CN108945461A

CN108945461A - Power load carrier for unmanned plane

Info

Publication number: CN108945461A
Application number: CN201810595826.5A
Authority: CN
Inventors: 不公告发明人
Original assignee: Ewatt Technology Co Ltd
Current assignee: Ewatt Technology Co Ltd
Priority date: 2018-06-11
Filing date: 2018-06-11
Publication date: 2018-12-07

Abstract

The invention discloses a kind of power load carriers for unmanned plane, belong to air vehicle technique field, including load-supporting part and power mechanism.Load-supporting part includes the first support arm and the second support arm, and the first support arm is provided with first end and second end, the first mounting hole and the first spacing zone are provided in second end；Second support arm is provided with third end and the 4th end, is provided with the second mounting hole and the second spacing zone on the 4th end.Power mechanism includes the first steering engine and the second steering engine.First steering engine includes first shell and first rotating shaft, and first shell is fixedly connected with the first spacing zone, and first rotating shaft is fixedly connected with first interface；Second steering engine includes second shell and the second shaft, and second shell is connected with the second spacing zone, and the second shaft is fixedly connected with second interface.The present invention reaches to be in various flight attitudes in unmanned plane, can be shot at any time to glass door and window, is conducive to help the technical effect of the indicator of trapped personnel escape in high residential building in time.

Description

Power load carrier for unmanned plane

Technical field

The invention belongs to air vehicle technique field, in particular to a kind of power load carrier for unmanned plane.

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 unmanned plane, unmanned aerial vehicle body in the prior art is formed using integrally formed structure fabrication.Nobody If owner is by fuselage, wing and positioned at the propeller of head, and is mounted in the video camera on unmanned plane to constitute.Usually From received professional training operator and with take off in the case where parasite power, the lift of flight be by wing and It is provided positioned at the propeller of head.When high-rise fire occurs, each building is observed by the video camera being mounted on unmanned plane The fire condition of layer, then indicator of trapped personnel is saved by aerial ladder.However the glass door and window of high residential building is difficult to smash, and causes to seek The personnel of rescuing are difficult to enter interior, and indoor indicator of trapped personnel is also difficult to escape from, and escape in time to be unfavorable for indicator of trapped personnel.If Glass is shot at by the emission element of unmanned plane, then due to fixed knot that unmanned plane and emission element are integrally formed Structure, the sighted direction of emission element are limited by unmanned plane during flying posture (such as tilting), can not at any time to glass door and window into Row shooting leads to be difficult to that indicator of trapped personnel is helped to escape in time.

In conclusion unmanned plane can not be in various flight attitudes, at any time to glass door in existing unmanned air vehicle technique Window is shot at, and is unfavorable for helping the indicator of trapped personnel escape in high residential building in time.

Summary of the invention

The technical problem to be solved by the present invention is to unmanned plane can not in various flight attitudes, at any time to glass door and window into Row shooting is unfavorable for helping the indicator of trapped personnel escape in high residential building in time.

In order to solve the above technical problems, the present invention provides a kind of power load carrier for unmanned plane, it is described to be used for The power load carrier of unmanned plane includes load-supporting part, and the load-supporting part includes the first support arm, and first support arm is set It is equipped with first end and second end, the first end is fixedly connected with the first clamping seat, and the first installation is provided in the second end Hole and the first spacing zone；Second support arm, second support arm are provided with third end and the 4th end, the third end and second Clamping seat is fixedly connected；The second mounting hole and the second spacing zone are provided on 4th end；Wherein, the first end and described Second end is the both ends of the first support arm opposition, and the third end and the 4th end are the second support arm opposition Both ends；Power mechanism, the power mechanism include: the first steering engine, and first steering engine includes first shell and first rotating shaft, institute It states first shell to be fixedly connected with first spacing zone, the first rotating shaft is fixedly connected with first interface；Second steering engine, institute Stating the second steering engine includes second shell and the second shaft, and the second shell is connected with second spacing zone, and described second turn Axis is fixedly connected with second interface.

Further, the power load carrier for unmanned plane includes that the first end is mutually hung down with the second interface Directly.

Further, the power load carrier for unmanned plane includes the third end and the second interface phase Vertically.

Further, the power load carrier for unmanned plane include first mounting hole include first through hole and Second through-hole, the first through hole and second through-hole are distributed relative to the central symmetry of the second end；Wherein, the first limit Position bar passes through the first through hole and second through-hole.

Further, the power load carrier for unmanned plane includes that the diameter of the first through hole is greater than described the The diameter of one gag lever post, and the diameter of second through-hole is greater than the diameter of first gag lever post.

Further, the power load carrier for unmanned plane include second mounting hole include third through-hole and Fourth hole, the third through-hole and the fourth hole are distributed relative to the central symmetry at the 4th end；Wherein, the second limit Position bar passes through the third through-hole and the fourth hole.

Further, the power load carrier for unmanned plane includes that the diameter of the third through-hole is greater than described the The diameter of two gag lever posts, and the diameter of the fourth hole is greater than the diameter of second gag lever post.

The utility model has the advantages that

The present invention provides a kind of power load carrier for unmanned plane, by by the first end of the first support arm and first Clamping seat is fixedly connected, and the third end of the second support arm is fixedly connected with the second clamping seat.The first installation of setting on the second end Hole and the first spacing zone, are arranged the second mounting hole and the second spacing zone on the 4th end.By of the first steering engine in power mechanism One shell and the first spacing zone are fixedly connected, and first rotating shaft is fixedly connected with first interface；Second shell and in second steering engine The connection of two spacing zones, the second shaft are fixedly connected with second interface.In actual operation, unmanned plane be moved to specified altitude assignment it Afterwards, can by the operating of first rotating shaft and/or the second steering engine, to drive the rotation of tube body, according to the flight attitude of unmanned plane, The direction of ejecting end meaning is adjusted, makes to be directed toward target area (such as window) wait penetrate direction emitted by object.To reach in nothing It is man-machine to be in various flight attitudes, glass door and window can be shot at any time, be conducive to help in high residential building in time The technical effect of indicator of trapped personnel escape.

Detailed description of the invention

It in order to more clearly explain the embodiment of the invention or the technical proposal in the existing technology, below will be to institute in embodiment Attached drawing to be used is needed to be briefly described, it should be apparent that, the accompanying drawings in the following description is only some implementations of the invention Example, for those of ordinary skill in the art, without creative efforts, can also obtain according to these attached drawings Obtain other attached drawings.

Fig. 1 is a kind of overall structure diagram of the grenade instrumentation for unmanned plane provided in an embodiment of the present invention；

Fig. 2 provides a kind of top view illustration of grenade instrumentation for unmanned plane for the embodiment of the present invention；

Fig. 3 provides a kind of left view schematic diagram of grenade instrumentation for unmanned plane for the embodiment of the present invention；

Fig. 4 provides a kind of right view schematic diagram of grenade instrumentation for unmanned plane for the embodiment of the present invention；

Fig. 5 provides a kind of front view schematic diagram of grenade instrumentation for unmanned plane for the embodiment of the present invention；

Fig. 6 provides a kind of rearview schematic diagram of grenade instrumentation for unmanned plane for the embodiment of the present invention；

Detailed description of the invention:

100-emission elements, 110-ejecting ends, 120-tube bodies, 121-first sides, 122-second sides, 123- Hollow portion, the 124-the first pedestal, the 125-the second pedestal, 126-third pedestals, the 127-the four pedestal, 130-handling ends, 131-enter bullet mouth, 132-control switches, 140-objects to be penetrated, the 150-the first positioning area, the 160-the second positioning area, and 170-the Three positioning areas, 180-baffles, the 181-the first trajectory, the 182-the second trajectory；

200-joint units, the 210-the first interface, 220-ontologies, the 230-the second interface, the 231-the first clamping Seat, the 232-the second clamping seat；

300-load-supporting parts, the 310-the first support arm, 311-first ends, 312-second ends, the 313-the first installation Hole, the 320-the second support arm, 321-third ends, the 322-the four end, the 323-the second mounting hole；

400-damping parts, the 410-the first gag lever post, the 411-the first fastening end, the 412-the second fastening end, 420-the Two gag lever posts, 421-third fastening ends, the 422-the four fastening end, the 430-the first elastic parts, the 440-the second elastic parts；

500-power mechanisms, the 510-the first steering engine, 511-first shells, 512-first rotating shafts, the 520-the second rudder Machine, 521-second shells, the 522-the second shaft, the 530-the first spacing zone, the 540-the second spacing zone.

Specific embodiment

In order to elaborate to a kind of power load carrier for unmanned plane provided by the invention, to support invention institute Technical problems to be solved, in the following, being done in detail to a kind of grenade instrumentation for unmanned plane first in embodiment provided by the invention Describe in detail it is bright, then during describing a kind of grenade instrumentation for unmanned plane, further targetedly draw the present invention A kind of power load carrier for unmanned plane of offer, it is complete, clear, clear to achieve the purpose that.

Following will be combined with the drawings in the embodiments of the present invention, and technical solution in the embodiment of the present invention carries out clear, complete Site preparation description, it is clear that described embodiments are only a part of the embodiments of the present invention, instead of all the embodiments.It is based on Embodiment in the present invention, those of ordinary skill in the art's every other embodiment obtained belong to what the present invention protected Range；Wherein "and/or" keyword involved in this implementation, indicate and or two kinds of situations, in other words, the present invention implement A and/or B mentioned by example, illustrate two kinds of A and B, A or B situations, describe three kinds of states present in A and B, 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 embodiment of the present invention, when component is referred to as " being fixed on " another component, it can be directly at another On component or there may also be components placed in the middle.When a component is considered as " connection " another component, it be can be directly It is connected to another component or may be simultaneously present component placed in the middle.When a component is considered as " being set to " another group Part, it, which can be, is set up directly on another component or may be simultaneously present component placed in the middle.Made in the embodiment of the present invention Term "vertical", "horizontal", "left" and "right" and similar statement are merely for purposes of illustration, and are not intended to The limitation present invention.

It is right first in order to which a kind of grenade instrumentation for unmanned plane provided in an embodiment of the present invention is described in detail Technical term involved in the embodiment of the present invention 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 ground when unmanned plane is parked；

It takes off the process that may is that unmanned plane reaches aerial rising from ground；

Landing may is that process of the unmanned plane from airborne to ground；

Object 140 to be penetrated can be the article for referring to shattered glass, such as glass marbles, metal hoodle, metal nail etc..

Referring to Figure 1, Fig. 1 is that a kind of overall structure of grenade instrumentation for unmanned plane provided in an embodiment of the present invention is shown It is intended to.A kind of grenade instrumentation for unmanned plane provided in an embodiment of the present invention, a kind of grenade instrumentation for unmanned plane include Emission element 100, joint unit 200, load-supporting part 300 and damping part 400.Now to emission element 100, joint unit 200, Load-supporting part 300 and damping part 400 carry out following detailed description respectively:

For emission element 100:

Emission element 100 may include ejecting end 110, tube body 120, handling end 130 and object to be penetrated 140.

Tube body 120 is provided with first side 121, second side 122 and hollow portion 123, can be set in first side 121 There are the first pedestal 124 and the second pedestal 125；Third pedestal 126 and the 4th pedestal 127 can be set in second side 122；Dress Unloading end 130 can be set into bullet mouth 131 and control switch 132, and object 140 to be penetrated is connected with control switch 132, and wait penetrate Object 140 is located in bullet mouth 131.Wherein, tube body 120 can be located at handling end 130 and enter between bullet mouth 131, and hollow portion 123 can To pass through into bullet mouth 131 and ejecting end 110；

Ejecting end 110 can also include the first positioning area 150, the second positioning area 160 and third positioning area 170, and first is fixed Position is fixedly installed with first laser transmitter in area 150, and second laser transmitter is fixedly installed on the second positioning area 160, the Image pick-up device is fixedly installed on three positioning areas 170.Wherein, the first positioning area 150 and the second positioning area 160 can be relative to thirds Positioning area 170 is symmetrical；Hollow portion 123 can be 30 ° -60 ° relative to the angular range of second interface 230.

Go out baffle 180 can be installed entering bullet mouth 131, baffle 180 and entering is hinged at bullet mouth 131.And baffle 180 can be connected with control switch 132, and baffle 180 can be located between bullet mouth 131 and control switch 132.

Hollow portion 123 may include the first trajectory 181 and the second trajectory 182.First trajectory 181 and the second trajectory 182 can To be parallel to each other distribution relative to first side 121.Wherein, the first trajectory 181 can be passed through into bullet mouth 131 and ejecting end 110, And the second trajectory 182 can be passed through into bullet mouth 131 and ejecting end 110.

Referring to Figure 1 and Fig. 2, Fig. 1 be a kind of grenade instrumentation for unmanned plane provided in an embodiment of the present invention entirety Structural schematic diagram, Fig. 2 provide a kind of top view illustration of grenade instrumentation for unmanned plane for the embodiment of the present invention.Tube body 120, which can be metal material, is made, and tube body 120 is rendered as hollow structure, which penetrates object for accommodating hoodle waiting 140.Tube body 120 has first side 121 and second side 122, and it is position that first side 121 and second side 122, which can be distributed, In the face of 120 left and right sides of tube body.The both ends of tube body 120 are that handling and enter bullet mouth 131 at end 130 respectively, and entering at bullet mouth 131 can be with Be provided with baffle 180, baffle 180 and entering is hinged at bullet mouth 131, i.e., baffle 180 can be opened relative to bullet mouth 131 is entered or Person's closure.Baffle 180 is located between bullet mouth 131 and control switch 132, and the inside for entering bullet mouth 131 have accommodate to Penetrate the space of object 140.Object 140 to be penetrated can be connected with control switch 132, excite position by the on-off of control switch 132 In entering the object to be penetrated 140 in bullet mouth 131, make object 140 to be penetrated from enter bullet mouth 131 along hollow portion 123 reach ejecting end 110, from 110 homed on its target region of ejecting end (such as glass edge of high residential building window).

First laser transmitter, the second positioning area 160 can be fixedly installed on first positioning area 150 of ejecting end 110 On can be fixedly installed with second laser transmitter, image pick-up device can be fixedly installed on third positioning area 170.First laser hair Emitter and second laser transmitter are symmetrical relative to image pick-up device.First laser transmitter and second laser transmitter can be Laser aiming utensil, such as beam of laser is emitted by first laser transmitter, the hot spot which generates in target area can To be the aiming point for indicating object 140 to be penetrated and coming to target.It can be improved by first laser transmitter and second laser transmitter Accuracy after penetrating object 140 and projecting.Image pick-up device can be camera, which can feed back in the region passed through to ground On the display of face operator, ground handling operator passes through the video image and first laser transmitter and second laser Aiming point caused by transmitter, precisely to be shot to target area.

Entering baffle 180 can be installed at bullet mouth 131, make baffle 180 and enter to be hinged at bullet mouth 131.And it keeps off Plate 180 can be connected with control switch 132, and baffle 180 can be located between bullet mouth 131 and control switch 132.In pipeline Can there are the first trajectory 181 and the second trajectory 182, the first trajectory 181 and the second trajectory 182 can be relative to first sides 121 Be parallel to each other distribution.Wherein, the first trajectory 181 can be passed through into bullet mouth 131 and ejecting end 110, and the second trajectory 182 can be with It passes through into bullet mouth 131 and ejecting end 110.In actual use, object 140 to be penetrated can be pre-loaded with the first trajectory 181 and second In trajectory 182, object 140 to be penetrated is blocked by baffle 180, such as two hoodles are respectively charged into the first trajectory 181 and the second bullet In road 182, then by the closure of baffle 180 it is separately fixed at two hoodles in the first trajectory 181 and the second trajectory 182.Baffle The control switch 132 of 180 sides can be connected with two hoodles respectively, when control switch 132 is closed, can excite positioned at the Object to be penetrated 140 in one trajectory 181 and the second trajectory 182 makes the first trajectory of hoodle approach 181 being located in the first trajectory 181, It is projected at a high speed from ejecting end 110, makes the second trajectory of hoodle approach 182 being located in the second trajectory 182, it is also high from ejecting end 110 Rapid fire goes out.Since there are two trajectories for tool, then entering to be packed into two objects 140 to be penetrated in bullet mouth 131, if which overcome only one It is a to be somebody's turn to do after penetrating object 140 when penetrating object 140 when projecting, when the shock strength wait penetrate object 140 is not enough to shattered glass, unmanned plane It is only drop to ground, object 140 to be penetrated of reloading takes off again to original position, is shot at, when this is both expended Between, also it is unfavorable for the technological deficiency succoured in time to indoor indicator of trapped personnel.When in pipeline have the first trajectory 181 and second When trajectory 182, if the shock strength wait penetrate object 140 for being located at the first trajectory 181 when being not enough to shattered glass, can make to be located at the The object to be penetrated 140 of two trajectories 182 emits simultaneously, bigger impact force is generated, then timely shattered glass, convenient for the people of indoor and outdoor Member's disengaging.To reach the glass that can quickly smash target area, the technical effect of indoor indicator of trapped personnel is succoured in time.

Referring to Figure 1, Fig. 1 is that a kind of overall structure of grenade instrumentation for unmanned plane provided in an embodiment of the present invention is shown It is intended to.Angular range of the hollow portion 123 relative to the second interface 230 (the second interface 230 can be parallel to each other with ground) Can be 30 ° -60 °, i.e., the angular range of route when penetrating object 140 and projecting and the second interface 230 can be 30 ° - 60°.Assuming that hollow portion 123 is A relative to the angle of the second interface 230, then 30 °≤A≤60 °.When 30 ° of A <, if transmitting Object 140 to be penetrated, then object 140 to be penetrated will generate recoil, the direction of the recoil and ejecting end 110 it is contrary, at this point, by force Big recoil mutually seriously affects the balance of unmanned plane itself, or even destroys the state of flight of unmanned plane, and unmanned plane is caused to stop It runs well, to be unfavorable for the normal work of unmanned plane, influences the stability of ejecting end 110, reduce the accuracy of shooting.When At 60 ° of A >, if emitting object 140 to be penetrated, make ejecting end 110 and wall close to horizontal state, it at this time can not be to target area The glass in domain is aimed at, but also powerful recoil caused by object to be penetrated 140 seriously affects the balance of unmanned plane itself, very To the state of flight for destroying unmanned plane, unmanned plane is caused to stop running well, to be unfavorable for the normal work of unmanned plane, influenced The stability of ejecting end 110 reduces the accuracy of shooting.

For joint unit 200:

The joint unit 200 may include the first interface 210, ontology 220 and the second interface 230.

First interface 210 can be detachably connected with fuselage；Ontology 220 can be fixedly connected with the first interface 210； Second interface 230 can be fixedly connected with ontology 220, and the first clamping seat 231 and the second card are provided on the second interface 230 Joint chair 232；Wherein, ontology 220 can be between the first interface 210 and the second interface 230；First clamping 231 He of seat Second clamping seat 232 can be rendered as symmetrically being distributed relative to the center of the second interface 230；First interface 210 and Two interfaces 230 can be rendered as symmetrical relative to ontology 220.First interface 210 can be rendered as engraved structure, And/or second interface 230 can be rendered as engraved structure, and/or, ontology 220 can be rendered as engraved structure.

Referring to Figure 1 and Fig. 3, Fig. 1 be a kind of grenade instrumentation for unmanned plane provided in an embodiment of the present invention entirety Structural schematic diagram, Fig. 3 are that the embodiment of the present invention provides a kind of left view schematic diagram of grenade instrumentation for unmanned plane.At nobody The clamping portion to match with the first interface 210 can be set in the fuselage bottom of machine, which can be with clamping portion Dismountable connection.Ontology 220 can be fixedly connected with the first interface 210, and the second interface 230 can be solid with ontology 220 Fixed connection, allows to constitute joint unit 200 by the first interface 210, ontology 220 and the second interface 230.Second The first clamping seat 231 and the second clamping seat 232 can be set on interface 230.First clamping seat 231 can be with the first support The first end 311 of arm 310 is mutually permanently connected, and the second clamping seat 232 can be mutual with the third end 321 of the second support arm 320 It is fixedly connected.The center of second interface 230 can be the geometric center of the second interface 230, such as the second interface 230 is in When being now square, the center of second interface 230 can be the geometric center of square.Ontology 220 can be positioned at Part between one interface 210 and the second interface 230, can be by the first interface 210, ontology 220 and the second interface 230 constitute joint unit 200.

First interface 210 can be rendered as engraved structure, and/or, the second interface 230 can be rendered as hollow out knot Structure, and/or, ontology 220 can be rendered as engraved structure.That is the first interface 210 and the second interface 230 can be rendered as Engraved structure or the first interface 210 and third interface can be rendered as engraved structure etc..Due to the first interface 210 can be rendered as engraved structure, and/or, the second interface 230 can be rendered as engraved structure, and/or, ontology 220 can be with It is rendered as engraved structure；When then the engraved structure can reduce the first interface 210 of production, ontology 220 and the second interface 230 Material, then reduce the weight of the first interface 210, ontology 220 and the second interface 230, when taking off to reduce unmanned plane The weight of entrained load is conducive to the flying height for promoting unmanned plane, increases the cruise duration of unmanned plane.

In order to the first interface 210 can and fuselage be detachably connected and be explained in detail, now said in detailed below Bright: unmanned plane can be multi-rotor unmanned aerial vehicle, and the fuselage of unmanned plane is segmented into including at least three sections, i.e. head, fuselage and machine Tail, and can be attached by the connection type of detachable connection between three sections, being constituted an internal structure with this can The fixed-wing unmanned plane of disassembly, so that when local damage occurs in the fuselage of unmanned plane, corresponding can remove and damage Bad position repairs, and has simple, convenient technical effect.And when the part of fuselage can not due to damaging When reparation, can also the position that can not repair of corresponding dismounting, i.e., the position that can not be repaired is substituted, to overcome In the prior art because fuselage is using integrated whole design, when so that there is fuselage local damage and can not repair, it has to more The technological deficiency for changing the entire fuselage of unmanned plane, reaches and significantly reduces the technical effect of maintenance cost.Also, in unmanned plane Head, and/or, fuselage, and/or, the attachment base to match with the first interface 210 can be set on tail, so that One interface 210 can be detachably connected with the fuselage.It then, must not when local damage, which occurs, in grenade instrumentation to be repaired It is changed without the technological deficiency of the entire fuselage of unmanned plane, reaches and significantly reduces the technical effect of maintenance cost.

For load-supporting part 300:

Load-supporting part 300 may include the first support arm 310 and the second support arm 320.

First end 311 and second end 312, first end 311 and the first clamping seat 231 has can be set in first support arm 310 It is fixedly connected, the first mounting hole 313 can be set in second end 312；

Third end 321 and the 4th end 322, third end 321 and the second clamping seat has can be set in second support arm 320 232 are fixedly connected；The second mounting hole 323 can be set on the 4th end 322；Wherein, first end 311 and second end 312 can be the both ends of the first support arm 310 opposition respectively, and third end 321 and the 4th end 322 can be the second support arm respectively The both ends of 320 opposition.First support arm 310 and/or the second support arm 320 can be and be rendered as engraved structure, to reduce nobody The weight of entrained load when machine takes off is conducive to the flying height for promoting unmanned plane, increases the cruise duration of unmanned plane.

First mounting hole 313 may include first through hole and the second through-hole, and first through hole and the second through-hole are relative to second The center at end 312 can be rendered as symmetrical.Wherein, the first gag lever post 410 passes through first through hole and the second through-hole；First is logical The diameter in hole can be greater than the diameter of the first gag lever post 410, and the diameter of the second through-hole can be greater than the first gag lever post 410 Diameter.Second mounting hole 323 may include third through-hole and fourth hole, and third through-hole and fourth hole are relative to the 4th The center at end 322 can be rendered as symmetrical.Wherein, the second gag lever post 420 can pass through third through-hole and fourth hole；The The diameter of three through-holes can be greater than the diameter of the second gag lever post 420, and the diameter of fourth hole can be greater than the second gag lever post 420 diameter.

Referring to Figure 1 and Fig. 4, Fig. 1 be a kind of grenade instrumentation for unmanned plane provided in an embodiment of the present invention entirety Structural schematic diagram, Fig. 4 are that the embodiment of the present invention provides a kind of right view schematic diagram of grenade instrumentation for unmanned plane.First end 311 and second end 312 can be respectively the first support arm 310 both ends, first end 311 can be fixed with the first clamping seat 231 Connection, makes the first support arm 310 and joint unit 200 link together, and when relay part is moved with unmanned plane, drives first Brace 310 moves together.The first mounting hole 313 can be set in second end 312, the first mounting hole 313 may include One through-hole and the second through-hole.

In order to which the first gag lever post 410 is explained in detail across first through hole and the second through-hole, following two is now provided Embodiment is described in detail:

The first embodiment.It the aperture direction of first through hole can be with second end 312 close to the plane phase of first through hole It is mutually parallel.First through hole can be formed along the direction of the column body section by installing a column in first end 311, So that the aperture direction of first through hole is parallel to each other relative to ducted body.The diameter of first through hole can be greater than the first gag lever post 410 diameter, it is assumed that the diameter of the first gag lever post 410 is B, and the diameter of first through hole is C1, then C1 > B.Due to first through hole Diameter be greater than the first gag lever post 410 diameter, then the first gag lever post 410 can slide in first through hole, this to be arranged The first support arm 310 outside the first gag lever post 410 can be moved along the first gag lever post 410.When object 140 to be penetrated from After ejecting end 110 projects, it is mobile relative to the first support arm 310 that generated back pressure can push emission element 100, then leads to It crosses and first spring is set between the first fastening end 411 and the first mounting hole 313, in the second fastening end 412 and the first mounting hole Second spring is set between 313, by the deformation of the first spring and/or second spring, to absorb energy caused by object 140 to be penetrated Amount.To overcome the back pressure damage unmanned plane and load-supporting part 300 that generate when penetrating object 140 and projecting, reaches and be conducive to nothing The technical effect that man-machine normal flight and 300 joint unit 200 of load-supporting part work normally.

Second of embodiment.It the aperture direction of second through-hole can be with second end 312 close to the plane phase of first through hole It is mutually parallel.The second through-hole can be formed along the direction of the column body section by installing a column in second end 312, So that the aperture direction of the second through-hole is parallel to each other relative to ducted body.The diameter of second through-hole can be greater than the first gag lever post 410 diameter, it is assumed that the diameter of the first gag lever post 410 is B, and the diameter of the second through-hole is C2, then C2 > B.Due to the second through-hole Diameter be greater than the first gag lever post 410 diameter, then the first gag lever post 410 can slide in the second through-hole, this to be arranged The first support arm 310 outside the first gag lever post 410 can be moved along the first gag lever post 410.When object 140 to be penetrated from After ejecting end 110 projects, it is mobile relative to the first support arm 310 that generated back pressure can push emission element 100, then leads to It crosses and first spring is set between the first fastening end 411 and the first mounting hole 313, in the second fastening end 412 and the first mounting hole Second spring is set between 313, by the deformation of the first spring and/or second spring, to absorb energy caused by object 140 to be penetrated Amount.To overcome the back pressure damage unmanned plane and load-supporting part 300 that generate when penetrating object 140 and projecting, reaches and be conducive to nothing The technical effect that man-machine normal flight and 300 joint unit 200 of load-supporting part work normally.

It should be noted that first through hole and the second through-hole can be different relative to the distance of the first interface 210, such as First through hole is more farther than the distance of second the first interface of through-hole distance 210, then makes between first through hole and the second through-hole With difference in height, after the first gag lever post 410 being made to pass through first through hole and the second through-hole by the difference in height, relative to Ground is heeling condition.First gag lever post 410 can be 30 ° -60 ° relative to the tilt angle on ground.If the first limit Bar 410 is W1 relative to the tilt angle on ground, then 30 °≤W1≤60 °, can make so among the above sky portion 123 relative to The angular range of second interface 230 can be 30 ° -60 °.

After the first gag lever post 410 passes through first through hole and the second through-hole, it is assumed that extended line by first through hole and P1 point is intersected at by the extended line of the second through-hole, is connected by P1 point, first through hole and the second through-hole and forms a right angle trigonometry Shape, the first gag lever post 410 across first through hole and the second throughhole portions are the bevel edge of the right angled triangle.First through hole and The right-angle side that P1 point is formed is Y1, and the right-angle side that the second through-hole and P1 point are formed is Y2, then Y2:Y1=Z1, then the range of Z1 can To be (1/2)≤Z1≤(√ 3)/2.Due to (1/2)≤Z1≤(√ 3)/2, when the first gag lever post 410 passes through first through hole and the After two through-holes, the first gag lever post 410 is heeling condition relative to ground, and hollow portion 123 can be made relative to the first linking The angular range in face 210 can be 30 ° -60 °, then ejecting end 110 can then make than handling end 130 closer to ground at this time Obtaining the object to be penetrated 140 projected from ejecting end 110 can be relative to the first shooting downwards of interface 210, and it is right in the sky to not only improve Glass at door and window is aimed at, and the recoil for being conducive to generate object 140 to be penetrated tilts upward, and it is downward to overcome recoil When, it will push the technological deficiency that unmanned plane decline bumps against ground or metope.Make unmanned plane safety, smooth flight to reach, And the technical effect that object 140 to be penetrated steadily projects.

Continuing with being a kind of grenade instrumentation for unmanned plane provided in an embodiment of the present invention referring to Fig. 1 and Fig. 4, Fig. 1 Overall structure diagram, Fig. 4 are that the embodiment of the present invention provides a kind of right view schematic diagram of grenade instrumentation for unmanned plane.For Third through-hole is passed through to second gag lever post 420 and fourth hole is explained in detail, now provide following two embodiment into Row is described in detail:

The first embodiment.It the aperture direction of third through-hole can be with the 4th end 322 close to the plane phase of third through-hole It is mutually parallel.Third through-hole can be formed along the direction of the column body section by installing a column on the 4th end 322, So that the aperture direction of third through-hole is parallel to each other relative to ducted body.The diameter of third through-hole can be greater than the second gag lever post 420 diameter, it is assumed that the diameter of the second gag lever post 420 is B, and the diameter of third through-hole is C3, then C3 > B.Due to third through-hole Diameter be greater than the second gag lever post 420 diameter, then the second gag lever post 420 can slide in third through-hole, this to be arranged The second support arm 320 outside the second gag lever post 420 can be moved along the second gag lever post 420.When object 140 to be penetrated from After ejecting end 110 projects, it is mobile relative to the second support arm 320 that generated back pressure can push emission element 100, then leads to The setting third spring between third fastening end 421 and the second mounting hole 323 is crossed, in the 4th fastening end 422 and the second mounting hole 4th spring is set between 323, by the deformation of third spring and/or the 4th spring, to absorb energy caused by object 140 to be penetrated Amount.To overcome the back pressure damage unmanned plane and load-supporting part 300 that generate when penetrating object 140 and projecting, reaches and be conducive to nothing The technical effect that man-machine normal flight and 300 joint unit 200 of load-supporting part work normally.

Second of embodiment.It the aperture direction of fourth hole can be with the 4th end 322 close to the plane phase of fourth hole It is mutually parallel.Fourth hole can be formed along the direction of the column body section by installing a column on the 4th end 322, So that the aperture direction of fourth hole is parallel to each other relative to ducted body.The diameter of fourth hole can be greater than the second gag lever post 420 diameter, it is assumed that the diameter of the second gag lever post 420 is B, and the diameter of third through-hole is C4, then C4 > B.Due to fourth hole Diameter be greater than the second gag lever post 420 diameter, then the second gag lever post 420 can slide in fourth hole, this to be arranged The second support arm 320 outside the second gag lever post 420 can be moved along the second gag lever post 420.When object 140 to be penetrated from After ejecting end 110 projects, it is mobile relative to the second support arm 320 that generated back pressure can push emission element 100, then leads to The setting third spring between third fastening end 421 and the second mounting hole 323 is crossed, in the 4th fastening end 422 and the second mounting hole 4th spring is set between 323, by the deformation of third spring and/or the 4th spring, to absorb energy caused by object 140 to be penetrated Amount.To overcome the back pressure damage unmanned plane and load-supporting part 300 that generate when penetrating object 140 and projecting, reaches and be conducive to nothing The technical effect that man-machine normal flight and 300 joint unit 200 of load-supporting part work normally.

Continuing with being a kind of grenade instrumentation for unmanned plane provided in an embodiment of the present invention referring to Fig. 1 and Fig. 5, Fig. 1 Overall structure diagram, Fig. 5 are that the embodiment of the present invention provides a kind of front view schematic diagram of grenade instrumentation for unmanned plane.The Three through-holes and fourth hole can be different relative to the distance of the first interface 210, such as third through-hole is than fourth hole distance The distance of first interface 210 is farther, then makes have difference in height between third through-hole and fourth hole, passes through the difference in height It is heeling condition relative to ground after the second gag lever post 420 can be made to pass through third through-hole and fourth hole.Second limit Position bar 420 can be 30 ° -60 ° relative to the tilt angle on ground.If inclination of i.e. the first gag lever post 410 relative to ground Angle is W2, then 30 °≤W2≤60 °, can make angle model of the sky portion 123 relative to the second interface 230 among the above in this way It encloses and can be 30 ° -60 °.

After the second gag lever post 420 passes through third through-hole and fourth hole, it is assumed that by third through-hole extended line and P2 point is intersected at by the extended line of fourth hole, is connected by P2 point, third through-hole with fourth hole and forms a right angle trigonometry Shape, the second gag lever post 420 across third through-hole and fourth hole part are the bevel edge of the right angled triangle.Third through-hole and The right-angle side that P2 point is formed is Y3, and the right-angle side that fourth hole and P1 point are formed is Y4, then Y4:Y3=Z2, then the range of Z2 can To be (1/2)≤Z2≤(√ 3)/2.Due to (1/2)≤Z2≤(√ 3)/2, when the second gag lever post 420 passes through third through-hole and the After four through-holes, the second gag lever post 420 is heeling condition relative to ground, and hollow portion 123 can be made relative to the first linking The angular range in face 210 can be 30 ° -60 °, then ejecting end 110 can then make than handling end 130 closer to ground at this time Obtaining the object to be penetrated 140 projected from ejecting end 110 can be relative to the first shooting downwards of interface 210, and it is right in the sky to not only improve Glass at door and window is aimed at, and the recoil for being conducive to generate object 140 to be penetrated tilts upward, and it is downward to overcome recoil When, it will push the technological deficiency that unmanned plane decline bumps against ground or metope.Make unmanned plane safety, smooth flight to reach, And the technical effect that object 140 to be penetrated steadily projects.

For damping part 400:

The damping part 400 may include the first gag lever post 410, the second gag lever post 420,430 and of the first elastic parts Second elastic parts 440.

First gag lever post 410 can be set the first fastening end 411 and the second fastening end 412, and the first fastening end 411 can be with It is fixedly connected with the first pedestal 124, and the second fastening end 412 can be fixedly connected with the second pedestal 125, the first gag lever post 410 can pass through the first mounting hole 313；Third fastening end 421 and the 4th fastening end 422 has can be set in second gag lever post 420, Third fastening end 421 can be fixedly connected with third pedestal 126, and the 4th fastening end 422 can be with the 4th pedestal 127 It is fixedly connected, the second gag lever post 420 can pass through second mounting hole 323.

First elastic parts 430 can be set in the outside of first gag lever post 410, and the first elastic parts 430 can be with Between the first fastening end 411 and the second fastening end 412；Second elastic parts 440 can be set in the second gag lever post 420 Outside, the second elastic parts 440 can be between third fastening end 421 and the 4th fastening ends 422.Wherein, first is tight Fixed end 411 and the second fastening end 412 can be the both ends of the first gag lever post 410 opposition, third fastening end 421 and the 4th fastening end 422 can be the both ends of the second gag lever post 420 opposition.

First elastic parts 430 may include the first spring and second spring, and the first spring can be set in described first The outside of gag lever post 410, and second spring can be set in the outside of the first gag lever post 410；Wherein, the first spring can position Between the first fastening end 411 and the first mounting hole 313, and second spring can be located at the second fastening end 412 and the first peace It fills between hole 313.Second elastic parts 440 may include third spring and the 4th spring, and third spring can be set in second The outside of gag lever post 420, and the 4th spring can be set in the outside of the second gag lever post 420；Wherein, third spring can position Between third fastening end 421 and the second mounting hole 323, and the 4th spring can be located at the 4th fastening end 422 and the second peace It fills between hole 323.

Referring to Figure 1 and Fig. 6, Fig. 1 be a kind of grenade instrumentation for unmanned plane provided in an embodiment of the present invention entirety Structural schematic diagram, Fig. 6 are that the embodiment of the present invention provides a kind of rearview schematic diagram of grenade instrumentation for unmanned plane.First limit Position bar 410 and/or the second gag lever post 420, which can be, is rendered as cylindrical metal, rod-shaped stick.First fastening end 411 and second is tight Fixed end 412 can be the both ends of the first gag lever post 410 respectively, and third fastening end 421 and the 4th fastening end 422 can be respectively The both ends of two gag lever posts 420.

First fastening end 411 of the first gag lever post 410 can be fixedly connected with the first pedestal 124, the first gag lever post 410 The second fastening end 412 be fixedly connected with the second pedestal 125, to make the tube body in the first gag lever post 410 and emission element 100 120 are fixed to each other.The third fastening end 421 of second gag lever post 420 is fixedly connected with the 4th pedestal 127, the second gag lever post 420 The 4th fastening end 422 be fixedly connected with the 4th pedestal 127, to make the tube body in the second gag lever post 420 and emission element 100 120 are fixed to each other.Then the first gag lever post 410 and the second gag lever post 420 is made to be separately fixed at the two sides of tube body 120, by tube body 120 are fixed between the first gag lever post 410 and the second gag lever post 420.

In order to be set in outside and the first elastic parts 430 packet of the first gag lever post 410 to the first elastic parts 430 It includes the first spring and second spring is explained in detail, following two embodiment is now provided and is described in detail respectively:

The first embodiment.It can be arranged with the first spring in the outside of the first gag lever post 410, the first spring can position Between the first fastening end 411 and the first mounting hole 313.One end of first spring can be clamped with the first fastening end 411, i.e., by One end of the first spring is kept out in first fastening end 411, is fixed on one end of the first spring at the first fastening end 411.First The other end of spring can be clamped with the second end 312 for being provided with the first mounting hole 313, i.e., keep out first by second end 312 The other end of spring is fixed on the other end of the first spring at second end 312.Make the both ends of the first spring respectively in this way and First fastening end 411, second end 312 are fixedly connected, when tube body 120 drives the first gag lever post 410 to move along the first mounting hole 313 When dynamic, also drive the first spring that elastic deformation occurs, it is mobile to absorb tube body 120 due to the elastic deformation that the first spring occurs The kinetic energy of generation reduces the generated mechanical energy pair when penetrating object 140 and projecting to reach the operating position of stable tube body 120 The damage of load-supporting part 300, joint unit 200, or influence the normal operating conditions of load-supporting part 300, joint unit 200；Together When, adverse effect when also reducing to unmanned plane stabilized flight or hovering.

Second of embodiment.It can be arranged with second spring in the outside of the first gag lever post 410, second spring can position Between the second fastening end 412 and the first mounting hole 313.One end of second spring can be clamped with the second fastening end 412, i.e., by One end of second spring is kept out in second fastening end 412, is fixed on one end of second spring at the second fastening end 412.Second The other end of spring can be clamped with the second end 312 for being provided with the first mounting hole 313, i.e., keep out second by second end 312 The other end of spring is fixed on the other end of second spring at second end 312.Make the both ends of second spring respectively in this way and Second fastening end 412, second end 312 are fixedly connected, when tube body 120 drives the first gag lever post 410 to move along the first mounting hole 313 When dynamic, also drive second spring that elastic deformation occurs, it is mobile to absorb tube body 120 due to the elastic deformation that second spring occurs The kinetic energy of generation reduces the generated mechanical energy pair when penetrating object 140 and projecting to reach the operating position of stable tube body 120 The damage of load-supporting part 300, joint unit 200, or influence the normal operating conditions of load-supporting part 300, joint unit 200；Together When, adverse effect when also reducing to unmanned plane stabilized flight or hovering.

Continuing with being a kind of grenade instrumentation for unmanned plane provided in an embodiment of the present invention referring to Fig. 1 and Fig. 6, Fig. 1 Overall structure diagram, Fig. 6 are that the embodiment of the present invention provides a kind of rearview schematic diagram of grenade instrumentation for unmanned plane.For The outside of second gag lever post 420 is set in the second elastic parts 440 and second elastic parts 440 includes third spring It is explained in detail with the 4th spring, following two embodiment is now provided and is described in detail respectively:

The first embodiment.It can be arranged with third spring in the outside of the second gag lever post 420, third spring can position Between third fastening end 421 and the second mounting hole 323.One end of third spring can be clamped with third fastening end 421, i.e., by One end of third spring is kept out in third fastening end 421, is fixed on one end of third spring at third fastening end 421.Third The other end of spring can be clamped with the 4th end 322 for being provided with the second mounting hole 323, i.e., keep out third by the 4th end 322 The other end of spring is fixed on the other end of third spring at the 4th end 322.Make the both ends of third spring respectively in this way and Third fastening end 421, the 4th end 322 are fixedly connected, when tube body 120 drives the second gag lever post 420 to move along the second mounting hole 323 When dynamic, also drive third spring that elastic deformation occurs, it is mobile to absorb tube body 120 due to the elastic deformation that third spring occurs The kinetic energy of generation reduces the generated mechanical energy pair when penetrating object 140 and projecting to reach the operating position of stable tube body 120 The damage of load-supporting part 300, joint unit 200, or influence the normal operating conditions of load-supporting part 300, joint unit 200；Together When, adverse effect when also reducing to unmanned plane stabilized flight or hovering.

Second of embodiment.It can be arranged with the 4th spring in the outside of the second gag lever post 420, the 4th spring can position Between the 4th fastening end 422 and the second mounting hole 323.One end of 4th spring can be clamped with the 4th fastening end 422, i.e., by One end of the 4th spring is kept out in 4th fastening end 422, is fixed on one end of the 4th spring at the 4th fastening end 422.4th The other end of spring can be clamped with the 4th end 322 for being provided with the second mounting hole 323, i.e., keep out the 4th by the 4th end 322 The other end of spring is fixed on the other end of the 4th spring at the 4th end 322.Make the both ends of the 4th spring respectively in this way and 4th fastening end 422, the 4th end 322 are fixedly connected, when tube body 120 drives the second gag lever post 420 to move along the second mounting hole 323 When dynamic, also drive the 4th spring that elastic deformation occurs, it is mobile to absorb tube body 120 due to the elastic deformation that the 4th spring occurs The kinetic energy of generation reduces the generated mechanical energy pair when penetrating object 140 and projecting to reach the operating position of stable tube body 120 The damage of load-supporting part 300, joint unit 200, or influence the normal operating conditions of load-supporting part 300, joint unit 200；Together When, adverse effect when also reducing to unmanned plane stabilized flight or hovering.

First spring and second spring can all be rendered as cylinder, and the diameter of the first spring can be the straight of second spring Twice of diameter assumes that the diameter of the first spring is P1, the diameter of second spring is P2, then P1=2*P2.Due to the first spring Diameter be twice of diameter of second spring, when recoil pushes the first spring and elastic deformation occurs for second spring, the One spring can be more with respect to second spring absorption recoil energy, then reduce tube body 120 relative to the first mounting hole 313 mobile distances and speed are conducive to the flight for stablizing unmanned plane so that reaching reduces recoil to the impact force of unmanned plane State improves the technical effect of shooting accuracy.

Third spring and the 4th spring can all be rendered as cylinder, and the diameter of third spring can be the straight of the 4th spring The diameter of twice of diameter, i.e. hypothesis third spring is P3, and the diameter of the 4th spring is P4, then P3=2*P4.Due to third spring Diameter be twice of diameter of the 4th spring, when recoil pushes third spring and elastic deformation occurs for the 4th spring, the Three springs can be more with respect to the 4th spring absorption recoil energy, then reduce tube body 120 relative to the second mounting hole 323 mobile distances and speed are conducive to the flight for stablizing unmanned plane so that reaching reduces recoil to the impact force of unmanned plane State improves the technical effect of shooting accuracy.

In practical applications, when fire occurs for high residential building, object 140 to be penetrated can be packed into ejecting end 110 in advance, it will First interface 210 is fixedly connected with the bottom of unmanned aerial vehicle body in joint unit 200.Flight system is passed through by ground handling operator It unites to issue to unmanned plane and instruct, unmanned plane is made to take off to the story height that fire occurs.Then by being arranged in ejecting end 110 The floor external circumstances of fire occur to watch for image pick-up device on three positioning areas 170, when finding the external windows of fiery residence floor, Unmanned plane can be hovered to window.Emitted again by being located at the first laser in ejecting end 110 on first positioning area 150 Device, second laser transmitter on the second positioning area 160 aim at the glass of window, can choose the edge to glass Place is aimed at, such as is aimed at positioned at the junction of glass and wall, lesser shock strength can be used in this way to hit Cullet.If by the spatial position of mobile unmanned plane, so that first laser transmitter and second laser transmitter are targeted to window The glass of mouth then can issue shooting instruction to unmanned plane by ground handling operator.At this point, being located at outside baffle 180 Control switch 132 is closed, since control switch 132 and object to be penetrated 140 connect, then the closure of control switch 132 can excite to It penetrates object 140 and reaches ejecting end 110 along the first trajectory 181 and/or the second trajectory 182 from entering bullet mouth 131, it is high from ejecting end 110 Rapid fire goes out.The glass at window can be smashed by the powerful kinetic energy of object 140 to be penetrated, has then got through and has been located in fire floor room The window that indicator of trapped personnel is connected to the external world, allows indoor indicator of trapped personnel to escape from window；It is also possible that being located at room Outer fire fighter is entered the room from window by equipment such as aerial ladders and is succoured.To reach by unmanned plane with transmitting Component 100, joint unit 200, load-supporting part 300 and damping part 400.Now to emission element 100, joint unit 200, load-bearing Component 300 and the flight of damping part 400 make object to be penetrated at the high residential building door and window that fire occurs, then through control switch 132 140 shattered glass door and windows carry out the technical effect for helping the indicator of trapped personnel in high residential building to escape in time.

For power mechanism 500:

Power mechanism 500 may include the first steering engine 510 and the second steering engine 520.

First steering engine 510 may include first shell 511 and first rotating shaft 512, and first shell 511 can be with the first limit Area 530 is fixedly connected, and first rotating shaft 512 can be fixedly connected with first interface；

Second steering engine 520 may include second shell 521 and the second shaft 522, and second shell 521 can be with the second limit Area 540 connects, and the second shaft 522 can be fixedly connected with second interface.

It is also provided with the first pedestal, the second pedestal and first interface in the first side of tube body, is gone back in second side Third pedestal, the 4th pedestal and and second interface can be set.Wherein, first interface be located at the first pedestal and the second pedestal it Between, second interface is between third pedestal and the 4th pedestal.

It is provided with the first mounting hole and the first spacing zone 530 in first support arm of load-supporting part in second end 312, first Mounting hole and the first spacing zone 530 can be located on the same side of second end 312, such as in a side of second end 312 The first mounting hole is arranged on the cylindrical body in upper stationary cylinder, and the first spacing zone 530 can be located at the same side with the cylindrical body On face.The second mounting hole and the second spacing zone 540 are provided in second support arm on 4th end 322.Second mounting hole and second Spacing zone 530 can be located on the same side at the 4th end 322, such as the stationary cylinder on a side at the 4th end 322, Second mounting hole is set on the cylindrical body, and the second spacing zone 530 can be located on the same side with the cylindrical body.

Specifically, the first pedestal, the second pedestal and first interface can also be arranged in tube body on the first side, first is connect Mouth with first rotating shaft 512 for being fixedly connected.Third pedestal, the 4th pedestal and second interface are set in second side, and second connects Mouth with the second shaft 522 for being fixedly connected.

The first mounting hole and the first spacing zone 530, the second support are also provided on first support arm of load-supporting part The second mounting hole and the second spacing zone 540 are also provided in arm on 4th end 322.First spacing zone 530 can place The first shell 511 of one steering engine 510, first shell 511 can be the shell of first motor, and first shell 511 is fixed on first On spacing zone 530.Second spacing zone 540 can place the second shell 521 of the second steering engine 520, and second shell 521 can be The shell of two motors, second shell 521 are fixed on the second spacing zone 540.

In order to be fixedly connected with the first spacing zone 530 to first shell 511, first rotating shaft 512 can connect with first Mouth is fixedly connected；Second shell 521 can be connected with the second spacing zone 540, and the second shaft 522 can be with the fixed company of second interface It connects and is explained in detail, following two embodiment is now provided and is described in detail:

The first embodiment.By the first shell 511 of the first steering engine 510 in power mechanism 500 and the first spacing zone 530 It is fixedly connected, the first rotating shaft 512 of the first steering engine 510 is fixedly connected with the first interface in first side in emission element. By the work of the first steering engine 510, first rotating shaft 512 is started turning, tube body is driven by the rotation of first rotating shaft 512 together It is mobile, it is assumed that first rotating shaft 512 is to rotate counterclockwise, then tube body will also rotate counterclockwise.Ejecting end is relative on ground at this time Lower movement in unmanned plane hovering when the window of high residential building, can pass through the first rudder to adjust the injection direction of object to be penetrated Machine 510 adjusts the injection direction of object to be penetrated, is shot in time to target area.It is in various in unmanned plane to reach In flight attitude, firing direction can be adjusted in time, be conducive to the technical effect succoured to the indicator of trapped personnel of high residential building.

Second of embodiment.By the second shell 521 of the second steering engine 520 in power mechanism 500 and the second spacing zone 540 It is fixedly connected, the second shaft 522 of the second steering engine 520 is fixedly connected with the second interface in second side in emission element. By the work of the second steering engine 520, the second shaft 522 is started turning, tube body is driven together by the rotation of the second shaft 522 It is mobile, it is assumed that the second shaft 522 is to rotate counterclockwise, then tube body will also rotate counterclockwise.Ejecting end is relative on ground at this time Lower movement in unmanned plane hovering when the window of high residential building, can pass through the second rudder to adjust the injection direction of object to be penetrated Machine 520 adjusts the injection direction of object to be penetrated, is shot in time to target area.It is in various in unmanned plane to reach In flight attitude, firing direction can be adjusted in time, be conducive to the technical effect succoured to the indicator of trapped personnel of high residential building.

It should be noted last that the above specific embodiment is only used to illustrate the technical scheme of the present invention and not to limit it, Although being described the invention in detail referring to example, those skilled in the art should understand that, it can be to the present invention Technical solution be modified or replaced equivalently, without departing from the spirit and scope of the technical solution of the present invention, should all cover In the scope of the claims of the present invention.

Claims

1. a kind of power load carrier for unmanned plane, which is characterized in that the power load carrier packet for unmanned plane It includes:

Load-supporting part, the load-supporting part include:

First support arm, first support arm are provided with first end and second end, and the first end and the first clamping seat are fixed It connects, is provided with the first mounting hole and the first spacing zone in the second end；

Second support arm, second support arm are provided with third end and the 4th end, and the third end and the second clamping seat are fixed Connection；The second mounting hole and the second spacing zone are provided on 4th end；

Wherein, the first end and the second end are the both ends of first support arm opposition, the third end and described the Four ends are the both ends of the second support arm opposition；

Power mechanism, the power mechanism include:

First steering engine, first steering engine include first shell and first rotating shaft, the first shell and first spacing zone It is fixedly connected, the first rotating shaft is fixedly connected with first interface；

Second steering engine, second steering engine include second shell and the second shaft, the second shell and second spacing zone Connection, second shaft are fixedly connected with second interface.

2. being used for the power load carrier of unmanned plane as described in claim 1, which is characterized in that described for the dynamic of unmanned plane Power load carrier includes:

The first end and the second interface are perpendicular.

3. being used for the power load carrier of unmanned plane as claimed in claim 2, which is characterized in that described for the dynamic of unmanned plane Power load carrier includes:

The third end and second interface are perpendicular.

4. being used for the power load carrier of unmanned plane as claimed in claim 3, which is characterized in that described for the dynamic of unmanned plane Power load carrier includes:

First mounting hole includes first through hole and the second through-hole, and the first through hole and second through-hole are relative to described The central symmetry of second end is distributed；

Wherein, the first gag lever post passes through the first through hole and second through-hole.

5. being used for the power load carrier of unmanned plane as claimed in claim 4, which is characterized in that described for the dynamic of unmanned plane Power load carrier includes:

The diameter of the first through hole is greater than the diameter of first gag lever post, and the diameter of second through-hole is greater than described the The diameter of one gag lever post.

6. being used for the power load carrier of unmanned plane as claimed in claim 5, which is characterized in that described for the dynamic of unmanned plane Power load carrier includes:

Second mounting hole includes third through-hole and fourth hole, and the third through-hole and the fourth hole are relative to described The central symmetry at the 4th end is distributed；

Wherein, the second gag lever post passes through the third through-hole and the fourth hole.

7. being used for the power load carrier of unmanned plane as claimed in claim 6, which is characterized in that described for the dynamic of unmanned plane Power load carrier includes:

The diameter of the third through-hole is greater than the diameter of second gag lever post, and the diameter of the fourth hole is greater than described the The diameter of two gag lever posts.