CN203497178U - Flying vehicle capable of taking off and landing on complex terrains - Google Patents
Flying vehicle capable of taking off and landing on complex terrains Download PDFInfo
- Publication number
- CN203497178U CN203497178U CN201320330520.XU CN201320330520U CN203497178U CN 203497178 U CN203497178 U CN 203497178U CN 201320330520 U CN201320330520 U CN 201320330520U CN 203497178 U CN203497178 U CN 203497178U
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- gear
- cross bar
- box frame
- wing
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Abstract
The utility model relates to a flying vehicle capable of taking off and landing on complex terrains. The flying vehicle comprises a main frame, two ducts, a transverse swinging wing, a lengthwise swinging swing, a direction control mechanism, an engine and a support, wherein shaft seats are arranged at the centers of the inner cavities of the ducts, and supports are uniformly distributed between the shaft seats and the peripheries of the inner walls of the ducts; propeller shafts are arranged in the shaft seats and can be rotatably matched with the shaft seats; propellers are arranged at the upper ends of the propeller shafts, and the outer walls of the two ducts are connected with each other by virtue of a connecting frame; the main frame is connected to the bottom of the connecting frame, and a seat is arranged on the front side of the main frame. The flying vehicle is characterized in that an output shaft of the engine is connected to the two propeller shafts with by virtue of a first transmission mechanism; the direction control mechanism is arranged on the main frame and is connected to the transverse swinging wing and the lengthwise swinging swing respectively with by virtue of a second transmission mechanism. The flying vehicle can take off and land on the narrow complex terrains such as high mountains or in canyons and is free of limitation of usable range.
Description
Technical field
The utility model relates to a kind of aircraft.Specifically, be only can carry a people, can be at the aircraft of the narrow and small MODEL OVER COMPLEX TOPOGRAPHY landing in high mountain or valley and so on.
Background technology
In aircraft manufacture field, all know, traditional small aircraft mainly contains two kinds, and a kind of is while being provided with the landing of flank in fuselage both sides, to need the side wing type aircraft of runway, the another kind of Vertical Lift aircraft of screw propeller that arranges at fuselage top.No matter be side wing type aircraft, or Vertical Lift aircraft, for meeting the enough buoyancy in flight course, just require the former two flanks and the latter's screw propeller to want enough length.And flank and screw propeller one are long, the horizontal space that aircraft occupies is on the ground just large.The horizontal space occupying due to above-mentioned two kinds of aircraft is larger, during landing, also will have enough horizontal spaces, also needs sufficiently long runway during a kind of aircraft landing before especially.Therefore, above-mentioned two kinds of aircraft can only be difficult to the narrow and small complex-terrain landing in high mountain or valley and so in larger region landing, and range of use is restricted.
Utility model content
Problem to be solved in the utility model be to provide a kind of can be at the aircraft of complex-terrain landing.This aircraft, can be in narrow and small complicated region landing, and range of use is unrestricted.
For addressing the above problem, take following technical scheme:
Of the present utility modelly can comprise at the aircraft of complex-terrain landing body frame, two ducts, laterally put the wing, longitudinally put the wing, direction control mechanism, driving engine and support, the axis of described two ducts parallels.There is axle bed at the center of described duct inner chamber, between the inwall surrounding of axle bed and duct, is evenly equipped with support.In axle bed, having oar axle and the two to be rotatable shape coordinates.There is screw propeller oar axle upper end, between the outer wall of described two ducts, by link span, is connected.Described body frame is connected to the bottom of link span, and there is seat the front side of body frame.The output shaft that is characterized in described driving engine is connected with two oar axles by the first transmission device.Described direction control mechanism is on body frame, and direction control mechanism is connected with longitudinal pendulum wing with the horizontal pendulum wing respectively by the second transmission device.
Wherein, described direction control mechanism contains two motors and controller, and described controller is connected with two motors respectively, and the output shaft of two motors is connected with described the second transmission device.
The centre of described link span is fixed with top chock, longitudinal center's line parallel of the longitudinal center line of top chock and described duct.In described body frame, be fixed with step, between upper and lower bearing seat, there is main shaft, the top and bottom of main shaft are stretched in described top chock and step by bearing respectively, on that in link span section main shaft, be fixed with two the first belt wheels, on described oar axle, all have the second belt wheel, two second belt wheels are all connected with two the first belt wheels on main shaft respectively by driving band.Stretch out under step described main shaft lower end, on the lower extending end of described main shaft and on the output shaft of described driving engine, all has the first gear, between two first gears, meshes together.By top chock, step, bearing, main shaft, the first belt wheel, the second belt wheel, driving band and two the first gears, form described the first transmission device.
The output shaft of described driving engine is vertical with described main shaft, and the gear of described main shaft lower end and the gear on engine output shaft are finishing bevel gear cuter.
Described oar axle upper end is fixed with drag reduction lid, and described upper drag reduction lid is for taper and its top are to being stream line pattern transition between rear; Described oar axle lower end is fixed with lower drag reduction lid, described lower drag reduction lid for taper and its top down, the top of described lower drag reduction lid is to being stream line pattern transition between lower end; On that section of oar axle between described the second belt wheel and described axle bed, have sleeve, the external diameter of this sleeve equates with the external diameter of upper drag reduction lid lower end and the external diameter that lower drag reduction covers end.
Box frame is arranged at body frame bottom, has the first cross bar in box frame, and the first cross bar two ends are all stretched out outside the two lateral walls of box frame and are connected with described longitudinal pendulum wing respectively.On first connecting rod in box frame, be fixed with worm gear, in the box frame of worm gear one side, have worm screw, worm and wheel meshes together.Between described worm screw lower end and box frame bottom, be rotatable shape and coordinate, worm screw upper end is connected with the output shaft of a motor after passing box frame top.In box frame, have the second cross bar, described the second cross bar parallels with described the first cross bar.The second cross bar one side in box frame has wheel shaft, is rotatable shape and coordinates between wheel shaft lower end and box frame bottom, and wheel shaft upper end is connected with the output shaft of another motor after passing box frame top.On wheel shaft, be fixed with the second gear, have the first teeth groove accordingly with this second gear on that section second cross bar, this first teeth groove and described the second gear mesh together.
There is transverse holes the centre of described longitudinal pendulum wing, the line of centers of this transverse holes is vertical with described the second cross bar, in transverse holes, be installed with connecting rod, the two ends of described connecting rod are stretched out respectively and are laterally being put the both sides of the wing, the two ends of described connecting rod are all connected with wing piece, thereby form longitudinal pendulum wing by the wing piece at connecting rod and connecting rod two ends.On that section of connecting rod in described transverse holes, there are two bearings, on that section of connecting rod between described two bearings, be fixed with the 3rd gear, on longitudinal pendulum wing of the 3rd gear one side, have the bar hole vertical with connecting rod, the two ends of described the second cross bar are stretched into respectively in the described bar hole on corresponding longitudinal pendulum wing.The centre in described bar hole communicates with described transverse holes, and described the second cross bar outer end side adjacent with described the 3rd gear has the second teeth groove, and this second teeth groove and described the 3rd gear mesh together.By the second gear on the first teeth groove in the middle of box frame, the first cross bar, the second cross bar, worm gear, worm screw, the second cross bar, wheel shaft, wheel shaft, the 3rd gear on connecting rod and second teeth groove at the second cross bar two ends form described the second transmission device.
Described support is under box frame, and the two links together.
Take such scheme, have the following advantages:
As can be seen from the above scheme, because the output shaft of described driving engine is connected with the oar axle in two ducts by the first transmission device, during landing, by driving engine, produce power and drive oar axle and blade in two ducts to rotate by the first transmission device, thereby make aircraft produce raising force.Output shaft due to two motors on described body frame is connected with longitudinal pendulum wing with the horizontal pendulum wing respectively by the second transmission device again, during flight, by two motors by the second transmission device drive respectively the horizontal pendulum wing and longitudinally the pendulum wing rotate, with meet aircraft rising or decline, move ahead, turnon left or right-hand corner needs.Compare with two kinds of conventional aircraft in background technology, both without flank, screw propeller is not exposed to fuselage outside yet, makes the small volume of whole aircraft, and the horizontal space occupying especially is on the ground very little.Therefore, this aircraft can not only can also be particularly useful for fighting flood and relieve victims and earthquake relief and other civilian and protection fields in the narrow and small complex-terrain landing in high mountain or valley and so in larger region landing, and range of use is unrestricted.
Accompanying drawing explanation
Fig. 1 be of the present utility model can be at the Flight Vehicle Structure schematic diagram of complex-terrain landing;
Fig. 2 is that schematic diagram is looked on a left side of Fig. 1;
Fig. 3 is the schematic top plan view of Fig. 1;
Fig. 4 is the part sectional view that removes Fig. 1 of seat;
Fig. 5 is the A-A cross-sectional schematic of Fig. 4;
Fig. 6 is the B-B cross-sectional schematic of Fig. 1;
Fig. 7 is the C-C cross-sectional schematic of Fig. 1;
Fig. 8 is the D-D cross-sectional schematic of Fig. 4;
Fig. 9 is the E-E cross-sectional schematic of Fig. 4;
Figure 10 is the F-F cross-sectional schematic of Fig. 5.
The specific embodiment
As shown in Figure 1, Figure 2, shown in Fig. 3, Fig. 4, Fig. 5, Fig. 6, Fig. 7, Fig. 8, Fig. 9 and Figure 10, of the present utility modelly can comprise at the aircraft of complex-terrain landing body frame 15 and two ducts 8, direction control mechanism.The axis of described two ducts 8 parallels, and the center of described duct 8 inner chambers is provided with axle bed 34, is evenly equipped with and supports 28 between the inwall surrounding of axle bed 34 and duct 8, and the two ends of described support 28 are cast as one with duct 8 inwalls and axle bed 34 respectively.In axle bed 34, be provided with oar axle 27, each oar axle 27 is all rotatable shape by two bearings with 34 of corresponding axle beds and coordinates.In described two bearings, a bearing is coro bearng, and another bearing is cylindrical bearing.Described oar axle 27 upper ends (front end) are provided with screw propeller 26.Between the outer wall of described two ducts 8, by link span, link together.The centre of described link span is fixed with top chock 41, longitudinal center's line parallel of the longitudinal center line of top chock 41 and described duct 8.
Described body frame 15 is vertical framework, and driving engine 14 is installed in it.The bottom of described body frame 15 tops and link span is fixed together, and the installed in front of body frame 15 has seat 7.A speed bar handle 9 and a directional control handle 13 are installed on described seat 7.Described direction control mechanism is on body frame 15.Described direction control mechanism contains two motors 6 and controller.Described controller is connected with two motors 6 respectively.For simplicity, in Fig. 1, omitted controller.Negotiation speed bar handle 9 and directional control handle 13 can be controlled flying speed and heading.
See Fig. 2 and Fig. 4, in the bottom of described body frame 15, be fixed with step 42,42 of top chock 41 and steps are provided with main shaft 24, the top and bottom of main shaft 24 are stretched in described top chock 41 and step 42 by bearing respectively, on that in link span section main shaft 24, be fixed with two the first belt wheels 23, on described oar axle 27, being all fixed with second belt wheel 30, two second belt wheels 30 is connected with two the first belt wheels 23 on main shaft 24 by a driving band 33 respectively.Stretch out under step 42 described main shaft 24 lower ends, on the lower extending end of described main shaft 24 and on the output shaft of described driving engine 14,25, two 25 of the first gears of the first gear are all installed and mesh together.For saving space, the output shaft of described driving engine 14 is vertical with described main shaft 24, and the first gear 25 of described main shaft 24 lower ends and the first gear 25 on driving engine 14 output shafts are finishing bevel gear cuter.By top chock 41, step 42, bearing, main shaft 24, the first belt wheel 23, the second belt wheel 30, driving band 33 and two the first gears 25, form described the first transmission device.
Described link span contains upper plate 11, middle plate 12 and lower plate 22, between this upper plate, middle plate and lower plate, parallel, their plate face is vertical with described main shaft 24, their both sides adjacent with two ducts 8 are fixed together with the outer wall of two ducts 8 respectively, on described middle plate 12, be processed with axis hole, described top chock 41 is in this axis hole.Described two the first belt wheels 23 are fixed on that section of main shaft 24 between middle plate 12 and lower plate 22.The upper plate 11 not being connected with two ducts 8, middle plate 12 and lower plate 22 front sides and rear side are respectively arranged with front connecting plate and rear connecting plate, the vertical both sides of described front connecting plate and rear connecting plate respectively with corresponding duct weld together.Between the upper end of front connecting plate and rear connecting plate, be provided with outside link plate 10, the surrounding of this outside link plate links together respectively and between the upper end of front connecting plate, rear connecting plate, two ducts 8, and outside link plate 10 center raises up, make the outside face of outside link plate 10 curved.
See Fig. 1, Fig. 7, Fig. 8, main, 15 bottoms are provided with box frame 5, be provided with the first cross bar 19, the first cross bar 19 two ends and all stretch out outside the two lateral walls of box frame 5 in box frame 5.On the first cross bar 19 in box frame 5, be fixed with worm gear 2, in the box frame 5 of worm gear 2 one sides, be provided with worm screw 1, worm screw 1 meshes together with worm gear 2.Between described worm screw 1 lower end and box frame 5 bottoms, by bearing, be rotatable shape and coordinate, worm screw 1 upper end is connected with the output shaft of a motor through behind box frame 5 tops.In box frame 5, be provided with the second cross bar 20, described the second cross bar 20 parallels with described the first cross bar 19.Described the first cross bar 19 is hollow tubular, and described the second cross bar 20 is moving type and stretches in the first cross bar 19.The second cross bar 20 1 sides in box frame 5 are provided with wheel shaft 16, be rotatable shape coordinate between wheel shaft 16 lower ends and box frame 5 bottoms by bearing, and wheel shaft 16 upper ends are connected with the output shaft of another motor 6 through behind box frame 5 tops.On wheel shaft 16, be fixed with the second gear 35, with on corresponding the first cross bar 19 sidewalls of described the second gear 35, be processed with axial long hole 45, on that section second cross bar 20 corresponding with axial long hole 45, be processed with the first teeth groove 17, by axial long hole 45, the first teeth groove 17 afterwards and on the second cross bar 20 meshes together described the second gear 35.
See Fig. 1, Fig. 2, Fig. 4, Fig. 5, Fig. 8, Fig. 9 and Figure 10, in box frame 5 both sides, be provided with longitudinal pendulum wing 18 and laterally put the wing.The centre of described longitudinal pendulum wing 18 is processed with horizontal blind hole 44, and described the first cross bar 19 stretches into and is fixed in described horizontal blind hole 44.Two are longitudinally all processed with through hole on the pendulum wing 18, and between the two sides of described through hole and longitudinally the pendulum wing 18, plane is perpendicular.In described through hole, be installed with connecting rod 3, described connecting rod 3 and described the first cross bar 19, the second cross bar 20 are vertical, the two ends of described connecting rod 3 are stretched out respectively and are longitudinally being put the both sides of the wing 18, and the two ends of described connecting rod 3 are all connected with wing piece 4, thereby form the described horizontal pendulum wing by the wing piece 4 at connecting rod 3 and connecting rod 3 two ends.On that section of connecting rod 3 in described through hole, be provided with two bearings, on that section of connecting rod 3 between described two bearings, be fixed with on longitudinal pendulum wing 18 of the 3rd gear 36, the three gear one sides and be processed with the bar hole vertical with connecting rod 3.See Figure 10, on a side pipe wall at the first cross bar 19 two ends, be processed with axial pass trough 39, connect, on longitudinal pendulum wing 18 of 3 one sides, be processed with bar hole parallel with described horizontal blind hole 44 and that be communicated with, tooth bar 40 is installed in bar hole.One end of described tooth bar 40 is fixed together by screw 38 and described axial pass trough 39 and the second cross bar 20 ends, and the second teeth groove 37 on described tooth bar 40 meshes together with the 3rd gear 36 on connecting rod 3.By the second gear 35 on the first teeth groove 17 in the middle of box frame 5, the first cross bar 19, the second cross bar 20, worm gear 2, worm screw 1, the second cross bar 20, wheel shaft 16, wheel shaft 16, the 3rd gear 36 on connecting rod 3 and described tooth bar 40 etc., form described the second transmission device.The output shaft of two motors 6 is connected with one end of wheel shaft 16 with worm screw 1 one end in described the second transmission device respectively.
See Fig. 4 and Fig. 9, be to reduce resistance, be fixed with drag reduction lid 32 in described oar axle 27 upper ends, described upper drag reduction lid 32 is for taper and its top are to being stream line pattern transition between rear.Described oar axle 27 lower ends are fixed with lower drag reduction lid 29, described lower drag reduction lid 29 for taper and its top down, the top of described lower drag reduction lid 29 is to being stream line pattern transition between lower end.Described the second belt wheel 30 and described axle, have sleeve 31 on that section of oar axle 27 of 34, and the external diameter of this sleeve and upper drag reduction cover the external diameter of 32 lower ends and external diameter that lower drag reduction covers 29 upper ends equates.
In described box frame 5 bottoms, be provided with support 21.Described support 21 is under box frame 5, and the two links together.
Claims (7)
1. can comprise body frame (15), two ducts (8), longitudinally put the wing (18), laterally put the wing, direction control mechanism, driving engine (14) and support (21) at the aircraft of complex-terrain landing, the axis of described two ducts (8) parallels; There is axle bed (34) at the center of described duct (8) inner chamber, between the inwall surrounding of axle bed (34) and duct (8), is evenly equipped with support (28); In axle bed (34), having oar axle (27) and the two to be rotatable shape coordinates; There is screw propeller (26) oar axle (27) upper end, between the outer wall of described two ducts (8), by link span, is connected; Described body frame (15) is connected to the bottom of link span, and there is seat (7) front side of body frame (15); The output shaft that it is characterized in that described driving engine (14) is connected with two oar axles (27) by the first transmission device; Described direction control mechanism is upper in body frame (15), and direction control mechanism is connected with longitudinal pendulum wing (18) with the horizontal pendulum wing respectively by the second transmission device.
2. according to claim 1 can be at the aircraft of complex-terrain landing, it is characterized in that described direction control mechanism contains two motors (6) and controller, described controller is connected with two motors (6) respectively, and the output shaft of two motors (6) is connected with described the second transmission device.
3. according to claim 1ly can, at the aircraft of complex-terrain landing, it is characterized in that the centre of described link span is fixed with top chock (41), longitudinal center's line parallel of the longitudinal center line of top chock (41) and described duct (8); In described body frame (15), be fixed with step (42), between upper and lower bearing seat, there is main shaft (24), the top and bottom of main shaft (24) are stretched in described top chock (41) and step (42) by bearing respectively, on that in link span section main shaft (24), be fixed with two the first belt wheels (23), on described oar axle (27), all have the second belt wheel (30), two second belt wheels (30) are all connected with two the first belt wheels (23) on main shaft (24) respectively by driving band (33); Stretch out under step (42) described main shaft (24) lower end, on the lower extending end of described main shaft (24) and on the output shaft of described driving engine, all has the first gear (25), between two first gears (25), meshes together; By top chock (41), step (42), bearing, main shaft (24), the first belt wheel (23), the second belt wheel (30), driving band (33) and two the first gears (25), form described the first transmission device.
4. according to claim 3 can be at the aircraft of complex-terrain landing, the output shaft that it is characterized in that described driving engine (14) is vertical with described main shaft (24), and the first gear (25) on first gear (25) of described main shaft (24) lower end and driving engine (14) output shaft is finishing bevel gear cuter.
5. according to claim 3 can be at the aircraft of complex-terrain landing, it is characterized in that described oar axle (27) upper end is fixed with drag reduction lid (32), described upper drag reduction lid (32) is for taper and its top are to being stream line pattern transition between rear; Described oar axle (27) lower end is fixed with lower drag reduction lid (29), described lower drag reduction lid (29) for taper and its top down, the top of described lower drag reduction lid (29) is to being stream line pattern transition between lower end; On that section of oar axle (27) between described the second belt wheel (30) and described axle bed (34), have sleeve (31), the external diameter of this sleeve covers the external diameter of (32) lower end with upper drag reduction and the external diameter of lower drag reduction lid (29) upper end equates.
6. according to claim 1 can be at the aircraft of complex-terrain landing, it is characterized in that box frame (5) is arranged at body frame (15) bottom, in box frame (5), have the first cross bar (19), the first cross bar (19) two ends are all stretched out outside the two lateral walls of box frame (5) and are connected with described longitudinal pendulum wing (18) respectively; On the first cross bar (19) in box frame (5), be fixed with worm gear (2), in the box frame (5) of worm gear (2) one sides, have worm screw (1), worm screw (1) meshes together with worm gear (2); Between described worm screw (1) lower end and box frame (5) bottom, be rotatable shape and coordinate, worm screw (1) upper end is connected with the output shaft of a motor (6) after passing box frame (5) top; In box frame (5), have the second cross bar (20), described the second cross bar (20) parallels with described the first cross bar (19); The second cross bar (20) one sides in box frame (5) have wheel shaft (16), between wheel shaft (16) lower end and box frame (5) bottom, be rotatable shape and coordinate, wheel shaft (16) upper end is connected with the output shaft of another motor (6) after passing box frame (5) top; On wheel shaft (16), be fixed with the second gear (35), have the first teeth groove (17) accordingly with this second gear on that section second cross bar (20), this first teeth groove and described the second gear (35) mesh together; There is transverse holes the centre of described longitudinal pendulum wing (18), the line of centers of this transverse holes is vertical with described the second cross bar (20), in transverse holes, be installed with connecting rod (3), the two ends of described connecting rod (3) are stretched out respectively and are laterally being put the both sides of the wing, the two ends of described connecting rod (3) are all connected with wing piece (4), thereby form the laterally pendulum wing by the wing piece (4) at connecting rod (3) and connecting rod (3) two ends; On that section of connecting rod (3) in described transverse holes, there are two bearings, on that section of connecting rod (3) between described two bearings, be fixed with the 3rd gear (36), on longitudinal pendulum wing (18) of the 3rd gear one side, have the bar hole vertical with connecting rod (3), the two ends of described the second cross bar (20) are stretched into respectively in the described bar hole on corresponding longitudinal pendulum wing (18); The centre in described bar hole communicates with described transverse holes, and described the second cross bar (20) outer end side adjacent with described the 3rd gear (36) has the second teeth groove (37), and this second teeth groove and described the 3rd gear (36) mesh together; By the second gear (35) on the first teeth groove (17) in the middle of box frame (5), the first cross bar (19), the second cross bar (20), worm gear (2), worm screw (1), the second cross bar (20), wheel shaft (16), wheel shaft (16), the 3rd gear (35) on connecting rod (3) and second teeth groove (37) at the second cross bar (20) two ends form described the second transmission device.
7. according to claim 6ly can, at the aircraft of complex-terrain landing, it is characterized in that described support (21) is under box frame (5), and the two link together.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320330520.XU CN203497178U (en) | 2013-06-08 | 2013-06-08 | Flying vehicle capable of taking off and landing on complex terrains |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320330520.XU CN203497178U (en) | 2013-06-08 | 2013-06-08 | Flying vehicle capable of taking off and landing on complex terrains |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203497178U true CN203497178U (en) | 2014-03-26 |
Family
ID=50328177
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320330520.XU Withdrawn - After Issue CN203497178U (en) | 2013-06-08 | 2013-06-08 | Flying vehicle capable of taking off and landing on complex terrains |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203497178U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103274048A (en) * | 2013-06-08 | 2013-09-04 | 无锡振华机械有限公司 | Aircraft capable of taking off and landing on complex terrain |
| CN104015925A (en) * | 2014-05-27 | 2014-09-03 | 南京航空航天大学 | Multi-purpose vertical take-off and landing unmanned aerial vehicle |
-
2013
- 2013-06-08 CN CN201320330520.XU patent/CN203497178U/en not_active Withdrawn - After Issue
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103274048A (en) * | 2013-06-08 | 2013-09-04 | 无锡振华机械有限公司 | Aircraft capable of taking off and landing on complex terrain |
| CN103274048B (en) * | 2013-06-08 | 2015-10-28 | 无锡振华机械有限公司 | Can at the aircraft of complex-terrain landing |
| CN104015925A (en) * | 2014-05-27 | 2014-09-03 | 南京航空航天大学 | Multi-purpose vertical take-off and landing unmanned aerial vehicle |
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| GR01 | Patent grant | ||
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| AV01 | Patent right actively abandoned |
Granted publication date: 20140326 Effective date of abandoning: 20160608 |
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| AV01 | Patent right actively abandoned |
Granted publication date: 20140326 Effective date of abandoning: 20160608 |
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| C20 | Patent right or utility model deemed to be abandoned or is abandoned |