CN113665794A - Composite material unmanned aerial vehicle wing - Google Patents
Composite material unmanned aerial vehicle wing Download PDFInfo
- Publication number
- CN113665794A CN113665794A CN202111123155.0A CN202111123155A CN113665794A CN 113665794 A CN113665794 A CN 113665794A CN 202111123155 A CN202111123155 A CN 202111123155A CN 113665794 A CN113665794 A CN 113665794A
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- wing
- composite material
- shell plate
- spoiler
- upper shell
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- 239000002131 composite material Substances 0.000 title claims abstract description 40
- 230000007246 mechanism Effects 0.000 claims abstract description 28
- 210000003205 muscle Anatomy 0.000 claims abstract description 21
- 229910000831 Steel Inorganic materials 0.000 claims description 10
- 239000010959 steel Substances 0.000 claims description 10
- 239000000463 material Substances 0.000 claims description 8
- 239000003733 fiber-reinforced composite Substances 0.000 claims description 5
- 210000001503 joint Anatomy 0.000 claims description 4
- 229910000838 Al alloy Inorganic materials 0.000 claims description 2
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 2
- 229920006231 aramid fiber Polymers 0.000 claims description 2
- 239000004917 carbon fiber Substances 0.000 claims description 2
- 239000004744 fabric Substances 0.000 claims description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 2
- 239000011208 reinforced composite material Substances 0.000 claims description 2
- 239000010935 stainless steel Substances 0.000 claims description 2
- 229910001220 stainless steel Inorganic materials 0.000 claims description 2
- 230000000694 effects Effects 0.000 description 7
- 230000001965 increasing effect Effects 0.000 description 7
- 238000005096 rolling process Methods 0.000 description 6
- 230000008859 change Effects 0.000 description 3
- 238000005452 bending Methods 0.000 description 2
- 230000002708 enhancing effect Effects 0.000 description 2
- 238000009941 weaving Methods 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000008602 contraction Effects 0.000 description 1
- 238000012272 crop production Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 239000003814 drug Substances 0.000 description 1
- 229940079593 drug Drugs 0.000 description 1
- 230000009977 dual effect Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000002265 prevention Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 230000004044 response Effects 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/58—Wings provided with fences or spoilers
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/36—Structures adapted to reduce effects of aerodynamic or other external heating
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
A composite material unmanned aerial vehicle wing comprises a composite material wing body, a turbulence assembly and a flow guide mechanism; the composite material wing body comprises an upper shell plate, a lower shell plate and a framework; the upper shell plate is connected with the lower shell plate, the upper shell plate and the lower shell plate are both connected with the framework, the flow guide mechanism comprises a variable-stiffness skin and a pneumatic muscle driver, and the flow disturbance assembly comprises a spoiler and a driving mechanism; the spoiler is arranged at the position close to the rear edge of the wing, the spoiler is rotatably arranged on the upper shell plate, the opening of the spoiler faces the rear edge of the wing, the spoiler is driven to rotate by a driving mechanism arranged in the inner cavity of the composite material wing body, a flow guide mechanism is arranged at the wing tip of the wing, the variable-stiffness skin is vertically fixed on the upper shell plate, two pneumatic muscle drivers are arranged in the variable-stiffness skin, the two pneumatic muscle drivers are arranged in a V shape in the same vertical plane, and the V-shaped opening is arranged downwards. The invention has reasonable structural design, high pneumatic efficiency, effectively improved lift force and convenient adjustment.
Description
Technical Field
The invention relates to a wing, in particular to a composite material unmanned aerial vehicle wing.
Background
Unmanned Aerial Vehicles (UAVs) have the advantages of flexibility, quick response, unmanned flight and low operating requirements. Unmanned aerial vehicle can realize influencing real-time transmission, high-risk area detection function through carrying on multi-functional sensor, is the powerful supplementary of satellite remote sensing and traditional aviation remote sensing.
At present, the application range of the unmanned aerial vehicle is very wide in the fields of electric power, communication, meteorology, agriculture, oceans, exploration, photography, disaster prevention and reduction, crop production estimation, drug control and smuggling, border patrol, public security and counter terrorism and the like. Unmanned aerial vehicle mainly includes fixed wing unmanned aerial vehicle and rotor unmanned aerial vehicle, and the wing is one of unmanned aerial vehicle's important part, installs on the fuselage, and its most important effect is production and adjustment lift. Because the operating environment of unmanned aerial vehicle is very abominable, the height of flight is higher, and the wing is crucial, also directly influences aerodynamic efficiency.
Disclosure of Invention
The invention aims to overcome the defects of the prior art and provides the composite material unmanned aerial vehicle wing which is reasonable in structural design, high in pneumatic efficiency, capable of effectively improving the lift force and convenient to adjust.
The technical scheme of the invention is as follows:
a composite material unmanned aerial vehicle wing comprises a composite material wing body, a turbulence assembly and a flow guide mechanism; the composite material wing body comprises an upper shell plate, a lower shell plate and a framework; the upper shell plate is connected with the lower shell plate, the upper shell plate and the lower shell plate are both connected with the framework, the flow guide mechanism comprises a variable-stiffness skin and a pneumatic muscle driver, and the flow disturbance assembly comprises a spoiler and a driving mechanism;
the spoiler is arranged at the position close to the rear edge of the wing, the spoiler is rotatably arranged on the upper shell plate, the opening of the spoiler faces the rear edge of the wing, the spoiler is driven to rotate by a driving mechanism arranged in the inner cavity of the composite material wing body, a flow guide mechanism is arranged at the wing tip of the wing, the variable-stiffness skin is vertically fixed on the upper shell plate, two pneumatic muscle drivers are arranged in the variable-stiffness skin, the two pneumatic muscle drivers are arranged in a V shape in the same vertical plane, and the V-shaped opening is arranged downwards.
Compared with the prior art, the invention has the beneficial effects that:
the design of the turbulence component can be used for reducing the lift force of wings, increasing the resistance and enhancing the rolling operation, when the spoilers of the wings on two sides are symmetrically opened through the driving mechanism, the effect at the moment is mainly to increase the resistance and reduce the lift force, so that the purposes of reducing the speed and reducing the height are achieved, when the spoilers are asymmetrically opened, the wing lift forces on two sides of the unmanned aerial vehicle are asymmetrical, so that the rolling operation effect is greatly increased, the aircraft rolling is accelerated, the structure of the pneumatic muscle driver has good designability, and the pneumatic artificial muscle which is inflated and extended or contracted can be obtained by designing the weaving angle of the weaving net sleeve of the pneumatic muscle driver. When the shrinkage rate is the inflation contraction of the pneumatic muscle in right time, the elongation rate is the inflation elongation of the pneumatic muscle in right time, and the shrinkage type pneumatic muscle has the advantages that the bending rigidity is increased after the pneumatic muscle is inflated due to the fact that the bending deformation volume change rate is large due to the characteristics of the structure of the shrinkage type pneumatic muscle, the variable-rigidity skin can be vertically arranged or bent towards the outer side of the wing tip, the effect that the airflow on the lower surface of the wing tip flows to the upper surface is weakened, the lift loss is reduced, the performance of the wing is effectively improved, and the unmanned aerial vehicle can fly more stably and safely.
The technical scheme of the invention is further explained by combining the drawings and the embodiment:
drawings
Fig. 1 is a schematic structural view of a composite material unmanned aerial vehicle wing of the present invention;
FIG. 2 is a cross-sectional view of the flow directing mechanism;
fig. 3 is a schematic view of the drive mechanism.
Detailed Description
Referring to fig. 1-2, a composite material unmanned aerial vehicle wing comprises a composite material wing body 1, a spoiler assembly 2 and a flow guide mechanism 3; the composite material wing body 1 comprises an upper shell plate 1-1, a lower shell plate 1-2 and a framework; the upper shell plate 1-1 is connected with the lower shell plate 1-2, the upper shell plate 1-1 and the lower shell plate 1-2 are both connected with a framework, the flow guide mechanism 3 comprises a variable-stiffness skin 3-1 and a pneumatic muscle driver 3-2, and the turbulence component 2 comprises a spoiler 2-1 and a driving mechanism 2-2;
the spoiler 2-1 is arranged close to the rear edge of the wing, the spoiler 2-1 is rotatably arranged on the upper shell plate 1-1, the opening of the spoiler 2-1 faces the rear edge of the wing, the spoiler 2-1 is driven to rotate by a driving mechanism arranged in the inner cavity of the composite material wing body 1, a flow guide mechanism is arranged at the wing tip of the wing, the variable stiffness skin 3-1 is vertically fixed on the upper shell plate 1-1, two pneumatic muscle drivers 3-2 are arranged in the variable stiffness skin 3-1, the two pneumatic muscle drivers 3-2 are arranged in the same vertical plane in a V-shaped manner, and the V-shaped opening is arranged downwards.
As shown in fig. 1-2, in one embodiment, the number of the diversion mechanisms 3 is two, the diversion mechanisms are arranged on the upper shell plate 1-2 side by side or side by side in a staggered manner, the variable stiffness skin 3-1 bends towards the wing tip when the pneumatic muscle driver 3-2 arranged close to the wing tip contracts, and the two diversion mechanisms 3 are designed in a dual mode, so that the effect that airflow flows around the lower surface of the wing tip to the upper surface is weakened, the loss of lift force is reduced, the performance of the wing is effectively improved, and the flight of the unmanned aerial vehicle is more stable and safe.
Furthermore, the spoiler 2-1 and the upper shell plate 1-1 are connected with the torsion springs through hinges, at least one torsion spring is arranged on a shaft of each hinge, and two torsion arms of each torsion spring are respectively fixed on the spoiler 2-1 and the upper shell plate 1-1.
As shown in fig. 3, the driving mechanism comprises a motor 2-21, a driving wheel 2-22 and a steel wire rope 2-23; the motors 2-21 are arranged in the inner cavity of the composite material wing body 1, output shafts of the motors 2-21 are connected with driving wheels 2-22, steel wire ropes 2-23 are wound on wheel grooves of the driving wheels 2-22, one ends of the steel wire ropes 2-23 are fixed on the driving wheels 2-22, and the other ends of the steel wire ropes penetrate through the upper shell plate 1-1 and are fixed in the middle of the spoiler 2-1. The number of spoilers 2-1 is usually two or three.
The hinge connection enables the spoiler 2-1 to turn relative to the composite material wing body 1, so that the angle between the spoiler 2-1 and the composite material wing body 1 can be adjusted, the adjustment of the size of the airflow on the surface of the wing is realized, the operation is more convenient, the design of the spoiler 2-1 can be used for reducing the lift force of the wing, increasing the resistance and enhancing the rolling operation, when the three spoilers 2-1 of the wings on two sides of the unmanned aerial vehicle are symmetrically opened, the effect is mainly to increase the resistance and reduce the lift force at the moment, so that the purposes of reducing the speed and the height are achieved, when the three spoilers 2-1 are asymmetrically opened, the lift forces on two sides of the unmanned aerial vehicle are asymmetrical, so that the rolling operation effect is greatly increased, so that the rolling of the aircraft is accelerated, and the design of the torsion spring enables the spoiler 2-1 to have good elasticity, when the steel wire rope pulls the included angle between the lower spoiler 2-1 and the upper shell plate 1-1 to be reduced, the resistance is reduced, when the steel wire rope releases, the included angle between the spoiler 2-1 and the upper shell plate 1-1 is increased under the action of the torsion spring of the spoiler, the resistance is increased, the lift force is reduced, the purposes of reducing the speed and the height are achieved, the change of the included angle between the spoiler 2-1 and the upper shell plate 1-1 can be adjusted according to needs, the change of the resistance and the lift force is realized, and the adaptability is good.
Usually, the variable stiffness skin 3-1 is made of model airplane thermal shrinkage cloth, and the composite material wing body 1 is of a stainless steel skeleton aluminum alloy skin structure. High strength and stability. The composite material wing body 1 is made of a fiber reinforced composite material. The fiber reinforced composite material has the characteristics of light weight, high rigidity, high toughness, designability and the like, the weight is greatly reduced, and optionally, the composite material wing body 1 is made of a carbon fiber reinforced composite material or an aramid fiber reinforced composite material.
The butt joint device 4 is installed to the wing root side of combined material wing body 1, and butt joint device 4 links firmly with the unmanned aerial vehicle fuselage. Reliable connection and convenient use. A cabin door is arranged on a lower shell plate 1-1 of the composite material wing body 1. The part of the inside of wing body 1 of being convenient for operating personnel is installed and is maintained.
The present invention is not limited to the above embodiments, and those skilled in the art can make various changes and modifications without departing from the scope of the invention.
Claims (9)
1. The utility model provides a combined material unmanned aerial vehicle wing which characterized in that: comprises a composite material wing body (1), a turbulent flow component (2) and a flow guide mechanism (3); the composite material wing body (1) comprises an upper shell plate (1-1), a lower shell plate (1-2) and a framework; the upper shell plate (1-1) is connected with the lower shell plate (1-2), the upper shell plate (1-1) and the lower shell plate (1-2) are connected with a framework, the flow guide mechanism (3) comprises a variable-stiffness skin (3-1) and a pneumatic muscle driver (3-2), and the flow disturbance assembly (2) comprises a flow disturbance plate (2-1) and a driving mechanism (2-2);
the spoiler (2-1) is arranged close to the rear edge of the wing, the spoiler (2-1) is rotatably arranged on the upper shell plate (1-1), the opening of the spoiler (2-1) faces the rear edge of the wing, the spoiler (2-1) is driven to rotate by a driving mechanism arranged in the inner cavity of the composite material wing body (1), a flow guide mechanism is arranged at the wing tip of the wing, the variable-stiffness skin (3-1) is vertically fixed on the upper shell plate (1-1), two pneumatic muscle drivers (3-2) are arranged in the variable-stiffness skin (3-1), the two pneumatic muscle drivers (3-2) are arranged in a V shape in the same vertical plane, and the V-shaped opening is arranged downwards.
2. The composite material unmanned aerial vehicle wing of claim 1, wherein: the spoiler (2-1) and the upper shell plate (1-1) are connected with the torsion springs through hinges, at least one torsion spring is arranged on a shaft of each hinge, and two torsion arms of each torsion spring are respectively fixed on the spoiler (2-1) and the upper shell plate (1-1).
3. A composite material drone wing according to claim 1 or 2, characterised in that: the variable-rigidity skin (3-1) is made of model airplane thermal shrinkage cloth.
4. A composite material drone wing according to claim 1 or 2, characterised in that: the composite material wing body (1) is of a stainless steel skeleton aluminum alloy skin structure.
5. A composite material drone wing according to claim 1 or 2, characterised in that: the composite material wing body (1) is made of a fiber reinforced composite material.
6. The composite material unmanned aerial vehicle wing of claim 2, wherein: the driving mechanism comprises a motor (2-21), a driving wheel (2-22) and a steel wire rope (2-23); the motor (2-21) is arranged in the inner cavity of the composite material wing body (1), an output shaft of the motor (2-21) is connected with the driving wheel (2-22), the steel wire rope (2-23) is wound on a wheel groove of the driving wheel (2-22), one end of the steel wire rope (2-23) is fixed on the driving wheel (2-22), and the other end of the steel wire rope penetrates through the upper shell plate (1-1) and is fixed in the middle of the spoiler (2-1).
7. The composite material unmanned aerial vehicle wing of claim 5, wherein: the composite material wing body (1) is made of a carbon fiber reinforced composite material or an aramid fiber reinforced composite material.
8. The composite material unmanned aerial vehicle wing of claim 1, wherein: the butt joint device (4) is installed to the wing root side of combined material wing body (1), and butt joint device (4) links firmly with the unmanned aerial vehicle fuselage.
9. The composite material unmanned aerial vehicle wing of claim 1, wherein: a cabin door is arranged on a lower shell plate (1-1) of the composite material wing body (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111123155.0A CN113665794A (en) | 2021-09-24 | 2021-09-24 | Composite material unmanned aerial vehicle wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111123155.0A CN113665794A (en) | 2021-09-24 | 2021-09-24 | Composite material unmanned aerial vehicle wing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113665794A true CN113665794A (en) | 2021-11-19 |
Family
ID=78550096
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111123155.0A Pending CN113665794A (en) | 2021-09-24 | 2021-09-24 | Composite material unmanned aerial vehicle wing |
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| Country | Link |
|---|---|
| CN (1) | CN113665794A (en) |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2189590Y (en) * | 1994-04-27 | 1995-02-15 | 钟守生 | Propeller-swinging plane |
| CN205186508U (en) * | 2015-11-11 | 2016-04-27 | 杭州深空实业股份有限公司 | Novel many rotor unmanned aerial vehicle wing |
| CN205633015U (en) * | 2016-05-24 | 2016-10-12 | 成都中科海新材料研究所（普通合伙） | Unmanned aerial vehicle's spoiler adjusting part |
| CN106741845A (en) * | 2017-02-10 | 2017-05-31 | 哈尔滨工业大学 | A kind of empty amphibious aircraft wing distressed structure of water |
| CN106827991A (en) * | 2017-02-10 | 2017-06-13 | 哈尔滨工业大学 | A kind of empty amphibious aircraft bistable state wing of water |
| CN108988750A (en) * | 2018-06-29 | 2018-12-11 | 苏州晶旭新能源科技有限公司 | A kind of solar-electricity plate supporting device |
| CN111376878A (en) * | 2018-12-29 | 2020-07-07 | 沃尔沃汽车公司 | Auxiliary brake spoiler system |
| CN212115233U (en) * | 2020-05-26 | 2020-12-08 | 安徽华新光电饰业有限公司 | Multifunctional LED linear lamp photovoltaic distribution box |
-
2021
- 2021-09-24 CN CN202111123155.0A patent/CN113665794A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2189590Y (en) * | 1994-04-27 | 1995-02-15 | 钟守生 | Propeller-swinging plane |
| CN205186508U (en) * | 2015-11-11 | 2016-04-27 | 杭州深空实业股份有限公司 | Novel many rotor unmanned aerial vehicle wing |
| CN205633015U (en) * | 2016-05-24 | 2016-10-12 | 成都中科海新材料研究所（普通合伙） | Unmanned aerial vehicle's spoiler adjusting part |
| CN106741845A (en) * | 2017-02-10 | 2017-05-31 | 哈尔滨工业大学 | A kind of empty amphibious aircraft wing distressed structure of water |
| CN106827991A (en) * | 2017-02-10 | 2017-06-13 | 哈尔滨工业大学 | A kind of empty amphibious aircraft bistable state wing of water |
| CN108988750A (en) * | 2018-06-29 | 2018-12-11 | 苏州晶旭新能源科技有限公司 | A kind of solar-electricity plate supporting device |
| CN111376878A (en) * | 2018-12-29 | 2020-07-07 | 沃尔沃汽车公司 | Auxiliary brake spoiler system |
| CN212115233U (en) * | 2020-05-26 | 2020-12-08 | 安徽华新光电饰业有限公司 | Multifunctional LED linear lamp photovoltaic distribution box |
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Application publication date: 20211119 |
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