CN208470105U - Adjustable rotor tail apparatus for fixed-wing unmanned plane - Google Patents

Adjustable rotor tail apparatus for fixed-wing unmanned plane Download PDF

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Publication number
CN208470105U
CN208470105U CN201820136964.2U CN201820136964U CN208470105U CN 208470105 U CN208470105 U CN 208470105U CN 201820136964 U CN201820136964 U CN 201820136964U CN 208470105 U CN208470105 U CN 208470105U
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CN
China
Prior art keywords
unmanned plane
wing
fixedly connected
pedestal
limiting slot
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CN201820136964.2U
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Chinese (zh)
Inventor
赵国成
李子轩
陈蒙
罗伟
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Ewatt Technology Co Ltd
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Ewatt Technology Co Ltd
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Priority to CN201820136964.2U priority Critical patent/CN208470105U/en
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Abstract

The utility model discloses a kind of adjustable rotor tail apparatus for fixed-wing unmanned plane, belong to air vehicle technique field, including tail, the first and second adjustable rotary wing mechanisms, first adjustable rotary wing mechanism includes the first propeller, first motor, first verts component and the first steering engine, first motor is provided with the first drive shaft and first base, first vert component include the first pedestal and the first limiting slot, the first steering engine include first rotating shaft and first fastening seat;Second adjustable rotary wing mechanism includes the second propeller, third motor, second verts component and the second steering engine, third motor is provided with third drive shaft and third pedestal, second vert component include the second pedestal and the second limiting slot, the second steering engine include the second shaft and second fastening seat.Tail includes third front end, third ontology and third rear end.The utility model has reached reduction maintenance cost;Unmanned plane has the technical effect low, adaptable to site requirements in landing and flight.

Description

Adjustable rotor tail apparatus for fixed-wing unmanned plane
Technical field
The utility model belongs to air vehicle technique field, the in particular to adjustable rotor tail of a kind of fixed-wing unmanned plane Device.
Background technique
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 the equipment such as radar, it is tracked, is positioned, is remotely controlled, telemetering and Digital Transmission.It can take off as common unmanned plane under wireless remotecontrol or be launched with booster rocket, it can also 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 only unmanned plane being carried out to scrap processing if fuselage local damage occur and can not repair.And unmanned plane be usually by by It crosses the operator of professional training and takes off in the case where cooperating parasite power, the lift of flight is by wing and to be located at The propeller of head provides, and unmanned plane is caused to cause unmanned plane to site requirements height, bad adaptability.
In conclusion in the prior art, if tail a part appearance damage of unmanned plane can not repair, needing to change Entire unmanned plane, increases maintenance cost;Unmanned plane is in landing and flight, to site requirements height, bad adaptability.
Utility model content
If, which there is damage, in tail a part that technical problem to be solved in the utility model is unmanned plane to repair When, entire unmanned plane is needed to change, maintenance cost is increased;Unmanned plane is in landing and flight, to site requirements height, adaptability Difference.
In order to solve the above technical problems, the utility model provides a kind of adjustable gyroplane for fixed-wing unmanned plane Tail apparatus, the adjustable rotor tail apparatus for fixed-wing unmanned plane includes: the first adjustable rotary wing mechanism, and described One adjustable rotary wing mechanism includes: the first propeller;First motor, the first motor are provided with the first drive shaft and the first bottom Seat, first drive shaft are fixedly connected with first propeller;First verts component, and described first component that verts includes the One pedestal and the first limiting slot, first pedestal are fixedly connected with the first base, first limiting slot and the first machine The wing is fixedly connected, and first limiting slot and first pedestal are hinged, and the first pedestal setting is in first limit Between position slot and the first base;First steering engine, first steering engine include first rotating shaft and first fastening seat, described first Shaft is connected with first pedestal, and the first fastening seat is fixedly connected with first limiting slot, and the first rotating shaft It is arranged between first pedestal and first limiting slot;Second adjustable rotary wing mechanism, the second adjustable rotor Mechanism includes: the second propeller;Third motor, the third motor are provided with third drive shaft and third pedestal, the third Drive shaft is fixedly connected with second propeller;Second verts component, and described second component that verts includes the second pedestal and the Two limiting slots, second pedestal are fixedly connected with the third pedestal, and second limiting slot and the second wing are fixedly connected, And second limiting slot and second pedestal are hinged, second pedestal setting is in second limiting slot and described the Between three pedestals;Second steering engine, second steering engine include the second shaft and the second fastening seat, second shaft and described the The connection of two pedestals, the second fastening seat are fixedly connected with second limiting slot, and second shaft setting is described the Between two pedestals and second limiting slot.Tail, the tail include: third front end, the third front end and described Second rear end is detachably connected;Third ontology, the third ontology are fixedly connected with the third front end;And the third Empennage is provided on ontology;Third rear end, the third rear end are fixedly connected with the third ontology;Wherein, described Three ontologies are arranged between the third front end and the third rear end, and the third front end, the third ontology It is integrally formed with the third rear end and constitutes the tail.
Further, the adjustable rotor tail apparatus for fixed-wing unmanned plane includes: first drive shaft It is perpendicular with the rotational plane of first propeller.
Further, the adjustable rotor tail apparatus for fixed-wing unmanned plane includes: the third drive shaft It is perpendicular with the rotational plane of second propeller.
Further, it includes: the first linking arm that first limiting slot and the first wing, which are fixedly connected, first connection Arm includes first end, second end and the first interlude, and first interlude and the first positioning area are detachably connected, and described first End is fixedly connected with first limiting slot;Wherein, the first end and the second end are the both ends of first linking arm.
Further, the adjustable rotor tail apparatus for fixed-wing unmanned plane includes: the first rotor;Second electricity Machine, second motor are provided with the second drive shaft and second base, and the second base is fixedly connected with the second end, institute The second drive shaft is stated to be fixedly connected with first rotor.
Further, the rotational plane of second drive shaft and first rotor is perpendicular.
Further, it includes: the second linking arm that second limiting slot and the second wing, which are fixedly connected, second connection Arm includes third end, the 4th end and the second interlude, and second interlude and the second positioning area are detachably connected, the third End is fixedly connected with the second limiting slot;Wherein, the third end and the 4th end are the both ends of second linking arm.
Further, the adjustable rotor tail apparatus for fixed-wing unmanned plane includes: the second rotor;4th electricity Machine, the 4th motor are provided with the 4th drive shaft and the 4th pedestal, and the 4th pedestal is fixedly connected with the 4th end, institute The 4th drive shaft is stated to be fixedly connected with second rotor.
Further, the rotational plane of the 4th drive shaft and second rotor is perpendicular.
Further, it includes: the first aerofoil plate that empennage is provided on the third ontology, the first aerofoil plate and described Third ontology is fixedly connected;Second aerofoil plate, the second aerofoil plate are fixedly connected with the third ontology, and first wing Panel and the second aerofoil plate are symmetrically distributed in the two sides of the third ontology;Wherein, the first aerofoil plate and described Two aerofoil plates constitute v-shaped structure, and the angular range of the v-shaped structure is 70 ° -90 °.
The utility model has the advantages that
The utility model provides a kind of adjustable rotor tail apparatus for fixed-wing unmanned plane, by the first wing The first adjustable rotary wing mechanism of upper setting, is arranged the second adjustable rotary wing mechanism on the second wing;The is driven by the first steering engine One adjustable rotary wing mechanism is deflected relative to the first wing, and the second steering engine drives the second adjustable rotary wing mechanism relative to the Two wings are deflected, and then adjust the side of power produced by the first adjustable rotary wing mechanism and the second adjustable rotary wing mechanism respectively To;The rotation of first adjustable rotary wing mechanism is driven by first motor, the second motor drives the rotation of the second adjustable rotary wing mechanism, makes First adjustable rotary wing mechanism and the second adjustable rotary wing mechanism generate lift or thrust;Then change the first adjustable rotary respectively Power caused by wing mechanism and the second adjustable rotary wing mechanism, the power come the VTOL provided for unmanned plane and needed for flying. Meanwhile being detachably connected the third front end of the second rear end of fuselage and tail, so that fuselage local damage occur can not When reparation, it can be replaced in time with local replacing component, when facilitating tail to damage.If to reach the tail of unmanned plane When a part appearance damage can not repair, tail can be replaced, maintenance cost is reduced;In unmanned plane in landing and flight, With technical effect low to site requirements, adaptable.
Detailed description of the invention
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 of fixed-wing unmanned plane provided by the embodiment of the utility model;
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 bottom 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 structural block diagram of the dynamical system of fixed-wing unmanned plane for the utility model embodiment;
Wherein, 100-head, the 110-the first front end, 120-the first noumenons, the 130-the first rear end, 140-is empty Speed pipe;
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 embodiment
The utility model provides a kind of adjustable rotor tail apparatus for fixed-wing unmanned plane, by the first wing The first adjustable rotary wing mechanism of upper setting, is arranged the second adjustable rotary wing mechanism on the second wing;The is driven by the first steering engine One adjustable rotary wing mechanism is deflected relative to the first wing, and the second steering engine drives the second adjustable rotary wing mechanism relative to the Two wings are deflected, and then adjust the side of power produced by the first adjustable rotary wing mechanism and the second adjustable rotary wing mechanism respectively To;The rotation of first adjustable rotary wing mechanism is driven by first motor, the second motor drives the rotation of the second adjustable rotary wing mechanism, makes First adjustable rotary wing mechanism and the second adjustable rotary wing mechanism generate lift or thrust;Then change the first adjustable rotary respectively Power caused by wing mechanism and the second adjustable rotary wing mechanism, the power come the VTOL provided for unmanned plane and needed for flying. Meanwhile being detachably connected the third front end of the second rear end of fuselage and tail, so that fuselage local damage occur can not When reparation, it can be replaced in time with local replacing component, when facilitating tail to damage.If to reach the tail of unmanned plane When a part appearance damage can not repair, tail can be replaced, maintenance cost is reduced;In unmanned plane in landing and flight, With technical effect low to site requirements, adaptable.
In order to be done in detail to a kind of adjustable rotor tail apparatus for fixed-wing unmanned plane provided by the utility model Illustrate, to support utility model technical problem to be solved, in the following, in embodiment provided by the utility model, first to solid Determine wing unmanned plane to elaborate, then during describing fixed-wing unmanned plane, further targetedly draws this reality Reach complete, clear, clear mesh with a kind of adjustable rotor tail apparatus for fixed-wing unmanned plane of novel offer 's.
Whole feelings before introducing the utility model embodiment, 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 between three sections by the connection type of detachable connection, 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 technical 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 whole design, so that there is 200 part damage of fuselage 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 Technical 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 on first wing 230 is set, and second be arranged on the second wing 240 is 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, pushing first to vert portion by the first steering engine 421 in the first adjustable rotary wing mechanism 250 of control Part 253 is located at the first propeller 252 in the plane with unmanned plane level, passes through first motor 431 and drives the first propeller 252 work, make 252 unmanned plane of the first propeller provide lift;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 sky and takes off, and then enters stabilized flight.In decline, 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 pulling fuselage 200 is stablized from eminence and is declined, 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 is suitble to unmanned plane different The technical effect of flying field progress 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, those of ordinary skill in the art's every other embodiment obtained, all belongs to In the range of the utility model protection;Wherein "and/or" keyword involved in this implementation, indicate and or two kinds of situations, change Sentence is talked about, and 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, such as A and/or B, indicate: only including A does not include B;Only including B does not include A;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 be 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, which can be, is 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" and "right" and similar statement be merely for purposes of illustration, not It is intended to limit the utility model.
It is practical new to this first in order to which fixed-wing unmanned plane provided by the embodiment of the utility model is described in detail Technical term involved in type embodiment does description below explanation:
Detachable connection, which may is that, to be bolted or is bonded;
It is fixedly connected and may is that welding or integrated molding;
Ground may is that the ground that unmanned plane is parked, or the face with this plane parallel;
Minimum flying speed, which may is that, makes unmanned plane keep flight, and minimum flying speed when not falling.Such as: In the present embodiment, the minimum flying speed of unmanned plane can be 20m/s;
Takeoff phase may is that unmanned plane reaches the process of aerial vertical ascent from ground;
Take off flatten the winged stage may is that unmanned plane reach it is aerial after, carry out the process of horizontal flight;
Landing phases may is that process of the unmanned plane from airborne to ground.
Referring to Figure 1, Fig. 1 is a kind of overall structure signal of fixed-wing unmanned plane provided by the embodiment of the utility model Figure.A kind of fixed-wing unmanned plane provided by the embodiment of the utility model.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, can be fixedly connected with pitot 140 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 the overall structure for referring to Fig. 1, Fig. 1 being a kind of fixed-wing unmanned plane provided by the embodiment of the utility model 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.Unmanned plane Head 100 can be rendered as hollow structure, i.e., can be accommodated in the inside of head 100 and place the skies of the electric elements of camera Between.Pitot 140 can be set on the first front end 110.Pitot 140 is also Pitot tube, stagnation pressure tube etc., pitot 140 be experience the stagnation pressure (also referred to as total pressure) and static pressure of air-flow, and by the pressure data measured send to air data computer, The device of flying instruments.Pitot 140 is primarily used to measurement flying speed, while can also have both other multiple functions.
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 The cruise duration of unmanned plane can be improved to reduce the loss of unmanned plane itself kinetic energy in man-machine obstruction.
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 two 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 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 Hollow structure, i.e. the second ontology 220 of fuselage 200 can be it is hollow, the hollow structure can be used for accommodating photography, camera shooting 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 improves the cruise duration of unmanned plane to reduce the loss of unmanned plane itself kinetic energy 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 Two sides.Assuming that plane locating for the first wing 230 and the second wing 240 is A plane, (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) locating for plane B it is flat Face, then it is farther from the ground to can be A plane ratio B plane for the distance relative to ground.The spacing of A plane and B plane 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 plane and B plane Support member can be set, which connects A plane and B plane, so that A plane and B plane 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 plane and B plane, and support column is mutually perpendicular to the first wing 230 and the second wing 240 respectively, It operates the first adjustable rotary wing mechanism 250 on the first wing 230 in the space far from B plane, also makes the second wing The second adjustable rotary wing mechanism 260 on 240 operates in the space far from B plane, 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 plane 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 causes so that the first propeller 252 and the second propeller 262 collide the second ontology 220 Safety accident occurs, unmanned plane is forced to stop working 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 bottom view schematic diagram of fixed-wing unmanned plane.? Can be fixedly 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, when so that the first linking arm 251 losing, 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 and significantly reduces the technical effect of 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, thus for turn of the first adjustable rotary wing mechanism 250 and the first rotor 254 It is dynamic that bigger space is provided, promote the safety during unmanned plane during flying or landing.
The second linking arm 261, the second linking arm 261 can be fixedly installed in the second positioning area of the second wing 240 The second interlude can also be detachably connected with the second positioning area, when so that the second linking arm 261 losing, 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 replacements.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 and significantly reduces the technical effect of 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, thus for the second adjustable rotary wing mechanism 260 and the second rotation The rotation of the wing 264 provides bigger space, promotes the safety during unmanned plane during flying or landing.
Referring to Figure 1, Fig. 1 is a kind of overall structure signal of fixed-wing unmanned plane provided by the embodiment of the utility model 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 is also possible to multiple-blade (more than two blades).Two blades can be with first First drive shaft of motor 431 is fixedly connected, and two blades can symmetrically be distributed in the two 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, is provided with through-hole on the protruding end (abbreviation K1);It is fixed with another protruding end on a face being away from each other on the first pedestal with first motor 431, 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 allowed 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 is 0 ° -90 ° and/or 0 °-(- 90 °), wherein 90 ° refer to and are directed away from ground, are located above unmanned plane, and and Angle when ground is perpendicular;- 90 ° refer to and are directed away from ground, be located at below unmanned plane, and with ground when perpendicular Angle;0 ° of angle referred to ground when parallel.To realize that controlling the first propeller 252 by the first steering engine 421 exists 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 the revolving speed of the first propeller 252 to realize by the first electricity tune 441.
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 greater 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, bigger thrust or lift 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 is also possible to multiple-blade (more than two blades).Two blades can and third The third drive shaft of motor 433 is fixedly connected, and two blades can symmetrically be distributed in the two 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, is provided with through-hole on the protruding end (abbreviation K3);It is fixed with another protruding end on a face being away from each other on the second pedestal with third motor 433, 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 allowed 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 is 0 ° -90 ° and/or 0 °-(- 90 °), wherein 90 ° refer to and are directed away from ground, are located above unmanned plane, and and Angle when ground is perpendicular;- 90 ° refer to and are directed away from ground, be located at below unmanned plane, and with ground when perpendicular Angle;0 ° of angle referred to ground when parallel.To realize that controlling the second propeller 262 by the second steering engine 422 exists 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 the revolving speed of the second propeller 262 to realize by the second electricity tune 442.
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 greater 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 be 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 be 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 the above-mentioned first end that first adjustable rotary wing mechanism 250 is mounted on to the first linking arm 251 on structure it is similar Seemingly;The structure that second adjustable rotary wing mechanism 260 is mounted on the 4th end of the second linking arm 261 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 the revolving speed of first motor 431 is promoted by the first electricity tune 441, so that the first propeller 252 revolving speed increases.Meanwhile by flight control system, the second steering engine 422 is controlled, the second propeller 262 is pushed 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 the revolving speed that third motor 433 is promoted by the second electricity tune 442, so that triple propeller revolving 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 revolving speed of propeller 252 and the second propeller 262 increase, can then increase the lift of unmanned plane, finally make nothing After the man-machine enough lift of 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 revolving speed of first motor 431, the revolving speed of first motor 431 is then lifted out, so that the first propeller The ascending increase of 252 revolving speed.Meanwhile by flight control system, the second steering engine 422 is controlled, the second propeller 262 is pushed 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 rotate, and first reduce the revolving speed of third motor 433 by the second electricity tune 442, are then lifted out turning for third motor 433 Speed, so that the ascending increase of triple propeller revolving speed.Since the first propeller 252 and the second propeller 262 are moved to 0 ° of position can provide the thrust for being parallel to ground then for unmanned plane;And the first propeller 252 and the second propeller 262 Revolving speed increase after, can then increase the thrust of unmanned plane, finally make unmanned plane obtain minimum flying speed, in the sky 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 revolving speed of motor 431, so that the revolving speed of the first propeller 252 is gradually reduced.Meanwhile by flight control system, the second steering engine is controlled 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 revolving speed of motor 433, so that triple propeller revolving 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 revolving speed of paddle 262 is gradually reduced, it can be then gradually reduced the thrust of unmanned plane, finally make unmanned plane from the air gradually 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 The lower section that forward open end, i.e. the second wing tip open end are located at 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, " induced drag " caused by can reducing because of the first wing tip trailing vortex and the second wing tip trailing vortex reduce to reach The destruction to lift is streamed, lift resistance ratio is improved, increases voyage, has the function that the technical 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 material needed for manufacturing 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 The technical effect of power loss (such as: oil consumption).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.
U-shaped rise can be fixedly installed 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 Degree range can be 90 ° -120 °.When unmanned plane landing, 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 undercarriage is 90 ° or 120 °, U-shaped undercarriage confrontation The ability of ground shock power is also strong, to improve the stability of U-shaped undercarriage 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 and be mutually detachably connected;Before third ontology 320 and third End 310, which can be, to be mutually permanently connected;Third rear end 330 and third ontology 320 can be and be mutually permanently connected.Wherein, Third ontology 320 can be set 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 set 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 two 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, 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 is rendered as cylinder can be in unmanned plane In flight course, air-flow is effectively reduced to the resistance of unmanned plane, increases the cruise duration of unmanned plane, improve 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 band it is big on 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 is also possible to tailplane or hangs down Straight tail, if tail 300 is tailplane, tailplane be may be mounted on the third ontology 320 of tail 300;If tail 300 be vertical tail, then vertical tail also may be mounted on the third ontology 320 of tail 300.
If tail 300 is rudder-vator, which be 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 °, Be in the flat winged stage in unmanned plane, can effectively stable unmanned plane course;When Β=90 °, make different directions in unmanned plane When deflection, the effect of rudder can be provided for unmanned plane.
(side can mutually hang down with third ontology 320 on side of the first aerofoil plate 340 towards third rear end 330 It can directly) be equipped with aileron (abbreviation W1), W1 aileron can be hinged with the first aerofoil plate 340, i.e. W1 aileron 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) it can also be equipped with aileron (abbreviation W2), W2 aileron 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.When unmanned plane needs to turn to, it can pass through control W1's and W2 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 sky Row.
For dynamical system 400:
Dynamical system 400 may include power supply part 410, displacement component 420, driving part 430 and regulating member 440.
The first delivery outlet, the second delivery outlet, third delivery outlet and the 4th delivery outlet has can be set in power supply part 410.Position Moving component 420 may include the first steering engine 421 and the second steering engine 422, 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 input with the third of first motor 431 Mouth connection.Second electricity adjusts 442 the 6th input port and the 6th delivery outlet can be set, and the second electricity adjusts 442 the 6th input port can To connect 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 The connection of four input ports.
Fig. 6 is referred to, Fig. 6 is a kind of knot for the dynamical system 400 that the utility model embodiment provides 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, battery.
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 electric energy for the mechanical energy that engine generates;Voltage-stablizer can keep the electricity as caused by generator Stable voltage can be exported after voltage-stablizer, voltage-stablizer can be connected with battery.Battery is connect with voltage-stablizer Effect can be battery can provide electric energy for voltage-stablizer, and voltage-stablizer keeps the electric energy generated by battery defeated after voltage-stablizer Stable voltage out;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, provides electric energy by battery for unmanned plane;It can be nothing if engine or power generation function work normally Man-machine offer electric energy, then battery stops providing electric energy for unmanned plane;It certainly, can not be nothing if electric power deficiency occurs in battery Man-machine offer electric energy can be mentioned by the normal work of engine perhaps generator by engine or generator for battery For electric energy, to supplement the electric energy of battery.
Electric energy is provided for voltage-stablizer if engine and generator is only arranged, it, can not when engine or generator failure 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 battery is set and provides electric energy for voltage-stablizer, when the failures such as electric energy deficiency, nothing occurs in battery 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 battery provides for voltage-stablizer Electric energy, and this battery 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 battery break down, electric energy can not be provided for unmanned plane, be faced with unmanned plane will There is no power resources, and fall and damage the technological deficiency of unmanned plane, reaches the safety for improving unmanned plane, in-flight power Stability technical 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, which can be, connects by conducting wire or use wireless power transmission, 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 connect with the third input port of first motor 431; Second electricity adjusts 442 the 6th input port that can connect 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 Revolving speed, the second electricity adjust 442 to control the revolving 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 controlled by flight control system 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 Technical effect.
It is noted that flight control system mainly passes through the first steering engine 421 of control, 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 revolving speed of control first motor 431, to control the first propeller 252 revolving speed;By controlling the revolving speed of third motor 433, to control the revolving speed of the second propeller 262.So that being controlled by flight Model of the system to the tilt angle of the first propeller 252 (i.e. the first propeller 252 0 ° -90 ° and/or 0 °-(- 90 °)) Enclose it is interior carry out rotation and revolving speed, and to the tilt angle of the second propeller 262 and the regulation of revolving speed.Reach and is controlled by flight 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 adjustable rotor tail apparatus for fixed-wing unmanned plane, by the first wing The first adjustable rotary wing mechanism of upper setting, is arranged the second adjustable rotary wing mechanism on the second wing;The is driven by the first steering engine One adjustable rotary wing mechanism is deflected relative to the first wing, and the second steering engine drives the second adjustable rotary wing mechanism relative to the Two wings are deflected, and then adjust the side of power produced by the first adjustable rotary wing mechanism and the second adjustable rotary wing mechanism respectively To;The rotation of first adjustable rotary wing mechanism is driven by first motor, the second motor drives the rotation of the second adjustable rotary wing mechanism, makes First adjustable rotary wing mechanism and the second adjustable rotary wing mechanism generate lift or thrust;Then change the first adjustable rotary respectively Power caused by wing mechanism and the second adjustable rotary wing mechanism, the power come the VTOL provided for unmanned plane and needed for flying. Meanwhile being detachably connected the third front end of the second rear end of fuselage and tail, so that fuselage local damage occur can not When reparation, it can be replaced in time with local replacing component, when facilitating tail to damage.If to reach the tail of unmanned plane When a part appearance damage can not repair, tail can be replaced, maintenance cost is reduced;In unmanned plane in landing and flight, With technical effect low to site requirements, adaptable.
It should be noted last that the above specific embodiment is only to illustrate the technical solution of the utility model rather than limits System, although the utility model is described in detail referring to example, those skilled in the art should understand 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 scope of the claims of the utility model.

Claims (10)

1. a kind of adjustable rotor tail apparatus for fixed-wing unmanned plane, which is characterized in that it is described for fixed-wing nobody The adjustable rotor tail apparatus of machine includes:
First adjustable rotary wing mechanism, the first adjustable rotary wing mechanism include:
First propeller;
First motor, the first motor are provided with the first drive shaft and first base, first drive shaft and described first Propeller is fixedly connected;
First verts component, and described first component that verts includes the first pedestal and the first limiting slot, first pedestal and described First base is fixedly connected, and first limiting slot and the first wing are fixedly connected, and first limiting slot and described first Pedestal is hinged, and first pedestal is arranged between first limiting slot and the first base;
First steering engine, first steering engine include that first rotating shaft and first fasten seat, the first rotating shaft and first pedestal Connection, the first fastening seat is fixedly connected with first limiting slot, and the first rotating shaft is arranged in first pedestal Between first limiting slot;
Second adjustable rotary wing mechanism, the second adjustable rotary wing mechanism include:
Second propeller;
Third motor, the third motor are provided with third drive shaft and third pedestal, the third drive shaft and described second Propeller is fixedly connected;
Second verts component, and described second component that verts includes the second pedestal and the second limiting slot, second pedestal and described Third pedestal is fixedly connected, and second limiting slot and the second wing are fixedly connected, and second limiting slot and described second Pedestal is hinged, and second pedestal is arranged between second limiting slot and the third pedestal;
Second steering engine, second steering engine include that the second shaft and second fasten seat, second shaft and second pedestal Connection, the second fastening seat is fixedly connected with second limiting slot, and second shaft is arranged in second pedestal Between second limiting slot;
Tail, the tail include:
Third front end, the third front end and the second rear end are detachably connected;
Third ontology, the third ontology are fixedly connected with the third front end;And empennage is provided on the third ontology;
Third rear end, the third rear end are fixedly connected with the third ontology;
Wherein, the third ontology is arranged between the third front end and the third rear end, and the third front end Portion, the third ontology and the third rear end, which are integrally formed, constitutes the tail.
2. being used for the adjustable rotor tail apparatus of fixed-wing unmanned plane as described in claim 1, which is characterized in that the use Include: in the adjustable rotor tail apparatus of fixed-wing unmanned plane
The rotational plane of first drive shaft and first propeller is perpendicular.
3. being used for the adjustable rotor tail apparatus of fixed-wing unmanned plane as claimed in claim 2, which is characterized in that the use Include: in the adjustable rotor tail apparatus of fixed-wing unmanned plane
The rotational plane of the third drive shaft and second propeller is perpendicular.
4. being used for the adjustable rotor tail apparatus of fixed-wing unmanned plane as claimed in claim 3, which is characterized in that described the One limiting slot and the first wing are fixedly connected and include:
First linking arm, first linking arm include first end, second end and the first interlude, first interlude and One positioning area is detachably connected, and the first end is fixedly connected with first limiting slot;
Wherein, the first end and the second end are the both ends of first linking arm.
5. being used for the adjustable rotor tail apparatus of fixed-wing unmanned plane as claimed in claim 4, which is characterized in that the use Include: in the adjustable rotor tail apparatus of fixed-wing unmanned plane
First rotor;
Second motor, second motor are provided with the second drive shaft and second base, the second base and the second end It is fixedly connected, second drive shaft is fixedly connected with first rotor.
6. being used for the adjustable rotor tail apparatus of fixed-wing unmanned plane as claimed in claim 5, it is characterised in that:
The rotational plane of second drive shaft and first rotor is perpendicular.
7. being used for the adjustable rotor tail apparatus of fixed-wing unmanned plane as claimed in claim 6, which is characterized in that described the Two limiting slots and the second wing are fixedly connected and include:
Second linking arm, second linking arm include third end, the 4th end and the second interlude, second interlude and Two positioning areas are detachably connected, and the third end is fixedly connected with the second limiting slot;
Wherein, the third end and the 4th end are the both ends of second linking arm.
8. being used for the adjustable rotor tail apparatus of fixed-wing unmanned plane as claimed in claim 7, which is characterized in that the use Include: in the adjustable rotor tail apparatus of fixed-wing unmanned plane
Second rotor;
4th motor, the 4th motor are provided with the 4th drive shaft and the 4th pedestal, the 4th pedestal and the 4th end It is fixedly connected, the 4th drive shaft is fixedly connected with second rotor.
9. being used for the adjustable rotor tail apparatus of fixed-wing unmanned plane as claimed in claim 8, it is characterised in that:
The rotational plane of 4th drive shaft and second rotor is perpendicular.
10. being used for the adjustable rotor tail apparatus of fixed-wing unmanned plane as claimed in claim 9, which is characterized in that described Being provided with empennage on third ontology includes:
First aerofoil plate, the first aerofoil plate are fixedly connected with the third ontology;
Second aerofoil plate, the second aerofoil plate are fixedly connected with the third ontology, and the first aerofoil plate and described Two aerofoil plates are symmetrically distributed in the two sides of the third ontology;
Wherein, the first aerofoil plate and the second aerofoil plate constitute v-shaped structure, and the angular range of the v-shaped structure is 70°-90°。
CN201820136964.2U 2018-01-26 2018-01-26 Adjustable rotor tail apparatus for fixed-wing unmanned plane Active CN208470105U (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201820136964.2U CN208470105U (en) 2018-01-26 2018-01-26 Adjustable rotor tail apparatus for fixed-wing unmanned plane

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201820136964.2U CN208470105U (en) 2018-01-26 2018-01-26 Adjustable rotor tail apparatus for fixed-wing unmanned plane

Publications (1)

Publication Number Publication Date
CN208470105U true CN208470105U (en) 2019-02-05

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
CN201820136964.2U Active CN208470105U (en) 2018-01-26 2018-01-26 Adjustable rotor tail apparatus for fixed-wing unmanned plane

Country Status (1)

Country Link
CN (1) CN208470105U (en)

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