CN114180213B - Helicopter rotor folding and fixing system - Google Patents
Helicopter rotor folding and fixing system Download PDFInfo
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- CN114180213B CN114180213B CN202111382567.6A CN202111382567A CN114180213B CN 114180213 B CN114180213 B CN 114180213B CN 202111382567 A CN202111382567 A CN 202111382567A CN 114180213 B CN114180213 B CN 114180213B
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- helicopter
- saddle
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- bracket
- joint
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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
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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
- 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
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- 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 folding and fixing system, which comprises: the device comprises a saddle-shaped bracket (1), a supporting truss (2) and a blade locking chuck (3); the saddle-shaped support (1) is clamped above the 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 a blade of the helicopter; the saddle-shaped support (1) comprises two bent front joint supports (102), a transverse pull rod (106) and two bent rear joint supports (108), wherein the front joint supports (102) and the rear joint supports (108) are respectively connected by adopting the transverse pull rod (106) with adjustable length, the bottoms of the front joint supports (102) and the rear joint supports (108) are connected with tail beam joints (4) on tail beams by adopting a single-double-lug structure, and eccentric shaft sleeves (103) are arranged on single lugs in the single-double-lug structure. Easy adjustment, anti-overturning, high strength and less parts.
Description
Technical Field
The invention belongs to the field of helicopter rotor folding device design, and particularly relates to a helicopter rotor folding and fixing system.
Background
Due to the unique rotor wing configuration, the helicopter can finish various actions such as hovering, vertical take-off and landing, flat flight, side flight and the like, and is widely applied to complex environments such as mountain areas, oceans, deserts and the like. However, after the rotor wing is installed on the helicopter, the vertical projection area of the whole helicopter body can be obviously increased, and the helicopter occupies a large space during transportation and storage of the whole helicopter body, so that the shipment requirements of carrier platforms such as ships and large-scale conveyers are difficult to meet. Therefore, engineering personnel can fold a plurality of paddles by redesigning the hinge structure at the paddle hub, and the transportation and storage space of the helicopter is effectively reduced.
However, the folded blade still cannot meet the shipment requirement, in the shipment process, the helicopter inevitably jolts and vibrates due to the limitation of sea conditions, road conditions and carrying modes, and at the moment, the blade can follow-up to flap and swing due to the cantilever structure, so that the blade and the body structure are extremely easy to damage.
Therefore, there is an urgent need for a device or system capable of fixing the helicopter rotor after folding, avoiding damage caused by the inability to move during transportation, and ensuring the integrity of technical and tactical efficiency of the helicopter.
Disclosure of Invention
The invention provides a helicopter rotor wing folding and fixing system, which solves the problem that in the existing blade shipment process, the helicopter inevitably jolts and vibrates due to the limitation of sea conditions, road conditions and carrying modes, so that the blade is injured.
The invention provides a helicopter rotor folding and fixing system, which comprises: the device comprises a saddle 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, a plurality of blade locking chucks 3 are fixedly arranged on the support truss 2, and each blade locking chuck 3 is used for respectively clamping one blade of the helicopter;
the saddle bracket 1 comprises two bent front joint brackets 102, a transverse pull rod 106 and two bent rear joint brackets 108, wherein the two bent front joint brackets 102 and the two bent rear joint brackets 108 are respectively connected by the transverse pull rod 106, the transverse pull rod 106 is a pull rod with adjustable length, the front joint brackets 102 and the rear joint brackets 108 which are positioned above the tail beam of the helicopter and 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.
Optionally, the support truss 2 comprises: a door-shaped frame, 4 diagonal draw bars 201, a two-way screw sleeve 205 and a three-phase joint 207;
two diagonal draw bars 201 are respectively arranged in the door-shaped frame 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 door-shaped frame, the bottoms of the two diagonal rods 201 arranged in the door-shaped frame and the top of the saddle-shaped bracket 1 are fixedly connected through a three-phase joint 207 by adopting a single-double-lug structure;
the bottoms of the two diagonal draw bars 201 arranged on the side surface of the door-shaped frame are fixedly connected to the top of the saddle-shaped bracket 1 by adopting a single-double-lug structure;
the top beam of the door-shaped frame is provided with a bidirectional screw sleeve 205 for adjusting the width of the top beam.
Optionally, the saddle bracket 1 further includes: a foot pedal 105;
a foot pedal 105 is also provided between the front joint bracket 102 and the rear joint bracket 108 on the same side of the helicopter tail boom.
Optionally, a plurality of cross beams are also connected within the foot pedal 105.
Alternatively, the saddle bracket 1 and the support truss 2 are formed by square tubes.
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 heading of the helicopter as a symmetry axis.
Optionally, the blade locking clamp 3 is fixedly connected to the support truss 2 through a triangular structure bracket.
Alternatively, the two stringers 206 of the portal frame are made of titanium alloy or stainless steel material.
The invention provides a helicopter rotor folding and fixing system, which comprises: the device comprises a saddle bracket 1, a support truss 2 and a blade locking chuck 3; the saddle-shaped support 1 is clamped above the tail beam of the 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 respectively clamping one blade of the helicopter; the saddle bracket 1 comprises two bent front joint brackets 102, a transverse pull rod 106 and two bent rear joint brackets 108, wherein the two bent front joint brackets 102 and the two bent rear joint brackets 108 are respectively connected by adopting the transverse pull rod 106, the transverse pull rod 106 is a pull rod with adjustable length, the pull rod is positioned above a tail beam of a helicopter, and the front joint brackets 102 and the rear joint brackets 108 which are positioned on the same side of the tail beam of the helicopter are connected through cross beams; 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 helicopter rotor folding and fixing system provided by the invention integrates easy adjustment, anti-overturning, high strength, few parts, rapid clamping, high integration level, outstanding performance and reliable connection between structures, can realize rapid clamping under the condition of small manual operation force, is very suitable for limiting the folded helicopter rotor, and can be popularized to various requirements for folding helicopter blades. Has good innovation, practicability and economy.
Drawings
Fig. 1 is a schematic structural view of a helicopter rotor folding and fixing system provided by the invention;
FIG. 2 is a schematic view of a saddle bracket according to the present invention;
FIG. 3 is a schematic view of a structure of a support truss according to the present invention;
reference numerals illustrate:
1-a saddle-type bracket; 2-a support truss; 3-blade locking chucks;
4-tail beam joints; 101-a first quick release pin; 102-front joint bracket;
103-eccentric sleeve; 104-a first cross beam; 105-foot pedal;
106, a transverse pull rod; 107-a second cross beam; 108-a rear joint bracket;
201-diagonal draw bar; 202-a third cross beam; 203-reinforcing beams;
204—a collet support bar; 205-a two-way screw sleeve; 206—stringers;
207—three-phase joint; 208-a second quick release pin; 2051-a screw sleeve;
2052—a long screw; 2053—a square shaft; 2054-short screw.
Detailed Description
The helicopter rotor folding and fixing system provided by the invention is explained below with reference to the accompanying drawings.
As shown in fig. 1-3, the invention provides a helicopter rotor wing folding and fixing system, which mainly comprises three parts, namely a saddle bracket 1, a support truss 2 and a blade locking chuck 3.
After the helicopter rotor is folded, a saddle bracket 1, a support 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 chucks 3 and locked, so that the helicopter blades and the tail beams form an integral structure, and inertial loads received by the folded helicopter rotor are transmitted to the machine 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 sleeve 103, a first cross member 104, a foot pedal 105, a transverse pull rod 106, a second cross member 107, and a rear joint bracket 108.
The front connector bracket 102 is mainly composed of three parts including a bracket, 5 three-hole binaural connectors and 2 single-hole binaural connectors. The three-hole double-lug connectors are respectively connected with the first cross beam 104, the foot pedal 105 and the second cross beam 107 from bottom to top. The transverse pull rod 106 and the support truss 2 are respectively connected through 2 single-hole double-lug connectors.
The front joint bracket 102 is connected with the 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 boom joint 4 through the first quick release pin 101. The fine adjustment requirement when the first quick release pin 101 is inserted is achieved through the eccentric sleeve 103.
The transverse pull rod 106 is a pull rod with adjustable length, and can be provided with two parts, one part is composed of a single-lug connector and a short rod with external threads, the other part is composed of a single-lug connector and a long rod with internal threads, and the requirements of length adjustment in a certain range are met through the matching of the internal threads and the external threads, so that helicopter tail beams of different batches of frames are adapted, the problem that equipment cannot be installed due to shape and position errors when the tail beam connector 4 is installed is avoided, and the interchangeability and the universality of a rotor folding and fixing system are improved.
The foot pedal 105 is provided with 2 to 3 hollow cross beams in the horizontal direction for the operator to tread.
The rear connector bracket 108 is similar in connector structure to the front connector bracket 102 and also includes three parts, namely a bracket, a three-hole binaural connector and a single-hole binaural connector. The primary difference between the front connector bracket 102 and the rear connector bracket 108 is the number and connector orientation of the three-hole binaural connectors.
As shown in fig. 3, the support truss 2 includes a gate-type frame including a top beam and two longitudinal beams 206, and the support truss 2 further includes: 4 diagonal braces 201, a third cross beam 202, a reinforcement beam 203, a collet support bar 204, a two-way screw sleeve 205, a three-phase joint 207 and a second quick release pin 208.
The diagonal draw bar 201 has the same structure as the transverse draw bar 106 and different lengths, and the diagonal draw bar 201 transmits the overturning torque received by the support truss 2 to the saddle-shaped bracket 1, so that the strength and the stability of the whole structure are ensured. In addition, because the single-lug joints at the end parts of the four diagonal draw bars 201 can be adjusted by 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.
The support truss 2 is provided with 5 third cross beams 202 and 5 chuck support rods 204, and each chuck support rod 204 is provided with 1 blade locking chuck 1 so as to be suitable for a helicopter with 5 blades.
The duplex screw sleeve 205 is composed of a screw sleeve 2051, a long screw 2052, a square shaft 2053, and a short screw 2054. Wherein, long screw 2052 and short screw 2054 all have square groove, can insert square axle 2053, and long screw 2052 and short screw 2054's screw thread opposite direction, the pitch is the same. The sleeve 2051 is internally provided with internal threads which are respectively matched with the long screw 2052 and the short screw 2054. In use, the long screw 2052 and the short screw 2054 can be brought closer together or separated by rotating the sleeve 2051. In addition, due to the square shaft 2053, the long screw 2052 and the short screw 2054 can only move along the axial direction, relative rotation can not occur, the assembly relation of other parts is ensured, and meanwhile, the strength and the rigidity of the bidirectional screw sleeve 205 can be effectively improved.
The three-phase connector 207 has 2 single Kong Shuanger connectors and 1 three-hole double-lug connector, and the two single-hole double-lug connectors are respectively connected with the diagonal draw bar 201 and the upper end of the rear connector bracket 108.
Of the constituent parts of the support truss 2, the parts connected by the single-hole double-lug joints 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 shape of the blade. Wherein, the blade locking clamping head 3 is connected with the clamping head supporting rod 204 of the supporting truss 2 through a quick release pin, and the blade locking clamping head 3 and the supporting truss 2 form an integral structure.
The helicopter rotor folding and fixing system provided by the invention has the advantages of few parts, high modularization degree and good maintainability. The helicopter rotor wing folding and fixing device is convenient and quick to use, high in practicality and capable of meeting the use requirements of weapon equipment for rapidly folding and fixing helicopter rotor wings and rapidly unfolding and recovering combat force.
The invention adopts saddle-shaped brackets, supporting trusses and blade locking chucks to respectively realize the functions of connecting a machine body structure, carrying out load transfer, fine adjustment of the structure and clamping and fixing the blades. The main advantages are:
an eccentric shaft sleeve is designed on the saddle-shaped bracket to finely adjust and compensate shape and position errors when tail beam joints of helicopters with different frames are installed;
the saddle-shaped bracket organically combines the integral frame beams through the brackets with multiple double-lug joints, so that the connecting pieces are reduced, and the interchangeability and the universality are improved;
the saddle-shaped bracket meets the length adjustment requirement in a certain range by arranging a transverse lower pull rod;
the support truss is matched with the bidirectional screw sleeve through the diagonal draw bar, so that the flexibility of the system is effectively improved, and meanwhile, the anti-overturning capacity is improved;
the supporting truss effectively transmits the load born by the blade locking chuck to the machine body through the transverse longitudinal beam, so that the rigidity of the system is effectively increased.
The helicopter rotor folding and fixing system provided by the invention also uses quick-release pins for connection at a plurality of connection parts, so that the dismounting efficiency can be greatly improved, and the practicability of the system is improved.
The helicopter rotor folding and fixing system provided by the invention integrates easy adjustment, anti-overturning, high strength, few parts, rapid clamping, high integration level, outstanding performance and reliable connection between structures, can realize rapid clamping under the condition of small manual operation force, is very suitable for limiting the folded helicopter rotor, and can be popularized to various requirements for folding helicopter blades. Has good innovation, practicability and economy.
Claims (7)
1. A helicopter rotor folding and securing system comprising: the device comprises a saddle-shaped bracket (1), a supporting truss (2) and a blade locking chuck (3);
the saddle-shaped support (1) is clamped above the tail beam of the 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 respectively clamping one blade of the helicopter;
the saddle-shaped bracket (1) comprises two bent front joint brackets (102), a transverse pull rod (106) and two bent rear joint brackets (108), wherein the two bent front joint brackets (102) and the two bent rear joint brackets (108) are respectively connected by adopting the transverse pull rod (106), the transverse pull rod (106) is a pull rod with adjustable length and is positioned above a helicopter tail beam, and the front joint brackets (102) and the rear joint brackets (108) which are positioned on the same side of the helicopter tail beam are connected by a cross beam;
the bottoms of the front joint support (102) and the rear joint support (108) are connected with a 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 support truss (2) comprises: the device comprises a door-shaped frame, 4 diagonal rods (201), a two-way screw sleeve (205) and a three-phase joint (207);
two diagonal draw bars (201) are respectively arranged in the door-shaped frame 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 door-shaped frame, the bottoms of two diagonal draw bars (201) arranged in the door-shaped frame and the top of the saddle-shaped bracket (1) are fixedly connected through a three-phase joint (207) by adopting a single-double-lug structure;
the bottoms of the two diagonal draw bars (201) arranged on the side surface of the door-shaped frame are fixedly connected to the top of the saddle-shaped bracket (1) by adopting a single-double-lug structure;
the top beam of the door-shaped frame is provided with a bidirectional screw sleeve (205) for adjusting the width of the top beam.
2. The system according to claim 1, wherein the saddle bracket (1) further comprises: a foot pedal (105);
a foot pedal (105) is arranged between the front joint bracket (102) and the rear joint bracket (108) which are positioned on the same side of the tail beam of the helicopter.
3. The system of claim 2, wherein a plurality of cross beams are also connected within the foot pedal (105).
4. The system according to claim 1, characterized in that the saddle brackets (1) and the support trusses (2) are made of square tubes.
5. The system according to claim 1, characterized in that the number of blade locking clips (3) is determined according to the number of helicopter blades, each blade locking clip (3) being symmetrically distributed on the support truss (2) with the helicopter heading as symmetry axis.
6. The system according to claim 1, characterized in that the blade locking clip (3) is fixedly connected to the support truss (2) by means of a triangular structural support.
7. The system of claim 1, wherein the two stringers (206) of the portal frame are of a titanium alloy or stainless steel material.
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 CN114180213A (en) | 2022-03-15 |
| CN114180213B true 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) |
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| US5148924A (en) * | 1987-09-16 | 1992-09-22 | Mark Abrahams & Sons, Ltd. | Sheet material handling frame |
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| 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 |
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| FR2836889B1 (en) * | 2002-03-11 | 2004-05-28 | Eurocopter France | METHOD AND DEVICE FOR FOLDING-FOLDING THE BLADES OF A ROTOR OF A GIRAVION |
| 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 |
| CN105691281B (en) * | 2016-01-20 | 2017-10-31 | 哈尔滨飞机工业集团有限责任公司 | A kind of auto-bank unit bearing |
| 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 |
| 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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2021
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| 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 |
| 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 |
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114180213A (en) | 2022-03-15 |
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