CN111216880B - Undercarriage control mechanism of small aircraft - Google Patents
Undercarriage control mechanism of small aircraft Download PDFInfo
- Publication number
- CN111216880B CN111216880B CN202010080469.6A CN202010080469A CN111216880B CN 111216880 B CN111216880 B CN 111216880B CN 202010080469 A CN202010080469 A CN 202010080469A CN 111216880 B CN111216880 B CN 111216880B
- Authority
- CN
- China
- Prior art keywords
- support
- lifting
- seat
- lifting support
- airplane
- 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.)
- Active
Links
- 230000007246 mechanism Effects 0.000 title claims abstract description 9
- 238000009434 installation Methods 0.000 claims abstract description 4
- 239000006096 absorbing agent Substances 0.000 claims description 9
- 230000035939 shock Effects 0.000 claims description 9
- 238000000034 method Methods 0.000 claims description 4
- 230000008569 process Effects 0.000 claims description 4
- 230000003014 reinforcing effect Effects 0.000 claims description 3
- 239000000872 buffer Substances 0.000 claims description 2
- 238000005096 rolling process Methods 0.000 claims description 2
- 230000005540 biological transmission Effects 0.000 abstract description 2
- 230000003116 impacting effect Effects 0.000 description 2
- 230000004075 alteration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 238000005728 strengthening Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/34—Alighting gear characterised by elements which contact the ground or similar surface wheeled type, e.g. multi-wheeled bogies
-
- 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
- B64C25/22—Operating mechanisms fluid
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/58—Arrangements or adaptations of shock-absorbers or springs
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/34—Alighting gear characterised by elements which contact the ground or similar surface wheeled type, e.g. multi-wheeled bogies
- B64C2025/345—Multi-wheel bogies having one or more steering axes
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Actuator (AREA)
- Forklifts And Lifting Vehicles (AREA)
Abstract
The invention relates to the technical field of undercarriage, in particular to an undercarriage control mechanism of a small airplane, which comprises a driving box, a first lifting support and a second lifting support, wherein side supports arranged on two sides of the driving box are respectively connected with the first lifting support and the second lifting support, and the undercarriage control mechanism has the advantages that: according to the invention, the driving box is respectively connected with one airplane wheel through the first lifting support and the second lifting support arranged on the two sides, and compared with a structure in which only one airplane wheel is arranged in a transmission manner, the driving box has better stability when an airplane glides; the invention can complete the lifting control of the first lifting bracket and the second lifting bracket through a set of driving equipment, thereby increasing the stability of the airplane during sliding and reducing the installation space of the driving equipment.
Description
Technical Field
The invention relates to the technical field of undercarriages, in particular to an undercarriage control mechanism of a small airplane.
Background
Landing gear is an accessory device used on the lower portion of an aircraft to support the aircraft for takeoff and landing or for ground movement during taxiing. In the landing gear used by a common small-sized airplane, a front main wheel is usually arranged at the front end of the airplane, and a group of rear main wheels are respectively arranged at two sides behind the airplane, so that the airplane has better sliding stability, and the arrangement of the rear main wheels is increased, so that a more favorable option is provided; the landing gear is driven to ascend and descend by a hydraulic driving device (such as a hydraulic cylinder), and the landing gear can transmit the impact force to the connected hydraulic device during landing of the airplane, so that the hydraulic driving device is easily damaged by the instantaneously caused impact force.
Disclosure of Invention
The present invention is directed to a landing gear control mechanism for a small aircraft to solve the problems set forth in the background above.
In order to achieve the purpose, the invention provides the following technical scheme: a landing gear control mechanism of a small airplane comprises a driving box, a first lifting support and a second lifting support, wherein two side ends of the driving box are fixedly connected with side supports through bolts, a notch is formed in the middle of each side support, a pair of supporting shaft seats are integrally formed on the outer side wall of each side support and located on two sides of the notch, the supporting shaft seats arranged on the side supports at two ends of the driving box are respectively connected with the first lifting support and the second lifting support, each of the first lifting support and the second lifting support is composed of a main supporting column and an auxiliary wheel socket, a shaft barrel seat is arranged at the upper end of the main supporting column and is rotatably connected with the supporting shaft seats through a rotating shaft, a main wheel socket in a U-shaped support is arranged at the lower end of the main supporting column, the auxiliary wheel socket is in a U-shaped support, wheels are rotatably connected between two side supporting rod ends of the auxiliary wheel socket, the end parts of two side supporting rods of the main wheel socket are respectively hinged with the middle parts, the utility model discloses a hydraulic lifting device, including main pillar, shaft cylinder seat, crank, jack, telescopic link, top seat, connecting rod, telescopic link, crank tip, crank fixed connection has hydraulic cylinder, hydraulic cylinder's telescopic link sets up upwards perpendicularly, and hydraulic cylinder's telescopic link upper end is fixed, and the both ends of top seat all articulate there is the connecting rod, and the other end of two connecting rods is respectively that the articulate inner that establishes is articulated mutually in first lifting support, the second lifting support, the both sides inner wall upper end of drive case all is provided with two sets of protection device.
Preferably, the outer side wall of the vertical side support of the support shaft seat is provided, and a reinforcing rib is welded between the outer side wall of the support shaft seat and the outer side wall of the side support.
Preferably, the upper end of the auxiliary wheel socket is provided with a first hinged seat, the upper side surface of the main support column is provided with a second hinged seat, and a pair of shock absorbers are connected between the first hinged seat and the second hinged seat.
Preferably, an included angle of 15-25 degrees is formed between the main support column arranged in the first lifting support and the second lifting support and the side wall of the side support, and an included angle of 50-60 degrees is formed between the side support rod of the auxiliary wheel socket and the side support rod of the main wheel socket.
Preferably, protection device includes spacing seat, spacing slider and electromagnetism telescopic link, and spacing seat compares integrated into one piece with the inside of drive case, and the slide has been seted up to the inside of spacing seat, and sliding connection has the spacing slider that matches and fit in the slide.
Preferably, an electromagnetic telescopic rod is fixedly arranged at an outer port of the slide way arranged in the limiting seat, and the end part of the telescopic rod of the electromagnetic telescopic rod is connected with the limiting slide block.
Compared with the prior art, the invention has the beneficial effects that: the invention has reasonable structure and strong functionality, and has the following advantages:
1. according to the invention, the driving box is respectively connected with one airplane wheel through the first lifting support and the second lifting support arranged on the two sides, and compared with a structure in which only one airplane wheel is arranged in a transmission manner, the driving box has better stability when an airplane glides;
2. according to the invention, the telescopic rod of the lifting hydraulic cylinder is controlled to stretch, so that the footstock at the upper end of the telescopic rod can lift and draw the end parts of the cranks in the first lifting support and the second lifting support through the connecting rod, thereby lifting the airplane wheels arranged in the first lifting support and the second lifting support, and the lifting control of the first lifting support and the second lifting support can be completed by one set of driving equipment, so that the stability of the airplane during sliding is increased, and meanwhile, the installation space of the driving equipment is reduced;
3. in the process that the aircraft descends, the aircraft wheels arranged in the first lifting support and the second lifting support descend, the telescopic rod of the electromagnetic telescopic rod is controlled to extend, the limiting slide block is ejected to the lower portion of the top seat, the top seat is supported and limited, impact force is prevented from impacting the telescopic rod of the lifting hydraulic cylinder, and the lifting hydraulic cylinder is effectively protected.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a front cross-sectional view of the present invention;
FIG. 3 is a cross-sectional view taken at A-A of FIG. 2;
fig. 4 is an enlarged view at B in fig. 3.
In the figure: the device comprises a driving box 1, a first lifting support 2, a second lifting support 201, a side supporting seat 3, a notch 301, a supporting shaft seat 4, a reinforcing rib 401, a main support column 5, a main wheel socket 501, a crank 502, a shaft barrel seat 6, a wheel 7, an auxiliary wheel socket 8, a first hinging seat 9, a second hinging seat 901, a shock absorber 10, a lifting hydraulic cylinder 11, a top seat 12, a connecting rod 13, a protection device 14, a limiting seat 15, a limiting sliding block 16 and an electromagnetic telescopic rod 17.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Referring to fig. 1 to 4, the present invention provides a technical solution: the utility model provides a small aircraft's undercarriage control mechanism, including drive case 1, first lifting support 2 and second lifting support 201, combine figure 1 and fig. 2 to show, the both sides end of drive case 1 all is through bolt fixedly connected with side support 3, notch 301 has been seted up at the middle part of collateral branch seat 3, the lateral wall of collateral branch seat 3 just is located notch 301 both sides integrated into one piece has a pair of support axle seat 4, the lateral wall setting of support axle seat 4 perpendicular side support 3, and the welding has enhancement rib 401 between the lateral wall of support axle seat 4 and collateral branch seat 3, be used for strengthening the connection effect between support axle seat 4 and the collateral branch seat 3 outer wall, the support axle seat 4 of establishing on the collateral branch seat 3 at drive case 1 both ends is connected with first lifting support 2 respectively, second lifting support 201.
The first lifting support 2 and the second lifting support 201 are both composed of a main pillar 5 and an auxiliary wheel socket 8, the upper end of the main pillar 5 is provided with a shaft cylinder seat 6, the shaft cylinder seat 6 is rotatably connected with a supporting shaft seat 4 through a rotating shaft, the lower end of the main pillar 5 is provided with a main wheel socket 501 of a U-shaped support, the auxiliary wheel socket 8 is a U-shaped support, a wheel 7 is rotatably connected between the two side support rod ends of the auxiliary wheel socket 8, the two side support rod ends of the main wheel socket 501 are respectively hinged with the middle parts of the two side support rods of the auxiliary wheel socket 8, the upper end of the auxiliary wheel socket 8 is provided with a first hinge seat 9, the upper side surface of the main pillar 5 is provided with a second hinge seat 901, and a pair of shock absorbers 10 are connected between the first hinge seat 9 and the second hinge seat 901, as shown in fig. 2, when the main wheel socket 501 generates a downward pressure on the auxiliary wheel socket 8 in the aircraft process, the shock absorber 10 is stretched by the upper end of the auxiliary wheel socket 8, and at this time, the shock absorber 10 buffers the impact force, thereby reducing the impact on the first lifting support 2 and the second lifting support 201 when the airplane falls.
An included angle of 15-25 degrees is formed between the main support column 5 arranged in the first lifting support 2 and the second lifting support 201 and the side wall of the side support seat 3, the first lifting support 2 and the second lifting support 201 are in a triangular type and support the driving box 1, the stability in supporting is improved, an included angle of 50-60 degrees is formed between the side support rod of the auxiliary wheel socket 8 and the side support rod of the main wheel socket 501, and a triangular support is formed among the main wheel socket 501, the auxiliary wheel socket 8 and the shock absorber 10, so that the stability of the main wheel socket 501 and the auxiliary wheel socket is improved.
Referring to fig. 1 and 2, a crank 502 is welded on one side of the shaft cylinder seat 6 away from the main pillar 5, the end of the crank 502 extends into the driving box 1 along the notch 301, a hydraulic lift cylinder 11 is fixedly connected to the bottom surface of the inside of the driving box 1 through a bolt, the telescopic rod of the hydraulic lift cylinder 11 is vertically arranged upward, the upper end of the telescopic rod of the hydraulic lift cylinder 11 is fixedly provided with a top seat 12, two ends of the top seat 12 are hinged with connecting rods 13, the other ends of the two connecting rods 13 are respectively hinged with the inner ends of the cranks 502 arranged in the first lifting support 2 and the second lifting support 201, when the telescopic rod of the hydraulic lift cylinder 11 is controlled to ascend, the top seat 12 at the upper end of the telescopic rod pulls the end of the crank 502 to ascend through the connecting rods 13, so that the airplane wheels 7 arranged in the first lifting support 2 and the second lifting support 201 descend for airplane sliding, otherwise, the telescopic, the wheels 7 arranged in the first lifting bracket 2 and the second lifting bracket 201 are lifted and retracted into the inner cabin of the airplane.
Referring to fig. 2, 3 and 4, two sets of protection devices 14 are disposed at the upper ends of the inner walls of the two sides of the driving box 1, each protection device 14 includes a limiting seat 15, a limiting slide block 16 and an electromagnetic telescopic rod 17, the limiting seats 15 and the inside of the driving box 1 are integrally formed, a slide way is disposed inside the limiting seats 15, a matching limiting slide block 16 is slidably connected in the slide way, the electromagnetic telescopic rod 17 is fixedly disposed at the outer port of the slide way, and the end of the telescopic rod of the electromagnetic telescopic rod 17 is connected with the limiting slide block 16, when the telescopic rod of the lifting hydraulic cylinder 11 is controlled to push the top seat 12 to the highest point, the airplane wheel 7 disposed in the first lifting support 2 and the second lifting support 201 is lowered, at this time, the telescopic rod of the electromagnetic telescopic rod 17 is controlled to extend, the limiting slide block 16 is pushed out to the lower side of the top seat 12, and the top seat, when the airplane lands, the airplane wheel 7 is in rolling contact with the ground, the crank 502 has a downward pulling force on the connecting rod 13, and under the support of the limit slider 16 on the top seat 12, impact on the telescopic rod of the hydraulic lifting cylinder 11 by impact force is prevented, so that the hydraulic lifting cylinder 11 is effectively protected.
The working principle is as follows: when the telescopic rod of the lifting hydraulic cylinder 11 is controlled to ascend, the top seat 12 at the upper end of the telescopic rod pulls the end part of the crank 502 to ascend through the connecting rod 13, so that the airplane wheels 7 arranged in the first lifting support 2 and the second lifting support 201 descend to be used when an airplane slides, otherwise, the telescopic rod of the lifting hydraulic cylinder 11 is controlled to descend, so that the airplane wheels 7 arranged in the first lifting support 2 and the second lifting support 201 ascend and retract into an inner cabin of the airplane, the lifting control of the first lifting support 2 and the second lifting support 201 can be completed through one set of driving equipment, the stability of the airplane when the airplane slides is improved, and meanwhile, the installation space of the driving equipment is reduced; in the descending process of the airplane, the telescopic rod of the lifting hydraulic cylinder 11 is controlled to push the top seat 12 to the highest point, so that the airplane wheel 7 arranged in the first lifting support 2 and the second lifting support 201 descends, the telescopic rod of the electromagnetic telescopic rod 17 is controlled to extend at the moment, the limiting slide block 16 is pushed out to the lower part of the top seat 12, the top seat 12 is supported and limited, the impact force is prevented from impacting the telescopic rod of the lifting hydraulic cylinder 11, and the lifting hydraulic cylinder 11 is effectively protected.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (1)
1. The utility model provides a landing gear control mechanism of small aircraft, includes drive box (1), first lifting support (2) and second lifting support (201), its characterized in that: the two side ends of the driving box (1) are fixedly connected with side supporting seats (3) through bolts, a notch (301) is formed in the middle of each side supporting seat (3), the outer side wall of each side supporting seat (3) is integrally formed with a pair of supporting shaft seats (4) which are positioned on the two sides of the notch (301), the supporting shaft seats (4) formed on the side supporting seats (3) at the two ends of the driving box (1) are respectively connected with a first lifting support (2) and a second lifting support (201), each of the first lifting support (2) and the second lifting support (201) is composed of a main supporting column (5) and an auxiliary wheel socket (8), a shaft cylinder seat (6) is arranged at the upper end of the main supporting column (5), the shaft cylinder seat (6) is rotatably connected with the supporting shaft seats (4) through a rotating shaft, a main wheel socket (501) which is a U-shaped support is arranged at the lower end of the main supporting column (5), and the auxiliary wheel socket, and the wheel (7) is rotatably connected between the support rod ends at the two sides of the auxiliary wheel socket (8), the end parts of two side supporting rods of the main wheel socket (501) are respectively hinged with the middle parts of two side supporting rods of the auxiliary wheel socket (8), a crank (502) is welded on one side of the shaft cylinder seat (6) far away from the main strut (5), and the end of the crank (502) extends to the inside of the driving box (1) along the notch (301), the bottom surface of the interior of the driving box (1) is fixedly connected with a lifting hydraulic cylinder (11) through bolts, a telescopic rod of the lifting hydraulic cylinder (11) is vertically arranged upwards, and the upper end of the telescopic rod of the lifting hydraulic cylinder (11) is fixedly provided with a top seat (12), both ends of the top seat (12) are hinged with connecting rods (13), one end of each connecting rod (13) is respectively hinged with the left end and the right end of the top seat (12), the other end of the connecting rod (13) at the left side is hinged with the inner end of a crank (502) arranged in the first lifting bracket (2); the other end of the connecting rod (13) at the right side is hinged with the inner end of a crank (502) arranged in the second lifting bracket (201); two groups of protection devices (14) are arranged at the upper ends of the inner walls of the two sides of the driving box (1);
the outer side wall of the vertical side support (3) of the support shaft seat (4) is arranged, and a reinforcing rib (401) is welded between the support shaft seat (4) and the outer side wall of the side support (3);
a first hinged seat (9) is arranged at the upper end of the auxiliary wheel socket (8), a second hinged seat (901) is arranged on the upper side surface of the main support column (5), and a pair of shock absorbers (10) is connected between the first hinged seat (9) and the second hinged seat (901);
an included angle of 15-25 degrees is formed between a main support column (5) arranged in the first lifting support (2) and the second lifting support (201) and the side wall of the side support (3), and an included angle of 50-60 degrees is formed between a side support rod of the auxiliary wheel socket (8) and a side support rod of the main wheel socket (501); when the aircraft lands, the main wheel socket (501) generates downward pressure on the auxiliary wheel socket (8), so that the upper end of the auxiliary wheel socket (8) stretches the shock absorber (10), the shock absorber (10) buffers impact force, and impact on the first lifting support (2) and the second lifting support (201) when the aircraft falls is reduced;
the protection device (14) comprises a limiting seat (15), a limiting sliding block (16) and an electromagnetic telescopic rod (17), the limiting seat (15) and the interior of the driving box (1) are integrally formed, a slide way is arranged in the limiting seat (15), and the limiting sliding block (16) matched with the slide way is connected in a sliding manner;
an electromagnetic telescopic rod (17) is fixedly arranged at the outer port of the slide way arranged in the limiting seat (15), and the telescopic rod end part of the electromagnetic telescopic rod (17) is connected with a limiting slide block (16);
when the airplane wheel lifting device is used, when the telescopic rod of the lifting hydraulic cylinder (11) is controlled to lift, the top seat (12) at the upper end of the telescopic rod pulls the end part of the crank (502) to lift through the connecting rod (13), so that the airplane wheels (7) arranged in the first lifting support (2) and the second lifting support (201) descend to be used when an airplane slides, otherwise, when the telescopic rod of the lifting hydraulic cylinder (11) is controlled to descend, the airplane wheels (7) arranged in the first lifting support (2) and the second lifting support (201) ascend and retract into an inner cabin of the airplane, and the lifting control on the first lifting support (2) and the second lifting support (201) can be completed through one set of driving equipment, so that the stability of the airplane when the airplane slides is improved, and meanwhile, the installation space of the driving equipment is reduced; in the descending process of the airplane, the telescopic rod of the lifting hydraulic cylinder (11) is controlled to push the footstock (12) to the highest point, so that the airplane wheel (7) arranged in the first lifting support (2) and the second lifting support (201) descends, the telescopic rod of the electromagnetic telescopic rod (17) is controlled to extend, the limiting slide block (16) is pushed out to the lower side of the footstock (12), and the footstock (12) is supported and limited;
when the airplane lands, the airplane wheel (7) is in rolling contact with the ground, the crank (502) has a downward pulling force on the connecting rod (13), and under the support of the limit sliding block (16) on the top seat (12), impact on a telescopic rod of the lifting hydraulic cylinder (11) by impact force is prevented, so that the lifting hydraulic cylinder (11) is effectively protected.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010080469.6A CN111216880B (en) | 2020-02-05 | 2020-02-05 | Undercarriage control mechanism of small aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010080469.6A CN111216880B (en) | 2020-02-05 | 2020-02-05 | Undercarriage control mechanism of small aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111216880A CN111216880A (en) | 2020-06-02 |
| CN111216880B true CN111216880B (en) | 2020-12-15 |
Family
ID=70808338
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010080469.6A Active CN111216880B (en) | 2020-02-05 | 2020-02-05 | Undercarriage control mechanism of small aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111216880B (en) |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2708248B1 (en) * | 1993-07-01 | 1995-10-06 | Messier Bugatti | Aircraft landing gear, of the side lift type. |
| CN106275394A (en) * | 2016-09-26 | 2017-01-04 | 华东电子工程研究所（中国电子科技集团公司第三十八研究所） | A kind of pint-sized airplane undercarriage |
| CN206679248U (en) * | 2017-04-27 | 2017-11-28 | 峨眉山市博派乐无人机科技有限公司 | Unmanned plane undercarriage |
| MA41565B1 (en) * | 2017-12-05 | 2019-11-29 | Univ Int Rabat | Detachable Landing Gear Drone |
| CN108839791A (en) * | 2018-08-29 | 2018-11-20 | 西安航远数字技术有限公司 | A kind of damping wheel mechanism |
-
2020
- 2020-02-05 CN CN202010080469.6A patent/CN111216880B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN111216880A (en) | 2020-06-02 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108502206B (en) | Double-deck unmanned aerial vehicle fuselage transportation bracket of multipurpose | |
| RU2544025C2 (en) | Aircraft under carriage front leg with integrated lift and directing control device | |
| CN111216880B (en) | Undercarriage control mechanism of small aircraft | |
| CN106742031B (en) | A kind of no rod-type aircraft tractor wheel holding mechanism | |
| CN111469613A (en) | Wheel deflection folding device of amphibious vehicle and boat | |
| CN109018313B (en) | Snowfield aircraft is with frame that rises and falls | |
| CN202670103U (en) | Passenger elevator car for transporting passenger | |
| CN105416151B (en) | A kind of rail mounted wrecker | |
| CN111251970A (en) | High-altitude balloon dynamic dispensing vehicle | |
| CN107650600B (en) | Folding type water skiing board | |
| CN212766727U (en) | Undercarriage buffer structure for unmanned aerial vehicle | |
| CN2584515Y (en) | Hand airstair | |
| CN104328759A (en) | Front water spraying frame mechanism of high-pressure sewer flushing vehicle | |
| CN113511262A (en) | Vehicle with a steering wheel | |
| CN205344662U (en) | Special type removes rescue intelligent service car | |
| CN110965455A (en) | High-speed light bridge girder erection vehicle for emergency rescue and bridge girder erection and collection method thereof | |
| CN208443203U (en) | A kind of deslagging head adjustable angle forklift for slag | |
| CN209553492U (en) | A kind of multi-functional undercarriage of aircraft | |
| CN215851457U (en) | Vehicle with a steering wheel | |
| CN110630059A (en) | Double-layer avoidance-free side parking hydraulic turnover box type parking space | |
| CN219904737U (en) | Fuselage bracket for unmanned aerial vehicle | |
| CN211996119U (en) | Main landing gear with central layout of retraction mechanism | |
| CN220314933U (en) | Telescopic rear protection structure for rear lifting vehicle | |
| CN218949027U (en) | Carriage lifting structure of airplane food vehicle | |
| CN214828714U (en) | Tunnel ring beam installation mechanism |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| TA01 | Transfer of patent application right | ||
| TA01 | Transfer of patent application right |
Effective date of registration: 20201117 Address after: No.2, hanghang Road, high tech Industrial Zone, Jianhu County, Yancheng City, Jiangsu Province, 224000 Applicant after: JIANGSU TIANYI AIRPORT SPECIAL EQUIPMENT Co.,Ltd. Address before: 312500 No.25, dongbaoshan, Wangjiayuan village, Yulin street, Xinchang County, Shaoxing City, Zhejiang Province Applicant before: XINCHANG COUNTY YULIN STREET ZHIXI MACHINERY FACTORY |
|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP01 | Change in the name or title of a patent holder | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 224000 No. 2 Hangkong Road, high tech Industrial Zone, Jianhu County, Yancheng City, Jiangsu Province Patentee after: Jiangsu Tianyi Aviation Industry Co.,Ltd. Address before: 224000 No. 2 Hangkong Road, high tech Industrial Zone, Jianhu County, Yancheng City, Jiangsu Province Patentee before: JIANGSU TIANYI AIRPORT SPECIAL EQUIPMENT Co.,Ltd. |
|
| EE01 | Entry into force of recordation of patent licensing contract | ||
| EE01 | Entry into force of recordation of patent licensing contract |
Application publication date: 20200602 Assignee: Jiangsu Tianyi Airport Equipment Maintenance Service Co.,Ltd. Assignor: Jiangsu Tianyi Aviation Industry Co.,Ltd. Contract record no.: X2023980044219 Denomination of invention: A Landing Gear Control Mechanism for Small Aircraft Granted publication date: 20201215 License type: Common License Record date: 20231024 |