CN206528623U - Three-stage fixed-wing unmanned plane provided with protection device - Google Patents

Abstract

The utility model is related to a kind of three-stage fixed-wing unmanned plane provided with protection device; the wing of the fixed-wing unmanned plane is three-stage airfoil structure; including being arranged on the slat of the leading edge of a wing, the main wing being arranged in the middle of wing and the wing flap for being arranged on trailing edge; main wing includes the outer wing of central wing and centrally disposed wing both sides, and wing flap includes the wing flap of centrally disposed wing trailing edge and is arranged on the flaperon of outer wing trailing edge；Preceding pull-type propeller is provided with front fuselage, protection device includes propeller protection device, wingtip protection device, empennage protection device.Advantage of the present utility model is embodied in：With higher maximum lift coefficient so that aircraft has higher maximum lift, while can reasonably be protected to fuselage and propeller.

Description

Three-stage fixed-wing unmanned plane provided with protection device

Technical field

The utility model is related to unmanned vehicle field, and in particular to a kind of three-stage fixed-wing provided with protection device without It is man-machine.

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.Especially existing unmanned plane, maximum lift coefficient is not enough, it is impossible to meet use requirement well.

Utility model content

The purpose of this utility model is for of the prior art not enough solid there is provided a kind of three-stage provided with protection device Wing unmanned plane is determined, with higher maximum lift coefficient so that aircraft has higher maximum lift, while can be to fuselage and spiral shell Rotation oar is reasonably protected.

To achieve the above object, the utility model discloses following technical scheme：

A kind of three-stage fixed-wing unmanned plane provided with protection device, the wing of the fixed-wing unmanned plane is three-stage aerofoil profile Structure, including it is arranged on the slat of the leading edge of a wing, the main wing being arranged in the middle of wing and the wing flap for being arranged on trailing edge, main wing Outer wing including central wing and centrally disposed wing both sides, wing flap includes the wing flap of centrally disposed wing trailing edge and is arranged on outer wing The flaperon of trailing edge；

Preceding pull-type propeller is provided with front fuselage, protection device includes propeller protection device, wingtip protection device, tail Wing protection device：Propeller protection device is located at the both sides and front of propeller, including skeleton and buffer unit, buffer unit patch Invest 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, and the other end extends forward, is connected with cross bar；Wingtip protection device is located at At wing wingtip, including left wing's tip wipes ground piece and the right flank tip wipes ground piece, the lower section of left and right wingtip is separately mounted to, when aircraft side When 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 Empennage wipes ground piece, when aircraft excessively comes back and afterbody is contacted to earth, and empennage is wiped ground piece and contacted to earth at first.

Further, the fixed-wing is rectangular wing, and middle central wing is flat segments, and left right lateral outer wing is carried The upper counterangle.

Further, the wing flap is fixed structure, removable or turntable with respect to main wing；The slat is led relatively The wing is fixed structure, removable or rotational structure.

Further, between the central wing and outer wing it is detachable structure, central wing and outer wing pass through some assembly and disassembly and filled Put installation wing.

Further, unmanned plane also includes empennage, and empennage includes the empennage attachment structure and empennage connection knot at wing rear Tailplane, the vertical tail at structure rear, empennage attachment structure are connected by assembling and disassembling device with wing, tailplane, vertical end The wing is connected by assembling and disassembling device with empennage attachment structure；Wherein, tailplane is stabilator, and aerofoil profile neutrality line is centre Recessed camber line, the chord length of tailplane root is more than or equal to the chord length of taper；Vertical tail is dynamic vertical tail, vertical end entirely The chord length of the root of the wing is more than or equal to the chord length of taper.

Further, empennage attachment structure is a rod member, and bar cross section is constant or changes, and is tied in bar cross section for change During structure, it is more than close to an end section of head and leans on a caudal end section.

Further, the assembling and disassembling device includes wing assembling and disassembling device, tail supporting rod-wing assembling and disassembling device and tail supporting rod-tail Wing assembling and disassembling device, wing assembling and disassembling device is distributed in wing exhibition upwards, wing is divided into three sections of left, center, right, three sections of wings pass through machine Wing assembling and disassembling device carries out assembly and disassembly；

Wing assembling and disassembling device is ear sheet type connecting structure, and ear sheet type connecting structure is provided with assembly and disassembly hole, and assembly and disassembly hole is bolt Connecting hole, ear sheet type connecting structure is provided with the installation sheet for being used for being fixedly connected with wing；

Or

Wing assembling and disassembling device is tubular type attachment structure, and central wing is connected with outer wing by the form of pipe fitting sleeving, one section of pipe It is affixed with outer wing, and the segment length of outer wing one is stretched out, another section of pipe is embedded in central wing；

Tail supporting rod-wing assembling and disassembling device is tubular type attachment structure, and pipe is provided with mounting hole, passed through by mounting hole with fuselage Bolt connection；Positioning lock tieholen is additionally provided with pipe；Pipe end is additionally provided with locking hoop；

Tail supporting rod-empennage assembling and disassembling device is the rectangle structure with fluting, provided with tail supporting rod mounting hole, shoe rod locking Hole, horizontal tail mounting hole and vertical fin mounting hole.

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；Ground piece is wiped to pass through fastener It is connected to the laminated structure of unmanned plane

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 three-stage fixed-wing unmanned plane provided with protection device disclosed in the utility model, with following beneficial effect Really：

An innovative point of the present utility model is to use three-stage air-foil.Relative to the single hop of current unmanned plane Formula or two-part aerofoil profile, three-stage aerofoil profile have higher maximum lift coefficient, and this causes aircraft to have higher maximum lift.It is maximum The raising of lift allows aircraft to have higher load capacity and lower stalling speed, can the landing on shorter runway, have Preferably fly at low speed performance.

The utility model carries out multi-faceted protection to unmanned plane, to lower use and maintenance cost.Unmanned plane take off and Easily collide during landing and wipe ground.Except front protection device above, the utility model is also from both sides and afterbody to nothing It is man-machine to be protected, so as to reach the protection in four orientation, it is to avoid impact, scraping damage wing when wingtip and empennage contact to earth, carry The high security of preceding pull-type 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 a 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 utility model embodiment will be clearly and completely described below, it is clear that described Embodiment is only a part of embodiment of the utility model, rather than whole embodiments.Based on the implementation in the utility model Example, the every other embodiment that those of ordinary skill in the art are obtained under the premise of creative work is not made is belonged to The scope of the utility model protection.

Core of the present utility model is to provide a kind of three-stage fixed-wing unmanned plane provided with protection device, with higher Maximum lift coefficient so that aircraft has higher maximum lift, while can reasonably be protected to fuselage and propeller.

A kind of three-stage fixed-wing unmanned plane provided with protection device, it is characterised in that the wing of the fixed-wing unmanned plane For three-stage airfoil structure, including it is arranged on the slat 107 of the leading edge of a wing, the main wing being arranged in the middle of wing and is arranged on wing The wing flap of trailing edge, main wing includes the outer wing 105 of central wing 106 and the both sides of the centrally disposed wing 106, and wing flap includes centrally disposed The wing flap 103 of the trailing edge of the wing 106 and the flaperon 101 for being arranged on the trailing edge of outer wing 105.

Preceding pull-type propeller is provided with front fuselage, protection device includes propeller protection device, wingtip protection device, tail Wing 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 a kind of embodiment of the present utility model, the fixed-wing is rectangular wing, and middle central wing 106 is straight Section, left right lateral outer wing 105 carries the upper counterangle.

In a kind of embodiment of the present utility model, the wing flap is fixed structure with respect to main wing, may move or rotatable Structure；The slat is fixed structure, removable or rotational structure with respect to main wing.

It is detachable structure between the central wing 106 and outer wing 105 in a kind of embodiment of the present utility model, in The centre wing 106 passes through some assembling and disassembling device installation wings with outer wing 105.

In a kind of embodiment of the present utility model, the unmanned plane also includes empennage, and empennage includes the tail at wing rear Tailplane 203, the vertical tail 201 at wing attachment structure 205 and the rear of empennage attachment structure 205, empennage attachment structure 205 It is connected by assembling and disassembling device with wing, tailplane 203, vertical tail 201 are connected by assembling and disassembling device and empennage attachment structure 205 Connect.

In a kind of embodiment of the present utility model, the tailplane is stabilator, and aerofoil profile neutrality line 211 is Middle recessed camber line, the chord length of the root of tailplane 203 is more than or equal to the chord length of taper.

In a kind of embodiment of the present utility model, the vertical tail 201 is dynamic vertical tail, the root of vertical tail entirely The chord length in portion is more than or equal to the chord length of taper.

In a kind of embodiment of the present utility model, the empennage attachment structure 205 be a rod member, bar cross section it is constant or Person changes, and when bar cross section is change structure, is more than close to an end section of head and leans on a caudal end section.

In a kind of embodiment of the present utility model, the assembling and disassembling device includes wing assembling and disassembling device 601, tail supporting rod-machine Wing assembling and disassembling device 605 and tail supporting rod-empennage assembling and disassembling device 607, wing assembling and disassembling device 301 are distributed in wing exhibition upwards, by wing Three sections of left, center, right are divided into, three sections of wings carry out assembly and disassembly by wing assembling and disassembling device 601；

Wing assembling and disassembling device 601 is ear sheet type connecting structure, and ear sheet type connecting structure is provided with assembly and disassembly hole 613,611, dress Hole is torn open for bolt connecting hole, ear sheet type connecting structure is provided with the installation sheet 615,617 for being used for being fixedly connected with wing；

Or

Wing assembling and disassembling device 601 is tubular type attachment structure, and central wing 106 is connected with outer wing 105 by the form of pipe fitting sleeving Connect, one section of pipe 605 and outer wing are affixed, and stretch out the segment length of outer wing one, another section of pipe is embedded in central wing 106；

Tail supporting rod-wing assembling and disassembling device is tubular type attachment structure, and pipe is provided with mounting hole 611, passes through mounting hole 611 and machine Body is bolted；Positioning lock tieholen 613 is additionally provided with pipe；Pipe end is additionally provided with locking hoop 615；

Tail supporting rod-empennage assembling and disassembling device is the rectangle structure with fluting, provided with tail supporting rod mounting hole 625, shoe lever lock Tieholen 621, horizontal tail mounting hole 623 and vertical fin mounting hole 627.

In a kind of embodiment of the present utility model, the slat 107 is made of changeability energy-absorbing material.

In a kind of embodiment of the present utility model, buffer unit is the foam being attached on skeleton 408.

In a kind of embodiment of the present utility model, left wing's tip wipes ground piece 413 and the right flank tip wipes ground piece 415 for along nobody The streamlined structure of direction of flow during machine flight；The stream of direction of flow when empennage wipes ground piece 417 for along unmanned plane during flying Linear structure.

In a kind of embodiment of the present utility model, it is the laminated structure that unmanned plane is connected to by fastener to wipe ground piece.

In a kind of embodiment of the present utility model, the unmanned plane also includes front three-point wheel undercarriage, undercarriage bag Nose-gear and main landing gear are included, nose-gear is arranged on the cross bar 407 of propeller protection device, and main landing gear is arranged on machine Body bottom.

In a kind of embodiment of the present utility model, the cross bar 407 includes two the first horizontal strokes for having certain longitudinal separation Bar and the second cross bar (Fig. 4), nose-gear include main support rod 401 and the inclined support bar 408 of both sides, the one end of main support rod 401 It 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, other end difference It is fixedly connected with the first cross bar for being set in front end, main support rod 401, inclined support bar 408, the first cross bar, the second cross bar are constituted Tetrahedral structure.

Specifically：

A kind of fixed-wing unmanned plane of the utility model, the unmanned plane air-foil is three-stage aerofoil profile, including slat, main wing And wing flap；The unmanned plane also has Multidirectional protection device, including propeller protection device, wingtip protection device and empennage protection Device；The unmanned plane can carry sprinkling system, for spraying operation；The unmanned plane also has assembling and disassembling device, including wing is assembled and disassembled Device and empennage assembling and disassembling device.The fixed-wing UAV system is great, low-speed characteristics are good, impact resistant, safe to use, just In 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 utility model.Another reality Apply outer wing in example and use three sections of aerofoil profiles.Because the outer wing of fixed wing aircraft typically has aileron to control the rolling of aircraft, using three Aileron turns into flaperon 101 during section aerofoil profile.The difference of flaperon 101 plays the rolling control function of aileron when deflecting, when not deflecting Flaperon 101 is wing flap, improves the lift coefficient of aircraft.Used can for slat 107 in another embodiment of the present utility model Deform the material of energy-absorbing, such as foam.So slat 107 sacrifices oneself and protects the miscellaneous part of aircraft in an impact.This Slat 107 is easy for 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.Of the present utility model one Slat 107 or wing flap 103 can be moved relative to main wing in individual embodiment.Such scheme causes aircraft can in high-performance cruise Single hop aerofoil profile is combined into main wing so that slat 107 and wing flap 103 to be withdrawn, reduces cruise drag.Another reality of the present utility model It is fixed to apply slat 107 in example, to reduce movable device, reduces cost and weight.Another embodiment of the present utility model Middle wing flap 103 is fixed, to reduce movable device, reduces 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 utility model reduce transportation clearance.Wing is along spanwise in one embodiment of the present utility model There is assembling and disassembling device, some wing sections can be splitted into.Wing is divided into port wing, central machine in another embodiment of the present utility model Three sections of the wing and starboard wing, 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 utility model, the unmanned plane includes the empennage attachment structure 205 positioned at wing rear With the tailplane 203 positioned at the rear of empennage attachment structure 205, vertical tail 201.Wherein, empennage attachment structure 205 is a bar Part.In one embodiment, this bar cross section is change, and the end section close to head is larger, and by caudal one End section is smaller.This Bars with Variable Cross-Section mitigates weight while intensity, rigidity needed for ensureing, saves material.In a reality Applying vertical tail 201 in example includes fixed fin and rudder 202, and vertical tail 201 is complete dynamic in another embodiment Vertical tail.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.In certain embodiments Tailplane 203 is stabilator, and the aerofoil profile neutrality line of tailplane 203 is middle recessed camber line, such Aerofoil profile provides higher lower pressure (such as Fig. 2 b).Tailplane 203 includes horizontal stabilizer and elevator in certain embodiments 204.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 utility model is innovated the convenient transportation for further improving tail on fixed-wing unmanned plane.At one Empennage and the rod member of main wing (or empennage and fuselage) are connected in embodiment to be separated from main wing/fuselage.In another reality Applying the rod member of this in example can separate from empennage.Vertical fin can be separated with horizontal tail In yet another embodiment.At another The left side of horizontal tail can be with separating on the right of horizontal tail in embodiment.These schemes cause a frame unmanned plane to be segmented into polylith, It is readily transported, reaches and 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.It is of the present utility model one innovation be the both sides of preceding pull-type propeller and before Side's equipment protection device, accordingly even when unmanned plane has collided personnel, propeller directly will not be got on the person.This both protects people Member, also reduces maintenance cost, because propeller and engine are usually aircraft components costly.In one embodiment this One 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.It is of the present utility model another Innovation is that nose-gear is arranged in propeller protection device.This causes nose-gear to protect propeller in itself, simultaneously The protection device of propeller provides support tie point for nose-gear so that compact conformation, aircraft weight is low.

Some innovations of the present utility model carry out multi-faceted protection to unmanned plane, to lower use and maintenance cost.Nothing Easily collide during man-machine take-off and landing and wipe ground.Except front protection device above, the utility model is also from both sides Unmanned plane is protected with afterbody, so as to reach the protection in four orientation.In one embodiment, the unmanned plane is in wing Wingtip protection device is housed, it is to avoid impact, scraping damage wing when wingtip contacts to earth at wingtip.In another embodiment, should Unmanned plane also includes 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 embodiments, 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 utility model 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.An application of the present utility model is to carry Load-carrying, flight and the sprinkler performance of high fixed-wing unmanned plane so that fixed wing aircraft has more preferable spraying efficiency.It is such nobody Machine can be used for forestry, the irrigation of agricultural and grass cultivation, moisten, spill medicine, fertilising and pollination etc..The unmanned plane includes a set of sprinkling system 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.

Raising sprinkling breadth, which can improve jet pipe in spraying efficiency, one embodiment of the present utility model, includes two sections of left and right Overhanging section of jet pipe, overhanging section of jet pipe stretches out along spanwise at wingtip.Overhanging section of jet pipe can be bent at wingtip.Will be outer Jet pipe can be reduced in the upward length of aircraft exhibition by stretching section jet pipe and bending upwards or posteriorly or anteriorly, reduced aircraft and taken off and dropping Length when falling, reduces the requirement to landing place.

Another embodiment of the present utility model changes the sprinkling direction of shower nozzle, increases actual breadth.The axis of shower nozzle with The angle of the wing 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 Deflected to the outside of wingtip, obtain higher breadth.

Another purpose of the present utility model is the flight resistance for reducing sprinkling Fixed Wing AirVehicle, to reduce power It is required that the loss with energy.Container is exposed at the surface of aircraft with unmanned plane by general sprinkling, or increases the body of fuselage Accumulate with surface area to dispose container.These methods both increase the flight resistance of aircraft.An innovation of the present utility model is Container is built in inside wing, and in the vicinity of full machine center of gravity.So with the full machine of change of liquid weight in container Position of centre of gravity change is little.In one embodiment, container is freestanding container, is built in inside wing, along the wing plane of symmetry It is symmetrical.In some embodiments, container has curved upper surface, is fitted with covering on wing；Container has under arc Surface, fits with covering under wing.Freestanding container is conveniently replaceable.In another embodiment, container is integral type container, The integrated container is made up of wingbar, rib, covering.Integrated container takes full advantage of original wing structure, saves material Material and aircraft weight.In order to further reduce in flight resistance, another embodiment of the present utility model shower nozzle along wing span The jet pipe of distribution, connection shower nozzle and pump is embedded in wing lower surface, can embed as needed installed in slat lower surface or main wing Lower surface.Pump is built in inside wing by another embodiment of the present utility model.

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.A purpose of the present utility model is reduction and suppresses this Plant liquid flowing.There is at least one at least one dividing plate, dividing plate in one embodiment of the present utility model inside container Close to vessel bottom aperture.This hole causes liquid to be connection.

In summary, fixed-wing unmanned plane has a wide range of applications, and the utility model improves multiple performances of aircraft, bag Include maximum lift coefficient, security, load-carrying, takeoff and landing performance, crash worthiness energy, security etc..Application of the present utility model will make Obtain 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 present utility model.One kind has three sections of aerofoil profiles, protection device and sprinkling system The detachable agricultural spraying unmanned plane of system.The present embodiment be to the schematically illustrate of the utility model partial content, should not Suitably limit the scope of claim.

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, the flap The wing includes the wing flap 103 of the centrally disposed trailing edge of the wing 106 and is arranged on the flaperon 101 of the trailing edge of outer wing 105.Three-stage aerofoil profile has There is high coefficient of lift combined characteristic, improve unmanned plane lifting capacity and low-speed characteristics.Flaperon 101,102 can differential deflection control Unmanned machine rolling processed, can simultaneously deflect down as high lift device, can also upward deflect simultaneously as flap.In another reality Difference deflection can only be carried out by applying flaperon 101,102 in example, it is impossible to be deflected in the same direction.When flaperon 101,102 is in neutrality Position, and when being deflected without difference, they have gap and rotation relative to main wing, play the lift-rising effect of wing flap.Wing flap 103 plays increasing Rise effect.In one embodiment, the deflection angle of wing flap 103 is adjustable, with adapt to different loads, aerial mission gas Dynamic demand.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 Power.In another embodiment, the deflection angle of wing flap 103 is changeless.When such design need not change deflection angle Movable device, 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 one side Face causes nose-gear to protect 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.

A purpose of the present utility model is that a frame is efficient, reliable sprinkling fixed-wing unmanned plane.Fig. 5 shows one kind 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 fuselage body Long-pending container, such built-in container maintains the clean streamline of aircraft configuration, does not increase the resistance of aircraft additionally.Container 300 are located at the center of gravity of aircraft and centre of lift, and the influence of the change of such amount of liquid medicine to center of gravity is little so that aircraft is easily protected Hold 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 (307,309,311,313,315,317,319) are connected with pump 331 by jet pipe (303,305,321).Jet pipe 321 is embedded in The lower surface of slat 107.

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 is perpendicular to horizontal plane, the axis of shower nozzle 311 and the axis of shower nozzle 313 and horizontal plane angle Larger, 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 level Face 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 most The distance between outer end shower nozzle, improves spraying efficiency.

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.A purpose of the present utility model is to reduce fixed-wing The transportation clearance of unmanned plane so that convenient transportation, reduces cost of transportation, expands application.Fig. 1 shows many of the unmanned plane Individual mounting mechanism, including wing assembling and disassembling device (601,603), tail supporting rod-wing assembling and disassembling device 605, tail supporting rod-empennage assembly and disassembly dress Put 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, Wing is divided 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 exhibitions A kind of assembling-disassembling structure is shown, the structure is ear sheet type connecting structure, assembly and disassembly hole 611,613 is bolt connecting hole.Installation sheet 615, 617 are fixedly connected for auricle with wing.Figure 12 b show the wing assembling-disassembling structure of another tubular type, and central wing is led to outer wing The form connection of pipe fitting sleeving is crossed, one section of pipe 605 and outer wing are affixed, and stretch out the segment length of outer wing one, another section of pipe 607 and center The wing is affixed to be embedded in central wing.Pipe 605 stretches out the external cylindrical surface of outer panel and the inner cylinder face of pipe 607 coordinates.Tail supporting rod is assembled and disassembled Device is located at tail supporting rod and wing link position, the assembly and disassembly for wing and tail supporting rod.Figure 13 is a kind of tubular type shoe Bar attachment structure, wherein mounting hole 611 are the structure and fuselage bolt connection；Positioning lock tieholen 613 be 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 knot with fluting Structure.Its mesopore 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 present utility model, a kind of to have three sections of aerofoil profiles, the anury of propeller protection device Agricultural spraying 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 preferred embodiment of the present utility model, rather than its limitations；Although it should be pointed out that with reference to upper Each embodiment is stated the utility model is described in detail, it will be understood by those within the art that, it still can be with Technical scheme described in the various embodiments described above is modified, or which part or all technical characteristic are equally replaced Change；And these modifications and replacement, the essence of corresponding technical scheme is departed from each embodiment technical scheme of the utility model Scope.

Claims (10)

1. the three-stage fixed-wing unmanned plane provided with protection device, it is characterised in that the wing of the fixed-wing unmanned plane is three sections Formula airfoil structure, including it is arranged on the slat of the leading edge of a wing, the main wing being arranged in the middle of wing and the flap for being arranged on trailing edge The wing, main wing includes the outer wing of central wing and centrally disposed wing both sides, and wing flap includes the wing flap of centrally disposed wing trailing edge and set Put the flaperon in outer wing trailing edge；

Preceding pull-type propeller is provided with front fuselage, protection device includes propeller protection device, wingtip protection device, empennage and protected Protection unit：Propeller protection device is located at the both sides and front of propeller, including skeleton and buffer unit, and buffer unit is attached at 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, the first vertical pole It is fixedly connected on second vertical pole one end on wing, the other end extends forward, is connected with cross bar；Wingtip protection device is located at wing At wingtip, including left wing's tip wipes ground piece and the right flank tip wipes ground piece, the lower section of left and right wingtip is separately mounted to, when aircraft side wing When contacting 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 empennage Ground piece is wiped, when aircraft excessively comes back and afterbody is contacted to earth, empennage is wiped ground piece and contacted to earth at first.

2. the three-stage fixed-wing unmanned plane according to claim 1 provided with protection device, it is characterised in that the fixation The wing is rectangular wing, and middle central wing is flat segments, and left right lateral outer wing carries the upper counterangle.

3. the three-stage fixed-wing unmanned plane according to claim 1 provided with protection device, it is characterised in that the wing flap It is fixed structure, removable or turntable with respect to main wing；The slat is fixed structure, may move or rotation relative to main wing Structure.

4. the three-stage fixed-wing unmanned plane according to claim 1 provided with protection device, it is characterised in that the center It is detachable structure between the wing and outer wing, central wing passes through some assembling and disassembling device installation wings with outer wing.

5. the three-stage fixed-wing unmanned plane according to claim 4 provided with protection device, it is characterised in that unmanned plane is also Including empennage, empennage includes the empennage attachment structure at wing rear and tailplane, the vertical tail at empennage attachment structure rear, Empennage attachment structure is connected by assembling and disassembling device with wing, and tailplane, vertical tail are connected knot with empennage by assembling and disassembling device Structure is connected；Wherein, tailplane is stabilator, and aerofoil profile neutrality line is middle recessed camber line, tailplane root Chord length is more than or equal to the chord length of taper；Vertical tail is dynamic vertical tail entirely, and the chord length of the root of vertical tail is more than or equal to the tip The chord length in portion.

6. the three-stage fixed-wing unmanned plane according to claim 5 provided with protection device, it is characterised in that empennage is connected Structure is a rod member, and bar cross section is constant or changes, and when bar cross section is change structure, the end section close to head is big In by a caudal end section.

7. the three-stage fixed-wing unmanned plane according to claim 5 provided with protection device, it is characterised in that the assembly and disassembly Device includes wing assembling and disassembling device, tail supporting rod-wing assembling and disassembling device and tail supporting rod-empennage assembling and disassembling device, wing assembling and disassembling device point Cloth is upward in wing exhibition, and wing is divided into three sections of left, center, right, and three sections of wings carry out assembly and disassembly by wing assembling and disassembling device；

Wing assembling and disassembling device is ear sheet type connecting structure, and ear sheet type connecting structure is provided with assembly and disassembly hole, and assembly and disassembly hole is bolt connection Hole, ear sheet type connecting structure is provided with the installation sheet for being used for being fixedly connected with wing；

Or

Wing assembling and disassembling device is tubular type attachment structure, and central wing is connected with outer wing by the form of pipe fitting sleeving, and one section is managed and outer The wing is affixed, and stretches out the segment length of outer wing one, and another section of pipe is embedded in central wing；

Tail supporting rod-wing assembling and disassembling device is tubular type attachment structure, and pipe is provided with mounting hole, and bolt is passed through by mounting hole and fuselage Connection；Positioning lock tieholen is additionally provided with pipe；Pipe end is additionally provided with locking hoop；

Tail supporting rod-empennage assembling and disassembling device is the rectangle structure with fluting, provided with tail supporting rod mounting hole, tail supporting rod locking hole, is put down Tail mounting hole and vertical fin mounting hole.

8. the three-stage fixed-wing unmanned plane according to claim 1 provided with protection device, it is characterised in that left wing's tip is wiped The streamlined structure of direction of flow when ground piece and the right flank tip wipe ground piece for along unmanned plane during flying；It is along nothing that empennage, which wipes ground piece, The streamlined structure of direction of flow during man-machine flight；It is the laminated structure that unmanned plane is connected to by fastener to wipe ground piece.

9. the three-stage fixed-wing unmanned plane according to claim 1 provided with protection device, it is characterised in that it is described nobody Machine also includes front three-point wheel undercarriage, and undercarriage includes nose-gear and main landing gear, and nose-gear is protected installed in propeller On the cross bar of protection unit, main landing gear is arranged on fuselage bottom.

10. the three-stage fixed-wing unmanned plane according to claim 9 provided with protection device, it is characterised in that the horizontal stroke Bar includes two the first cross bars and the second cross bar for having certain longitudinal separation, and nose-gear includes the oblique branch of main support rod and both sides Strut, 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, The other 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 Constitute tetrahedral structure.