CN207009672U

CN207009672U - The antenna structure and aircraft of angle adjustable

Info

Publication number: CN207009672U
Application number: CN201720998155.8U
Authority: CN
Inventors: 朱海波
Original assignee: Yuneec International Co Ltd
Current assignee: Yuneec International Co Ltd
Priority date: 2017-08-10
Filing date: 2017-08-10
Publication date: 2018-02-13
Anticipated expiration: 2027-08-10

Abstract

The utility model discloses a kind of antenna structure of angle adjustable and aircraft, the antenna structure includes：Antenna, antenna holder, and channel components, wherein, the antenna is fixed on the antenna holder, also, the antenna holder, by the channel components, adjustable angle, which saves land, is arranged on the tail position of the aircraft.The performance of antenna transmitting of the present utility model and reception signal significantly improves.And simple in construction, easily fabricated, manufacturing cost is low.

Description

The antenna structure and aircraft of angle adjustable

Technical field

It the utility model is related to vehicle technology field, and in particular to the antenna technical field of aircraft.

Background technology

In recent years, growing and ripe with vehicle technology, the application field of aircraft is more and more extensive, therewith And come, it is that user puts forward higher and higher requirement to the performance of aircraft.

For example, antenna is as aircraft and the critical elements of extraneous radio communication, it is desirable to which it is launched and the energy of reception signal Power is sufficiently stable.

But the limitation due to aircraft on volume and weight limits the design of antenna, aircraft day have impact on The signal transmitting of line and receive capabilities.

In summary, there is an urgent need to a kind of aircraft day knot with the transmitting of more preferable signal and receive capabilities for this area Structure.

The content of the invention

The purpose of this utility model is just to provide a kind of aircraft antenna structure, it is possible to increase the signal of antenna occurs and connect Receive function.

In one side of the present utility model, there is provided a kind of antenna structure of angle adjustable, for aircraft, bag Contain：

Antenna holder,

The antenna being arranged on the antenna holder,

The channel components being arranged on the fuselage of the aircraft, wherein

The antenna holder adjustable angle, which saves land, to be buckled in the channel components.

Preferably, engage on the antenna holder comprising at least one multi-angle engaging groove, the multi-angle on groove Runing rest axle is provided with, and

The channel components include the runing rest axle mounting groove that position and size match with the runing rest axle, and And

The antenna holder is rotatably installed in the runing rest axle mounting groove by the runing rest axle.

Preferably, the multi-angle engaging groove also includes the first pin and the second pin, and

The channel components also match comprising the position and size respectively with first pin and second pin Main body be fixed groove and folding angles stopper slot.

Preferably, first pin can be with the main body card along the groove formed with the inner side edge of second pin Fixed groove and folding angles stopper slot is closed with least two different angle to engage.

Preferably, the inner side edge of first pin and second pin along upper comprising the corresponding kink of at least two, So that first pin and second pin can be fixed with the main body groove with folding angles stopper slot so that Few 2 different angles engaging.

Preferably, the antenna is chip aerial.

Preferably, antenna slot is provided with the antenna holder, for housing the antenna.

Preferably, the channel components are arranged on the tail position of the fuselage of the aircraft.

Preferably, engage groove comprising 2 multi-angles on the antenna holder, set respectively on the multi-angle engaging groove Runing rest axle is equipped with, and

The channel components include position and size and installed with 2 runing rest axles that the runing rest axle matches Groove.

Second aspect of the present utility model provides a kind of aircraft, and this aircraft includes day described above Cable architecture.

The utility model embodiment compared with prior art, at least with following difference and effect：

1. antenna is launched and the performance of reception signal significantly improves.

2. simple in construction, easily fabricated, manufacturing cost is low.

It should be understood that in the scope of the utility model, above-mentioned each technical characteristic of the present utility model and below (such as implementation Example) in specifically describe each technical characteristic between can be combined with each other, so as to form new or preferable technical scheme.It is limited to Length, no longer tire out one by one state herein.

Brief description of the drawings

Fig. 1 is the aircraft flight posture and structural representation according to one embodiment of the present utility model；

Fig. 2 is the landing stationary posture schematic diagram that takes off according to one embodiment of the present utility model；

Fig. 3 is the flight attitude schematic diagram according to the aircraft of one embodiment of the present utility model；

Fig. 4 is the landing stationary posture schematic diagram that takes off according to the aircraft of one embodiment of the present utility model；

Fig. 5 is the critical piece schematic diagram according to the aircraft of one embodiment of the present utility model；

Fig. 6 is the critical piece schematic diagram according to the aircraft of one embodiment of the present utility model；

Fig. 7 is the assembling schematic diagram according to the aircraft of one embodiment of the present utility model；

Fig. 8 is vertical heat emission hole structural representation in the prior art；

Fig. 9 is the line style heat emission hole of angular flux windward according to the aircraft of one embodiment of the present utility model；

Figure 10 is air flow and vertical heat emission hole schematic diagram in the prior art；

Figure 11 is the line style of the angular flux windward heat emission hole and air stream of the aircraft according to one embodiment of the present utility model To schematic diagram；

Figure 12 is the empennage antenna decomposing schematic representation according to the aircraft of one embodiment of the present utility model；

Figure 13 is schematic diagram under the empennage antenna folds state according to the aircraft of one embodiment of the present utility model；

Figure 14 is to reset schematic diagram according to the empennage antenna of the aircraft of one embodiment of the present utility model；

Figure 15 is the empennage antenna structure view according to the aircraft of one embodiment of the present utility model；

Figure 16 is the empennage antenna element schematic diagram according to the aircraft of one embodiment of the present utility model；

Figure 17 is the empennage antenna folds view according to the aircraft of one embodiment of the present utility model；

Figure 18 is the empennage antenna folds view according to the aircraft of one embodiment of the present utility model；

Figure 19 is the empennage antenna folds view according to the aircraft of one embodiment of the present utility model；

Figure 20 is to be knocked preceding view according to the empennage antenna of the aircraft of one embodiment of the present utility model；

Figure 21 is to be knocked rear view according to the empennage antenna of the aircraft of one embodiment of the present utility model；

Figure 22 is the critical piece schematic diagram according to the aircraft of one embodiment of the present utility model；

Figure 23 is the scheme of installation according to the camera lens of the aircraft of one embodiment of the present utility model；

Figure 24 is the position view according to the camera lens of the aircraft of one embodiment of the present utility model；

Figure 25 is the critical piece schematic diagram according to the camera lens of the aircraft of one embodiment of the present utility model.

In all of the figs, identical reference is used for representing identical element or structure, wherein：

1：Fuselage

2：Horn

3：Propeller component

4：Propeller protects component

5：Blade

6：Motor cover

7：Linking arm

8：Link

9：Kink

101：Intermediate radiator part

102：Side thermal component

103：Advance air port

104：Bracing piece

105：Impeller

106：Side air inlet

107：Middle air inlet

11：Chip aerial

12：Antenna holder

13：Antenna slot

14：Multi-angle engages groove

15：First pin

16：Second pin

17：Runing rest axle

18：Folding angles stopper slot

19：Runing rest axle mounting groove

21：Main body is fixed groove

22：Channel components

51：Image plate

52：Master control borad

53：Battery

54：Video camera

61：Frame

611：Frame main body

62：Upper lid

63：Rotational positioning axle

64：Support member

Embodiment

In the following description, in order that reader more fully understands the application and proposes many ins and outs.But this Even if the those of ordinary skill in field is appreciated that without these ins and outs and many variations based on following embodiment And modification, each claim of the application technical scheme claimed can also be realized.In addition, this practicality disclosed below As long as involved technical characteristic does not form conflict can and is mutually combined each other in new each embodiment.

Term

As used herein, term " aircraft " refers to the flight equipment such as unmanned plane.

As used herein, term " motor cover " refers to the part of the drive device for housing aircraft propeller.

As used herein, term " arch " refers to a kind of shape, and centre has a kink to concave, and both ends are to kink Same lateral bend, in " bow " font.

As used herein, term " air inlet " refers to the opening opened up on the fuselage of aircraft, for introducing air-flow.

As used herein, the thin slice of term " impeller " fingerboard shape, the direction entered along air-flow, is arranged on air inlet.

As used herein, term " multi-angle engaging groove " refers to fix with being used for at least two different angle Mounting groove and/or the groove structure that fastens of groove.

As used herein, term " runing rest axle " refers to the support shaft for being rotatably fixed.

As used herein, term " folding angles stopper slot ", which refers to, engages matching grooves with multi-angle, and can be down to Few two or more different angle engages the groove of groove fixation with the multi-angle.

As used herein, term " rotational positioning axle " refers to the locating shaft being rotationally fixed.

As used herein, term " damping gear " refers to realizes the gear of slowing effect by increasing frictional resistance.

As used herein, term " channel components " refers to the part being made up of multiple grooves, and the part is used for fixed antenna branch Frame.

As used herein, term " multi-angle engaging groove " refers to the slot parts being made up of multiple pins, and multiple slotting Engaging groove, position and the size and the groove match in above-mentioned channel components of pin are formed between pin.

1. the rack construction of aircraft

The present inventor is by in-depth study extensively, it is proposed that a kind of new rack construction.Referring to the drawings, this frame Structure is mainly comprising frame main body, horn, propeller component and propeller protection component.Wherein, frame main body and horn One end connects；The propeller component other end with horn, and propeller protection component connection respectively.Also, propeller is protected Component is used not only for protecting propeller component, and is additionally operable to as undercarriage.

More specifically, propeller component, which further includes, is used to housing the motor cover of motor, motor cover respectively with horn The other end, and propeller protection component connection.The height of motor cover is set must be so that when aircraft be risen and fallen with reverse side, electricity Hood can support fuselage as undercarriage.

More specifically, propeller protection component includes multiple linking arms and multiple links, wherein, each linking arm One end is connected with motor cover, and the other end connects in link.Propeller component includes blade, also, each linking arm with even The one end for connecing frame connection extends downwardly, and is connected with link, so as to be configured to protect the accommodation space of blade.

According to above-mentioned rack construction, the guard space to propeller component, especially blade is not only constituted, and simultaneously Constitute and facilitate the front-back two-sided supporting construction risen and fallen, further, this structure both simply has convenient manufacture.

It is described in detail with reference to the accompanying drawings further below.

As shown in Fig. 1, Fig. 6 and Figure 12, the rack construction of the aircraft of the present embodiment includes：Fuselage 1, horn 2, bottom The propeller component 3 of blade 5, and propeller protection component 4 are provided with, wherein, one end connection fuselage 1 of horn 2, the other end Connect propeller component 3；Also, propeller protection component 4 is used to protect blade 5；And it is additionally operable to as undercarriage, such as Fig. 2 It is shown.

More specifically, can as illustrated, propeller protection component 4 forms three-dimensional guard space in the outside of blade 5 Blocking object produces shock from the outside of blade 5 to blade, meanwhile, the bottom of propeller protection component 4 can smoothly support Aircraft, realize the effect of undercarriage.So, be advantageous to mitigate overall volume reduction, overall weight, and structure letter Single, easily fabricated, overall manufacturing cost is relatively low.

In the present embodiment, rack construction includes 4 propeller components 3, is separately positioned on the head on both sides and tail of fuselage 1 Portion both sides, are symmetrical set, and in other words, 4 propeller components 3 are symmetricly set on the front-end and back-end of the both sides of fuselage 1.But The present embodiment not limited to this, in other embodiments, rack construction can include the propeller component 3 of varying number, for example, can To set 3, or 4 propeller components, etc. in every side of fuselage.

In the present embodiment, propeller component 3 also includes the motor cover 6 on the top for being arranged on blade 5, the height of motor cover 6 Height of the degree more than fuselage 1 so that when aircraft is risen and fallen with reverse side, motor cover 6 is used as undercarriage, can support fuselage (such as Shown in Fig. 3, Fig. 4).Further say, can be due to a variety of causes such as decrease speed, wind speed, interference when aircraft carries out flight Posture can not be adjusted in time before ground is dropped to, in this case, the motor cover 6 of the aircraft in the present embodiment can be with The undercarriage of reverse side is provided for aircraft, can smoothly support the aircraft in topsy-turvydom to drop to ground, meanwhile, The aircraft takeoff under this state can be supported.It is this to support the front-back two-sided structure risen and fallen to make aircraft with more flexible Flight performance, can also provide more preferable protection to rising and falling for aircraft, and simple in construction, easily fabricated, overall manufacture Cost is relatively low.

In the present embodiment, propeller protection component 4 includes 8 linking arms 7 and 2 links 8, and link 8 distinguishes position In the both sides of fuselage 1, one end of each linking arm 7 connects a motor cover 6, other end connection link 8.More specifically, As illustrated, each motor cover 6 is connected with 2 linking arms 7 respectively, also, the connection of each link 8 is same positioned at fuselage 1 All linking arms 7 on side, the protection knot to all blades 5 of side is formed so as to all linking arms 7 with the side of fuselage 1 Structure.As can be seen here, from the point of view of any side of fuselage 1, one end of each linking arm 7 is connected with motor cover 6, the other end and company Frame 8 is connect to connect, and linking arm 7 extends downwardly in one end close to link 8, thus, all companies of every side of fuselage 1 Connect the link 8 on arm 7 and the side and constitute protection structure to all blades 5, the protection structure have higher fastness and Impact resistance.In this case, in flight course, its blade can be protected preferably aircraft, hinder outside Shock of the object to blade, improves flight safety.Meanwhile it also ensure that aircraft in carrying process to the guarantor of blade Shield.This is advantageous to while necessary blade protection is provided, reduce volume, mitigate weight, and simple in construction, manufacturing cost It is relatively low.

As above, in the present embodiment, one end being connected with link 8 of each linking arm 7 extends downwardly, with link 8 Connection, so as to be configured to protect the accommodation space of blade 5.Specifically, each linking arm 7 is in bent, can be right angle Bent, but the utility model not limited to this, in other embodiments, each linking arm 7 can also be 120 ° of bendings, or 130 ° of bendings, bending angle do not limit specifically, as long as each linking arm 7 can be connected with motor cover 6 and link 8 Afterwards, the accommodation space of blade 5 can be protected by being formed.

In the present embodiment, as illustrated, link 8 has the shape of bending, arched structure.Specifically, connect The both ends of frame 8 are bent towards fuselage 1, are so advantageous to protect blade 5, are made the front of blade 5 in the protection domain of link 8, Exterior object is avoided from frontal crash blade 5.Yet further say, as illustrated, there is kink 9 middle part of link 8, Kink 9 is towards the side indent of fuselage 1, thus, from the point of view of any side of fuselage 1, all linking arms 7 that 1 motor cover 6 is connected Positioned at the side of the kink 9, all linking arms 7 that another motor cover 6 is connected are located at the opposite side of the kink 9, this Sample is advantageous to strengthen the intensity and impact resistance of whole propeller protection component 4.Improve the protective capability to blade 5.But this Utility model not limited to this, in other embodiments, link 8 can also be other shapes, for example, link 8 can be W Shape or S-shaped or linear pattern, or link can be both ends towards fuselage direction bending, etc..Also, link 8 can also There are multiple kinks 9, link 8 is divided for multistage, there are multiple motor covers 6 per side corresponding to fuselage 1.This In the case of, the linking arm being connected with same motor cover 6 can be connected with same section of link 8.

In the present embodiment, each motor cover 6 is connected with 2 linking arms 7 respectively.2 companies being connected with each motor cover 6 It is any angle between 30 ° to 150 ° to connect the angular range between arm, such as 75-90 °, it is still further preferred that 75 °, in this case Force resolution effect is best.But the utility model not limited to this, in other embodiments, motor cover 6 can respectively with 1,3 Or more linking arm 7 connect, also, the angle between adjacent linking arm 7 can be any angle between 15-45 °, preferably Between ground is 30-35 °, it is still further preferred that 30 °, force resolution effect is best in this case.Each motor cover 6 connects 1 connection The advantages of arm 7, is simple in construction, reduction weight.The advantages of each motor cover 6 connects 3 or more linking arm 7 is intensity It is higher, there is more preferable impact resistance.

In the present embodiment, fuselage 1, horn 2, propeller protection component 4 are formed in one and are made, and so make simply, Manufacturing cost is low.But the utility model not limited to this, in other embodiments, the side such as buckle, screw and screw can also be passed through Formula connects all parts.

The major advantage of the rack construction of above-mentioned aircraft includes：

1. it can adapt to different flight attitudes, there is provided a variety of lifting support postures, realize front-back two-sided rise and fall.

2. effectively protection propeller component, especially paddle blade structure, has higher impact resistance and security.

It is 3. small volume, in light weight.

It is 4. simple in construction, easily fabricated, manufacturing cost is low.

In summary, the rack construction of above-mentioned aircraft has very wide application prospect in aircraft field.

2. high efficiency and heat radiation hole is designed

The present inventor is by in-depth study extensively, it is proposed that a kind of new radiating pore structure, in the structure shown here, in machine The upper surface of body, that is, the both sides of upper lid set the side thermal component of form fit, set intermediate radiator portion in middle part Part, and the impeller being arranged in order is provided with the air inlet of above-mentioned thermal component, it is low after height before the direction of impeller, relative to The angle of horizontal direction progressively reduces from the head of fuselage to empennage direction, and is fixed by bracing piece.Further, frame knot Structure is also comprising the advance air port for being arranged on upper surface, positioned at the front end of intermediate radiator part.According to this structure, by improved The angle that air inlet and impeller structure are formed, efficiently utilizes air-flow general and its heat is fully taken out of, extends flight to reach Device service life, avoid organism temperature too high, burn out the risk of chip or parts.By above-mentioned thermal component, effectively realize The uniformly and effectively radiating of aircraft.

It is described in detail further below.

Such as Figure 11, shown in Figure 12, in the present embodiment, the rack construction of aircraft includes：Fuselage 1, horn 2, propeller Component 3, one end of horn 2 are connected with fuselage 1, and the other end is connected with propeller component 3, also, the upper surface of fuselage 1, also It is that the both sides of upper lid 62 are provided with side thermal component 102.In the present embodiment, the surface of fuselage 1 is provided with side thermal component 102, effective radiating of the heat generating components of the both sides contributed in fuselage.

In the present embodiment, side thermal component 102 includes the side air inlet for the strip that shape matches of being leaned to one side with fuselage 1 106th, impeller 105, wherein, as shown in Fig. 9, Figure 11, impeller 105 is obliquely arranged in side air inlet 106 with being arranged in order, and And the incline direction of impeller 105 is set must make aircraft in flight, air-flow being capable of approaching side air inlet 106.In such case Under, side air inlet 106 can farthest coordinate the shape of the both sides of fuselage 1, there is provided more effective air flow inlet, also, leaf Plate 105 is arranged in order, and is tilted, and makes aircraft in flight, the direction and the incline direction phase one of impeller 105 that air-flow enters Cause, both reduced the air drag that aircraft runs into flight course, and can enter more wind in direction windward again, improve Radiating efficiency.By contrast, such as Fig. 8, shown in Figure 10, conventional heat emission hole of the prior art is vertical heat emission hole, it is impossible to effectively Body heat is discharged, the flight of aircraft long term high temperature, service life can be caused shorter, and easily burns out chip or parts, Potential safety hazard be present, and maintenance cost is higher.

Further say, in the present embodiment, impeller 105 is along aircraft direction of advance, in incline direction low after preceding height Set, wherein, before the head position of fuselage 1 is, after the tail position of fuselage 1 is.

In the present embodiment, impeller 105 progressively subtracts relative to the angle of horizontal direction from the head of fuselage 1 to empennage direction It is small.In other words, impeller 105 compares " vertical " in the head position close to fuselage 1, then gradually " flat along the backward directions of fuselage 1 Lie ", this is advantageous to air-flow approaching side air inlet 106 in aircraft flight, and can preferably reduce air drag.But this reality With new not limited to this, in other embodiments, impeller 105 can also be a steady state value relative to the angle of horizontal direction, I.e. each impeller 105 is parallel to each other, or, impeller 105 can also use different folders in the diverse location of side air inlet 106 Angle.

In the present embodiment, side thermal component 102 is also fixedly installed on the bracing piece in side air inlet 106 comprising both ends 104, bracing piece 104 passes through each impeller 105.Impeller 105 can more be securely disposed at side air intake by bracing piece 104 In mouth 106, and larger stream pressure can be kept out.In the present embodiment, 1 bracing piece is provided with side air inlet 106 104, but the utility model not limited to this, in other embodiments, 2 or more bracing pieces 104 can also be set.

In the present embodiment, the rack construction of aircraft is also comprising the upper surface for being arranged on aircraft, that is, upper lid 62 Centre position intermediate radiator part 101, intermediate radiator part 101 include middle air inlet 107, impeller 105, impeller 105 Obliquely be arranged at being arranged in order in middle air inlet 107, and the incline direction of impeller 105 set must make aircraft fly During row, air-flow can enter middle air inlet 107.Thus, be advantageous to more effectively using the air-flow run into aircraft flight, The heat generating components in the centre position to being arranged on aircraft interior radiates.Coordinate the side thermal component 102 of above-mentioned both sides, it is right The radiating effect of the heat generating components of the overall each position of aircraft is more perfect.

In the present embodiment, intermediate radiator part 101 is also fixedly installed on the reinforcement in middle air inlet 107 comprising both ends Bar 104, bracing piece 104 pass through each impeller 105.Impeller 105 can more be securely disposed at centre by bracing piece 104 In air inlet 107, and larger stream pressure can be kept out.In the present embodiment, 1 is provided with middle air inlet 107 Bracing piece 104, but the utility model not limited to this, in other embodiments, 2 or more bracing pieces can also be set 104。

In the present embodiment, the rack construction of aircraft also includes the advance air port 103 for the upper surface for being arranged on fuselage 1, Advance air port 103 is located at the front end of intermediate radiator part 101, both, near the position on the head of fuselage 1.Advance air port 103 Opening direction set and must make aircraft in flight, air-flow can enter advance air port 103.More specifically, in fuselage 1 The local complexity plate of the centre on the head of close fuselage 1 of upper surface makes the local complexity plate be produced with upper surface slightly towards lower extension One opening, the opening direction is just consistent with the direction of advance of aircraft, enters so as to supply stream.Advance air port 103 Set, can with above-mentioned side thermal component 102, and intermediate radiator part 101 provide jointly integration, more effectively dissipate Hot property, the heat generating components in aircraft fuselage 1 is set uniformly to be radiated.

The major advantage of above-mentioned radiating pore structure includes：

1. provide more preferable heat dispersion.

2. strengthen the performance and flight safety of aircraft.

3. simple in construction, easily fabricated, manufacturing cost is low.

In summary, radiating pore structure provided by the utility model has very wide application prospect in aircraft field.

3. adjustable-angle antenna

The present inventor is by in-depth study extensively, it is proposed that a kind of new angle adjustable antenna structure.By Aircraft empennage position sets the antenna holder and channel components being mutually matched, and sets inner side edge edge to have on antenna holder The pin of multiple kinks, pin is inserted and secured on different angle in the channel components on empennage position, enter one Step ground, also provide another by runing rest axle and runing rest axle mounting groove between antenna holder and channel components and fix branch Point, enable antenna module flexible modulation as needed to different postures, i.e. antenna can adjust different angle, and energy It is enough to stablize in the regulation angle, the calm signal of communication changing condition for tackling aircraft in flight course, significantly improve day Line launches and the performance of reception signal.

It is detailed further below.

Such as Figure 12, Figure 13, Figure 14, Figure 15, shown in Figure 16, the antenna structure in the present embodiment includes：Antenna 11, antenna branch Frame 12, and channel components 22, wherein, antenna 11 is fixed on antenna holder 12, also, antenna holder 12 passes through channel components 22, adjustable angle, which saves land, is arranged on the tail position of aircraft, and in other words, the direction of antenna 11 is also angle adjustable, As shown in Figure 17, Figure 18 and Figure 19.

More specifically, in the present embodiment, the lower section of antenna holder 12 is provided with two multi-angle engaging grooves 14, more Runing rest axle 17 is provided with angle engaging groove 14, channel components 22 include position and size and the phase of runing rest axle 17 The runing rest axle mounting groove 19 matched somebody with somebody.

Specifically, in the present embodiment, the lower section of antenna holder 12 is provided with two multi-angle engaging grooves 14, polygonal Runing rest axle 17 is provided with degree engaging groove 14, channel components 22 include position and size matches with runing rest axle 17 Runing rest axle mounting groove 19.Antenna holder 12 is by its runing rest axle 17, the runing rest axle peace being inserted on fuselage In tankage 19, realize and fix, but can rotate, in this case, if running into external force, antenna holder 12 can be around rotation branch Frame axle 17 flips an angle, and avoids directly causing to fracture with external force effect, at the same time, runing rest axle 17 still can be protected Hold and be embedded in runing rest axle mounting groove 19, in other words, antenna holder 12 is releasably set by runing rest axle 17 In the runing rest axle mounting groove 19 of the tail position of aircraft.

In the present embodiment, the first pin 15 and the second pin 16 are provided with multi-angle engaging groove 14, aircraft Be provided with fuselage the main body to match with the position and size of the first pin 15 and the second pin 16 be fixed groove 21 with And folding angles stopper slot 18.Enable the first pin 15 and the second pin 16 insert respectively main body be fixed groove 21 and In folding angles stopper slot 18.

In the present embodiment, the groove that the first pin 15 engages with the second pin 16 formation at least two different angle.Specifically Say that the inner side edge of the first pin 15 and the second pin 16 is along 2 kinks are above provided with, so that the first pin 15 and second is inserted in ground The groove 21 that can be fixed at different angles with main body of pin 16 engages with folding angles stopper slot 18.Stated differently, since The inner side edge of first pin 15 and the second pin 16 along being above provided with 2 kinks, when the first pin 15 and the second pin 16 with Different angles and main body are fixed groove 21 when engaging with folding angles stopper slot 18, and the posture of antenna holder 12 is different, Thus the direction of antenna 11 is different, so being capable of the state of flight of flexible adaptation different angle, makes the performance of antenna more preferable. Although the inner side edge of the first pin 15 and the second pin 16 edge is above provided with 2 kinks, the utility model in the present embodiment Not limited to this, in other embodiments, can be in the inner side edge of the first pin 15 and the second pin 16 along being above provided with 3 or more More kink, so as to which antenna 11 is adjusted into more different angles.

In the present embodiment, antenna 11 is chip aerial, but the utility model not limited to this, in other embodiments, day Line 11 can also be other kinds of antenna, for example, wire antenna, helical antenna, etc..

In the present embodiment, antenna slot 13 is provided with antenna holder 12, for housing antenna 11.Tail position is flight The tail position of device.

The major advantage of above-mentioned antenna structure includes：

2. simple in construction, easily fabricated, manufacturing cost is low.

In summary, antenna structure provided by the utility model significantly improves the ability of antenna transmitting and reception signal, And simple in construction, manufacturing cost is low, therefore there is very wide application prospect in aircraft field.

4. the disconnected antenna structure of drop resistant

The present inventor is by in-depth study extensively, it is proposed that a kind of disconnected antenna structure of new drop resistant.Specifically, Antenna holder is partly releasably set on board the aircraft by being arranged on the channel components of aircraft empennage position, for example, By runing rest axle and the runing rest axle mounting groove positioned at tail position, antenna holder is set to run into external force collision or impact When, it can be overturn along runing rest axle, make to be inserted in folding angles stopper slot and main body is fixed in groove first inserts Pin and the second pin can release, that is, can be released between multi-angle engaging groove and channel components, but runing rest axle Still it is rotatable to be connected with runing rest axle mounting groove, so as to avoid the direct effect with external force, reach part and released But the technique effect that the drop resistant still connected on the whole is broken.

It is described in further detail below.

As shown in figures 13-16, in the present embodiment, the antenna structure that aircraft also breaks comprising a kind of drop resistant.This day knot Structure includes：Antenna 11, antenna holder 12, and the channel components 22 being arranged on the fuselage of aircraft, wherein, antenna 11 is fixed On antenna holder 12, also, antenna holder 12 is releasably arranged on the tail position of aircraft by channel components 22, As shown in Figure 20 and Figure 21.

In the present embodiment, the first pin 15 and the second pin 16 are provided with multi-angle engaging groove 14, aircraft Be provided with fuselage the main body to match with the position and size of the first pin 15 and the second pin 16 be fixed groove 21 with And folding angles stopper slot 18.Enable the first pin 15 and the second pin 16 insert respectively main body be fixed groove 21 and In folding angles stopper slot 18, further fixation is played.

Further say, in the present embodiment, the first pin 15 forms at least two different angle with the second pin 16 and engaged Groove.Specifically, the inner side edge of the first pin 15 and the second pin 16 is along 2 kinks are above provided with, so that first inserts Pin 15 and the second pin 16 groove 21 that can be fixed at different angles with main body engage with folding angles stopper slot 18.Change Sentence is talked about, because the inner side edge of the first pin 15 and the second pin 16 edge is above provided with 2 kinks, when the first pin 15 and the Two pins 16 are fixed groove 21 when engaging with folding angles stopper slot 18 with main body at different angles, antenna holder 12 Posture is different, and thus the direction of antenna 11 is different, so being capable of the state of flight of flexible adaptation different angle, makes antenna Performance is more preferable.Although the inner side edge of the first pin 15 and the second pin 16 is along 2 kinks are above provided with the present embodiment, originally Utility model not limited to this, in other embodiments, can be in the inner side edge of the first pin 15 and the second pin 16 along upper setting There is the kink of 3 or more, so as to which antenna 11 is adjusted into more different angles.

The disconnected antenna structure of above-mentioned drop resistant includes following major advantage：

1. there is stronger impact resistant capability.

2. easy to maintenance, maintenance cost is low.

3. simple in construction, easily fabricated, manufacturing cost is low.

5. circuit board stacks

The present inventor is by in-depth study extensively, it is proposed that a kind of new stacked structures, for the side of stacking Image plate in aircraft, master control borad and battery, and video camera are fixed in frame main body by formula, wherein, before video camera Put.This set can further reduce the integral thickness of stacked structures, fuselage is made thinner on the whole, reduce The overall center of gravity of fuselage, and center of gravity is concentrated, and improves flight stability and controllability.

It is detailed further below.

Such as Fig. 5, Fig. 6, Fig. 7, shown in Figure 22, in the present embodiment, the stacked structures of aircraft include：Frame main body 611st, image plate 51, master control borad 52, and battery 53, wherein, image plate 51, master control borad 52 and battery 53 are with stacked on top Mode is fixed on the fuselage 1 of aircraft, i.e. in frame main body 611.

Specifically, image plate 51 is the circuit board for image procossing.Master control borad 52 is referred to as main circuit board, plate On be provided with binding site, for processor, memory, and to the parts such as external equipment engage.Generally, these parts can be inserted directly Enter slot, or use connection.

By stacked on top, make to realize centralized layout between image plate 51, master control borad 52, and battery 53, have and subtract Small size, the center of gravity of aircraft is set more to concentrate, so that the advantages of further improving flying quality.

In the present embodiment, image plate 51, master control borad 52 and battery 53 by screw and screw with the side of stacked on top Formula is fixed on the fuselage 1 of aircraft, i.e., in frame main body 611.For example, spiral shell can be set for corresponding position on master control borad 52 Hole so that image plate 51 and battery 53 can be screwed on master control borad 52.But the utility model not limited to this, at it In his embodiment, image plate 51, master control borad 52 and battery 53 can also be by buckle or plug-in units and jack, with stacked on top Mode be fixed in the frame main body 611 of aircraft.

In the present embodiment, image plate 51 is arranged on the upside of frame main body 611 with master control borad 52, and battery 53 is arranged on machine The downside of frame body 611.This mode be advantageous to for image plate 51, master control borad 52 and battery 53 provide one it is safer Accommodation space, reduce in flight course by the probability impacted, it is ensured that flight safety.But the utility model is not restricted to this, Image plate 51, master control borad 52 and battery 53 can be stacked in turn, can also be stacked with random order, can be all stacked on The upside of frame main body 611, it is possibility to have the upside for being stacked on frame main body 611, some is stacked under frame main body 611 Side.

If image plate 51, master control borad 52 and battery 53 in turn stack, battery 53 is located at image plate 51 and master control borad 52 lower sections, be advantageous to improve flight stability, further, it is possible to easily mount and dismount battery 53.

In the present embodiment, stacked structures also include video camera 54, wherein, video camera 54 is arranged on image plate 51, master Control the front side of plate 52 and battery 53, i.e. be arranged on the front side of frame main body 611.In other words, video camera 54 is arranged on flight The front side of the fuselage 1 of device.This set can further reduce the thickness of stacked structures, fuselage is made on the whole more It is thin, the overall center of gravity of fuselage is reduced, improves flight stability and controllability.In particular, can be with video camera 54 and machine Frame body 611 can be rotatably attached by screw, can also be connected by modes such as buckles.

In the present embodiment, connecting line is included on video camera 54, for being electrically connected with image plate 51, for transmitting image letter Number etc. information.But the utility model not limited to this, in other embodiments, video camera 54 can also be fixed on by mounting bracket On image plate 51.

In the present embodiment, stack formula structure and also include upper lid 62, upper lid 62 is arranged on frame main body 611 in a stacked Upside, the space for housing image plate 51 and master control borad 52 is formed with frame main body 611.In the present embodiment, upper lid 62 is logical The upside that screw is fixed on frame main body 611, but the utility model not limited to this are crossed, in other embodiments, can also be passed through The modes such as buckle, plug-in unit and jack are configured.

The major advantage of above-mentioned stacked structures includes：

1. integral body is made thinner.

2. making center of gravity more concentrate, and fuselage entirety center of gravity is reduced, improve flight stability and controllability.

3. simple in construction, easily fabricated, manufacturing cost is low.

In summary, stacked structure provided by the utility model has very wide application prospect in aircraft field.

6. the angle adjustment of camera lens

The present inventor is by in-depth study extensively, it is proposed that a kind of angle adjustment mechanism of new camera lens, this knot Structure is connected by the mutual cooperation covered on frame, camera lens, and fuselage, higher to the utilization rate of space structure.In this structure In, the both sides of camera lens are provided with rotational positioning axle, and camera lens is rotatably attached by rotational positioning axle with support member.Specifically Say, rotational positioning axle is on the one hand rotatably attached by the support member being arranged in frame, allow camera lens fixed by rotating Position axle relative to support member rotation adjustment angle, at the same time, rotational positioning axle further with fuselage lid be fixedly connected, with As both fixedly connected parts, thus make structure more reasonable, so as to save the structure space of fuselage, make overall structure more It is small.Also, damping gear is set on the contact surface of rotational positioning axle and support member, makes to be connected with support member through the above way Camera lens can conveniently, subtly realize angle adjustment, also, easily keep during aircraft flight the mirror adjusted The angle of head.

Below in conjunction with the accompanying drawings, further the angle adjustment mechanism of camera lens is illustrated.

As shown in Figure 23,24,25, in the present embodiment, the angle adjustment mechanism of camera lens includes：Camera lens 54 and for supporting The support member 64 of camera lens 54, wherein, the both sides of camera lens 54 are provided with rotational positioning axle 63, camera lens 54 by rotational positioning axle 63 with Support member 64 is rotatably attached.Specifically, the rotational positioning axle 63 for being arranged on the both sides of camera lens 54 can be rotatably set in branch In support member 64, thus, the rotation by rotated locating shaft 63 relative to support member 64, the angle of camera lens 54 can be adjusted, so as to Angle lenses adjustment function is realized by relatively more simple structure, also, this structure effectively reduces aircraft Structure space, reduce overall volume.

Further, as above, camera lens 54 realizes angular adjustment by the relative rotation of rotational positioning axle 63 and support member 64, In this case, regulation is that camera lens 54 rotates upwardly and downwardly angle.But the utility model not limited to this, in other embodiments, Camera lens 54 also includes a retainer plate, after rotational positioning axle 63 is fixedly connected with retainer plate both sides, rotatably with support member 64 Connection, meanwhile, the upper and lower ends of camera lens 54 are rotatably connected by the second rotary shaft with retainer plate, in this case, mirror First 54 not only can also pass through the second rotation axial adjustment left and right corner degree around the upper lower angle of the adjustment of locating shaft 63 is rotated.

In the present embodiment, support member 64 is arranged in the frame 61 of aircraft by integrally formed mode.But this reality With new not limited to this, in other embodiments, support member 64 can also pass through screw and screw, plug-in unit and jack or buckle Mode be arranged in the frame 61 of aircraft.

In the present embodiment, support member 64 is connected with the upper lid 62 of aircraft.In particular, the front end of upper lid 62 is set There is the region for housing camera lens 54, the size and dimension in the region can coordinate the size of camera lens 54 and its under rotational case The requirement of shooting visual angle.In this case, by support member 64, the rotatable connection branch to camera lens 54 can either be realized Support, and can enough realize being fixedly connected for frame 61 and upper lid 62, further reduce the structure space required for aircraft, make to fly Row body product is smaller.

In the present embodiment, through hole is provided with support member 64, is correspondingly provided with screw on upper lid 62, support member 64 with Upper lid 62 is fixedly connected by through hole, screw, and screw.But the utility model not limited to this, in other embodiments, support It can also be achieved a fixed connection, do not done herein superfluous by plug-in unit and jack or buckle, or other modes between part 64 and upper lid 62 State.

In the present embodiment, position is provided with support member 63, the recess that shapes and sizes match with rotational positioning axle 63, Rotational positioning axle 64 can be rotatably set in recess.In this case, camera lens 54 can easily be mounted and dismounted. But the utility model not limited to this, in other embodiments, can also on support member 63 set location, shapes and sizes with turn The through hole that dynamic locating shaft 63 matches, rotational positioning axle 64 can be rotatably set in through hole.Or can also be on support member 63 The recess that set location, shape match with size with rotational positioning axle 63, is rotatably inserted into the both ends of rotational positioning axle 64 And be fixed in the recess, etc. will not be described here.

In the present embodiment, be provided with damping gear on the surface of rotational positioning axle 63, for the recess with support member 64, Or through-hole surfaces produce damping.In this case, not only can more easily intense adjustment camera lens 54 angle, and In aircraft flight or carrying process, the angle of camera lens 54 can be more easily kept, and will not be slided or be offset.But the utility model Not limited to this, in other embodiments, damping gear can also be set on the surface of recess or through hole, be used for and rotational positioning The surface of axle 63 produces damping, can equally play a part of facilitating intense adjustment angle and effectively keep angle, not do herein Repeat.

The angle adjustment mechanism of above-mentioned camera lens has advantages below：

1. structure space layout is more rationally effective, aircraft overall volume is smaller.

2. camera lens can be mounted and dismounted easily, and can freely, be subtly adjusted, and can be in aircraft The stability of regulation angle is kept in flight and carrying process.

3. structure is most simplified, easily fabricated, manufacturing cost is low.

In summary, the angle adjustment mechanism of camera lens provided by the utility model has very wide answer in aircraft field Use prospect.

It should be noted that the various new improvement proposed in the utility model, both can independently be realized, can also carry out Be combined with each other realization, can be combined with as a kind of new Flight Vehicle Structure, and can also be combined with each other between each technical characteristic makes With will not be described here.

It should be noted that be all incorporated as referring in this application in all documents that the utility model refers to, as It is individually recited with each document as with reference to such.In addition, it is to be understood that reading in above-mentioned instruction of the present utility model After appearance, those skilled in the art can make various changes or modifications to the utility model, and these equivalent form of values equally fall within this Apply for appended claims limited range.

Also, in claims and specification of this patent, such as first and second or the like relational terms are only Only it is used for making a distinction an entity or operation with another entity or operation, and not necessarily requires or imply these realities Any this actual relation or order be present between body or operation.Moreover, term " comprising ", "comprising" or its it is any its His variant is intended to including for nonexcludability, so that process, method, article or equipment including a series of elements are not Only include those key elements, but also the other element including being not expressly set out, or also include for this process, method, Article or the intrinsic key element of equipment.In the absence of more restrictions, the key element limited by sentence " including one ", and It is not precluded within the process including the key element, method, article or equipment and other identical element is also present.The power of this patent In sharp claim and specification, if it is mentioned that perform certain behavior according to certain key element, then refer to perform the row according at least to the key element For the meaning, which includes two kinds of situations：The behavior is performed according only to the key element and is performed according to the key element and other key elements The behavior.

Although by referring to some preferred embodiments of the present utility model, the utility model is shown and retouched State, but it will be understood by those skilled in the art that can to it, various changes can be made in the form and details, without departing from Spirit and scope of the present utility model.

Claims

A kind of 1. antenna structure of angle adjustable, for aircraft, it is characterised in that include：

Antenna holder (12),

The antenna (11) being arranged on the antenna holder (12),

The channel components (22) being arranged on the fuselage of the aircraft, wherein

Antenna holder (12) adjustable angle, which saves land, to be buckled in the channel components (22).
2. the antenna structure of angle adjustable as claimed in claim 1, it is characterised in that included on the antenna holder (12) At least one multi-angle engaging groove (14), the multi-angle engages is provided with runing rest axle (17) on groove (14), and

The channel components (22) include position and size and installed with the runing rest axle that the runing rest axle (17) matches Groove (19), and

The antenna holder (12) is rotatably installed in the runing rest axle mounting groove by the runing rest axle (17) (19) in.
3. the antenna structure of angle adjustable as claimed in claim 2, it is characterised in that the multi-angle engaging groove (14) The first pin (15) and the second pin (16) are also included, and

The channel components (22) also comprising respectively with first pin (15) and position and the chi of second pin (16) The very little main body to match is fixed groove (21) and folding angles stopper slot (18).
4. the antenna structure of angle adjustable as claimed in claim 3, it is characterised in that first pin (15) with it is described The inner side edge of second pin (16) can be fixed groove (21) and folding angles limit along the groove formed with the main body Position groove (18) is engaged with least two different angle.
5. the antenna structure of angle adjustable as claimed in claim 4, it is characterised in that first pin (15) with it is described The inner side edge of second pin (16) includes the corresponding kink of at least two along upper, so that first pin (15) and described the Two pins (16) can be fixed groove (21) and folding angles stopper slot (18) with least two different angle with the main body Engaging.
6. the antenna structure of angle adjustable as claimed in claim 1, it is characterised in that the antenna (11) is sheet day Line.
7. the antenna structure of angle adjustable as claimed in claim 1, it is characterised in that set on the antenna holder (12) There is antenna slot (13), for housing the antenna (11).
8. the antenna structure of angle adjustable as claimed in claim 1, it is characterised in that the channel components (22) are arranged on The tail position of the fuselage of the aircraft.
9. the antenna structure of angle adjustable as claimed in claim 2, it is characterised in that

Engage groove (14) comprising 2 multi-angles on the antenna holder (12), distinguish on the multi-angle engaging groove (14) Runing rest axle (17) is provided with, and

The channel components (22) include position and size and pacified with 2 runing rest axles that the runing rest axle (17) matches Tankage (19).
10. a kind of aircraft, it is characterised in that include the antenna structure as described in claim 1-9.