CN206900647U - A kind of more rotors of combined type are tethered at UAS - Google Patents

A kind of more rotors of combined type are tethered at UAS Download PDF

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Publication number
CN206900647U
CN206900647U CN201720700278.9U CN201720700278U CN206900647U CN 206900647 U CN206900647 U CN 206900647U CN 201720700278 U CN201720700278 U CN 201720700278U CN 206900647 U CN206900647 U CN 206900647U
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fuselage
tethered
posture
motor
rotors
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CN201720700278.9U
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Chinese (zh)
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张士江
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Feiling Intelligent Control Beijing Technology Co ltd
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Powerise Mountains (beijing) Technology Co Ltd
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Abstract

It the utility model is related to and small-sized be tethered at unmanned air vehicle technique field, provide a kind of more rotors of combined type and be tethered at UAS, including being tethered at unmanned aerial vehicle platform and ground power supply system, being tethered at unmanned aerial vehicle platform includes fuselage, the dynamical system on fuselage, the airborne equipment in fuselage and the load below fuselage, dynamical system includes setting up and down along fuselage and turns to two opposite main rotor systems on same axis and be distributed in four posture oar systems of fuselage surrounding, and four posture oar systems are in cross arranged in a crossed manner.In the utility model, lifting drive is provided using two main rotor systems for being coaxially disposed and inverting, hovering efficiency is higher, can for a long time hover and perform task in predetermined altitude, and this dynamical system improves the ability of inorganic spot hover, make its situation about losing of being flown in the absence of unmanned plane because out of control;And airframe structure is more compact, the fuselage for being not easy to occur conventional more rotors in landing such as rocks at the wild effect.

Description

A kind of more rotors of combined type are tethered at UAS
Technical field
The utility model is related to it is small-sized be tethered at unmanned air vehicle technique field, be to be related to the more rotor systems of combined type more specifically Stay UAS.
Background technology
The existing middle-size and small-size unmanned plane that is tethered at is more based on more rotors of normal arrangement, the hovering of normal arrangement multi-rotor unmanned aerial vehicle Efficiency is low, and wind resistance is bad, and airscrew diameter is bigger, and folding and unfolding is more dumb, and wind resisting stability is poorer, is not suitable in complicated ring Used in border.
Utility model content
The purpose of this utility model is that providing a kind of more rotors of combined type is tethered at UAS, it is intended to solves existing skill It is tethered at that unmanned plane hovering efficiency is low and wind resistance is poor, the inflexible technical problem of folding and unfolding in art.
In order to solve the above technical problems, the technical solution of the utility model is:A kind of more rotors of combined type are provided and are tethered at nothing Man-machine system, including unmanned aerial vehicle platform and ground power supply system are tethered at, the unmanned aerial vehicle platform that is tethered at includes fuselage, located at described Dynamical system on fuselage, the airborne equipment in the fuselage and the load below the fuselage, the power System includes setting up and down along the fuselage and turns to two opposite main rotor systems on same axis and be distributed in institute Four posture oar systems of fuselage surrounding are stated, four posture oar systems are in cross arranged in a crossed manner.
Alternatively, each main rotor system includes main motor and main screw, and each main motor is respectively positioned on described In fuselage, each main screw is fixed on the motor shaft of each main motor and is located at the fuselage outer side.
Alternatively, main motor seat is provided with the fuselage, two main motors of two main rotor systems are stood by a motor Post is fixedly connected, and the motor column is passed vertically through and is fixed on the main motor seat.
Alternatively, each posture oar system includes posture motor, posture propeller and guard ring, each posture motor It is fixed on respectively by a motor beam on the main motor seat, each posture propeller is fixed on the electricity of each posture motor On arbor, each guard ring is enclosed outside each posture propeller, the motor beam position for the two posture motors being oppositely arranged It is opposite in the rotation direction for the two posture propellers on same straight line, being disposed adjacent.
Alternatively, the fuselage includes skeleton and the parcel skeleton and forms the fuselage skin in cabin, the fuselage Covering is provided with heat emission hole.
Alternatively, the load is located at below the main rotor system, is set between the load and the main rotor system There is switching cabin, be provided with multiple load beams on the switching cabin, each load beam passes through a fuselage support arm and the appearance respectively State oar system connects.
Alternatively, a pull bar is provided with the fuselage, the pull bar extends downwardly from and is placed through the main rotation of lower section The pull bar bottom is fixed in wing system, the switching cabin.
Alternatively, a load hanger is provided with below the switching cabin, the load is fixed in the load hanger.
Alternatively, undercarriage is equipped with each load beam, the load hanger is highly less than the height of the undercarriage Degree.
Alternatively, the ground power supply system includes generator, the alternating current of generator can be converted into the straight of direct current Stream power supply and the winch being connected with the dc source, the winch are put down by composite optical/electrical cable and the unmanned plane that is tethered at Platform connects.
In the utility model, lifting drive is provided using two main rotor systems that are coaxially disposed and invert, hovering efficiency compared with Height, it can for a long time hover and perform task in predetermined altitude, and this dynamical system improves the ability of inorganic spot hover, makes it not That unmanned plane flies loss because out of control be present;And main rotor system more compact structure setting up and down, in landing not The fuselage for conventional more rotors easily occur such as rocks at the wild effect, moreover, four posture oar systems are responsible for unmanned aerial vehicle platform behaviour The stability of control, compared with being routinely tethered at more rotors, hoverning stability is higher, though in extreme conditions, unmanned plane machine according to So there is stable and reliable maneuvering performance;Meanwhile load is arranged at below fuselage, effective utilization space is compact-sized, tears open Dress is convenient.
Brief description of the drawings
Fig. 1 is the stereochemical structure signal that the more rotors of combined type that the utility model embodiment provides are tethered at UAS Figure;
Fig. 2 is the side view that the more rotors of combined type that the utility model embodiment provides are tethered at UAS;
Fig. 3 is the dimensional structure diagram of the utility model embodiment middle fuselage;
Fig. 4 is the dimensional structure diagram that unmanned aerial vehicle platform is tethered in the utility model embodiment;
Fig. 5 is the side view that unmanned aerial vehicle platform is tethered in the utility model embodiment;
Fig. 6 is the sectional view that unmanned aerial vehicle platform is tethered in the utility model embodiment.
Embodiment
In order that the purpose of this utility model, technical scheme and advantage are more clearly understood, below in conjunction with accompanying drawing and implementation Example, the utility model is further elaborated.It should be appreciated that specific embodiment described herein is only explaining The utility model, it is not used to limit the utility model.
It should be noted that when element is referred to as " being fixed on " or " being arranged at " another element, it can be directly another On one element or it may be simultaneously present centering elements.When an element is referred to as " being connected to " another element, it can be with It is directly to another element or may be simultaneously present centering elements.
It should also be noted that, the orientation term such as left and right, upper and lower in the present embodiment, be only each other relative concept or Using the normal operating condition of product as reference, and should not be regarded as restrictive.
Reference picture 1, Fig. 2, the more rotors of a kind of combined type that the utility model embodiment provides are tethered at UAS, including It is tethered at unmanned aerial vehicle platform 100 and ground power supply system 200.Being tethered at unmanned aerial vehicle platform 100 includes fuselage 110, on fuselage 110 Dynamical system 120, the airborne equipment (not shown) in fuselage 110 and the load located at the lower section of fuselage 110 130.Wherein, dynamical system 120 includes setting up and down along fuselage 110 and turns to two opposite main rotor systems on same axis System 121 and four posture oar systems 122 for being distributed in the surrounding of fuselage 110, four posture oar systems 122 are set in cross intersection Put.
In the utility model, lifting drive, hovering efficiency are provided using two main rotor systems 121 for being coaxially disposed and inverting It is higher, it can for a long time hover and perform task in predetermined altitude, and this dynamical system 120 improves the ability of inorganic spot hover, Make its situation about losing of being flown in the absence of unmanned plane because out of control;And main rotor system more compact structure setting up and down, dropping The fuselage 110 for being not easy to occur conventional more rotors when falling such as rocks at the wild effect, moreover, four posture oar systems 122 are responsible for The stability of unmanned aerial vehicle platform manipulation, compared with being routinely tethered at more rotors, hoverning stability is higher, even in extreme condition Under, unmanned plane machine still has stable and reliable maneuvering performance;Meanwhile load 130 is arranged at the lower section of fuselage 110, effectively profit It is compact-sized with space, convenient disassembly.
Reference picture 3, in the present embodiment, fuselage 110 includes skeleton (not shown) and wrapping frame and forms cabin Fuselage skin 111.Skeleton encloses the fuselage 110 to be formed with fuselage skin 111 and is cylindrical in shape structure, and tubular structure is broad in the middle, Upper and lower ends are small.The two ends of fuselage 110 have opening, for installing two main rotor systems 121.Airborne equipment is located at cabin Interior, fuselage skin 111 is provided with heat emission hole 1111.Specifically, heat emission hole 1111 is located at the middle part of fuselage skin 111, and circumferentially Uniformly divide rich, so, air-flow when can be rotated using two main rotor systems 121 is radiated to airborne equipment in cabin.
Reference picture 4 is to Fig. 6, and in the present embodiment, two groups of structures of main rotor system 121 are identical, but two groups of main rotor systems 121 Contrarotation, prevailing lift is provided to be tethered at unmanned aerial vehicle platform 100.Every group of main rotor system 121 include main motor 1211 and Main screw 1212.One of which main rotor system 121 is at the upper end open of fuselage 110.Specifically, main motor 1211 In in fuselage 110, outside motor-shaft extending to the fuselage 110 of main motor 1211, main screw 1212 is fixed on the electricity of main motor 1211 On arbor and positioned at the outside of fuselage 110.Another group of main rotor system 121 is at the lower ending opening of fuselage 110.Specifically, should The main motor 1211 of group main rotor system 121 also is located on the inside of lower ending opening, i.e., in fuselage 110, the electricity of main motor 1211 Arbor is extended outside fuselage 110, and main screw 1212 is fixed on the motor shaft of main motor 1211 and positioned at the outside of fuselage 110.Ginseng According to Fig. 6, main motor seat 1213 is provided with fuselage 110, two main motors 1211 of two groups of main rotor systems 121 pass through a motor column 1214 are fixedly connected, and motor column 1214 passes vertically through and is fixed on main motor seat 1213.So, main motor seat is passed through 1213 and motor column 1214 realize two groups of main rotor systems 121 main motor 1211 fixation, certainly, motor column 1214 Effect in addition to fixed main motor 1211, be also responsible for main motor 1211 lifting certain altitude.
Reference picture 4 is to Fig. 6, and in the present embodiment, four groups of structures of posture oar system 122 are identical.Every group of posture oar system 122 wraps Include posture motor 1221, posture propeller 1222 and guard ring 1223.Every group of posture motor 1221 passes through a motor beam respectively 1224 are fixed on the main motor seat 1213 in fuselage 110.Specifically, fuselage 110 is provided with four mounting holes 1112, Mei Ge electricity Machine beam 1224 is horizontally disposed, and one end of motor beam 1224 is stretched into fuselage 110 by mounting hole 1112 and is fixed on main motor seat On 1213, posture motor 1221 is fixed on the other end of motor beam 1224, and posture propeller 1222 is fixed on posture motor On 1221 motor shaft, and guard ring 1223 is enclosed outside each posture propeller 1222.In the present embodiment, two postures that are oppositely arranged The motor beam 1224 of motor 1221 is located along the same line, and the rotation direction for two posture propellers 1222 being disposed adjacent is opposite. In the present embodiment, four groups of posture oar systems 122 for being distributed in the surrounding of fuselage 110 are responsible for the transverse direction and longitudinal direction stabilization of tethered platform Property, so both ensure the higher hovering efficiency of coaxial double main rotors, and also improve the manipulation stability of tethered platform.
In the present embodiment, load 130 is located at the lower section of two main rotor system 121, specifically being located under fuselage 110 The lower section of that group of main rotor system 121 of port.Switching cabin 140 is additionally provided between load 130 and the main rotor system 121.Specifically Ground, fuselage 110 is interior to be provided with a pull bar 135, and pull bar 135 extends downwardly from and is placed through the main rotor system 121 of lower section, cabin of transferring 140 are fixed on the bottom of pull bar 135.Switching is provided with multiple load beams 131 on cabin 140, and each load beam 131 passes through a fuselage respectively Support arm 134 is connected with each posture oar system 122.Specifically, load beam 131 omits slant setting, and its higher one end with putting vertically The bottom of fuselage support arm 134 connection put, relatively low one end is connected with switching cabin 140, and the top of fuselage support arm 134 is fixedly connected on In motor beam 1224.Undercarriage 132 is equipped with each load beam 131.The lower section of switching cabin 140 is provided with a load hanger 133, load 130 are fixed in load hanger 133.The height of load hanger 133 is less than the height of undercarriage 132, so, ensures that unmanned plane utilizes When undercarriage 132 drops to the state of ground, load 130 is not contacted to earth.
Referring again to Fig. 1, Fig. 2, ground power supply system 200 includes generator 210, can turn the alternating current of generator 210 The winch 230 for being changed to the dc source 220 of direct current and being connected with dc source 220, winch 230 pass through composite optical/electrical cable 240 are connected with being tethered at unmanned aerial vehicle platform 100.In the present embodiment, the operation principle that more rotors are tethered at UAS is:Ground Generator 210 in electric power system 200 is responsible for unmanned plane power supply is tethered at, and generator 210 exports the exchange that rated power needs Electricity, the direct current for becoming high pressure is converted through dc source 220, high voltage direct current is by the composite optical/electrical cable 240 on winch 230 It is conveyed to and is tethered at unmanned aerial vehicle platform 100, and be tethered at unmanned aerial vehicle platform 100 and be responsible for hanging load 130, and hovers over for a long time predetermined Highly, the manipulation of unmanned aerial vehicle platform 100 and the data communication of load 130 etc. are tethered at ground is then transferred to by optical fiber.In nothing During man-machine long-time hovering, four posture oar systems 122 are responsible for the transverse direction and longitudinal direction stability of tethered platform, so as to ensure The hovering efficiency of unmanned plane.
Preferred embodiment of the present utility model is these are only, it is all in this practicality not to limit the utility model All any modification, equivalent and improvement made within new spirit and principle etc., should be included in guarantor of the present utility model Within the scope of shield.

Claims (10)

1. a kind of more rotors of combined type are tethered at UAS, including are tethered at unmanned aerial vehicle platform and ground power supply system, the system Unmanned aerial vehicle platform is stayed to include fuselage, the dynamical system on the fuselage, the airborne equipment in the fuselage and set Load below the fuselage, it is characterised in that:The dynamical system includes setting up and down along the fuselage and is located at same Two opposite main rotor systems are turned on axis and are distributed in four posture oar systems of the fuselage surrounding, four appearances State oar system is in cross arranged in a crossed manner.
2. the more rotors of combined type as claimed in claim 1 are tethered at UAS, it is characterised in that:Each main rotor system Including main motor and main screw, each main motor is respectively positioned in the fuselage, and each main screw is fixed on each institute State on the motor shaft of main motor and be located at the fuselage outer side.
3. the more rotors of combined type as claimed in claim 2 are tethered at UAS, it is characterised in that:Master is provided with the fuselage Motor cabinet, two main motors of two main rotor systems are fixedly connected by a motor column, and the motor column passes vertically through And it is fixed on the main motor seat.
4. the more rotors of combined type as claimed in claim 3 are tethered at UAS, it is characterised in that:Each posture oar system Including posture motor, posture propeller and guard ring, each posture motor is fixed on the main electricity by a motor beam respectively On support, each posture propeller is fixed on the motor shaft of each posture motor, and each guard ring is enclosed located at each described Outside posture propeller, the motor beam for the two posture motors being oppositely arranged is located along the same line, described in two be disposed adjacent The rotation direction of posture propeller is opposite.
5. the more rotors of combined type as claimed in claim 1 are tethered at UAS, it is characterised in that:The fuselage includes skeleton And wrap up the skeleton and form the fuselage skin in cabin, the fuselage skin is provided with heat emission hole.
6. the more rotors of combined type as claimed in claim 1 are tethered at UAS, it is characterised in that:The load is positioned at described Switching cabin is provided with below main rotor system, between the load and the main rotor system, is provided with the switching cabin multiple Load beam, each load beam are connected by a fuselage support arm with the posture oar system respectively.
7. the more rotors of combined type as claimed in claim 6 are tethered at UAS, it is characterised in that:One is provided with the fuselage Pull bar, the pull bar extend downwardly from and are placed through the main rotor system of lower section, and the pull bar is fixed in the switching cabin Bottom.
8. the more rotors of combined type as claimed in claims 6 or 7 are tethered at UAS, it is characterised in that:Under the switching cabin Side is provided with a load hanger, and the load is fixed in the load hanger.
9. the more rotors of combined type as claimed in claim 8 are tethered at UAS, it is characterised in that:On each load beam Provided with undercarriage, the load hanger is highly less than the height of the undercarriage.
10. the more rotors of combined type as claimed in claim 1 are tethered at UAS, it is characterised in that:The surface power supply system System includes generator, the alternating current of generator can be converted to the dc source of direct current and be connected with the dc source Winch, the winch are connected by composite optical/electrical cable with the unmanned aerial vehicle platform that is tethered at.
CN201720700278.9U 2017-06-15 2017-06-15 A kind of more rotors of combined type are tethered at UAS Active CN206900647U (en)

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107187592A (en) * 2017-06-15 2017-09-22 山川创智(北京)科技有限公司 A kind of many rotors of combined type are tethered at UAS
CN111758465A (en) * 2020-07-11 2020-10-13 浙江极客桥智能装备股份有限公司 Tea frost prevention method and system based on unmanned aerial vehicle

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107187592A (en) * 2017-06-15 2017-09-22 山川创智(北京)科技有限公司 A kind of many rotors of combined type are tethered at UAS
CN111758465A (en) * 2020-07-11 2020-10-13 浙江极客桥智能装备股份有限公司 Tea frost prevention method and system based on unmanned aerial vehicle

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Effective date of registration: 20190726

Address after: 102200 No. 15, Block A, Block B, Xinyuan Science Park, Changping District, Beijing

Patentee after: Beijing Liao Time Technology Co.,Ltd.

Address before: 100000, No. 1, No. 3, building 158, No. 3076 West Fourth Ring Road, Beijing, Haidian District

Patentee before: SHANCHUAN CHUANGZHI (BEIJING) TECHNOLOGY CO.,LTD.

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Effective date of registration: 20221013

Address after: 100000 Commercial A02-141, Block A, Floor 2, No. 116, Zizhuyuan Road, Haidian District, Beijing

Patentee after: Feiling Intelligent Control (Beijing) Technology Co.,Ltd.

Address before: 102200 No.15, gate B, block a, Xinyuan Science Park, Changping District, Beijing

Patentee before: Beijing Liao Time Technology Co.,Ltd.

TR01 Transfer of patent right