CN104691736A - Fixed-wing unmanned aerial vehicle - Google Patents
Fixed-wing unmanned aerial vehicle Download PDFInfo
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- CN104691736A CN104691736A CN201510107697.7A CN201510107697A CN104691736A CN 104691736 A CN104691736 A CN 104691736A CN 201510107697 A CN201510107697 A CN 201510107697A CN 104691736 A CN104691736 A CN 104691736A
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- 230000017525 heat dissipation Effects 0.000 claims description 10
- 238000005452 bending Methods 0.000 claims description 6
- 238000000034 method Methods 0.000 abstract description 9
- 241000208340 Araliaceae Species 0.000 description 3
- 235000005035 Panax pseudoginseng ssp. pseudoginseng Nutrition 0.000 description 3
- 235000003140 Panax quinquefolius Nutrition 0.000 description 3
- 235000008434 ginseng Nutrition 0.000 description 3
- 238000004891 communication Methods 0.000 description 2
- 238000005194 fractionation Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000002146 bilateral effect Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 210000001503 joint Anatomy 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
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Abstract
The invention discloses a fixed-wing unmanned aerial vehicle. The fixed-wing unmanned aerial vehicle comprises a fuselage main body, and wings and a tail which are installed on the fuselage main body, wherein the tail comprises an empennage and a tail rod fixed between the fuselage main body and the empennage; the wings comprise middle-section wings, left-section wings and right-section wings; the middle-section wings are fixed on the fuselage main body, and the left-section wings and the right-section wings are detachably installed on the left sides and the right sides of the middle-section wings respectively. According to the fixed-wing unmanned aerial vehicle disclosed by the invention, the whole wings of relatively large sizes are split into three sections respectively, wherein the middle-section wings can be integrated with electronic circuit equipment such as flying and receiving equipment, without being disassembled from the fuselage main body. In a transportation process, the left-section wings and the right-section wings can be disassembled, so that the space is saved, and the transportation is convenient.
Description
Technical field
The application belongs to technical field of taking photo by plane, and particularly relates to a kind of fixed-wing unmanned vehicle.
Background technology
Unmanned vehicle has that volume is little, lightweight, expense is low, flexible operation and the high feature of safety, can be widely used in taking photo by plane, monitor, search and rescue, the field such as resource exploration.
Existing fixed-wing unmanned vehicle, due to left and right wing and empennage longer, take up room large, be not easy to carry and transport.In addition, the antenna of fixed-wing unmanned vehicle is installed on the top of fuselage main body usually, because antenna is positioned at top, there is the bad problem of signal on the one hand, on the other hand, because antenna convexedly stretches in top, easily collide in transport or moving process and cause damage.
In view of this, be necessary to provide a kind of novel fixed-wing unmanned vehicle.
Summary of the invention
The object of the present invention is to provide a kind of fixed-wing unmanned vehicle, to overcome deficiency of the prior art.
For achieving the above object, the invention provides following technical scheme:
The embodiment of the present application discloses a kind of fixed-wing unmanned vehicle, comprise fuselage main body and the wing be installed in fuselage main body and afterbody, described afterbody comprises empennage and is fixed on the foot piece between fuselage main body and empennage, described wing comprises stage casing wing, left section of wing and right section of wing, described stage casing wing is fixed in described fuselage main body, and described left section of wing and right section of wing are detachably installed on the left and right sides of stage casing wing respectively.
Preferably, in above-mentioned fixed-wing unmanned vehicle, the end of described left section of wing and right section of wing is extended with guide rod respectively, and the end of described stage casing wing is provided with the mounting hole holding described guide rod.
Preferably, in above-mentioned fixed-wing unmanned vehicle, described guide rod comprises the first guide rod and the second guide rod that are set up in parallel, and the diameter of described first guide rod and development length are all greater than described second guide rod.
Preferably, in above-mentioned fixed-wing unmanned vehicle, the diameter of described second guide rod reduces gradually along the direction deviating from described left section of wing or right section of wing.
Preferably, in above-mentioned fixed-wing unmanned vehicle, between described left section of wing and stage casing wing and between right section of wing and stage casing wing, be fixed with the buckle limiting relative movement between adjacent wing respectively.
Preferably, in above-mentioned fixed-wing unmanned vehicle, described buckle comprises two elastic arms formed from middle part bending, these two elastic arms are formed with holding section in relative position is recessed in opposite directions, described holding section has curved surfaces, the end of described two elastic arms is formed with extension arm respectively to outer bending, in splayed opening between described two extension arms, the end face of wing both sides, described stage casing is fixed with the first adapter plate respectively, the end face of described left section of wing and right section of wing is fixed with the second adapter plate, described first adapter plate and the second adapter plate are respectively equipped with hole clipping or draw-in groove on correspondence position, described stage casing wing, left section of wing and right section of wing are respectively equipped with the insert port inserted for described buckle elastic arm, described insert port presses close to described first adapter plate or the second adapter plate is arranged.
Preferably, in above-mentioned fixed-wing unmanned vehicle, the top of described fuselage main body is recessed is formed with a space, umbrella storehouse, and the top in space, described umbrella storehouse hides umbrella Cang Gai, detachably fixes between described umbrella Cang Gai and fuselage main body.
Preferably, in above-mentioned fixed-wing unmanned vehicle, the front end of described fuselage main body is fixed with an on-hook plate, described on-hook plate is vertically arranged, described on-hook plate offers the suppending hole hanging aerial camera, the outside of described on-hook plate hides head-shield, detachably installs between described head-shield and fuselage main body.
Preferably, in above-mentioned fixed-wing unmanned vehicle, the below of described fuselage main body is upwards recessed is formed with an on-hook space, and the opening part in this on-hook space hides Lower Hold lid, detachably fixes between described Lower Hold lid and fuselage main body.
Preferably, in above-mentioned fixed-wing unmanned vehicle, the both sides of described wing are separately installed with a rotor in symmetric position, described each rotor drives respectively by a motor, the rear of described motor is formed with a heat dissipation channel, described heat dissipation channel is positioned at the below of described wing, is wherein provided with antenna in heat dissipation channel described in; Described antenna is rotatable in the horizontal direction and between vertical direction.
Compared with prior art, the invention has the advantages that:
(1), the present invention carries out syllogic fractionation for larger-size whole wing, and wherein stage casing wing can be integrated and fly the electronic circuit apparatus such as sky, reception, without the need to dismantling between itself and fuselage main body.In transportation, left section of wing and right section of wing can be disassembled, conserve space, convenient transport.
(2), three sections of wings complete assembled after, the separation between wing can be limited by buckle.
(3), in transportation, foot piece can be taken up room by front slotting minimizing;
(4), astronomical cycle in the below of wing, share heat dissipation channel with motor, do not take upper and lower space, and not easily come in contact collision in moving process, and antenna be positioned at below, signal of communication is good.
Accompanying drawing explanation
In order to be illustrated more clearly in the embodiment of the present application or technical scheme of the prior art, be briefly described to the accompanying drawing used required in embodiment or description of the prior art below, apparently, the accompanying drawing that the following describes is only some embodiments recorded in the application, for those of ordinary skill in the art, under the prerequisite not paying creative work, other accompanying drawing can also be obtained according to these accompanying drawings.
Figure 1 shows that the schematic perspective view of fixed-wing unmanned vehicle in the specific embodiment of the invention;
Figure 2 shows that the exploded perspective view of fixed-wing unmanned vehicle in the specific embodiment of the invention;
Figure 3 shows that the structural representation of fixed-wing unmanned vehicle skeleton in the specific embodiment of the invention;
Figure 4 shows that the fixing schematic diagram in the specific embodiment of the invention between buckle and adapter plate;
Figure 5 shows that the cutaway view of A-A in Fig. 4;
Figure 6 shows that the upward view of fixed-wing unmanned vehicle in the specific embodiment of the invention;
Figure 7 shows that the schematic perspective view after inserting before foot piece in the specific embodiment of the invention.
Detailed description of the invention
Below in conjunction with the accompanying drawing in the embodiment of the present invention, be described in detail the technical scheme in the embodiment of the present invention, obviously, described embodiment is only the present invention's part embodiment, instead of whole embodiments.Based on the embodiment in the present invention, the every other embodiment that those of ordinary skill in the art obtain under the prerequisite not making creative work, all belongs to the scope of protection of the invention.
Shown in ginseng Fig. 1 and Fig. 2, fixed-wing unmanned vehicle comprises fuselage main body 10 and the wing 20 that is installed in fuselage main body 10 and afterbody 30, and afterbody 30 comprises empennage 31 and is fixed on the foot piece 32 between fuselage main body 10 and empennage 31.
Wing 20 comprises stage casing wing 21, left section of wing 22 and right section of wing 23, and wherein, stage casing wing 21 is fixed in fuselage main body 10, and left section of wing 22 and right section of wing 23 are detachably installed on the left and right sides of stage casing wing 21 respectively.
In this technical scheme, carry out syllogic fractionation for larger-size whole wing, wherein stage casing wing can be integrated and fly the electronic circuit apparatus such as sky, reception, without the need to dismantling between itself and fuselage main body.In transportation, left section of wing and right section of wing can be disassembled, conserve space, convenient transport.
The end of left section of wing 22 and right section of wing 23 is extended with guide rod 221 respectively, and the end of stage casing wing 21 coordinates guide rod 221 to be provided with mounting hole 211, and left section of wing 22 and right section of wing 23 can realize fixing fast with stage casing wing 21 by guide rod 221.Guide rod 221 is preferably set side by side with 2.When guide rod 221 is only provided with 1, it is preferably flats.
In this technical scheme, left section of wing 22 or right section of wing 23 are plugged in the mounting hole of stage casing wing respectively by two guide rods, fast speed assembly and disassembly can be realized, adopt two guide rods, assembling rear left section wing can be avoided or relatively rotate between right section of wing and stage casing wing.
Shown in ginseng Fig. 4 and Fig. 5, buckle 40 is fixed with respectively between left section of wing 22 and stage casing wing 21 and between right section of wing 23 and stage casing wing 21, after stage casing wing 21 completes assembling with left section of wing 22 and right section of wing 23 respectively, buckle 40, in order to the relatively fixing of place that achieve a butt joint, therefore can prevent left section of wing 22 and right section of wing 23 from transfering to from stage casing wing 21 after fixation.
Buckle 40 comprises two elastic arms 41 formed from middle part bending, and these two elastic arms 41 are formed with holding section 42 in relative position is recessed in opposite directions, and holding section 42 has curved surfaces.The end of two elastic arms 41 is formed with extension arm 43 respectively to outer bending, in splayed opening between two extension arms 43.
Shown in composition graphs 3 and Fig. 6, the end face of stage casing wing 21 both sides is fixed with respectively the first adapter plate 212, the end face of left section of wing 22 and right section of wing 23 is fixed with on the second adapter plate 222, first adapter plate 212 and the second adapter plate 222 on correspondence position, is respectively equipped with hole clipping 2221.
Stage casing wing 21, left section of wing 22 and right section of wing 23 are respectively equipped with the insert port 231 inserted for buckle 40 elastic arm 41, insert port 231 presses close to the first adapter plate 212 or the second adapter plate 222 is arranged.
After stage casing wing 21 completes assembling with left section of wing 22 and right section of wing 23 respectively, the first adapter plate 212 and the second adapter plate 222 are fitted, and the hole clipping simultaneously on two adapter plates is relative.The end of the first adapter plate 212 and the second adapter plate 222 is clamp-oned between two elastic arms 41 by the splayed opening between two extension arms 43, two elastic arms 41 of buckle 40 insert in the insert port 231 on stage casing wing 21 and left section of wing 22 respectively, promote buckle 40 further until two holding sections 42 are slipped in the hole clipping on two adapter plates respectively.So, can not come off from insert port 231 after buckle 40 completes engaging, left section of wing 22 can be limited by buckle 40 and right section of wing 23 comes off from stage casing wing 21 simultaneously, when left section of wing 22 and right section of wing 23 are dismantled by needs, directly buckle 40 be extracted.
Be easy to it is contemplated that hole clipping 2221 can also be arranged to groove, between the first adapter plate 212 and the second adapter plate 222, also multiple buckle can be set.
Fuselage main body 10 is provided with a foot piece passage, and one end of foot piece 32 is installed in this tail pipe passage, and foot piece 32 is contracted in the adjustable length in foot piece passage.Further, foot piece passage runs through fuselage main body 10, and namely foot piece 32 is by interting the head exceeding fuselage main body 10.Structure after foot piece 32 shrinks as shown in Figure 7.
In this technical scheme, foot piece 32 can be interted to shorten the space shared by whole afterbody 30 forward, convenient disassembly, conserve space, conveniently transport, be easy to carry.When deployed, foot piece 32 can be extracted to relevant position, then by relative with fuselage main body 10 for foot piece 32 fixing.
Shown in ginseng Fig. 3, fuselage main body 10 comprises skeleton and is installed on the housing outside skeleton, and skeleton comprises a horizontally disposed stay bearing plate 11, and the bilateral symmetry of stay bearing plate 11 is provided with brace panel 12, and brace panel 12 is vertical with stay bearing plate 11 to be arranged.Stay bearing plate 11 offers multiple lightening hole 111.
In this technical scheme, skeleton structure is simple, greatly reduces the weight of body, stay bearing plate 11 is fixed by brace panel 12 and housing, can increase the contact surface between skeleton and housing, make between skeleton and housing more firm, and stay bearing plate 11 also not easily bends distortion.
The top of stay bearing plate 11 is provided with fixed support 13, and foot piece passage is formed between fixed support 13 and stay bearing plate 11.Fixed support 13 offers fixed orifice, to the below of fixed orifice being provided with screw on stay bearing plate 11, foot piece offers through hole, when assembling, first through hole on foot piece is corresponding with the fixed orifice on fixed support, then screw be each passed through fixed orifice and through hole and fix with the screw on stay bearing plate, thus it is relative fixing to realize between foot piece with fuselage main body.When needs disassembled for transport, unclamp screw and screw is extracted, inserting before foot piece.
Stage casing wing 21 comprises two strut bars be set up in parallel 213, and these two strut bars 213 are fixed by screws in fuselage main body 10.When disassembled for transport, stage casing wing 21 is without the need to dismantling from fuselage main body 10, and stage casing wing 21 and fuselage main body 10 can integrally be transported.
The front end of stay bearing plate 11 is fixed with an on-hook plate 14, and on-hook plate 14 vertical support plate 11 is arranged, and on-hook plate 14 offers the suppending hole hanging aerial camera.The outside of on-hook plate 14 hides head-shield 50, detachably installs between head-shield 50 and fuselage main body 10.
When operation taken photo by plane by needs, first head-shield 50 is pulled down, then aerial camera is suspended on on-hook plate 14, end of taking photo by plane, take off aerial camera and head-shield 50 is covered.
Left section of wing 22 and right section of wing 23 are separately installed with a rotor 61 in symmetric position, each rotor 61 drives respectively by a motor 62, wherein, the rear of the motor 62 on left section of wing 22 is formed with a heat dissipation channel 63, be provided with antenna 70 in this heat dissipation channel 63, antenna 70 can rotate in the horizontal direction and between vertical direction.Antenna 70 is installed on the below of left section of wing 22.
Antenna 70 is easy to it is contemplated that can also be arranged in the heat dissipation channel of right section of wing 23.
Antenna 70 is installed on the below of wing, and communication efficiency is good on the one hand, not taking the space on fuselage main body 10 top on the other hand, providing possibility for arranging space, umbrella storehouse above fuselage main body.And the ingenious heat-dissipating space that make use of motor 62 of antenna 70, not only dispels the heat conveniently, and does not additionally take up room.When transporting, antenna can turn to level attitude, does not take up room.
The top of fuselage main body 10 is recessed is formed with a space, umbrella storehouse 15, and the top in space, umbrella storehouse 15 hides has umbrella storehouse to cover 16, detachably fixes between umbrella storehouse lid 16 and fuselage main body 10.
In this technical scheme, by space, reserved umbrella storehouse 15, user is facilitated as required parachute to be installed.
The below of fuselage main body 10 is upwards recessed is formed with an on-hook space 17, and the opening part in on-hook space 17 hides Lower Hold lid 18, detachably fixes between Lower Hold lid 18 and fuselage main body 10.
In this this technical scheme, aerial camera The Cloud Terrace can be hung as required in on-hook space 17, be convenient to shooting and find a view.The position of an installation camera is provided with respectively at the head of fuselage main body 10 and bottom, therefore for user provides multiple different selection in this case.
It should be noted that, in this article, the such as relational terms of first and second grades and so on is only used for an entity or operation to separate with another entity or operational zone, and not necessarily requires or imply the relation that there is any this reality between these entities or operation or sequentially.And, term " comprises ", " comprising " or its any other variant are intended to contain comprising of nonexcludability, thus make to comprise the process of a series of key element, method, article or equipment and not only comprise those key elements, but also comprise other key elements clearly do not listed, or also comprise by the intrinsic key element of this process, method, article or equipment.When not more restrictions, the key element limited by statement " comprising ... ", and be not precluded within process, method, article or the equipment comprising described key element and also there is other identical element.
The above is only the detailed description of the invention of the application; it should be pointed out that for those skilled in the art, under the prerequisite not departing from the application's principle; can also make some improvements and modifications, these improvements and modifications also should be considered as the protection domain of the application.
Claims (10)
1. a fixed-wing unmanned vehicle, it is characterized in that, comprise fuselage main body and the wing be installed in fuselage main body and afterbody, described afterbody comprises empennage and is fixed on the foot piece between fuselage main body and empennage, described wing comprises stage casing wing, left section of wing and right section of wing, described stage casing wing is fixed in described fuselage main body, and described left section of wing and right section of wing are detachably installed on the left and right sides of stage casing wing respectively.
2. fixed-wing unmanned vehicle according to claim 1, is characterized in that: the end of described left section of wing and right section of wing is extended with guide rod respectively, and the end of described stage casing wing is provided with the mounting hole holding described guide rod.
3. fixed-wing unmanned vehicle according to claim 2, is characterized in that: described guide rod comprises the first guide rod and the second guide rod that are set up in parallel, and the diameter of described first guide rod and development length are all greater than described second guide rod.
4. fixed-wing unmanned vehicle according to claim 3, is characterized in that: the diameter of described second guide rod reduces gradually along the direction deviating from described left section of wing or right section of wing.
5. fixed-wing unmanned vehicle according to claim 1, is characterized in that: be fixed with the buckle limiting relative movement between adjacent wing respectively between described left section of wing and stage casing wing and between right section of wing and stage casing wing.
6. fixed-wing unmanned vehicle according to claim 5, it is characterized in that: described buckle comprises two elastic arms formed from middle part bending, these two elastic arms are formed with holding section in relative position is recessed in opposite directions, described holding section has curved surfaces, the end of described two elastic arms is formed with extension arm respectively to outer bending, in splayed opening between described two extension arms, the end face of wing both sides, described stage casing is fixed with the first adapter plate respectively, the end face of described left section of wing and right section of wing is fixed with the second adapter plate, described first adapter plate and the second adapter plate are respectively equipped with hole clipping or draw-in groove on correspondence position, described stage casing wing, left section of wing and right section of wing are respectively equipped with the insert port inserted for described buckle elastic arm, described insert port presses close to described first adapter plate or the second adapter plate is arranged.
7. fixed-wing unmanned vehicle according to claim 1, is characterized in that: the top of described fuselage main body is recessed is formed with a space, umbrella storehouse, and the top in space, described umbrella storehouse hides umbrella Cang Gai, detachably fixes between described umbrella Cang Gai and fuselage main body.
8. fixed-wing unmanned vehicle according to claim 1, it is characterized in that: the front end of described fuselage main body is fixed with an on-hook plate, described on-hook plate is vertically arranged, described on-hook plate offers the suppending hole hanging aerial camera, the outside of described on-hook plate hides head-shield, detachably installs between described head-shield and fuselage main body.
9. fixed-wing unmanned vehicle according to claim 1, it is characterized in that: the below of described fuselage main body is upwards recessed is formed with an on-hook space, the opening part in this on-hook space hides Lower Hold lid, detachably fixes between described Lower Hold lid and fuselage main body.
10. fixed-wing unmanned vehicle according to claim 1, it is characterized in that: the both sides of described wing are separately installed with a rotor in symmetric position, described each rotor drives respectively by a motor, the rear of described motor is formed with a heat dissipation channel, described heat dissipation channel is positioned at the below of described wing, is wherein provided with antenna in heat dissipation channel described in; Described antenna is rotatable in the horizontal direction and between vertical direction.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510107697.7A CN104691736A (en) | 2015-03-12 | 2015-03-12 | Fixed-wing unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510107697.7A CN104691736A (en) | 2015-03-12 | 2015-03-12 | Fixed-wing unmanned aerial vehicle |
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| Publication Number | Publication Date |
|---|---|
| CN104691736A true CN104691736A (en) | 2015-06-10 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510107697.7A Pending CN104691736A (en) | 2015-03-12 | 2015-03-12 | Fixed-wing unmanned aerial vehicle |
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| CN (1) | CN104691736A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN105366046A (en) * | 2015-12-15 | 2016-03-02 | 江苏艾锐泰克无人飞行器科技有限公司 | Fixed-wing air vehicle and control method in vertical posture |
| WO2016141742A1 (en) * | 2015-03-12 | 2016-09-15 | 杨华东 | Fixed-wing unmanned aircraft capable of being quickly disassembled and installed |
| CN109131877A (en) * | 2017-06-19 | 2019-01-04 | 昊翔电能运动科技(昆山)有限公司 | Unmanned vehicle |
| CN109625268A (en) * | 2019-01-11 | 2019-04-16 | 北京云影飞扬科技有限公司 | A kind of electronic fixed-wing unmanned plane of novel agricultural remote sensing |
| CN110562452A (en) * | 2019-09-23 | 2019-12-13 | 浙江驭云航空科技有限公司 | Can dismantle VTOL unmanned aerial vehicle of use |
| CN110562448A (en) * | 2019-09-16 | 2019-12-13 | 北京理工大学珠海学院 | Tailstock type unmanned aerial vehicle |
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| CN110562452A (en) * | 2019-09-23 | 2019-12-13 | 浙江驭云航空科技有限公司 | Can dismantle VTOL unmanned aerial vehicle of use |
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