CN208021707U - Fuselage for fixed-wing unmanned plane - Google Patents

Abstract

The utility model discloses a kind of fuselages for fixed-wing unmanned plane, belong to air vehicle technique field, including the second front end, the second ontology and the second rear end.Second front end and the first rear end are detachably connected；Second ontology and the second front end are fixedly connected.Second ontology includes first side and second side, and the first wing is provided in first side, and the first adjustable rotary wing mechanism is provided on the first wing；It is provided with the second wing in second side, the second adjustable rotary wing mechanism is provided on second wing；Second rear end is fixedly connected with second ontology.The utility model has reached the structure of simplified unmanned plane, makes the landing process of unmanned plane more easily technique effect.

Description

Fuselage for fixed-wing unmanned plane

Technical field

The utility model belongs to air vehicle technique field, more particularly to a kind of fuselage for fixed-wing unmanned plane.

Background technology

Unmanned unmanned plane referred to as " unmanned plane ", is grasped using radio robot and the presetting apparatus provided for oneself Vertical not manned unmanned plane.Without cockpit on machine, but automatic pilot, presetting apparatus, information collecting device are installed etc. Equipment.On ground, naval vessels or machine tool remote control station personnel are by equipment such as radars, to its into line trace, positioning, remote control, telemetering and Digital Transmission.It can take off as common unmanned plane under wireless remotecontrol or be launched with booster rocket, it also can be by machine tool Aerial launch is taken to fly.

For fixed-wing unmanned plane, unmanned aerial vehicle body in the prior art using integrally formed structure fabrication and At.Typically from the operating personnel that have received professional training and with take off in the case of parasite power；The lift of flight is It is provided by wing and positioned at the propeller of head, and needs to put down dedicated wheel undercarriage when unmanned plane landing, led Cause the load of unmanned plane excessive, landing is inconvenient.

But in the prior art, unmanned plane is complicated, and the landing process of unmanned plane is inconvenient.

Utility model content

Technical problem to be solved in the utility model is the complicated of unmanned plane, and the landing process of unmanned plane is inconvenient It is prompt.

In order to solve the above technical problems, the utility model provides a kind of fuselage for fixed-wing unmanned plane, the use Include in the fuselage of fixed-wing unmanned plane：Second front end, second front end and the first rear end are detachably connected；Second Ontology, second ontology are fixedly connected with second front end；Second ontology includes first side and second side, It is provided with the first wing in the first side, the second wing, and first wing and institute are provided in the second side State the both sides that the second wing is symmetrically distributed in second ontology along the center vertical pivot of second ontology；First wing On be provided with the first adjustable rotary wing mechanism, the second adjustable rotary wing mechanism is provided on second wing；Second rear end, Second rear end is fixedly connected with second ontology, and the diameter of section of second ontology is towards after described second It is sequentially reduced on the direction of end；Wherein, second ontology setting second front end and second rear end it Between, and second front end, second ontology and second rear end are integrally formed and constitute the fuselage.

Further, the fuselage for fixed-wing unmanned plane includes：First wing include the first preceding fastening end, First forward open end and the first positioning area, the first preceding fastening end are fixedly connected with the first side, and described first is fixed Position area is arranged between the described first preceding fastening end and first forward open end；Wherein, first forward open end and described First preceding fastening end is the both ends of first wing.

Further, the fuselage for fixed-wing unmanned plane includes：First end flank, the first end flank Angle with first wing is 60 ° -90 °；And the first end flank includes the first wing tip fastening end and the first wing tip Open end；And first wing tip fastening end is fixedly connected with first forward open end, first wing tip open end deviates from First forward open end constitutes the both ends of the first end flank with first wing tip fastening end.

Further, the fuselage for fixed-wing unmanned plane includes：Second wing include the second preceding fastening end, Second forward open end and the second positioning area, the second preceding fastening end are fixedly connected with the second side, and described second is fixed Position area is arranged between the described second preceding fastening end and second forward open end；Wherein, second forward open end and described Second preceding fastening end is the both ends of second wing.

Further, the fuselage for fixed-wing unmanned plane includes：The second end flank, the second end flank Angle with second wing is 60 ° -90 °；And the second end flank includes the second wing tip fastening end and the second wing tip Open end；And second wing tip fastening end is fixedly connected with second forward open end, second wing tip open end deviates from Second forward open end constitutes the both ends of the second end flank with second wing tip fastening end；Wherein, described first Wing tip open end and second wing tip open end are symmetrically distributed along the center vertical pivot of the fuselage.

Advantageous effect：

The utility model provides a kind of fuselage for fixed-wing unmanned plane, by by the first of the second front end and head Rear end is detachably connected so that, can be with local replacing component when fuselage local damage occur can not repair.Second ontology and Two front ends are fixedly connected, and so that the diameter of section of the second ontology is sequentially reduced on the direction towards the second rear end, to reduce Suffered gas-flow resistance in unmanned plane during flying.And the first wing is set in the first side of the second ontology, in the first wing The first adjustable rotary wing mechanism of upper setting.Second wing is set in the second side of the second ontology, is arranged on the second wing Second adjustable rotary wing mechanism, direction and power of different sizes can be generated respectively on the first wing and the second wing, after And it is landing and required power of flying that unmanned plane provides.To reach the structure of simplified unmanned plane, make the landing of unmanned plane Journey more easily technique effect.

Description of the drawings

In order to illustrate the embodiment of the utility model or the technical proposal in the existing technology more clearly, below will be to embodiment Needed in attached drawing be briefly described, it should be apparent that, the accompanying drawings in the following description is only the utility model Some embodiments for those of ordinary skill in the art without creative efforts, can also be according to this A little attached drawings obtain other attached drawings.

Fig. 1 is a kind of overall structure diagram for fixed-wing unmanned plane that the utility model embodiment provides；

Fig. 2 provides a kind of top view illustration of fixed-wing unmanned plane for the utility model embodiment；

Fig. 3 provides a kind of upward view schematic diagram of fixed-wing unmanned plane for the utility model embodiment；

Fig. 4 provides a kind of side view schematic diagram of fixed-wing unmanned plane for the utility model embodiment；

Fig. 5 provides a kind of front view schematic diagram of fixed-wing unmanned plane for the utility model embodiment；

Fig. 6 provides a kind of structure diagram of the dynamical system of fixed-wing unmanned plane for the utility model embodiment；

100-heads, the 110-the first front end, 120-the first noumenons, the 130-the first rear end, 140-pitots；

200-fuselages, the 210-the second front end, the 220-the second ontology, the 230-the first wing, the 240-the second wing, 250-the first adjustable rotary wing mechanism, the 251-the first linking arm, the 252-the first propeller, 253-the first verts component, 254-the first rotor, the 255-the first limiting slot, the 260-the second adjustable rotary wing mechanism, the 261-the second linking arm, 262-the Two propellers, 263-the second verts component, the 264-the second rotor, the 265-the second limiting slot, the 270-the second rear end, 280-the first aileron, the 290-the second aileron；

300-tails, 310-third front ends, 320-third ontologies, 330-third rear ends, the 340-the first aerofoil Plate, the 350-the second aerofoil plate；

400-dynamical systems, 410-power supply parts, 420-displacement components, the 421-the first steering engine, the 422-the second rudder Machine, 430-driving parts, 431-first motors, the 432-the second motor, 433-third motors, the 434-the four motor, 440-regulating members, the 441-the first electricity are adjusted, and the 442-the second electricity is adjusted.

Specific implementation mode

The utility model provides a kind of fuselage for fixed-wing unmanned plane, by by the first of the second front end and head Rear end is detachably connected so that, can be with local replacing component when fuselage local damage occur can not repair.Second ontology and Two front ends are fixedly connected, and so that the diameter of section of the second ontology is sequentially reduced on the direction towards the second rear end, to reduce Suffered gas-flow resistance in unmanned plane during flying.And the first wing is set in the first side of the second ontology, in the first wing The first adjustable rotary wing mechanism of upper setting.Second wing is set in the second side of the second ontology, is arranged on the second wing Second adjustable rotary wing mechanism, direction and power of different sizes can be generated respectively on the first wing and the second wing, after And it is landing and required power of flying that unmanned plane provides.To reach the structure of simplified unmanned plane, make the landing of unmanned plane Journey more easily technique effect.

In order to elaborate to a kind of fuselage for fixed-wing unmanned plane provided by the utility model, to support practicality Novel technical problem to be solved first does in detail fixed-wing unmanned plane in the following, in embodiment provided by the utility model Illustrate, then during describing fixed-wing unmanned plane, further targetedly draws one kind provided by the utility model It is complete, clear, clear to achieve the purpose that for the fuselage of fixed-wing unmanned plane.

Before introducing the utility model embodiment, the whole feelings first to fixed-wing unmanned plane provided by the utility model Condition does following general description：The utility model by being divided into the fuselage 200 of unmanned plane including at least three sections, i.e., head 100, Fuselage 200 and tail 300, and be attached by the connection type of detachable connection between three sections, it is constituted in one with this The dismountable fixed-wing unmanned plane of portion's structure, so that, can be corresponding when local damage occurs in the fuselage 200 of unmanned plane It removes the position for occurring damaging to repair, there is simple, convenient technique effect.And when fuselage 200 it is local because Appearance is when damaging and can not repair, can also the position that can not repair of corresponding dismounting, i.e., the position that can not be repaired is carried out more It replaces, to overcome in the prior art because fuselage 200 is using integrated global design so that 200 part damage of fuselage occur When wound can not repair, it has to which the technological deficiency for replacing the entire fuselage 200 of unmanned plane reaches and significantly reduces maintenance cost Technique effect.

Also, unmanned plane is during executing landing operation, included by the fixed-wing unmanned plane in the utility model The first adjustable rotary wing mechanism 250 being arranged on the first wing 230, and second be arranged on the second wing 240 are adjustable Rotor mechanism 260 carries out matching operation (being operated) and generates lifting force, and fuselage 200 is pulled to rise or decline.Example Such as：When unmanned plane takes off, first is pushed to vert portion by the first steering engine 421 controlled in the first adjustable rotary wing mechanism 250 Part 253 makes the first propeller 252 be located in the plane with unmanned plane level, passes through first motor 431 and drives the first propeller 252 work, make the first propeller 252 provide lift for unmanned plane；Control the second rudder in the second adjustable rotary wing mechanism 260 Machine 422 pushes second to vert component 263, make the second propeller 262 be located at and the plane of unmanned plane level in, it is electric to pass through third Machine 433 drives the work of the second propeller 262, so that the second propeller 262 is also provided lift for unmanned plane, by the first propeller 252 Resultant force, upward lifting force is provided for unmanned plane caused by rotation with the second propeller 262, to realize hanging down for unmanned plane Directly take off.It when unmanned plane is drawn high certain altitude, then pushes first to vert component 253 by the first steering engine 421, makes the first spiral shell Revolve paddle 252 be located at and the perpendicular plane of plane of unmanned plane level in, verted component by the second steering engine 422 promotion second 263, make in the plane that the second propeller 262 is located at and the plane of unmanned plane level is perpendicular, to generate water on unmanned plane Flat-pushing power pushes unmanned plane to slide in the air and takes off, and then enters stabilized flight.When declining, by controlling the first steering engine 421 Push first to vert component 253, make the first propeller 252 be located at and the plane of unmanned plane level in, pushed away by the second steering engine 422 Dynamic second verts component 263, make the second propeller 262 be located at and the plane of unmanned plane level in, make 252, the first propeller with Second 262, propeller pulls fuselage 200 to stablize decline from eminence, until stablizing landing, avoids 200 hard landing of fuselage and causes Fuselage 200 and carrying equipment damage, greatly reduce the risk of landing accident, having reached makes unmanned plane be suitble to different Flying field carries out the technique effect of landing operation.

The following will be combined with the drawings in the embodiments of the present invention, carries out the technical scheme in the embodiment of the utility model Clearly and completely describe, it is clear that the described embodiments are only a part of the embodiments of the utility model, rather than whole Embodiment.Based on the embodiments of the present invention, the every other embodiment that those of ordinary skill in the art are obtained all belongs to In the range of the utility model protection；Involved "and/or" keyword wherein in this implementation, indicate and or two kinds of situations, change Sentence is talked about, and the A mentioned by the utility model embodiment and/or B illustrate two kinds of A and B, A or B situations, describe A and B and deposited Three kinds of states indicate such as A and/or B：It includes B to only include A not；It includes A to only include B not；Including A and B.

Meanwhile in the utility model embodiment, when component is referred to as " being fixed on " another component, it can be directly another On one component or there may also be components placed in the middle.When a component is considered as " connection " another component, it can be It is directly connected to another component or may be simultaneously present component placed in the middle.When a component be considered as " being set to " another Component, it can be set up directly on another component or may be simultaneously present component placed in the middle.The utility model embodiment Used in term " vertical ", " horizontal ", "left", "right" and similar statement be merely for purposes of illustration, not It is intended to limit the utility model.

It is new to this practicality first in order to which the fixed-wing unmanned plane provided the utility model embodiment is described in detail Involved technical term does description below explanation in type embodiment：

Detachable connection can be：It is bolted or is bonded；

Being fixedly connected to be：Welding is integrally formed；

Ground can be：The ground that unmanned plane is parked, or the face with this plane parallel；

Minimum flying speed can be：Minimum flying speed when making unmanned plane keep flight, and not falling.Such as： In the present embodiment, the minimum flying speed of unmanned plane can be 20m/s；

Takeoff phase can be：Unmanned plane reaches the process of aerial vertical ascent from ground；

Take off winged stage that flattens can be：After unmanned plane reaches in the air, the process of horizontal flight is carried out；

Landing phases can be：Process of the unmanned plane from airborne to ground.

Fig. 1 is referred to, Fig. 1 is a kind of overall structure signal for fixed-wing unmanned plane that the utility model embodiment provides Figure.A kind of fixed-wing unmanned plane that the utility model embodiment provides.A kind of fixed-wing unmanned plane includes head 100, fuselage 200, tail 300 and dynamical system 400 now carry out head 100, fuselage 200, tail 300 and dynamical system 400 following respectively It is described in detail：

For head 100：

Head 100 may include the first front end 110, the first noumenon 120 and the first rear end 130.First front end 110 can be rendered as pyramidal structure, and pitot 140 can be fixedly connected on the first front end 110；The first noumenon 120 can To be fixedly connected with the first front end 110, and the diameter of section of the first front end 110 is in the direction towards the first noumenon 120 On be sequentially increased；First rear end 130 can be fixedly connected with the first noumenon 120, and the diameter of section of the first noumenon 120 exists It is sequentially increased on towards the direction of the first rear end 130；Wherein, the first noumenon 120 is arranged behind the first front end 110 and first Between end 130, and the first front end 110, the first noumenon 120 and the first rear end 130 are integrally formed and constitute head 100.

Show continuing with a kind of overall structure for the fixed-wing unmanned plane for referring to Fig. 1, Fig. 1 being the utility model embodiment offer It is intended to.First front end 110 can be fixedly connected with the first noumenon 120, and the first rear end 130 can be solid with the first noumenon 120 Fixed connection, to be made of the head 100 of unmanned plane the first front end 110, the first noumenon 120 and the first rear end 130.Nobody The head 100 of machine can be rendered as hollow structure, i.e., the electric elements of placement camera can be accommodated in the inside of head 100 Space.It can be provided with pitot 140 on the first front end 110.Pitot 140 is also Pitot tube, stagnation pressure tube etc., air speed Pipe 140 is to experience the stagnation pressure (also referred to as total head) and static pressure of air-flow, and send the pressure data measured to atmosphere data and calculate The device of machine, flying instruments.Pitot 140 is primarily used to measure flying speed, while can also have both other a variety of work( Energy.

Since the diameter of section of the first front end 110 is sequentially increased on the direction towards the first noumenon 120, the first noumenon 120 diameter of section is sequentially increased on the direction towards the first rear end 130, and the first front end 110 is rendered as taper Structure.So that 100 overall construction of head of unmanned plane, can be in flight course in unmanned plane, effectively reduce air-flow to nothing Man-machine obstruction moves loss of energy to reduce unmanned plane itself, can improve the cruise duration of unmanned plane.

For fuselage 200：

Fuselage 200 may include the second front end 210, the second ontology 220 and the second rear end 270.Second front end 210 and first rear end 130 be detachably connected, the second ontology 220 is fixedly connected with the second front end 210, the second rear end Portion 270 is fixedly connected with second ontology 220, and the diameter of section of second ontology 220 is towards second rear end It is sequentially reduced on 270 direction.

Second ontology 220 may include first side and second side, and the first wing 230 is provided in first side, the It is provided with the second wing 240 on two side faces, and the first wing 230 and the second wing 240 are along the center of the second ontology 220 Vertical pivot is symmetrically distributed in the both sides of the second ontology 220；The first adjustable rotary wing mechanism 250 is provided on first wing 230, The second adjustable rotary wing mechanism 260 is provided on second wing 240.

Second ontology 220 is arranged between the second front end 210 and the second rear end 270, and the second front end 210, Second ontology 220 and the second rear end 270, which are integrally formed, constitutes the fuselage 200；

First wing 230 may include the first preceding fastening end, the first forward open end and the first positioning area, the first preceding fastening end It is fixedly connected with first side, and the first positioning area is arranged between the first preceding fastening end and the first forward open end；Wherein, One forward open end and the first preceding fastening end are the both ends of first wing 230.

Fuselage 200 can also include the first linking arm 251 and the second linking arm 261.First linking arm 251 includes first End, second end and the first interlude, the first interlude and the first positioning area are detachably connected；First end and second end is described The both ends of one linking arm 251.First adjustable rotary wing mechanism 250 may include the first propeller 252, first motor 431, first Vert component 253, the first steering engine 421.First motor 431 is provided with the first drive shaft and first base, the first drive shaft and One propeller 252 is fixedly connected；First component 253 that verts includes the first pedestal and the first limiting slot 255, the first pedestal and the One pedestal is fixedly connected, and the first limiting slot 255 is fixedly connected with first end, and the first limiting slot 255 is mutually cut with scissors with the first pedestal It connects, the first pedestal is arranged between the first limiting slot 255 and first base；First steering engine 421 includes that first rotating shaft and first are tight Gu seat, first rotating shaft is connected with the first pedestal, and the first fastening seat and the first limiting slot 255 are fixedly connected, and first rotating shaft is set It sets between the first pedestal and the first limiting slot 255；Wherein, the first drive shaft is mutually hung down with the rotational plane of the first propeller 252 Directly.

Fuselage 200 can also include the first rotor 254 and the second motor 432.Second motor 432 is provided with the second driving Axis and second base, second base are fixedly connected with second end, and the second drive shaft is fixedly connected with the first rotor 254；Described The rotational plane of two drive shafts and first rotor 254 is perpendicular.

Second wing 240 may include the second preceding fastening end, the second forward open end and the second positioning area, the second preceding fastening end It is fixedly connected with second side, and the second positioning area is arranged between the second preceding fastening end and the second forward open end；Before second Open end and the second preceding fastening end are the both ends of second wing 240.

Second linking arm 261 may include third end, the 4th end and the second interlude, the second interlude and the second positioning area It is detachably connected；Third end and the 4th end are the both ends of second linking arm 261.Second adjustable rotary wing mechanism 260 can be with It verts component 263 and the second steering engine 422 including the second propeller 262, third motor 433, second.Third motor 433 is provided with Third drive shaft and third pedestal, third drive shaft are fixedly connected with the second propeller 262；Second component 263 that verts can wrap The second pedestal and the second limiting slot 265 are included, the second pedestal is fixedly connected with third pedestal, and the second limiting slot 265 and third end are solid Fixed connection, and the second limiting slot 265 and the second pedestal are hinged, the setting of the second pedestal is in the second limiting slot 265 and described the Between three pedestals；Second steering engine 422 may include the second shaft and the second fastening seat, and the second shaft is connected with the second pedestal, the Two fastening seats and the second limiting slot 265 are fixedly connected, and the setting of the second shaft the second pedestal and the second limiting slot 265 it Between；The rotational plane of third drive shaft and second propeller 262 is perpendicular.

Fuselage 200 can also include the second rotor 264 and the 4th motor 434.4th motor 434 is provided with the 4th driving Axis and the 4th pedestal, the 4th pedestal and the 4th end are fixedly connected, and the 4th drive shaft is fixedly connected with the second rotor 264；4 wheel driven The rotational plane of moving axis and second rotor 264 is perpendicular.

Fuselage 200 can also include first end flank and/or the second end flank.

The angle of first end flank and the first wing 230 can be 60 ° -90 °.First end flank may include first Wing tip fastening end and the first wing tip open end；And the first wing tip fastening end is fixedly connected with the first forward open end, the first wing tip Open end constitutes the both ends of first end flank away from the first forward open end and the first wing tip fastening end.

The angle of the second end flank and the second wing 240 can be 60 ° -90 °.The second end flank may include second Wing tip fastening end and the second wing tip open end；And the second wing tip fastening end is fixedly connected with the second forward open end, the second wing tip Open end constitutes the both ends of the second end flank away from the second forward open end and the second wing tip fastening end.Wherein, first wing Sharp open end and second wing tip open end are symmetrically distributed along the center vertical pivot of the fuselage 200.

Fuselage 200 can also include the first aileron 280 and/or the second aileron 290.The setting of first aileron 280 rotation exists On first wing 230, and the first aileron 280 is rotated on the first wing 230 relative to first side；And/or the Two ailerons 290 rotation setting on the second wing 240, and the second aileron 290 on the second wing 240 relative to the second side Face is rotated.

Fig. 2 is referred to, Fig. 2 is that the utility model embodiment provides a kind of top view illustration of fixed-wing unmanned plane.Machine Second front end 210 of body 200 can be detachably connected with the first rear end 130 of head 100.During fuselage 200 can have Second ontology 220 of hollow structure, i.e. fuselage 200 can be hollow, which can be used for accommodating photography, camera shooting is set Standby, electric elements etc..The diameter of section of second ontology 220 can be sequentially reduced on the direction towards the second rear end 270, be made 200 overall construction of fuselage for obtaining unmanned plane, can be in flight course in unmanned plane, effectively reduce and flow through unmanned aerial vehicle body 200 air-flow moves loss of energy to reduce unmanned plane itself, improves the cruise duration of unmanned plane to the obstruction of unmanned plane.

First side and second side can be two opposites of 200 second ontology 220 of fuselage, such as can be and ground Two perpendicular sides of face.First wing 230 is installed on the first side, and the second wing 240 is installed on the second side.The One wing 230 and the second wing 240 can symmetrically be distributed in the second ontology 220 along the center vertical pivot of the second ontology 220 Both sides.Assuming that the plane residing for the first wing 230 and the second wing 240 is A planes, (top is at the top of the second ontology 220 Side far from ground, bottom are the side close to ground, and top and bottom make mutually contradictory) residing for plane it is flat for B Face can be then that A plane ratio B planes are farther from the ground relative to the distance on ground.The spacing of A planes and B planes can be with It is needed according to the design of unmanned plane to determine, such as distance range can be 10cm -1000cm.Between A planes and B planes It can be provided with support member, which connects A planes and B planes, so that A planes and B planes is fixed to each other, such as first Wing 230 and the second wing 240 are fixedly mounted on the support columns, and the top of the support column and the second ontology 220 is fixedly connected, Support column is between A planes and B planes, and support column is mutually perpendicular to the first wing 230 and the second wing 240 respectively, Then so that the first adjustable rotary wing mechanism 250 on the first wing 230 is operated in the space far from B planes, also make the second wing The second adjustable rotary wing mechanism 260 on 240 operates in the space far from B planes, if so as to avoid by the first adjustable rotary First propeller 252 in wing mechanism 250, the second propeller 262 is all located in B planes in the second adjustable rotary wing mechanism 260, and And when the first propeller 252 and closer 262 the second ontology of distance 220 of the second propeller, due to turning for the first propeller 252 Dynamic, the second propeller 262 rotation so that the first propeller 252 and the second propeller 262 collide the second ontology 220, cause Safety accident occurs, unmanned plane is forced to be stopped suddenly, and collides the propeller broken blade generated after generation, jeopardizes winged Personnel safety in row region.

Fig. 3 is referred to, Fig. 3 is that the utility model embodiment provides a kind of upward view schematic diagram of fixed-wing unmanned plane.? Can be installed with the first linking arm 251 in first positioning area of the first wing 230, the first linking arm 251 first among Section can also be detachably connected with the first positioning area so that when the first linking arm 251 loses, or be connected to the first linking arm When the first adjustable rotary wing mechanism 250 in 251 in first end breaks down, the first linking arm 251 can be replaced in time. When can not be repaired to overcome the appearance damage of the first adjustable rotary wing mechanism 250, it has to replace the entire fuselage of unmanned plane 200 technological deficiency reaches the technique effect for significantly reducing maintenance cost.First linking arm 251 can be with the first wing 230 are mutually perpendicular to, i.e. the first linking arm 251 can be with the center vertical pivot of the second ontology 220 mutually usually, this makes the first connection It the both ends of arm 251 can be far from the second ontology 220, to turn for the first adjustable rotary wing mechanism 250 and the first rotor 254 The dynamic space for providing bigger, promotes the safety during unmanned plane during flying or landing.

The second linking arm 261, the second linking arm 261 can be installed in the second positioning area of the second wing 240 The second interlude can also be detachably connected with the second positioning area so that when the second linking arm 261 loses, or be connected to It, can be in time to the second linking arm when the second adjustable rotary wing mechanism 260 in second linking arm 261 in second end breaks down 261 replace.When can not be repaired to overcome the appearance damage of the second adjustable rotary wing mechanism 260, it has to replace unmanned plane The technological deficiency of entire fuselage 200, reaches the technique effect for significantly reducing maintenance cost.Second linking arm 261 can be with Second wing 240 is mutually perpendicular to, i.e. the second linking arm 261 can be with the center vertical pivot of the second ontology 220 mutually usually, this makes It the both ends of second linking arm 261 can be far from the second ontology 220, to be revolved for the second adjustable rotary wing mechanism 260 and second The rotation of the wing 264 provides the space of bigger, promotes the safety during unmanned plane during flying or landing.

Fig. 1 is referred to, Fig. 1 is a kind of overall structure signal for fixed-wing unmanned plane that the utility model embodiment provides Figure.In order to which the first adjustable rotary wing mechanism 250 and the second adjustable rotary wing mechanism 260 are described in detail, now provide following Two kinds of embodiments are explained in detail：

The first embodiment.First adjustable rotary wing mechanism 250 may include the first propeller 252, first motor 431, first verts component 253, the first steering engine 421.First propeller 252 can be twayblade, i.e., the first propeller 252 can To include two blades；First propeller 252 can also be multiple-blade (more than two blade).Two blades can be with first First drive shaft of motor 431 is fixedly connected, and two blades can symmetrically be distributed in the both sides of the first drive shaft, and first Drive shaft and the plane of two blades rotation are perpendicular.The first base of first motor 431 can vert component 253 with first The first pedestal be fixedly connected, first motor 431 first fastening seat can be fixedly connected with the first limiting slot 255, first inclines First limiting slot 255 of rotation member 253 can be fixedly connected with the first end of the first linking arm 251.Due to the first limiting slot 255 It is hinged with the first pedestal, such as：It is fixed with protruding end in one end of the first limiting slot 255, through-hole is provided on the protruding end (abbreviation K1)；It is fixed with another protruding end on a face being away from each other with first motor 431 on the first pedestal, the protruding end On be provided with through-hole (abbreviation K2), K1 and K2 match, i.e. the diameter of K1 and K2 can be identical.Bearing can be worn from K1 and K2 It crosses, and the bearing can be connected with the first rotating shaft of the first steering engine 421.First rotating shaft is allow to drive bearing operation, By operating drive the first pedestal to be moved relative to the first limiting slot 255, the direction of the movement can be relative to Ground be 0 ° -90 ° and/or 0 °-(- 90 °), wherein 90 ° refer to being directed away from ground, be located at unmanned plane above, and and Angle when ground is perpendicular；- 90 ° refer to being directed away from ground, is located at below unmanned plane, and with ground when perpendicular Angle；0 ° refers to angle with ground when parallel.Existed to control the first propeller 252 by the first steering engine 421 to realize 0 ° -90 ° and/or 0 °-(- 90 °) in the range of rotated.First electricity can be installed to adjust on the first limiting slot 255 441, the first electricity tune 441 can be connected with first motor 431, passed through the first electricity and adjusted 441 rotations that can control first motor 431 Rotary speed adjusts 441 to adjust the rotating speed of the first propeller 252 to realize by the first electricity.

It can be fixedly installed the second motor 432 in the second end of the first linking arm 251, the second of the second motor 432 Pedestal can be fixedly connected with second end.Second drive shaft of the second motor 432 can be fixedly connected with the first rotor 254, And the rotational plane of the second drive shaft and the first rotor 254 is perpendicular.First rotor 254 can be multiple-blade (2 or more Blade) rotor.Above-mentioned first propeller 252 can be the propeller of big screw pitch, i.e., the pitch of the first rotor 254 is than the first rotation The pitch of the wing 254 is small.Since the pitch of the first rotor 254 is more than the pitch of the first rotor 254, so the first rotor 254 exists 0 ° -90 ° and/or 0 °-(- 90 °) in the range of when being rotated, the thrust or lift of bigger can be provided for unmanned plane.

Second of embodiment.Second adjustable rotary wing mechanism 260 may include the second propeller 262, third motor 433, second verts component 263, the second steering engine 422.Second propeller 262 can be twayblade, i.e., the second propeller 262 can To include two blades；Second propeller 262 can also be multiple-blade (more than two blade).Two blades can and third The third drive shaft of motor 433 is fixedly connected, and two blades can symmetrically be distributed in the both sides of third drive shaft, third Drive shaft and the plane of two blades rotation are perpendicular.The third pedestal of third motor 433 can vert component 263 with second The second pedestal be fixedly connected, the second steering engine 422 second fastening seat can be fixedly connected with the second limiting slot 265, second inclines Second limiting slot 265 of rotation member 263 can be fixedly connected with the third end of the second linking arm 261.Due to the second limiting slot 265 It is hinged with the second pedestal, such as：It is fixed with protruding end in one end of the second limiting slot 265, through-hole is provided on the protruding end (abbreviation K3)；It is fixed with another protruding end on a face being away from each other with third motor 433 on the second pedestal, the protruding end On be provided with through-hole (abbreviation K4), K3 and K4 match, i.e. the diameter of K3 and K4 can be identical.Bearing can be worn from K3 and K4 It crosses, and the bearing can be connected with the second shaft of the second steering engine 422.The second shaft is allow to drive bearing operation, By operating drive the second pedestal to be moved relative to the second limiting slot 265, the direction of the movement can be relative to Ground be 0 ° -90 ° and/or 0 °-(- 90 °), wherein 90 ° refer to being directed away from ground, be located at unmanned plane above, and and Angle when ground is perpendicular；- 90 ° refer to being directed away from ground, is located at below unmanned plane, and with ground when perpendicular Angle；0 ° refers to angle with ground when parallel.Existed to control the second propeller 262 by the second steering engine 422 to realize 0 ° -90 ° and/or 0 °-(- 90 °) in the range of rotated.Second electricity can be installed to adjust on the second limiting slot 265 442, the second electricity tune 442 can be connected with the second motor 432, passed through the second electricity and adjusted 442 rotations that can control the second motor 432 Rotary speed adjusts 442 to adjust the rotating speed of the second propeller 262 to realize by the second electricity.

It can be fixedly installed the 4th motor 434 on the 4th end of the second linking arm 261, the 4th of the 4th motor 434 the Pedestal can be fixedly connected with the 4th end.4th drive shaft of the 4th motor 434 can be fixedly connected with the second rotor 264, And the rotational plane of the 4th drive shaft and the second rotor 264 is perpendicular.Second rotor 264 can be multiple-blade (2 or more Blade) rotor.Above-mentioned second propeller 262 can be the propeller of big screw pitch, i.e., the pitch of the second rotor 264 is than the second spiral shell The pitch for revolving paddle 262 is small.Since the pitch of the second propeller 262 is more than the pitch of the second rotor 264, so the second propeller 262 0 ° -90 ° and/or 0 °-(- 90 °) in the range of rotated when, can be provided for unmanned plane bigger thrust or Lift.

In the first above-mentioned embodiment, the first adjustable rotary wing mechanism 250 may be mounted at the first linking arm 251 In second end, the first rotor 254 may be mounted in the first end of the first linking arm 251；Or in the first linking arm 251 First adjustable rotary wing mechanism 250 is installed, it is adjustable to be also equipped with first in the second end of the first linking arm 251 in first end Formula rotor mechanism 250.In above-mentioned second of embodiment, the second adjustable rotary wing mechanism 260 may be mounted at the second connection On 4th end of arm 261, the second rotor 264 may be mounted on the third end of the second linking arm 261；Or in the second linking arm Second adjustable rotary wing mechanism 260 is installed on 261 third end, is also equipped on the 4th end of the second linking arm 261 Two adjustable rotary wing mechanisms 260.Since the first adjustable rotary wing mechanism 250 being mounted in the second end of the first linking arm 251 Structure and it is above-mentioned by the first adjustable rotary wing mechanism 250 be mounted on the first linking arm 251 first end on structure it is similar Seemingly；By the second adjustable rotary wing mechanism 260 be mounted on the second linking arm 261 the 4th end on structure and it is above-mentioned can by second The structure that mode rotor mechanism 260 is mounted on the third end of the second linking arm 261 is similar.It is not repeated herein.

In order to the first adjustable rotary wing mechanism 250 and the second adjustable rotary wing mechanism 260 for unmanned plane provide lift or Thrust realizes that the landing of unmanned plane is explained in detail, and now provides following embodiment and is described in detail：

The first embodiment, takeoff phase.The first steering engine 421 can be controlled by flight control system, push the first spiral Paddle 252 is moved to 90 ° of positions；Then it adjusts 441 control first motors 431 to work by the first electricity, is driven by first motor 431 First propeller 252 rotates, and adjusts 441 to promote the rotating speed of first motor 431 by the first electricity so that the first propeller 252 rotating speed increases.Meanwhile by flight control system, the second steering engine 422 is controlled, push the second propeller 262 to be moved to 90 ° of positions It sets；Then it adjusts 442 control third motors 433 to work by the second electricity, drives the second propeller 262 to rotate by third motor 433, And 442 are adjusted to promote the rotating speed of third motor 433 by the second electricity so that triple propeller rotating speed increases.Due to first Propeller 252 and the second propeller 262 are moved to 90 ° of positions, and the lift perpendicular to ground can be then provided for unmanned plane；And And first the rotating speed of propeller 252 and the second propeller 262 increase, can then increase the lift of unmanned plane, finally so that nothing After the enough lift of man-machine acquisition, take off vertically.

Second of embodiment is taken off the winged stage that flattens.It is in and takes off vertically in unmanned plane, and rise to certain altitude Afterwards.The first steering engine 421 can be controlled by flight control system, the first propeller 252 is pushed to be gradually moved into 0 ° of position；Then pass through First electricity adjusts 441 control first motors 431 to work, and drives the first propeller 252 to rotate by first motor 431, and pass through the One electricity adjusts 441 first to reduce the rotating speed of first motor 431, is then lifted out the rotating speed of first motor 431 so that the first propeller The ascending increase of 252 rotating speed.Meanwhile by flight control system, the second steering engine 422 is controlled, push the second propeller 262 to move It moves to 0 ° of position；Then it adjusts 442 control third motors 433 to work by the second electricity, the second propeller is driven by third motor 433 262 rotations, and adjust 442 first to reduce the rotating speed of third motor 433 by the second electricity, it is then lifted out turning for third motor 433 Speed so that the ascending increase of triple propeller rotating speed.Since the first propeller 252 and the second propeller 262 are moved to 0 ° of position can then provide the thrust for being parallel to ground for unmanned plane；And the first propeller 252 and the second propeller 262 Rotating speed increase after, can then increase the thrust of unmanned plane, finally so that unmanned plane obtain minimum flying speed, in the air into Row flight.

The third embodiment, landing phases.During unmanned plane is in flat and flies, the can be controlled by flight control system One steering engine 421 pushes the first propeller 252 to be gradually moved into 90 ° of positions from 0 °；Then 441 controls first are adjusted by the first electricity Motor 431 works, and drives the first propeller 252 to rotate by first motor 431, and adjusts 441 to reduce first by the first electricity The rotating speed of motor 431 so that the rotating speed of the first propeller 252 is gradually reduced.Meanwhile by flight control system, controlling the second steering engine 422, it pushes the second propeller 262 to be moved to and is gradually moved into 90 ° of positions from 0 °；Then 442 control thirds are adjusted by the second electricity Motor 433 works, and drives the second propeller 262 to rotate by third motor 433, and adjusts 442 to reduce third by the second electricity The rotating speed of motor 433 so that triple propeller rotating speed is gradually reduced.Since the first propeller 252 and the second propeller 262 move It moves to 90 ° of positions, the pulling force perpendicular to ground can be then provided for unmanned plane；And the first propeller 252 and the second spiral After the rotating speed of paddle 262 is gradually reduced, it can be then gradually reduced the thrust of unmanned plane, finally so that unmanned plane is gradual from the air Drop to ground to be landed.

First end flank may include the first wing tip fastening end and the first wing tip open end, and the first of first end flank Wing tip fastening end can be fixedly connected with the first forward open end of the first wing 230, and the first wing tip open end deviates from first Forward open end, i.e. the first wing tip open end can be located at the lower section of unmanned aerial vehicle body 200.At this point, first end flank and first Wing 230 constitutes angle (abbreviation F1), and the range of the angle (abbreviation F1) can be 60 ° -90 °；The second of the second end flank Wing tip fastening end can be fixedly connected with the second forward open end of the second wing 240, and the second wing tip open end deviates from second Forward open end, i.e. the second wing tip open end are located at the lower section of unmanned aerial vehicle body 200.At this point, the second end flank and the second wing 240 constitute angle (abbreviation F2), and the range of the angle (abbreviation F2) can be 60 ° -90 °.Above-mentioned first wing tip open end and Two wing tip open ends can be using the center vertical pivot of fuselage 200 as symmetry axis, distribution axisymmetricly.Take the folder of above-mentioned F1 and F2 Angular region can reduce " induced drag " caused by the first wing tip trailing vortex and the second wing tip trailing vortex, be reduced to reach The destruction to lift is streamed, lift resistance ratio is improved, increases voyage, has the function that the technique effect for increasing lift.Meanwhile first end Portion's flank and the second end flank are all mutually perpendicular to level ground, so first end flank and the second end flank and ground Spacing is nearest, keeps the material needed for manufacture first end flank and the second end flank also less, to mitigate first end side The own wt of the wing and the second end flank, the overall weight for reducing unmanned plane have reached increase voyage, it is motor-driven to reduce nobody Power loss (such as：Oil consumption) technique effect.When unmanned plane drops to ground, first end flank and the second end flank are also The effect of undercarriage can be served as.

Fig. 4 is referred to, Fig. 4 is that the utility model embodiment provides a kind of side view schematic diagram of fixed-wing unmanned plane.? The first aileron 280 is also provided on first wing 230, the first aileron 280 can be located at first close to the first wing 230 At forward open end, the first aileron 280 can be hinged with the first wing 230, i.e., the first aileron 280 can be relative to the first wing 230 move up and down.It is also provided with the second aileron 290 on the second wing 240, the second aileron 290 can be located at close to the At second forward open end of two wings 240, the second aileron 290 can be hinged with the second wing 240, i.e. the second aileron 290 can be with It is moved up and down relative to the second wing 240.First pair can be connected with motor respectively with the second aileron 290, pass through unmanned plane Flight control system controls motor, and first is secondary and/or second aileron 290 moves up and down driving, and then makes in nothing in-flight It is man-machine to be deflected to scheduled direction.

It can be fixedly installed U-shaped rise on the bottom (i.e. close to the side on ground) of the second ontology 220 of unmanned plane Frame is fallen, which is open towards ground, and undercarriage can integrally be made by foamed material, the angular aperture of U-shaped undercarriage It can be 90 ° -120 ° to spend range.When unmanned plane lands, the U-shaped undercarriage of foam can be touched in unmanned plane and ground During touching, the ability of shock is absorbed, reduces the impact force for facing unmanned plane in unmanned plane descent, to reach protection The safety of unmanned plane and airborne equipment.Also, when the opening angle of U type undercarriages is 90 ° or 120 °, U-shaped undercarriage confrontation The ability of ground shock power is also strong, to improve the U-shaped undercarriage stability of itself.

For tail 300：

Tail 300 may include third front end 310, third ontology 320 and third rear end 330.

Third front end 310 and the second rear end 270 can be mutually detachably connected；Before third ontology 320 and third End 310 can be mutually permanently connected；Third rear end 330 and third ontology 320 can be mutually permanently connected.Wherein, Third ontology 320 can be arranged between third front end 310 and third rear end 330, and can be by third front end 310, third ontology 320 and third rear end 330, which are integrally formed, constitutes tail 300；

Also, empennage can be provided on third ontology 320.Empennage may include the first aerofoil plate 340 and second wing Panel 350, the first aerofoil plate 340 can be fixedly connected with third ontology 320, and the second aerofoil plate 350 can be with third ontology 320 It is fixedly connected, and the first aerofoil plate 340 can be symmetrically distributed in the both sides of third ontology 320 with the second aerofoil plate 350.Its In, the first aerofoil plate 340 and the second aerofoil plate 350 may be constructed v-shaped structure, and the angular range of v-shaped structure can be 70 °- 90°。

Fig. 5 is referred to, Fig. 5 is that the utility model embodiment provides a kind of front view schematic diagram of fixed-wing unmanned plane.Machine The third front end 310 of tail 300 can be mutually detachably connected with the second rear end 270 of fuselage 200.Third ontology 320 Between third front end 310 and third rear end 330, third ontology 320 can be rendered as cylindrical structure.In third ontology 320 can be equipped with empennage at third rear end 330.Third ontology 320, which is rendered as cylinder, to be in unmanned plane In flight course, resistance of the air-flow to unmanned plane is effectively reduced, increases the cruise duration of unmanned plane, improves the flight speed of unmanned plane Degree.

Tail 300 can be rudder-vator.Rudder-vator can form (i.e. 340 He of the first aerofoil plate by two aerofoils in left and right Second aerofoil plate 350), two aerofoils in left and right can be separately fixed on the third ontology 320 of tail 300, can be on band is big The horizontal tail of dihedral.Vee tail can have the function of vertical fin and horizontal tail concurrently.Aerofoil can be divided into fixed stabilization and hinged rudder face Two parts may be alternatively configured full ejector half formula.Two V-shaped tail surfaces have certain projected area, institute in vertical view and side-looking direction Longitudinal direction (pitching) and course-stability can be played simultaneously.When both sides, rudder face makees same direction deflection, lifting rudder action；Point When not making different directions deflection (differential), then direction rudder action can be played.But tail 300 can also be tailplane or hang down Straight tail, if tail 300 is tailplane, tailplane may be mounted on the third ontology 320 of tail 300；If tail 300 be vertical tail, then vertical tail can also be mounted on the third ontology 320 of tail 300.

If tail 300 is rudder-vator, which can be by 350 structure of the first aerofoil plate 340 and the second aerofoil plate At v-shaped structure, the angular range of v-shaped structure can be 70 ° -90 °, i.e. the first aerofoil plate 340 and the second aerofoil plate 350 Angle (abbreviation β) range can be 70 ° -90 °, which can be away from the direction of level ground.When Β=70 °, It is in the flat winged stage in unmanned plane, can effectively stablize the course of unmanned plane；When Β=90 °, make different directions in unmanned plane When deflection, the effect of rudder can be provided for unmanned plane.

It (can mutually hang down with third ontology 320 side on side of the first aerofoil plate 340 towards third rear end 330 Aileron (abbreviation W1) can directly) be installed, W1 ailerons can be hinged with the first aerofoil plate 340, i.e. W1 ailerons can be relative to First aerofoil plate 340 moves up and down.It (side can be on side of the second aerofoil plate 350 towards third rear end 330 Three ontologies 320 are perpendicular) aileron (abbreviation W2) can also be installed, W2 ailerons can be hinged with the second aerofoil plate 350, i.e. W2 Aileron can be moved up and down relative to the second aerofoil plate 350.It, can be by controlling W1's and W2 when unmanned plane needs to turn to It moves up and down, to change the navigation direction of unmanned plane.To realize that unmanned plane is flexibly flown towards all directions in the air Row.

For dynamical system 400：

Dynamical system 400 may include power supply part 410, displacement component 420, driving part 430 and regulating member 440.

Power supply part 410 can be provided with the first delivery outlet, the second delivery outlet, third delivery outlet and the 4th delivery outlet.Position It may include the first steering engine 421 and the second steering engine 422 to move component 420, and the first steering engine 421 is provided with the first input port, the first rudder First input port of machine 421 can be connected with the first delivery outlet；Second steering engine 422 is provided with the second input port, the second steering engine 422 The second input port can be connected with the second delivery outlet.

Driving part 430 may include first motor 431 and the second motor 432, and it is defeated that first motor 431 is provided with third Entrance, the second motor 432 are provided with the 4th input port；Regulating member 440 may include that the first electricity tune 441 and the second electricity are adjusted 442, the first electricity adjusts 441 to be provided with the 5th input port and the 5th delivery outlet, and the first electricity adjusts 441 the 5th input port that can and power The third delivery outlet of component 410 connects, and the first electricity adjusts 441 the 5th delivery outlet that can be inputted with the third of first motor 431 Mouth connection.Second electricity tune 442 can be provided with the 6th input port and the 6th delivery outlet, and the second electricity adjusts 442 the 6th input port can To be connected with the 4th delivery outlet of power supply part 410, the second electricity adjusts 442 the 6th delivery outlet can be with the of the second motor 432 Four input ports connect.

Fig. 6 is referred to, Fig. 6 is that the utility model embodiment provides a kind of knot of the dynamical system 400 of fixed-wing unmanned plane Structure block diagram.The dynamical system 400 of unmanned plane may include power supply part 410, displacement component 420, driving part 430 and adjust Component 440.Power supply part 410 may include engine, generator, voltage-stablizer, accumulator.

Engine can be by the mechanical energy that can be converted into of other forms, such as engine is that two-stroke aviation piston starts Machine；Generator can convert the mechanical energy that engine generates to electric energy；Voltage-stablizer can keep electric caused by generator Stable voltage can be exported after voltage-stablizer, voltage-stablizer can be connected with accumulator.Accumulator is connect with voltage-stablizer Effect can be accumulator can provide electric energy for voltage-stablizer, and voltage-stablizer keeps the electric energy generated by accumulator defeated after voltage-stablizer Go out stable voltage；And if engine or generator break down, and when can not provide electric energy for unmanned plane, can cut automatically It is changed to storage battery power supply, electric energy is provided for unmanned plane by accumulator；If engine or power generation function normal work, can be nothing Man-machine offer electric energy, then accumulator stopping provide electric energy for unmanned plane；Certainly, can not be nothing if electric power deficiency occurs in accumulator Man-machine offer electric energy can be carried by engine or generator for accumulator by the normal work of engine either generator For electric energy, to supplement the electric energy of accumulator.

It, can not when engine or generator failure if only setting engine and generator provide electric energy for voltage-stablizer When providing electric energy for unmanned plane, unmanned plane in landing or in-flight will be faced with no power resources, and damage of falling The danger of bad unmanned plane；Or only setting accumulator provides electric energy for voltage-stablizer, when the failures such as electric energy deficiency, nothing occurs in accumulator When method provides electric energy for unmanned plane, unmanned plane in landing or in-flight will be faced with no power resources, and fall Damage the danger of unmanned plane.So providing electric energy by engine and generator for voltage-stablizer and accumulator provides for voltage-stablizer Electric energy, and this accumulator can mutually switch with generator and provide electric energy for voltage-stablizer, and unmanned plane can be overcome to fly In due to generator break down or accumulator break down, electric energy can not be provided for unmanned plane, make unmanned plane that will be faced with There is no power resources, and the technological deficiency for the damage unmanned plane that falls, reach the safety for improving unmanned plane, in-flight power Stability technique effect.

Meanwhile the burning voltage that voltage-stablizer is exported will enter current divider, each shunting delivery outlet of current divider can incite somebody to action Electric energy is assigned to displacement component 420, driving part 430 and regulating member 440, and current divider may be video camera, fly automatically Control system distributes electric energy, and the mode of the distribution electric energy can connect or use wireless power transmission by conducting wire, these It may also apply to the utility model.First delivery outlet of power supply part 410 can connect with the first input port of the first steering engine 421 It connects, the second delivery outlet of power supply part 410 can be connected with the second input port of the second steering engine 422, then pass through power supply part 410 provide electric energy for the first steering engine 421 and the second steering engine 422.First electricity adjust 441 the 5th input port can and power supply part 410 third delivery outlet connection, the first electricity adjust 441 the 5th delivery outlet that can be connected with the third input port of first motor 431； Second electricity adjusts 442 the 6th input port that can be connected with the 4th delivery outlet of power supply part 410, and the 6th of the second electricity tune 442 is defeated Outlet can be connected with the 4th input port of the second motor 432.So that adjusting 441 to control first motor 431 by the first electricity Rotating speed, the second electricity adjust 442 to control the rotating speed of the second motor 432.To pass through the flight from ground remote control device into unmanned plane Control system sends control instruction, and by flight control system come control the first steering engine 421 of unmanned plane, the second steering engine 422, The working condition of first motor 431 and the second motor 432, and then reach and the state of unmanned plane landing, flight is controlled Technique effect.

It is noted that flight control system is mainly by controlling the first steering engine 421, to drive first to vert component 253 movement, with control the first propeller 252 0 ° -90 ° and/or 0 °-(- 90 °) in the range of rotated；Pass through control Make the second steering engine 422, come drive second vert component 263 move, with control the second propeller 262 at 0 ° -90 ° and/or 0 °-(- 90 °) in the range of rotated；Also, by the rotating speed for controlling first motor 431, to control the first propeller 252 rotating speed；By controlling the rotating speed of third motor 433, to control the rotating speed of the second propeller 262.So that being controlled by flight The model at the angle of inclination (i.e. the first propeller 252 0 ° -90 ° and/or 0 °-(- 90 °)) of the first propeller of system pair 252 It encloses and interior carries out rotation and rotating speed, and the regulation and control at angle of inclination and rotating speed to the second propeller 262.Reach and is controlled by flying System controls the motion state of unmanned plane landing, flight, and controls the technology effect of the movement speed of unmanned plane landing, flight Fruit.

The utility model provides a kind of fuselage for fixed-wing unmanned plane, by by the first of the second front end and head Rear end is detachably connected so that, can be with local replacing component when fuselage local damage occur can not repair.Second ontology and Two front ends are fixedly connected, and so that the diameter of section of the second ontology is sequentially reduced on the direction towards the second rear end, to reduce Suffered gas-flow resistance in unmanned plane during flying.And the first wing is set in the first side of the second ontology, in the first wing The first adjustable rotary wing mechanism of upper setting.Second wing is set in the second side of the second ontology, is arranged on the second wing Second adjustable rotary wing mechanism, direction and power of different sizes can be generated respectively on the first wing and the second wing, after And it is landing and required power of flying that unmanned plane provides.To reach the structure of simplified unmanned plane, make the landing of unmanned plane Journey more easily technique effect.

It should be noted last that the above specific implementation mode is only to illustrate the technical solution of the utility model rather than limit System, although the utility model is described in detail with reference to example, it will be understood by those of ordinary skill in the art that, it can be right The technical solution of the utility model is modified or replaced equivalently, without departing from the spirit and model of technical solutions of the utility model It encloses, should all cover in the right of the utility model.

Claims (5)

1. a kind of fuselage for fixed-wing unmanned plane, which is characterized in that the fuselage for fixed-wing unmanned plane includes：

Second front end, second front end and the first rear end are detachably connected；

Second ontology, second ontology are fixedly connected with second front end；Second ontology include first side and Second side is provided with the first wing in the first side, the second wing, and described first is provided in the second side Wing and second wing are symmetrically distributed in the both sides of second ontology along the center vertical pivot of second ontology；It is described It is provided with the first adjustable rotary wing mechanism on first wing, the second adjustable rotary wing mechanism is provided on second wing；

Second rear end, second rear end are fixedly connected with second ontology, and the diameter of section of second ontology It is sequentially reduced on the direction towards second rear end；

Wherein, second ontology is arranged between second front end and second rear end, and second front end Portion, second ontology and second rear end, which are integrally formed, constitutes the fuselage.

2. being used for the fuselage of fixed-wing unmanned plane as described in claim 1, which is characterized in that described to be used for fixed-wing unmanned plane Fuselage include：

First wing include the first preceding fastening end, the first forward open end and the first positioning area, the first preceding fastening end and The first side is fixedly connected, and first positioning area is arranged in the described first preceding fastening end and first forward open end Between；

Wherein, first forward open end and the first preceding fastening end are the both ends of first wing.

3. being used for the fuselage of fixed-wing unmanned plane as claimed in claim 2, which is characterized in that described to be used for fixed-wing unmanned plane Fuselage include：

The angle of first end flank, the first end flank and first wing is 60 ° -90 °；And the first end Flank includes the first wing tip fastening end and the first wing tip open end；And first wing tip fastening end and first forward open end It is fixedly connected, first wing tip open end deviates from first forward open end, described in the composition of first wing tip fastening end The both ends of first end flank.

4. being used for the fuselage of fixed-wing unmanned plane as claimed in claim 3, which is characterized in that described to be used for fixed-wing unmanned plane Fuselage include：

Second wing include the second preceding fastening end, the second forward open end and the second positioning area, the second preceding fastening end and The second side is fixedly connected, and second positioning area is arranged in the described second preceding fastening end and second forward open end Between；

Wherein, second forward open end and the second preceding fastening end are the both ends of second wing.

5. being used for the fuselage of fixed-wing unmanned plane as claimed in claim 4, which is characterized in that described to be used for fixed-wing unmanned plane Fuselage include：

The angle of the second end flank, the second end flank and second wing is 60 ° -90 °；And the second end Flank includes the second wing tip fastening end and the second wing tip open end；And second wing tip fastening end and second forward open end It is fixedly connected, second wing tip open end deviates from second forward open end, described in the composition of second wing tip fastening end The both ends of the second end flank；

Wherein, first wing tip open end and second wing tip open end are symmetrically divided along the center vertical pivot of the fuselage Cloth.