CN112224389A - Retractable main landing gear capable of meeting requirements of different specifications and layouts - Google Patents
Retractable main landing gear capable of meeting requirements of different specifications and layouts Download PDFInfo
- Publication number
- CN112224389A CN112224389A CN202011073020.3A CN202011073020A CN112224389A CN 112224389 A CN112224389 A CN 112224389A CN 202011073020 A CN202011073020 A CN 202011073020A CN 112224389 A CN112224389 A CN 112224389A
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- CN
- China
- Prior art keywords
- buffer
- rod
- mounting bracket
- supporting rod
- wheel
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- 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.)
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Classifications
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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
-
- 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
- B64C25/20—Operating mechanisms mechanical
-
- 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
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/58—Arrangements or adaptations of shock-absorbers or springs
Abstract
The invention discloses a retractable main landing gear capable of adapting to different specifications and layout requirements, which comprises a mounting bracket, wherein the mounting bracket comprises a main mounting bracket and a buffer mounting bracket, supporting rod rotating shafts are respectively and rotatably mounted on the left wing and the right wing of the main mounting bracket, the axes of the two groups of supporting rod rotating shafts are arranged in parallel with the left wing and the right wing of the corresponding main mounting bracket, supporting rods are respectively and rotatably mounted on the two groups of supporting rod rotating shafts, and the bottoms of the supporting rods are rotatably connected with wheel assemblies; the buffer mounting bracket is rotatably provided with a buffer rotating shaft, the axis of the buffer rotating shaft coincides with the axis of the supporting rod rotating shaft, the buffer rotating shaft is rotatably provided with a buffer supporting column, and the bottom of the buffer supporting column is rotatably connected with the bottom of the supporting rod. The invention is convenient to adjust and can be retracted and retracted, can meet the requirements of aircrafts with different specifications in a bearing range on parameters such as layout, weight, aerodynamics and the like, and reduces unnecessary design and purchase cost of the aircrafts in the development stage.
Description
Technical Field
The invention relates to the technical field of aircraft landing gears, in particular to a retractable main landing gear which can meet different specifications and layout requirements.
Background
The landing gear is used as a part of an aircraft body, the requirement of the design of the overall structure of the aircraft is firstly met, so before the layout parameters of the landing gear are considered, the landing gear is firstly designed according to the overall aerodynamic layout of the aircraft, the reasonability of the connection with the structure of the aircraft body is ensured, the conventional layout is divided into three layout modes, namely an upper single wing layout mode, a middle single wing layout mode and a lower single wing layout mode, the different layout modes are different in the parameter requirements, the installation position and the receivable space position of the landing gear, meanwhile, the landing gear is also different from the connection structure of the aircraft body, the landing gear layout is mainly different according to the requirements of the center of the aircraft and the like, and the.
Due to the particularity of the aviation industry, in order to avoid problems during the flight process and cause serious loss, in the design and development process of the aircraft, various tester models are adopted in the industry to carry out single experiment and compatibility experiment of the latest technology, or principle feasibility experiments are carried out to verify the novel experimental technology, most scaling verifiers have limited scale and weight, and the experiment purpose of most verifiers is not to carry out the technical verification of the undercarriage, therefore, the landing gear used by the verifier only needs to meet the takeoff and landing requirements of the aircraft without the need of intensive design and research, so the purchase of the model airplane landing gear becomes a common choice for the landing gear of the verifier, the existing model airplane undercarriage is poor in universality, cannot meet the design requirements of different models and bring adaptability change, the specification requirement is limited greatly, and meanwhile, most of the existing model airplane undercarriage is poor in strength and cannot be folded and unfolded.
Disclosure of Invention
The purpose of the invention is as follows: the invention aims to provide a retractable main undercarriage which can adapt to different specifications and layout requirements, solves the problems that the existing model airplane undercarriage is poor in universality and cannot meet the design requirements of different models, so that the adaptability is changed, and simultaneously solves the problems that most existing model airplane undercarriages are poor in strength and cannot be retracted. The retractable main landing gear adopts a retractable form of longitudinal retraction and unfolding-to-release, so that the landing gear can meet two layout forms of a front three point and a rear three point, can be freely selected to retract towards the front end or the tail end according to the space of a machine body, and can be suitable for the requirements of different layouts and different sizes of the type of a verification machine.
The technical scheme is as follows: the retractable main landing gear capable of adapting to different specifications and layout requirements comprises a mounting bracket, wherein the mounting bracket comprises a main mounting bracket and a buffer mounting bracket, supporting rod rotating shafts are respectively rotatably mounted on the left wing and the right wing of the main mounting bracket, the axes of the two groups of supporting rod rotating shafts are arranged in parallel with the left wing and the right wing of the corresponding main mounting bracket, supporting rods are respectively rotatably mounted on the two groups of supporting rod rotating shafts, and the bottoms of the supporting rods are rotatably connected with wheel assemblies; the buffer installation support is provided with a buffer rotating shaft in a rotating mode, the axis of the buffer rotating shaft coincides with the axis of the supporting rod rotating shaft, the buffer rotating shaft is provided with a buffer supporting column in a rotating mode, and the bottom of the buffer supporting column is connected with the bottom of the supporting rod in a rotating mode.
Further, the buffering pillar includes buffer top connecting piece, buffer and buffer base, buffer top connecting piece, buffer and buffer base connect gradually according to the order, and the one end that the buffer was kept away from to buffer top connecting piece rotates with the buffer pivot to be connected, the buffer base rotates with the bottom of bracing piece to be connected.
Further, the bracing piece includes bracing piece top journal stirrup, bracing piece pipe shaft and bracing piece base, bracing piece top journal stirrup, bracing piece pipe shaft and bracing piece base connect gradually in proper order, and the one end that the bracing piece pipe shaft was kept away from to bracing piece top journal stirrup rotates with the bracing piece pivot to be connected, the bracing piece base rotates with the wheel subassembly to be connected.
Further, the wheel assembly comprises a wheel connecting piece, a wheel spindle reinforcing disc and a wheel, the wheel connecting piece is rotatably connected with the supporting rod base, and the wheel is connected with the wheel connecting piece through the wheel spindle reinforcing disc.
Further, the installing support still includes wheel rotating assembly, wheel rotating assembly includes pull rod, receipts pole, corner pull rod support and wheel swivel connected coupler, the one end of pull rod with receive the pole and rotate and be connected, the other end of receiving the pole rotates with corner pull rod support and is connected, corner pull rod support cover is established in the bottom of bracing piece pipe shaft, corner pull rod support passes through wheel swivel connected coupler and is connected with the wheel swivel connected coupler.
Further, the wheel rotating assembly further comprises a connecting rod, a connecting rod connecting piece and a limiting buffer, the connecting rod connecting piece is rotatably installed at the end part of the retracting rod close to the pull rod, the other end of the connecting rod connecting piece is rotatably connected with the connecting rod, and the other end of the connecting rod is rotatably connected with the limiting buffer.
Furthermore, the length of the tube body of the supporting rod can be adjusted; the main mounting bracket is of a V-shaped structure, and the angles of two wings of the main mounting bracket can be adjusted; the length of the buffer support is adjustable.
The undercarriage can meet the parameter requirements of various different types of aircrafts, avoids repeated design, only needs to replace parts correspondingly loaded, and can also adjust the length of the buffer strut and the installation position of the retracting pull rod to carry out fine adjustment by adjusting the length of the tube body of the supporting rod without changing the parameters of the parts under the condition that the overall layout is not changed greatly, and can also adjust the angles of two wings of the main installation support to adapt to the requirements of aircrafts with different layouts and different specifications.
Has the advantages that: compared with the prior art, the invention has the following advantages:
(1) the undercarriage can be retracted and retracted, the overall aerodynamic performance of the airplane is improved, the undercarriage can meet two layout forms of a front three-point layout form and a rear three-point layout form by adopting a retraction and extension form of longitudinal retraction and unfolding, and the retraction of the front end or the tail end can be freely selected according to the space of the airplane body;
(2) the mounting bracket is used for connecting the undercarriage and the undercarriage, the buffer strut is used for absorbing load, the support rod provides rigid support for the undercarriage, the airplane wheel assembly meets the sliding requirement of the aircraft, the retraction actuator provides power for retraction of the undercarriage, the connection of the airplane wheel rotating assembly enables the airplane wheel to rotate along with retraction of the undercarriage, and the effective area occupied by the airplane wheel is reduced, so that the effective space required by retraction of the undercarriage is reduced;
(3) the supporting structure, the main mounting bracket and the buffer mounting bracket of the invention have adjustable mounting angles and mounting positions, so that the undercarriage is convenient to adjust and disassemble, can meet the requirements of testing machines with different specifications in the buffer bearing range on parameters such as layout, weight, aerodynamics and the like, and reduces unnecessary design and purchase cost in the aircraft development stage.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a diagram of the operational state of the present invention;
FIG. 3 is a schematic view of a wheel assembly mounting structure;
FIG. 4 is a schematic view of the wheel rotation assembly;
FIG. 5 is a schematic view of a support rod base mounting structure;
FIG. 6 is a schematic view of a base of the support rod;
FIG. 7 is a schematic view of a main mounting bracket configuration;
fig. 8 is a schematic view of a connecting rod and connecting rod connecting piece mounting structure.
Detailed Description
The invention is further described below with reference to the following figures and examples:
as shown in fig. 1 to 8, the retractable main landing gear adaptable to different specifications and layout requirements comprises a mounting bracket, wherein the mounting bracket comprises a main mounting bracket 1 and a buffer mounting bracket 2, the main mounting bracket 1 is of a V-shaped structure, a symmetrical plane of the main mounting bracket 1 is matched with a symmetrical plane of a machine body, supporting rod rotating shafts 3 are respectively and rotatably mounted on left and right wings of the main mounting bracket 1, the supporting rod rotating shafts 3 can rotate around the axes thereof, the axes of the two groups of supporting rod rotating shafts 3 are arranged in parallel with the left and right wings of the corresponding main mounting bracket 1, supporting rods 4 are respectively and rotatably mounted on the two groups of supporting rod rotating shafts 3, a rotational degree of freedom exists between the two supporting rod rotating shafts 3, the rotational center line is perpendicular to the axes of the supporting rod rotating shafts 3, and the bottom of the supporting;
the supporting rod 4 comprises a supporting rod top end support lug 41, a supporting rod tube body 42 and a supporting rod base 43, the supporting rod top end support lug 41, the supporting rod tube body 42 and the supporting rod base 43 are sequentially connected, one end, far away from the supporting rod tube body 42, of the supporting rod top end support lug 41 is rotatably connected with the supporting rod rotating shaft 3, a rotational degree of freedom exists between the supporting rod top end support lug 41 and the supporting rod rotating shaft 3, the rotating center line is perpendicular to the axis of the supporting rod rotating shaft 3, and the supporting rod base 43 is rotatably connected; when the undercarriage is in an unfolded state, the rotation center line between the support rod top end lug 41 and the support rod rotating shaft 3 is vertical to the axis of the support rod rotating shaft 3, the support rod base 43 is simultaneously connected with the buffer support columns 7, the support rods 4 and the airplane wheel assemblies 5, the symmetrical planes of the two groups of buffer support columns 7 are overlapped with the symmetrical planes of the two groups of support rod bases 43, and the buffer support columns 7 can rotate around the support rod bases 43 in the symmetrical planes of the two groups of support rod bases;
the buffer mounting bracket 2 is rotatably provided with a buffer rotating shaft 6, the axis of the buffer rotating shaft 6 is superposed with the axis of the supporting rod rotating shaft 3, the buffer rotating shaft 6 can rotate around the axis, the buffer rotating shaft 6 is rotatably provided with a buffer strut 7, and the bottom of the buffer strut 7 is rotatably connected with the bottom of the supporting rod 4;
the buffer strut 7 comprises a buffer top connecting piece 71, a buffer 72 and a buffer cushion seat 73, the buffer top connecting piece 71, the buffer 72 and the buffer cushion seat 73 are sequentially connected, one end of the buffer top connecting piece 71, which is far away from the buffer 72, is rotatably connected with the buffer rotating shaft 6, a rotational degree of freedom exists between the two, the rotation center line is vertical to the axis of the buffer rotating shaft 6, and the buffer cushion seat 73 is rotatably connected with the bottom of the supporting rod 4;
the wheel assembly 5 comprises a wheel connecting member 51, a wheel spindle reinforcing disc 52 and a wheel 53, wherein the wheel connecting member 51 is rotatably connected with the supporting rod base 43, and the wheel connecting member 51 can rotate around a connecting position with the supporting rod base 43; the airplane wheel 53 is connected with the airplane wheel connecting piece 51 through the airplane wheel main shaft reinforcing disc 52, a connecting main shaft of the airplane wheel 53 is assembled with a main mounting hole of the airplane wheel main shaft reinforcing disc 52, a gap is formed in a matching mode, an outer ring on one side of the airplane wheel main shaft reinforcing disc 52 is fixedly connected with the airplane wheel 53 through uniformly distributed bolts, a boss is arranged on the other side of the airplane wheel main shaft reinforcing disc 52 and connected with the mounting hole of the airplane wheel connecting piece 51, and a supporting part for reducing the rotating friction coefficient between the boss and the mounting hole is mounted at the connecting position; the defect that the mechanical property of the main shaft of the airplane wheel is poor when the airplane wheel of the existing landing gear is connected in a cantilever state can be overcome by arranging the airplane wheel main shaft reinforcing disc 52;
the retractable actuator 8 provides power for the retraction of the undercarriage, a telescopic rod of the retractable actuator 8 is simultaneously connected with the two groups of supporting rod rotating shafts 3 through a threaded rod end joint bearing, the supporting rod rotating shafts 3 are driven to rotate through the extension and retraction of the telescopic rod of the retractable actuator 8, so that the supporting rods 4 are driven to rotate around the supporting rod rotating shafts 3, the undercarriage is retracted, the extension process is the same as the retraction principle, and the process is opposite;
the mounting bracket further comprises an airplane wheel rotating assembly 9, the airplane wheel rotating assembly 9 comprises a pull rod 91, a retracting rod 92, a corner pull rod support 93 and an airplane wheel rotating connecting piece 94, one end of the pull rod 91 is rotatably connected with the retracting rod 92, the retracting rod 92 can rotate around the pull rod 91, the other end of the retracting rod 92 is rotatably connected with the corner pull rod support 93 and can rotate around a connecting part with the corner pull rod support 93, the corner pull rod support 93 is sleeved at the bottom of the supporting rod pipe body 42 and is positioned between the supporting rod pipe body 42 and the supporting rod base 43, the corner pull rod support 93 can rotate around the axis of the supporting rod 4, the corner pull rod support 93 is connected with the airplane wheel connecting piece 51 through the airplane wheel rotating connecting piece 94, and the airplane wheel rotating connecting piece 94 can rotate around a connecting part with the corner pull rod; the structure overcomes the defects that after the existing undercarriage is stored, the attachment degree of the airplane wheel and the undercarriage is poor, and the occupied effective space in the airplane body is too large;
meanwhile, in order to overcome the defects that the existing landing gear is easy to block or move in different directions by utilizing the mechanism with one side as a dead point position, and the mechanical property of a connecting part is poor, the wheel rotating assembly 9 further comprises a connecting rod 95, a connecting rod connecting piece 96 and a limiting buffer 97, wherein the connecting rod connecting piece 96 is rotatably arranged at the end part of the retraction rod 92 close to the pull rod 91, the other end of the connecting rod connecting piece 96 is rotatably connected with the connecting rod 95, and the other end of the connecting rod 95 is rotatably connected with the limiting buffer 97;
the undercarriage overcomes the defect that the existing undercarriage can not meet the requirements of aircrafts with different layouts and different specifications, when the aircraft types of different specifications are verified, only the length of the supporting rod pipe body 42 and the length and the size of the main mounting bracket 1 and other parts are required to be adjusted and modified correspondingly, the undercarriage can meet the requirements of aircrafts with different specifications in a bearing range on parameters such as layout, weight, aerodynamics and the like, redesign and research on the undercarriage are not required, the undercarriage can be folded and unfolded, the overall aerodynamic performance of the aircraft is improved, the undercarriage can meet the two layout forms of a front three-point layout form and a rear three-point layout form by adopting a folding and unfolding form of longitudinal folding and unfolding, and meanwhile, the undercarriage can be freely selected to fold and unfold towards the front end or the tail end according to the space of the aircraft.
Claims (7)
1. The utility model provides a retractable main undercarriage that adaptable different specifications and overall arrangement required which characterized in that: the airplane wheel assembly mounting device comprises a mounting bracket, wherein the mounting bracket comprises a main mounting bracket and a buffer mounting bracket, supporting rod rotating shafts are respectively and rotatably mounted on the left wing and the right wing of the main mounting bracket, the axes of two groups of the supporting rod rotating shafts are arranged in parallel with the left wing and the right wing of the corresponding main mounting bracket, supporting rods are respectively and rotatably mounted on the two groups of the supporting rod rotating shafts, and the bottoms of the supporting rods are rotatably connected with an airplane wheel assembly; the buffer installation support is provided with a buffer rotating shaft in a rotating mode, the axis of the buffer rotating shaft coincides with the axis of the supporting rod rotating shaft, the buffer rotating shaft is provided with a buffer supporting column in a rotating mode, and the bottom of the buffer supporting column is connected with the bottom of the supporting rod in a rotating mode.
2. A retractable main landing gear according to claim 1, adapted to meet different specifications and layout requirements, wherein: the buffer support column comprises a buffer top connecting piece, a buffer and a buffer base, wherein the buffer top connecting piece, the buffer and the buffer base are sequentially connected, one end, far away from the buffer, of the buffer top connecting piece is rotatably connected with the buffer rotating shaft, and the buffer base is rotatably connected with the bottom of the supporting rod.
3. A retractable main landing gear according to claim 1, adapted to meet different specifications and layout requirements, wherein: the bracing piece includes bracing piece top journal stirrup, bracing piece pipe shaft and bracing piece base, bracing piece top journal stirrup, bracing piece pipe shaft and bracing piece base connect gradually in proper order, and the one end that the bracing piece pipe shaft was kept away from to bracing piece top journal stirrup rotates with the bracing piece pivot to be connected, the bracing piece base rotates with the wheel subassembly to be connected.
4. A retractable main landing gear according to claim 3, wherein the retractable main landing gear is adaptable to different specifications and layout requirements, and is characterized in that: the airplane wheel assembly comprises an airplane wheel connecting piece, an airplane wheel main shaft reinforcing disc and an airplane wheel, the airplane wheel connecting piece is rotatably connected with the supporting rod base, and the airplane wheel is connected with the airplane wheel connecting piece through the airplane wheel main shaft reinforcing disc.
5. A retractable main landing gear capable of meeting different specifications and layout requirements according to claim 4, wherein: the mounting bracket further comprises a wheel rotating assembly, the wheel rotating assembly comprises a pull rod, a retracting rod, a corner pull rod support and a wheel rotating connecting piece, one end of the pull rod is connected with the retracting rod in a rotating mode, the other end of the retracting rod is connected with the corner pull rod support in a rotating mode, the corner pull rod support is sleeved at the bottom of the supporting rod pipe body, and the corner pull rod support is connected with the wheel rotating connecting piece through the wheel rotating connecting piece.
6. A retractable main landing gear capable of meeting different specifications and layout requirements according to claim 5, wherein: the airplane wheel rotating assembly further comprises a connecting rod, a connecting rod connecting piece and a limiting buffer, the connecting rod connecting piece is rotatably installed at the end portion, close to the pull rod, of the retraction rod, the other end of the connecting rod connecting piece is rotatably connected with the connecting rod, and the other end of the connecting rod is rotatably connected with the limiting buffer.
7. A retractable main landing gear according to claim 3, wherein the retractable main landing gear is adaptable to different specifications and layout requirements, and is characterized in that: the length of the supporting rod pipe body is adjustable; the main mounting bracket is of a V-shaped structure, and the angles of two wings of the main mounting bracket can be adjusted; the length of the buffer support is adjustable.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011073020.3A CN112224389B (en) | 2020-10-09 | 2020-10-09 | Retractable main landing gear capable of meeting requirements of different specifications and layouts |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011073020.3A CN112224389B (en) | 2020-10-09 | 2020-10-09 | Retractable main landing gear capable of meeting requirements of different specifications and layouts |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112224389A true CN112224389A (en) | 2021-01-15 |
| CN112224389B CN112224389B (en) | 2022-04-19 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202011073020.3A Active CN112224389B (en) | 2020-10-09 | 2020-10-09 | Retractable main landing gear capable of meeting requirements of different specifications and layouts |
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Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0615901A1 (en) * | 1993-03-15 | 1994-09-21 | Messier Bugatti | Aircraft landing gear with lateral retraction |
| CN101637658A (en) * | 2009-07-24 | 2010-02-03 | 珠海海曼电子模型有限公司 | Electric retractable undercarriage of prototype aircraft |
| GB201203248D0 (en) * | 2012-02-24 | 2012-04-11 | Messier Dowty Ltd | Landing gear |
| CN202783777U (en) * | 2012-08-24 | 2013-03-13 | 董韬 | Unmanned aerial vehicle undercarriage |
| CN104290902A (en) * | 2014-08-26 | 2015-01-21 | 中国直升机设计研究所 | Rocking arm-type undercarriage |
| CN204895841U (en) * | 2015-01-09 | 2015-12-23 | 成都飞机设计研究所 | Be provided with an arm -type main landing gear of buffer |
| CN206374970U (en) * | 2017-01-09 | 2017-08-04 | 宿迁市飞鹰模具开发科技有限公司 | A kind of fixed-wing unmanned plane front foot frame retracting device |
| CN206427263U (en) * | 2017-02-09 | 2017-08-22 | 四川中飞赛维航空科技有限公司 | multi-rotor unmanned aerial vehicle undercarriage |
| CN206528627U (en) * | 2017-02-09 | 2017-09-29 | 深圳光启飞行包科技有限公司 | Undercarriage for aircraft |
| CN108860607A (en) * | 2018-06-19 | 2018-11-23 | 智飞智能装备科技东台有限公司 | It is a kind of from steady wind resistance unmanned plane |
| CN109263874A (en) * | 2018-10-30 | 2019-01-25 | 佛山市神风航空科技有限公司 | A kind of oil electric mixed dynamic multi-rotor aerocraft |
| CN208544417U (en) * | 2018-06-04 | 2019-02-26 | 四川航泰航空装备有限公司 | A kind of unmanned plane main landing gear |
| CN110834721A (en) * | 2018-08-17 | 2020-02-25 | 中国飞机强度研究所 | Leg sledge combined landing device of vertical take-off and landing aircraft |
-
2020
- 2020-10-09 CN CN202011073020.3A patent/CN112224389B/en active Active
Patent Citations (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0615901A1 (en) * | 1993-03-15 | 1994-09-21 | Messier Bugatti | Aircraft landing gear with lateral retraction |
| CN101637658A (en) * | 2009-07-24 | 2010-02-03 | 珠海海曼电子模型有限公司 | Electric retractable undercarriage of prototype aircraft |
| GB201203248D0 (en) * | 2012-02-24 | 2012-04-11 | Messier Dowty Ltd | Landing gear |
| US20150041587A1 (en) * | 2012-02-24 | 2015-02-12 | Messier-Dowty Limited | Landing gear |
| CN202783777U (en) * | 2012-08-24 | 2013-03-13 | 董韬 | Unmanned aerial vehicle undercarriage |
| CN104290902A (en) * | 2014-08-26 | 2015-01-21 | 中国直升机设计研究所 | Rocking arm-type undercarriage |
| CN204895841U (en) * | 2015-01-09 | 2015-12-23 | 成都飞机设计研究所 | Be provided with an arm -type main landing gear of buffer |
| CN206374970U (en) * | 2017-01-09 | 2017-08-04 | 宿迁市飞鹰模具开发科技有限公司 | A kind of fixed-wing unmanned plane front foot frame retracting device |
| CN206427263U (en) * | 2017-02-09 | 2017-08-22 | 四川中飞赛维航空科技有限公司 | multi-rotor unmanned aerial vehicle undercarriage |
| CN206528627U (en) * | 2017-02-09 | 2017-09-29 | 深圳光启飞行包科技有限公司 | Undercarriage for aircraft |
| CN208544417U (en) * | 2018-06-04 | 2019-02-26 | 四川航泰航空装备有限公司 | A kind of unmanned plane main landing gear |
| CN108860607A (en) * | 2018-06-19 | 2018-11-23 | 智飞智能装备科技东台有限公司 | It is a kind of from steady wind resistance unmanned plane |
| CN110834721A (en) * | 2018-08-17 | 2020-02-25 | 中国飞机强度研究所 | Leg sledge combined landing device of vertical take-off and landing aircraft |
| CN109263874A (en) * | 2018-10-30 | 2019-01-25 | 佛山市神风航空科技有限公司 | A kind of oil electric mixed dynamic multi-rotor aerocraft |
Also Published As
| Publication number | Publication date |
|---|---|
| CN112224389B (en) | 2022-04-19 |
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