CN110116803B - Variable chord length system for blade - Google Patents
Variable chord length system for blade Download PDFInfo
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- CN110116803B CN110116803B CN201910360934.9A CN201910360934A CN110116803B CN 110116803 B CN110116803 B CN 110116803B CN 201910360934 A CN201910360934 A CN 201910360934A CN 110116803 B CN110116803 B CN 110116803B
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- shape memory
- memory alloy
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- alloy wire
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- 229910001285 shape-memory alloy Inorganic materials 0.000 claims abstract description 43
- 238000000034 method Methods 0.000 claims description 8
- 238000010438 heat treatment Methods 0.000 claims description 6
- 230000005540 biological transmission Effects 0.000 claims description 5
- 238000005192 partition Methods 0.000 claims description 4
- HZEWFHLRYVTOIW-UHFFFAOYSA-N [Ti].[Ni] Chemical compound [Ti].[Ni] HZEWFHLRYVTOIW-UHFFFAOYSA-N 0.000 claims description 3
- 229910001000 nickel titanium Inorganic materials 0.000 claims description 3
- 229920002302 Nylon 6,6 Polymers 0.000 claims description 2
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 2
- 229910052782 aluminium Inorganic materials 0.000 claims description 2
- 230000003068 static effect Effects 0.000 claims description 2
- 125000006850 spacer group Chemical group 0.000 claims 1
- 230000000670 limiting effect Effects 0.000 description 3
- 238000005452 bending Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000002829 reductive effect Effects 0.000 description 2
- 239000000956 alloy Substances 0.000 description 1
- 230000008094 contradictory effect Effects 0.000 description 1
- 230000001627 detrimental effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000005489 elastic deformation Effects 0.000 description 1
- 238000004134 energy conservation Methods 0.000 description 1
- 230000006870 function Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000036961 partial effect Effects 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
- 230000000452 restraining effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Images
Classifications
-
- 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
-
- 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
- B64C2027/4733—Rotor blades substantially made from particular materials
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
Abstract
The embodiment of the invention discloses a variable chord length system for a blade, relates to the technical field of rotor crafts, and can adjust the chord length of the blade. The invention comprises the following steps: two ends of the spring (5) are fixedly connected with the front edge clapboard and the rear edge clapboard of the cross-shaped mixed honeycomb structure (6); one end of a driving wire system (4) is fixedly connected with a driver sliding block (2), and after the driving wire system bypasses a pulley block e and passes through a sliding block (7), one end of the driving wire bypasses a tail direction changer (9) at the rear edge of the blade to change the pulling force direction and is fixedly connected with a cross-shaped mixed honeycomb structure (6); the shape memory alloy wire (1) rounds the two ends of the pulley blocks a, b, c and d and is respectively fixedly connected with the two driver sliding blocks and connected with the power supply device (10). The shape memory alloy wire (1) is electrified to generate deformation, the driving wire system (4) is driven to stretch the cross-shaped mixed honeycomb structure (6), and the cross-shaped mixed honeycomb structure (6) is reset through the spring when the electrification is cancelled. The invention is suitable for the variable chord length of the rotor craft.
Description
Technical Field
The invention relates to the technical field of rotorcraft, in particular to a variable chord length system for a blade.
Background
At present, large-to-heavy transport helicopters, small-to-rotor unmanned aerial vehicles, and rotor aircrafts have been applied to many fields due to the characteristics of hovering, flexible taking-off and landing and the like.
Blade design is an important part of the development process of a rotorcraft, and as with many aircraft designs, many design parameters are actually contradictory and difficult to balance, such as: the large chord length configuration can reduce the required power and relieve the stall problem when the performance of the rotor wing is close to the flight envelope boundary by increasing the chord length of the blade; however, at low gross weight and low altitude, the large chord configuration consumes more power and is detrimental to flight.
If one wants to further increase the versatility of a rotorcraft, one needs to take care of more design criteria, which makes the design of the blades more difficult.
Disclosure of Invention
Embodiments of the present invention provide a variable chord length system for a blade that is capable of adjusting the chord length of the blade.
In order to achieve the above purpose, the embodiment of the invention adopts the following technical scheme:
the embodiment of the invention discloses a blade chord length changing system, relates to the technical field of helicopters, and can adjust the chord length of a blade. The invention comprises the following steps:
the device comprises a shape memory alloy wire 1, a driver sliding block 2, a driver guide rail 3, a driving wire system 4, a spring 5, a cross-shaped mixed honeycomb structure 6, a sliding block 7, a guide rail 8, a tail direction changer 9, a power supply device 10, pulley blocks a, b, c, d and e.
Two ends of the spring 5 are fixedly connected with the front edge clapboard and the rear edge clapboard of the cross-shaped mixed honeycomb structure 6; one end of a driving wire system 4 is fixedly connected with the driver sliding block 2, and after bypassing the pulley block e and passing through the sliding block 7, one end bypasses the tail deviator 9 and is fixedly connected with the cross-shaped hybrid honeycomb structure 6; the shape memory alloy wire 1 is wound around the two ends of the pulley blocks a, b, c and d, is respectively fixedly connected with the two driver sliding blocks and is connected with the power supply device 10.
The shape memory alloy wire 1 is electrified to generate deformation, the driving wire system 4 is driven to stretch the cross-shaped mixed honeycomb structure 6, and the cross-shaped mixed honeycomb structure 6 is reset through the spring when the electrification is cancelled.
The embodiment realizes the change of the chord length of the blade of the rotorcraft, so that the chord length of the rotorcraft can be changed according to the situation in the flight process.
Compared with the traditional blade chord length changing system driven by springs and centrifugal force or driven by hydraulic pressure, the honeycomb structure has light weight and high surface rigidity, and the weight of the aircraft can be reduced.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings needed to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without creative efforts.
FIG. 1 is a schematic structural view of a blade according to an embodiment of the present invention at a normal chord length state;
FIG. 2 is a schematic structural diagram of a blade in a variable chord length state according to an embodiment of the present invention;
fig. 3 is a comparison graph of chord lengths of a blade in a normal chord length state and a blade in a variable chord length state according to an embodiment of the present invention.
FIG. 4 is a schematic side view and a schematic positional relationship of a part of the components according to an embodiment of the present invention;
FIG. 5 is an enlarged partial view of the trailing edge of a blade provided by an embodiment of the present invention;
FIG. 6 is a front view and a top view of the slider (7) with the drive line system (4) and the spring (5) passing through the opening according to the embodiment of the present invention;
FIG. 7 is a partially enlarged view and a connection manner of the shape memory alloy wire (1), the driving wire system (4) and the slider (2) according to the embodiment of the present invention;
fig. 8 is a schematic structural diagram of the slider (2) and the guide rail (3) according to the embodiment of the present invention.
Detailed Description
In order to make the technical solutions of the present invention better understood, the present invention will be described in further detail with reference to the accompanying drawings and specific embodiments. Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the accompanying drawings are illustrative only for the purpose of explaining the present invention, and are not to be construed as limiting the present invention. As used herein, the singular forms "a", "an", "the" and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise. It will be further understood that the terms "comprises" and/or "comprising," when used in this specification, specify the presence of stated features, integers, steps, operations, elements, and/or components, but do not preclude the presence or addition of one or more other features, integers, steps, operations, elements, components, and/or groups thereof. It will be understood that when an element is referred to as being "connected" or "coupled" to another element, it can be directly connected or coupled to the other element or intervening elements may also be present. Further, "connected" or "coupled" as used herein may include wirelessly connected or coupled. As used herein, the term "and/or" includes any and all combinations of one or more of the associated listed items. It will be understood by those skilled in the art that, unless otherwise defined, all terms (including technical and scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. It will be further understood that terms, such as those defined in commonly used dictionaries, should be interpreted as having a meaning that is consistent with their meaning in the context of the prior art and will not be interpreted in an idealized or overly formal sense unless expressly so defined herein.
An embodiment of the present invention provides a variable chord length system for a blade, as shown in fig. 1, the variable chord length system includes:
a driving device (I), a transmission device (II) and a cross-shaped mixed honeycomb structure (6).
The drive device (I) comprises: the device comprises a shape memory alloy wire (1), a driver sliding block (2), a driver guide rail (3), a power supply device (10) and a fixing device.
The transmission (II) comprises: the device comprises a driving line system (4), a spring (5), a sliding block (7), a guide rail (8), a tail deviator (9), a pulley block (a), a pulley block (b), a pulley block (c), a pulley block (d) and a pulley block (e).
Two ends of the spring (5) are respectively and fixedly connected with the front edge and the rear edge of the cross-shaped mixed honeycomb structure (6) through the partition boards. The crisscross hybrid honeycomb structure can be also called a crisscross flexible honeycomb structure, is a hybrid honeycomb composed of an N-type structure and an H-type structure, is currently in the research front, and is mainly applied to flexible skins. The configuration of the cross-shaped mixed honeycomb can not only have larger in-plane deformation, but also obtain larger out-plane bending rigidity by adjusting and optimizing unit parameters and other measures in the design, and the configuration is relatively in line with the requirements of the design on elastic deformation materials.
One end of a driving line system (4) is fixedly connected with a driver sliding block (2), the driving line system (4) bypasses a pulley block (e) and penetrates a sliding block (7), and one end of the driving line system (4) bypasses a tail direction changer (9) and is fixedly connected with a cross-shaped hybrid honeycomb structure (6). The tail deviator (9) is installed at the rear edge of the blade and used for changing the direction of the pulling force of the driving line system (4).
The shape memory alloy wire (1) sequentially bypasses two ends of the pulley block (a), two ends of the pulley block (b), two ends of the pulley block (c) and two ends of the pulley block (d).
The shape memory alloy wire (1) is respectively and fixedly connected with the two driver sliding blocks (2).
The shape memory alloy wire (1) is connected with a power supply device (10).
When the chord length of the blade is at the initial chord length, the pre-stretched spring (5) applies compressive stress to the moving end of the cross-shaped mixed honeycomb structure (6) through the connected front edge and rear edge clapboards of the cross-shaped mixed honeycomb structure (6). The cross hybrid honeycomb (6) is prevented from being compressed by the spring (5) to less than the initial chord length by a stopper end provided on the driver guide rail (3).
The whole mechanism can be in the original length in the most time in flight, the pre-stretched spring (5) is connected with the front edge partition plate and the rear edge partition plate of the cross-shaped mixed honeycomb structure (6), and uniform pressure stress is applied to the moving end of the cross-shaped mixed honeycomb structure (6). Meanwhile, the spring (5) provides a certain restraining force for the cross-shaped mixed honeycomb structure (6) under the original length state without driving force, and the mechanism chord length is prevented from being changed when the driving device is not started. Meanwhile, a corresponding limiting end is also arranged on the driver guide rail (3) to prevent the cross-shaped mixed honeycomb structure (6) from being compressed to be smaller than the initial chord length by the spring (5).
For example, as shown in figure 1, two ends of the spring (5) are fixedly connected with the front edge clapboard and the rear edge clapboard of the cross-shaped mixed honeycomb structure (6). One end of the driving wire system (4) is fixedly connected with the driver sliding block (2), and after bypassing the pulley block e and passing through the sliding block (7), one end bypasses the tail deviator (9) and is fixedly connected with the cross-shaped mixed honeycomb structure (6). The shape memory alloy wire (1) rounds the two ends of the pulley blocks a, b, c and d and is respectively fixedly connected with the two driver sliding blocks and connected with the power supply device (10). The pre-stretched spring (5) is connected with the front edge clapboard and the rear edge clapboard of the cross-shaped mixed honeycomb structure (6), uniform compressive stress is applied to the moving end of the cross-shaped mixed honeycomb structure (6), certain constraint force is applied to the cross-shaped mixed honeycomb structure (6) under the original length state without driving force, and the mechanism chord length is prevented from being changed when the driving device is not started. Meanwhile, a corresponding limiting end is also arranged on the driver guide rail (3) to prevent the spring from compressing the honeycomb to be smaller than the initial chord length.
In a preferred embodiment of the present invention, the drive line system (4) is formed by a static rope made of nylon 66.
The shape memory alloy wire (1) can be made of nickel-titanium shape memory alloy. And provides a power-on strategy of the shape memory alloy wire based on the nickel-titanium shape memory alloy material, which comprises the following steps:
heating the shape memory alloy wire (1) to 45 degrees after electrifying 6A current in the shape memory alloy wire (1); then, when the shape memory alloy wire (1) is naturally cooled to the temperature lower than 30 ℃, electrifying the 6A current again until the temperature of the shape memory alloy wire (1) is heated again to 45 ℃; the process is repeated, and after the current of 6A is kept electrified, the temperature of the shape memory alloy wire (1) fluctuates within the range of 30-45 degrees.
Wherein, the maximum heating temperature of the shape memory alloy wire (1) is set to 55 degrees under the consideration of energy conservation, so the maximum heating temperature is set to 55 degrees, 6A current is used for heating to the temperature, the temperature is naturally cooled until the temperature is lower than 30 degrees, and the temperature is heated again to 45 degrees. Therefore, the mechanism can be ensured to keep a state of variable chord length, and the mechanism does not need to be heated all the time, thereby saving energy.
When the blade chord length needs to be increased, the power supply device (10) energizes the shape memory alloy wire (1). After the shape memory alloy wire (1) is deformed, the driver sliding block (2) is pulled to move along the driver guide rail (3), the driving wire system (4) is driven to generate pulling force to pull the cross-shaped mixed honeycomb structure (6), and the sliding blocks (7) at the two ends of the cross-shaped mixed honeycomb structure (6) move along the guide rail (8), so that the chord length of the paddle is increased.
For example: when the power supply device (10) energizes the shape memory alloy wire (1), the shape memory alloy wire (1) deforms and provides tension, and the tension is transmitted to the cross-shaped mixed honeycomb structure (6) through the transmission device (II) to stretch the cross-shaped mixed honeycomb structure so as to achieve the effect of changing the chord length of the paddle. When the current is cut off, the shape memory alloy wire (1) recovers to the original length, the spring (5) recovers and deforms the cross-shaped mixed honeycomb structure (6), and the chord length returns to the original length. For example, as shown in fig. 2, a current is supplied to the shape memory alloy wire (1) through the power supply device (10), heat is generated to deform the shape memory alloy wire and pull the driver slider (2) to move along the driver guide rail (3), the drive wire system (4) is driven to generate a pulling force and pull the cross-shaped hybrid honeycomb structure (6), and sliders (7) at two ends of the cross-shaped hybrid honeycomb structure move along the guide rail (8) to increase the chord length of the blade.
The embodiment realizes the change of the chord length of the blade of the rotorcraft, so that the chord length of the rotorcraft can be changed according to the situation in the flight process.
Compared with the traditional blade chord length changing system driven by springs and centrifugal force or driven by hydraulic pressure, the honeycomb structure has light weight and high surface rigidity, and the weight of the aircraft can be reduced.
Furthermore, ribs made of thin aluminum strips can be added into the cross-shaped mixed honeycomb, so that an H-shaped structure is obtained, the bending resistance in the vertical direction is improved, and the structural strength of the blade in the edge chord length process is further improved.
The blade variable-chord length system provided by the embodiment selects an S300-C helicopter as a prototype. The chord length of the blade is 171mm, and the diameter is 8.18 m. The length of the shape memory alloy wire is 1m, the deformation after current is applied is 42mm, and the requirement that the chord length can be increased by 20 percent is met.
The embodiments in the present specification are described in a progressive manner, and the same and similar parts among the embodiments are referred to each other, and each embodiment focuses on the differences from the other embodiments. In particular, for the apparatus embodiment, since it is substantially similar to the method embodiment, it is relatively simple to describe, and reference may be made to some descriptions of the method embodiment for relevant points. The above description is only for the specific embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are included in the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (5)
1. A variable chord length system for a blade, the variable chord length system comprising in combination:
the device comprises a driving device (I), a transmission device (II) and a cross-shaped mixed honeycomb structure (6);
the drive device (I) comprises: the shape memory alloy wire (1), the driver sliding block (2), the driver guide rail (3), the power supply device (10) and the fixing device;
the transmission (II) comprises: the device comprises a driving line system (4), a spring (5), a sliding block (7), a guide rail (8), a tail deviator (9), a pulley block a, a pulley block b, a pulley block c, a pulley block d and a pulley block e;
two ends of the spring (5) are respectively fixedly connected with the front edge and the rear edge of the cross-shaped mixed honeycomb structure (6) through the partition boards;
one end of a driving wire system (4) is fixedly connected with the driver sliding block (2), the driving wire system (4) bypasses the pulley block e and penetrates through the sliding block (7), and one end of the driving wire system (4) bypasses the tail direction changer (9) and is fixedly connected with the cross-shaped hybrid honeycomb structure (6);
the shape memory alloy wire (1) sequentially bypasses two ends of the pulley block a, two ends of the pulley block b, two ends of the pulley block c and two ends of the pulley block d;
the shape memory alloy wire (1) is respectively and fixedly connected with the two driver sliding blocks (2);
the shape memory alloy wire (1) is connected with a power supply device (10);
when the chord length of the paddle is increased, the power supply device (10) is electrified to the shape memory alloy wire (1);
after the shape memory alloy wire (1) is deformed, the driver sliding block (2) is pulled to move along the driver guide rail (3), the driving wire system (4) is driven to generate pulling force to pull the cross-shaped mixed honeycomb structure (6), and the sliding blocks (7) at the two ends of the cross-shaped mixed honeycomb structure (6) move along the guide rail (8);
the shape memory alloy wire (1) is nickel-titanium shape memory alloy;
setting the highest heating temperature of the shape memory alloy wire (1) to be 55 degrees;
further comprising:
s1, heating the shape memory alloy wire (1) to 45 degrees after the shape memory alloy wire (1) is electrified with 6A current;
s2, after that, when the shape memory alloy wire (1) is naturally cooled to a temperature lower than 30 ℃, the current of 6A is electrified again until the temperature of the shape memory alloy wire (1) is heated again to 45 ℃;
repeating the processes S1-S2, and keeping the electrified 6A current, the temperature of the shape memory alloy wire (1) fluctuates within the range of 30-45 degrees.
2. A variable chord length system for a blade according to claim 1 wherein the pre-stretched springs (5) apply compressive stress to the moving end of the cross-shaped hybrid honeycomb (6) through the attached cross-shaped hybrid honeycomb (6) leading and trailing edge spacers when the chord length of the blade is at the initial chord length.
3. A variable chord length system for a blade according to claim 2 wherein the cross hybrid honeycomb (6) is prevented from being compressed to less than the initial chord length by a spring (5) by a stop end provided on the actuator guide rail (3).
4. A variable chord length system for a blade according to claim 1 wherein the drive line system (4) is comprised of static rope of nylon 66.
5. The variable chord length system for a blade of claim 1, further comprising:
thin aluminum strips are used as ribs in the cross-shaped hybrid honeycomb structure (6), so that an H-shaped structure in the cross-shaped hybrid honeycomb structure (6) is obtained.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910360934.9A CN110116803B (en) | 2019-04-30 | 2019-04-30 | Variable chord length system for blade |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910360934.9A CN110116803B (en) | 2019-04-30 | 2019-04-30 | Variable chord length system for blade |
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| Publication Number | Publication Date |
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| CN110116803A CN110116803A (en) | 2019-08-13 |
| CN110116803B true CN110116803B (en) | 2022-05-03 |
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| CN201910360934.9A Active CN110116803B (en) | 2019-04-30 | 2019-04-30 | Variable chord length system for blade |
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| CN111605703B (en) * | 2020-04-28 | 2022-04-08 | 南京航空航天大学 | Variable chord length system for variable rotating speed tail rotor blade of helicopter |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN101665156A (en) * | 2008-09-03 | 2010-03-10 | 北京航空航天大学 | Connecting and unlocking mechanism driven by SMA wire |
| CN101362339A (en) * | 2008-09-28 | 2009-02-11 | 哈尔滨工业大学 | Deployable/folding arm driven by shape memory alloy spring |
| CN101503113A (en) * | 2009-03-23 | 2009-08-12 | 哈尔滨工业大学 | Shape memory spring driven hinder margin camber variable wing |
| CN102582823A (en) * | 2009-03-27 | 2012-07-18 | 哈尔滨工业大学 | Airfoil capable of realizing deformation in wingspan direction or chord length direction |
| CN102072125B (en) * | 2011-01-19 | 2012-11-28 | 南京航空航天大学 | One-way shape memory effect-based two-way linear driver and method thereof |
| CN103158860B (en) * | 2013-03-19 | 2015-01-07 | 哈尔滨工业大学 | Variable trailing edge wing driven by combination of shape memory alloy and piezoelectric fibrous composite material |
| CN104443354B (en) * | 2014-11-21 | 2016-10-12 | 南京航空航天大学 | A kind of wing with self adaptation variable camber trailing edge |
| CN108045553A (en) * | 2017-11-29 | 2018-05-18 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of variable camber trailing edge |
| CN108100228A (en) * | 2017-11-30 | 2018-06-01 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of active flexible Telescopic truss structure |
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