CN207141361U - A kind of horn and unmanned plane - Google Patents

Abstract

The utility model embodiment discloses a kind of horn and unmanned plane.The horn is installed on loose impediment, and the outline with the loose impediment after folding is bonded.The unmanned plane includes fuselage, the horn as described above being connected with the fuselage and the power set located at the horn, outline of the horn with the fuselage after folding and is bonded.Pass through above-mentioned technical proposal, the horn that the utility model embodiment provides can be bonded after folding with the outline of loose impediment so that the structure using the loose impediment of the horn is compacter.When the horn is applied to unmanned plane, horn is bonded after folding with the outline of fuselage, and foldable structure is simple, and horn structure of unmanned plane after folding is compacter.

Description

A kind of horn and unmanned plane

Technical field

The utility model is related to unmanned air vehicle technique field, more particularly to a kind of horn and with this horn nobody Machine.

Background technology

UAV, abbreviation unmanned plane (UAV), it is a kind of new ideas equipment being in developing rapidly, it has Maneuverability, rapid reaction, unmanned, operation require the advantages of low.Unmanned plane is set by carrying multiclass sensor or shooting It is standby, it is possible to achieve image real-time Transmission, high-risk areas detecting function, to be the strong supplement of satellite remote sensing and traditional air remote sensing. At present.The use range of unmanned plane has widened military affairs, scientific research, civilian three big field, specifically in power communication, meteorology, agriculture Industry, ocean, exploration, photograph, prevent and reduce natural disasters, Crop Estimation, drug law enforcement anti-smuggling, border patrol, the field such as public security anti-terrorism are applied very Extensively.

At present, the problem of rotor wing unmanned aerial vehicle generally existing is not portable.Based on this, although there is some unmanned functions to accomplish to roll over Fold and be accommodated in certain space, but still suffer from the problems such as foldable structure is excessively complicated and not compact enough.

Utility model content

The utility model embodiment provides a kind of horn and the unmanned plane with this horn, can solve the problem that existing foldable The problem of foldable structure of unmanned plane is excessively complicated and not compact enough.

In order to solve the above technical problems, the technical scheme that the utility model uses is：A kind of horn is provided, is installed on Loose impediment, outline of the horn with the loose impediment after folding are bonded.

In certain embodiments, the horn includes main frame arm and the slave arm being connected with the main frame arm.

In certain embodiments, the main frame arm includes at least two connecting rod, at least one at least two connecting rod One end of connecting rod is connected with the slave arm.

In certain embodiments, the main frame arm include first connecting rod, be connected with one end of the first connecting rod the 3rd Connecting rod, the slave arm are connected with the end of the third connecting rod.

In certain embodiments, the main frame arm also includes second connecting rod, one end of the second connecting rod and described first One end of one end connection of connecting rod, the other end and third connecting rod connects.In certain embodiments, the second connecting rod and described the One end of one connecting rod is hinged.

In certain embodiments, the third connecting rod is hinged with the second connecting rod.

In certain embodiments, the angle α between the first connecting rod and the second connecting rod is obtuse angle；Described second connects Angle β between bar and the third connecting rod is obtuse angle.

In certain embodiments, the end of the slave arm and the third connecting rod is hinged.

In certain embodiments, the middle part of the slave arm and the end of the third connecting rod are hinged.

In certain embodiments, the loose impediment is unmanned plane.

In order to solve the above technical problems, another technical scheme that the utility model uses is：A kind of unmanned plane is provided, wrapped Include：Fuselage, the horn being connected with the fuselage and the power set on the horn, the horn after folding with it is described The outline fitting of fuselage.

In certain embodiments, the horn is horn as described above.

In certain embodiments, the fuselage corresponds to the horn and is provided with accepting groove, and the horn is contained in after folding In the accepting groove.

In certain embodiments, the horn at least two, each horn include main frame arm and with the master The connected slave arm of horn, the power set are located at the slave arm, and two horns are after folding, respectively positioned at two The power set on the slave arm are directed away from mutual direction and set.

In certain embodiments, the slave arm is additionally provided with undercarriage.

In certain embodiments, the undercarriage is hinged with the slave arm, and at least two horns are after folding, extremely Separated by a distance between few two slave arms, the undercarriage folding storage is between at least two slave arms.

In certain embodiments, it is additionally provided with antenna in the undercarriage.

In certain embodiments, the junction of the horn and the fuselage is provided with position limiting structure.

In certain embodiments, the position limiting structure includes installed part and elastomeric element；The installed part includes main part And rotating shaft, the rotating shaft connects the fuselage and the main part, the horn are sheathed on the rotating shaft, the main part direction The surface of the horn has the first stop part, and the horn has the second stop part towards the surface of the main part；It is described Elastomeric element is sheathed on the rotating shaft, and one end of the elastomeric element abuts with the horn, and the other end supports with the fuselage Connect.

In certain embodiments, the main part towards the surface of the horn be helicoid.

In certain embodiments, the main part towards the surface of the horn include helicoid and with the helicoid phase The Rough Horizontal Plane connect.

In certain embodiments, the Rough Horizontal Plane has the 3rd stop part.

The beneficial effect of the utility model embodiment is：The utility model embodiment provide horn after folding can with can The outline fitting of mobile object so that the structure using the loose impediment of the horn is compacter.When the horn is applied to During unmanned plane, horn is bonded after folding with the outline of fuselage, and foldable structure is simple, and the knot of horn unmanned plane after folding Structure is compacter.

Brief description of the drawings

, below will be in the utility model embodiment in order to illustrate more clearly of the technical scheme of the utility model embodiment The required accompanying drawing used is briefly described.It should be evident that drawings described below is only of the present utility model one A little embodiments, for those of ordinary skill in the art, on the premise of not paying creative work, can also be according to these Accompanying drawing obtains other accompanying drawings.

Fig. 1 is a kind of dimensional structure diagram for unmanned plane that the utility model embodiment provides, and wherein unmanned plane is in Deployed condition；

Fig. 2 is the dimensional structure diagram at another visual angle of unmanned plane described in Fig. 1；

Fig. 3 is the dimensional structure diagram of unmanned plane shown in Fig. 1, and wherein unmanned plane is in folded state；

Fig. 4 is the upward view of unmanned plane shown in Fig. 3；

Fig. 5 is a kind of schematic diagram for position limiting structure that the utility model embodiment provides；

Fig. 6 is the three-dimensional exploded view of position limiting structure shown in Fig. 3；

Fig. 7 is the structural representation of installed part in position limiting structure shown in Fig. 3.

Embodiment

For the ease of understanding the utility model, below in conjunction with the accompanying drawings and specific embodiment, the utility model is carried out more detailed Thin explanation.It should be noted that when element is expressed " being fixed on " another element, it can be directly in another element Above or therebetween there may be one or more elements placed in the middle.When an element is expressed " connection " another element, it can To be directly to another element or there may be one or more elements placed in the middle therebetween.This specification is used Term " vertical ", " horizontal ", the orientation of the instruction such as "left", "right" " top " " bottom " or position relationship be based on accompanying drawing Shown orientation or position relationship, it is for only for ease of description utility model and simplifies description, rather than indicates or imply and be signified Device or element must have specific orientation, with specific azimuth configuration and operation, therefore it is not intended that to this practicality New limitation.

Unless otherwise defined, technology all used in this specification and scientific terminology are with belonging to skill of the present utility model The implication that the technical staff in art field is generally understood that is identical.It is intended merely in term used in the description of the present utility model The purpose of specific embodiment is described, is not intended to limit the utility model.In addition, the utility model disclosed below is each As long as involved technical characteristic does not form conflict can and is mutually combined each other in embodiment.This specification is made Term "and/or" includes the arbitrary and all combination of one or more related Listed Items.

Fig. 1-Fig. 4 is referred to, the unmanned plane 100 includes：Power Component 10, fuselage 20, camera device 30 and undercarriage 40. Wherein, Power Component 10 is installed on fuselage 20, for providing power for unmanned plane 100, and drives unmanned plane 100 to fly and enter The adjustment of row flight attitude.The control circuit component being made up of electronic components such as MCU, control electricity are generally included in fuselage 20 Road component includes multiple control modules, e.g., for controlling the flight control modules of unmanned plane during flying posture, for the unmanned plane that navigates Big dipper module and data processing for handling the environmental information acquired in related airborne equipment (e.g., camera device 30) Module etc..In addition, the rear end of fuselage 20 is also provided with battery compartment, it is above-mentioned control circuit component that the battery compartment, which is used to house, The battery of power supply, battery can be directly out of the insertion of the rear end of fuselage 20 battery compartments.

Camera device 30 is installed on the front end of fuselage 20, for gathering the image information of photographed scene.Undercarriage 40 is installed In Power Component 10, for making unmanned plane 100 smoothly be parked in ground or a plane when unmanned plane 100 lands, branch is played Support acts on.It is, of course, understood that in some other embodiments, camera device 30 and undercarriage 40 can also be installed In other suitable positions, such as：Camera device 30 is installed on the side or lower section of fuselage 20, and undercarriage 40 is installed on fuselage 20 lower section etc., is not especially limited in the utility model embodiment.

Specifically, in the present embodiment, Power Component 10 includes horn 11, is installed on power set on horn 11.Power The drive device 12 that device includes and the propeller (not shown) in drive device 12.The driving of each drive device 12 with Its corresponding propeller rotational, so as to provide power for unmanned plane 100, unmanned plane 100 is driven to fly.

Horn 11 of the present utility model is foldable relative to fuselage 20, and horn 11 pastes after folding with the outline of fuselage 20 Closing, i.e. horn 11 matches after folding at least towards the shape and the outer contour shape of fuselage 20 of that part of fuselage 20, from And cause unmanned plane structure is compacter to easily facilitate carrying.Furthermore, it is to be understood that in actual applications, this practicality is new The application field for the horn 11 that type embodiment provides should not be limited only to unmanned air vehicle technique field.Horn 11 can also be installed on other The loose impediment of type, such as：Unmanned boat, unmanned submarines, robot etc., horn 11 after folding with the loose impediment Outline is bonded, so that compacter using the structure of the loose impediment of the horn 11.

In one of the embodiments, horn 11 includes main frame arm 111 and slave arm 112, one end installation of main frame arm 111 In fuselage 20, the other end is connected with slave arm 112.Power set and undercarriage 40 are mounted on the end of slave arm.Main frame arm 111 can rotate relative to fuselage 20, and when main frame arm 11 rotates relative to fuselage 20, slave arm 112 is under the drive of main frame arm 111 It can also be rotated relative to fuselage 20.For horn 11 after folding, main frame arm 111 and slave arm 112 are close to fuselage 20.In this implementation In example, by setting main frame arm 111 to be rotated relative to fuselage 20, you can realize the folding to horn 11, foldable structure is simple, uses It is convenient；Also, by suitably being designed, such as, make main frame arm 111 and slave arm 112 towards the surface of fuselage 20 and machine The outline of body 20 matches, so that outline of the horn 11 with fuselage 20 after folding is bonded, enables to horn 11 through folding The structure of unmanned plane 100 is compacter afterwards.

In the present embodiment, main frame arm 111 includes the first connecting rod 1111 being hinged with fuselage 20 and the phase of first connecting rod 1111 Second connecting rod 1112 even and the third connecting rod 1113 being connected with second connecting rod 1112.Slave arm 112 is in the middle with the 3rd The end of connecting rod 1113 is connected, and the middle part of slave arm 112 refers to the centre position of the length direction of slave arm 112.Wherein, at this In embodiment, the middle part of slave arm 112 is connected with the end of third connecting rod 1113.When first connecting rod 1111 rotates relative to fuselage 20 When, drive second connecting rod 1112, third connecting rod 1113 and slave arm 112 to be rotated relative to fuselage 20.In addition, in the present embodiment In, the angle α between first connecting rod 1111 and second connecting rod 1112 is obtuse angle, between second connecting rod 1112 and third connecting rod 1113 Angle β be also obtuse angle, so as to which, first connecting rod 1111, second connecting rod 1112 and third connecting rod 1113 form the knot of an arch Structure, in 100 flight of unmanned plane, the domes can lift the intensity of horn 11 so that the horn 11 can bear bigger Pulling force.

Second connecting rod 1112 can be fixedly connected or be hinged with the connected mode of first connecting rod 1111.When When the other end of two connecting rods 1112 and first connecting rod 1111 is be hinged, it can be adjusted when folding horn 11 according to the profile of fuselage 20 The angle of first connecting rod 1111 and second connecting rod 1112 so that the structure after folding is compacter.Similarly, in the present embodiment In, third connecting rod 1113 and the connected mode and slave arm 112 of second connecting rod 1112 and the company of the end of third connecting rod 1113 The mode of connecing can also be fixedly connected or be hinged.When third connecting rod 1113 and second connecting rod 1112, and/or, slave arm 112 with When the end of third connecting rod 1113 is be hinged, the He of second connecting rod 1112 can be adjusted according to the profile of fuselage 20 when folding horn 11 The angle of third connecting rod 1113, and/or, the angle of third connecting rod 1113 and slave arm 112 so that the structure after folding is more It is compact.

Referring to Fig. 2, the present embodiment middle fuselage 20 includes first surface 20a and second table relative with first surface 20a Face 20b, main frame arm 111 are articulated with first surface 20a, i.e. main frame arm 111 is installed in rotation on first surface 20a.Horn 11 after folding, first connecting rod 1111, second connecting rod 1112 and third connecting rod 1113 be close to respectively positioned at first surface 20a and Fuselage side 20c between second surface 20b, slave arm 112 are close to second surface 20b.And in order to be further ensured that horn 11 After folding, horn 11 is more bonded with the outline of fuselage 20, and the position of the corresponding horn 11 of fuselage 20 is additionally provided with accepting groove 21, after folding, horn 11 is contained in the accepting groove 21 horn 11.

It is understood that the structure of horn 11 is not limited to structure described above, if horn 11 after folding with The outline fitting of fuselage 20.Such as if the outline of fuselage 20 is an oblong surface, the shape of horn 11 can To be changed to the arc-shaped to match with the oblong surface.And for example, horn 11 can also be a flexible piece with some strength, when When being folded, can according to the outline of fuselage 20 change horn 11 shape so that horn 11 after folding with fuselage 20 Outline fitting, and after spreading out, because it has certain intensity, drive device 12 can be supported to complete unmanned plane 100 flight.

In the present embodiment, unmanned plane 100 includes two horns 11, and one end of one of horn 11 is installed on fuselage 20 Side, one end of another horn 111 is installed on the opposite side of fuselage 20, and two horns 111 can be upward with respect to fuselage 20 Or rotate down；The middle part connection of the corresponding slave arm 112 of the other end of each main frame arm 111, each slave arm 112 Both ends be used to drive device 12 be installed it is convenient so that the distance of each drive device 12 to main frame arm 111 is equal Directly different flight attitudes is realized by adjusting the rotating speed of each drive device 12.When two main frame arms 111 are with respect to fuselage 20 When being rotated up, two main frame arms 111 and two slave arms 112 are gradually distance from fuselage 20, a certain default when being rotated upwardly into During angle, as shown in figure 1, the drive device 12 for being arranged at the both ends of each slave arm 112 is generally aligned in the same plane, two horns 11 For deployed condition.When two main frame arms 111 rotate down with respect to fuselage 20, two main frame arms 111 and two slave arms 112 are equal Fuselage 20 is moved closer to, until two main frame arms 111 are close to the two opposite sides of fuselage 20 respectively, two slave arms 112 are close to In the lower surface of fuselage 20, as shown in figure 3, two horns 11 are folded state.

Fig. 3 and Fig. 4 are referred to, in the present embodiment, two horns 11 are after folding, respectively on slave arm 112 Power set are directed away from mutual direction and set.That is, for two horns 11 after folding, power set are provided with that of propeller One end is set away from one another.

In addition, in the present embodiment, undercarriage 40 is additionally provided with slave arm 112.Wherein, in order to make full use of unmanned plane 100 space, can also be by for realizing that unmanned plane 100 and the antenna of the communication connection of other equipment are arranged at the undercarriage 40 It is interior.The antenna can be or can be including compass, WIFI communication antennas, LTE antenna or gps receiver etc..Wherein, in order that Overall structure of the unmanned plane 100 after folding is compacter, undercarriage 40 and slave arm 112 are be hinged, and undercarriage 40 can be Rotated in the presence of external force relative to slave arm 112, two horns 11 are separated by a spacing after folding between two slave arms 112 From the folding storage of undercarriage 40 is between two slave arms 112.

When folding unmanned plane 100, two undercarriages 40 can be rotated first towards close to the direction of main frame arm 111, made It is parallel to obtain the corresponding slave arm 112 of two undercarriages 40, then rotates main frame arm 111 so that main frame arm 111 drives slave Arm 112, drive device 12 and undercarriage 40 rotate down with respect to fuselage 20, until main frame arm 111 is close to fuselage side 20c, with And slave arm 112 is close to second surface 20b, now, two folding storages of undercarriage 40 between two slave arms 112, so as to So that whole unmanned plane 100, after folding, structure becomes closely, to be easy to carry, meanwhile, the foldable structure is simple, convenient Use.

When deploying unmanned plane 100, main frame arm 111 can be rotated first so that main frame arm 111 drives slave arm 112, driven Dynamic device 12 and undercarriage 40 are rotated up with respect to fuselage 20, until one end of main frame arm 111 supports main frame arm 111 and fuselage 20 The position limiting structure of junction；Then undercarriage 40 is rotated so that the angle between undercarriage 40 and slave arm 112 is in 90 °.

It is, of course, understood that in some other embodiments, unmanned plane 100 can also include four undercarriages 40, two of which undercarriage 40 is installed on the both ends of one of slave arm 112, and it is secondary that another two undercarriage 40 is installed on another The both ends of horn 112.In this embodiment, it is that unmanned plane 100 provides stable support by four undercarriages 40, machine can be avoided Body 20 contacts with supporting surface, reduces the abrasion of fuselage 20.

Please continue to refer to Fig. 2, in the present embodiment, one end of fuselage 20 is provided with rubber blanket 22, and the rubber blanket 22 can be with The bottom (as shown in Figure 2) of one end of fuselage 20 is arranged at, the side of one end of fuselage can also be arranged at, for for unmanned plane 100 provide support.Wherein, the quantity of the rubber blanket 22 can be 1,2,3,5 etc., not make to have in the present embodiment Body limits.When unmanned plane 100 is in deployed condition, two undercarriages 40 form stable support with rubber blanket 22, are jointly Unmanned plane 100 provides the stable/landing platform that takes off.When unmanned plane 100 is in folded state, undercarriage 40 is towards close to main The direction of horn 111 rotates, until it is parallel with slave arm 112.In the present embodiment, two undercarriages 40 and rubber blanket are passed through 22 be that unmanned plane 100 provides stable support, can reduce the quantity of undercarriage 40 so that the structure of unmanned plane 100 is more stepped up Gather, be convenient for carrying.

It is understood that in the present embodiment, include two horns 11 with power set 10, exemplified by the utility model Embodiment illustrates, but in some other embodiments, power set 10 can also include more or lesser amount of Horn 11.

It is understood that in the present embodiment, each horn 11 includes a main frame arm 111 and a slave arm 112. In some other embodiments, each horn 11 can also include greater number of main frame arm 111 and/or slave arm 112.

For example in certain embodiments, each horn 11 can include at least two main frame arms 111 and a slave arm 112, at least two main frames arm 111 is set in parallel in the side of fuselage 20 and is connected with a slave arm 112.Usually, when , it is necessary to adjust the rotating speed of the drive device 12 at the both ends of slave arm 112 to produce when unmanned plane 100 needs to carry out the adjustment of flight attitude Raw different size of pulling force；And when pulling force caused by the drive device 12 at the both ends of slave arm 112 is in different size, can be to main frame Arm 111 produces a twisting resistance；In the presence of the twisting resistance, main frame arm 111 easily produces certain elastic deformation, so as to, On the one hand, unmanned plane 100 is not flown accurately and in time with predetermined flight attitude, influence the control essence of unmanned plane 100 Degree, on the other hand, main frame arm 111 by twisting resistance easily because being shortened the service life of horn 11 for a long time.And in the embodiment In, horn 11 includes at least two main frame arms 111, can reduce each master when carrying out the adjustment of flight attitude of unmanned plane 100 The twisting resistance that horn 111 is born, the elastic deformation of main frame arm 111 is reduced, so as to lift the control accuracy of unmanned plane 100 and prolong The service life of long horn 11.

The steadiness of horn 11 when wherein, in the present embodiment, in order to be lifted at 100 flight of unmanned plane, horn 11 and machine The junction of body 20 is provided with position limiting structure, in 100 flight of unmanned plane, the angle between horn 11 and fuselage 20 to be limited Due to a certain predetermined angle, avoid horn 11 because of the gravity of itself and rotated down with respect to fuselage 20, or, because by by spiral Pulling force caused by oar rotation and relative fuselage 20 is rotated up, influence the normal flight of unmanned plane 100.The position limiting structure can be Any appropriate limiting component, such as：Springlock etc. or a folder that can be adjusted in real time between horn 11 and fuselage 20 The control device at angle, the control device include driver element, by controlling the driver element, can control horn 11 with respect to machine Body 20 rotates and the angle between horn 11 and fuselage 20 is fixed on into a certain predetermined angle according to use state.

Especially, in order to reduce the weight of unmanned plane 100 and production cost, the position limiting structure can also be such as Fig. 5 or Position limiting structure 50 shown in Fig. 6.The position limiting structure 50 is arranged at the junction of fuselage 20 and horn 11, including：The He of installed part 51 Elastomeric element 52.Wherein, installed part 51 includes main part 511 and rotating shaft 512, and rotating shaft 512 connects fuselage 20 and main part 511, Horn 11 is sheathed on rotating shaft 512；Main part 511 has the first stop part 511a towards the surface of horn 11, and horn 11 is towards master The surface in body portion 511 has the second stop part 111a；Elastomeric element 52 is sheathed on rotating shaft 512, and one end of elastomeric element 52 with Horn 11 abuts, and the other end abuts with fuselage 20.

Thus, when user deploys horn 11, horn 11 is because by upward external force, relative fuselage 20 is rotated up, directly The second stop part 111a to horn 11 is held in the first stop part 511a.In the state of the expansion of horn 11, on the one hand, horn 11 by its frictional force between main part 511 due to being overcome the gravity of its own, so that will not be downward with respect to fuselage 20 Rotate；On the other hand, when drive device 12 drives propeller rotation and when producing upward pulling force to horn 11, horn 11 due to Its pulling force being subject to also is offset to its downward pressure by the first stop part 511a, so as to turn upwards with respect to fuselage 20 It is dynamic.When user folds horn 11, the second stop part 111a of horn 11 is due to by downward external force and along main part 5111 rotate down (i.e. towards the surface of horn 11 with respect to fuselage 20：Rotated away from the first stop part 5111a direction), Until horn 11 is bonded with the outline of fuselage 20.

Specifically, in certain embodiments, main part 5111 towards the surface of horn 11 be helicoid, the two of the helicoid Edge forms a difference in height on the axis direction perpendicular to rotating shaft 512, and the barrier formed by the difference in height forms first Stop part 511a.In this embodiment, due to main part 511 towards the surface of horn 11 be helicoid, therefore, when second stop Portion 111a be directed away from the first stop part 5111a direction rotate when, horn 11 on the axis direction perpendicular to rotating shaft 512 not Break close to fuselage 20 and extrude elastomeric element 52, so as to, under the reaction force of elastomeric element 52, horn 11 and main part Frictional force between 511 gradually increases, and then horn 11 will not be rocked arbitrarily after folding, the unmanned plane 100 after folding Structure is compacter.

Or in further embodiments, as shown in fig. 7, main part 511 includes a helicoid towards the surface of horn 11 5111 and a Rough Horizontal Plane 5112, an edge of the helicoid 5111 and a side edge of the Rough Horizontal Plane 5112, the spiral The other edge in face 5111 and the other edge of the Rough Horizontal Plane 5112 form a difference in height on the axis direction of rotating shaft 512, The barrier formed by the difference in height forms the first stop part 511a.In this embodiment, by setting the direction of main part 511 The surface of horn 11 is the combination of a helicoid 5111 and a Rough Horizontal Plane 5112, can further enhance machine after horn 11 folds Frictional force between arm 11 and main part 511, lift compactedness of the horn 11 through folded configuration.Meanwhile when user is by second Stop part 111a (horn 11) from Rough Horizontal Plane 5112 slide into helicoid 5111 to deploy horn 11 when, can stop to horn 11 forces, only in the presence of surplus energy, you can horn 11 is turned into deployed condition, and (i.e. the second stop part 111a is held in first Stop part 511a).

In addition, it is excessive in order to avoid rotating the angle of horn 11 when user folds horn 11, and cause the second stop part 111a slide rails, the 3rd stop part 511b further can also be set on Rough Horizontal Plane 5112.

It should be noted that preferably implementation of the present utility model is given in specification of the present utility model and its accompanying drawing Example, still, the utility model can be realized by many different forms, however it is not limited to the implementation described by this specification Example, these embodiments are not as the extra limitation to the utility model content, there is provided the purpose of these embodiments is made to this reality With the understanding more thorough and comprehensive of new disclosure.Also, above-mentioned each technical characteristic continues to be mutually combined, formed not upper The various embodiments that face is enumerated, it is accordingly to be regarded as the scope of the utility model specification record；Further, to ordinary skill For personnel, it can according to the above description be improved or be converted, and all these modifications and variations should all belong to this practicality newly The protection domain of type appended claims.

Claims (23)

1. a kind of horn (11), is installed on loose impediment, it is characterised in that the horn (11) after folding with it is described removable The outline fitting of animal body.

2. horn (11) according to claim 1, it is characterised in that the horn include main frame arm (111) and with it is described The connected slave arm (112) of main frame arm (111).

3. horn (11) according to claim 2, it is characterised in that the main frame arm (111) includes at least two connecting rod, One end of at least one connecting rod at least two connecting rod is connected with the slave arm (112).

4. horn (11) according to claim 3, it is characterised in that the main frame arm (111) includes first connecting rod (1111), the third connecting rod (1113) being connected with one end of the first connecting rod (1111), the slave arm (112) and described the The end of three connecting rods (1113) is connected.

5. horn (11) according to claim 4, it is characterised in that the main frame arm (111) also includes second connecting rod (1112), one end of the second connecting rod (1112) is connected with one end of the first connecting rod (1111), and the other end and the 3rd connects One end connection of bar (1113).

6. horn (11) according to claim 5, it is characterised in that the second connecting rod (1112) and the first connecting rod (1111) one end is hinged.

7. horn (11) according to claim 5, it is characterised in that the third connecting rod (1113) and the second connecting rod (1112) it is hinged.

8. the horn (11) according to claim any one of 5-7, it is characterised in that the first connecting rod (1111) and described Angle α between second connecting rod (1112) is obtuse angle；Between the second connecting rod (1112) and the third connecting rod (1113) Angle β is obtuse angle.

9. the horn (11) according to claim any one of 4-6, it is characterised in that the slave arm (112) and described the The end of three connecting rods (1113) is hinged.

10. horn (11) according to claim 9, it is characterised in that the middle part and the described 3rd of the slave arm (112) The end of connecting rod (1113) is hinged.

11. the horn (11) according to claim any one of 1-7, it is characterised in that the loose impediment is unmanned plane.

A kind of 12. unmanned plane (100), it is characterised in that the horn (11) that is connected including fuselage (20), with the fuselage (20) and Power set located at the horn (11), outline of the horn (11) with the fuselage (20) after folding are bonded.

13. unmanned plane (100) according to claim 12, it is characterised in that the horn (11) is such as claim 1- Horn any one of 10.

14. unmanned plane (100) according to claim 12, it is characterised in that the corresponding horn of the fuselage (20) (11) accepting groove (21) is provided with, the horn (11) is contained in after folding in the accepting groove (21).

15. unmanned plane (100) according to claim 12, it is characterised in that the horn (11) at least two is each The horn (11) includes main frame arm (111) and the slave arm (112) being connected with the main frame arm (111), the power dress Put (12) and be located at the slave arm (112), two horns (11) are after folding, respectively positioned at two slave arms (112) power set on are directed away from mutual direction and set.

16. unmanned plane (100) according to claim 15, it is characterised in that the slave arm (112) is additionally provided with undercarriage (40)。

17. unmanned plane (100) according to claim 16, it is characterised in that the undercarriage (40) and the slave arm (112) it is hinged, at least two horns (11) are separated by a spacing after folding between at least two slave arms (112) From undercarriage (40) folding storage is between at least two slave arms (112).

18. unmanned plane (100) according to claim 16, it is characterised in that be additionally provided with antenna in the undercarriage (40).

19. the unmanned plane (100) according to claim any one of 12-18, it is characterised in that the horn (11) and described The junction of fuselage (20) is provided with position limiting structure (50).

20. unmanned plane (100) according to claim 19, it is characterised in that the position limiting structure (50) includes installed part And elastomeric element (52) (51)；

The installed part (51) includes main part (511) and rotating shaft (512), the rotating shaft (512) connect the fuselage (20) and The main part (511), the horn (11) are sheathed on the rotating shaft (512), and the main part (511) is towards the horn (11) surface has the first stop part (511a), and the horn (11) has second towards the surface of the main part (511) Stop part (111a)；The elastomeric element (52) is sheathed on the rotating shaft (512), and one end of the elastomeric element (52) and institute Horn (11) abutting is stated, the other end abuts with the fuselage (20).

21. unmanned plane (100) according to claim 20, it is characterised in that the main part (511) is towards the horn (11) surface is helicoid.

22. unmanned plane (100) according to claim 20, it is characterised in that the main part (511) is towards the horn (11) surface includes helicoid (5111) and the Rough Horizontal Plane (5112) to connect with the helicoid (5111).

23. unmanned plane (100) according to claim 22, it is characterised in that the Rough Horizontal Plane (5112) has the 3rd Stop part (511b).