosed hood, and the enclosed hood is at least one set of relative Gas channel is offered on surface, so as to form cross-ventilation in the enclosed hood；

   Airflow speed increasing device, the airflow speed increasing device is arranged in the gas channel, by cutting and promoting air along one Individual direction motion, makes the air in the gas channel form positive and negative pressure difference, the cross-ventilation described in speedup in gas channel Speed.
8. 8. rotor craft according to claim 7, it is characterised in that the engine is provided with bent axle, the air-flow Speeder is provided with rotating shaft, and the bent axle is connected with the rotating shaft by transmission device, and described transmission device one end is connected to On the bent axle of the engine, the other end of the transmission device is connected in the rotating shaft of the airflow speed increasing device, the song Axle drives the airflow speed increasing device by the transmission device.
9. 9. rotor craft according to claim 1, it is characterised in that the rotor craft also includes：

   Undercarriage, the undercarriage are connected to the aircraft body bottom.