CN105799917A - Helicopter rotor blade mooring method and device - Google Patents
Helicopter rotor blade mooring method and device Download PDFInfo
- Publication number
- CN105799917A CN105799917A CN201610153244.2A CN201610153244A CN105799917A CN 105799917 A CN105799917 A CN 105799917A CN 201610153244 A CN201610153244 A CN 201610153244A CN 105799917 A CN105799917 A CN 105799917A
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- China
- Prior art keywords
- blade
- mooring
- blades
- helicopter rotor
- fuselage
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
- B64C27/46—Blades
- B64C27/473—Constructional features
- B64C27/50—Blades foldable to facilitate stowage of aircraft
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
Abstract
The invention discloses a helicopter rotor blade mooring method and device, and relates to the technical field of helicopters.The helicopter rotor blade mooring method is used for mooring at least three helicopter rotor blades and comprises the following steps that 1, one or two blades are selected to be parallel to a helicopter body mooring according to different even and odd numbers of blades; 2, when the even and odd numbers of the blades are different, the moored blades in the first step is adopted as a symmetric center, and the other blades are moored; 3, rigid supports are used for connecting various blade sleeves.The helicopter rotor blade mooring device comprises blade sleeves, supporting rods and rigid supports, wherein the blades needing to be moored are sleeved with the blade sleeves, one end of each supporting rod is connected with the corresponding blade sleeve, the other end of each supporting rod is connected with the helicopter body, and the rigid supports are used for connecting the blade sleeves on the blades.The helicopter rotor blade mooring method and device have the advantages that the number of the supporting rods is decreased, and the mooring efficiency of workers is improved.
Description
Technical field
The present invention relates to Helicopter Technology field, be specifically related to a kind of helicopter rotor blade mooring method and helicopter rotor blade mooring device.
Background technology
Being Appropriate application space on naval vessel, helicopter must carry out the folding of rotor when parking, for ensureing that folding rear rotor is not moved and rocks, it is necessary to folding rotor blade is carried out mooring.The size of helicopter is big, the sheet number of blade is many, traditional rotor is folding with mooring method is: rotor adopts parallel backfolding scheme, single paddle many employings support bar independently carries out mooring, this rotor is folding and mooring scheme is many to ground handling equipment requirement, every blade at least needs 1-2 support bar, and blade support bar is many, causes the weight gain of helicopter support equipment.Depopulated helicopter size is little, and paddle blade number is few, adopt traditional rotor folding and mooring scheme to easily cause the quantity of blade support bar many, increase the weight of depopulated helicopter support equipment on warship and the difficulty of operation and maintenance.
Summary of the invention
It is an object of the invention to provide a kind of helicopter rotor blade mooring method and helicopter rotor blade mooring device, to solve or the problem at least existing in mitigation technique background at least one place.
The technical solution used in the present invention is: provide a kind of helicopter rotor blade mooring method, for at least containing the helicopter rotor blade mooring of three blades, comprise the steps of step one: when blade quantity is odd number, one of them blade is parallel to fuselage mooring；When blade quantity is even number, two adjacent blades are parallel to fuselage mooring；Step 2: when blade quantity is odd number, the mooring blade in step one is symmetrical centre, all the other blades according to the distance of the mooring blade in circumferencial direction and the step one of propeller hub by near to remote symmetrical mooring successively；When blade quantity is even number, with two blades adjacent described in step one for symmetrical centre, all the other blades according to the distance of two blades adjacent with described in step one of the circumferencial direction at propeller hub by near to remote symmetrical mooring successively；Step 3: utilize rigid support to connect each blade set.
Preferably, in described step one during mooring blade, utilize blade set that the blade needing mooring is pulled to the position parallel with fuselage.
Preferably, all the other blades in described step 2 are connected by support bar and fuselage are fixing.
Preferably, first all the other blade moorings in described step 2 particularly as follows: will need the symmetrical blade of the mooring blade along circumference mooring in described step one of propeller hub to rotate, then described symmetrical blade is rotated near fuselage direction, finally described symmetrical blade is rotated 2 ° to 5 ° to the direction that two blades are close.
Preferably, described close fuselage direction rotates, it would be desirable to the blade of rotation rotates 2 ° to 5 ° relative to the blade of mooring last time near fuselage.
Present invention also offers a kind of helicopter rotor blade mooring device, comprise blade set, support bar and rigid support, wherein, described blade set is set on the blade needing mooring, described support bar one end is connected with described blade set, the other end is connected with fuselage, and described rigid support is for connecting the blade set on each blade.
Preferably, described rigid support, with triangle for elementary cell, is provided with blade set link, and the quantity of described link is identical with the quantity of blade.
The beneficial effects of the present invention is:
The helicopter rotor blade mooring method of the present invention decreases the quantity of flight support bar, improves the work efficiency of rotor blade mooring staff.
The helicopter rotor blade mooring device of the present invention utilizes rigid support to be linked together by the blade of each mooring, and rigid support is with triangle for elementary cell, and mooring is more stable.
Accompanying drawing explanation
Fig. 1 is the flow chart of the helicopter rotor blade mooring method of the present invention；
Fig. 2 is the helicopter rotor blade mooring device schematic diagram of one embodiment of the invention.
Wherein, 1-the first blade, 2-the second blade, 3-the 3rd blade, 4-support bar, 5-rigid support, 6-blade set, 7-fuselage, 8-propeller hub.
Detailed description of the invention
For making purpose of the invention process, technical scheme and advantage clearly, below in conjunction with the accompanying drawing in the embodiment of the present invention, the technical scheme in the embodiment of the present invention is further described in more detail.In the accompanying drawings, same or similar label represents same or similar element or has the element of same or like function from start to finish.Described embodiment is a part of embodiment of the present invention, rather than whole embodiments.The embodiment described below with reference to accompanying drawing is illustrative of, it is intended to is used for explaining the present invention, and is not considered as limiting the invention.Based on the embodiment in the present invention, the every other embodiment that those of ordinary skill in the art obtain under not making creative work premise, broadly fall into the scope of protection of the invention.Below in conjunction with accompanying drawing, embodiments of the invention are described in detail.
In describing the invention; it will be appreciated that; term " orientation or the position relationship of the instruction such as " center ", " longitudinal direction ", " transverse direction ", "front", "rear", "left", "right", " vertically ", " level ", " top ", " end " " interior ", " outward " be based on orientation shown in the drawings or position relationship; be for only for ease of the description present invention and simplifying and describe; rather than instruction or imply indication device or element must have specific orientation, with specific azimuth configuration and operation, therefore it is not intended that limiting the scope of the invention.
As it is shown in figure 1, a kind of helicopter rotor blade mooring method, at least containing the helicopter rotor blade mooring of three blades, comprise the steps of step one: when blade quantity is odd number, one of them blade is parallel to fuselage mooring；When blade quantity is even number, two adjacent blades are parallel to fuselage mooring；Step 2: when blade quantity is odd number, the mooring blade in step one is symmetrical centre, all the other blades according to the distance of the mooring blade in circumferencial direction and the step one of propeller hub by near to remote symmetrical mooring successively；When blade quantity is even number, with two blades adjacent described in step one for symmetrical centre, all the other blades according to the distance of two blades adjacent with described in step one of the circumferencial direction at propeller hub by near to remote symmetrical mooring successively；Step 3: utilize rigid support to connect each blade set.
The helicopter rotor blade mooring method of the present invention decreases the quantity of flight support bar, improves the work efficiency of rotor blade mooring staff.
In step one during mooring blade, utilize blade set that the blade needing mooring is pulled to the position parallel with fuselage.
All the other blades in step 2 are connected by support bar and fuselage are fixing.
First all the other blade moorings in step 2 particularly as follows: will need two symmetrical blades of mooring blade along circumference mooring in described step one of propeller hub to rotate, then described symmetrical blade is rotated near fuselage direction, finally described symmetrical blade is rotated 3 ° to the direction that two blades are close.
It is understood that the angle that described symmetrical blade rotates to the direction that two blades are close can also set according to practical situation.Such as, in an alternative embodiment, the angle that described symmetrical blade rotates to the direction that two blades are close is 2 °；In another alternative, the angle that described symmetrical blade rotates to the direction that two blades are close is 5 °；And the angle that described symmetrical blade rotates to the direction that two blades are close arbitrarily can set as required between 2 ° to 5 °.
In step 2, during all the other blades of concrete mooring, symmetrical blade rotates near fuselage direction, it would be desirable to the blade of rotation rotates 3 ° relative to the blade of mooring last time near fuselage.
It is understood that in step 2, during all the other blades of concrete mooring, it is necessary to the angle that the blade of rotation rotates near fuselage relative to the blade of mooring last time can set according to practical situation.Such as, in an alternative embodiment, it is necessary to the blade of rotation is 2 ° relative to the blade of mooring last time near the angle that fuselage rotates；In another alternative, it is necessary to the blade of rotation is 5 ° relative to the blade of mooring last time near the angle that fuselage rotates；And need the angle that the blade rotated rotates near fuselage relative to the blade of mooring last time arbitrarily can set between 2 ° to 5 ° as required.
As shown in Figure 2, present invention also offers a kind of helicopter rotor blade mooring device, comprise blade set 6, support bar 4 and rigid support 5, wherein, blade set 6 is set on the blade needing mooring, one end of support bar 4 is overlapped 6 with blade and is connected, and the other end is connected with fuselage, and rigid support 5 is for connecting the blade set 6 on each blade.
Rigid support 5, with triangle for elementary cell, is provided with blade set link, and the quantity of described link is identical with the quantity of blade.
In the helicopter rotor blade mooring device of the present embodiment, the helicopter rotor blade mooring method according to the present invention, first blade is overlapped 6 and be set on the 3rd blade 3, and the 3rd blade is pulled to and the parallel position of fuselage 7；Then blade set 6 is utilized to be respectively sleeved on the first blade 1 and the second blade 2, and the first blade 1 and the second blade 2 are rotated along the circumference of propeller hub 8 near the 3rd blade 3, until with the 3rd blade parallel position, then again the first blade 1 and the second blade 2 are rotated 3 ° near fuselage 7, last again the first blade 1 and the second blade 2 are rotated 3 ° to the direction that two blades are close, connected the blade set 6 on first blade the 1, second blade 2 and the 3rd blade 3 by rigid support 5.
Last it is noted that above example is only in order to illustrate technical scheme, it is not intended to limit.Although the present invention being described in detail with reference to previous embodiment, it will be understood by those within the art that: the technical scheme described in foregoing embodiments still can be modified by it, or wherein portion of techniques feature is carried out equivalent replacement；And these amendments or replacement, do not make the essence of appropriate technical solution depart from the spirit and scope of various embodiments of the present invention technical scheme.
Claims (7)
1. a helicopter rotor blade mooring method, at least containing the helicopter rotor blade mooring of three blades, it is characterised in that comprise the steps of
Step one: when blade quantity is odd number, one of them blade is parallel to fuselage mooring；When blade quantity is even number, two adjacent blades are parallel to fuselage mooring；
Step 2: when blade quantity is odd number, the mooring blade in step one is symmetrical centre, all the other blades according to the distance of the mooring blade in circumferencial direction and the step one of propeller hub by near to remote symmetrical mooring successively；When blade quantity is even number, with two blades adjacent described in step one for symmetrical centre, all the other blades according to the distance of two blades adjacent with described in step one of the circumferencial direction at propeller hub by near to remote symmetrical mooring successively；
Step 3: utilize rigid support to connect each blade set.
2. helicopter rotor blade mooring method as claimed in claim 1, it is characterised in that: in described step one during mooring blade, utilize blade set that the blade needing mooring is pulled to the position parallel with fuselage.
3. helicopter rotor blade mooring method as claimed in claim 1, it is characterised in that: all the other blades in described step 2 are connected by support bar and fuselage are fixing.
4. helicopter rotor blade mooring method as claimed in claim 1, it is characterized in that: first all the other blade moorings in described step 2 particularly as follows: will need the symmetrical blade of the mooring blade along circumference mooring in described step one of propeller hub to rotate, then described symmetrical blade is rotated near fuselage direction, finally described symmetrical blade is rotated 2 ° to 5 ° to the direction that two blades are close.
5. helicopter rotor blade mooring method as claimed in claim 4, it is characterised in that: described close fuselage direction rotates, it would be desirable to the blade of rotation rotates 2 ° to 5 ° relative to the blade of mooring last time near fuselage.
6. a helicopter rotor blade mooring device, it is characterized in that: comprise blade set (6), support bar (4) and rigid support (5), wherein, described blade set (6) is set on the blade needing mooring, one end of described support bar (4) is connected with described blade set (6), the other end is connected with fuselage (7), and described rigid support (7) is for connecting the blade set (6) on each blade.
7. helicopter rotor blade mooring device as claimed in claim 6, it is characterised in that: described rigid support (5), with triangle for elementary cell, is provided with blade set link, and the quantity of described link is identical with the quantity of blade.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610153244.2A CN105799917B (en) | 2016-03-17 | 2016-03-17 | A kind of helicopter rotor blade is tethered at method and helicopter rotor blade mooring device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610153244.2A CN105799917B (en) | 2016-03-17 | 2016-03-17 | A kind of helicopter rotor blade is tethered at method and helicopter rotor blade mooring device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105799917A true CN105799917A (en) | 2016-07-27 |
| CN105799917B CN105799917B (en) | 2019-11-19 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610153244.2A Active CN105799917B (en) | 2016-03-17 | 2016-03-17 | A kind of helicopter rotor blade is tethered at method and helicopter rotor blade mooring device |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110884675A (en) * | 2019-12-04 | 2020-03-17 | 中国直升机设计研究所 | Helicopter blade mooring device |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3133715A (en) * | 1961-12-22 | 1964-05-19 | Sud Aviation | Apparatus for supporting and holding foldable rotor blades of helicopters |
| US4245801A (en) * | 1979-02-15 | 1981-01-20 | United Technologies Corporation | Tail rotor control cable-pylon fold accommodation |
| US4712978A (en) * | 1986-12-01 | 1987-12-15 | Tiemann James P | Helicopter blade and the like stand-off and folding device |
| US5211538A (en) * | 1991-11-27 | 1993-05-18 | Bell Helicopter Textron Inc. | Method for folding helicopter main rotor blades |
| US6047924A (en) * | 1996-10-22 | 2000-04-11 | Eurocopter | Method of folding the blades of a main rotor of a rotary-wing aircraft, and apparatus for implementing the method |
| CN201800916U (en) * | 2010-10-12 | 2011-04-20 | 徐延宇 | Lifting folding propeller |
-
2016
- 2016-03-17 CN CN201610153244.2A patent/CN105799917B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3133715A (en) * | 1961-12-22 | 1964-05-19 | Sud Aviation | Apparatus for supporting and holding foldable rotor blades of helicopters |
| US4245801A (en) * | 1979-02-15 | 1981-01-20 | United Technologies Corporation | Tail rotor control cable-pylon fold accommodation |
| US4712978A (en) * | 1986-12-01 | 1987-12-15 | Tiemann James P | Helicopter blade and the like stand-off and folding device |
| US5211538A (en) * | 1991-11-27 | 1993-05-18 | Bell Helicopter Textron Inc. | Method for folding helicopter main rotor blades |
| US6047924A (en) * | 1996-10-22 | 2000-04-11 | Eurocopter | Method of folding the blades of a main rotor of a rotary-wing aircraft, and apparatus for implementing the method |
| CN201800916U (en) * | 2010-10-12 | 2011-04-20 | 徐延宇 | Lifting folding propeller |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110884675A (en) * | 2019-12-04 | 2020-03-17 | 中国直升机设计研究所 | Helicopter blade mooring device |
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| Publication number | Publication date |
|---|---|
| CN105799917B (en) | 2019-11-19 |
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