CN109484649A - A kind of hoisting mechanism for the dynamic unmanned plane of oil - Google Patents
A kind of hoisting mechanism for the dynamic unmanned plane of oil Download PDFInfo
- Publication number
- CN109484649A CN109484649A CN201811581014.1A CN201811581014A CN109484649A CN 109484649 A CN109484649 A CN 109484649A CN 201811581014 A CN201811581014 A CN 201811581014A CN 109484649 A CN109484649 A CN 109484649A
- Authority
- CN
- China
- Prior art keywords
- unmanned aerial
- aerial vehicle
- shaped part
- unmanned plane
- oil
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 230000007246 mechanism Effects 0.000 title claims abstract description 25
- 230000008859 change Effects 0.000 abstract description 3
- 230000002787 reinforcement Effects 0.000 abstract 1
- 239000003921 oil Substances 0.000 description 34
- 238000010586 diagram Methods 0.000 description 3
- 238000005728 strengthening Methods 0.000 description 3
- 229910000831 Steel Inorganic materials 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 238000011161 development Methods 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000012544 monitoring process Methods 0.000 description 2
- 239000010959 steel Substances 0.000 description 2
- 230000004584 weight gain Effects 0.000 description 2
- 235000019786 weight gain Nutrition 0.000 description 2
- 208000035473 Communicable disease Diseases 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 230000002146 bilateral effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 150000001875 compounds Chemical class 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 208000015181 infectious disease Diseases 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000013507 mapping Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D9/00—Equipment for handling freight; Equipment for facilitating passenger embarkation or the like
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Load-Engaging Elements For Cranes (AREA)
Abstract
This application provides a kind of hoisting mechanisms for the dynamic unmanned plane of oil, including the first U-shaped part and the second U-shaped part；Two free ends of the first U-shaped part are connect with two cantilevers of the head two sides of unmanned plane respectively；Two free ends of the second U-shaped part are connect with two cantilevers of the tail two sides of unmanned plane respectively；Multiple rigid connecting rods are provided between the first U-shaped part and the second U-shaped part.The hoisting mechanism of the application is connected on four cantilevers of unmanned plane by way of rigid frame, it is not necessary that additional reinforcement structure is arranged on unmanned plane, without carrying out any change to unmanned plane structure, infrastructure cost is greatly saved, increases without the additional weight of worry.The hoisting mechanism of the application carries out integral hoisting operation to unmanned plane in the case where may not need to unmanned plane dismantling, reduces because dismantling bring reliability reduces the problem of influencing attendance time.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicles, in particular to an oil-driven unmanned aerial vehicle with multiple rotors, and particularly relates to a hoisting mechanism for the oil-driven unmanned aerial vehicle.
Background
The unmanned plane is called unmanned plane for short, and is an unmanned plane operated by radio remote control equipment and a self-contained program control device. Unmanned aerial vehicles can be classified into military and civil applications according to the application field. For military use, unmanned aerial vehicles divide into reconnaissance aircraft and target drone. The civil unmanned aerial vehicle is widely applied to the fields of aerial photography, agriculture, plant protection, miniature self-timer, express transportation, disaster relief, wild animal observation, infectious disease monitoring, surveying and mapping, news reporting, power inspection, disaster relief, movie and television shooting and the like.
Current many rotor unmanned aerial vehicle is electronic unmanned aerial vehicle usually. Many rotor electric unmanned aerial vehicle's simple structure easily makes, and motor light in weight, rotation are steady, and driving system is easily standardized, therefore the complete machine is easily controlled relatively, and the flight noise is low, and development is comparatively active in the civilian field of short voyage. However, because the energy density of the battery is far lower than that of fuel oil, the electric unmanned aerial vehicle is limited by the battery, the range is short, the load level is low, and the electric unmanned aerial vehicle cannot be applied to the field of military large-load reconnaissance and attack. And the fuel unmanned aerial vehicle of current long voyage adopts the stationary vane structure usually, takes off to descend and receives the restriction in airport, can't hover, and the cost is high, controls loaded down with trivial details, and the nimble mobility of use is not enough.
CN 106697278A discloses many rotor unmanned aerial vehicle of direct-driven formula oil moves fixed speed variable pitch, including fuselage, driving system, undercarriage and avionics system, the fuselage for the integrated fuselage of full compound material, driving system constitute by engine system, variable pitch system, oil feeding system and rotor system. Above-mentioned prior art's oil moves unmanned aerial vehicle's six rotors equiangular interval and around the organism setting, the application load that leads to carrying on the organism can only set up under the organism, and because each direction all receives blockking of rotor, the load of carrying can only develop the operation downwards, can't launch the weapon to oblique top or observe, there is the load level low, structural layout is unreasonable, be difficult to exert unmanned aerial vehicle's control and the defect of security advantage, the development of rotor unmanned aerial vehicle in military affairs and monitoring field has been restricted and has been used.
CN 205998123U discloses a vertical overall arrangement fuel power four rotor flight platform, and its constitution includes frame, driving system, navigation and control system, electrical system and task platform. Four identical machine arms are butted in pairs on a hard shell type machine body connected with an undercarriage to form a rack; the power system is arranged at the tail end of each horn and provides power and energy for the flying platform; the navigation and control system senses and controls the attitude, height and position of the flight platform; the electric system has the functions of charging, power supply and indication; the task platform is used for installing different task devices. This prior art's oil moves unmanned aerial vehicle has set up four independent engines, and the air current interference of adjacent rotor each other is difficult to arrange and is solved, and the interval that increases the engine can further increase volume and weight.
Above-mentioned prior art's oil moves unmanned aerial vehicle all disposes an oil and moves the engine on every cantilever, and naked engine adds the noise of rotor, leads to unmanned aerial vehicle hardly can use in urban airspace, uses under the military environment not there is not any disguise yet. CN 106184754a discloses a multi-rotor unmanned aerial vehicle, this unmanned aerial vehicle drives two pairs of rotors around through the oil engine that sets up the diaxon output in the fuselage inside, but the technique of the purpose-made oil engine that its adopted is immature, and the output of engine is limited, can't be applied to the armed unmanned aerial vehicle of heavy load. Its transmission structure is special, can't adopt current ripe big horsepower oil to move engine drive unmanned aerial vehicle. And the adopted full-symmetrical machine body structure can not flexibly set loads on the machine body in a large range, the gravity center position is concentrated on one point, and the load layout is greatly limited.
To overcome the above drawbacks of the prior art, the applicant of the present application discloses, in the previously filed chinese patent application 201711089265.3, a four-rotor oil-driven drone comprising a fuselage, a landing gear and four rotors supported by four cantilevers attached to the fuselage, wherein the fuselage has a longitudinal axis of symmetry and each cantilever carries at its distal end a pod surrounding the rotor; the aircraft nose and the tail of unmanned aerial vehicle respectively are provided with two rotors of being symmetrical in the symmetry axis and arranging, and the distance of two rotors of symmetry axis with one side equals apart from the symmetry axis. This prior art's four rotor unmanned aerial vehicle of oil-drive can avoid the air current interference of adjacent rotor through set up a kuppe at every rotor, makes the diameter maximize of rotor expand moreover, can be under the condition of the length that need not to prolong the cantilever, effectual improvement unmanned aerial vehicle's lift as far as possible, therefore can improve unmanned aerial vehicle's carrying capacity.
This prior art has effectively overcome prior art's defect, but along with the promotion of carrying capacity, unmanned aerial vehicle's volume and weight also increase thereupon by a wide margin for unmanned aerial vehicle's transportation problem becomes more outstanding, adopts the mode of disassembling to transport and has reduced unmanned aerial vehicle's reliability, has also reduced the time of attendance.
Disclosure of Invention
The invention aims to provide a hoisting mechanism for an oil-driven unmanned aerial vehicle, so as to reduce or avoid the problems.
In order to solve the technical problem, the invention provides a hoisting mechanism for an oil-driven unmanned aerial vehicle, wherein the oil-driven unmanned aerial vehicle comprises a body, an undercarriage and an engine arranged in the body of the oil-driven unmanned aerial vehicle, the body is provided with a longitudinal symmetrical axis, the head and the tail of the oil-driven unmanned aerial vehicle are respectively provided with two cantilevers which are arranged symmetrically to the longitudinal symmetrical axis, each cantilever supports a rotor wing, and the hoisting mechanism comprises: the hoisting mechanism comprises a first U-shaped piece and a second U-shaped piece; two free ends of the first U-shaped part are respectively connected with two cantilevers at two sides of the machine head; two free ends of the second U-shaped piece are respectively connected with two cantilevers at two sides of the tail; a plurality of rigid connecting rods are arranged between the first U-shaped part and the second U-shaped part.
Preferably, the cantilever has a joint portion located on an outer side of the fuselage; and the free ends of the first U-shaped piece and the second U-shaped piece are provided with clamping ring parts connected with the joint parts.
Preferably, the joint part is provided with an annular flange, and the clamping ring part is provided with a clamping groove for the flange to pass through.
Preferably, the clamping ring part comprises a first half ring and a second half ring which are clamped and connected on two sides of a connecting sheet arranged at the free ends of the first U-shaped part and the second U-shaped part.
The hoisting mechanism of this application is connected on unmanned aerial vehicle's four cantilevers through the form of rigid frame, need not to set up extra additional strengthening on unmanned aerial vehicle, need not carry out any change to the unmanned aerial vehicle structure, has saved structural cost greatly, also need not worry extra weight gain.
Drawings
The drawings are only for purposes of illustrating and explaining the present invention and are not to be construed as limiting the scope of the present invention. Wherein,
fig. 1 is a schematic perspective view of an oil-powered unmanned aerial vehicle according to an embodiment of the present invention;
fig. 2 shows a schematic structural view of the oil-driven unmanned aerial vehicle shown in fig. 1 with a part of the structure removed;
fig. 3 shows a schematic structural diagram of a hoisting mechanism for an oil-driven unmanned aerial vehicle according to an embodiment of the present invention;
figure 4 shows a schematic view of the mounting mechanism of figure 3 mounted to an unmanned aerial vehicle;
FIG. 5 is a schematic view of FIG. 4 with a part of the structure omitted;
fig. 6 shows a schematic view of a joint portion of a boom of the oil-powered drone of the present application;
fig. 7 shows an enlarged schematic view at a of fig. 5.
Detailed Description
In order to more clearly understand the technical features, objects, and effects of the present invention, embodiments of the present invention will now be described with reference to the accompanying drawings. Wherein like parts are given like reference numerals.
As described in the background art, the present invention provides an improved structure for making the prior art unmanned plane easy to lift and transport, aiming at the shortcomings of the prior art oil-driven quad-rotor unmanned plane disclosed in chinese patent application 201711089265.3.
Specifically, the hoisting mechanism for the oil-driven unmanned aerial vehicle can implement hoisting aiming at the oil-driven quad-rotor unmanned aerial vehicle disclosed by the prior art and can also implement hoisting operation aiming at the oil-driven unmanned aerial vehicle disclosed below the specification of the application. For example, as shown in fig. 1-2, wherein fig. 1 is a schematic perspective view of an oil-driven drone according to an embodiment of the present invention; fig. 2 shows a schematic structural view of the oil-driven unmanned aerial vehicle shown in fig. 1 with a part of the structure removed.
Referring to fig. 1-2, like the prior art, the unmanned aerial vehicle driven by oil of this application also includes fuselage 1, undercarriage 2, four cantilevers 3 and four rotors 5, and four cantilevers 3 are connected to fuselage 1, and every cantilever 3 all supports a rotor 5 of the same diameter. The fuselage 1 is the rectangular shape of bilateral symmetry structure, and fuselage 1 has a longitudinal symmetry axis 6, and fuselage 1 is the rectangular shape on the whole and is parallel to symmetry axis 6 sets up. The aircraft nose and the tail of unmanned aerial vehicle respectively are provided with two symmetries in rotor 5 that symmetry axis 6 arranged. Loads such as a photoelectric pod 7 and a weapon barrel 8 are arranged below the fuselage 1. The fuselage 1 is a generally elongated shuttle-shaped structure with narrow nose and tail widths and a maximum mid-width for the engine 99. A pod mounting structure capable of mounting the photoelectric pod 7 is arranged at the front end of the machine body 1, and a mounting frame capable of mounting the weapon launching tube 8 is arranged below the machine body 1. Each rotor 5 is provided with a circular air guide sleeve 4 with the same shape around the rotor.
Unmanned aerial vehicle of prior art that aforementioned background art cites and the unmanned aerial vehicle that this application is shown in fig. 1-2 all have the problem that volume and weight are too big to be transported, therefore this application provides hoisting machine structure for under this condition, and it can need not to carry out the integral hoisting operation to unmanned aerial vehicle under the condition of disassembling unmanned aerial vehicle, has reduced because the reliability that disassembles and bring reduces the problem that influences the time of attendance.
Specifically, in order to solve the technical problem, the application provides a hoisting mechanism for an oil-driven unmanned aerial vehicle, and the specific structure is shown in fig. 3-5, wherein fig. 3 is a schematic structural diagram of the hoisting mechanism for the oil-driven unmanned aerial vehicle according to one specific embodiment of the invention; figure 4 shows a schematic view of the mounting mechanism of figure 3 mounted to an unmanned aerial vehicle; fig. 5 is a schematic diagram of fig. 4 with a structure of a display portion omitted.
As shown in the drawings, as mentioned before, the oil-driven unmanned aerial vehicle of the present application includes a body 1, an undercarriage 2 and an engine 99 installed inside the body 1 of the oil-driven unmanned aerial vehicle, the body 1 has a longitudinal symmetry axis 6, the head and the tail of the oil-driven unmanned aerial vehicle are respectively provided with two cantilevers 3 arranged symmetrically to the symmetry axis 6, and each cantilever 3 supports a rotor 5.
In the illustrated embodiment, the hoisting mechanism of the oil-driven unmanned aerial vehicle of the present application comprises a first U-shaped piece 41 and a second U-shaped piece 42; the two free ends of the first U-shaped part 41 are respectively connected with the two cantilevers 3 at the two sides of the machine head; two free ends of the second U-shaped part 42 are respectively connected with two cantilevers 3 at two sides of the tail; a plurality of rigid connecting rods 43 are provided between the first U-shaped member 41 and the second U-shaped member 42.
Because the fuselage 1 of unmanned aerial vehicle generally adopts the combined material to make, it is sufficient for maintaining the aerodynamic profile of unmanned aerial vehicle, but for the hoist and mount of whole unmanned aerial vehicle, the intensity of fuselage 1 is not enough, takes place to warp or break very easily. The hoisting mechanism of this application constitutes first U-shaped piece 41, second U-shaped piece 42 and rigid connection pole 43 with the steel pipe to connect on unmanned aerial vehicle's four cantilevers 3 with the form of steel frame. Cantilever 3 originally just has the ability of bearing whole unmanned aerial vehicle's weight at the flight in-process, consequently, will hoist and mount the mechanism and connect on cantilever 3, need not to set up extra additional strengthening on unmanned aerial vehicle, need not carry out any change to the unmanned aerial vehicle structure, has saved structural cost greatly, also need not worry extra weight gain.
Further, the cantilever 3 of the unmanned aerial vehicle of the present and present application has a joint portion 34 located outside the fuselage 1, i.e. the cantilever 3 is connected to the fuselage 1 through the joint portion 34. Because there is stress concentration's trend in the joint portion 34 of cantilever 3, consequently in unmanned aerial vehicle structural design, joint portion 34 is through strengthening very much, sets up the position that hoisting machine constructs and cantilever 3 is connected in joint portion 34 can avoid cantilever 3's structural deformation, has reduced the risk of hoist and mount. In one embodiment of the application, the free ends of the first and second U-shaped members 41, 42 are provided with a snap ring portion 44 connected to the joint portion 34. The clamping ring part 44 can clamp the hoisting mechanism and the joint part 34 of the cantilever 3, so that the hoisting mechanism is prevented from moving relative to the machine body to extrude the machine body to cause damage.
Further, as can be seen in the joint part schematic view of the boom of the oil-driven unmanned aerial vehicle shown in fig. 6 and the enlarged schematic view at a of fig. 5 shown in fig. 7, the joint part 34 has an annular flange 341, and the snap ring part 44 is provided with a snap groove 441 through which the flange 341 passes. That is, in the present embodiment, the collar portion 44 can restrict the positional movement of the hoisting mechanism with respect to the cantilever 3 by fitting the flange 341 of the joint portion 34 into the fitting groove 441.
Further, in fig. 3, two snap ring portions are shown in an exploded manner, wherein the snap ring portion 44 is shown to comprise a first half ring 442 and a second half ring 443 which are clamped and connected on both sides of a connecting piece 444 provided at the free ends of the first U-shaped member 41 and the second U-shaped member 42. The upper ends of the first and second half rings 442 and 443 may be coupled to both sides of the coupling piece 444 by bolts (not shown), and the lower ends are coupled to each other by bolts. The first half ring 442 and the second half ring 443 each have a slot 441 through which the flange 341 can pass.
To sum up, the hoisting machine of this application constructs and can need not to carry out the integral hoisting operation to unmanned aerial vehicle under the condition of disassembling unmanned aerial vehicle, has reduced because disassemble the problem that the reliability that brings reduces the influence time of attendance.
It should be appreciated by those of skill in the art that while the present invention has been described in terms of several embodiments, not every embodiment includes only a single embodiment. The description is given for clearness of understanding only, and it is to be understood that all matters in the embodiments are to be interpreted as including technical equivalents which are related to the embodiments and which are combined with each other to illustrate the scope of the present invention.
The above description is only an exemplary embodiment of the present invention, and is not intended to limit the scope of the present invention. Any equivalent alterations, modifications and combinations can be made by those skilled in the art without departing from the spirit and principles of the invention.
Claims (4)
1. The utility model provides a hoisting machine constructs for oil moves unmanned aerial vehicle, oil moves unmanned aerial vehicle includes fuselage (1), undercarriage (2) and installs engine (99) inside fuselage (1) of oil moves unmanned aerial vehicle, fuselage (1) has a longitudinal symmetry axis (6), oil moves unmanned aerial vehicle's aircraft nose and tail respectively be provided with two symmetries in cantilever (3) that longitudinal symmetry axis (6) were arranged, every cantilever (3) all support there is a rotor (5), its characterized in that: said hoisting means comprise a first U-shaped element (41) and a second U-shaped element (42); two free ends of the first U-shaped part (41) are respectively connected with two cantilevers (3) on two sides of a machine head of the unmanned aerial vehicle; two free ends of the second U-shaped part (42) are respectively connected with two cantilevers (3) on two sides of the tail of the unmanned aerial vehicle; a plurality of rigid connecting rods (43) are arranged between the first U-shaped part (41) and the second U-shaped part (42).
2. Hoisting mechanism according to claim 1, characterized in that said cantilever (3) has a joint (34) located outside said body (1); the free ends of the first U-shaped part (41) and the second U-shaped part (42) are provided with clamping ring parts (44) connected with the joint parts (34).
3. Hoisting mechanism according to claim 2, characterized in that said joint part (34) has an annular flange (341) and said collar part (44) is provided with a slot (441) for the passage of said flange (341).
4. A hoisting mechanism according to claim 3, characterized in that said clamping ring (44) comprises a first half-ring (442) and a second half-ring (443) which are clamped on either side of a connecting piece (444) provided at the free ends of said first (41) and second (42) U-shaped members.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811581014.1A CN109484649A (en) | 2018-12-24 | 2018-12-24 | A kind of hoisting mechanism for the dynamic unmanned plane of oil |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811581014.1A CN109484649A (en) | 2018-12-24 | 2018-12-24 | A kind of hoisting mechanism for the dynamic unmanned plane of oil |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109484649A true CN109484649A (en) | 2019-03-19 |
Family
ID=65711682
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811581014.1A Pending CN109484649A (en) | 2018-12-24 | 2018-12-24 | A kind of hoisting mechanism for the dynamic unmanned plane of oil |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109484649A (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2414977A (en) * | 2004-05-18 | 2005-12-14 | Allan Gill | Flying platform |
| CN106218894A (en) * | 2016-08-09 | 2016-12-14 | 高琴 | The helicopter loading device of traffic accident treatment and processing method thereof |
| CN206826921U (en) * | 2017-03-21 | 2018-01-02 | 西南科技大学 | A kind of mobile platform based on rotor |
| CN107738752A (en) * | 2017-11-20 | 2018-02-27 | 德州新星职业中等专业学校 | Oily electricity mixing four-axle aircraft |
| CN107985576A (en) * | 2017-12-04 | 2018-05-04 | 长安大学 | A kind of Fei Pa robots for Bridge Crack detection |
| CN108016613A (en) * | 2017-12-25 | 2018-05-11 | 西安冰果智能航空科技有限公司 | A kind of dynamic displacement quadrotor unmanned plane of small-sized oil |
| CN207758982U (en) * | 2018-01-05 | 2018-08-24 | 河南正大航空科技股份有限公司 | A kind of unmanned plane integral frame structure |
-
2018
- 2018-12-24 CN CN201811581014.1A patent/CN109484649A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2414977A (en) * | 2004-05-18 | 2005-12-14 | Allan Gill | Flying platform |
| CN106218894A (en) * | 2016-08-09 | 2016-12-14 | 高琴 | The helicopter loading device of traffic accident treatment and processing method thereof |
| CN206826921U (en) * | 2017-03-21 | 2018-01-02 | 西南科技大学 | A kind of mobile platform based on rotor |
| CN107738752A (en) * | 2017-11-20 | 2018-02-27 | 德州新星职业中等专业学校 | Oily electricity mixing four-axle aircraft |
| CN107985576A (en) * | 2017-12-04 | 2018-05-04 | 长安大学 | A kind of Fei Pa robots for Bridge Crack detection |
| CN108016613A (en) * | 2017-12-25 | 2018-05-11 | 西安冰果智能航空科技有限公司 | A kind of dynamic displacement quadrotor unmanned plane of small-sized oil |
| CN207758982U (en) * | 2018-01-05 | 2018-08-24 | 河南正大航空科技股份有限公司 | A kind of unmanned plane integral frame structure |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN207450216U (en) | A kind of load configuration structure of the dynamic unmanned plane of oil | |
| CN207450249U (en) | A kind of unmanned plane rotor pulp distance varying mechanism | |
| CN107672799A (en) | A kind of electronic unmanned plane | |
| US20220119107A1 (en) | Modular unmanned aerial vehicles | |
| CN109484649A (en) | A kind of hoisting mechanism for the dynamic unmanned plane of oil | |
| CN107697309A (en) | Radiator structure for the dynamic unmanned plane of oil | |
| CN107672780A (en) | A kind of load configuration structure of the dynamic unmanned plane of oil | |
| CN107719661A (en) | A kind of unmanned plane rotor pulp distance varying mechanism | |
| CN207450269U (en) | For the radiator structure of the dynamic unmanned plane of oil | |
| CN209258371U (en) | The cantilever connection structure of the dynamic unmanned plane of oil | |
| CN209258406U (en) | A kind of hoisting mechanism for unmanned plane | |
| CN107757883A (en) | A kind of dynamic unmanned plane undercarriage of oil | |
| CN207450243U (en) | A kind of dynamic quadrotor unmanned plane of oil | |
| CN109484611A (en) | A kind of fuselage bearing structure of the dynamic unmanned plane of oil | |
| CN109484636A (en) | The support construction of pod for the dynamic unmanned plane of oil | |
| CN207450227U (en) | A kind of dynamic unmanned plane undercarriage of oil | |
| CN216834262U (en) | Big load foldable six-rotor unmanned aerial vehicle | |
| CN107719655A (en) | A kind of dynamic four rotor wing unmanned aerial vehicles of oil | |
| CN109484628B (en) | Oil moves unmanned aerial vehicle's simple and easy transport mechanism | |
| CN209305827U (en) | A kind of improved unmanned plane pulp distance varying mechanism | |
| CN209336992U (en) | A kind of unmanned plane Simple transportation mechanism | |
| CN209258410U (en) | A kind of fuel system for the dynamic unmanned plane of oil | |
| CN214729636U (en) | Unmanned vehicles with broken window function | |
| CN109484635B (en) | A kuppe for oiling move unmanned aerial vehicle's rotor | |
| CN109850175B (en) | Novel transmitting frame structure |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20190319 |