CN204998771U - Aircraft of VTOL - Google Patents
Aircraft of VTOL Download PDFInfo
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- CN204998771U CN204998771U CN201520537810.0U CN201520537810U CN204998771U CN 204998771 U CN204998771 U CN 204998771U CN 201520537810 U CN201520537810 U CN 201520537810U CN 204998771 U CN204998771 U CN 204998771U
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Abstract
The utility model provides a muffjoint duck wing section of verting is controlled on the top through verting, vert to control telescopic one end and the duck wing section of verting fixed connection, should vert to control the telescopic other end and rotate and penetrate this duck cautiously in the root that aircraft of VTOL, at the thriving root of the anterior both sides of its fuselage each fixed connection duck, the thriving root of this duck to be connected with the servo motor transmission, rotate this leading screw of installation in one side of this duck wing section of verting, be equipped with corresponding fin girder canned paragraph at two vertical tail opposite sides, connect the fin section of verting through rotating between the fin girder canned paragraph of both sides, rotate the installation rear -mounted propeller in middle part one side of this fin section of verting, this leading screw and rear -mounted propeller are connected with the engine -drive through bevel gear pair and transmission shaft respectively, and the transmission shaft passes in controlling the sleeve from verting. The beneficial effects of the utility model are that: the convenience, oil consumption rate of taking off and land is low, small in noise, vibration are little, simple structure, the integrated production of modularization of easily operating, be convenient for.
Description
Technical field
The utility model relates to a kind of aircraft, specifically a kind of aircraft of vertical takeoff and landing, can meet the demand of multiple military affairs, public affair and civilian task.
Background technology
At present, aircraft is mainly divided into autogyro and the large class of fixed wing aircraft two.Autogyro has superior low speed low-altitude performance, and can take off in very low range or land, but its efficiency and speed are all lower, and these 2 have become the key factor restricting the wider application of autogyro.Fixed wing aircraft flying radius is large, and efficiency is high, but low-altitude low-speed performance is relatively poor, higher to airport conditional request, when without runway, cannot obtain enough lift and take off and landing.The high-performance cruise performance of the vertical takeoff and landing of autogyro with hover performance and fixed wing aircraft combines by the advantage therefore in conjunction with this two classes aircraft, has become current a lot of people to carry out the emphasis direction of aircraft research.
Prior art has one " dragonfly " X-50A unmanned plane, is a aircraft experimental engine that can take off vertically and land.This study program is proposed by U.S. national defense advanced research projects agency, and Boeing is responsible for Development Prototype, and this aircraft is referred to as canard rotor/wing unmanned plane." dragonfly " X-50A is designed with special wide rotor, when taking off landing, this wide rotor is exactly the screw propeller on unmanned plane, when aircraft is flat fly time, rotor is locked on fuselage, it just becomes fixed wing, aircraft with fixed-wing jet airplane mode flight, thus makes this aircraft both have the same vertical takeoff and landing of autogyro and hovering ability, again can as fixed wing aircraft high speed cruise flight.
The topmost technical matters of above-mentioned aircraft comes from the flight control problem during lifting/flat flies patten transformation.Flat fly pattern when aircraft is changed into by the pattern of taking off vertically, or change into vertical landing pattern in a flash by the flat pattern of flying, level speed levels off to zero, and aircraft cannot obtain any lift within this short time, is easy to cause aircraft out of control.At present, all have control problem during this patten transformation in lifting/flat " rotor/wing " technology flying patten transformation.Patten transformation generally needs tens seconds, and fast also wants tens seconds, changes too fast mistake and all easily causes aircraft control out of control slowly.
Another prior art is V-22 " osprey " the formula tiltrotor manufactured by American Bell Incorporated and Boeing's collaborated design that United States Corps started in 2007 to equip.When aircraft vertical take-off and landing, rotor shaft perpendicular to ground, in cross-arranging type helicopter flight state, and can aloft hover, front and back flight; After tiltrotor is taken off and reach a certain height, rotor shaft can tilt forward 90 ° of angles, is the level of state, and rotor is used as pulling force screw propeller and is used, and now tilting rotor function does distance flight with higher speed as fixed wing aircraft.V-22 tiltrotor has merged the advantage of autogyro and fixed wing aircraft, is successful case rare in tilting rotor technology.
Above-mentioned tiltrotor has many advantages compared with general autogyro, fixed wing aircraft, but also there is some shortcomings part, be mainly manifested in: structure design, maneuvering and control technology and maneuvering system dynamics design, aerodynamic characteristic is complicated, technical matters difficulty is higher.
All the time, what people made every effort to study a kind of novel pneumatic layout can vertical takeoff and landing, the aircraft that structure is simple, safe and reliable, a kind of aircraft not having aforesaid drawbacks, thus this double mode aircraft is widely used.
Summary of the invention
The utility model compensate for the deficiencies in the prior art, aircraft continues to provide lift in autogyro landing pattern and fixed wing aircraft cruise mode switching process to provide one to ensure, offline mode is made to change smooth transition, to guarantee that a kind of of flight safety can the aircraft of vertical takeoff and landing.
One of the technical solution of the utility model is: a kind of aircraft of vertical takeoff and landing, comprise fuselage, host wing, two vertical tail, preposition screw propeller, rear-mounted propeller and driving engine, host wing is provided with in the both sides of fuselage, two vertical tail is provided with on the two sides of tail of fuselage, at the front and rear of fuselage, preposition screw propeller is housed respectively, rear-mounted propeller, preposition screw propeller is connected with driving engine by transmission device with the axle of rear-mounted propeller, it is characterized in that, the canard wing root with its one is provided with in the front part sides of described fuselage, the top of this canard wing root is by the manipulation sleeve connection one canard section of verting of verting, vert manipulation sleeve one end be fixedly connected with the canard section of verting, this other end verting manipulation sleeve rotates and penetrates in this canard wing root, and be connected with servomotor, rotate in the side of this canard section of verting and this preposition screw propeller is installed, being provided with corresponding fin girder canned paragraph at described two vertical tail opposite sides, by being rotationally connected the empennage section of verting between the fin girder canned paragraph of both sides, in the side, middle part of this empennage section of verting, rear-mounted propeller being installed, this preposition screw propeller is connected with driving engine with transmission shaft respectively by bevel-gear pair with rear-mounted propeller, and transmission shaft passes in the manipulation sleeve that verts, fin girder canned paragraph is identical with type of drive with the connection mode between described canard wing root and the canard section of verting with type of drive with the connection mode of the empennage section of verting.
Two of the technical solution of the utility model is: a kind of aircraft of vertical takeoff and landing, comprise fuselage, host wing, two vertical tail, host wing is provided with in the both sides of fuselage, two vertical tail is provided with on the two sides of tail of fuselage, it is characterized in that, the canard wing root with its one is provided with in the front part sides of described fuselage, the top of this canard wing root is by the manipulation sleeve connection one canard section of verting of verting, vert manipulation sleeve one end be fixedly connected with the canard section of verting, this other end verting manipulation sleeve rotates and penetrates in this canard wing root, and be connected with servomotor, whirlpool spray, turbofan or turbo oar engine are housed in the side of this canard section of verting, being provided with corresponding fin girder canned paragraph at described two vertical tail opposite sides, by being rotationally connected the empennage section of verting between the fin girder canned paragraph of both sides, the spray of another whirlpool, turbofan or turbo oar engine being installed in the side, middle part of this empennage section of verting, this fin girder canned paragraph is identical with type of drive with the connection mode between described canard wing root and the canard section of verting with type of drive with the connection mode of the empennage section of verting.
In above-mentioned two kinds of technical schemes: the polygonal breach being provided with a semicircle or semicircle shape between described two vertical tails in the middle part of tail cone.
Described host wing is triangle, and is provided with the dihedral angle; Merge at the postmedian of described fuselage and triangle host wing, fuselage extends back and shrinks, and terminates in the indentation, there between two vertical tail.
Described canard wing root and the trapezoidal straight wing of the canard section of verting composition, and be arranged on the driving compartment front lower place of fuselage.
Described host wing is integrated or makes folding structure.
The beneficial effects of the utility model are:
1, landing is convenient: do not need airport and runway during the utility model landing, when turning out for work, required support is less, and support expense is extremely low.
2, gas consumption rate is low: the utility model is when cruising flight, and because wing can produce lift, screw propeller only enters, so gas consumption rate is more much lower than autogyro for pushing away (drawing).
3, noise is little: the mode with fixed wing aircraft when the utility model is because cruising is flown, and therefore noise ratio autogyro is much smaller.
4, vibrate little: because screw propeller layout of the present utility model is at the wing far-end away from fuselage, therefore the extent of vibration of its passenger cabin is more much lower than general autogyro.
5, structure is simple, is easy to operation, is convenient to the integrated production of modularization.
Different model of the present utility model can meet the demand of multiple military affairs, public affair and civilian task, and can give on scene commander official and more select and greater flexibility.At military aspect, it is particularly suitable for the task of performing the aspects such as hit the beach, fight search and rescue, special operations.In civilian, the utility model is applicable to the tasks such as anti-riot special duty in the city day by day blocked up, fire-fighting command, aviation training, First aid station, news tracking completely.As air taxi, mid-air-bus can going sightseeing in area, archipelago and coastland, also transportation burden can be performed not having any area on airport, be specially adapted to the development and construction of economically less developed region, an important component part of modernization air transport network can be become.
Accompanying drawing explanation
Fig. 1 is integral structure (put down and the fly cruising condition) schematic diagram of the utility model side;
Fig. 2 is the birds-eye view of Fig. 1;
Fig. 3 is the left view of Fig. 1;
Fig. 4 is the amplification view at A place in Fig. 2;
Fig. 5 is the amplification view at B place in Fig. 2;
Fig. 6 is the integral structure schematic diagram of the utility model vertical lift state side.
In figure: 1-fuselage; 2-canard wing root; The 3-canard section of verting; The preposition screw propeller of 4-; 5-host wing; The two vertical tail of 6-; 7-fin girder canned paragraph; The 8-empennage section of verting; 9-rear-mounted propeller; 10-verts manipulation sleeve; 11-(screw propeller) driving engine; 12-transmission shaft; 13-gear pair, 14, servomotor, 15, half round cut, 16, the empennage section of verting axle drive shaft, 17, flexible axle.
Detailed description of the invention
As shown in figs 1 to 6, the aircraft of a kind of vertical takeoff and landing of the utility model, comprise fuselage 1, host wing 5, two vertical tail 6, preposition screw propeller 4, rear-mounted propeller 9 and driving engine 11, host wing 5 is provided with in the both sides of fuselage 1, two vertical tail 6 is provided with on the two sides of tail of fuselage, at the front and rear of fuselage, preposition screw propeller 4, rear-mounted propeller 9 are housed respectively, the axle of preposition screw propeller 4 and rear-mounted propeller 9 is in transmission connection by transmission device and driving engine 11.The canard wing root 2 with its one is provided with in the front part sides of described fuselage 1, the top of this canard wing root 2 connects a canard section of verting 3 by the manipulation sleeve 10 that verts, vert manipulation sleeve 10 one end be fixedly connected with the canard section of verting 3, this other end verting manipulation sleeve 10 rotates and penetrates in this canard wing root 2, and is in transmission connection with servomotor 14; Rotate in the side of this canard section of verting 3 and this preposition screw propeller 4 is installed.During work, servomotor 14 drives the canard section of verting 3 to turn forward by bevel-gear pair 13 and turn 90 degrees, and preposition screw propeller 4 turn 90 degrees (axially verting between vertical and horizontal of screw propeller) along with the canard section of verting 3 is inclined with angle.
Being provided with corresponding fin girder canned paragraph 7 at described two vertical tails 6 opposite side, by being rotationally connected the empennage section of verting 8 between the fin girder canned paragraph 7 of both sides, in the side, middle part of this empennage section of verting 8, rear-mounted propeller 9 being installed.
This preposition screw propeller 4 and rear-mounted propeller 9 are in transmission connection (at the two ends of transmission shaft 12, a bevel-gear pair 13 being respectively housed in figure) respectively by bevel-gear pair 13 and transmission shaft 12 with described driving engine 11.
The connection mode of fin girder canned paragraph 7 and the empennage section of verting 8 and type of drive of verting (see Fig. 5) can be identical with type of drive of verting with connection mode between described canard wing root 2 and the canard section of verting 3.Also can in two vertical tail 6(Fig. 5 of side above) in not shown with servomotor 14(by flexible axle 17, the empennage section of verting axle drive shaft 16 and a bevel-gear pair 13) be in transmission connection, flexible axle 17 is connected with the two ends of bevel-gear pair 13 respectively with one end of the empennage section of verting axle drive shaft 16, the other end of flexible axle 17 is connected with servomotor 14, the other end of the empennage section of verting axle drive shaft 16 is fixedly connected with the empennage section of verting 8, drives the empennage section of verting 8 to do the deflection of 0-90 degree.In the diagram side two vertical tails 6 by bevel-gear pair 13 and transmission shaft 12 not shown with driving engine 11() be in transmission connection.
The polygonal breach 15 of a semicircle or semicircle shape is provided with in the middle part of tail cone between described two vertical tails 6.
Described host wing 5 is triangle, and is provided with the dihedral angle, to improve the lateral stability of aircraft.Merge at the postmedian of described fuselage 1 and triangle host wing, fuselage 1 extends back and shrinks, and terminates in breach 15 place between two vertical tail 6.Take off at aircraft vertical, when landing, the air-flow vertically downward that rear-mounted propeller produces can be smooth and easy by breach 15, forms static air cushion in the below of host wing 5.
The axis direction of rear-mounted propeller 9 of the present utility model is the same with preposition screw propeller 4 can when offline mode switch transition flies, along pitch axis by vertical angle forward 90 degree vert.Three screw propellers are triangularly arranged, and form a stable lifting table, aircraft can be made to take off reposefully, land.Three screw propellers are arranged in the horizontal surface of sustained height.
Three screw propellers are set to vert along pitch axis in the horizontal direction and between vertical direction, to change offline mode.Screw propeller also can vert the angle (three-sixth turn of can inclining in theory) of 30 degree backward, makes aircraft can inverted flight, for aircraft reconnaissance hover landing provides certain convenience.
Described canard wing root 2 and the canard section of verting 3 form the trapezoidal straight wing, and are arranged on the driving compartment front lower place of fuselage.
Described host wing 5 is with fuselage one or makes folding structure, parks area to save, and is convenient to transport and naval vessel use.
Preposition screw propeller 4 in above-described embodiment and rear-mounted propeller 9 can spray with whirlpool, turbofan or turbo oar engine replace (not shown), save the driving engine 11 for driving propeller rotational, transmission shaft 12 and bevel-gear pair 13, other structures are same as the previously described embodiments simultaneously.
The described canard section of verting 3, the empennage section of verting 8 and propelling unit as screw propeller, whirlpool spray, turbofan or turbo oar engine vert with angle.
Operation and control system of the present utility model is routine techniques, is namely controlled driving engine 11 by control system, realizes controlling the rotating speed of each screw propeller; By control system, servomotor 14 is controlled, realize to each prop shaft to the control of verting, thus realize different flight attitudes (be elevated or put down and fly).
Principle of work of the present utility model (for embodiment shown in the drawings) is: when aircraft be in take off vertically state time (as shown in Figure 6), the axes normal of preposition screw propeller 4 and rear-mounted propeller 9 is in horizontal surface.Driving engine 11 drives preposition screw propeller 4 and rear-mounted propeller 9 to rotate by transmission shaft 12 and bevel-gear pair 13, the air-flow that screw propeller produces, and forms a static air cushion in aircraft bottom.Along with the rising of aircraft, by the manipulation sleeve 10 that verts, and flexible axle 17, the empennage section of verting axle drive shaft 16 and a bevel-gear pair 13 handle before and after screw propeller axis along pitch axis by vertical angle forward 90 degree vert, vert in process, the air-flow that preposition screw propeller 4 sprays to the back lower place creates the component of both direction, one is pulling force forward, and another is the lift manufacturing air cushion 5 times at host wing and produce.Rear-mounted propeller 9 also produces two component simultaneously, and one is thrust forward, and another is the lift that antagonistic force jet downwards produces.Aircraft is in offline mode switching process, and the lift that this two component are formed by stacking, can meet the aerodynamic force requirement controlled needed for aircraft flight completely.
Aircraft when landing, manipulation theoretical with take off identical, just order is on the contrary.
Aircraft vertical takeoff condition as shown in Figure 6, by the manipulation sleeve 10 that verts, each propeller axis along pitch axis by vertical angle forward 0-90 degree vert, aircraft is converted to by taking off vertically and flat flies cruising condition, as Figure 1-Figure 5, now the lift of aircraft is provided by wing completely.
Driving engine 11 of the present utility model can adopt combustion engine or electrical motor.
Above schematic diagram is all for screw propeller propelling, and by other form propelling units as whirlpool spray, turbofan, whirlpool slurry driving engine, reason is identical, just propeller system is replaced by whirlpool spray, turbofan, whirlpool slurry propelling unit, and again calculates related data.
Claims (6)
1. the aircraft of a vertical takeoff and landing, comprise fuselage, host wing, two vertical tail, preposition screw propeller, rear-mounted propeller and driving engine, host wing is provided with in the both sides of fuselage, two vertical tail is provided with on the two sides of tail of fuselage, at the front and rear of fuselage, preposition screw propeller is housed respectively, rear-mounted propeller, preposition screw propeller is connected with driving engine by transmission device with the axle of rear-mounted propeller, it is characterized in that, the canard wing root with its one is provided with in the front part sides of described fuselage, the top of this canard wing root is by the manipulation sleeve connection one canard section of verting of verting, vert manipulation sleeve one end be fixedly connected with the canard section of verting, this other end verting manipulation sleeve rotates and penetrates in this canard wing root, and be connected with servomotor, rotate in the side of this canard section of verting and this preposition screw propeller is installed, being provided with corresponding fin girder canned paragraph at described two vertical tail opposite sides, by being rotationally connected the empennage section of verting between the fin girder canned paragraph of both sides, in the side, middle part of this empennage section of verting, rear-mounted propeller being installed, this preposition screw propeller is connected with driving engine with transmission shaft respectively by bevel-gear pair with rear-mounted propeller, and transmission shaft passes in the manipulation sleeve that verts, fin girder canned paragraph is identical with type of drive with the connection mode between described canard wing root and the canard section of verting with type of drive with the connection mode of the empennage section of verting.
2. the aircraft of a vertical takeoff and landing, comprise fuselage, host wing, two vertical tail, host wing is provided with in the both sides of fuselage, two vertical tail is provided with on the two sides of tail of fuselage, it is characterized in that, the canard wing root with its one is provided with in the front part sides of described fuselage, the top of this canard wing root is by the manipulation sleeve connection one canard section of verting of verting, vert manipulation sleeve one end be fixedly connected with the canard section of verting, this other end verting manipulation sleeve rotates and penetrates in this canard wing root, and is connected with servomotor; Whirlpool spray, turbofan or turbo oar engine are housed in the side of this canard section of verting; Being provided with corresponding fin girder canned paragraph at described two vertical tail opposite sides, by being rotationally connected the empennage section of verting between the fin girder canned paragraph of both sides, the spray of another whirlpool, turbofan or turbo oar engine being installed in the side, middle part of this empennage section of verting; This fin girder canned paragraph is identical with type of drive with the connection mode between described canard wing root and the canard section of verting with type of drive with the connection mode of the empennage section of verting.
3. the aircraft of vertical takeoff and landing according to claim 1 and 2, is characterized in that, is provided with the polygonal breach of a semicircle or semicircle shape between described two vertical tails in the middle part of tail cone.
4. the aircraft of vertical takeoff and landing according to claim 1, is characterized in that, described host wing is triangle, and is provided with the dihedral angle; Merge at the postmedian of described fuselage and triangle host wing, fuselage extends back and shrinks, and terminates in the indentation, there between two vertical tail.
5. the aircraft of vertical takeoff and landing according to claim 1 and 2, is characterized in that, described canard wing root and the trapezoidal straight wing of the canard section of verting composition, and is arranged on the driving compartment front lower place of fuselage.
6. the aircraft of vertical takeoff and landing according to claim 1 and 2, is characterized in that, described host wing is integrated or makes folding structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520537810.0U CN204998771U (en) | 2015-07-23 | 2015-07-23 | Aircraft of VTOL |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520537810.0U CN204998771U (en) | 2015-07-23 | 2015-07-23 | Aircraft of VTOL |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204998771U true CN204998771U (en) | 2016-01-27 |
Family
ID=55155672
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520537810.0U Expired - Fee Related CN204998771U (en) | 2015-07-23 | 2015-07-23 | Aircraft of VTOL |
Country Status (1)
| Country | Link |
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| CN (1) | CN204998771U (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106143896A (en) * | 2016-08-05 | 2016-11-23 | 朱幕松 | Go straight up to fly solar energy unmanned plane soon |
| CN106989816A (en) * | 2017-06-02 | 2017-07-28 | 中国航发南方工业有限公司 | Turbo oar engine vibration-measuring sensor is calibrated and measurement apparatus |
| CN108454819A (en) * | 2018-04-23 | 2018-08-28 | 成都航空职业技术学院 | Three-surface configuration VTOL general-purpose aircraft |
| CN109163808A (en) * | 2018-08-29 | 2019-01-08 | 深圳市旭发智能科技有限公司 | A kind of news method for tracing and system based on far infrared |
| CN111655576A (en) * | 2018-02-22 | 2020-09-11 | 小鹰公司 | Fixed wing aircraft with rear rotor |
| CN112960100A (en) * | 2021-03-03 | 2021-06-15 | 北京博鹰通航科技有限公司 | Aircraft and control method thereof |
| CN114026022A (en) * | 2019-08-02 | 2022-02-08 | 小鹰公司 | Fixed wing aircraft with rear rotor and T-shaped empennage |
| WO2022067401A1 (en) * | 2020-09-29 | 2022-04-07 | Alberto Carlos Pereira Filho | Vertical-take-off aerial vehicle with aerofoil-shaped integrated fuselage and wings |
-
2015
- 2015-07-23 CN CN201520537810.0U patent/CN204998771U/en not_active Expired - Fee Related
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106143896A (en) * | 2016-08-05 | 2016-11-23 | 朱幕松 | Go straight up to fly solar energy unmanned plane soon |
| CN106143896B (en) * | 2016-08-05 | 2018-08-31 | 朱幕松 | Go straight up to winged solar energy unmanned plane soon |
| CN106989816A (en) * | 2017-06-02 | 2017-07-28 | 中国航发南方工业有限公司 | Turbo oar engine vibration-measuring sensor is calibrated and measurement apparatus |
| CN111655576A (en) * | 2018-02-22 | 2020-09-11 | 小鹰公司 | Fixed wing aircraft with rear rotor |
| CN111655576B (en) * | 2018-02-22 | 2024-01-23 | 小鹰公司 | Fixed wing aircraft with rear rotor |
| CN108454819A (en) * | 2018-04-23 | 2018-08-28 | 成都航空职业技术学院 | Three-surface configuration VTOL general-purpose aircraft |
| CN109163808A (en) * | 2018-08-29 | 2019-01-08 | 深圳市旭发智能科技有限公司 | A kind of news method for tracing and system based on far infrared |
| CN114026022A (en) * | 2019-08-02 | 2022-02-08 | 小鹰公司 | Fixed wing aircraft with rear rotor and T-shaped empennage |
| WO2022067401A1 (en) * | 2020-09-29 | 2022-04-07 | Alberto Carlos Pereira Filho | Vertical-take-off aerial vehicle with aerofoil-shaped integrated fuselage and wings |
| GB2614832A (en) * | 2020-09-29 | 2023-07-19 | Carlos Pereira Atibaia Filho Alberto | Vertical-take-off aerial vehicle with aerofoil-shaped integrated fuselage and wings |
| EP4223636A4 (en) * | 2020-09-29 | 2024-05-15 | Alberto Carlos Pereira Filho | Vertical-take-off aerial vehicle with aerofoil-shaped integrated fuselage and wings |
| CN112960100A (en) * | 2021-03-03 | 2021-06-15 | 北京博鹰通航科技有限公司 | Aircraft and control method thereof |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160127 Termination date: 20160723 |
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| CF01 | Termination of patent right due to non-payment of annual fee |