CN114162311A - An electronically controlled multi-stage buffer landing gear and a method of using the same - Google Patents
An electronically controlled multi-stage buffer landing gear and a method of using the same Download PDFInfo
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- CN114162311A CN114162311A CN202111195024.3A CN202111195024A CN114162311A CN 114162311 A CN114162311 A CN 114162311A CN 202111195024 A CN202111195024 A CN 202111195024A CN 114162311 A CN114162311 A CN 114162311A
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- 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
- B64C25/36—Arrangements or adaptations of wheels, tyres or axles in general
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- 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
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- 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
- B64C25/62—Spring shock-absorbers; Springs
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Tires In General (AREA)
Abstract
本发明涉及电控分级式起落架技术领域，尤其涉及一种电控多级缓冲起落架及其使用方法，包括碰撞辅轮轮胎、主轮轮胎和固定筒，所述碰撞辅轮轮胎和主轮轮胎的数量均为两组，每组所述碰撞辅轮轮胎内均安装有碰撞辅轮轮毂，每组所述主轮轮胎内均安装有主轮轮毂。本发明通过一旦飞机降落到接近地面时，碰撞辅助轮首先接触地面，冲击力使得弧形型高强度钢片组形变，承受第一次冲击力，当高强度钢片组，持续承受压力继续形变到水平“一”形时，快速形变成“⌒”形，突发反向释放下降挤压过程中蓄积的弹性势能，降低机体下冲动能，使轮胎呈“上二下三”的排布，减小了过程中所受冲击力强度，提高了乘客的舒适度。
The invention relates to the technical field of electronically controlled graded landing gear, in particular to an electronically controlled multi-stage buffer landing gear and a method for using the same, comprising a collision auxiliary wheel tire, a main wheel tire and a fixed cylinder, the collision auxiliary wheel tire and the main wheel The number of tires is two groups, the collision auxiliary wheel hubs are installed in each group of collision auxiliary wheel tires, and the main wheel hubs are installed in each group of main wheel tires. According to the invention, once the aircraft lands close to the ground, the collision auxiliary wheel first contacts the ground, and the impact force causes the arc-shaped high-strength steel sheet group to deform and bear the first impact force. When the high-strength steel sheet group continues to bear the pressure and continues to deform When it reaches the horizontal "one" shape, it quickly transforms into a "⌒" shape, and suddenly releases the elastic potential energy accumulated during the descending extrusion process in a reverse direction, reducing the downward impulse energy of the body, so that the tires are arranged in "up two down three" , reducing the impact strength in the process and improving the comfort of passengers.
Description
Technical Field
The application relates to the technical field of electronic control hierarchical landing gears, in particular to an electronic control multilevel buffering landing gear and a using method thereof.
Background
The aircraft landing gear is the only part supporting the aircraft and is indispensable. The existing passenger plane landing gear is mostly a beam type landing gear, and generally comprises a stressed strut, a shock absorber, a torsion arm, a support rod system, an airplane wheel, a brake system and the like. The main bearing member is a beam (a strut or a shock-absorbing strut). When subjected to a horizontal impact from the front, the shock strut does not perform its shock-absorbing function well, and when landing, the strut must be subjected to a bending moment, and the sealing means of the shock strut is subject to wear.
The invention aims to solve the technical problem that passengers are uncomfortable due to large impact force when a wide-body passenger plane starts and lands, and provides an electric control hierarchical type buffering undercarriage, so that the instantaneous impact force when the wide-body passenger plane lands is relieved, the landing safety of the airplane is improved, and the discomfort of the passengers is reduced. Compare with traditional undercarriage, this novel undercarriage's main wheel is because it is little to bear the impact force, and life is longer, and the replacement is conveniently dismantled to the collision auxiliary wheel, improves the life of undercarriage and improves the security of undercarriage.
Summary of the invention
The invention aims to provide an electric control multi-level buffer undercarriage and a using method thereof, which aim to solve the problems in the background technology.
The embodiment of the application adopts the following technical scheme:
an electric control multistage buffering undercarriage and a using method thereof comprise an auxiliary collision wheel tire, a main wheel tire and a fixed cylinder, wherein the number of the auxiliary collision wheel tire and the number of the main wheel tire are two, each auxiliary collision wheel tire is internally provided with an auxiliary collision wheel hub, each main wheel hub is internally provided with a main wheel hub, each auxiliary collision wheel hub is internally provided with a first hollow flange, each hollow flange is internally provided with a first fixed part by rotating a knob, each hollow flange is internally provided with a second hollow flange which is matched with the first hollow flange, each hollow flange is internally provided with a third fixed part by rotating a knob, each main wheel hub is internally provided with a second flange with a notch, each notched flange is internally provided with a first notched flange which is matched with the second notched flange, and each notched flange is internally provided with a second fixed part by rotating a knob, every group take breach ring flange one and every group take equal fixedly connected with setting element one between the breach ring flange two, every group cavity ring flange one and every group equal fixedly connected with mounting three between the cavity ring flange two, every group all be provided with connection structure between collision auxiliary wheel hub and the main wheel tire, connection structure includes high strength steel sheet group, and is two sets of the both sides that the main wheel tire is relative all are provided with horizontal rocking arm and connecting rod, every horizontal rocking arm is fixed connection respectively on the connecting rod, be provided with transmission structure in the solid fixed cylinder.
Preferably, the high-strength steel sheet group is provided with a downward convex part, the high-strength steel sheet group is arranged in the hollow flange plate I and the hollow flange plate II and in the notched flange plate I and the notched flange plate II and is fixed through the fixing part III and the fixing part II respectively, the positioning part I is inserted in the high-strength steel sheet group, and the fixing part III is inserted in the high-strength steel sheet group.
Preferably, the high-strength steel sheet group is in a shape of 'power', and the first hollow flange and the second hollow flange of each group are in a shape of 'convex'.
Every the connecting rod is fixed connection respectively and is located the centre main wheel hub's tip, two all be provided with the parallel key on the connecting rod, two all install bevel gear one on the connecting rod, every bevel gear one is respectively through parallel key and connecting rod fixed connection.
The two opposite ends of the connecting rod are inserted into the fixed cylinder, the first conical gear is arranged in the fixed cylinder, the transmission structure comprises a second conical gear which is located on the upper side and rotatably mounted in the fixed cylinder, and a motor is mounted in the fixed cylinder. And the second conical gear is positioned at the lower side and is fixedly connected with an output shaft of the motor, and the two second conical gears are respectively meshed with the two first conical gears.
Sliding connection has hydraulic stem one in the solid fixed cylinder, be provided with the connector on the hydraulic stem one, the upper end fixedly connected with monolithic of hydraulic stem one connects, the tip fixedly connected with connecting plate of solid fixed cylinder, install hydraulic stem two on the monolithic connects, the connector is connected with monolithic connects the articulated.
The hydraulic stem one side is provided with the fixed plate, the circular port has been seted up on the surface of fixed plate, circular port female connection has the screw rod, the hydraulic stem two-pass is fixed with the upper end of fixed plate through the screw rod, be provided with the connecting piece between fixed plate and the connecting plate, be provided with two bolts in the connecting piece, the connecting plate is connected with the connecting piece is articulated through a bolt, the fixed plate is connected with the connecting piece is articulated through another bolt, the bottom of fixed plate links to each other with the aircraft organism.
And the first hydraulic rod and the fixed cylinder are fixedly sleeved with circular plates, and a spring is fixedly connected between the two circular plates.
The collision auxiliary wheel tires are respectively positioned on the outer sides of the main wheel tires, the collision auxiliary wheel tires and the main wheel tires are symmetrically distributed about the fixed cylinder, the number of the collision auxiliary wheel tires in each group is two, and the number of the main wheel tires in each group is three.
The first hollow flange plate is fixed with the collision auxiliary wheel hub through the first fixing part, the second hollow flange plate in each group is fixed with the first hollow flange plate through the third fixing part, and the first flange plate with the notch in each group is fixed with the second flange plate with the notch through the second fixing part.
A use method of an electric control multi-level buffer undercarriage comprises the following steps:
s1, when the airplane needs to land, firstly, the landing gear is driven to extend out of the airplane body through a hydraulic lifting system with the landing gear, and the main wheel of the landing gear is contacted with the bottom surface when the airplane takes off;
s2, when the airplane needs to land, the landing gear is driven to extend out of the airplane body through the hydraulic rod II with the joint, the motor is started to enable the bevel gear II to rotate and drive the bevel gear I to rotate, the transversely-placed rocker arm is made to rotate, the height of the tire of the collision auxiliary wheel is driven to fall, the contact surface is lower than that of the tire of the main wheel and forms a proper angle with the ground, and the tires are arranged in a mode of 'lower two and upper three';
and S3, finally, the main wheel tire contacts the ground again, bears the second impact force through linkage with the hydraulic rod I, finishes the landing of the airplane, decomposes the primary collision borne by the landing into the secondary collision, and utilizes the elastic energy storage and reverse release device of the auxiliary collision wheel to achieve the purposes of increasing the buffering time, reducing the impact force intensity borne in the process, and improving the landing safety of the airplane and the landing comfort of passengers.
The embodiment of the application adopts at least one technical scheme which can achieve the following beneficial effects:
one of them, when using, the aircraft slides and takes off the tire of stage undercarriage and is "two under and three on, keep the main wheel and bottom surface contact, when the aircraft needs to descend, at first, drive the undercarriage through the hydraulic lifting system who takes the undercarriage and stretch out the aircraft organism, the main wheel and the bottom surface contact of undercarriage when the aircraft takes off, when the aircraft needs to descend, drive the undercarriage through the second hydraulic stem that takes the joint and stretch out the aircraft organism, and the starter motor makes the second conical gear rotate and drive first conical gear and rotate, make the horizontal rocking arm rotatory, drive the high decline of collision auxiliary wheel tire, the contact surface is less than the main wheel tire, and be suitable angle with ground, the tire is arranging of" two under and three on ", structural design is reasonable, and is comparatively practical.
Secondly, once the aircraft lands to be close to the ground, the collision auxiliary wheel firstly contacts the ground, the impact force enables the arc-shaped high-strength steel sheet group to be deformed and bears the first impact force, when the high-strength steel sheet group continuously bears the pressure and continuously deforms to a horizontal 'one' shape, the shape is quickly changed into a 'cutting paper' shape, the elastic potential energy accumulated in the descending extrusion process is suddenly and reversely released, the descending impact energy of the machine body is reduced, the tires are arranged in 'two upper and three lower', the impact force intensity borne in the process is reduced, and the comfort level of passengers is improved.
And finally, the main wheel tire contacts the ground again, and bears secondary impact force through linkage with the hydraulic rod I, the aircraft landing is completed, primary collision received by the aircraft landing is decomposed into secondary collision, and the elastic energy storage and reverse release device of the auxiliary collision wheel is utilized to achieve the time of increasing buffering, reduce the impact strength received by the process, and improve the safety of the aircraft landing and the comfort level of passengers when landing.
And fourthly, the circular plate positioned on the upper side is moved through the linkage of the hydraulic rod I, the spring is fixedly connected between the two circular plates, so that the spring is stressed and compressed or stretched, and a certain buffering effect is achieved between the two circular plates due to the effect of the spring, so that a certain buffering effect is achieved between the hydraulic rod I and the fixed cylinder, the secondary impact force is further relieved, the impact strength received in the process is reduced, and the practicability of the equipment is improved.
Drawings
The accompanying drawings, which are included to provide a further understanding of the application and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the application and together with the description serve to explain the application and not to limit the application. In the drawings:
figure 1 is a schematic view of the general construction of the landing gear of the present invention;
FIG. 2 is a schematic exploded view of the landing gear of the present invention;
FIG. 3 is a schematic structural view of a high strength steel sheet set according to the present invention;
FIG. 4 is a schematic structural view of a first flange plate with a notch according to the present invention;
FIG. 5 is a schematic structural view of a transverse rocker arm of the present invention;
FIG. 6 is a schematic structural view of a connecting rod of the present invention;
fig. 7 is a schematic structural view of a fixing plate according to the present invention.
In the figure: 1. a crash sub-tire; 2. bumping into the auxiliary wheel hub; 21. a hollow flange plate I; 22. a first fixing part; 23. a first flange plate with a notch; 24. a second fixing part; 25. a first positioning piece; 26. a second flange plate with a notch; 27. a hollow flange plate II; 28. a third fixing part; 3. a main wheel tire; 31. a main wheel hub; 4. a high-strength steel sheet set; 5. transversely placing the rocker arm; 6. a connecting rod; 61. a first conical gear; 62. a flat bond; 7. a fixed cylinder; 71. a second bevel gear; 72. a motor; 73. a connecting plate; 8. a first hydraulic rod; 81. a single piece joint; 82. a connector; 84. a fixing plate; 85. a circular hole; 86. a screw; 87. a connecting member; 88. a bolt; 89. a second hydraulic rod; 9. a circular plate; 91. a spring.
Detailed Description
In order to make the objects, technical solutions and advantages of the present application more apparent, the technical solutions of the present application will be described in detail and completely with reference to the following specific embodiments of the present application and the accompanying drawings. It should be apparent that the described embodiments are only some of the embodiments of the present application, 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 application.
The technical solutions provided by the embodiments of the present application are described in detail below with reference to the accompanying drawings.
Example 1: referring to fig. 1, 2, 3, 4, 5, 6 and 7, an electrically controlled multi-level buffer landing gear and a method for using the same includes a secondary collision tire 1, a primary tire 3 and a fixing cylinder 7, wherein the secondary collision tire 1 and the primary tire 3 are provided in two groups, a secondary collision wheel hub 2 is installed in each group of secondary collision tire 1, a primary wheel hub 31 is installed in each group of primary tire 3, a hollow flange 21 is installed on each group of secondary collision wheel hub 2, a fixing member 22 is screwed into each group of hollow flange 21, a hollow flange 27 is installed on each group of hollow flange 21, a fixing member 28 is screwed into each group of hollow flange 27, a flange 26 with a notch is installed on each group of primary wheel hubs 31, a flange 23 with a notch is installed on each group of flange 26, a fixing part II 24 is arranged in each group of the first notched flange plates 23, a positioning part I25 is fixedly connected between each group of the first notched flange plates 23 and each group of the second notched flange plates 26, a fixing part III 28 is fixedly connected between each group of the first notched flange plates 21 and each group of the second notched flange plates 27, a connecting structure is arranged between each group of the collision auxiliary wheel hubs 2 and the main wheel tires 3, the connecting structure comprises a high-strength steel sheet group 4, transverse rocker arms 5 and connecting rods 6 are arranged on two opposite sides of each group of the main wheel tires 3, each transverse rocker arm 5 is respectively and fixedly connected onto the connecting rods 6, a transmission structure is arranged in the fixed cylinder 7, the convex part of the high-strength steel sheet group 4 is downward, the high-strength steel sheet group 4 is arranged in the first notched flange plates 21 and the second notched flange plates 27, and in the first notched flange plates 23 and the second notched flange plates 26 and is respectively fixed through the fixing parts III 28 and II 24, locating piece one 25 pegs graft in high strength steel sheet group 4, mounting three 28 pegs graft in high strength steel sheet group 4, high strength steel sheet group 4 is "shape", every group cavity ring flange one 21 and every group cavity ring flange two 27 are "protruding" shape, every connecting rod 6 is fixed connection respectively at the tip that is located middle main wheel hub 31, all be provided with flat key 62 on two connecting rods 6, all install bevel gear one 61 on two connecting rods 6, every bevel gear one 61 is respectively through flat key 62 and connecting rod 6 fixed connection, two connecting rod 6 relative both ends are all pegged graft in solid fixed cylinder 7, two bevel gear one 61 all set up in solid fixed cylinder 7, the transmission structure includes two bevel gear two 71, it installs in solid fixed cylinder 7 to be located upside bevel gear two 71 rotation, install motor 72 in solid fixed cylinder 7. The bevel gear II 71 positioned on the lower side is fixedly connected with an output shaft of the motor 72, the two bevel gear II 71 are respectively meshed with the two bevel gear I61, a hydraulic rod I8 is connected in the fixed cylinder 7 in a sliding manner, a connector 82 is arranged on the hydraulic rod I8, a single-chip connector 81 is fixedly connected to the upper end of the hydraulic rod I8, a connecting plate 73 is fixedly connected to the end of the fixed cylinder 7, a hydraulic rod II 89 is mounted on the single-chip connector 81, the connector 82 is hinged to the single-chip connector 81, a fixing plate 84 is arranged on one side of the hydraulic rod I8, a circular hole 85 is formed in the surface of the fixing plate 84, a screw 86 is connected to the circular hole 85 in a threaded manner, the hydraulic rod II 89 is fixed to the upper end of the fixing plate 84 through the screw 86, a connecting piece 87 is arranged between the fixing plate 84 and the connecting plate 73, two bolts 88 are arranged in the connecting piece 87, and the connecting plate 73 is hinged to the connecting piece 87 through one bolt 88, the fixing plate 84 is hinged to the connecting piece 87 through another bolt 88, the bottom of the fixing plate 84 is connected with an airplane body, the first hydraulic rod 8 and the fixing cylinder 7 are fixedly sleeved with the circular plates 9, springs 91 are fixedly connected between the two circular plates 9, the auxiliary collision wheel tires 1 are located on the outer sides of the main wheel tires 3 of each group respectively, the auxiliary collision wheel tires 1 and the main wheel tires 3 of each group are symmetrically distributed about the fixing cylinder 7, the number of the auxiliary collision wheel tires 1 of each group is two, the number of the main wheel tires 3 of each group is three, the first hollow flange 21 of each group is fixed with the auxiliary collision wheel hub 2 through the first fixing piece 22 respectively, the second hollow flange 27 of each group is fixed with the first hollow flange 21 through the third fixing piece 28 respectively, and the first notched flange 23 of each group is fixed with the second notched flange 26 through the second fixing piece 24 respectively.
When the airplane needs to land, the undercarriage is driven to extend out of an airplane body through a hydraulic lifting system with the undercarriage, the main wheel of the undercarriage is in contact with the bottom surface when the airplane takes off, when the airplane needs to land, the undercarriage is driven to extend out of the airplane body through a second hydraulic rod 89 with a joint, a motor 72 is started to enable a second bevel gear 71 to rotate and drive a first bevel gear 61 to rotate, a transverse rocker arm 5 is made to rotate, the height of a collision auxiliary wheel tire 1 is driven to descend, the contact surface is lower than that of a main wheel tire 3 and forms a proper angle with the ground, and the tires are arranged in a mode of 'lower two upper three'; then, once the airplane lands on the ground, the collision auxiliary wheel firstly contacts the ground, the impact force makes the arc-shaped high-strength steel sheet group 4 deform, and bears the first impact force, when the high-strength steel sheet group 4 continuously bears the pressure and continuously deforms to a horizontal 'one' shape, the shape is quickly changed into a 'shape', the elastic potential energy accumulated in the descending extrusion process is suddenly and reversely released, the downward-impact energy of the airplane body is reduced, and the tires are arranged in an 'upper two lower three' shape; finally, the main wheel tyre 3 contacts the ground again, bears a second impact force through linkage with the hydraulic rod I8 to finish the landing of the airplane, and achieves the purposes of increasing the buffering time, reducing the impact force intensity borne in the process and improving the safety of the landing of the airplane and the comfort level of passengers during the landing by decomposing the primary collision borne by the landing into the secondary collision and utilizing the elastic energy storage and reverse release device of the auxiliary collision wheel;
make the plectane 9 that is located the upside to produce through the linkage of hydraulic stem one 8 and remove, because fixedly connected with spring 91 between two plectanes 9 for spring 91 atress compression or tensile, because spring 91's effect makes and has certain cushioning effect between two plectanes 9, makes and has certain cushioning effect between hydraulic stem one 8 and the solid fixed cylinder 7, has further alleviated the secondary impact force, reduces the intensity that the in-process impact force received, has improved the practicality of this equipment.
As will be appreciated by one skilled in the art, embodiments of the present invention may be provided as a method, system, or computer program product. Accordingly, the present invention may take the form of an entirely hardware embodiment, an entirely software embodiment or an embodiment combining software and hardware aspects. Furthermore, the present invention may take the form of a computer program product embodied on one or more computer-usable storage media (including, but not limited to, disk storage, CD-ROM, optical storage, and the like) having computer-usable program code embodied therein.
It should also be noted that the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of other like elements in a process, method, article, or apparatus that comprises the element.
The above description is only an example of the present application and is not intended to limit the present application. Various modifications and changes may occur to those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application should be included in the scope of the claims of the present application.
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Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111195024.3A CN114162311B (en) | 2021-10-12 | 2021-10-12 | An electronically controlled multi-stage buffer landing gear and a method of using the same |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111195024.3A CN114162311B (en) | 2021-10-12 | 2021-10-12 | An electronically controlled multi-stage buffer landing gear and a method of using the same |
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| Publication Number | Publication Date |
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| CN114162311A true CN114162311A (en) | 2022-03-11 |
| CN114162311B CN114162311B (en) | 2022-05-24 |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5337976A (en) * | 1992-03-31 | 1994-08-16 | Messier-Bugatti | Raisable landing gear for heavier-than-air aircraft, in particular for helicopters |
| US6173920B1 (en) * | 1994-12-08 | 2001-01-16 | The Boeing Company | Very large aircraft landing gear having eight wheel truck |
| JP2003246264A (en) * | 2002-02-25 | 2003-09-02 | Kayaba Ind Co Ltd | Wheel lifting support device |
| CN206691357U (en) * | 2017-04-06 | 2017-12-01 | 天津飞悦航空零部件制造有限公司 | Durable type undercarriage |
| CN107985566A (en) * | 2017-12-07 | 2018-05-04 | 佛山市神风航空科技有限公司 | Aerial photography aircraft undercarriage with damping auxiliary wheel |
| CN111137440A (en) * | 2020-01-20 | 2020-05-12 | 潘宇泽 | Auxiliary brake retractable landing gear based on civil aircraft safe landing |
-
2021
- 2021-10-12 CN CN202111195024.3A patent/CN114162311B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5337976A (en) * | 1992-03-31 | 1994-08-16 | Messier-Bugatti | Raisable landing gear for heavier-than-air aircraft, in particular for helicopters |
| US6173920B1 (en) * | 1994-12-08 | 2001-01-16 | The Boeing Company | Very large aircraft landing gear having eight wheel truck |
| JP2003246264A (en) * | 2002-02-25 | 2003-09-02 | Kayaba Ind Co Ltd | Wheel lifting support device |
| CN206691357U (en) * | 2017-04-06 | 2017-12-01 | 天津飞悦航空零部件制造有限公司 | Durable type undercarriage |
| CN107985566A (en) * | 2017-12-07 | 2018-05-04 | 佛山市神风航空科技有限公司 | Aerial photography aircraft undercarriage with damping auxiliary wheel |
| CN111137440A (en) * | 2020-01-20 | 2020-05-12 | 潘宇泽 | Auxiliary brake retractable landing gear based on civil aircraft safe landing |
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| Publication number | Publication date |
|---|---|
| CN114162311B (en) | 2022-05-24 |
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