CN108786143A - A kind of unitized anti-crash fixed-wing aeromodelling airplane of fuselage - Google Patents
A kind of unitized anti-crash fixed-wing aeromodelling airplane of fuselage Download PDFInfo
- Publication number
- CN108786143A CN108786143A CN201810542563.1A CN201810542563A CN108786143A CN 108786143 A CN108786143 A CN 108786143A CN 201810542563 A CN201810542563 A CN 201810542563A CN 108786143 A CN108786143 A CN 108786143A
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- Prior art keywords
- wing
- aeromodelling airplane
- fuselage
- pivoted arm
- engine
- Prior art date
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- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims abstract description 34
- 230000005484 gravity Effects 0.000 claims abstract description 32
- 230000007246 mechanism Effects 0.000 claims abstract description 19
- 230000003139 buffering effect Effects 0.000 claims description 44
- 229920001971 elastomer Polymers 0.000 claims description 31
- 239000000126 substance Substances 0.000 claims description 29
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 24
- 239000004917 carbon fiber Substances 0.000 claims description 24
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 24
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 claims description 21
- 230000035939 shock Effects 0.000 claims description 20
- 239000005060 rubber Substances 0.000 claims description 19
- 239000000872 buffer Substances 0.000 claims description 18
- 238000013016 damping Methods 0.000 claims description 16
- 238000009434 installation Methods 0.000 claims description 16
- 239000000806 elastomer Substances 0.000 claims description 12
- 238000005452 bending Methods 0.000 claims description 3
- 230000001934 delay Effects 0.000 claims 1
- 230000005389 magnetism Effects 0.000 claims 1
- 239000007787 solid Substances 0.000 claims 1
- 230000008439 repair process Effects 0.000 abstract description 3
- 230000008859 change Effects 0.000 description 13
- 238000010586 diagram Methods 0.000 description 9
- 230000006378 damage Effects 0.000 description 7
- 230000000694 effects Effects 0.000 description 5
- 238000005516 engineering process Methods 0.000 description 4
- 238000012423 maintenance Methods 0.000 description 4
- 230000033228 biological regulation Effects 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 230000035945 sensitivity Effects 0.000 description 3
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 2
- 230000003416 augmentation Effects 0.000 description 2
- 230000006870 function Effects 0.000 description 2
- 230000007257 malfunction Effects 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 229910052751 metal Inorganic materials 0.000 description 2
- 230000002159 abnormal effect Effects 0.000 description 1
- 238000004026 adhesive bonding Methods 0.000 description 1
- 230000008602 contraction Effects 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 238000007667 floating Methods 0.000 description 1
- 230000001771 impaired effect Effects 0.000 description 1
- 229910052742 iron Inorganic materials 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000008450 motivation Effects 0.000 description 1
- 230000007935 neutral effect Effects 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
- 230000001360 synchronised effect Effects 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
Classifications
-
- A—HUMAN NECESSITIES
- A63—SPORTS; GAMES; AMUSEMENTS
- A63H—TOYS, e.g. TOPS, DOLLS, HOOPS OR BUILDING BLOCKS
- A63H27/00—Toy aircraft; Other flying toys
- A63H27/02—Model aircraft
-
- A—HUMAN NECESSITIES
- A63—SPORTS; GAMES; AMUSEMENTS
- A63H—TOYS, e.g. TOPS, DOLLS, HOOPS OR BUILDING BLOCKS
- A63H27/00—Toy aircraft; Other flying toys
- A63H27/001—Making or assembling thereof, e.g. by folding
-
- A—HUMAN NECESSITIES
- A63—SPORTS; GAMES; AMUSEMENTS
- A63H—TOYS, e.g. TOPS, DOLLS, HOOPS OR BUILDING BLOCKS
- A63H27/00—Toy aircraft; Other flying toys
- A63H27/14—Starting or launching devices for toy aircraft; Arrangements on toy aircraft for starting or launching
Abstract
The invention discloses a kind of unitized anti-crash fixed-wing aeromodelling airplane of fuselage, aircraft is made of body, two big module of avionics power plant module.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 both 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 both sides, the main mounting bracket is fixedly mounted on along the center of gravity graduation mark of the body on body.Aeromodelling airplane of the present invention has the advantages that easy-maintaining debugging, easily replacement fuselage, repair and time cost are low.
Description
Technical field
The present invention relates to a kind of aeromodelling airplanes, fly more particularly to a kind of unitized anti-crash fixed-wing model plane of fuselage
Machine.
Background technology
Fixed-wing model plane are referred to generating the thrust advanced or pulling force using power plant, 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, aeromodelling airplane is made to change 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, air crash is can still result in.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, by " murphy's law "（Murphy's Law）Known to：Anything that can go wrong
will go wrong. ：" everything malfunctions whenever possible, that is just bound to malfunction." model plane there is a possibility that it is born, 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 with winged control face by push-pull rod and hinge, to realize the control to flying control face.If
Model plane collide, then main easily to generate destruction to wing and fuselage, when being repaired 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 flying control face setting angle
It is debugged.Perfect flight could be only realized 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 aircraft and flies the adjustment again of control face, or even sometimes
It may require that and replace entire fuselage 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 critical pieces 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.
Invention content
The present invention provides a kind of unitized anti-crash fixed-wing aeromodelling airplanes of fuselage, at least to solve in the prior art
Aeromodelling airplane debugging not easy to repair is not easy to replace fuselage, the maintenance cost that air crash occurs and the problem that time cost is high
The present invention provides a kind of unitized anti-crash fixed-wing aeromodelling airplane of fuselage, including body, avionics power plant module and
Quick despatch magnetic mechanism, the center of gravity of the aeromodelling airplane are located at the front side in the aeromodelling airplane aerodynamic centre.
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 both 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 are low aspect ratio, the big rear wing for omiting angle, the wing with body to there is fixed installation angle, the propeller to be selected from two leaves
One kind in 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 pitch and be 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 plate, bolt, the top plate respectively with left plate,
Right 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 plate
Through-hole, the bolt are fixed on first through hole, in the second through-hole, and the buffering pivoted arm is mounted on by bolt on steering fork, institute
It states base bottom and is 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 top plate phase that the lower shaft of the pedestal passes through 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, the buffering pivoted arm top is that bending is tied 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, the present invention by engine, receiver, governor, steering engine, undercarriage, flight control flaps etc.
An integral module is assembled, unitized avionics power plant module is formed, need not be debugged again when replacing fuselage, effectively
Save a large amount of install debug times.Meanwhile body, wing and vertical tail are integrally formed module by the present invention, are reached
The characteristics of rapid integral replacing itself, and the fuselage of different styles can share a set of avionics power plant module, airplane hobbyist
An avionics power plant module only need to be bought, achievees the purpose that possess multi rack model plane by replacing the fuselage of different styles, effectively
Great amount of cost is saved, and when air crash accident occurs, airplane hobbyist only needs the graduation mark being aligned on fuselage to move avionics
Power module is attracted the replacement that fuselage can be completed with fuselage, does not need installation and debugging large number of equipment, effectively increases replacement effect
Rate has saved plenty of time cost.In addition, the present invention detaches flight control flaps with the fuselage for being easy to happen damaged in collision, it will
Flight control flaps are mounted on avionics power plant module, and flight control flaps is made to be in the tail portion of aircraft, are needed more when air crash occurs
Change planes body when, since flight control flaps also have avionics power plant module and undamaged (most most to ruin accident all be aircraft machine
Head contacts to earth）, therefore, as long as integral installation on new fuselage, simplifies the installation steps again of aeromodelling airplane, when saving a large amount of
Between.
Description of the drawings
Fig. 1 is structural schematic diagram of the embodiment of the present invention；
Fig. 2 is avionics power plant module structural schematic diagram of the embodiment of the present invention；
Fig. 3 is system control logic schematic diagram of the embodiment of the present invention；
Fig. 4 is anti-crash carbon fiber buffer bar schematic view of the mounting position of the embodiment of the present invention；
Fig. 5 is anti-crash carbon fiber buffer bar structural schematic diagram of the embodiment of the present invention；
Fig. 6 is nose-gear structural schematic diagram of the embodiment of the present invention；
Fig. 7 is the structural schematic diagram of the big voyage configuration aeromodelling airplane of the embodiment of the present invention；
Fig. 8 is the structural schematic diagram of high speed configuration aeromodelling airplane of the embodiment of the present invention；
Fig. 9 is the structural schematic diagram of the big quick configuration aeromodelling airplane of the embodiment of the present invention；
Figure 10 is the structural schematic diagram of aeromodelling airplane quick despatch magnetic mechanism partial structurtes of the embodiment of the present invention.
Specific implementation mode
In order to enable those skilled in the art to better understand the solution of the present invention, below in conjunction in the embodiment of the present invention
Attached drawing, technical scheme in the embodiment of the invention is clearly and completely described, it is clear that described embodiment is only
The embodiment of a part of the invention, instead of all the embodiments.Based on the embodiments of the present invention, ordinary skill people
The every other embodiment that member is obtained without making creative work should all belong to the model that the present invention protects
It encloses.
It should be noted that term " first " in description and claims of this specification and above-mentioned attached drawing, "
Two " etc. be for distinguishing similar object, without being used to describe specific sequence or precedence.The present invention can pass through peace
Different fuselage and wing are filled, achievees the purpose that converting aircraft air force configuration, theoretically the present invention has infinite a variety of skies
Aerodynamic force configuration.
The embodiment of the invention discloses a kind of unitized anti-crash fixed-wing aeromodelling airplanes of fuselage, as shown in Figure 1, described
Aeromodelling airplane includes body 1, avionics power plant module 2, and the aerodynamic centre of the aeromodelling airplane is located at and aeromodelling airplane center of gravity
Front side.
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 21 both sides of main 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 21 bottom of main 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 both sides of engine, institute
It states steering engine by the first push-pull rod 23, the second push-pull rod 24 to be connected 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 the 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
It is combined into a body first, being installed together with upper fuselage, lower fuselage.The wing includes（But it is not limited to）It is several below：
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 with body there is fixed installation angle, the propeller 30 to be selected from two leaf major diameter fine pitch propellers, leafy minor diameter
One kind in 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
Respectively by：Avionics is equipped with magnet firm banking with power plant module, is fixed in pedestal and magnet is housed, be also fixed on upper fuselage
Magnet, and avionics is equipped with L-shaped structure with power plant module front end, and the groove of the upper front fuselages of is constituted.As long as avionics when installation
The groove that front fuselage is directed at the L-shaped structure of power plant module front end is inserted into, then rear end avionics and the magnetic on power plant module
The attracted just assembly of fixed magnet is completed on the upper fuselage of iron alignment.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 embodiment of the present invention by the assembly of avionics power plant module and body as a whole, by ensuring that center of gravity is located at
Before whole aerodynamic centre, it is ensured that aircraft can carry out stabilized flight, effectively avoid crashing.
The embodiment of the present invention by fuselage, head, wing, vertical tail by being integrally formed module --- body 1, it can
To replace rapidly, if body 1 is impaired, old body 1 need to only be removed from avionics power plant module, then by avionics power plant module with
Graduation mark on new body 1 mutually binds, and on the one hand can ensure the center of gravity of new crate with aerodynamic centre's relative position not
It changes, so that it is guaranteed that new aircraft has higher stability；29 thrust line of engine of another aspect aircraft and fuselage
Relative position does not also change, from ensuring that the active flight characteristic of new aircraft and crate do not change；Meanwhile it is new winged
The flight control flaps 25 of machine also do not change with the relative position of fuselage, neutral position and the deflection angle model of flight control flaps 25
It encloses and does not also change, so that it is guaranteed that the control moment of flight control flaps 25 is constant, avoid debugging again to aircraft, it is ensured that is new
Aircraft can directly be flown again, and the maintenance and debugging time cost of crashed aircraft can be small from pervious several hours to tens
When do not shorten within five seconds not etc., maintenance efficiency can be improved thousands of times.
It should be noted that having 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
The relative position of aerodynamic center and its center of gravity is stablized constant.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 it is two leaf major diameter fine pitch propellers that the wingtip at wing edge, which has winglet, propeller 30,.
For the embodiment of the present invention by using high aspect ratio, the wing of high lift-drag ratio, improving lift reduces wing load, into
And improve flight pneumatic efficiency.In addition, the embodiment of the present invention improves the boat of aeromodelling airplane by loading high capacity cell
Journey.
As shown in figure 8, being a kind of aeromodelling airplane of high speed configuration.Fuselage 1 uses the profound ratios of little Zhan, and angle, small thickness are omited 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 embodiment of the present invention uses the profound ratios of little Zhan, and angle, the delta shaped wing of small thickness are omited after big, and small cross-sectional area body has
Effect reduces flight resistance, and reduces aircraft weight by using small-capacity cells, improves engine jet velocity, 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 embodiment of the present invention improves motor power and pushes away by using middle diameter high pitch propeller, small-capacity cells
Compare again, and then makes aircraft that there is higher control sensitivity.
It should be noted that can also stress to improve flight stability using with the fuselage 1 of high stability configuration.This
Invention can also make aircraft with more ornamental value and interest by using world's name machine with ornamental value configuration.Or it gives
Player does it yourself to design the DIY configurations with various wings, and player is made to enjoy the enjoyment created.
The embodiment of the present invention has been effectively ensured engine and has pushed away by overlapping the center of gravity of aeromodelling airplane with motor power line
The nose-up pitching moment that power generates is zero, it is ensured that aeromodelling airplane is convenient for control.Meanwhile the embodiment of the present invention is by ensuring various configuration
There is identical fixed installation angle between wing and fuselage, prevent the wing of various configurations from awing being generated to fuselage additional
Out-of-balance force away from, it is ensured that different fuselages can be with normal flight.In addition, the embodiment of the present invention by by the position of centre of gravity of battery with
The center of gravity of aircraft entirety overlaps, it is ensured that battery, when replacing, the center of gravity of aeromodelling airplane will not become because of the capacity of battery
Change and change, user can need on battery capacity be freely replaced without according to practical flight to influence aeromodelling airplane weight
The variation of the heart, it is ensured that the flight stability of aeromodelling airplane.
The embodiment of the present invention controls engine 29, receiver 32, governor 32, steering engine 31, undercarriage 27,28, flight
Rudder 25 etc. assembles an integral module, forms unitized avionics power plant module 2, need not be adjusted again when replacing fuselage
Examination, effectively saves a large amount of install debug times.Meanwhile the embodiment of the present invention is by fuselage, wing, tailplane and vertical tail
The characteristics of being integrally formed module, reaching rapid integral replacing itself, and the fuselage of different styles can share a set of boat
Electronic power module 2, airplane hobbyist need to only buy an avionics power plant module 2, be reached by replacing the fuselage of different styles
The purpose for possessing multi rack model plane is effectively saved great amount of cost, and when air crash accident occurs, airplane hobbyist only needs to be aligned
Avionics power plant module 2 is sticked the replacement that fuselage can be completed in fuselage by the graduation mark on fuselage, and it is a large amount of not need installation and debugging
Equipment effectively increases replacement efficiency, has saved plenty of time cost.In addition, the embodiment of the present invention by flight control flaps 25 with
It is easy to happen the fuselage separation of damaged in collision, flight control flaps 25 are mounted on avionics power plant module 2, and make flight control flaps
25 are in the tail portion of aircraft, when generation air crash needs replacing fuselage, since flight control flaps 25 also have avionics power plant module 2 simultaneously
It is undamaged, therefore, as long as integral installation on new fuselage, simplifies the installation steps again of aeromodelling airplane, when saving a large amount of
Between.
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..The present invention is real
The core that example only uses an avionics power plant module 2 as aircraft is applied, by body of changing planes, keeps user's low cost experience complete
The flight characteristics of different aircrafts, to improve flight enjoyment.It is upper using, it, can be quickly by more for different demands
Body of changing planes reaches the change of flight characteristics, 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 with low throttle slower flight and lift is enough, be greatly improved and stay
The empty time, and when needing relatively high speed and sensitivity, it is profound than swept-back wing fuselage to change little Zhan.There can be ratio in this way
The higher 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 avionics is dynamic
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 replace fuselage
When overall package, need not debug, effectively save a large amount of install debug times.
In flight, as shown in figure 3, user sends control signal by ground remote control device to receiver, 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
It includes carbon fiber shock structure 41, shell 42, damping fork 43, elastic shock attenuation cushion rubber 44 to tie up buffer bar 4, 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 positioned at 42 one end of shell, and the elastic shock attenuation cushion rubber 44 is pitched with damping respectively
43, the one end of shell 42 far from damping fork 43 is connected.
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, to push cushion rubber 54 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 not will produce destruction before fuselage is completely born
And deformation, realize the protection to fuselage 1 and avionics power plant module 2.
The impact energy that the embodiment of the present invention generates when crashing to small-sized model plane by using anti-crash carbon fiber buffer bar 4
It is absorbed, plays effective cushioning and protection, it is ensured that fuselage 1 and avionics power plant module 2 will not be damaged because crossing large impact
It is bad, greatly prolong the service life and total flight time of aircraft.In addition, the electronic power module of Air China of the embodiment of the present invention 2 is arranged in
Fuselage rearward position, especially engine 29 and propeller 30 are all located at aircraft rear end, are absorbed using buffer bar 5 and fuselage
Born energy protects avionics power plant module 2, especially engine 29, propeller 30, steering engine, flight control flaps to greatest extent
25 equal elements are without damage, the maximized damage for reducing aircraft, it is ensured that aircraft can be realized again by replacing fuselage rapidly
Flight, 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 273 bottom of buffering pivoted arm, and the steering fork 272 includes top plate, left plate, right plate, inserts
Pin, the top plate are connected with left plate, right 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 by bolt on steering fork 272, and 271 bottom of the 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, the lower shaft of the pedestal 271 to pass through jack and steering fork on the top plate
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, buffering pivoted arm lower part
The length ratio of red switch arm top and buffering pivoted arm lower part is 1：2~1：7, 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 in lower shaft and eases up on red switch arm 273.Pedestal 271
It is floating connection between main mounting bracket 21.Lower shaft eases up the card slot all having on red switch arm 273 for fixed rubber ring 275.
Steering fork 272 is inserted in the axis of pedestal 271 so that steering fork 272 can carry out left and right turn in the horizontal direction.
It should be noted that elastomer 275 or 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, when aeromodelling airplane lands, wheel 274 is buffered pivoted arm by impulse force under the drive of wheel 274
273 lower part is rotated relative to steering fork 272, makes the buffering pivoted arm top of buffering pivoted arm 273 far from lower shaft, pair 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, so that wheel 274 is synchronized and 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 embodiment of the present invention by pedestal 271 and buffers 273 top phase of pivoted arm using elastomer 275
Even, when being impacted, impact force suffered by nose-gear is absorbed using elastomer 275, reduces pedestal 271,273 institute of buffering pivoted arm
By impulse force, and then improve the service life of nose-gear 27.In addition, in aircraft Abnormal Landing（It is born）When, nose-gear
Cushion performance can effectively absorb the moment impact for falling and being generated to fuselage, mitigate the stress concentration of fuselage, reduce born to flying
Damage caused by machine.Meanwhile the embodiment of the present invention is rotatablely connected by using steering fork 272 with lower shaft, and steering fork 272 is made
Left and right turn can be carried out 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 embodiment of the present invention reaches prompt user's avionics power by the way that quick despatch magnetic mechanism is arranged on the fuselage 1
The effect of 2 installation site of module further facilitates installation of the user to avionics power plant module 2, reduces the assembling of aeromodelling airplane
And maintenance difficulty again, 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
The upside of electronic power module 2, and " L " type hook 53 is mounted on 52 front of the second magnetic substance, 1 downside of the body be additionally provided 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 ends L be inserted into, and groove 54 side have indent socket, for L-shaped knot
One end of structure 53 is caught in.
When mounted, the groove 54 that the L-shaped structure 53 of 2 front end of avionics power plant module need to be only directed at 1 front end of body is inserted into
And it is fixed, then by fixed first magnetic substance, 51 phase on the second magnetic substance 52 alignment body 1 on the avionics power plant module of rear end
It is attracted, completes assembly.
The embodiment of the present invention is saved traditional gluing mode, is made to body 1 more by using quick despatch magnetic mechanism
It is quick that transformation obtains very simple, improves and replaces efficiency, shortens needed for replacing that the used time can be less than 5 for known user
The replacement of body 1 is rapidly completed in the time of second.
Finally it should be noted that the above embodiments are merely illustrative of the technical scheme of the present invention and are not intended to be limiting thereof, to the greatest extent
Invention is explained in detail with reference to above-described embodiment for pipe, it should be understood by a person of ordinary skill in the art that technology
Personnel can still be modified or replaced equivalently the specific implementation mode of the present invention after reading present specification, but this
A little modifications are changed within all without departing from the present patent application accompanying claims protection domain.
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,
The center of gravity of lower fuselage, wing, vertical tail, the body is additionally provided with graduation mark, and the avionics power plant module includes main installation
Holder, 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 both 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 both 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 along the center of gravity graduation mark of the body on 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 one kind slightly in the wing at angle, the wing and upper fuselage,
Lower fuselage, which is installed together, is combined into a body, and the wing has fixed installation angle, the propeller choosing with body
One kind from 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 buffers for anti-crash carbon fiber
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 positioned 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 are mounted on buffering pivoted arm bottom, the steering fork include top plate, left plate, right plate,
Bolt, the top plate are connected with left plate, right 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 by bolt on steering fork, and the base bottom is equipped with lower shaft, the top plate that the pedestal passes through 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 is connected with lower shaft, buffering pivoted arm upper end respectively.
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 are 1 with the length ratio for buffering pivoted arm lower part：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.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810542563.1A CN108786143A (en) | 2018-05-30 | 2018-05-30 | A kind of unitized anti-crash fixed-wing aeromodelling airplane of fuselage |
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| CN201810542563.1A CN108786143A (en) | 2018-05-30 | 2018-05-30 | A kind of unitized anti-crash fixed-wing aeromodelling airplane of fuselage |
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| CN113955075A (en) * | 2021-10-09 | 2022-01-21 | 西安远方航空技术发展有限公司 | Aircraft |
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