CN200995782Y - Airplane - Google Patents
Airplane Download PDFInfo
- Publication number
- CN200995782Y CN200995782Y CN200720000872.3U CN200720000872U CN200995782Y CN 200995782 Y CN200995782 Y CN 200995782Y CN 200720000872 U CN200720000872 U CN 200720000872U CN 200995782 Y CN200995782 Y CN 200995782Y
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- fuselage
- engine
- wing
- vertical pivot
- transverse axis
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- 238000009434 installation Methods 0.000 claims description 43
- 230000005540 biological transmission Effects 0.000 claims description 9
- 230000007306 turnover Effects 0.000 abstract description 2
- 238000000034 method Methods 0.000 description 2
- 241000220317 Rosa Species 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000013016 damping Methods 0.000 description 1
- 230000003292 diminished effect Effects 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 210000003041 ligament Anatomy 0.000 description 1
- 230000009347 mechanical transmission Effects 0.000 description 1
- 230000001141 propulsive effect Effects 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 238000009987 spinning Methods 0.000 description 1
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Abstract
A novel plane, comprising a fuselage, a left wing, a right wing, a left engine, a right engine, a cockpit, an undercarriage and a tail, is characterized in that the left wing and the right wing are connected with the both sides of the fuselage symmetrically through an open and close mechanism; the left engine and the right engine are connected symmetrically with the both sides of the fuselage through a turn-over mechanism.
Description
Technical field
The utility model relates to aviation aircraft, comprise fuselage, wing, empennage, driving engine (aviation propelling unit), alighting gear and other electronic machine, transmission device, identical substantially with existing aircraft, on this basis, combine new structure design, make it to become a kind of aircraft that can the change of flight attitude.
Background technology
In the prior art, there is fixed wing the fuselage both sides of aircraft, the arranged beneath of wing has driving engine, driving engine towards fixing, driving engine can be propeller type driving engine, turbine engine, fanjet, jet engine etc., afterbody is equipped with empennage, alighting gear is equipped with in the fuselage below, this aircraft need have long runway when taking off and land, be unsuitable in the landing of the airport in dash road, can not to what kind of vertical takeoff and landing of autogyro, flight attitude, the flying method of fixed wing aircraft are single, can not change.
The utility model content
The purpose of this utility model provides a kind of type aircraft, its aerodynamic configuration and driving engine towards changing, flight attitude, flying method be maneuverability more, but vertical takeoff and landing, horizontal flight fast again has comformability widely.
For achieving the above object, the utility model is by the following technical solutions:
A kind of type aircraft has fuselage, port wing, starboard wing, Left Hand Engine, right driving engine, driving compartment, alighting gear, empennage, it is characterized in that: described port wing, starboard wing are connected the fuselage both sides symmetrically by open-and-close mechanism; Described Left Hand Engine, right driving engine are connected the fuselage both sides symmetrically by switching mechanism.By the control of open-and-close mechanism, port wing, starboard wing fuselage folding relatively forward or backward.
Described open-and-close mechanism is made up of left vertical pivot, right vertical pivot, first engine installation, second engine installation, described left vertical pivot is arranged in the fuselage rotationally, top of vertical pivot, a left side and port wing inner affixed, described first engine installation drives left vertical pivot rotation by Left Drive mechanism, and left vertical pivot rotation drives the relative fuselage of port wing and launches or gathering; Described right vertical pivot is arranged in the fuselage rotationally, the top of right vertical pivot and starboard wing inner affixed, and described second engine installation drives right vertical pivot rotation by right transmission device, and right vertical pivot rotation drives the relative fuselage of starboard wing and launches or draw in.
Described switching mechanism is made up of left transverse axis, right transverse axis, the 3rd engine installation, the 4th engine installation, described left transverse axis is arranged on the fuselage left side rotationally, left side transverse axis and Left Hand Engine are affixed, described the 3rd engine installation drives left transverse axis rotation by Left Drive mechanism, thereby make the Left Hand Engine upset, described right transverse axis is arranged on the fuselage right side rotationally, and right transverse axis and right driving engine are affixed, described the 4th engine installation drives right transverse axis rotation by right transmission device, thereby makes right driving engine upset.Also can adopt the electric tramsmission or the mechanical transmission structure of other form, specifically decide according to the kind of driving engine.
Between described wing and the fuselage stretch is housed, one end of stretch is connected with wing, and the other end and fuselage flexibly connect, stretch and the engine installation coordinated that is installed in the fuselage, drive wing and be offset forward or backward, thereby the relative fuselage of wing is launched or close up.
The wing inner end can be made wedge-shaped design fiting vibration damping with fuselage, and below the wing and between the fuselage stretch can be set, stretch is lived wing from the below diagonal ligament, to increase the stable degree of wing.Stretch is connected in the appropriate location of wing, and stretch is launched the relative fuselage of wing with the engine installation coordinated or closed up.Alighting gear can be the fixed bracket of wheeled or similar helicopter, also can be other form, can decide according to the aircraft practical use.The installation site of wing, driving engine and quantity can be decided according to the actual requirements.Also can be connected stretch with the wing appropriate location, drive the stretch displacement, realize the relative fuselage folding of wing by engine installation at forebody.
The beneficial effect of this aircraft is: wing fuselage relatively closes up or launches, and its angle of facining the wind can change, and the aerodynamic configuration of aircraft can change, and purposes is more extensive, can be widely used in military affairs, civilian, carrier-borne aircraft etc.Driving engine changes air inlet and jet direction by upset, and when driving engine rotated to be the angle of inclination by horizontal direction, the air-flow that driving engine produces is oblique, and thrust can strengthen the climb rate of aircraft obliquely down, therefore can take off on than the dash road.When engine rotation was vertical direction, the air-flow that driving engine produces was directly downward, and thrust can make the aircraft vertical takeoff and landing straight up, or aloft hovers.After aircraft rose, turn of engine was a horizontal direction, the air-flow of its generation backward, thrust forward, steadily flight fast forward of aircraft.But each spinning of left and right driving engine is one jiao mutually, aircraft can side be flown, and turn to more flexible.Empennage is made up of tailplane, vertical tail, also can realize turning to of aircraft by regulating empennage.Thereby simplify the angular adjustment of left and right driving engine.Driving engine can require and specific design for example, can be designed to the culvert formula propeller engine of class electrical motor according to aircraft power, also can give to close jet-propelled machine and use.
Description of drawings
Fig. 1 is the structural representation of the utility model embodiment one.
Fig. 2 is the front view of Fig. 1.
Fig. 3 is the A-A cutaway view Amplified image of Fig. 2.
Fig. 4 is the B-B cutaway view Amplified image of Fig. 2.
Fig. 5 is the structural representation after middle wing gathering embodiment illustrated in fig. 1, driving engine turn over and turn 90 degrees.
Fig. 6 is the structural representation of the utility model embodiment two.
Fig. 7 is the structural representation of the utility model embodiment three.
The specific embodiment
Number in the figure
1 fuselage, 2 port wings, 3 starboard wings, 4 Left Hand Engines, 5 right driving engines
6 driving compartments, 7 tailplanes, 8 left vertical pivot 801 driven gears
9 right vertical pivot 901 driven gears 10 vertical tails
11 first engine installations, 111 driving gears, 12 second engine installations, 121 driving gears
13 the 3rd engine installations, 131 bevel gears 14 the 4th engine installation, 141 bevel gears
15 left transverse axis 151 bevel gears 16 right transverse axis 161 bevel gears
17 Left Hand Engines, 18 right driving engine 9 stretch 191 hinge-points
20 stretch, 201 hinge-points
Please refer to Fig. 1, Fig. 2, the utility model is a kind of type aircraft, has fuselage 1, port wing 2, starboard wing 3, Left Hand Engine 4, right driving engine 5, driving compartment 6, tailplane 7, vertical tail 10,
Please refer to Fig. 3, open-and-close mechanism is made up of left vertical pivot 8, right vertical pivot 9, first engine installation 11, second engine installation 12.Left side vertical pivot 8 is arranged in the fuselage 1 rotationally, the top of left vertical pivot 8 and port wing 2 inner affixed, and first engine installation 11 drives left vertical pivot 8 rotations by Left Drive mechanism, thereby makes port wing 2 relative fuselages 1 expansion or gatherings.First engine installation 11 can be electrical motor or HM Hydraulic Motor.Left Drive mechanism is made of the driving gear 111 that meshes together, driven gear 801, and driving gear 111 is fixed on the output shaft of first engine installation 11, and driven gear 801 is fixed on the left vertical pivot 8.Right vertical pivot 9 is arranged in the fuselage 1 rotationally, the top of right vertical pivot 9 and starboard wing 3 inner affixed, and second engine installation 12 drives right vertical pivot 9 rotations by right transmission device, thereby makes starboard wing 3 relative fuselages 1 expansion or gatherings; Second engine installation 12 can be electrical motor or HM Hydraulic Motor.Right transmission device is made of the driving gear 121 that meshes together, driven gear 901, and driving gear 121 is fixed on the output shaft of second engine installation 12, and driven gear 901 is fixed on the right vertical pivot 9.
Please refer to Fig. 4, switching mechanism is made up of left transverse axis 15, right transverse axis 16, the 3rd engine installation 13, the 4th engine installation 14.Left side transverse axis 15 is arranged on the left side of fuselage 1 rotationally, the outer end and the Left Hand Engine 4 of left side transverse axis 15 are affixed, the 3rd engine installation 13 drives left transverse axis 15 rotations by Left Drive mechanism, thereby makes Left Hand Engine 4 upsets, and the 3rd engine installation 13 can be electrical motor or HM Hydraulic Motor.Left Drive mechanism is made of the bevel gear 131 that meshes together, bevel gear 151, and bevel gear 131 is fixed on the output shaft of the 3rd engine installation 13, and bevel gear 151 is fixed on the left transverse axis 15.Right transverse axis 16 is arranged on the right side of fuselage 1 rotationally, the outer end and the right driving engine 5 of right transverse axis 16 are affixed, the 4th engine installation 14 drives right transverse axis 16 rotations by right transmission device, thereby makes right driving engine 4 upsets, and the 4th engine installation 14 can be electrical motor or HM Hydraulic Motor.Right transmission device is made of the bevel gear 141 that meshes together, bevel gear 161, and bevel gear 141 is fixed on the output shaft of the 4th engine installation 14, and bevel gear 161 is fixed on the right transverse axis 16.
Please refer to Fig. 5, when Left Hand Engine 4, right driving engine 5 rotated to be vertical direction by horizontal direction, the air-flow that each driving engine produces was directly downward, and thrust can make the aircraft vertical takeoff and landing straight up, or aloft hovers.After the relative fuselage of wing closed up, the aircraft occupation space diminished, and can be used for military uses such as carrier-borne aircraft.In embodiment illustrated in fig. 1, Left Hand Engine 4 and right driving engine 5 all have only one, in order to increase propulsive force, Left Hand Engine and right driving engine can be two as shown in Figure 6, Left Hand Engine 17 is fixed together by connecting rod and Left Hand Engine 4, overturns jointly with Left Hand Engine 4.Right driving engine 18 is fixed together by connecting rod and right driving engine 5, overturns jointly with right driving engine 5.Left Hand Engine and right driving engine also can be many, and each driving engine adopts series connected mode to link together, common upset.Above-mentioned open-and-close mechanism, switching mechanism are opened, are stopped by the electric device automatic guidance in the prior art, manipulations such as location.
Please refer to Fig. 7, stretch 19 is equipped with in the below of port wing 2, the upper end of stretch 19 is connected in the appropriate location of port wing 2, the lower end, upper end and the fuselage 1 of stretch 19 are hinged, stretch 19 plays and supports and stretching action, with hinge-point 191 be fulcrum can be forward, swing backward, stretch 19 and above-mentioned engine installation coordinated, drive port wing 2 and be offset forward or backward, make port wing 2 relative fuselages 1 expansion or close up.Also can in fuselage 1 pendulous device be set, the lower end of this pendulous device and stretch 19 directly links, and drives stretch 19 and is offset forward or backward, and the relative forward or backward fuselage 1 of drive port wing 2 launches or closes up.
Stretch 20 is equipped with in the below of starboard wing 3, the upper end of stretch 20 is connected in the appropriate location of starboard wing 3, the lower end of stretch 20 and fuselage 1 are hinged, stretch 20 plays and supports and stretching action, with hinge-point 201 be fulcrum can be forward, swing backward, stretch 20 and above-mentioned engine installation coordinated drive starboard wing 3 and be offsets forward or backward, make starboard wing 3 relative fuselages 1 expansion or close up.Also can in fuselage 1 pendulous device be set, the lower end of this pendulous device and stretch 20 directly links, and drives stretch 20 and is offset forward or backward, and the relative forward or backward fuselage 1 of drive starboard wing 3 launches or closes up.
Claims (4)
1, a kind of type aircraft has fuselage, port wing, starboard wing, Left Hand Engine, right driving engine, driving compartment, alighting gear, empennage, it is characterized in that: described port wing, starboard wing are connected the fuselage both sides symmetrically by open-and-close mechanism; Described Left Hand Engine, right driving engine are connected the fuselage both sides symmetrically by switching mechanism.
2, a kind of type aircraft as claimed in claim 1, it is characterized in that: described open-and-close mechanism is made up of left vertical pivot, right vertical pivot, first engine installation, second engine installation, described left vertical pivot is arranged in the fuselage rotationally, top of vertical pivot, a left side and port wing inner affixed, described first engine installation drives left vertical pivot rotation by Left Drive mechanism, and left vertical pivot rotation drives the relative fuselage of port wing and launches or gathering; Described right vertical pivot is arranged in the fuselage rotationally, the top of right vertical pivot and starboard wing inner affixed, and described second engine installation drives right vertical pivot rotation by right transmission device, and right vertical pivot rotation drives the relative fuselage of starboard wing and launches or draw in.
3, a kind of type aircraft as claimed in claim 1, it is characterized in that: described switching mechanism is made up of left transverse axis, right transverse axis, the 3rd engine installation, the 4th engine installation, described left transverse axis is arranged on the fuselage left side rotationally, left side transverse axis and Left Hand Engine are affixed, described the 3rd engine installation drives left transverse axis rotation by Left Drive mechanism, thereby make the Left Hand Engine upset, described right transverse axis is arranged on the fuselage right side rotationally, right transverse axis and right driving engine are affixed, described the 4th engine installation drives right transverse axis rotation by right transmission device, thereby makes right driving engine upset.
4, a kind of type aircraft as claimed in claim 1, it is characterized in that: between described wing and the fuselage stretch is housed, one end of stretch is connected with wing, the other end and fuselage flexibly connect, stretch and the engine installation coordinated that is installed in the fuselage, drive wing and be offset forward or backward, thereby the relative fuselage of wing is launched or close up.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200720000872.3U CN200995782Y (en) | 2007-01-17 | 2007-01-17 | Airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200720000872.3U CN200995782Y (en) | 2007-01-17 | 2007-01-17 | Airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN200995782Y true CN200995782Y (en) | 2007-12-26 |
Family
ID=38994212
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN200720000872.3U Expired - Fee Related CN200995782Y (en) | 2007-01-17 | 2007-01-17 | Airplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN200995782Y (en) |
Cited By (24)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102556336A (en) * | 2011-12-30 | 2012-07-11 | 北京理工大学 | Wing fast unfolding device for folding-wing unmanned plane |
| CN102556337A (en) * | 2011-12-30 | 2012-07-11 | 北京理工大学 | Bevel gear guiding type wing unfolding mechanism |
| WO2013037178A1 (en) * | 2011-09-16 | 2013-03-21 | Zhao Wenzhi | Novel airplane |
| CN103029833A (en) * | 2011-10-08 | 2013-04-10 | 赵文志 | Novel aircraft |
| CN103043214A (en) * | 2012-12-19 | 2013-04-17 | 天津全华时代航天科技发展有限公司 | Folding type unmanned plane |
| CN103419924A (en) * | 2013-08-28 | 2013-12-04 | 哈尔滨市奇正水稻种植专业合作社 | All-round sea, land and air wing type airflow orientation aircraft |
| CN103482057A (en) * | 2013-09-17 | 2014-01-01 | 无锡振华机械有限公司 | Telescopic wing of aircraft |
| CN104071336A (en) * | 2014-06-30 | 2014-10-01 | 中国人民解放军国防科学技术大学 | Portable folding wing unmanned aerial vehicle |
| CN104812666A (en) * | 2012-01-20 | 2015-07-29 | 赵文志 | Novel airplane |
| CN105217027A (en) * | 2015-09-24 | 2016-01-06 | 苏州大闹天宫机器人科技有限公司 | Vertical takeoff and landing formula bimodal airflight equipment and control method thereof |
| CN105539807A (en) * | 2016-01-15 | 2016-05-04 | 杨汉波 | Deformable airplane with front-rear double propeller and front-rear double wing |
| CN105667763A (en) * | 2016-03-30 | 2016-06-15 | 仲贤辉 | Folding wing type unmanned aerial vehicle for municipal garden landscaping |
| CN105667762A (en) * | 2016-03-30 | 2016-06-15 | 仲贤辉 | Unmanned aerial vehicle for municipal gardens |
| CN106043082A (en) * | 2016-06-15 | 2016-10-26 | 陈昌志 | Flying ambulance car |
| CN106163919A (en) * | 2014-04-04 | 2016-11-23 | 空中客车英国运营有限责任公司 | Including the aircraft of foldable air dynamical structure and the method manufacturing the foldable air dynamical structure for aircraft |
| CN106394868A (en) * | 2016-12-22 | 2017-02-15 | 湖南文理学院 | Folding type unmanned plane wing |
| CN106494608A (en) * | 2015-09-06 | 2017-03-15 | 陈康 | Many shrouded propeller variable geometry Electric aircrafts |
| CN106800085A (en) * | 2009-09-09 | 2017-06-06 | 威罗门飞行公司 | Elevon control system |
| CN107458578A (en) * | 2017-08-09 | 2017-12-12 | 中北大学 | Imitative flying fish formula flight bus |
| CN108082452A (en) * | 2017-12-04 | 2018-05-29 | 安徽工程大学 | A kind of jet reversing arrangement of aircraft |
| CN108394561A (en) * | 2018-04-01 | 2018-08-14 | 周佰平 | A kind of high-altitude remove haze unmanned plane |
| CN110395381A (en) * | 2018-04-24 | 2019-11-01 | 广州刀锋智能科技有限公司 | A kind of Intelligent flight device |
| CN111942597A (en) * | 2020-06-10 | 2020-11-17 | 魏晶晶 | Novel hybrid aircraft |
| CN113232853A (en) * | 2021-04-02 | 2021-08-10 | 陈�峰 | Short-distance take-off and landing aircraft |
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2007
- 2007-01-17 CN CN200720000872.3U patent/CN200995782Y/en not_active Expired - Fee Related
Cited By (33)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112124563A (en) * | 2009-09-09 | 2020-12-25 | 威罗门飞行公司 | Elevon control system |
| CN106800085A (en) * | 2009-09-09 | 2017-06-06 | 威罗门飞行公司 | Elevon control system |
| CN106800085B (en) * | 2009-09-09 | 2020-08-18 | 威罗门飞行公司 | Elevon control system |
| WO2013037178A1 (en) * | 2011-09-16 | 2013-03-21 | Zhao Wenzhi | Novel airplane |
| CN103029833A (en) * | 2011-10-08 | 2013-04-10 | 赵文志 | Novel aircraft |
| CN102556337A (en) * | 2011-12-30 | 2012-07-11 | 北京理工大学 | Bevel gear guiding type wing unfolding mechanism |
| CN102556336A (en) * | 2011-12-30 | 2012-07-11 | 北京理工大学 | Wing fast unfolding device for folding-wing unmanned plane |
| CN104812666A (en) * | 2012-01-20 | 2015-07-29 | 赵文志 | Novel airplane |
| CN103043214A (en) * | 2012-12-19 | 2013-04-17 | 天津全华时代航天科技发展有限公司 | Folding type unmanned plane |
| CN103419924B (en) * | 2013-08-28 | 2016-02-24 | 哈尔滨市奇正水稻种植专业合作社 | The all-round wing-type air-flow directional aircraft of aeroamphibious |
| CN103419924A (en) * | 2013-08-28 | 2013-12-04 | 哈尔滨市奇正水稻种植专业合作社 | All-round sea, land and air wing type airflow orientation aircraft |
| CN103482057B (en) * | 2013-09-17 | 2015-11-25 | 无锡振华机械有限公司 | The telescopic wing of aircraft |
| CN103482057A (en) * | 2013-09-17 | 2014-01-01 | 无锡振华机械有限公司 | Telescopic wing of aircraft |
| CN106163919A (en) * | 2014-04-04 | 2016-11-23 | 空中客车英国运营有限责任公司 | Including the aircraft of foldable air dynamical structure and the method manufacturing the foldable air dynamical structure for aircraft |
| CN104071336A (en) * | 2014-06-30 | 2014-10-01 | 中国人民解放军国防科学技术大学 | Portable folding wing unmanned aerial vehicle |
| CN104071336B (en) * | 2014-06-30 | 2016-04-27 | 中国人民解放军国防科学技术大学 | Portable folding wing unmanned plane |
| CN106494608A (en) * | 2015-09-06 | 2017-03-15 | 陈康 | Many shrouded propeller variable geometry Electric aircrafts |
| CN105217027A (en) * | 2015-09-24 | 2016-01-06 | 苏州大闹天宫机器人科技有限公司 | Vertical takeoff and landing formula bimodal airflight equipment and control method thereof |
| CN105539807A (en) * | 2016-01-15 | 2016-05-04 | 杨汉波 | Deformable airplane with front-rear double propeller and front-rear double wing |
| CN105667762A (en) * | 2016-03-30 | 2016-06-15 | 仲贤辉 | Unmanned aerial vehicle for municipal gardens |
| CN105667763A (en) * | 2016-03-30 | 2016-06-15 | 仲贤辉 | Folding wing type unmanned aerial vehicle for municipal garden landscaping |
| CN105667763B (en) * | 2016-03-30 | 2018-01-05 | 西安京东天鸿科技有限公司 | A kind of municipal afforestation folding wings unmanned plane |
| CN105667762B (en) * | 2016-03-30 | 2018-01-05 | 西安京东天鸿科技有限公司 | A kind of municipal gardens unmanned plane |
| CN106043082A (en) * | 2016-06-15 | 2016-10-26 | 陈昌志 | Flying ambulance car |
| CN106394868A (en) * | 2016-12-22 | 2017-02-15 | 湖南文理学院 | Folding type unmanned plane wing |
| CN107458578A (en) * | 2017-08-09 | 2017-12-12 | 中北大学 | Imitative flying fish formula flight bus |
| CN108082452A (en) * | 2017-12-04 | 2018-05-29 | 安徽工程大学 | A kind of jet reversing arrangement of aircraft |
| CN108394561A (en) * | 2018-04-01 | 2018-08-14 | 周佰平 | A kind of high-altitude remove haze unmanned plane |
| CN108394561B (en) * | 2018-04-01 | 2021-05-25 | 南通寓无疆科技有限公司 | High-altitude haze-removing unmanned aerial vehicle |
| CN110395381A (en) * | 2018-04-24 | 2019-11-01 | 广州刀锋智能科技有限公司 | A kind of Intelligent flight device |
| CN110395381B (en) * | 2018-04-24 | 2021-06-22 | 广州刀锋智能科技有限公司 | Intelligent aircraft |
| CN111942597A (en) * | 2020-06-10 | 2020-11-17 | 魏晶晶 | Novel hybrid aircraft |
| CN113232853A (en) * | 2021-04-02 | 2021-08-10 | 陈�峰 | Short-distance take-off and landing aircraft |
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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: 20071226 Termination date: 20160117 |
|
| EXPY | Termination of patent right or utility model |