CN208611786U - A kind of unitized anti-crash fixed-wing aeromodelling airplane of fuselage - Google Patents

Abstract

The utility model discloses a kind of unitized anti-crash fixed-wing aeromodelling airplane of fuselage, aircraft is made of body, the big module of avionics power plant module two.Body includes upper fuselage, lower fuselage, wing, vertical tail structure, quick despatch magnetic mechanism, the center of gravity of body is additionally provided with graduation mark, the avionics power plant module includes main mounting bracket, quick despatch magnetic mechanism, steering engine, first push-pull rod, second push-pull rod, flight control flaps, electron speed regulator, receiver, battery, nose-gear, main landing gear, engine and propeller, the engine is mounted on main mounting bracket two sides, the flight control flaps are symmetrical bi-wing configuration, the flight control flaps are mounted in main mounting bracket, and the bi-wing configuration of the flight control flaps is located at main mounting bracket two sides, the main mounting bracket is fixedly mounted on body along the center of gravity graduation mark of the body.The utility model aeromodelling airplane has the advantages that easy-maintaining debugging, Yi Genghuan fuselage, maintenance and time cost are low.

Description

A kind of unitized anti-crash fixed-wing aeromodelling airplane of fuselage

Technical field

The utility model relates to a kind of aeromodelling airplanes, more particularly to a kind of unitized anti-crash fixed-wing model plane of fuselage Aircraft.

Background technique

Fixed-wing model plane are referred to generating the thrust advanced or pulling force using power device, be generated by the fixation wing of fuselage Lift, in the aircraft that cannot be manned for overweighting air of endoatmosphere flight.Usually using on wireless device control model plane Flight control rudder face (hereinafter referred to as fly control face) deflection, to generate control moment, change aeromodelling airplane by the intention of operator Become flight attitude.But the flexibility of aircraft is two aspects contradicted with the stability of aircraft, and the aircraft the stable more does not allow Easy active manipulation.Especially aeromodelling airplane many places are strong in the air-flow variation in 100 meters of near-earth conditions below, this altitude range Strong, aircraft easily change of flight posture due to flow perturbation, if partially long from the steady time for replying posture, aircraft is likely to do not having also It is just born before replying flight attitude.Although electronic stability augmentation technology at this stage substantially increases the stability of flight, electricity The effect that son increases steady technology is limited, if encountering strong disturbance, aircraft also cannot keep stabilization.In addition electronic stability augmentation can not gram Artificial operation error is taken, can still result in air crash.Though the toughness material of anti-crash can be used to improve the anti-of aircraft itself Crash ability, but material toughness itself is limited, still can be broken and fracture under severe impact, it can not be substantially to aircraft sheet Body plays a protective role.

Generally speaking, from " murphy's law " (Murphy's Law): Anything that can go wrong Will go wrong.: " everything malfunctions whenever possible, that is just bound to malfunction." model plane there are it is born a possibility that, then It is just bound to born.And born buffer capacity is insufficient, will damage aircraft.The winged control face peace of existing overwhelming majority aeromodelling airplane On wing, tailplane and vertical tail, be connected structure with fuselage.And it controls steering engine and is also contained in wing, horizontal tail It on the wing, vertical tail or fuselage, and is connect by push-pull rod and hinge with winged control face, to realize the control to winged control face.If Model plane collide, then main easily to generate destruction to wing and fuselage, when repairing to wing or fuselage, it is necessary to dress The structures such as the control steering engine connecting rod on Wing-Body Configurations remove one by one, and take a significant amount of time steering engine, and governor starts Machine, gyroscope receiver, battery etc. equipment are mounted on new fuselage wing, and are needed again to winged control face setting angle It is debugged.It is just only able to achieve perfect flight after accurately debugging and flying control, once intermediate so more installation and debugging Step has any flaw, can result in aircraft and crashes again.For the fixed-wing model plane that crash accident often occurs, often Secondary crash, which results in model plane user and needs to consume a large amount of time, repairs to aircraft and flies the adjustment again of control face, or even sometimes It may require that the entire fuselage of replacement even entire model plane, cause a large amount of economic loss.

And aeromodelling airplane model is numerous on Vehicles Collected from Market, although engine, electron speed regulator, and receiver, steering engine, gyro Instrument, modularization and the generalization of the main components such as remote controler, but fuselage, the big component such as wing only realize modularization, and And do not have versatility.For example, the airframe and wing of this model, cannot on another airplane, if It loads onto, is unable to stabilized flight.If airplane hobbyist is caused to want to collect a variety of aircrafts, aeromodelling airplane can only be directly bought Whole (including all devices in aircraft), seriously limits collection of the airplane hobbyist to aircraft.

Further, since model plane often land by violence landing or again, landing gear structure is often subject to huge impact, holds very much Frangibility or deformation seriously affect the service life of aeromodelling airplane.

Summary of the invention

The utility model provides a kind of unitized anti-crash fixed-wing aeromodelling airplane of fuselage, at least to solve existing skill Aeromodelling airplane is not easy to repair in art debugs, is not easy to replace fuselage, the maintenance cost that air crash occurs and the problem that time cost is high

The utility model provides a kind of unitized anti-crash fixed-wing aeromodelling airplane of fuselage, including body, avionics move Power module and quick despatch magnetic mechanism, before the center of gravity of the aeromodelling airplane is located at the aeromodelling airplane aerodynamic centre Side.

Further, the body includes fuselage, wing, vertical tail, and the center of gravity of the body is additionally provided with graduation mark, The avionics power plant module includes main mounting bracket, steering engine, the first push-pull rod, the second push-pull rod, flight control flaps, electronic speed regulation Device, receiver, battery, nose-gear, main landing gear, engine and propeller, the engine are mounted on main mounting bracket two Side, the propeller are connected with engine, and the center of gravity of aeromodelling airplane is overlapped with motor power line, and the nose-gear is led It falls frame and is mounted on main mounting bracket bottom, the steering engine is mounted in main mounting bracket, and the flight control flaps are symmetrical double Wing structure, the flight control flaps are mounted in main mounting bracket, and the bi-wing configuration of the flight control flaps is located at hair Motivation two sides, the steering engine are connected by the first push-pull rod, the second push-pull rod with flight control flaps, the main mounting bracket along The center of gravity graduation mark of the body is fixedly mounted on body, and the battery center of gravity is overlapped with aeromodelling airplane center of gravity.

Further, the wing is selected from wing or middle aspect ratio wing or tool with high aspect ratio, high lift-drag ratio There is the wing of low aspect ratio, big rear slightly angle, the wing and body have fixed installation angle, and the propeller is selected from two leaves One of major diameter fine pitch propeller, leafy minor diameter high pitch propeller or middle diameter high pitch propeller, the boat The aerodynamic centre of mould aircraft and the relative position of aeromodelling airplane center of gravity are fixed.

Further, the electron speed regulator is connected with engine, the receiver respectively with electron speed regulator, steering engine phase Even, the battery is connected with electron speed regulator.

Further, the avionics power plant module is additionally provided with head buffer.

Further, the head buffer is anti-crash carbon fiber buffer bar, the anti-crash carbon fiber buffer bar Including carbon fiber shock structure, shell, damping fork, elastic shock attenuation cushion rubber, the pilot hole of perforation, the carbon fiber are equipped in the shell Dimension shock structure inserts in the pilot hole of shell, and the carbon fiber shock structure and damping fork are connected, and with positioned at shell one end Damping fork is connected, and one end that the elastic shock attenuation cushion rubber is pitched with damping fork, shell far from damping respectively is connected.

Further, the nose-gear includes pedestal, steering fork, buffering pivoted arm, wheel, elastomer, the wheel peace Mounted in buffering pivoted arm bottom, the steering fork includes top plate, left plate, right side plate, bolt, the top plate respectively with left plate, Right side plate is connected, and the left plate, right side Board position are opposite, and first through hole, second are respectively equipped on the left plate, right side plate Through-hole, the bolt are fixed on first through hole, in the second through-hole, and the buffering pivoted arm is mounted on steering fork by bolt, institute Base bottom is stated equipped with lower shaft, the pedestal is connected by lower shaft with the top plate of steering fork, and the buffering pivoted arm top passes through bullet Property body is connected with steering fork or pedestal.

Further, the aeromodelling airplane further includes quick despatch magnetic mechanism, and the quick despatch magnetic mechanism includes First magnetic substance, the second magnetic substance and " L " type hook；First magnetic substance is fixed on the downside of body；Second magnetic substance It is fixed on the upside of avionics power plant module, one end of " L " the type hook is vertically fixed on the upside of avionics power plant module, and described " L " type hook is mounted in front of the second magnetic substance, is additionally provided on the downside of the body and is linked up with the groove to match with " L " type, described When " L " type hook is engaged in the trench, the first magnetic substance can carry out magnetic be bonded with the second magnetic substance.

Further, there is jack, the lower shaft of the pedestal passes through the top plate phase of jack and steering fork on the top plate Even, the steering fork can be rotated relative to pedestal in level angle.

Further, the elastomer is cushion rubber, and the cushion rubber is connected with lower shaft, buffering pivoted arm upper end respectively.

Further, the buffering pivoted arm includes buffering pivoted arm top, buffering pivoted arm lower part, the buffering pivoted arm top Length ratio with buffering pivoted arm lower part is 1:2 ~ 1:7, and the buffering pivoted arm top is bending knot relative to buffering pivoted arm lower part Structure, and the steering fork is connected with the upper end of buffering pivoted arm lower part.

Further, quick despatch magnetic mechanism is housed, it is magnetic that the main mounting bracket leads to quick despatch on the body Mechanism is fixed on organism bottom.

Further, the battery is rechargeable battery.

Compared with prior art, by engine, receiver, governor, steering engine, undercarriage, flight controls the utility model Rudder etc. assembles an integral module, forms unitized avionics power plant module, does not need to be debugged again when replacing fuselage, Effectively save a large amount of install debug times.Meanwhile body, wing and vertical tail are integrally formed by the utility model Module, the characteristics of reaching rapid integral replacing itself, and the fuselage of different styles can share a set of avionics power plant module, navigate Mould fan need to only buy an avionics power plant module, reach the mesh for possessing multi rack model plane by replacing the fuselage of different styles , it is effectively saved great amount of cost, and when air crash accident occurs, airplane hobbyist only needs the graduation mark being aligned on fuselage will Avionics power plant module and fuselage are attracted the replacement that fuselage can be completed, and do not need installation and debugging large number of equipment, effectively increase Efficiency is replaced, plenty of time cost has been saved.In addition, the utility model is by flight control flaps and the machine for being easy to happen damaged in collision Flight control flaps from being mounted on avionics power plant module, and flight control flaps is made to be in the tail portion of aircraft, when falling by status When machine needs replacing fuselage, since flight control flaps are there are also avionics power plant module and undamaged (most most ruins accident all It is that plane nose contacts to earth), therefore, as long as integral installation on new fuselage, simplifies the installation steps again of aeromodelling airplane, section Save the plenty of time.

Detailed description of the invention

Fig. 1 is the utility model embodiment structural schematic diagram；

Fig. 2 is the utility model embodiment avionics power plant module structural schematic diagram；

Fig. 3 is the utility model embodiment system control logic schematic diagram；

Fig. 4 is the utility model embodiment anti-crash carbon fiber buffer bar schematic view of the mounting position；

Fig. 5 is the utility model embodiment anti-crash carbon fiber buffer bar structural schematic diagram；

Fig. 6 is the utility model embodiment nose-gear structural schematic diagram；

Fig. 7 is the structural schematic diagram of the big voyage configuration aeromodelling airplane of the utility model embodiment；

Fig. 8 is the structural schematic diagram of the utility model embodiment high speed configuration aeromodelling airplane；

Fig. 9 is the structural schematic diagram of the big quick configuration aeromodelling airplane of the utility model embodiment；

Figure 10 is the structural schematic diagram of the utility model embodiment aeromodelling airplane quick despatch magnetic mechanism partial structurtes.

Specific embodiment

In order to make those skilled in the art better understand the scheme of the utility model, below in conjunction with the utility model reality The attached drawing in example is applied, the technical scheme in the utility model embodiment is clearly and completely described, it is clear that described Embodiment is only the embodiment of the utility model a part, instead of all the embodiments.Based on the reality in the utility model Example is applied, every other embodiment obtained by those of ordinary skill in the art without making creative efforts is all answered When the range for belonging to the utility model protection.

It should be noted that the specification and claims of the utility model and term " first " in above-mentioned attached drawing, " second " etc. is to be used to distinguish similar objects, without being used to describe a particular order or precedence order.The utility model can To achieve the purpose that converting aircraft air force configuration, theoretically the utility model has by installing different fuselage and wing There are infinite a variety of air force configurations.

The utility model embodiment discloses a kind of unitized anti-crash fixed-wing aeromodelling airplane of fuselage, as shown in Figure 1, The aeromodelling airplane includes body 1, avionics power plant module 2, and the aerodynamic centre of the aeromodelling airplane is located at and aeromodelling airplane The front side of center of gravity.

Optionally, the body 1 includes body, wing, vertical tail, and the center and center of gravity of the body 1 are additionally provided with Graduation mark, the avionics power plant module 2 include main mounting bracket 21, steering engine 31, the first push-pull rod 23, the second push-pull rod 24, fly Row control flaps 25, electron speed regulator 32, receiver 32, battery 22, nose-gear 27, main landing gear 28, engine 29 and spiral Paddle 30, the engine 29 are mounted on main 21 two sides of mounting bracket, and the propeller 30 is connected with engine 29, aeromodelling airplane Aerodynamic centre is overlapped with motor power line, and the nose-gear 27, main landing gear 28 are mounted on main 21 bottom of mounting bracket Portion, the steering engine are mounted in main mounting bracket 21, and the flight control flaps 25 are symmetrical bi-wing configuration, the flight control Rudder 25 is mounted in main mounting bracket 21, and the bi-wing configuration of the flight control flaps 25 is located at 29 two sides of engine, institute It states steering engine to be connected by the first push-pull rod 23, the second push-pull rod 24 with flight control flaps 25, the main mounting bracket 21 is along institute The center and center of gravity graduation mark for stating body 1 are fixedly mounted on body, and 22 center of gravity of battery is overlapped with aeromodelling airplane center of gravity.

Particularly, the wing includes multiple wings of a variety of configurations, and multiple wings of a variety of configurations can be optional A body is combined into first, being installed together with upper fuselage, lower fuselage.The wing is including (but not limited to) following several: Wing with high aspect ratio, the wing of high lift-drag ratio or middle aspect ratio wing or with low aspect ratio, big rear slightly angle, the machine The wing and body have fixed installation angle, and the propeller 30 is selected from two leaf major diameter fine pitch propellers, leafy minor diameter One of high pitch propeller or middle diameter high pitch propeller, the aerodynamic centre of the aeromodelling airplane and aeromodelling airplane The relative position of center of gravity is fixed.

Particularly, quick despatch magnetic mechanism as described in Figure 10 includes the first magnetic substance.Second magnetic substance and hook；First Magnetic substance is located above the second magnetic substance；Hook is located in front of magnetic substance；The hook is L-shaped.Quick despatch magnetic mechanism Magnet firm banking is equipped with by: avionics and power plant module respectively, it is fixed in pedestal that magnet is housed, it is also fixed on upper fuselage Magnet, and avionics and power plant module front end are equipped with L-shaped structure, and the groove of the upper front fuselage of is constituted.As long as avionics when installation The groove insertion of front fuselage is directed at the L-shaped structure of power plant module front end, then the magnetic on rear end avionics and power plant module Iron is directed at the attracted just assembly of magnet fixed on upper fuselage and completes.Very simple is quick.Used time is less than 5 seconds.

Wherein, as shown in Figure 1, electron speed regulator, receiver, steering engine are integrated in aviation packet 32, and battery 22, aviation packet 32 between nose-gear 27, main landing gear 28, and steering engine passes through the first push-pull rod 23, the second push-pull rod 24 and flight control flaps 25 connect, and realize control of the steering engine to flight control flaps 25.

Such as Fig. 1, though fuselage 1, fuselage 1` are the airframe of a variety of different models, can by with avionics power plant module Combination complete aeromodelling airplane assembling, fast implemented the replacement of airframe 1, avionics power plant module 2 is integrated with except fuselage Remaining outer equipment, and every sub- equipment is all modularization, is conveniently replaceable.

The utility model embodiment by the assembly of avionics power plant module and body as a whole, by ensuring center of gravity Before whole aerodynamic centre, it is ensured that aircraft is able to carry out stabilized flight, effectively avoids crashing.

The utility model embodiment is by being integrally formed module for fuselage, head, wing, vertical tail --- body 1, it can replace rapidly, if body 1 is impaired, old body 1 need to only be removed from avionics power plant module, then by avionics power mould Block is mutually binded with the graduation mark on new body 1, on the one hand can guarantee the center of gravity of new crate position opposite with aerodynamic centre It sets and does not change, so that it is guaranteed that new aircraft stability with higher；29 thrust line of engine and machine of another aspect aircraft The relative position of body does not also change, and from the active flight characteristic for ensuring new aircraft and crate, no change has taken place；Meanwhile The new flight control flaps 25 of aircraft also do not change with the relative position of fuselage, the neutral position and deflection angle of flight control flaps 25 Degree range does not also change, so that it is guaranteed that the control moment of flight control flaps 25 is constant, avoids debugging again to aircraft, really Protecting new aircraft can directly be flown again, and the maintenance and debugging time cost of crashed aircraft can be from pervious several hours to tens A hour does not shorten within five seconds not etc., and maintenance efficiency can be improved thousands of times.

It should be noted that have specific graduation mark on different money fuselages so that avionics power plant module 2 be aligned graduation mark with After fuselage bonding, the center of gravity of entire aircraft is located just at aircraft can be with the position of centre of gravity of stabilized flight, the i.e. sky of aeromodelling airplane Stablize constant in the relative position of aerodynamic center and its center of gravity.Keep the configuration of a variety of body combinations air having the same dynamic Power center and center of gravity.

As shown in fig. 7, being a kind of aeromodelling airplane of big voyage configuration.Fuselage 1 is using high aspect ratio, the machine of high lift-drag ratio The wing, and the wingtip at wing edge has winglet, propeller 30 is two leaf major diameter fine pitch propellers.

For the utility model embodiment by using high aspect ratio, the wing of high lift-drag ratio, improving lift reduces wing load Lotus, and then improve flight pneumatic efficiency.In addition, the utility model embodiment improves model plane by loading high capacity cell Flight.

As shown in figure 8, being a kind of aeromodelling airplane of high speed configuration.Fuselage 1 uses the profound ratio of little Zhan, omits angle, small thickness after big The delta shaped wing of degree, and body is small cross-sectional area body；Propeller 30 is leafy minor diameter high pitch propeller, and battery 22 is Small-capacity cells.

The utility model embodiment uses the profound ratio of little Zhan, omits angle, the delta shaped wing of small thickness, small cross-sectional area machine after big Body effectively reduces flight resistance, and reduces aircraft weight by using small-capacity cells, improves engine jet speed Degree improves flying speed.

As shown in figure 9, for a kind of aeromodelling airplane of big quick configuration.Fuselage 1 is profound than wing using medium exhibition, and middle diameter is big Pitch propeller, small-capacity cells.

The utility model embodiment improves motor power by using middle diameter high pitch propeller, small-capacity cells With thrust ratio, and then make aircraft control sensitivity with higher.

It should be noted that can also stress to improve flight stability using the fuselage 1 with high stability configuration.This Utility model can also make aircraft with more ornamental value and interest by using world's name machine with ornamental value configuration.Or Person does it yourself to design the DIY configuration with various wings to player, and player is made to enjoy the enjoyment created.

The utility model embodiment has been effectively ensured and has started by the way that the center of gravity of aeromodelling airplane to be overlapped with motor power line The nose-up pitching moment that machine thrust generates is zero, it is ensured that aeromodelling airplane is convenient for control.Meanwhile the utility model embodiment is by ensuring not With the installation angle of identical fixation between the wing of isomorphism type and fuselage, prevent the wing of various configurations awing to fuselage Generate additional unbalanced moments, it is ensured that different fuselages can be with normal flight.In addition, the utility model embodiment is by by battery Position of centre of gravity be overlapped with the center of gravity of aircraft entirety, it is ensured that battery when replacing, the center of gravity of aeromodelling airplane will not be because The volume change of battery and change, user can be needed according to practical flight to battery capacity carry out freely be replaced without shadow Ring the variation of aeromodelling airplane center of gravity, it is ensured that the flight stability of aeromodelling airplane.

The utility model embodiment flies engine 29, receiver 32, governor 32, steering engine 31, undercarriage 27,28 Control flaps 25 etc. assemble an integral module, form unitized avionics power plant module 2, do not needed when replacing fuselage again into Row debugging, effectively saves a large amount of install debug times.Meanwhile the utility model embodiment by fuselage, wing, tailplane and The characteristics of vertical tail is integrally formed module, reaches rapid integral replacing itself, and the fuselage of different styles can be total to With a set of avionics power plant module 2, airplane hobbyist need to only buy an avionics power plant module 2, by the machine for replacing different styles Body achievees the purpose that possess multi rack model plane, is effectively saved great amount of cost, and when air crash accident occurs, and airplane hobbyist is only Need to be aligned the graduation mark on fuselage avionics power plant module 2 sticked into fuselage and the replacement of fuselage can be completed, do not need installation with Large number of equipment is debugged, replacement efficiency is effectively increased, has saved plenty of time cost.In addition, the utility model embodiment will fly Row control flaps 25 are separated with the fuselage for being easy to happen damaged in collision, and flight control flaps 25 are mounted on avionics power plant module 2, and Flight control flaps 25 are made to be in the tail portion of aircraft, when generation air crash needs replacing fuselage, since there are also navigate for flight control flaps 25 Electronic power module 2 is simultaneously undamaged, therefore, as long as integral installation, on new fuselage, simplify aeromodelling airplane installs step again Suddenly, the plenty of time is saved.

It should also be noted that the body of various configuration has the profound ratio of different wing exhibition, wing, slightly angle, the upper counterangle, machine afterwards Body sectional area etc., therefore the aircraft of various configuration has different lift coefficients, lift resistance ratio, stability etc..This is practical new Type embodiment only uses an avionics power plant module 2 to allow user's low cost experience by body of changing planes as the core of aircraft The flight characteristics of entirely different aircraft, to improve flight enjoyment.It is upper using, for different demands, can quickly lead to The change that replacement fuselage reaches flight characteristics is crossed, to adapt to specifically need.Especially when needing long airborne period, Change the profound fuselage higher than lift coefficient of bigger exhibition, in this way can be with low throttle slower flight and lift is enough, greatly mention High airborne period, and when needing relatively high speed and sensitivity, it is profound than swept-back wing fuselage to change little Zhan.It in this way can be with There are the relatively high speed of a ship or plane and control sensitivity.If aircraft is born, fuselage can greatly absorb damage energy, so that it is guaranteed that boat Electronic power module 2 it is intact, can fly again rapidly, achieve the effect that save fund cost and time cost.

Particularly, fuselage 1 is impact resistance material, further increases the impact resistance ability of aeromodelling airplane.

Optionally, as shown in figure 3, the electron speed regulator is connected with engine, the receiver respectively with electronic speed regulation Device, steering engine are connected, and the battery is connected with electron speed regulator.

Wherein, as shown in figure 3, battery can be powered to electron speed regulator, steering engine, engine respectively by receiver. Receiver receives radio control signal, and control signal is formed after decoding, and is sent to governor, and governor controls engine and turns Speed.Receiver sends control signals to steering engine, control steering engine rotation simultaneously, and steering engine pulls push-pull rod, controls flight control flaps 25 deflecting facets generate control moment, to control the change of aircraft flight attitude.Avionics power plant module 2 can be in replacement fuselage When overall package, do not need to debug, effectively save a large amount of install debug times.

In flight, as shown in figure 3, user sends control signal to receiver by ground remote control device, pass through receiving Machine realizes the control to governor, steering engine, to reach the control to flight status and flight attitude.

Optionally, as shown in figure 4, the avionics power plant module 2 is additionally provided with head buffer 4.

Particularly, as shown in figure 5, the head buffer 4 is anti-crash carbon fiber buffer bar 4, the anti-crash carbon fiber Tieing up buffer bar 4 includes carbon fiber shock structure 41, shell 42, damping fork 43, elastic shock attenuation cushion rubber 44, is equipped with and passes through in the shell 42 Logical pilot hole 45, the carbon fiber shock structure 41 insert in the pilot hole 45 of shell 42, and the carbon fiber shock structure 41 with Damping fork 43 is connected, and is connected with the damping fork 43 for being located at 42 one end of shell, and the elastic shock attenuation cushion rubber 44 is pitched with damping respectively 43, shell 42 is connected far from one end of damping fork 43.

Wherein, as shown in figure 5, anti-crash carbon fiber buffer bar 4 by carbon fiber shock structure 41, shell 42, damping fork 43 and Several elastic shock attenuation cushion rubbers 44 form, and are located at head front, and carbon fiber shock structure 41 forward extends out.

When aircraft is crashed downwards with head, the carbon fiber shock structure 41 at head contacts to earth at first, carbon fiber shock structure 41 To head internal contraction, so that cushion rubber 54 be pushed to stretch.Cushion rubber generates reversal interlocking relay and carbon fiber bar is prevented to shrink, and realizes to aircraft The deceleration of body quickly reduces the relative velocity of aircraft and ground, it is ensured that fuselage will not generate destruction before fuselage is completely born And deformation, realize the protection to fuselage 1 and avionics power plant module 2.

The impact that the utility model embodiment generates when crashing by using anti-crash carbon fiber buffer bar 4 to small-sized model plane Energy is absorbed, and effective cushioning and protection is played, it is ensured that fuselage 1 and avionics power plant module 2 will not be because crossing large impact And damage, greatly prolong the service life and total flight time of aircraft.In addition, the electronic power module of the utility model embodiment Air China 2 are arranged in fuselage rearward position, especially engine 29 and propeller 30 is all located at aircraft rear end, utilize buffer bar 5 and machine Body absorbs born energy, protects avionics power plant module 2, especially engine 29 to greatest extent, propeller 30, steering engine, flies The elements such as row control flaps 25 are not damaged, the maximized damage for reducing aircraft, it is ensured that aircraft can by replacing fuselage rapidly, Realization is flown again, avoids debugging again.

Optionally, the nose-gear 27 includes pedestal 271, steering fork 272, buffering pivoted arm 273, wheel 274, elastomer 275, the wheel 274 is mounted on buffering 273 bottom of pivoted arm, and the steering fork 272 includes top plate, left plate, right side plate, inserts Pin, the top plate are connected with left plate, right side plate respectively, and the left plate, right side Board position are opposite, the left plate, right side It is respectively equipped with first through hole, the second through-hole on plate, the bolt is fixed on first through hole, in the second through-hole, the buffering pivoted arm 273 are mounted on steering fork 272 by bolt, and 271 bottom of pedestal is equipped with lower shaft, and the pedestal 271 is by lower shaft and turns It is connected to the top plate of fork 272,273 top of buffering pivoted arm is connected by elastomer 275 with steering fork 272 or pedestal 271.

Particularly, as shown in fig. 6, having jack on the top plate, the lower shaft of the pedestal 271 passes through jack and steering fork Top plate be connected, the steering fork 272 can be rotated relative to pedestal 271 in level angle.

Particularly, as shown in fig. 6, the elastomer 275 is cushion rubber 275, the cushion rubber 275 turns with lower shaft, buffering respectively 273 upper end of arm is connected.

Particularly, described slow as shown in fig. 6, the buffering pivoted arm 273 includes buffering pivoted arm top, buffers pivoted arm lower part The length ratio of red switch arm top and buffering pivoted arm lower part is 1:2 ~ 1:7, and the buffering pivoted arm top is relative under buffering pivoted arm Portion is bending structure, and the steering fork 272 is connected with the upper end of buffering pivoted arm lower part.

Wherein, as shown in fig. 6, elastomer 275 is cushion rubber 275 and is linked on the gentle red switch arm 273 of lower shaft.Pedestal 271 It is floating connection between main mounting bracket 21.The card slot for fixed rubber ring 275 is all had on the gentle red switch arm 273 of lower shaft. Steering fork 272 is inserted in the axis of pedestal 271, and steering fork 272 is allowed to carry out left and right turn in the horizontal direction.

It should be noted that elastomer 275 can also be metal spring, and can distinguish when elastomer 275 is metal spring It is fixedly linked with steering fork 272, buffering pivoted arm upper end.

As shown in fig. 6, wheel 274 is buffered pivoted arm under the drive of wheel 274 by impulse force when aeromodelling airplane lands 273 lower part is rotated relative to steering fork 272, makes the buffering pivoted arm top for buffering pivoted arm 273 far from lower shaft, to and to cushion rubber 275 are stretched, and cushion rubber 275 forms reversed elastic force, resist pivoted arm rotation, to generate buffering effect to takeoff and landing.

Steering fork 272 can be transmitted to wheel 274 by buffering pivoted arm 273, make wheel 274 is synchronous to turn to when turning to.

Common model plane nose-gear is often subject to huge impact due to often landing by violence landing or again, it is easy to It fractures or deforms, lose turning function, the utility model embodiment is pushed up pedestal 271 and buffering pivoted arm 273 using elastomer 275 End is connected, and when being impacted, absorbs impact force suffered by nose-gear using elastomer 275, reduces pedestal 271, buffering pivoted arm Impulse force suffered by 273, and then improve the service life of nose-gear 27.In addition, at aircraft Abnormal Landing (born), it is preceding to rise and fall The cushion performance of frame can effectively absorb the moment impact for falling and generating to fuselage, and the stress for mitigating fuselage is concentrated, and reduce born It is damaged caused by aircraft.Meanwhile the utility model embodiment is rotatablely connected by using steering fork 272 with lower shaft, is made Steering fork 272 can carry out left and right turn in the horizontal direction, it is ensured that aircraft has angle regulation function before take-off.

Optionally, quick despatch magnetic mechanism is housed, the main mounting bracket 21 passes through quick despatch magnetic on the fuselage 1 Property mechanism is fixed on 1 bottom of fuselage.

The utility model embodiment reaches prompt user's avionics by the way that quick despatch magnetic mechanism is arranged on the fuselage 1 The effect of 2 installation site of power plant module further facilitates installation of the user to avionics power plant module 2, reduces aeromodelling airplane Assembling and again maintenance difficulty, expand the usable range of aeromodelling airplane.

Optionally, the battery 22 is rechargeable battery.

Optionally, as shown in Figure 10, the aeromodelling airplane further includes quick despatch magnetic mechanism, and the quick despatch is magnetic Mechanism includes the first magnetic substance 51, the second magnetic substance 52 and " L " type hook 53；First magnetic substance 51 is fixed under body 1 Side；Second magnetic substance 52 is fixed on 2 upside of avionics power plant module, and one end of " L " the type hook 53 is vertically fixed on boat 2 upside of electronic power module, and " L " type hook 53 is mounted on 52 front of the second magnetic substance, be additionally provided on the downside of the body 1 with The groove 54 that " L " type hook 53 matches, when " L " the type hook 53 is fastened in groove 54, the first magnetic substance 51 and second Magnetic substance 52 can carry out magnetic fitting.

Wherein, as shown in Figure 10, groove 54 is located at the downside of body 1, and groove 54 be in the first magnetic substance 51 and head it Between.Groove 54 be open it is larger, for L-shaped structure 53 the end L be inserted into, and groove 54 side have indent socket, for L shape knot One end of structure 53 is caught in.

During installation, the groove 54 that the L-shaped structure 53 of 2 front end of avionics power plant module is directed at 1 front end of body need to be only inserted into And it is fixed, then by 51 phase of the first magnetic substance fixed on the second magnetic substance 52 alignment body 1 on the avionics power plant module of rear end It is attracted, completes assembly.

The utility model embodiment is saved traditional gluing mode, is made to body 1 by using quick despatch magnetic mechanism Replacement to become very simple quick, improve replacement efficiency, shorten the used time needed for replacing, for known user, Ke Yi The replacement of body 1 is rapidly completed in time less than 5 seconds.

Finally it should be noted that above embodiments are only to illustrate the technical solution of the utility model rather than limit it System, although the utility model is described in detail referring to above-described embodiment, those of ordinary skill in the art should Understand, technical staff read present specification after specific implementation of the utility model can still be modified or Equivalent replacement, but these are modified or are changed within all without departing from present utility model application accompanying claims protection scope.

Claims (10)

1. a kind of unitized anti-crash fixed-wing aeromodelling airplane of fuselage, which is characterized in that the aeromodelling airplane includes body, boat The center of gravity of electronic power module and quick despatch magnetic mechanism, the aeromodelling airplane is located at the aeromodelling airplane aerodynamic centre Front side.

2. anti-crash fixed-wing aeromodelling airplane according to claim 1, which is characterized in that the body include upper fuselage, Lower fuselage, wing, vertical tail, the center of gravity of the body are additionally provided with graduation mark, and the avionics power plant module includes main installation Bracket, steering engine, the first push-pull rod, the second push-pull rod, flight control flaps, electron speed regulator, receiver, battery, nose-gear, master Undercarriage, engine and propeller, the engine is two, and is separately mounted to main mounting bracket two sides, the propeller It is connected with engine, the nose-gear, main landing gear are mounted on main mounting bracket bottom, and the steering engine is mounted on main installation branch On frame, the flight control flaps are symmetrical bi-wing configuration, and the flight control flaps are mounted in main mounting bracket, and described winged The bi-wing configuration of row control flaps is located at main mounting bracket two sides, the steering engine by the first push-pull rod, the second push-pull rod with Flight control flaps are connected, and the main mounting bracket is fixedly mounted on body along the center of gravity graduation mark of the body, described Battery center of gravity is overlapped with aeromodelling airplane center of gravity, and the center of gravity of the aeromodelling airplane is overlapped with motor power line.

3. aeromodelling airplane according to claim 2, which is characterized in that the wing is selected to be hindered with high aspect ratio, promotion The wing of ratio or middle aspect ratio wing or with low aspect ratio, it is big after slightly one of wing at angle, the wing and upper fuselage, Lower fuselage, which is installed together, is combined into a body, and the wing and body have fixed installation angle, the propeller choosing From one of two leaf major diameter fine pitch propellers, leafy minor diameter high pitch propeller or middle diameter high pitch propeller, The aerodynamic centre of the aeromodelling airplane and the relative position of aeromodelling airplane center of gravity are fixed.

4. aeromodelling airplane according to claim 2, which is characterized in that the electron speed regulator is connected with engine, described Receiver is connected with electron speed regulator, steering engine respectively, and the battery is connected with electron speed regulator.

5. aeromodelling airplane according to claim 2, which is characterized in that the avionics power plant module is additionally provided with head buffering Device.

6. aeromodelling airplane according to claim 5, which is characterized in that the head buffer is anti-crash carbon fiber buffering Bar, the anti-crash carbon fiber buffer bar include carbon fiber shock structure, shell, damping fork, elastic shock attenuation cushion rubber, in the shell Pilot hole equipped with perforation, the carbon fiber shock structure insert in the pilot hole of shell, and the carbon fiber shock structure and damping Fork is connected, and is connected with the damping fork for being located at shell one end, and the elastic shock attenuation cushion rubber is respectively with damping fork, shell far from damping One end of fork is connected.

7. aeromodelling airplane according to claim 2, which is characterized in that the nose-gear includes pedestal, steering fork, buffering Pivoted arm, wheel, elastomer, the wheel be mounted on buffering pivoted arm bottom, the steering fork include top plate, left plate, right side plate, Bolt, the top plate are connected with left plate, right side plate respectively, and the left plate, right side Board position are opposite, the left plate, the right side It is respectively equipped with first through hole, the second through-hole on side plate, the bolt is fixed on first through hole, in the second through-hole, and the buffering turns Arm is mounted on steering fork by bolt, and the base bottom is equipped with lower shaft, and the pedestal passes through the top plate of lower shaft and steering fork It is connected, the buffering pivoted arm top is connected by elastomer with steering fork or pedestal.

8. aeromodelling airplane according to claim 7, which is characterized in that have jack, the bottom of the pedestal on the top plate Axis is connected by jack with the top plate of steering fork, and the steering fork can be rotated relative to pedestal in level angle, the bullet Property body be cushion rubber, the cushion rubber respectively with lower shaft, buffering pivoted arm upper end be connected.

9. aeromodelling airplane according to claim 7, which is characterized in that the buffering pivoted arm includes buffering pivoted arm top, delays Red switch arm lower part, the buffering pivoted arm top and the length ratio for buffering pivoted arm lower part are 1:2 ~ 1:7, the buffering pivoted arm top It is bending structure relative to buffering pivoted arm lower part, and the steering fork is connected with the upper end of buffering pivoted arm lower part.

10. aeromodelling airplane according to claim 1, which is characterized in that the aeromodelling airplane further includes quick despatch magnetism Mechanism, the quick despatch magnetic mechanism include the first magnetic substance, the second magnetic substance and " L " type hook；First magnetic substance It is fixed on the downside of body；Second magnetic substance is fixed on the upside of avionics power plant module, and one end of " L " the type hook is vertically solid Be scheduled on the upside of avionics power plant module, and " L " type hook is mounted in front of the second magnetic substance, be additionally provided on the downside of the body with " L " type links up with the groove that matches, " L " the type hook engaging in the trench when, the first magnetic substance and the second magnetic substance can be into The magnetic fitting of row.