CN109733596A - Unmanned plane - Google Patents

Abstract

This disclosure relates to a kind of unmanned plane, comprising: fuselage；Rotor assembly, the quantity of the rotor assembly are multiple, and can laterally, be longitudinally mounted on verting on the fuselage；And first mounting base, it is fixedly mounted on the fuselage, for installing gun post.In this way, gun post is mounted on the fuselage of unmanned plane by the first mounting base, when gun post needs adjustment direction, vert direction and then the adjustment unmanned aerial vehicle body posture of adjustable part or all of rotor assembly, finally make gun post that fuselage be followed to keep identical posture, realize the firing direction of gun post and the adjustment of firing point, and that realizes unmanned plane removes holder.

Description

Unmanned plane

Technical field

This disclosure relates to unmanned plane carry accessory technical field, and in particular, to a kind of unmanned plane.

Background technique

With the fast development of unmanned air vehicle technique, requirement of the user to unmanned plane is also higher and higher.To meet unmanned plane Carry device would generally be arranged in multi-functional demand, unmanned plane on fuselage during fabrication, to be used for the corresponding functional component of carry. Such as carry on unmanned aerial vehicle body shooting, sighting device in the task of execution when need adjustment direction to carry out rapidly and accurately Run-home usually installs holder on the fuselage of unmanned plane in the related technology, realizes shooting dress by adjusting the angle of holder The direction adjustment set.But for the unmanned plane of certain types, setting holder will increase the overall weight of unmanned plane, thus shadow The service performance for ringing unmanned plane, causes unmanned plane volume to be multiplied, and Portability is had a greatly reduced quality, while cruising ability is deteriorated.

Summary of the invention

The purpose of the embodiment of the present disclosure is to provide a kind of unmanned plane, which can realize gun post firing direction The load-carrying of unmanned plane is reduced while adjustment, that realizes unmanned plane removes holder.

To achieve the goals above, the embodiment of the present disclosure provides a kind of unmanned plane, comprising: fuselage；Rotor assembly, the rotation The quantity of wing assembly is multiple, and can be mounted on laterally and/or longitudinally verting on the fuselage；And first mounting base, It is fixedly mounted on the fuselage, for installing gun post.

Optionally, the unmanned plane further includes the foot prop being rotatably connected on the fuselage, and the foot prop is used for Expansion is packed up with supporting the unmanned plane in the unmanned plane during flying when unmanned plane lands.

Optionally, it has been rotatably coupled first motor seat on the fuselage, has been fixed with first in the first motor seat The rotating output shaft of motor, the first motor is formed with external screw thread；The foot prop has first cooperated with the external screw thread Interconnecting piece；The rotating output shaft drives the first connecting portion close to or away from the first motor, to drive the foot prop It is unfolded or packs up.

Optionally, the foot frame structure is the frame with cavity, and the first motor seat is contained in the cavity.

Optionally, the unmanned plane further includes extending transversely through in the fuselage and the support arm that can longitudinally rotate, the rotation Wing assembly is fixed on the both ends of the support arm.

Optionally, the rotor assembly includes blade and the second motor for driving the blade rotation；The end of the support arm Portion is fixed with the steering engine that verts, and the output end of the steering engine that verts is connected with the second motor cabinet for installing second motor； The rotation of the second motor cabinet described in servo driving of verting is so that the rotor assembly laterally verts.

Optionally, the unmanned plane further includes the driving device for controlling the gun post shooting, the driving dress It sets and is connect with the flight control system of the unmanned plane.

Optionally, the gun post is gun, and first mounting base is configured to accommodate the gun stock of the gun.

Optionally, the gun have trigger and the guard ring around the trigger；It is equipped in first mounting base For driving the driving assembly of the trigger, the driving component include can side insertion into the guard ring withhold bar with And driving described in withhold bar close to or away from the trigger third motor.

Optionally, offered in first mounting base supply described in withhold bar sliding sliding slot, the third motor it is defeated Outlet is rotatably connected to link assembly, to be constituted crank block slider structure with the bar of withholding.

Optionally, the gun post is rocket gun, and first mounting base is configured to connect the rocket gun The mounting bracket of gun barrel.

According to the second aspect of the disclosure, a kind of unmanned plane is provided, comprising: fuselage；Rotor assembly, the rotor assembly Quantity be multiple, and can laterally, longitudinal be mounted on verting on the fuselage；And gun post, it is fixedly mounted on On the fuselage.

Through the above technical solutions, gun post is mounted on the fuselage of unmanned plane by the first mounting base, when shooting fills It sets when needing adjustment direction, verting for adjustable part or all of rotor assembly and then adjusts unmanned aerial vehicle body posture at direction, Finally make gun post that fuselage be followed to keep identical posture, realizes the firing direction of gun post and the tune of firing point It is whole, and that realizes unmanned plane removes holder.

Other feature and advantage of the embodiment of the present disclosure will the following detailed description will be given in the detailed implementation section.

Detailed description of the invention

Attached drawing is to further understand for providing to the embodiment of the present disclosure, and constitute part of specification, under The specific embodiment in face is used to explain the disclosure together, but does not constitute the limitation to the embodiment of the present disclosure.In the accompanying drawings:

Fig. 1 is the structural schematic diagram for the unmanned plane that a kind of illustrative embodiments of the disclosure provide；

Fig. 2 is the bottom view of unmanned plane shown in fig. 1；

Fig. 3 is the mounting structure schematic diagram of foot prop in unmanned plane shown in fig. 1；

Fig. 4 is the scheme of installation of another angle of foot prop；

Fig. 5 is the structural schematic diagram of foot prop mounting base；

Fig. 6 is the structural schematic diagram of rotor assembly in unmanned plane shown in fig. 1；

Fig. 7 is the mounting structure schematic diagram of gun post in unmanned plane shown in fig. 1；

Fig. 8 is the mounting structure schematic diagram of another angle of gun post in unmanned plane shown in fig. 1；

Fig. 9 is the structural schematic diagram for the unmanned plane that disclosure another kind illustrative embodiments provide；

Figure 10 is the bottom view of the unmanned plane shown in Fig. 9；

Figure 11 is the structural schematic diagram for the rocket gun that a kind of illustrative embodiments of the disclosure provide；

Figure 12 is another angular views of the rocket gun shown in Figure 11；

Figure 13 is the cross-sectional view of the rocket gun shown in Figure 11；

Figure 14 is the front view of the rocket gun shown in Figure 11；

Figure 15 is the rearview of the rocket gun shown in Figure 11；

Figure 16 is the structural schematic diagram that steering engine is limited in Figure 13；

Figure 17 is the structural schematic diagram for the unmanned plane that disclosure another kind illustrative embodiments provide；

Figure 18 is the partial schematic diagram of part A in Figure 17；

Figure 19 is image pick-up device and the connection frame for installing image pick-up device in unmanned plane shown in Figure 17 Schematic diagram；

Figure 20 is the structural schematic diagram for the unmanned plane that disclosure another kind illustrative embodiments provide.

Description of symbols

100- fuselage；101- body；102- radome fairing；103- slideway；104- sliding rail；105- elastic component；The first electricity of 110- Base；120- rotating output shaft；130- foot prop mounting base；The first ear mount of 131-；The second ear mount of 132-；133- first rotating shaft； The second shaft of 134-；200- rotor assembly；210- blade；The second motor of 220-；The second motor cabinet of 230-；The installation of 240- steering engine Seat；250- third shaft；The first mounting base of 300-；301- vertical plate；302- transverse slat；303- fastener；311- withholds bar；312- Three motors；313- link assembly；320- sliding slot；400- gun post；411- trigger；412- guard ring；421- gun barrel；422- bullet Body；423- tail-hood；424- guide pad；425- cabling channel；500- foot prop；510- first connecting portion；600- support arm；710- image picks up Take device；711- camera；712- connection frame；713- ring flange；720- laser-targeting device；The first locating part of 810-；811- Limit steering engine；812- bar；The second locating part of 820-.

Specific embodiment

It is described in detail below in conjunction with specific embodiment of the attached drawing to the embodiment of the present disclosure.It should be understood that this Locate described specific embodiment and be only used for describing and explaining the embodiment of the present disclosure, is not limited to the embodiment of the present disclosure.

In the disclosure, in the absence of explanation to the contrary, the noun of locality used such as "upper", "lower", "top", "bottom" are Refer to upper and lower when unmanned plane equals winged state；"inner", "outside" refer to the inner and outer of corresponding component profile；" longitudinal direction " refers to nobody The front-rear direction of machine flight；" transverse direction " refers to the left and right directions of unmanned plane during flying, i.e., perpendicular to the side of " longitudinal direction " in horizontal plane To.In addition, term " first " used in the embodiment of the present disclosure, " second " etc. are to distinguish an element with another and want Element does not have succession and importance.In the following description when referring to the accompanying drawings, unless otherwise indicated, the identical number in different attached drawings Word indicates the same or similar element.

Referring to Fig.1 and Fig. 9, the embodiment of the present disclosure provide a kind of unmanned plane, including fuselage 100, rotor assembly 200 and first Mounting base 300.The quantity of rotor assembly 200 can be multiple, and can be mounted on fuselage 100 with laterally and/or longitudinally verting On, to realize the adjustment of unmanned plane during flying posture by adjusting laterally or longitudinally verting for rotor assembly 200.Wherein, rotor is total Propeller blade is referred at 200 and for installing blade and driving the components of blade adjustment posture, the components are for example It may include the second following motors, second motor cabinet etc.；First mounting base 300 is fixedly mounted on fuselage 100, for installing Gun post 400, for example, the first mounting base 300 can be fixedly mounted on the bottom of fuselage 100,400 carry of gun post is in machine The lower section of body 100；Gun post 400 can arbitrarily be capable of the device of weapon delivery for gun, rocket gun or crossbow bolt etc., It can be the device that can emit infrared light etc..

In this way, gun post 400 is mounted on the fuselage 100 of unmanned plane by the first mounting base 300, work as gun post 400 when needing adjustment direction, and verting for adjustable part or all of rotor assembly 200 and then adjusts flying for fuselage 100 at direction Row posture finally makes gun post 400 that fuselage 100 be followed to keep identical posture, realizes the firing direction of gun post 400 And the adjustment of firing point, and that realizes unmanned plane removes holder.

In some embodiments, rotor assembly 200 can longitudinally vert, and be verted by this, unmanned plane can be made preceding Into or retreat when fuselage 100 do not vert, attitude stabilization can be improved the stability of gun post 400；In other implementations In example, rotor assembly 200 can laterally vert, and be verted by this, and unmanned plane fuselage 100 in roll motion can be made not send out Life is verted, and attitude stabilization can be improved the stability of gun post 400；In further embodiments, rotor assembly 200 can Enough longitudinal vert also can laterally vert, so that unmanned plane fuselage 100 in omnidirectional moving does not vert, attitude stabilization, Can be improved the stability of gun post 400, and the pose adjustment of unmanned plane is flexible, can be advanced, be retreated, pitching, The movement such as roll.In narration below the embodiment of the present disclosure, only it is illustrated by taking a kind of finally embodiment as an example, other two kinds of feelings Condition is similar therewith, will not repeat them here.It does and shows by taking some application environments of quadrotor drone as an example below in conjunction with Fig. 1 and Fig. 6 Example property explanation.

It is understood in advance that in order to improve fire accuracy, gun post 400 be can have for run-home object Aiming elements, the object information around the available unmanned plane of aiming elements in predetermined induction zone, it is ensured that investigating and shooting Target is not lost in the process.In the embodiment of the present disclosure, which can be the photographic device being mounted on fuselage 100, It can be the sighting device etc. that gun post 400 has in itself, be not specifically limited here.Certainly, in the requirement of some fire accuracies In not high embodiment, aiming elements can also be not provided with.

When target object is located at the front of gun post 400, gun post 400 can be directly shot at.In mesh In the case where marking range of the object beyond gun post 400, four rotor assemblies 200 tilt forward simultaneously, each rotor assembly 200 blade 210 can either generate component straight up so that unmanned plane is maintained at predetermined altitude, can also generate forward Driving force, so that unmanned plane is advanced forward.In this course, the fuselage 100 of unmanned plane can not vert, i.e., protect always It holds in horizontality, it is ensured that flight stability.When target object enters in the range of gun post 400, gun post 400 can To be shot at.In addition, unmanned plane is during flight forward, since fuselage 100 remains horizontal, i.e. gun post 400 It does not vert, gun post 400 can be continued towards target object and be shot at.

When target object is located at the diagonally above and frontward of gun post 400, in a kind of embodiment, raising blade can be synchronized 210 revolving speed improves lift, until gun post 400 is shot at when target object is located at the front of gun post 400, I.e. above-mentioned shooting course.In another embodiment, the revolving speed of two blades 210 in front side can be only improved, so that fuselage 100 Front end raise up, gun post 400 can be shot at towards diagonally above and frontward at this time.

When target object is located at the left front of gun post 400, in a kind of embodiment, four rotor assemblies 200 can To vert to the left simultaneously, the blade 210 of each rotor assembly 200 can either generate component straight up so that unmanned plane is kept In predetermined altitude, driving force to the left can be also generated, so that unmanned plane is advanced to the left, until target object is located at gun post 400 front, gun post 400 are shot at.In this course, the fuselage 100 of unmanned plane can not vert, i.e., Remain at horizontality, it is ensured that flight stability.In addition, during unmanned plane is in flight to the left, since fuselage 100 is kept Level, i.e. gun post 400 are not verted, and gun post 400 can be continued towards target object and be shot at.It is another real It applies in mode, two rotor assemblies 200 of front side can only be made to vert to the left, by adjusting the revolving speed of blade 210, it is ensured that four The power of the vertical direction of a blade 210 is identical, simultaneously as two blades 210 of front side generate driving force to the left, so that machine The front end of body 100 moves to left, and gun post 400 can be shot at towards left front at this time.

Gun post 400 is similar with above-mentioned several situations to the shooting of the target object of other positions, and the disclosure does not do one One illustrates.It is further to note that above-mentioned " front " is only the theoretical case of shooting, here for convenience, no Consider the air drag that is subject to of shooting matter that gun post 400 issues and parabolic path under the effect of gravity.

In the embodiment of the present disclosure, verting for fuselage 100 itself can meet the direction tune at any angle of gun post 400 It is whole, optimize unmanned aerial vehicle platform mechanism so as to reduce the load-carrying of unmanned plane without additional setting holder, effectively extend nobody The cruising ability of machine.In addition, the first mounting base 300 in the embodiment of the present disclosure is in addition to can unremovably be mounted on fuselage Except on 100, can also removably it be connected with each other with fuselage 100, in order to the dismounting and replacement of gun post 400, Improve the versatility of unmanned plane.First mounting base 300 can according to gun post 400 specific structure and have adaptation setting Structure type, the embodiment of the present disclosure do not limit this.

The disclosure without limitation, such as can have camera function to the concrete forms of above-mentioned aiming elements for common Device, or the inductor of ultrasonic wave, infrared ray or other forms.According to some embodiments, referring to Figure 17 and Figure 18, Aiming elements may include image pick-up device 510, and image pick-up device 510 includes one or more camera lenses, and the disclosure is implemented In example, image pick-up device 510 can be forward sight binocular assembly, and the flight control system connection of forward sight binocular assembly and unmanned plane will Acquired image is transferred to flight control system, or is further transferred to the observation screen or control flow of earth station, so that work people Member can monitor target object in real time.Here, forward sight binocular assembly refers to the image pickup using binocular vision imaging principle Device utilizes two images of the imaging device from different position acquisition testees, by between calculating image corresponding points Position deviation has measurement efficiency height, advantage with high accuracy to obtain object dimensional geological information.

Specifically, forward sight binocular assembly includes two cameras for being mounted on front fuselage.Referring to Fig.1 7 to Figure 19, according to Some embodiments, fuselage 100 may include body 101 and the radome fairing 102 that is located on body 101, before the radome fairing 102 End is configured to streamlined to reduce windage.Two above-mentioned cameras 711 are mounted on the front end of body 101, and radome fairing 102 Front end offers the via hole corresponding to camera 711, so as to 711 captured image of camera.In order to avoid the influence of radome fairing 102 is taken the photograph As first 711 vision area, the front end of camera 711 can be forwardly convex in radome fairing 102.

Further, two cameras 711 can be symmetrical with the longitudinal centre line setting of fuselage 100, in this way, two camera shootings First 711 job area is symmetrical, and image pickup precision can be improved.The quantity of above-mentioned via hole can be two, open up respectively In the position corresponding to camera 711 of radome fairing 102；In another embodiment, via hole may be that a transverse direction is prolonged The strip hole stretched, two cameras 711 pick up the image in front by the strip hole.

Referring to Fig.1 9, according to some embodiments, the front end of fuselage 100 can be equipped with connection frame 712, the connection frame 712 Such as it may be mounted at the front end of above-mentioned body 101.The front end face of connection frame 712 is straight, and the rear end of camera 711 is formed with The ring flange 713 being mountable on connection frame 712, i.e. camera 711 are connected to by ring flange 713 and connection frame 712 On fuselage 100.Ring flange 713 is fitted and connected with connection frame 712, the two face contact, to improve the stability of camera 711.

Further, referring to Fig.1 7 to Figure 19, aiming elements can also include laser-targeting device 520, further to mention High pointing accuracy, to carry out precision strike to target object.

Similarly with image pick-up device 710, laser-targeting device 720 is also connect with the flight control system of unmanned plane, so that Unmanned plane can be accurately positioned target object.According to some embodiments, laser-targeting device 720 can be installed in rotation on machine On body 100 or the first mounting base 300.In this way, being filled first by laser aiming in the immovable situation of posture of fuselage 100 It sets 720 itself rotations to be accurately positioned target object, if target object deviates the current range of gun post 400, fly Control system can control fuselage 100 and do pose adjustment；If target object is in the current range of gun post 400, in fuselage 100 Posture do not adjust in the case where, shooting can be completed in gun post 400.

Laser-targeting device 720 can be installed to fuselage 100 or the first by structures such as any suitable shaft or bulbs In mounting base 300, for example, three axis hangers can be set on fuselage 100, laser-targeting device 720 is fixed on three axis hangers. It is rotated by the multiple degrees of freedom of three axis hangers, laser-targeting device 720 can be made to emit laser towards multiple orientation, improve it Job area.

In some cases, such as when gun post 400 is gun, gun post 400 can generate certain in excitation Recoil, which will affect the stability of unmanned plane, in order to solve this problem, can set on gun post 400 Set buffer unit.For example, damper element can be set between gun post 400 and fuselage 100, or can also be in the first peace Damper element is set between dress seat 300 and fuselage 100, the embodiment of the present disclosure is not construed as limiting this.Referring to Figure 20, according to some realities Example is applied, the slideway 103 that front and back extends can be set on fuselage 100, slideway 103 is equipped with sliding rail 104, sliding rail with being slidably matched 104 rear end is connected on fuselage 100 by elastic component 105.First mounting base 300 is mounted on sliding rail 104, and the two uses Rigidly connected form, so that switching performance is reliable, it is ensured that fire accuracy.In this way, after gun post 400 is excited shooting, Recoil brought by shooting is transmitted in elasticity 105 by the first mounting base 300, sliding rail 104, and elastic component 105 is by this recoil Power is transferred on fuselage 100 after absorbing, to make the recoil be buffered, while elastic component 105 can play reduction vibration again Dynamic effect guarantees the stability of fuselage 100.This structure can be to avoid gun post 400 after excitation to the control of unmanned plane It has an impact, guarantees the quality and security reliability of unmanned plane, meet use need of the unmanned plane in carry gun post 400 It asks.

In the embodiment of the present disclosure, slideway 103 and sliding rail 104 can be using the forms being arbitrarily slidably matched, as long as the two Cross-sectional shape match.For example, as shown in figure 20, slideway 103 can be with structure according to an embodiment of the present disclosure It makes as open column shape, sliding rail 104 is contained in slideway 103.The slideway 103 of open column shape can limit sliding rail 104 except front and back The displacement on direction other than direction, to ensure that direction of the gun post 400 in shooting, so that recoil preferably passes It is handed on elastic component 105 and is absorbed, to play optimal buffering shock attenuation result.In other embodiments, slideway 103 is gone back It is so structured that any other can circumferentially surround the shape of sliding rail 104, sliding rail 104 is limited with the circumferential direction in sliding rail 104 Position is moved forward and backward sliding rail 104 along slideway 103 always, it is ensured that the stability that sliding rail 104 is run, and then preferably control nothing It is man-machine.

Further, as shown in figure 20, slideway 103 may include two points of slideways of time interval, and sliding rail 104 runs through two A to divide slideway, the first mounting base 300 may be mounted at the middle position between two points of slideways, and such first mounting base 300 can To guarantee the stability after gun post 400 is installed simultaneously by two points of slideways to the support force at 104 both ends of sliding rail.At it In his embodiment, slideway 103 or a coherent slideway, the first mounting base 300 be may be mounted at positioned at slideway 103 Rear end sliding rail 104 on.

According to some embodiments, sliding rail 104 can be hinged with elastic component 105, and elastic component 105 can be hinged with fuselage 100. In this way, using hinged structure, so that when no matter gun post 400 is with the shooting of which kind of angle, such as when gun post 400 is being penetrated It is influenced when hitting by air drag etc., when shooting angle generates offset, hinged elastic component 105 can adaptively deviate corresponding Angle, to play the role of absorbing buffering to the recoil of shooting.

According to some embodiments, elastic component 105 can be compressed spring.Compressed spring and sliding rail 104 and fuselage 100 connect It connects, not only can provide sliding rail 104 certain rigid support after the shooting of gun post 400, but also shooting bring can be absorbed Recoil plays the role of buffering absorbing, the stability of unmanned plane complete machine is improved, so that unmanned plane is more easily controlled.Compress bullet Spring can be as above-mentioned hinged with sliding rail 104 and fuselage 100, more fully to absorb 400 bring recoil of gun post.? In some embodiments, elastic component 105 or air spring etc. are hinged between sliding rail 104 and fuselage 100.

In some embodiments, the carry for the ease of the gun post 400 on unmanned plane and use, slideway 103 The bottom of fuselage 100 can be separately positioned on sliding rail 104, the first mounting base 300 is mounted on the lower section of sliding rail 104, the first peace Dress seat 300 can be fixedly mounted on sliding rail 104, can also be connected with each other in a manner of removably with sliding rail 104, in order to tear open Dress and replacement, improve the versatility of unmanned plane.

For the ease of the replacement and repair of each components, slideway 103 and elastic component 105 can be detachably connected to respectively On fuselage 100, in this way, the unmanned plane can be used when being not connected to slideway 103 and elastic component 105 as common unmanned plane, Slideway 103 and elastic component 105 can also be connected in case of need, and the first mounting base 300 and gun post 400 are being installed It is used afterwards as Tactical Unmanned Air Vehicle.In other embodiments, slideway 103 and elastic component 105 can also be fixedly connected on fuselage It on 100, is such as welded on fuselage 100, to guarantee that each part of entire unmanned plane is more firmly mounted.

Referring to Fig. 2 and Figure 10, the unmanned plane that the embodiment of the present disclosure provides can also include being rotatably connected to fuselage 100 On foot prop 500, so as to when unmanned plane lands expansion to support unmanned plane, packed up in unmanned plane during flying.I.e. nobody In landing, foot prop 500 is turned to landing stage contact position to support unmanned plane machine, 500 turns of foot prop in unmanned plane during flying It moves to the position close with fuselage 100, generates collision with barrier to avoid during unmanned plane during flying.Foot prop 500 can It the bottom of fuselage 100 is arranged in, and can be symmetricly set on 100 longitudinal centre line two sides of fuselage multiple, for nothing The steady balanced support force of man-machine offer.

Further, as shown in figure 3, foot prop 500 can by be arranged in the foot prop mounting base 130 of 100 bottom of fuselage with Fuselage 100 is rotatably connected.Specifically, can be distinguished in foot prop mounting base 130 referring to Fig. 3 and Fig. 5 according to some embodiments It is formed with the first ear mount of a pair 131 for installing foot prop 500 and the second ear mount of a pair for installing first motor seat 110 132, two the first ear mounts 131 and two the second ear mounts 132 are oppositely arranged, and one end of foot prop 500 passes through across two first The first rotating shaft 133 of ear mount 131 is installed in rotation on fuselage 100, and one end of first motor seat 110 passes through across two Second shaft 134 of two ear mounts 132 is installed in rotation on fuselage 100, and first rotating shaft 133 and the second shaft 134 are mutually equal Row setting.First motor (not shown), the formation of rotating output shaft 120 of first motor are fixed in first motor seat 110 There is external screw thread, foot prop 500 has the first connecting portion 510 cooperated with external screw thread, and rotating output shaft 120 drives when first motor works Dynamic first connecting portion 510 is close to or away from first motor, to drive foot prop 500 to be unfolded or pack up.

Further, referring to Fig. 4, for foot prop 500 it is so structured that the frame with cavity, first connecting portion 510 can be with It is configured to rod piece, and is fixedly mounted between the opposite side wall of frame.First motor seat 110 accommodates in the cavities, the first electricity The rotating output shaft 120 of machine is stretched out from the siding of first motor seat 110, and extends radially through first connecting portion 510, and first connects The part of socket part 510 penetrated through is formed with internal screw thread, to cooperate with the external screw thread of rotating output shaft 120.With foot prop 500 For when expansion, first motor starting, rotating output shaft 120 passes through first connecting portion 510 around own axis, foot prop 500 Threaded function power rotated around first rotating shaft 133 far from fuselage 100, first connecting portion 510 drives rotating output shaft 120 to make the One motor cabinet 110 is rotated around the second shaft 134 far from fuselage 100 simultaneously, and in rotation process, first connecting portion 510 and rotation are defeated Shaft 120 is threadedly engaged, first connecting portion 510 along rotating output shaft 120 axial movement and be gradually distance from first motor.Foot prop 500 when packing up, and first motor starting, rotating output shaft 120 rotates backward, so that foot prop 500 is around first rotating shaft 133 and first Motor cabinet 110 is rotated close to fuselage 100 simultaneously around the second shaft 134, and in the process, first connecting portion 510 moves closer to the One motor.

The disclosure is not specifically limited the mode of verting of rotor assembly 200, below only for showing embodiment in attached drawing It illustrates.Specifically, referring to Fig.1 and Fig. 9, unmanned plane can also include extending transversely through in fuselage 100 and capable of indulging To the support arm 600 of rotation, rotor assembly 200 is fixed on the both ends of support arm 600.I.e. rotor assembly 200 can be pacified by support arm 600 Realize that the longitudinal direction of itself is verted on fuselage 100, and through longitudinally rotating for support arm 600.Wherein, the rotation of support arm 600 can To be controlled by being located at any form of driving mechanism inside fuselage 100, such as can be arranged in the outside of support arm 600 Gear, the gear and support arm 600 are cooperated by keyway, can be rotated by driving motor sliding tooth wheel to control support arm 600 Rotation.

Further, referring to Fig. 6, rotor assembly 200 may include the second electricity that blade 210 and driving blade 210 rotate Machine 220；The end of support arm 600 is fixed with steering engine (not shown) of verting, and the output end for the steering engine that verts is connected with for installing Second motor cabinet 230 of the second motor 220；The second motor cabinet of servo driving 230 that verts rotates so that rotor assembly 200 laterally inclines Turn.Wherein, the steering engine that verts can be fixedly connected by steering engine mounting base 240 with support arm 600.Steering engine mounting base 240 may include There are sleeve sections and construction section, sleeve sections are socketed on the periphery wall of 600 end of support arm, and construction section is for accommodating the steering engine that verts.The Two motor cabinets 230 include top plate and the side plate positioned at top plate both ends, and the second motor 220 is mounted on above top plate, and construction section is located at Between two side plates, the mounting hole passed through for third shaft 250 is offered on side plate, the output end and third shaft of the steering engine that verts 250 axial connections realize the transverse direction of rotor assembly 200 to drive the second motor cabinet 230 to rotate synchronously by third shaft 250 It verts.

In addition, in the embodiments of the present disclosure, unmanned plane can also include the driving dress for controlling the shooting of gun post 400 It sets, driving device can be connect with the flight control system of unmanned plane.In this way, the staff in earth station can pass through remote controler etc. Remote control equipment to the flight control system of unmanned plane send signal, flight control system promote driving device control gun post 400 into Row shooting.Or in another embodiment, it after above-mentioned aiming elements lock onto target object, transmits signals to and flies control system System, flight control system can directly initiate driving device, improve the reaction speed of system.

According to one embodiment, referring to Figures 1 and 2, gun post 400 can be gun, and the first mounting base 300 can be with Relative configurations are the gun stock that can accommodate gun.Gun can be set in the bottom of fuselage 100, and gun stock may include and fuselage The connected second connecting portion in 100 bottoms and the support portion for carrying gun.

Further, the guard ring 412 that there is trigger 411 and be arranged around trigger 411 referring to Fig. 7, gun；First installation Driving assembly for driving trigger 411 is installed on seat 300, the driving assembly may include can side insertion to guard ring Withholding bar 311 and driving in 412 withholds third motor 312 of the bar 311 close to or away from trigger 411, the third motor 312 The driving device that as above-mentioned control gun post 400 is shot.In this way, worked when shooting by control third motor 312, Bar 311 can to withhold towards the movement of trigger 411, apply certain pressure, and then pulloff 411 to trigger 411, make rifle Bullet is projected from gun.

Further, referring to Fig. 8, the sliding slot 320 for withholding the sliding of bar 311 can be offered in the first mounting base 300, The output end of third motor 312 can be rotatably connected to link assembly 313, with withhold bar 311 and constituted crank block slider structure.Even Bar assembly 313 may include the driving lever being connected with the output end of third motor 312, and connects driving lever and withhold bar 311 Connecting rod, withhold bar 311 and be formed as sliding block in crank block slider structure.In the illustrated embodiment, third motor 312 can The rear of gun is arranged in, bar 311 is withheld from the front side of trigger 411 to extending into guard ring 412, the extension of sliding slot 320 Direction and trigger 411 to withhold direction substantially parallel.When third motor 312 works, output end drives driving lever rotation certain Angle, driving lever is withheld bar 311 by connecting rod drive and 320 is swung along the chute, and then realizes withholding or releasing to trigger 411 It puts.

According to another embodiment, referring to Fig. 9 and Figure 10, gun post 400 can also be rocket gun, the first mounting base 300 can be that can connect the mounting bracket of the gun barrel of rocket gun with relative configurations.In the embodiment shown in Fig. 9 and Figure 10, Mounting bracket can be plate；According to another embodiment, as is illustrated by figs. 11 and 12, mounting bracket can be fixed on gun barrel 421 top, the upper end can be fixed on the bottom of fuselage 100, by rocket gun carry in 100 bottom of fuselage of unmanned plane. Mounting bracket can do adaptability design according to the type of unmanned plane, the embodiment of the present disclosure to its specific structure without limitation, example If 4 and Figure 15, mounting bracket may include the vertical plate 301 for being fixed on 421 top of gun barrel referring to Fig.1, it is vertically connected on vertical plate 301 The transverse slat 302 of top can offer the mounting hole passed through for fastener 303 on transverse slat 302, to be realized by fastener 303 Mounting bracket is detachably connected with fuselage 100.Mounting bracket can also be detachably connected with gun barrel 421, in this way, installation branch Frame (i.e. the first mounting base 300) can be detachably connected with fuselage 100 and gun post 400 respectively, to facilitate components Maintenance and replacement.It wherein, is the bonding strength for increasing mounting bracket 800 and fuselage, mounting hole can be to be arranged at intervals on cross It is multiple on plate 302, while for rocket gun to be firmly secured on fuselage 100, mounting bracket may be along the longitudinal direction It is spaced multiple.Further, sparking motor is additionally provided in gun barrel, which is above-mentioned control shooting dress Set the driving device of 400 shootings.

The rocket gun that the embodiment of the present disclosure provides includes 421 above-mentioned and the body 422 that is contained in gun barrel 421 of gun barrel, Body 422 can be carried and protected by gun barrel 421.

According to some embodiments, rocket gun further includes the first locating part 810 and the second locating part 820, wherein the first limit Part 810 can be contained in gun barrel 421 for 422 front limit of body, the second locating part 820 can also to be contained in gun barrel For to being limited after body 422 in 421.In this way, the first locating part 810 and the second locating part 820 pass through respectively to body 422 Front and back limits and body 422 is locked in gun barrel 421, so as to prevent unmanned plane from playing body 422 in flight course in band Deviate from from gun barrel 421.

Further, 1 and Figure 13, body 422 can have fusiform head referring to Fig.1, which can be towards nothing Man-machine front reduces the gas being subject to during unmanned plane during flying to rely on 422 head of body to rectify before rocket launcher system fire Resistance.3 and Figure 16 referring to Fig.1, according to some embodiments, the first locating part 810 may include the limit being mounted on gun barrel 421 Steering engine 811, and it is connected to the swingable bar 812 of the output shaft of limit steering engine 811.In this way, passing through control limit steering engine 811 direction of rotation and rotation angle can make bar 812 be against the front of body 422 before the transmitting of body 422 with locking Body 422 is rocked to the radial outside of body 422 when body 422 emits to discharge body 422.Wherein, body 422 is sent out Steering engine 811 is limited when penetrating can be performed simultaneously with the igniter of rocket gun, precisely to be hit object.In the disclosure In embodiment, the first locating part 810 can be the multiple body 422 is securely limited in gun barrel of circumferentially spaced setting In 421.Referring for example to Figure 14, the first locating part 810 can be two and setting symmetrical above and below, so as to which body 422 is equal It is locked in gun barrel 421 to weighing apparatus.In addition, as shown in Figure 14 and Figure 16, the output shaft of limit steering engine 811 can be set along the longitudinal direction It sets, one end of bar 812 is set on the output shaft of limit steering engine 811, and the other end is for rotating to the head surface of body 422 To clamp body 422.Wherein, the part that bar 812 is contacted with body 422 can have type identical with 422 surface of body face, To avoid the head to body 422 from causing to scratch while increasing the clamping force with body 422.

According to some embodiments, referring to Fig.1 2, rocket gun can also include tail-hood 423, and tail-hood 423 can be further to bullet It is limited after body 422, and can prevent unmanned plane foreign matter in ground or flight course from entering in gun barrel 421.Tail-hood 423 can be with Split installation gun barrel 421 tail portion and can body 422 emit when be detached from gun barrel 421 so that body 422 emit after The front and back end of gun barrel 421 forms air-flow and leads to field, reduces the resistance that unmanned plane is integrally subject to after body 422 emits, improves unmanned plane Flying quality.Wherein, the gas shock power of its rear end is detached from gun barrel 421 when tail-hood 423 can emit by body 422, can also With by other means be crushed after be detached from gun barrel 421, the embodiment of the present disclosure does not limit this.

According to one embodiment, tail-hood 423 can be by normal temperature cure glue sticking in the tail portion of gun barrel 421, such as can To be fixed on the tail portion of gun barrel 421 by cold setting resin glue sticking.Normal temperature cure glue can solidify at normal temperature to realize Its binding function, and can then melt rapidly after encountering high temperature, in the embodiments of the present disclosure, it can be produced when due to rocket launcher system fire Raw a large amount of heat, which facilitates the thawing of normal temperature cure glue, to realize the separation of tail-hood 423 Yu gun barrel 421.

Further, referring to Fig.1 5, tail-hood 423 can also include the muti-piece mutually spliced, and pass through normal temperature cure glue phase Mutually bonding, it is broken when body 422 emits so as to fast implement tail-hood 423, reduce the disengaging difficulty of tail-hood 423.

According to some embodiments, to reduce the load-carrying of unmanned plane, realizing lightweight demand, tail-hood 423 can be carbon fiber Plate, such as can be made by carbon fiber Sandwich board.

In addition, as shown in figure 13, in the embodiments of the present disclosure, the second locating part 820 can be arranged for fitting in body 422 Tail portion limit plate, limit plate can be arranged close to tail-hood 423, so as to preventing body 422 from moving in gun barrel 421 or It is the collision tail-hood 423 when UAV Attitude instantaneously adjusts.Limit plate can be structured as ring-type, so that the height of 422 tail portion of body Warm air can reach tail-hood 423 by cyclic annular limit plate and then carry out broken to tail-hood 423 or tail-hood 423 be made to fall off.Its In, the internal diameter of cyclic annular limit plate can be less than the outer diameter of body 422, by limit after body 422 in gun barrel 421.

According to the specific embodiment that the disclosure provides, referring to Fig.1 3, the inner wall of gun barrel 421 circumferentially spaced can be arranged Have multiple guide pads 424, guide pad 424 can axially extend and be bonded the inner wall that gun barrel 421 is set and body 422 it Between.Wherein, the front end of guide pad 424 can be arranged close to the front end of gun barrel 421, in body 422 from 421 internal emission of gun barrel Body 422 is oriented in the process, body 422 is avoided to be detached from preset path, realizes the accurate strike to object.Further Ground, guide pad 424 can have the surface with the cooperation of the outer contour shape of body 422, steadily to accommodate body 422.Such as In the illustrated embodiment, body 422 is configured to cylindrical body, and the surface of guide pad 424 contacted with body 422 can be arc Shape.

Further, referring to Fig.1 3, the front end of the inside of gun barrel 421 is also provided with the annular coaxial with gun barrel 421 Cabling channel 425.Wherein, there are gap between gun barrel 421 and body 422, cabling channel 425 is formed in the gap, cabling Slot 425 can be fixedly connected with the front end of guide pad 424, and limit steering engine 811 may be mounted in cabling channel 425.Cabling channel 425 It can pass through for signal wire, control line etc., to realize the connection of rocket gun and system for flight control computer, control is flown by unmanned plane System controls the transmitting of rocket gun and limits the work of steering engine 811.

The embodiment of the present disclosure also provides the unmanned plane of another structure type, including fuselage 100, rotor assembly 200 and penetrates Hit device 400.The quantity of rotor assembly 200 can be multiple, and can be mounted on fuselage 100 with laterally and/or longitudinally verting On, to realize the adjustment of unmanned plane during flying posture by adjusting laterally or longitudinally verting for rotor assembly 200.Gun post 400 It is fixedly mounted on fuselage 100, gun post 400 can arbitrarily emit for above-mentioned gun, rocket gun or crossbow bolt etc. The device of weapon is also possible to that the device of infrared light etc. can be emitted.In the case where gun post 400 is weapon, Ke Yishi Existing expeditionary warfare reduces casualties, and the weapon can cooperate other detectings on above-mentioned aiming elements or unmanned plane The carry equipment (such as infrared sensor etc.) of class realizes the function of " look into and beat one " of unmanned plane.Nothing provided in this embodiment Man-machine to have similar beneficial effect with the above-mentioned unmanned plane with the first mounting base 300, which is not described herein again, and this reality Applying the structures such as foot prop 500, the rotor assembly 200 of the unmanned plane in example can also be with the above-mentioned nothing with the first mounting base 300 It is man-machine similar, it also repeats no more here.

The preferred embodiment of the embodiment of the present disclosure is described in detail in conjunction with attached drawing above, still, the embodiment of the present disclosure is simultaneously The detail being not limited in above embodiment can be to disclosure reality in the range of the technology design of the embodiment of the present disclosure The technical solution for applying example carries out a variety of simple variants, these simple variants belong to the protection scope of the embodiment of the present disclosure.

It is further to note that specific technical features described in the above specific embodiments, in not lance In the case where shield, it can be combined in any appropriate way, in order to avoid unnecessary repetition, the embodiment of the present disclosure pair No further explanation will be given for various combinations of possible ways.

In addition, any combination can also be carried out between a variety of different embodiments of the embodiment of the present disclosure, as long as it is not The thought of the embodiment of the present disclosure is violated, equally should be considered as embodiment of the present disclosure disclosure of that.

Claims (12)

1. a kind of unmanned plane characterized by comprising

Fuselage (100)；

Rotor assembly (200), the quantity of the rotor assembly (200) is multiple, and can be installed with laterally and/or longitudinally verting On the fuselage (100)；And

First mounting base (300) is fixedly mounted on the fuselage (100), for installing gun post (400).

2. unmanned plane according to claim 1, which is characterized in that the unmanned plane further include be rotatably connected to it is described Foot prop (500) on fuselage (100), the foot prop (500) be used for the unmanned plane landing when be unfolded with support it is described nobody Machine is packed up in the unmanned plane during flying.

3. unmanned plane according to claim 2, which is characterized in that be rotatably coupled first on the fuselage (100) Motor cabinet (110) is fixed with first motor, the rotating output shaft (120) of the first motor in the first motor seat (110) It is formed with external screw thread；The foot prop (500) has the first connecting portion (510) cooperated with the external screw thread；The rotation output Axis (120) drives the first connecting portion (510) close to or away from the first motor, to drive the foot prop (500) to be unfolded Or it packs up.

4. unmanned plane according to claim 3, which is characterized in that the foot prop (500) is configured with the frame of cavity, The first motor seat (110) is contained in the cavity.

5. unmanned plane according to claim 1, which is characterized in that the unmanned plane further includes extending transversely through in the fuselage (100) and the support arm (600) that can longitudinally rotate, the rotor assembly (200) are fixed on the both ends of the support arm (600).

6. unmanned plane according to claim 5, which is characterized in that the rotor assembly (200) includes blade (210) and drives Move the second motor (220) of the blade (210) rotation；The end of the support arm (600) is fixed with the steering engine that verts, described to vert The output end of steering engine is connected with the second motor cabinet (230) for installing second motor (220)；The servo driving that verts Second motor cabinet (230) rotates so that the rotor assembly (200) laterally verts.

7. unmanned plane according to claim 1, which is characterized in that the unmanned plane further includes for controlling the shooting dress The driving device of (400) shooting is set, the driving device is connect with the flight control system of the unmanned plane.

8. unmanned plane described in any one of -7 according to claim 1, which is characterized in that the gun post (400) is gun, First mounting base (300) is configured to accommodate the gun stock of the gun.

9. unmanned plane according to claim 8, which is characterized in that the gun have trigger (411) and around described The guard ring (412) of trigger (411)；Driving group for driving the trigger (411) is installed on first mounting base (300) Part, the driving component include can side insertion to the guard ring (412) in withholding bar (311) and drive described in withhold Third motor (312) of the bar (311) close to or away from the trigger (411).

10. unmanned plane according to claim 9, which is characterized in that offered described in confession on first mounting base (300) The sliding slot (320) of bar (311) sliding is withheld, the output end of the third motor (312) is rotatably connected to link assembly (313), To be constituted crank block slider structure with the bar (311) of withholding.

11. unmanned plane described in any one of -7 according to claim 1, which is characterized in that the gun post (400) is rocket Cylinder, first mounting base (300) are configured to connect the mounting bracket of the rocket launcher.

12. a kind of unmanned plane characterized by comprising

Fuselage (100)；

Rotor assembly (200), the quantity of the rotor assembly (200) is multiple, and can be installed with laterally and/or longitudinally verting On the fuselage (100)；And

Gun post (400) is fixedly mounted on the fuselage (100).