CN105599895A - Multi-axis aircraft - Google Patents
Multi-axis aircraft Download PDFInfo
- Publication number
- CN105599895A CN105599895A CN201610068713.0A CN201610068713A CN105599895A CN 105599895 A CN105599895 A CN 105599895A CN 201610068713 A CN201610068713 A CN 201610068713A CN 105599895 A CN105599895 A CN 105599895A
- Authority
- CN
- China
- Prior art keywords
- screw
- hole
- motor
- clamping
- support bar
- 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.)
- Granted
Links
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 claims description 23
- 238000009434 installation Methods 0.000 claims description 22
- 238000010276 construction Methods 0.000 claims description 9
- 230000002787 reinforcement Effects 0.000 claims description 5
- 229910000838 Al alloy Inorganic materials 0.000 claims description 3
- 239000000956 alloy Substances 0.000 claims description 3
- 238000005267 amalgamation Methods 0.000 claims description 3
- 238000004519 manufacturing process Methods 0.000 abstract description 3
- 230000035945 sensitivity Effects 0.000 abstract description 2
- 230000002860 competitive effect Effects 0.000 abstract 1
- 238000000034 method Methods 0.000 abstract 1
- 238000010586 diagram Methods 0.000 description 3
- 230000005484 gravity Effects 0.000 description 2
- 239000004033 plastic Substances 0.000 description 2
- 229920003023 plastic Polymers 0.000 description 2
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000002360 explosive Substances 0.000 description 1
- 229910052744 lithium Inorganic materials 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 239000011347 resin Substances 0.000 description 1
- 229920005989 resin Polymers 0.000 description 1
- 239000013589 supplement Substances 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/30—Parts of fuselage relatively movable to reduce overall dimensions of aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
- B64C25/18—Operating mechanisms
- B64C25/24—Operating mechanisms electric
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/12—Rotor drives
- B64C27/14—Direct drive between power plant and rotor hub
-
- 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
- B64D47/00—Equipment not otherwise provided for
- B64D47/02—Arrangements or adaptations of signal or lighting devices
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Remote Sensing (AREA)
- Support Of Aerials (AREA)
- Toys (AREA)
Abstract
The invention belongs to the technical field of an unmanned aerial vehicle and specifically relates to a multi-axis aircraft. The multi-axis aircraft comprises a frame, a plurality of pipe clamps and an aircraft arm, wherein the pipe clamps are uniformly distributed on a side surface of the frame; an inner end of the aircraft arm is connected with the pipe clamps; a motor base is arranged at an outer end of the aircraft arm; a positive assembling motor is arranged in the motor base; a reversed assembling motor is arranged in the middle of the aircraft arm; a propeller easily assembled structure is respectively arranged on each of the revolving shafts of the positive assembling motor and the reversed assembling motor; a positive assembling propeller is arranged on the propeller easily assembled structure on the positive assembling motor; a reversed assembling propeller is arranged on the propeller easily assembled structure on the reversed assembling motor; an electric footstool foldable device is arranged at the bottom of the frame; and a footstool is connected with the electric footstool foldable device. The multi-axis aircraft can increase the generated lifting force within the limited volume size; the cruising power is higher; the manufacturing cost is lower; the structure is stable and firm; the sensitivity, the stability and the remote control precision are higher; the mounting and dismounting of each part are simple; and the multi-axis aircraft has competitive advantages in the competition process.
Description
Technical field
The invention belongs to unmanned plane technical field, be specifically related to a kind of Multi-axis aircraft.
Background technology
Multi-axis aircraft, be many rotor wing unmanned aerial vehicles, be provided with multiple screws, realize flight by the multiple screws of multiple Electric Machine Control, be widely used in take photo by plane, monitor, the every field such as search and rescue, resource exploration, agricultural, have that volume is little, lightweight, expense is low, a feature such as flexible operation and security height. On Multi-axis aircraft foot rest that flexibility and stability influence to aircraft is set is very large, the foot rest of existing Multi-axis aircraft is substantially all fixed, there is part also can only manually fold by folding foot rest, after aircraft takeoff, can not draw in time foot rest in, so the flexibility of aircraft and less stable, and the length of the lift of Multi-axis aircraft and the power of motor and horn is relevant, the lift that heavy-duty motor produces is larger, but heavy-duty motor power consumption is large, very high to the performance requirement of battery, flying power is poor; Longer horn can arrange more motors, and the lift that driven by motor screw can produce is larger, but the length of horn is all restricted, so the lift of common Multi-axis aircraft and weight ratio are lower, while being designed to small aircraft, load capacity is limited.
Summary of the invention
The present invention is directed to flexibility and the less stable of Multi-axis aircraft in prior art, lift and weight ratio are lower, the little drawback of load capacity while being designed to small aircraft, a kind of Multi-axis aircraft is provided, this Multi-axis aircraft is provided with electric stand folding device, can control foot rest by electric stand folding device and automatically draw in and launch, can effectively improve flexibility and the stability of Multi-axis aircraft; The formal dress motor arranging on horn and anyway motor can shorten the distance between adjacent motor, can under the horn condition of equal length, more low-power machine be set, avoid causing horn long because being provided with two motors, and can replace heavy-duty motor with the motor of two smaller powers, reach the lift level that heavy-duty motor can provide, and low-power machine is lower to the performance requirement of battery, power consumption is less, thus the flying power of energy Multi-axis aircraft.
Goal of the invention of the present invention is achieved through the following technical solutions: a kind of Multi-axis aircraft, comprise frame, some pipe clamps, horn, pipe clamp is evenly distributed on the side of frame, the inner of horn is connected with pipe clamp, horn outer end is provided with motor cabinet, in motor cabinet, be provided with formal dress motor, in the middle of horn, be provided with anti-dress motor, in the rotating shaft of formal dress motor and anti-dress motor, be provided with the easy assembling structure of screw, the easy assembling structure of screw on formal dress motor is provided with formal dress screw, formal dress screw is positioned at the top of horn, the easy assembling structure of screw on anti-dress motor is provided with anti-dress screw, anti-dress screw is positioned at horn below, formal dress screw is all down with the wind-force that anti-dress screw produces, all for Multi-axis aircraft provides lift, frame bottom is provided with electric stand folding device, on electric stand folding device, is connected with foot rest, described frame comprises and forms the basic components such as the framework, radio receiver, lithium battery of Multi-axis aircraft.
Described pipe clamp comprises clamping element and lower clamping element, described upper clamping element comprises two columns parallel to each other, two root posts are positioned at same level height, column is provided with the through hole A that runs through the upper and lower two ends of column, in through hole A, be provided with internal thread, between two root posts, be provided with arched girder, the top of arched girder and column upper end are positioned at same level height, and the arc of the lower surface of arched girder is semi arch; Described lower clamping element is the square slab structure that has semicircular structure groove, and the radius of semicircular structure groove equates with the radius of arched girder lower surface semi arch; The centre position of the lower clamping element upside of the groove side of being positioned at slab structure, lower clamping element both sides are respectively equipped with a through hole B who runs through the upper and lower two ends of lower clamping element, in through hole B, be provided with internal thread, distance between distance between two through hole A and two through hole B equates, in the time that upper clamping element is together with lower clamping element amalgamation, arched girder and groove form the installing hole A of a circular configuration, and through hole A is identical with the internal thread hand of spiral in through hole B. Thereby by being set in through hole A and through hole B, bolt regulate the distance between upper clamping element and the lower clamping element of pipe clamp to clamp horn, arranging like this can make the installing/dismounting of horn become very easy, and pipe clamp structure is also very simple, can adopt plastics manufacture, cost is low, can use multiple pipe clamps to be fixed installation to horn simultaneously, install very firm.
Horizontal range between formal dress propeller center position and anti-dress propeller center position is greater than the half of longer screw length in two screws, formal dress propeller center position with instead fill horizontal range between propeller center position be less than two screw length and half.
The easy assembling structure of described screw comprises screw clamping device and pedestal, and screw clamping device comprises upper grip block and the lower grip block for clamping screw, and lower grip block lower surface is provided with two groups of hook-type fasteners of symmetry mutually; Described pedestal is shell-like structure, pedestal both sides are respectively equipped with an elastic button, base interior is stretched in elastic button inner side, and elastic button is connected with slide bar in the end of pedestal inner side, described pedestal upper surface is provided with some embedded holes corresponding with hook-type fastener, embedded hole is positioned at slide bar top, and the hook-type fastener on lower grip block can and catch on slide bar through embedded hole; Described pedestal center is also provided with a rotating shaft installing hole that connects the upper and lower both sides of pedestal. The easy assembling structure of screw when mounted, in advance screw is arranged on screw clamping device, only need to be with several for subsequent use screw clamping devices that screw is installed while going out to take a flight test, in the time that needs are changed, need not use in addition the instruments such as screwdriver, only need to press the elastic button of bottom base both sides, screw clamping device can be installed on pedestal, and pedestal is mounted in the rotating shaft of motor, so just realize the replacing of screw, dismounting and installation are all very convenient, simple and fast.
Described electric stand folding device comprises fixed head, fixed head is frame-shaped construction, the fixed head surrounding of frame-shaped construction is provided with some installing hole B, on fixed head, be also provided with a fixing hole that runs through the upper and lower two ends of fixed head, the both sides of frame-shaped construction fixed head are respectively equipped with a rotating hole, fixed head is hinged with link by the rotating hole of both sides, and link is provided with the screw A corresponding with fixing hole, between fixing hole and screw A, is provided with bolt A; On link, be connected with foot rest revolving part, described foot rest revolving part comprises two plate washers parallel to each other, between two plate washers, be provided with motor mounting plate, on motor mounting plate, be connected with drive motors, the rotating shaft of drive motors runs through motor mounting plate and between two plate washers, the rotating shaft of drive motors is provided with external screw thread; Two plate washers lay respectively at the both sides of link, and plate washer and link hinged, link is provided with fixture block, between fixture block and drive motors, be provided with cross bar, in the middle of cross bar, be provided with screw B, the screw B on rotating shaft and the cross bar of drive motors is spirally connected, and rotating shaft and the cross bar of drive motors are orthogonal; On described drive motors, be connected with the tube connector for foot rest is installed, drive motors is arranged in tube connector.
Described foot rest comprises horizontal ground rod and vertical support bar, laterally between ground rod and vertical support bar, be provided with T-shaped foot rest connector, T-shaped foot rest connector is made up of two mutual symmetrical foot rest clamping elements, described foot rest clamping element comprises that cross section is that support bar clamping portion and the cross section of C shape structure is the ground rod clamping part of C shape structure, support bar clamping subordinate end is connected with the centre position of ground rod clamping part upside, and support bar clamping portion and ground rod clamping part orthogonal, the centre position of ground rod clamping part downside is provided with dead slot, the left and right sides of support bar clamping portion is provided with some engaging lug A, and the upside of ground rod clamping part is provided with some engaging lug B, on described engaging lug A and engaging lug B, is all provided with screw C, is provided with the bolt B for clamping two foot rest clamping elements in screw C, junction between described support bar clamping portion and ground rod clamping part is provided with reinforcement, both sides, junction between support bar clamping portion and ground rod clamping part are also respectively equipped with the gusset plate of a triangular structure of right angle, reinforcement and gusset plate can improve the firm performance of T-shaped foot rest connector, the impulsive force that Multi-axis aircraft when landing ground rod is subject to ground can be delivered to ground rod clamping part centre position, thereby ground rod clamping part is caused to damage, and being provided with dead slot, ground rod clamping part centre position avoid ground rod clamping part to sustain damage, and still old part of grabbing folder ground rod of ground rod clamping part upper groove two ends, can not impact its robustness. T-shaped foot rest connector can adopt plastics or resin material to make, and cost is very cheap, and lightweight, little to the burden of Multi-axis aircraft.
In described frame, be also provided with radome, comprise pallet and tray support bar, pallet edge is provided with guardrail, guardrail is provided with the opening for installing wire, described pallet lower surface is provided with Connection Block, Connection Block is provided with screw D, and tray support bar upper end position is provided with external screw thread, and tray support bar upper end is spirally connected by the screw D on external screw thread and Connection Block. The effect of radome is the Electromagnetic Interference in order to make GPS locator not produced by motor, GPS locator is arranged on the pallet of radome, the electromagnetic wave impact distance that motor can produce is very short, by increasing the distance between GPS locator and motor, can eliminate the impact on GPS locator of electromagnetic wave that motor produces. By screw and externally threaded setting, pallet can disassemble from support bar very easily, also facilitates the installation of GPS locator or magnetic compass simultaneously. The setting of guardrail, can be limited to GPS locator or magnetic compass in pallet, prevents that GPS locator or magnetic compass from coming off. GPS locator or magnetic compass will be connected with Multi-axis aircraft frame by electric wire, and the opening arranging on guardrail is the installation in order to facilitate electric wire.
As preferably, described motor cabinet comprises upper shell and lower house, on upper shell and lower house, be respectively equipped with a half-round in correspondence with each other, two half-round form one for clamping the horn clamping part of horn, on upper shell, be also provided with motor mounting groove, lower house is provided with control circuit board mounting groove, control circuit board mounting groove is positioned under motor mounting groove, motor mounting groove bottom is provided with motor holder, motor holder separates motor mounting groove and control circuit board mounting groove, and motor holder is provided with the installing hole C for formal dress motor is installed; The junction of upper shell and lower house is provided with anti-collision rubber, and the upper shell of anti-collision rubber both sides and lower house junction are provided with lampshade; Described lower house bottom is also provided with some louvres.
As preferably, described arched girder is provided with the reinforced hole A that runs through the upper and lower both sides of arched girder, and the bottom portion of groove on described lower clamping element is provided with reinforced hole B. The setting of reinforced hole A and reinforced hole B, is in order with screw, horn to be fixed, and prevents that horn from coming off.
As preferably, described upper grip block surrounding is provided with some fixed installations hole A, and described lower grip block surrounding is provided with the fixed installation hole B corresponding with fixedly mounting hole A, and the quantity of fixed installation hole A equates with the quantity that fixedly mounts hole B.
As preferably, described fixed installation hole A quantity is at least three.
As preferably, described tube connector is provided with screw E. Screw E is in order to reinforce being connected between electric stand folding device and foot rest, makes structure more firm.
As preferably, described Connection Block is positioned at pallet lower surface center. Arranging like this can make the strong point of tray support pole pair pallet be positioned at pallet center, can play best balanced state, each side stress balance, and GPS locator or the magnetic compass in pallet, placed are like this not easy to drop.
As preferably, tray support bar is up-thin-low-thick pyramidal structure. Tray support bar is arranged to upper coarse and lower fine pyramidal structure, can be by the decentralization of tray support bar, center of gravity below, be erected at tray support bar on Multi-axis aircraft more firm, that is to say, radome also can be more firm.
As preferably, described tray support pole length is 80mm-150mm. Through test of many times, tray support pole length is in the time that 80mm is above, be that the interior GPS locator arranging of pallet or magnetic compass and Multi-axis aircraft frame are apart from more than 80mm, the electromagnetic wave that motor produces is just negligible on the impact of GPS locator or magnetic compass, if tray support bar is too high, can make the center of gravity of tray support bar up move, unstable while causing Multi-axis aircraft flight.
As preferably, radome adopts aluminum alloy material to make.
Compared with prior art, the present invention has following beneficial effect: the electric stand folding device that the present invention arranges, can control foot rest when the remote control Multi-axis aircraft by electric stand folding device and automatically draw in and launch, can effectively improve flexibility and the stability of Multi-axis aircraft; The formal dress motor arranging on horn and anyway motor can shorten the distance between adjacent motor, can under the horn condition of equal length, more low-power machine be set, avoid causing horn long because being provided with two motors, and can replace heavy-duty motor with the motor of two smaller powers, reach the lift level that heavy-duty motor can provide, and low-power machine is lower to the performance requirement of battery, power consumption is less, battery cost is less, thus the flying power of energy Multi-axis aircraft. Pipe clamp can make that the installation of horn is more easy and structure is more firm. The easy assembling structure of screw can be realized Fast Installation and the dismounting of screw, and this saves time in the time carrying out the match of Multi-axis aircraft is very useful. Radome can prevent that GPS locator is subject to the electromagnetic impact that motor produces, thereby can improve remote control precision and the sensitive performance of Multi-axis aircraft. The structure of foot rest is also very simple and firm, and the T-shaped foot rest connector of employing can reduce Multi-axis aircraft and take off and produce impulsive force when landing foot rest is damaged, and improves the life-span of foot rest.
In sum, the present invention can improve the lift producing in the time of the volume size limiting, and flying power is longer, cost of manufacture is lower, stabilized structure, have higher sensitivity, stability and remote control precision, the installation and removal of all parts are also very simple simultaneously, can make the present invention occupy during the games very large advantage what carry out Multi-axis aircraft.
Brief description of the drawings
Fig. 1 is stereogram of the present invention;
Fig. 2 is electric stand folding device structural representation;
Fig. 3 is the cross section structure schematic diagram of Fig. 2;
Fig. 4 is fixed plate structure schematic diagram;
Fig. 5 is pipe clamp front view;
Fig. 6 is upper clamping element top view;
Fig. 7 is lower clamping element upward view;
Fig. 8 is motor cabinet stereogram;
Fig. 9 is Fig. 8 explosive view;
Figure 10 is the easy assembling structure stereogram of screw;
Figure 11 is that the easy assembling structure of screw uses state diagram;
Figure 12 is the upward view of Figure 11;
Figure 13 is the upward view of Figure 10;
Figure 14 is T-shaped foot rest connector stereogram;
Figure 15 is foot rest clamping element structural representation;
Figure 16 is radome stereogram;
Figure 17 is radome sectional view;
Mark in figure: 1, frame, 2, pipe clamp, 3, horn, 4, motor cabinet, 5, formal dress motor, 6, anti-dress motor, 7, the easy assembling structure of screw, 8, formal dress screw, 9, anti-dress screw, 10, electric stand folding device, 11, foot rest, 12, radome, 101, fixed head, 102, installing hole B, 103, fixing hole, 104, rotating hole, 105, link, 106, screw A, 107, bolt A, 108, foot rest revolving part, 109, plate washer, 110, motor mounting plate, 111, drive motors, 112, fixture block, 113, cross bar, 114, screw B, 115, tube connector, 116, screw E, 201, upper clamping element, 202, lower clamping element, 203, column, 204, through hole A, 205, arched girder, 206, groove, 207, through hole B, 208, installing hole A, 209, reinforced hole A, 210, reinforced hole B, 401, upper shell, 402, lower house, 403, half-round, 404, horn clamping part, 405, motor mounting groove, 406, control circuit board mounting groove, 407, motor holder, 408, installing hole C, 409, anti-collision rubber, 410, lampshade, 411, louvre, 701, screw clamping device, 702, pedestal, 703, upper grip block, 704, lower grip block, 705, hook-type fastener, 706, elastic button, 707, slide bar, 708, embedded hole, 709, rotating shaft installing hole, 710, fixed installation hole A, 711, fixed installation hole B, 1101, laterally ground rod, 1102, vertically support bar, 1103, T-shaped foot rest connector, 1104, foot rest clamping element, 1105, support bar clamping portion, 1106, ground rod clamping part, 1107, dead slot, 1108, engaging lug A, 1109, engaging lug B, 1110, screw C, 1111, bolt B, 1112, reinforcement, 1113, gusset plate, 1201, pallet, 1202, tray support bar, 1203, guardrail, 1204, opening, 1205, Connection Block, 1206, screw D.
Detailed description of the invention
Below in conjunction with embodiment that accompanying drawing is represented, the invention will be further described:
Embodiment 1
As shown in the figure, a kind of Multi-axis aircraft, comprise frame 1, pipe clamp 2, horn 3, pipe clamp 2 is evenly distributed on the side of frame 1, the inner of horn 3 is connected with pipe clamp 2, horn 3 outer ends are provided with motor cabinet 4, in motor cabinet 4, be provided with formal dress motor 5, in the middle of horn 3, be provided with anti-dress motor 6, in the rotating shaft of formal dress motor 5 and anti-dress motor 6, be provided with the easy assembling structure 7 of screw, the easy assembling structure 7 of screw on formal dress motor 5 is provided with formal dress screw 8, formal dress screw 8 is positioned at horn 3 tops, the easy assembling structure 7 of screw on anti-dress motor 6 is provided with anti-dress screw 9, anti-dress screw 9 is positioned at horn 3 belows, frame 1 bottom is provided with electric stand folding device 10, on electric stand folding device 10, be connected with foot rest 11,
Described pipe clamp 2 comprises clamping element 201 and lower clamping element 202, described upper clamping element 201 comprises two columns 203 parallel to each other, two root posts 203 are positioned at same level height, column 203 is provided with the through hole A204 that runs through the upper and lower two ends of column, in through hole A204, be provided with internal thread, between two root posts 203, be provided with arched girder 205, the top of arched girder 205 and column 203 upper ends are positioned at same level height, and the arc of the lower surface of arched girder 205 is semi arch; Described lower clamping element 202 is for having the square slab structure of semicircular structure groove 206, and the radius of semicircular structure groove 206 equates with the radius of arched girder 205 lower surface semi arches; The centre position of lower clamping element 202 upsides of groove 206 side's of being positioned at slab structures, lower clamping element 202 both sides are respectively equipped with a through hole B207 who runs through lower clamping element two ends Shang Xia 202, in through hole B207, be provided with internal thread, distance between distance between two through hole A204 and two through hole B207 equates, in the time that upper clamping element 201 is together with lower clamping element 202 amalgamations, arched girder 205 and groove 206 form the installing hole A208 of a circular configuration, and through hole A204 is identical with the internal thread hand of spiral in through hole B207; Described arched girder 205 is provided with the reinforced hole A209 that runs through arched girder both sides Shang Xia 205, and groove 206 bottoms on described lower clamping element 202 are provided with reinforced hole B210.
Horizontal range between formal dress screw 8 centers and anti-dress screw 9 centers is greater than the half of longer screw length in two screws, formal dress screw 8 centers with instead fill horizontal range between screw 9 centers be less than two screw length and half;
The easy assembling structure 7 of described screw comprises screw clamping device 701 and pedestal 702, screw clamping device 701 comprises upper grip block 703 and the lower grip block 704 for clamping screw, and lower grip block 704 lower surfaces are provided with two groups of hook-type fasteners 705 of symmetry mutually; Described pedestal 702 is shell-like structure, pedestal 702 both sides are respectively equipped with an elastic button 706, pedestal 702 inside are stretched in elastic button 706 inner sides, and elastic button 706 is connected with slide bar 707 in the end of pedestal 702 inner sides, described pedestal 702 upper surfaces are provided with four embedded holes 708 corresponding with hook-type fastener 705, embedded hole 708 is positioned at slide bar 707 tops, and the hook-type fastener 705 on lower grip block 704 can and catch on slide bar 707 through embedded hole 708; Described pedestal 702 centers are also provided with a rotating shaft installing hole 709 that connects pedestal both sides Shang Xia 702; Described upper grip block 703 surroundings are provided with four fixed installation hole A710, and described lower grip block 704 surroundings are provided with the fixed installation hole B711 corresponding with fixedly mounting hole A710, and the quantity of fixed installation hole A710 equates with the quantity of fixed installation hole B711.
Described electric stand folding device 10 comprises fixed head 101, fixed head 101 is frame-shaped construction, fixed head 101 surroundings of frame-shaped construction are provided with four installing hole B102, on fixed head 101, be also provided with a fixing hole 103 that runs through fixed head two ends Shang Xia 101, the both sides of frame-shaped construction fixed head 101 are respectively equipped with a rotating hole 104, fixed head 101 is hinged with link 105 by the rotating hole 104 of both sides, link 105 is provided with the screw A106 corresponding with fixing hole 103, between fixing hole 103 and screw A106, is provided with bolt A107; On link 105, be connected with foot rest revolving part 108, described foot rest revolving part 108 comprises two plate washers 109 parallel to each other, between two plate washers 109, be provided with motor mounting plate 110, on motor mounting plate 110, be connected with drive motors 111, the rotating shaft of drive motors 111 runs through motor mounting plate 110 and between two plate washers 109, the rotating shaft of drive motors 111 is provided with external screw thread; Two plate washers 109 lay respectively at the both sides of link 105, and plate washer 109 is hinged with link 105, link 105 is provided with fixture block 112, between fixture block 112 and drive motors 111, be provided with cross bar 113, in the middle of cross bar 113, be provided with screw B114, screw B114 on the rotating shaft of drive motors 111 and cross bar 113 is spirally connected, and the rotating shaft of drive motors 111 and cross bar 113 are orthogonal; On described drive motors 111, be connected with the tube connector 115 for foot rest 11 is installed, drive motors 111 is arranged in tube connector 115; Tube connector 115 is provided with screw E116.
Described foot rest 11 comprises horizontal ground rod 1101 and vertical support bar 1102, laterally between ground rod 1101 and vertical support bar 1102, be provided with T-shaped foot rest connector 1103, T-shaped foot rest connector 1103 is made up of two mutual symmetrical foot rest clamping elements 1104, described foot rest clamping element 1104 comprises that cross section is that support bar clamping portion 1105 and the cross section of C shape structure is the ground rod clamping part 1106 of C shape structure, support bar clamping portion 1105 lower ends are connected with the centre position of ground rod clamping part 1106 upsides, and support bar clamping portion 1105 is orthogonal with ground rod clamping part 1106, the centre position of ground rod clamping part 1106 downsides is provided with dead slot 1107, support bar clamping portion 1105 is each side provided with an engaging lug A1108, the upside of ground rod clamping part 1106 is provided with two engaging lug B1109, on described engaging lug A1108 and engaging lug B1109, be all provided with screw C1110, in screw C1110, be provided with the bolt B 1111 for clamping two foot rest clamping elements 1104, junction between described support bar clamping portion 1105 and ground rod clamping part 1106 is provided with reinforcement 1112, and the both sides, junction between support bar clamping portion 1105 and ground rod clamping part 1106 are also respectively equipped with the gusset plate 1113 of a triangular structure of right angle,
In described frame 1, be also provided with the radome 12 of aluminum alloy material, radome 12 comprises pallet 1201 and tray support bar 1202, pallet 1201 edges are provided with guardrail 1203, guardrail 1203 is provided with the opening 1204 for installing wire, described pallet 1201 lower surface centers are provided with Connection Block 1205, Connection Block 1205 is provided with screw D1206, tray support bar 1202 upper end positions are provided with external screw thread, and tray support bar 1202 upper ends are spirally connected by the screw D1206 on external screw thread and Connection Block 1205. Tray support bar 1202 is up-thin-low-thick pyramidal structure, and tray support bar 1202 length are 120mm.
Described motor cabinet 4 comprises upper shell 401 and lower house 402, on upper shell 401 and lower house 402, be respectively equipped with a half-round 403 in correspondence with each other, two half-round 403 form one for clamping the horn clamping part 404 of horn 3, on upper shell 401, be also provided with motor mounting groove 405, lower house 402 is provided with control circuit board mounting groove 406, control circuit board mounting groove 406 is positioned under motor mounting groove 405, motor mounting groove 405 bottoms are provided with motor holder 407, motor holder 407 separates motor mounting groove 405 and control circuit board mounting groove 406, motor holder 407 is provided with the installing hole C408 for formal dress motor 5 is installed, upper shell 401 is provided with anti-collision rubber 409 with the junction of lower house 402, and upper shell 401 and lower house 402 junctions of anti-collision rubber 409 both sides are provided with lampshade 410, described lower house 402 bottoms are also provided with louvre 411.
Specific embodiment described in literary composition is only to the explanation for example of the present invention's spirit. Those skilled in the art can make various amendments or supplement or adopt similar mode to substitute described specific embodiment, but can't depart from spirit of the present invention or surmount the defined scope of appended claims.
Claims (10)
1. a Multi-axis aircraft, comprise frame (1), some pipe clamps (2), horn (3), pipe clamp is evenly distributed on the side of frame, the inner of horn is connected with pipe clamp, horn outer end is provided with motor cabinet (4), in motor cabinet, be provided with formal dress motor (5), in the middle of horn, be provided with anti-dress motor (6), in the rotating shaft of formal dress motor and anti-dress motor, be provided with the easy assembling structure of screw (7), the easy assembling structure of screw on formal dress motor is provided with formal dress screw (8), formal dress screw is positioned at the top of horn, the easy assembling structure of screw on anti-dress motor is provided with anti-dress screw (9), anyway screw is positioned at the below of horn, frame bottom is provided with electric stand folding device (10), on electric stand folding device, be connected with foot rest (11),
Described pipe clamp comprises clamping element (201) and lower clamping element (202), described upper clamping element comprises two columns parallel to each other (203), two root posts are positioned at same level height, column is provided with the through hole A(204 that runs through the upper and lower two ends of column), in through hole A, be provided with internal thread, between two root posts, be provided with arched girder (205), the top of arched girder and column upper end are positioned at same level height, and the arc of the lower surface of arched girder is semi arch; Described lower clamping element is for having the square slab structure of semicircular structure groove (206), and the radius of semicircular structure groove equates with the radius of arched girder lower surface semi arch; The centre position of the lower clamping element upside of the groove side of being positioned at slab structure, lower clamping element both sides are respectively equipped with a through hole B(207 who runs through the upper and lower two ends of lower clamping element), in through hole B, be provided with internal thread, distance between distance between two through hole A and two through hole B equates, in the time that upper clamping element is together with lower clamping element amalgamation, arched girder and groove form the installing hole A(208 of a circular configuration), and through hole A is identical with the internal thread hand of spiral in through hole B;
Horizontal range between formal dress propeller center position and anti-dress propeller center position is greater than the half of longer screw length in two screws, formal dress propeller center position with instead fill horizontal range between propeller center position be less than two screw length and half;
The easy assembling structure of described screw comprises screw clamping device (701) and pedestal (702), screw clamping device comprises upper grip block (703) and the lower grip block (704) for clamping screw, and lower grip block lower surface is provided with two groups of hook-type fasteners (705) of symmetry mutually; Described pedestal is shell-like structure, pedestal both sides are respectively equipped with an elastic button (706), base interior is stretched in elastic button inner side, and elastic button is connected with slide bar (707) in the end of pedestal inner side, described pedestal upper surface is provided with some embedded holes corresponding with hook-type fastener (708), embedded hole is positioned at slide bar top, and the hook-type fastener on lower grip block can and catch on slide bar through embedded hole; Described pedestal center is also provided with a rotating shaft installing hole (709) that connects the upper and lower both sides of pedestal;
Described electric stand folding device comprises fixed head (101), fixed head is frame-shaped construction, the fixed head surrounding of frame-shaped construction is provided with some installing hole B(102), on fixed head, be also provided with a fixing hole (103) that runs through the upper and lower two ends of fixed head, the both sides of frame-shaped construction fixed head are respectively equipped with a rotating hole (104), fixed head is hinged with link (105) by the rotating hole of both sides, link is provided with the screw A(106 corresponding with fixing hole), between fixing hole and screw A, be provided with bolt A(107); On link, be connected with foot rest revolving part (108), described foot rest revolving part comprises two plate washers parallel to each other (109), between two plate washers, be provided with motor mounting plate (110), on motor mounting plate, be connected with drive motors (111), the rotating shaft of drive motors runs through motor mounting plate and between two plate washers, the rotating shaft of drive motors is provided with external screw thread; Two plate washers lay respectively at the both sides of link, and plate washer and link are hinged, link is provided with fixture block (112), between fixture block and drive motors, be provided with cross bar (113), in the middle of cross bar, be provided with screw B(114), screw B on rotating shaft and the cross bar of drive motors is spirally connected, and rotating shaft and the cross bar of drive motors are orthogonal; On described drive motors, be connected with the tube connector (115) for foot rest is installed, drive motors is arranged in tube connector;
Described foot rest comprises horizontal ground rod (1101) and vertical support bar (1102), laterally between ground rod and vertical support bar, be provided with T-shaped foot rest connector (1103), T-shaped foot rest connector is made up of two mutual symmetrical foot rest clamping elements (1104), described foot rest clamping element comprises that cross section is that support bar clamping portion (1105) and the cross section of C shape structure is the ground rod clamping part (1106) of C shape structure, support bar clamping subordinate end is connected with the centre position of ground rod clamping part upside, and support bar clamping portion and ground rod clamping part orthogonal; The centre position of ground rod clamping part downside is provided with dead slot (1107); The left and right sides of support bar clamping portion is provided with some engaging lug A(1108), the upside of ground rod clamping part is provided with some engaging lug B(1109), on described engaging lug A and engaging lug B, be all provided with screw C(1110), in screw C, be provided with the bolt B (1111) for clamping two foot rest clamping elements; Junction between described support bar clamping portion and ground rod clamping part is provided with reinforcement (1112), and the both sides, junction between support bar clamping portion and ground rod clamping part are also respectively equipped with the gusset plate (1113) of a triangular structure of right angle;
In described frame, be also provided with radome (12), comprise pallet (1201) and tray support bar (1202), pallet edge is provided with guardrail (1203), guardrail is provided with the opening (1204) for installing wire, described pallet lower surface is provided with Connection Block (1205), Connection Block is provided with screw D(1206), tray support bar upper end position is provided with external screw thread, and tray support bar upper end is spirally connected by the screw D on external screw thread and Connection Block.
2. Multi-axis aircraft according to claim 1, it is characterized in that, described motor cabinet comprises upper shell (401) and lower house (402), on upper shell and lower house, be respectively equipped with a half-round (403) in correspondence with each other, two half-round form one for clamping the horn clamping part (404) of horn, on upper shell, be also provided with motor mounting groove (405), lower house is provided with control circuit board mounting groove (406), control circuit board mounting groove is positioned under motor mounting groove, motor mounting groove bottom is provided with motor holder (407), motor holder separates motor mounting groove and control circuit board mounting groove, motor holder is provided with the installing hole C(408 for formal dress motor is installed), the junction of upper shell and lower house is provided with anti-collision rubber (409), and the upper shell of anti-collision rubber both sides and lower house junction are provided with lampshade (410), described lower house bottom is also provided with some louvres (411).
3. Multi-axis aircraft according to claim 1, is characterized in that, described arched girder is provided with the reinforced hole A(209 that runs through the upper and lower both sides of arched girder), the bottom portion of groove on described lower clamping element is provided with reinforced hole B(210).
4. Multi-axis aircraft according to claim 1, it is characterized in that, described upper grip block surrounding is provided with some fixed installations hole A(710), described lower grip block surrounding is provided with the fixed installation hole B(711 corresponding with fixedly mounting hole A), the quantity of fixed installation hole A equates with the quantity of fixed installation hole B.
5. Multi-axis aircraft according to claim 4, is characterized in that, described fixed installation hole A quantity is at least three.
6. according to the Multi-axis aircraft described in claim 1-5 any one, it is characterized in that, described tube connector is provided with screw E(116).
7. according to the Multi-axis aircraft described in claim 1-5 any one, it is characterized in that, described Connection Block is positioned at pallet lower surface center.
8. according to the Multi-axis aircraft described in claim 1-5 any one, it is characterized in that, tray support bar is up-thin-low-thick pyramidal structure.
9. according to the Multi-axis aircraft described in claim 1-5 any one, it is characterized in that, described tray support pole length is 80mm-150mm.
10. according to the Multi-axis aircraft described in claim 1-5 any one, it is characterized in that, radome adopts aluminum alloy material to make.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610068713.0A CN105599895B (en) | 2016-01-29 | 2016-01-29 | Multi-axis aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610068713.0A CN105599895B (en) | 2016-01-29 | 2016-01-29 | Multi-axis aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105599895A true CN105599895A (en) | 2016-05-25 |
| CN105599895B CN105599895B (en) | 2017-09-29 |
Family
ID=55980371
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610068713.0A Expired - Fee Related CN105599895B (en) | 2016-01-29 | 2016-01-29 | Multi-axis aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105599895B (en) |
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106347626A (en) * | 2016-11-16 | 2017-01-25 | 北京韦加无人机科技股份有限公司 | Foldable multi-rotor plant protection unmanned aerial vehicle |
| WO2018019152A1 (en) * | 2016-07-29 | 2018-02-01 | 深圳亿天航科技有限公司 | Motor mounting base for electronic speed controller of multi-rotor plant-protection aircraft |
| CN107902070A (en) * | 2017-10-27 | 2018-04-13 | 陈淇健 | A kind of frame central part and the multi-rotor unmanned aerial vehicle based on the frame central part |
| CN107914877A (en) * | 2017-12-20 | 2018-04-17 | 聊城揽悦创新科技有限公司 | Three axis connecting rod unmanned planes |
| WO2018076468A1 (en) * | 2016-10-25 | 2018-05-03 | 深圳市大疆创新科技有限公司 | Shielding apparatus and unmanned aerial vehicle |
| CN108377781A (en) * | 2018-03-08 | 2018-08-10 | 南京太司德智能科技有限公司 | A kind of screen of trees cleaning air-robot of suspension cutter structure |
| CN109484612A (en) * | 2018-12-24 | 2019-03-19 | 沈阳旋飞航空技术有限公司 | A kind of pole bracket for the dynamic unmanned plane of oil |
| CN109896004A (en) * | 2019-03-25 | 2019-06-18 | 上海应用技术大学 | A kind of unmanned plane of scalable horn |
| CN110077596A (en) * | 2019-05-27 | 2019-08-02 | 广西云瑞科技有限公司 | A kind of four axis unmanned plane during flying platform of multipurpose and unmanned plane |
| CN110271664A (en) * | 2019-07-04 | 2019-09-24 | 深圳市智旋科技有限公司 | A kind of safeguard structure and its application method of the patrol unmanned machine of forest line walking fire behavior |
| CN110316350A (en) * | 2019-07-25 | 2019-10-11 | 武汉天易航科技有限公司 | A kind of foldable horn mechanism of unmanned plane |
| CN110770125A (en) * | 2018-11-21 | 2020-02-07 | 深圳市大疆创新科技有限公司 | Multi-rotor unmanned aerial vehicle |
| CN113661119A (en) * | 2020-10-14 | 2021-11-16 | 深圳市大疆创新科技有限公司 | Multi-rotor unmanned aerial vehicle |
| CN113872100A (en) * | 2021-09-13 | 2021-12-31 | 国家电网有限公司 | Unmanned aerial vehicle zero detection device for ultra-high voltage transmission line tension tower porcelain insulator |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201367115Y (en) * | 2008-11-17 | 2009-12-23 | 西安智澜科技发展有限公司 | Foldable four-axis multi-rotor wing aerocraft |
| CN103963969A (en) * | 2014-04-30 | 2014-08-06 | 中国科学院长春光学精密机械与物理研究所 | Aircraft with multiple layers of rotary wings of circumferentially distributed rotary planes |
| US20140217229A1 (en) * | 2011-09-27 | 2014-08-07 | Singapore Technologies Aerospace Ltd | Unmanned aerial vehicle |
| CN104176247A (en) * | 2014-07-16 | 2014-12-03 | 李一波 | Four-rotor unmanned aerial vehicle with engine for directly driving rotor |
| CN204056295U (en) * | 2014-09-25 | 2014-12-31 | 佛山市安尔康姆航空科技有限公司 | Pneumatic structure four rotor unmanned aircraft |
| CN204223178U (en) * | 2014-10-21 | 2015-03-25 | 湖北省机电研究设计院股份公司 | A kind of folding unmanned plane |
-
2016
- 2016-01-29 CN CN201610068713.0A patent/CN105599895B/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201367115Y (en) * | 2008-11-17 | 2009-12-23 | 西安智澜科技发展有限公司 | Foldable four-axis multi-rotor wing aerocraft |
| US20140217229A1 (en) * | 2011-09-27 | 2014-08-07 | Singapore Technologies Aerospace Ltd | Unmanned aerial vehicle |
| CN103963969A (en) * | 2014-04-30 | 2014-08-06 | 中国科学院长春光学精密机械与物理研究所 | Aircraft with multiple layers of rotary wings of circumferentially distributed rotary planes |
| CN104176247A (en) * | 2014-07-16 | 2014-12-03 | 李一波 | Four-rotor unmanned aerial vehicle with engine for directly driving rotor |
| CN204056295U (en) * | 2014-09-25 | 2014-12-31 | 佛山市安尔康姆航空科技有限公司 | Pneumatic structure four rotor unmanned aircraft |
| CN204223178U (en) * | 2014-10-21 | 2015-03-25 | 湖北省机电研究设计院股份公司 | A kind of folding unmanned plane |
Cited By (22)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2018019152A1 (en) * | 2016-07-29 | 2018-02-01 | 深圳亿天航科技有限公司 | Motor mounting base for electronic speed controller of multi-rotor plant-protection aircraft |
| WO2018076468A1 (en) * | 2016-10-25 | 2018-05-03 | 深圳市大疆创新科技有限公司 | Shielding apparatus and unmanned aerial vehicle |
| CN109644581A (en) * | 2016-10-25 | 2019-04-16 | 深圳市大疆创新科技有限公司 | Screening arrangement and unmanned vehicle |
| CN109644581B (en) * | 2016-10-25 | 2020-05-22 | 深圳市大疆创新科技有限公司 | Shielding device and unmanned vehicles |
| CN106347626A (en) * | 2016-11-16 | 2017-01-25 | 北京韦加无人机科技股份有限公司 | Foldable multi-rotor plant protection unmanned aerial vehicle |
| CN107902070A (en) * | 2017-10-27 | 2018-04-13 | 陈淇健 | A kind of frame central part and the multi-rotor unmanned aerial vehicle based on the frame central part |
| CN107902070B (en) * | 2017-10-27 | 2024-06-11 | 陈淇健 | Rack center piece and multi-rotor unmanned aerial vehicle based on same |
| CN107914877A (en) * | 2017-12-20 | 2018-04-17 | 聊城揽悦创新科技有限公司 | Three axis connecting rod unmanned planes |
| CN108377781A (en) * | 2018-03-08 | 2018-08-10 | 南京太司德智能科技有限公司 | A kind of screen of trees cleaning air-robot of suspension cutter structure |
| CN108377781B (en) * | 2018-03-08 | 2023-10-20 | 南京太司德智能科技有限公司 | Tree obstacle cleaning aerial robot with hanging cutter structure |
| CN110770125A (en) * | 2018-11-21 | 2020-02-07 | 深圳市大疆创新科技有限公司 | Multi-rotor unmanned aerial vehicle |
| WO2020103037A1 (en) * | 2018-11-21 | 2020-05-28 | 深圳市大疆创新科技有限公司 | Multirotor unmanned aerial vehicle |
| CN109484612A (en) * | 2018-12-24 | 2019-03-19 | 沈阳旋飞航空技术有限公司 | A kind of pole bracket for the dynamic unmanned plane of oil |
| CN109896004B (en) * | 2019-03-25 | 2022-11-15 | 上海应用技术大学 | Unmanned aerial vehicle with telescopic arm |
| CN109896004A (en) * | 2019-03-25 | 2019-06-18 | 上海应用技术大学 | A kind of unmanned plane of scalable horn |
| CN110077596A (en) * | 2019-05-27 | 2019-08-02 | 广西云瑞科技有限公司 | A kind of four axis unmanned plane during flying platform of multipurpose and unmanned plane |
| CN110077596B (en) * | 2019-05-27 | 2024-04-26 | 广西云瑞科技有限公司 | Multipurpose four-axis unmanned aerial vehicle flight platform and unmanned aerial vehicle |
| CN110271664A (en) * | 2019-07-04 | 2019-09-24 | 深圳市智旋科技有限公司 | A kind of safeguard structure and its application method of the patrol unmanned machine of forest line walking fire behavior |
| CN110316350A (en) * | 2019-07-25 | 2019-10-11 | 武汉天易航科技有限公司 | A kind of foldable horn mechanism of unmanned plane |
| WO2022077285A1 (en) * | 2020-10-14 | 2022-04-21 | 深圳市大疆创新科技有限公司 | Multirotor unmanned aerial vehicle |
| CN113661119A (en) * | 2020-10-14 | 2021-11-16 | 深圳市大疆创新科技有限公司 | Multi-rotor unmanned aerial vehicle |
| CN113872100A (en) * | 2021-09-13 | 2021-12-31 | 国家电网有限公司 | Unmanned aerial vehicle zero detection device for ultra-high voltage transmission line tension tower porcelain insulator |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105599895B (en) | 2017-09-29 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105599895A (en) | Multi-axis aircraft | |
| CN105292510B (en) | A kind of multi-functional aerial photography aircraft | |
| CN208715437U (en) | Connection structure and navigation unit by water | |
| CN105460209B (en) | A kind of implementation method of aerial photography aircraft | |
| CN107323651B (en) | Arm subassembly, frame and unmanned aerial vehicle | |
| CN102849219B (en) | Omni-directional damping single-freedom-degree photoelectric reconnaissance platform device | |
| CN112607008A (en) | Anti-collision device based on large-scale many rotor unmanned aerial vehicle | |
| CN205186507U (en) | Four rotor crafts of folded cascade | |
| CN106005362A (en) | Multifunctional unmanned aerial vehicle frame set | |
| CN110539889A (en) | Plant protection unmanned aerial vehicle of two medical-kit double cell overall arrangement of big load | |
| CN207943154U (en) | A kind of Portable unmanned machine | |
| CN205076033U (en) | Electronic foot rest folding device | |
| CN211969736U (en) | Many rotor crafts's organism and many rotor crafts | |
| CN209684031U (en) | A kind of unmanned plane dynamic test device | |
| CN112109890B (en) | A folding oar presss from both sides drive assembly for unmanned aerial vehicle | |
| CN110697020A (en) | Unmanned aerial vehicle lightweight folding frame | |
| CN208470123U (en) | Unmanned plane, which navigates, flies view finder unit | |
| CN205916345U (en) | Small -size fixed wing uavs launching cradle | |
| CN206299970U (en) | Automatic weather station fixed mechanism | |
| CN210822802U (en) | Load suspension device for unmanned aerial vehicle to acquire ground coordinates | |
| CN205030047U (en) | A shield cover for on multiaxis aircraft | |
| CN212448091U (en) | Unmanned aerial vehicle frame is patrolled and examined to bridge and unmanned aerial vehicle is patrolled and examined to bridge | |
| CN207580154U (en) | For the exploration equipment of Along Railway | |
| CN203816169U (en) | Portable basketball stand capable of being converted into table tennis table | |
| CN206766322U (en) | One kind uses the new-type racing machine frame of upper counterangle structure |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20170929 Termination date: 20220129 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |