CN106986040A - A kind of fixed-wing unmanned plane provided with protection device - Google Patents
A kind of fixed-wing unmanned plane provided with protection device Download PDFInfo
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- CN106986040A CN106986040A CN201611261559.5A CN201611261559A CN106986040A CN 106986040 A CN106986040 A CN 106986040A CN 201611261559 A CN201611261559 A CN 201611261559A CN 106986040 A CN106986040 A CN 106986040A
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
- B64D45/04—Landing aids; Safety measures to prevent collision with earth's surface
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/13—Propulsion using external fans or propellers
- B64U50/14—Propulsion using external fans or propellers ducted or shrouded
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
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- Catching Or Destruction (AREA)
Abstract
The present invention relates to a kind of fixed-wing unmanned plane provided with protection device, preceding pull-type propeller is provided with front fuselage, protection device includes propeller protection device, wingtip protection device, empennage protection device：Propeller protection device is located at the both sides and front of propeller; including skeleton and buffer unit; buffer unit is attached on the outside of skeleton; skeleton includes being located at the first vertical pole, the cross bar in front and second vertical pole on right side on the left of propeller; first vertical pole and second vertical pole one end are fixedly connected on wing; the other end extends forward, is connected with cross bar；Wingtip protection device is located at wing wingtip, including left wing's tip wipes ground piece and the right flank tip wipes ground piece；Empennage protection device is located at the bottom of unmanned plane tailplane.The present invention carries out multi-faceted protection to unmanned plane, it is to avoid impact, scraping damage wing when wingtip and empennage contact to earth, the security of pull-type fixed-wing unmanned plane, reduces maintenance cost, reduce application risk before improving.
Description
Technical field
The present invention relates to unmanned air vehicle technique field, and in particular to a kind of fixed-wing unmanned plane provided with protection device.
Background technology
In recent years, with the development and the reduction of cost of unmanned vehicle technology, fixed-wing unmanned plane is in military, peace
The every field extensive use such as guarantor, traffic, exploration, mapping, meteorology.In military domain, fixed-wing unmanned plane is generally used for height
The investigation of outage speed, strike etc..On civil area, fixed-wing unmanned plane is generally used for taking photo by plane, surveyed and drawn, inspection etc..
The various applications of unmanned plane have different technical requirements.For example, cruise of the unmanned plane of long-range scouting to aircraft
It is required that it is high, and the unmanned plane of landing in the wild requires that aircraft must adapt to simple and crude landing place.For the nothing taken photo by plane and surveyed and drawn
Man-machine load-carrying requirement is shooting tripod head, and the unmanned plane for being used for pesticide spraying then needs big drugloading rate to improve single sortie
Spray area.Although these unmanned planes have different applications and requirement, they have some common performance hopes.For example, big
Load-carrying, short landing distance, impact resistant, low maintenance cost, high security are the desirable characteristics of most of unmanned plane.Fixed-wing without
Man-machine security and maintenance cost is its efficient, key factor of widespread adoption of influence.Preceding pull-type fixed-wing unmanned plane by
It is located at forefront in its propeller, is most susceptible to destruction, and also have necessarily to the personnel around it, other animals and plants
It is dangerous.
The content of the invention
The purpose of the present invention be for it is of the prior art it is not enough there is provided a kind of fixed-wing provided with protection device nobody
Machine, is reasonably protected to fuselage and propeller.
To achieve the above object, the invention discloses following technical scheme：
A kind of fixed-wing unmanned plane provided with protection device, preceding pull-type propeller, protection device bag are provided with front fuselage
Include propeller protection device, wingtip protection device, empennage protection device：
Propeller protection device is located at the both sides and front of propeller, including skeleton and buffer unit, and buffer unit is attached
On the outside of skeleton, skeleton includes being located at the first vertical pole, the cross bar in front and second vertical pole on right side on the left of propeller, and first indulges
Bar and second vertical pole one end are fixedly connected on wing, and the other end extends forward, is connected with cross bar；
Wingtip protection device is located at wing wingtip, including left wing's tip wipes ground piece and the right flank tip wipes ground piece, is separately mounted to
The lower section of left and right wingtip, when aircraft side wing contacts to earth, wipes ground piece and contacts to earth at first；
Empennage protection device is located at the bottom of unmanned plane tailplane, and empennage protection device is that empennage wipes ground piece, works as aircraft
When excessively coming back and the afterbody is contacted to earth, empennage is wiped ground piece and contacted to earth at first.
Further, buffer unit is the foam being attached on skeleton.
Further, left wing's tip wipes ground piece and the right flank tip wipes the streamline of direction of flow when ground piece is along unmanned plane during flying
Type structure；The streamlined structure of direction of flow when empennage wipes ground piece for along unmanned plane during flying.
Further, it is the laminated structure that unmanned plane is connected to by fastener to wipe ground piece.
Further, the unmanned plane also includes front three-point wheel undercarriage, and undercarriage includes nose-gear and master rises and falls
Frame, nose-gear is arranged on the cross bar of propeller protection device, and main landing gear is arranged on fuselage bottom.
Further, the cross bar includes two the first cross bars and the second cross bar for having certain longitudinal separation, nose-gear
Inclined support bar including main support rod and both sides, main support rod one end is fixed on the second cross bar of rear end, two inclined support bars
One end is symmetrically fixed on main support rod, and the other end is fixedly connected with being set in the first cross bar of front end respectively, main support rod, tiltedly
Support bar, the first cross bar, the second cross bar constitute tetrahedral structure.
A kind of fixed-wing unmanned plane provided with protection device disclosed by the invention, has the advantages that：
The present invention carries out multi-faceted protection to unmanned plane, to lower use and maintenance cost.Unmanned plane take-off and landing
Shi Rongyi collides and wipes ground.Except front protection device above, the present invention is also carried out from both sides and afterbody to unmanned plane
Protection, so as to reach the protection in four orientation, it is to avoid impact, scraping damage wing when wingtip and empennage contact to earth, improves preceding drawing
The security of formula fixed-wing unmanned plane, reduces maintenance cost, reduces application risk.
Brief description of the drawings
Fig. 1 a:A kind of agricultural spraying unmanned plane with three sections of aerofoil profiles, propeller protection device.
Fig. 1 b:Fig. 1 b another angle, it is shown that ground is wiped in connection and empennage of the nose-gear with propeller protection device
Piece.
Fig. 2 a：A kind of horizontal tail aerofoil profile.
Fig. 2 b：Another horizontal tail aerofoil profile.
Fig. 3 a：A kind of cross section of propeller protection device.
Fig. 3 b：Another cross section of propeller protection device.
Fig. 4:The double cross bar protection devices of nose-gear.
Fig. 5 a:Three-stage aerofoil profile wing and preposition nozzle.
Fig. 5 b:Three-stage aerofoil profile wing and postposition nozzle.
Fig. 6：Sprinkling system connection figure
Fig. 7：Schematic diagram built in container
Fig. 8：Structure of container schematic diagram
Fig. 9：Shower nozzle, jet pipe connection front view
Figure 10：Another jet pipe, nozzle layout of sprinkler schematic diagram
Figure 11：Aircraft broken away view
Figure 12 a：A kind of wing mounting mechanism
Figure 12 b：Another wing assembling-disassembling structure
Figure 13：A kind of wing-tail supporting rod attachment structure
Figure 14：A kind of empennage assembling-disassembling structure
Figure 15：Anury fixed-wing agricultural spraying unmanned plane with three sections of aerofoil profiles, propeller protection device.
Embodiment
The technical scheme in the embodiment of the present invention will be clearly and completely described below, it is clear that described implementation
Example only a part of embodiment of the invention, rather than whole embodiments.Based on the embodiment in the present invention, this area is common
The every other embodiment that technical staff is obtained under the premise of creative work is not made, belongs to the model that the present invention is protected
Enclose.
The core of the present invention is to provide a kind of fixed-wing unmanned plane provided with protection device, and fuselage and propeller are closed
The protection of reason.
A kind of fixed-wing unmanned plane provided with protection device, preceding pull-type propeller, protection device bag are provided with front fuselage
Include propeller protection device, wingtip protection device, empennage protection device：
Propeller protection device is located at the both sides and front of propeller, including skeleton 408 and buffer unit, buffer unit patch
The outside of skeleton 408 is invested, skeleton 408 includes the first vertical pole 409 on the left of propeller, the cross bar 407 in front and right side
Second vertical pole 411, the first vertical pole 409 and the one end of the second vertical pole 411 are fixedly connected on wing, and the other end extends forward, with horizontal stroke
Bar 407 is connected；
Wingtip protection device is located at wing wingtip, including left wing's tip wipes ground piece 413 and the right flank tip wipes ground piece 415, respectively
Installed in the lower section of left and right wingtip, when aircraft side wing contacts to earth, wipe ground piece and contact to earth at first；
Empennage protection device is located at the bottom of unmanned plane tailplane, and empennage protection device is that empennage wipes ground piece 417, when winged
When machine excessively comes back and the afterbody is contacted to earth, empennage is wiped ground piece 417 and contacted to earth at first.
In an embodiment of the present invention, buffer unit is the foam being attached on skeleton 408.
In an embodiment of the present invention, left wing's tip wipes ground piece 413 and the right flank tip wipes ground piece 415 along unmanned plane to fly
The streamlined structure of direction of flow during row；Empennage wipes the streamlined of direction of flow when ground piece 417 is along unmanned plane during flying
Structure.
In an embodiment of the present invention, it is the laminated structure that unmanned plane is connected to by fastener to wipe ground piece.
In an embodiment of the present invention, the unmanned plane also includes front three-point wheel undercarriage, before undercarriage includes
Undercarriage and main landing gear, nose-gear are arranged on the cross bar 407 of propeller protection device, and main landing gear is arranged on fuselage bottom
Portion.
In an embodiment of the present invention, the cross bar 407 include two the first cross bars for having certain longitudinal separation and
Second cross bar (Fig. 4), nose-gear includes main support rod 401 and the inclined support bar 408 of both sides, and the one end of main support rod 401 is fixed
On the second cross bar of rear end, two one end of inclined support bar 408 are symmetrically fixed on main support rod 401, and the other end is respectively with setting
The first cross bar for being scheduled on front end is fixedly connected, and main support rod 401, inclined support bar 408, the first cross bar, the second cross bar constitute four sides
Body structure.
Specifically：
A kind of fixed-wing unmanned plane of the present invention, the unmanned plane air-foil is three-stage aerofoil profile, including slat, main wing and the flap
The wing；The unmanned plane also has Multidirectional protection device, including propeller protection device, wingtip protection device and empennage protection dress
Put；The unmanned plane can carry sprinkling system, for spraying operation；The unmanned plane also has assembling and disassembling device, including wing assembly and disassembly dress
Put and empennage assembling and disassembling device.The fixed-wing UAV system is great, low-speed characteristics are good, impact resistant, safe to use, is easy to
Transport, available for agricultural spray operation.
Relative to the unistage type or two-part aerofoil profile of current unmanned plane, three-stage aerofoil profile has higher maximum lift
Coefficient, this causes aircraft to have higher maximum lift.Maximum lift coefficient is the important technology index of an airplane, is affected winged
The multiple performance of machine.For example, higher maximum lift coefficient causes aircraft to have lower stalling speed (to keep putting down winged lowest speed
Degree).Lower flying speed causes unmanned plane to have higher resolution ratio in investigation, shooting, exploration.Maximum lift coefficient is carried
It is high to enable unmanned plane is liftoff earlier when taking off to soar simultaneously, realize short distance of taking off.Lower flying speed also to fly
Can brake stopping during machine landing landing in shorter distance, reduce landing distance.In the air during flight, higher lift coefficient
So that aircraft there can be bigger weight under same uniform velocity, payload is improved.Three sections of aerofoil profiles make to get stream preferably close to
The upper surface of aerofoil profile, postpones the separation of upper surface flow field and obtains higher lift coefficient.
Wing uses three sections of aerofoil profiles close to the main wing of the aircraft plane of symmetry in one embodiment of the present of invention.Another embodiment
Middle outer wing is using three sections of aerofoil profiles.Because the outer wing of fixed wing aircraft typically has aileron to control the rolling of aircraft, using three sections of wings
Aileron turns into flaperon 101 during type.The difference of flaperon 101 plays the rolling control function of aileron, flap pair when not deflecting when deflecting
The wing 101 is wing flap, improves the lift coefficient of aircraft.Slat 107 has used deformable energy-absorbing in another embodiment of the present invention
Material, such as foam.So slat 107 sacrifices oneself and protects the miscellaneous part of aircraft in an impact.This slat 107 is
It is easy to what is repaired or directly replace, to reduce maintenance cost.
The need for difference, slat 107 and wing flap 103 can be fixed or moveable.The reality of the present invention
Applying slat 107 or wing flap 103 in example can move relative to main wing.Such scheme allows aircraft will in high-performance cruise
Slat 107 and wing flap 103 are withdrawn is combined into single hop aerofoil profile with main wing, reduces cruise drag.Stitched in an alternative embodiment of the invention
The wing 107 is fixed, to reduce movable device, reduces cost and weight.Wing flap 103 is solid in another embodiment of the present invention
Fixed, to reduce movable device, reduce cost and weight.
The size of fixed-wing unmanned plane make it that transport is inconvenient sometimes, limits and is used into using scope or improve
This.Some innovations of the present invention reduce transportation clearance.Wing has assembly and disassembly to fill along spanwise in one embodiment of the present of invention
Put, some wing sections can be splitted into.Wing is divided into port wing, central wing and starboard wing three in an alternative embodiment of the invention
Section, this three sections of wings can be taken apart.Central machine wing panel is flat segments in another embodiment, and left and right wing has anhedral.
In some embodiments of the present invention, the unmanned plane includes the empennage attachment structure 205 and position positioned at wing rear
Tailplane 203, vertical tail 201 in the rear of empennage attachment structure 205.Wherein, empennage attachment structure 205 is a rod member.
In one embodiment, this bar cross section is change, and the end section close to head is larger, and is cut by caudal one end
Face is smaller.This Bars with Variable Cross-Section mitigates weight while intensity, rigidity needed for ensureing, saves material.In one embodiment
Middle vertical tail 201 includes fixed fin and rudder 202, and vertical tail 201 is complete dynamic vertical in another embodiment
Empennage.The chord length of vertical fin root can be more than the chord length of taper, can also be equal to the chord length of taper.Level in certain embodiments
Empennage 203 is stabilator, and the aerofoil profile neutrality line of tailplane 203 is middle recessed camber line, such aerofoil profile
Higher lower pressure (such as Fig. 2 b) is provided.Tailplane 203 includes horizontal stabilizer and elevator 204 in certain embodiments.
The chord length of horizontal tail root can be more than the chord length of taper, can also be equal to the chord length of taper.
One of the present invention innovates the convenient transportation for further improving tail on fixed-wing unmanned plane.In an implementation
The rod member of connection empennage and main wing (or empennage and fuselage) can be separated from main wing/fuselage in example.In another embodiment
In this rod member can be separated from empennage.Vertical fin can be separated with horizontal tail In yet another embodiment.In another implementation
The left side of horizontal tail can be with separating on the right of horizontal tail in example.These schemes cause a frame unmanned plane to be segmented into polylith, are easy to
Transport, reaches and is used using being assembled again behind ground.
A key factor of the unmanned plane in is security, and another key factor is maintenance cost.In-flight
Once there is personnel and the property that deviation is possible to damage periphery in unmanned plane.Propeller in operating is also potential safety hazard.It is preceding to draw
Formula fixed-wing unmanned plane is located at forefront due to its propeller, is most susceptible to destruction, and to the personnel around it, other are dynamic
Plant also has certain danger.Reasonable Protection to propeller and engine makes as pull-type fixed-wing unmanned plane before reducing
With, maintenance cost, the key of application risk is reduced.The innovation of the present invention is in the both sides of preceding pull-type propeller and front dress
Standby protection device, accordingly even when unmanned plane has collided personnel, propeller directly will not be got on the person.This both protects personnel,
Maintenance cost is also reduced, because propeller and engine are usually aircraft components costly.In one embodiment this
Protection device is made up of rod member.In another embodiment protection device by rod member skeleton and skeleton both sides buffer unit group
Into.Buffer unit is the foam being attached on rod member In yet another embodiment.Foam is shaped such that rod member in front of propeller
Total profile to be streamlined, reduce resistance.The security of pull-type fixed-wing unmanned plane, reduces maintenance cost before the innovation is improved
With.
In some embodiments, the unmanned plane undercarriage is front three-point wheel undercarriage.Another innovation of the present invention
It is that nose-gear is arranged in propeller protection device.This causes nose-gear to protect propeller in itself, while spiral
The protection device of oar provides support tie point for nose-gear so that compact conformation, aircraft weight is low.
Some innovations of the present invention carry out multi-faceted protection to unmanned plane, to lower use and maintenance cost.Unmanned plane
Easily collide during take-off and landing and wipe ground.Except front protection device above, the present invention is also from both sides and afterbody pair
Unmanned plane is protected, so as to reach the protection in four orientation.In one embodiment, the unmanned plane is filled at wing wingtip
There is wingtip protection device, it is to avoid impact, scraping damage wing when wingtip contacts to earth.In another embodiment, the unmanned plane is also
Including the empennage protection device positioned at tailplane bottom, it is to avoid impact, scraping damage empennage when horizontal tail is contacted to earth.In some implementations
Example in, these protection devices for ease of replacing wiping ground piece.
The size of fixed-wing unmanned plane is generally large, the fixed-wing unmanned plane of especially high load-carrying.The size of unmanned plane makes
Its transport is inconvenient, cost of transportation is high can not even to be transported, and this limits and have impact on the application of unmanned plane and is applied to
This.Another innovation of the present invention reduces the transportation clearance of fixed-wing unmanned plane, so as to overcome this difficulty.
Agriculturally fixed-wing unmanned plane is applied in Grain Growth Situation, insect pest detection etc., and is sprayed with greater need for the agricultural chemicals of labour
Spill, the spraying operations such as sprinkling of pollinating largely use depopulated helicopter or many rotors.The application of the present invention is to improve solid
Determine the load-carrying, flight and sprinkler performance of wing unmanned plane so that fixed wing aircraft has more preferable spraying efficiency.Such unmanned plane can
For forestry, agricultural and grass cultivation irrigation, moisten, spill medicine, fertilising and pollination etc..The unmanned plane includes a set of sprinkling system,
Including：Container, pump, jet pipe, shower nozzle, shower nozzle are connected by jet pipe with pump, and pump is connected by jet pipe with container.
It is overhanging including two sections of left and right that raising sprinkling breadth can improve jet pipe in spraying efficiency, one embodiment of the present of invention
Section jet pipe, overhanging section of jet pipe stretches out along spanwise at wingtip.Overhanging section of jet pipe can be bent at wingtip.By overhanging section
Jet pipe is bent upwards or posteriorly or anteriorly can reduce jet pipe in the upward length of aircraft exhibition, reduce aircraft in takeoff and landing
Length, reduces the requirement to landing place.
An alternative embodiment of the invention changes the sprinkling direction of shower nozzle, increases actual breadth.The axis and wing of shower nozzle
The angle of the plane of symmetry becomes big greatly with the change of shower nozzle and the distance of the wing plane of symmetry.This causes the sprinkling direction of shower nozzle progressively guide vane
The outside deflection of the tip, obtains higher breadth.
Another object of the present invention is the flight resistance for reducing sprinkling Fixed Wing AirVehicle, to reduce the requirement of power
With the loss of energy.Container is exposed at the surface of aircraft with unmanned plane by general sprinkling, or increase fuselage volume and
Surface area disposes container.These methods both increase the flight resistance of aircraft.The innovation of the present invention is by container
It is placed in inside wing, and in the vicinity of full machine center of gravity.So with the position of centre of gravity of the full machine of change of liquid weight in container
Change is little.In one embodiment, container is freestanding container, is built in inside wing, symmetrical along the wing plane of symmetry.
In some embodiments, container has curved upper surface, is fitted with covering on wing；Container has arcuate lower surface, with machine
Covering is fitted under the wing.Freestanding container is conveniently replaceable.In another embodiment, container is integral type container, the integral type
Container is made up of wingbar, rib, covering.Integrated container takes full advantage of original wing structure, saves material and aircraft
Weight.It is distributed to further reduce shower nozzle in flight resistance, another embodiment of the invention along wing span, connects shower nozzle
Wing lower surface is embedded in the jet pipe of pump, can be embedded as needed installed in slat lower surface or main wing lower surface.The present invention
Another embodiment pump is built in inside wing.
Because liquid can flow back and forth in a reservoir, or even agitate, the flight of the change of its inertia force and center of gravity to aircraft
Posture is impacted, and interference even destroys normal state of flight.It is an object of the invention to reduce and suppress this liquid
Body flows.There is at least one dividing plate, dividing plate at least one close to container in one embodiment of the present of invention inside container
Base apertures.This hole causes liquid to be connection.
In summary, fixed-wing unmanned plane has a wide range of applications, and the present invention improves multiple performances of aircraft, including most
Rise higher force coefficient, security, load-carrying, takeoff and landing performance, crash worthiness energy, security etc..The application of the present invention will cause fixed-wing
Aircraft has wider market in agricultural and other field.
Fig. 1 a and Fig. 1 b are a kind of embodiment of the invention.It is a kind of that there is three sections of aerofoil profiles, protection device and sprinkling system
Detachable agricultural spraying unmanned plane.The present embodiment is, to the schematically illustrate of partial content of the present invention, should not inadequately to limit
The scope of claim is made.
Unmanned plane shown in Fig. 1 includes power set, wing, tailplane, vertical tail, tail supporting rod, protection device, sprinkling
System.Wherein：
Air-foil is three-stage aerofoil profile, including：The slat 107 for being arranged on the leading edge of a wing, the master being arranged in the middle of wing
The wing and the wing flap for being arranged on trailing edge, main wing include the outer wing 105 of central wing 106 and the both sides of the centrally disposed wing 106, wing flap
Wing flap 103 and the flaperon 101 for being arranged on the trailing edge of outer wing 105 including the centrally disposed trailing edge of the wing 106.Three-stage aerofoil profile has
High coefficient of lift combined characteristic, improves unmanned plane lifting capacity and low-speed characteristics.Flaperon 101,102 can differential deflection control nothing
Man-machine rolling, can simultaneously deflect down as high lift device, can also upward deflect simultaneously as flap.In another embodiment
Middle flaperon 101,102 can only carry out difference deflection, it is impossible to be deflected in the same direction.When flaperon 101,102 is in the neutral position,
And when being deflected without difference, they have gap and rotation relative to main wing, the lift-rising effect of wing flap is played.Wing flap 103 plays lift-rising work
With.In one embodiment, the deflection angle of wing flap 103 is adjustable, with adapt to different loads, aerial mission pneumatic need
Ask.For example, using large deflection angle that deflection angle is reduced or eliminated to improve lift, during cruise to reduce resistance during takeoff and landing.
In another embodiment, the deflection angle of wing flap 103 is changeless.Such design need not change work during deflection angle
Motivation structure, it is fairly simple, and save material and weight.
Wing is rectangular wing in Fig. 1, and middle central wing is flat segments, and left right lateral outer wing carries the upper counterangle, carried
High unmanned plane lateral stability.The advantage of rectangular wing is easy for manufacture.In another embodiment, wing carries contraction coefficient,
Chord length at the aircraft plane of symmetry is more than the chord length at wingtip.When mean chord is constant, the wing with contraction coefficient has lower
Aerodynamic drag and bigger medicine-chest capacity.
Empennage is connected by empennage attachment structure 205 with wing, including vertical tail (201,202) and tailplane
(203、204)；Vertical tail 201 includes fixed fin and rudder 202；Tailplane 203 includes horizontal stabilizer and liter
Rudder 204 drops.In another embodiment, vertical tail is all moving fin.In another embodiment, tailplane is complete dynamic flat
Tail.Chord length of the vertical tail with contraction coefficient, i.e. root in Fig. 1 is more than the chord length of taper.In another embodiment, vertically
Empennage is flat segments, and the chord length of each exhibition position is the same.Chord length of the tailplane with contraction coefficient, i.e. root in Fig. 1 is more than taper
Chord length.In another embodiment, tailplane is flat segments, and the chord length of each exhibition position is the same.
Fig. 2 shows the different airfoil profiles of tailplane.Fig. 2 a show symmetrical tailplane aerofoil profile.Above and below symmetrical airfoil
Symmetrically, neutrality line is straight line.Fig. 2 b show recessed tailplane aerofoil profile.The neutrality line 211 of recessed aerofoil profile is curved under centre
Camber line.Recessed aerofoil profile has higher lower pressure, strengthens the trim ability of full machine.
Protection device includes propeller protection device, wingtip protection device and empennage protection device.Propeller protection device
Including the first vertical pole 409, the cross bar 407 in front and second vertical pole 411 on right side positioned at the left side of power set 501.First indulges
The one end of 409 and second vertical pole of bar 411 is fixedly attached on wing, and the other end extends forward, is connected with cross bar 407.Protect rod member
A kind of cross section of structure such as Fig. 3 a, only rod member skeleton 408, another cross section such as Fig. 3 b, including rod member skeleton 408 ease up
Flushing device 406.Buffer unit 406 has energy reserve ability or absorbs the elastomeric material of energy, and such as foam is attached to skeleton
408 outside.This open attached structure is convenient to the replacement of buffer unit 406.Wingtip protection device includes left wing's tip
Wipe ground piece 413 and the right flank tip wipes ground piece 415, be separately mounted to the lower section of left and right wingtip, when aircraft side wing contacts to earth, left wing
The tip wipes ground piece 413 or the right flank tip 415 contacts to earth at first, protects miscellaneous part.Flowing when wiping the structure of ground piece for along flight
Direction, front face area and aerodynamic drag are small.Empennage protection device is that empennage wipes ground piece 417, positioned at the lower section of horizontal tail 203.When winged
When machine excessively comes back and the afterbody is contacted to earth, empennage is wiped ground piece and contacted to earth at first, protects miscellaneous part.Empennage wipes the knot of ground piece 417
Direction of flow when structure is along flight, front face area and aerodynamic drag are small.The structure for wiping ground piece 413,415,417 is conveniently replaceable,
The laminated structure of aircraft is e.g. connected to by fastener.
As shown in Fig. 1 b, the nose-gear of aircraft is connected on the main support rod 401 of propeller.This innovation is on the one hand
So that nose-gear protects propeller in itself, while main support rod 401 provides tie point for nose-gear again.
Fig. 4 shows a kind of new preceding guard bar and nose-gear structure.In the structure, propeller cross bar 407 includes two
Root has the transverse bar member of certain longitudinal separation, and nose-gear includes middle main support rod 401 and both sides inclined support bar 408.Main branch
Strut 401 is fixedly connected with the one end of inclined support bar 408, and the other end is fixedly connected with the first cross bar respectively.The main support of nose-gear
Bar 401, inclined support bar 408 and propeller cross bar 407 constitute tetrahedral structure, the structure in fore-and-aft direction, left and right directions simultaneously
With higher strength and stiffness, it is ensured that nose-gear it is durable in use.
It is an object of the invention to a frame is efficient, reliable sprinkling fixed-wing unmanned plane.Fig. 5 shows a kind of sprinkling
System, including container 300, pump 331, jet pipe (303,305,321,323) and shower nozzle (307,309,311,313,315,317,
319).Fig. 7 is shown inside the centrally located wing of container 300, symmetrical.Compared to external container and increase body volume
Container, such built-in container maintains the clean streamline of aircraft configuration, does not increase the resistance of aircraft additionally.Container 300
At the center of gravity and centre of lift of aircraft, the influence of the change of such amount of liquid medicine to center of gravity is little so that aircraft is easily kept
Good state of flight.Pump 331 is located inside main wing 105, and container 300 is connected with pump 331 by jet pipe 323.Shower nozzle (307,
309th, 311,313,315,317,319) it is connected with pump 331 by jet pipe (303,305,321).Jet pipe 321 is embedded in slat 107
Lower surface.
The connection of jet pipe 303, jet pipe 305 and jet pipe 321 is bent connection, during sprinkling, and jet pipe 303, jet pipe 305 are exhibition
Shape is opened, parallel to horizontal plane, during non-sprinkling, jet pipe 303, jet pipe 305 are rugosity, are folded up perpendicular to horizontal plane, or
Fold back in the horizontal plane.Jet pipe after folding no longer reaches the scope beyond wingtip, is easy to the takeoff and landing of aircraft.
During sprinkling, the axis of shower nozzle 319 perpendicular to horizontal plane, the axis of shower nozzle 311 and the axis of shower nozzle 313 and horizontal plane angle compared with
Greatly, the axis of shower nozzle 315 and the axis of shower nozzle 317 and horizontal plane angle are smaller, the axis of shower nozzle 307 and the axis of shower nozzle 309 and horizontal plane
Angle is minimum.The sprinkling direction of shower nozzle is with progressively outside away from the aircraft plane of symmetry so that sprinkling breadth is more than left and right outermost
The distance between shower nozzle is held, spraying efficiency is improved.
In one embodiment, the upper surface of container 300 is arcwall face, is fitted with Skinning Surfaces on main wing 107；Container 300
Lower surface is arcwall face, is fitted with 107 times coverings of main wing.Under the conditions of same volume, the thickness of container is reached maximum, reduce
Container anterior-posterior length and left and right length, further reduce the gravity center shift scope of decoction.
The mobile of liquid in container can cause the center of gravity of aircraft to change, therefore the flight of influence aircraft.Fig. 8 is shown
There is dividing plate 302 laterally, longitudinal inside container 300, several perforates are arranged at dividing plate bottom.These dividing plates slow down the shifting of liquid
It is dynamic, improve the flight stability of aircraft.
Figure 10 illustrates another jet pipe, nozzle layout of sprinkler form.Jet pipe 321 is arranged on below wing by support 312,
Shower nozzle 310 is distributed along jet pipe, and spout is backwards.Spout causes decoction to have a speed backward, the speed with respect to aircraft backwards
All or part of flying speed for offsetting aircraft, reduces horizontal velocity of the decoction with respect to ground, so as to reduce the further mist of decoction
Change.
The size of fixed-wing unmanned plane causes transport inconvenient sometimes.It is an object of the invention to reduce fixed-wing nobody
The transportation clearance of machine so that convenient transportation, reduces cost of transportation, expands application.Fig. 1 shows multiple dresses of the unmanned plane
Tear mechanism, including wing assembling and disassembling device (601,603), tail supporting rod-wing assembling and disassembling device 605, tail supporting rod-empennage assembling and disassembling device open
607.Figure 11 shows all parts of the aircraft after taking apart.Wing assembling and disassembling device 601 and 603 is distributed in wing exhibition upwards, by machine
Gap is into three sections of left, center, right.Three sections of wings carry out assembly and disassembly by wing assembling and disassembling device 601 and 603.Figure 12 a are illustrated
A kind of assembling-disassembling structure, the structure is ear sheet type connecting structure, and assembly and disassembly hole 611,613 is bolt connecting hole.Installation sheet 615,617 is used
It is fixedly connected in auricle with wing.Figure 12 b show the wing assembling-disassembling structure of another tubular type, and central wing passes through pipe fitting with outer wing
The form connection of socket, one section of pipe 605 and outer wing are affixed, and stretch out the segment length of outer wing one, and another section of pipe 607 and central wing are affixed
It is embedded in central wing.Pipe 605 stretches out the external cylindrical surface of outer panel and the inner cylinder face of pipe 607 coordinates.Shoe rod assembling and disassembling device position
In tail supporting rod and wing link position, the assembly and disassembly for wing and tail supporting rod.Figure 13 connects for a kind of tubular type tail supporting rod
Structure, wherein mounting hole 611 are the structure and fuselage bolt connection；Positioning lock tieholen 613 is tail supporting rod positioning, locking
Hole；615 be tail supporting rod locking hoop.Empennage assembling-disassembling structure is as belonging to Figure 14, and the structure is the rectangle structure with fluting.Wherein
Hole 625 is tail supporting rod mounting hole, and hole 621 is tail supporting rod locking hole, and hole 623 is horizontal tail mounting hole, and hole 627 is vertical fin mounting hole.
Figure 15 is another embodiment of the invention, and a kind of anury with three sections of aerofoil profiles, propeller protection device is agricultural
Spray unmanned plane schematic diagram.
The difference of the present embodiment and first embodiment is essentially consisted in：Fixed-wing unmanned plane shown in the present embodiment is anury
Fixed-wing unmanned plane.The size of tailless UAV is smaller, more convenient for transporting and using.The unmanned plane includes：Power set, spiral shell
Revolve oar protection device, undercarriage, wing, double vertical tails 201.
Double vertical tails 201 include fixed fin and rudder 203.Double vertical tails 201 are leaned on installed in wing both sides
At nearly wingtip.
Described above is only the preferred embodiment of the present invention, rather than its limitations；Although it should be pointed out that with reference to above-mentioned each
The present invention is described in detail embodiment, it will be understood by those within the art that, it still can be to above-mentioned each
Technical scheme described in embodiment is modified, or carries out equivalent substitution to which part or all technical characteristic；And this
A little modifications and replacement, do not make the essence of corresponding technical scheme depart from the scope of various embodiments of the present invention technical scheme.
Claims (6)
1. a kind of fixed-wing unmanned plane provided with protection device, it is characterised in that be provided with preceding pull-type propeller in front fuselage, is protected
Protection unit includes propeller protection device, wingtip protection device, empennage protection device：
Propeller protection device is located at the both sides and front of propeller, including skeleton and buffer unit, and buffer unit is attached at bone
On the outside of frame, skeleton includes being located at the first vertical pole, the cross bar in front and second vertical pole on right side on the left of propeller, the first vertical pole and
Second vertical pole one end is fixedly connected on wing, and the other end extends forward, is connected with cross bar；
Wingtip protection device is located at wing wingtip, including left wing's tip wipes ground piece and the right flank tip wipes ground piece, is separately mounted to left and right
The lower section of wingtip, when aircraft side wing contacts to earth, wipes ground piece and contacts to earth at first；
Empennage protection device is located at the bottom of unmanned plane tailplane, and empennage protection device is that empennage wipes ground piece, when aircraft is excessive
When coming back and the afterbody is contacted to earth, empennage is wiped ground piece and contacted to earth at first.
2. a kind of fixed-wing unmanned plane provided with protection device according to claim 1, it is characterised in that buffer unit is
It is attached to the foam on skeleton.
3. a kind of fixed-wing unmanned plane provided with protection device according to claim 1, it is characterised in that left wing's tip wipes ground
The streamlined structure of direction of flow when piece and the right flank tip wipe ground piece for along unmanned plane during flying；It is along nobody that empennage, which wipes ground piece,
The streamlined structure of direction of flow during machine flight.
4. a kind of fixed-wing unmanned plane provided with protection device according to claim 3, it is characterised in that it is logical to wipe ground piece
Cross the laminated structure that fastener is connected to unmanned plane.
5. a kind of fixed-wing unmanned plane provided with protection device according to claim 1, it is characterised in that the unmanned plane
Also include front three-point wheel undercarriage, undercarriage includes nose-gear and main landing gear, and nose-gear is protected installed in propeller
On the cross bar of device, main landing gear is arranged on fuselage bottom.
6. a kind of fixed-wing unmanned plane provided with protection device according to claim 5, it is characterised in that the cross bar bag
Two the first cross bars and the second cross bar for having certain longitudinal separation are included, nose-gear includes main support rod and the bearing diagonal of both sides
Bar, main support rod one end is fixed on the second cross bar of rear end, and two inclined support bar one end are symmetrically fixed on main support rod, separately
One end is fixedly connected with being set in the first cross bar of front end respectively, main support rod, inclined support bar, the first cross bar, the second cross bar structure
Into tetrahedral structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611261559.5A CN106986040A (en) | 2016-12-30 | 2016-12-30 | A kind of fixed-wing unmanned plane provided with protection device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611261559.5A CN106986040A (en) | 2016-12-30 | 2016-12-30 | A kind of fixed-wing unmanned plane provided with protection device |
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| CN106986040A true CN106986040A (en) | 2017-07-28 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201611261559.5A Pending CN106986040A (en) | 2016-12-30 | 2016-12-30 | A kind of fixed-wing unmanned plane provided with protection device |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111361749A (en) * | 2020-03-31 | 2020-07-03 | 中国商用飞机有限责任公司 | Crash protection device for fixed-wing aircraft model |
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|---|---|---|---|---|
| JPH10100998A (en) * | 1996-09-26 | 1998-04-21 | Japan Aviation Electron Ind Ltd | Tail blade protecting structure for industrial unmanned helicopter |
| US20060186261A1 (en) * | 2002-10-11 | 2006-08-24 | Stefan Unzicker | Vertical take-off and landing aircraft |
| CN104709460A (en) * | 2015-03-12 | 2015-06-17 | 江苏艾锐泰克无人飞行器科技有限公司 | Fixed-wing unmanned aerial vehicle capable of being quickly disassembled and assembled |
| CN206384156U (en) * | 2016-12-30 | 2017-08-08 | 马晓辉 | Fixed-wing unmanned plane provided with protection device |
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2016
- 2016-12-30 CN CN201611261559.5A patent/CN106986040A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH10100998A (en) * | 1996-09-26 | 1998-04-21 | Japan Aviation Electron Ind Ltd | Tail blade protecting structure for industrial unmanned helicopter |
| US20060186261A1 (en) * | 2002-10-11 | 2006-08-24 | Stefan Unzicker | Vertical take-off and landing aircraft |
| CN104709460A (en) * | 2015-03-12 | 2015-06-17 | 江苏艾锐泰克无人飞行器科技有限公司 | Fixed-wing unmanned aerial vehicle capable of being quickly disassembled and assembled |
| CN206384156U (en) * | 2016-12-30 | 2017-08-08 | 马晓辉 | Fixed-wing unmanned plane provided with protection device |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111361749A (en) * | 2020-03-31 | 2020-07-03 | 中国商用飞机有限责任公司 | Crash protection device for fixed-wing aircraft model |
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Effective date of registration: 20200410 Address after: 710000 1st floor, R & D building, No. 21, Yingbin Avenue, Xi'an Aviation base, Shaanxi Province Applicant after: Xi'an riding Aviation Technology Co.,Ltd. Address before: 710089 No. 2116, No. 21, 9 Yingbin Road, Yanliang District, Xi'an, Shaanxi, Yanliang Applicant before: Ma Xiaohui |
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Application publication date: 20170728 |