CN114180213A - Helicopter rotor wing folding and fixing system - Google Patents
Helicopter rotor wing folding and fixing system Download PDFInfo
- Publication number
- CN114180213A CN114180213A CN202111382567.6A CN202111382567A CN114180213A CN 114180213 A CN114180213 A CN 114180213A CN 202111382567 A CN202111382567 A CN 202111382567A CN 114180213 A CN114180213 A CN 114180213A
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- support
- helicopter
- saddle
- lug
- joint
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- 230000002457 bidirectional effect Effects 0.000 claims description 8
- 229910001069 Ti alloy Inorganic materials 0.000 claims description 2
- 239000010935 stainless steel Substances 0.000 claims description 2
- 229910001220 stainless steel Inorganic materials 0.000 claims description 2
- 230000007306 turnover Effects 0.000 abstract description 4
- 230000006378 damage Effects 0.000 description 3
- 210000005069 ears Anatomy 0.000 description 3
- 230000008901 benefit Effects 0.000 description 2
- 230000010354 integration Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 230000003014 reinforcing effect Effects 0.000 description 2
- 208000027418 Wounds and injury Diseases 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 208000014674 injury Diseases 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000011295 pitch Substances 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B65—CONVEYING; PACKING; STORING; HANDLING THIN OR FILAMENTARY MATERIAL
- B65D—CONTAINERS FOR STORAGE OR TRANSPORT OF ARTICLES OR MATERIALS, e.g. BAGS, BARRELS, BOTTLES, BOXES, CANS, CARTONS, CRATES, DRUMS, JARS, TANKS, HOPPERS, FORWARDING CONTAINERS; ACCESSORIES, CLOSURES, OR FITTINGS THEREFOR; PACKAGING ELEMENTS; PACKAGES
- B65D61/00—External frames or supports adapted to be assembled around, or applied to, articles
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B65—CONVEYING; PACKING; STORING; HANDLING THIN OR FILAMENTARY MATERIAL
- B65D—CONTAINERS FOR STORAGE OR TRANSPORT OF ARTICLES OR MATERIALS, e.g. BAGS, BARRELS, BOTTLES, BOXES, CANS, CARTONS, CRATES, DRUMS, JARS, TANKS, HOPPERS, FORWARDING CONTAINERS; ACCESSORIES, CLOSURES, OR FITTINGS THEREFOR; PACKAGING ELEMENTS; PACKAGES
- B65D85/00—Containers, packaging elements or packages, specially adapted for particular articles or materials
- B65D85/68—Containers, packaging elements or packages, specially adapted for particular articles or materials for machines, engines or vehicles in assembled or dismantled form
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Mutual Connection Of Rods And Tubes (AREA)
Abstract
The invention provides a helicopter rotor wing folding and fixing system, which comprises: the device comprises a saddle-shaped bracket (1), a support truss (2) and a blade locking chuck (3); the saddle-shaped support (1) is clamped above a tail beam of the helicopter, the support truss (2) is fixedly arranged above the saddle-shaped support (1), and a plurality of blade locking chucks (3) are fixedly arranged on the support truss (2) and respectively clamp one helicopter blade; the saddle-shaped support (1) comprises two bent front joint supports (102), a transverse pull rod (106) and two bent rear joint supports (108), the front joint supports (102) and the rear joint supports (108) are connected through the transverse pull rod (106) with adjustable length respectively, the bottoms of the front joint supports (102) and the rear joint supports (108) are connected with a tail beam joint (4) on a tail beam through a single-lug and double-lug structure, and an eccentric shaft sleeve (103) is arranged on a single lug in the single-lug and double-lug structure. Easy regulation, turnover resistance, high strength and few parts.
Description
Technical Field
The invention belongs to the field of design of helicopter rotor wing folding devices, and particularly relates to a helicopter rotor wing folding and fixing system.
Background
The helicopter can complete various actions such as hovering, vertical take-off and landing, flat flying, lateral flying and the like due to the unique rotor wing configuration, and is widely applied to complex environments such as mountainous regions, oceans, deserts and the like. However, after the helicopter is provided with the rotor, the vertical projection area of the whole body can be obviously increased, and the helicopter occupies a larger space during transportation and storage of the whole machine, so that the loading and transporting requirements of carrying platforms such as ships and large-scale transport planes are difficult to meet. Therefore, engineering personnel realize the folding of the blades by redesigning the hinge structure at the hub, and effectively reduce the transportation and storage space of the helicopter.
However, the folded paddle can not meet the loading and transporting requirement, and in the loading and transporting process, the helicopter inevitably jolts and vibrates under the limitation of sea conditions, road conditions and a carrying mode, and at the moment, the paddle can flap and oscillate along with the cantilever structure, so that the paddle and the body structure are extremely easy to damage.
Therefore, there is an urgent need for a device or system for fixing a folded helicopter rotor, which avoids damage caused by immobility during transportation and ensures the integrity of the technical and tactical performance of the helicopter.
Disclosure of Invention
The invention provides a folding and fixing system for a helicopter rotor, which solves the problem that the helicopter inevitably bumps and vibrates to cause blade injury due to the limitation of sea conditions, road conditions and carrying modes in the loading and transporting process of the existing blade.
The invention provides a helicopter rotor wing folding and fixing system, which comprises: the device comprises a saddle-shaped bracket 1, a support truss 2 and a blade locking chuck 3;
the saddle-shaped support 1 is clamped above a tail beam of a helicopter, the support truss 2 is fixedly arranged above the saddle-shaped support 1, a plurality of blade locking chucks 3 are fixedly arranged on the support truss 2, and each blade locking chuck 3 is used for clamping one helicopter blade;
the saddle-shaped support 1 comprises two bent front joint supports 102, a transverse pull rod 106 and two bent rear joint supports 108, the two bent front joint supports 102 and the two bent rear joint supports 108 are respectively connected by the transverse pull rod 106, the transverse pull rod 106 is a pull rod with adjustable length and is positioned above a tail beam of the helicopter, and the front joint supports 102 and the rear joint supports 108 positioned on the same side of the tail beam of the helicopter are connected by a cross beam;
the bottoms of the front joint support 102 and the rear joint support 108 are connected with the tail beam joint 4 on the tail beam by adopting a single-double-lug structure, and an eccentric shaft sleeve 103 is arranged on a single lug in the single-double-lug structure.
Optionally, the support truss 2 includes: the device comprises a door-shaped frame, 4 diagonal draw bars 201, a bidirectional threaded sleeve 205 and a three-phase joint 207;
two diagonal draw bars 201 are respectively arranged inside and on one side surface of the door-shaped frame, and a three-phase joint 207 is arranged at the bottom of the door-shaped frame;
the bottom of the portal frame, the bottoms of two diagonal draw bars 201 arranged inside the portal frame and the top of the saddle bracket 1 are fixedly connected by a single-lug and double-lug structure through a three-phase joint 207;
the bottoms of two diagonal draw bars 201 arranged on the side surface of the portal frame are fixedly connected to the top of the saddle-shaped bracket 1 by adopting a single-lug and double-lug structure;
the top beam of the door-shaped frame is provided with a bidirectional threaded sleeve 205 for adjusting the width of the top beam.
Optionally, the saddle bracket 1 further comprises: a foot pedal 105;
a foot pedal 105 is also provided between the front and rear connector brackets 102, 108 on the same side of the helicopter tail boom.
Optionally, a plurality of beams are further connected to the inside of the footrest 105.
Optionally, the saddle-shaped support 1 and the support truss 2 are formed by square pipes.
Optionally, the number of the blade locking chucks 3 is determined according to the number of the helicopter blades, and each blade locking chuck 3 is symmetrically distributed on the support truss 2 by taking the helicopter course as a symmetry axis.
Optionally, the blade locking chuck 3 is fixedly connected to the support truss 2 through a triangular structural support.
Optionally, the two longitudinal beams 206 of the door frame are made of titanium alloy or stainless steel.
The invention provides a helicopter rotor wing folding and fixing system, which comprises: the device comprises a saddle-shaped bracket 1, a support truss 2 and a blade locking chuck 3; the helicopter tail beam locking device comprises a saddle-shaped support 1, a support truss 2, a plurality of blade locking chucks 3, a helicopter tail beam and a helicopter tail beam, wherein the saddle-shaped support 1 is clamped above the helicopter tail beam, the support truss 2 is fixedly arranged above the saddle-shaped support 1, the support truss 2 is fixedly provided with the plurality of blade locking chucks 3, and each blade locking chuck 3 is used for clamping one helicopter blade; the saddle-shaped support 1 comprises two bent front joint supports 102, a transverse pull rod 106 and two bent rear joint supports 108, the two bent front joint supports 102 and the two bent rear joint supports 108 are respectively connected by the transverse pull rod 106, the transverse pull rod 106 is a pull rod with adjustable length and is positioned above a tail beam of the helicopter, and the front joint supports 102 and the rear joint supports 108 positioned on the same side of the tail beam of the helicopter are connected by a cross beam; the bottoms of the front joint support 102 and the rear joint support 108 are connected with the tail beam joint 4 on the tail beam by adopting a single-double-lug structure, and an eccentric shaft sleeve 103 is arranged on a single lug in the single-double-lug structure. The folding and fixing system for the helicopter rotor provided by the invention integrates easy adjustment, turnover resistance, high strength, few parts, quick clamping, high integration level, outstanding performance and reliable connection between structures, can realize quick clamping under the condition of smaller manual operating force, is very suitable for limiting the folded helicopter rotor, and can be popularized to various requirements of folding helicopter blades. Has good innovation, practicability and economy.
Drawings
FIG. 1 is a schematic structural view of a helicopter rotor folding and fastening system provided in accordance with the present invention;
FIG. 2 is a schematic structural view of a saddle bracket provided by the present invention;
FIG. 3 is a schematic structural view of a support truss provided in the present invention;
description of reference numerals:
1-saddle type support; 2, supporting a truss; 3-blade locking chuck;
4-tail beam joint; 101 — a first quick release pin; 102 — front joint support;
103-eccentric shaft sleeve; 104 — a first beam; 105-a foot pedal;
106-transverse tie rod; 107 — second beam; 108 — rear joint support;
201, diagonal draw bars; 202-third beam; 203-a reinforcing beam;
204-chuck support bar; 205-bidirectional threaded sleeve; 206-longitudinal beam;
207-three phase junction; 208 — a second quick release pin; 2051-thread insert;
2052-long screw; 2053-square shaft; 2054-short screw.
Detailed Description
The folding and fixing system for helicopter rotors provided by the invention is explained below with reference to the attached drawings.
As shown in figures 1-3, the invention provides a folding and fixing system for a helicopter rotor, which mainly comprises a saddle-shaped bracket 1, a supporting truss 2 and a blade locking chuck 3.
After the helicopter rotor wing is folded, a saddle-shaped bracket 1, a supporting truss 2 and a blade locking chuck 3 are erected on a tail beam joint 4 in sequence. The blades are sequentially placed into the blade locking chuck 3 and locked, so that the helicopter blades and the tail beam form an integral structure, and inertial load received after the helicopter rotor wing is folded is transferred to the body.
As shown in fig. 2, the saddle bracket 1 is composed of a first quick release pin 101, a front joint bracket 102, an eccentric bushing 103, a first beam 104, a foot pedal 105, a transverse pull rod 106, a second beam 107 and a rear joint bracket 108.
The front joint support 102 is mainly composed of three parts including a support, 5 three-hole double-lug joints and 2 single-hole double-lug joints. The three-hole double-lug joint is connected with the first cross beam 104, the pedal plate 105 and the second cross beam 107 from bottom to top. The cross tie 106 and the supporting truss 2 are respectively connected through 2 single-hole double-lug joints.
The front joint bracket 102 is connected with an eccentric shaft sleeve 103 through a double-lug structure at the lower end of the bracket arranged on the front joint bracket, and is connected with the tail beam joint 4 through a first quick-release pin 101. The requirement of fine adjustment when the first quick release pin 101 is inserted is realized through the eccentric bushing 103.
The transverse pull rod 106 is a pull rod with adjustable length and can be provided with two parts, one part is formed by a single lug connector and a short rod with external threads, the other part is formed by a single lug connector and a long rod with internal threads, the requirement of length adjustment in a certain range is met through the matching of the internal threads and the external threads, the problem that equipment cannot be installed due to the form and position errors caused when the tail beam connector 4 is installed is solved, and the interchangeability and the universality of the rotor wing folding fixing system are improved.
The foot pedal 105 is provided with 2-3 horizontal hollow beams for an operator to step on.
Rear joint support 108 is similar in construction to front joint support 102 and includes three portions, a three-hole double lug joint and a single-hole double lug joint. The primary difference between the front joint mount 102 and the rear joint mount 108 is the number of three-hole binaural joints and the joint orientation.
As shown in fig. 3, the support truss 2 includes a door-shaped frame, the door-shaped frame includes a top beam and two longitudinal beams 206, and the support truss 2 further includes: 4 diagonal draw bars 201, a third cross beam 202, a reinforcing beam 203, a chuck support bar 204, a bidirectional threaded sleeve 205, a three-phase joint 207 and a second quick-release pin 208.
The diagonal draw bar 201 and the transverse draw bar 106 have the same structure and different lengths, and the turnover torque received by the support truss 2 is transmitted to the saddle-shaped support 1 through the diagonal draw bar 201, so that the strength and stability of the whole structure are ensured. In addition, because the single-lug joints at the ends of the four diagonal draw bars 201 can be adjusted in a certain length through internal threads, the length adjustment of the support truss 2 in multiple directions is realized, the installation error is compensated, and the overall adaptability of the system is improved.
And 5 third cross beams 202 and 5 chuck support rods 204 are arranged on the support truss 2, and 1 blade locking chuck 1 is installed on each chuck support rod 204 so as to be adapted to the helicopter with 5 blades.
The bidirectional screw sleeve 205 is composed of a screw sleeve 2051, a long screw 2052, a square shaft 2053, and a short screw 2054. The long screw 2052 and the short screw 2054 are both provided with a square groove, so that the square shaft 2053 can be inserted, the thread directions of the long screw 2052 and the short screw 2054 are opposite, and the thread pitches are the same. The screw sleeve 2051 is internally provided with internal threads which are respectively matched with the long screw 2052 and the short screw 2054. When in use, the long screw 2052 and the short screw 2054 can be moved close to or away from each other by rotating the screw 2051. In addition, due to the existence of the square shaft 2053, the long screw 2052 and the short screw 2054 can only move axially without relative rotation, so that the assembly relationship of other parts is ensured, and the strength and rigidity of the bidirectional screw sleeve 205 can be effectively improved.
Three-phase joint 207 has 2 haplopore ears to connect and 1 three hole ears connect, and two haplopore ears connect respectively with diagonal draw bar 201 and rear joint support 108 upper end and be connected.
The parts of the components of the support truss 2 that are connected by the single-hole binaural joint are locked by the second quick release pins 208.
The blade locking chuck 3 is used for clamping the blade, and any existing clamping device can be selected according to the specific appearance of the blade. The blade locking chuck 3 is connected with the chuck support rod 204 of the support truss 2 through a quick release pin, and the blade locking chuck 3 and the support truss 2 form an integral structure.
The folding and fixing system for the helicopter rotor provided by the invention has the advantages of few parts, high modularization degree and good maintainability. Convenient to use is swift, and the practicality is high, can satisfy the quick folding fixed and the rapid weapon equipment user demand who resumes the fighting capacity of expanding of helicopter rotor.
The invention adopts the saddle-shaped support, the support truss and the blade locking chuck to respectively realize the functions of connecting the machine body structure, load transmission and structure fine adjustment and blade clamping and fixing. Its main advantage has:
an eccentric shaft sleeve is designed on the saddle-shaped bracket to finely adjust and compensate the shape and position errors when the tail beam joint of the helicopter is installed at different erection times;
the saddle-shaped support organically combines the whole frame beam through the support with the multi-double lug joint, so that connecting pieces are reduced, and interchangeability and universality are improved;
the saddle-shaped bracket meets the length adjustment requirement in a certain range by arranging the transverse lower pull rod;
the support truss is matched with the bidirectional threaded sleeve for use through the diagonal draw bar, so that the flexibility of the system is effectively improved, and the anti-overturning capacity is improved;
the supporting truss effectively transmits the load received by the blade locking chuck to the machine body through the transverse longitudinal beam, and the rigidity of the system is effectively improved.
The helicopter rotor wing folding and fixing system provided by the invention is connected by using the quick-release pins at a plurality of connecting parts, so that the dismounting efficiency can be greatly improved, and the practicability of the system is improved.
The folding and fixing system for the helicopter rotor provided by the invention integrates easy adjustment, turnover resistance, high strength, few parts, quick clamping, high integration level, outstanding performance and reliable connection between structures, can realize quick clamping under the condition of smaller manual operating force, is very suitable for limiting the folded helicopter rotor, and can be popularized to various requirements of folding helicopter blades. Has good innovation, practicability and economy.
Claims (8)
1. A helicopter rotor folding and securing system, comprising: the device comprises a saddle-shaped bracket (1), a support truss (2) and a blade locking chuck (3);
the saddle-shaped support (1) is clamped above a tail beam of a helicopter, the support truss (2) is fixedly arranged above the saddle-shaped support (1), a plurality of blade locking chucks (3) are fixedly arranged on the support truss (2), and each blade locking chuck (3) is used for clamping one helicopter blade;
the saddle-shaped support (1) comprises two bent front joint supports (102), a transverse pull rod (106) and two bent rear joint supports (108), the two bent front joint supports (102) and the two bent rear joint supports (108) are respectively connected through the transverse pull rod (106), the transverse pull rod (106) is a pull rod with adjustable length and is positioned above a tail beam of the helicopter, and the front joint supports (102) and the rear joint supports (108) which are positioned on the same side of the tail beam of the helicopter are connected through a cross beam;
the bottoms of the front joint support (102) and the rear joint support (108) are connected with the tail beam joint (4) on the tail beam by adopting a single-double-lug structure, and an eccentric shaft sleeve (103) is arranged on a single lug in the single-double-lug structure.
2. The system according to claim 1, characterized in that the support truss (2) comprises: the device comprises a door-shaped frame, 4 diagonal draw bars (201), a bidirectional threaded sleeve (205) and a three-phase joint (207);
two diagonal draw bars (201) are respectively arranged inside and on one side surface of the door-shaped frame, and a three-phase joint (207) is arranged at the bottom of the door-shaped frame;
the bottom of the portal frame, the bottoms of two diagonal draw bars (201) arranged inside the portal frame and the top of the saddle-shaped bracket (1) are fixedly connected by a single-lug and double-lug structure through a three-phase joint (207);
the bottoms of two diagonal draw bars (201) arranged on the side surface of the portal frame are fixedly connected to the top of the saddle-shaped support (1) by adopting a single-lug and double-lug structure;
the top beam of the door-shaped frame is provided with a bidirectional threaded sleeve (205) for adjusting the width of the top beam.
3. The system according to claim 1, wherein the saddle bracket (1) further comprises: a foot pedal (105);
a pedal plate (105) is also arranged between the front joint support (102) and the rear joint support (108) which are positioned on the same side of the tail boom of the helicopter.
4. A system according to claim 3, characterised in that a plurality of cross beams are also connected in the footboard (105).
5. The system according to claim 1, characterized in that the saddle-shaped support (1) and the support truss (2) are made up of square tubes.
6. The system according to claim 1, characterized in that the number of blade locking grippers (3) is determined according to the number of helicopter blades, each blade locking gripper (3) being symmetrically distributed on the support truss (2) with a helicopter heading as axis of symmetry.
7. System according to claim 1, characterized in that the blade locking clip (3) is fixedly connected to the support girder (2) by means of a triangular structural support.
8. The system of claim 2, wherein the two longitudinal beams (206) of the portal frame are made of titanium alloy or stainless steel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111382567.6A CN114180213B (en) | 2021-11-19 | 2021-11-19 | Helicopter rotor folding and fixing system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111382567.6A CN114180213B (en) | 2021-11-19 | 2021-11-19 | Helicopter rotor folding and fixing system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114180213A true CN114180213A (en) | 2022-03-15 |
| CN114180213B CN114180213B (en) | 2023-04-25 |
Family
ID=80541099
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111382567.6A Active CN114180213B (en) | 2021-11-19 | 2021-11-19 | Helicopter rotor folding and fixing system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114180213B (en) |
Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| BE854327A (en) * | 1976-05-05 | 1977-11-07 | Inventec Patents Ltd | WORKSHOP |
| US5148924A (en) * | 1987-09-16 | 1992-09-22 | Mark Abrahams & Sons, Ltd. | Sheet material handling frame |
| US20040026564A1 (en) * | 2002-03-11 | 2004-02-12 | Michel Romani | Method and apparatus for folding/unfolding the blades of a rotary-wing aircraft rotor |
| CN200955254Y (en) * | 2006-09-30 | 2007-10-03 | 王雄文 | Supporting device for building |
| CN203306171U (en) * | 2013-05-14 | 2013-11-27 | 侯宇嘉 | Foldable wheelchair bicycle |
| CN203714419U (en) * | 2014-02-11 | 2014-07-16 | 江苏瑞铁轨道装备有限公司 | Whole load and transport frame used for wagon bogie |
| CN204916216U (en) * | 2015-08-05 | 2015-12-30 | 上海航空机械有限公司 | Helicopter main reducer is with synthesizing bracket |
| CN105691281A (en) * | 2016-01-20 | 2016-06-22 | 哈尔滨飞机工业集团有限责任公司 | Swashplate support |
| CN205819953U (en) * | 2016-07-18 | 2016-12-21 | 上海航空机械有限公司 | A kind of comprehensive bracket of lifting airscrew |
| CN206384098U (en) * | 2016-12-30 | 2017-08-08 | 宋树森 | A kind of folding bicycle structure |
| CN207712308U (en) * | 2017-11-29 | 2018-08-10 | 中国直升机设计研究所 | A kind of helicopter flag hanging device |
| CN208412161U (en) * | 2018-06-11 | 2019-01-22 | 中国人民解放军总参谋部第六十研究所 | A kind of unmanned helicopter rotor draw off gear |
| CN111794511A (en) * | 2020-07-17 | 2020-10-20 | 中国十九冶集团有限公司 | Protective device for construction of single-beam hanging beam working face |
-
2021
- 2021-11-19 CN CN202111382567.6A patent/CN114180213B/en active Active
Patent Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| BE854327A (en) * | 1976-05-05 | 1977-11-07 | Inventec Patents Ltd | WORKSHOP |
| US5148924A (en) * | 1987-09-16 | 1992-09-22 | Mark Abrahams & Sons, Ltd. | Sheet material handling frame |
| US20040026564A1 (en) * | 2002-03-11 | 2004-02-12 | Michel Romani | Method and apparatus for folding/unfolding the blades of a rotary-wing aircraft rotor |
| CN200955254Y (en) * | 2006-09-30 | 2007-10-03 | 王雄文 | Supporting device for building |
| CN203306171U (en) * | 2013-05-14 | 2013-11-27 | 侯宇嘉 | Foldable wheelchair bicycle |
| CN203714419U (en) * | 2014-02-11 | 2014-07-16 | 江苏瑞铁轨道装备有限公司 | Whole load and transport frame used for wagon bogie |
| CN204916216U (en) * | 2015-08-05 | 2015-12-30 | 上海航空机械有限公司 | Helicopter main reducer is with synthesizing bracket |
| CN105691281A (en) * | 2016-01-20 | 2016-06-22 | 哈尔滨飞机工业集团有限责任公司 | Swashplate support |
| CN205819953U (en) * | 2016-07-18 | 2016-12-21 | 上海航空机械有限公司 | A kind of comprehensive bracket of lifting airscrew |
| CN206384098U (en) * | 2016-12-30 | 2017-08-08 | 宋树森 | A kind of folding bicycle structure |
| CN207712308U (en) * | 2017-11-29 | 2018-08-10 | 中国直升机设计研究所 | A kind of helicopter flag hanging device |
| CN208412161U (en) * | 2018-06-11 | 2019-01-22 | 中国人民解放军总参谋部第六十研究所 | A kind of unmanned helicopter rotor draw off gear |
| CN111794511A (en) * | 2020-07-17 | 2020-10-20 | 中国十九冶集团有限公司 | Protective device for construction of single-beam hanging beam working face |
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| Publication number | Publication date |
|---|---|
| CN114180213B (en) | 2023-04-25 |
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