CN117227965A - Variable camber airfoil structure with deformation feedback - Google Patents
Variable camber airfoil structure with deformation feedback Download PDFInfo
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- CN117227965A CN117227965A CN202311450340.XA CN202311450340A CN117227965A CN 117227965 A CN117227965 A CN 117227965A CN 202311450340 A CN202311450340 A CN 202311450340A CN 117227965 A CN117227965 A CN 117227965A
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- 230000008859 change Effects 0.000 claims abstract description 7
- 230000007246 mechanism Effects 0.000 claims description 20
- 238000005452 bending Methods 0.000 claims description 14
- 230000003014 reinforcing effect Effects 0.000 claims description 9
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims description 6
- 238000000034 method Methods 0.000 claims description 5
- 230000001105 regulatory effect Effects 0.000 abstract description 2
- 230000005540 biological transmission Effects 0.000 description 7
- 230000006870 function Effects 0.000 description 5
- 238000005516 engineering process Methods 0.000 description 4
- 239000000463 material Substances 0.000 description 4
- 239000000919 ceramic Substances 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 229910001285 shape-memory alloy Inorganic materials 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000007596 consolidation process Methods 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000008713 feedback mechanism Effects 0.000 description 1
- 230000017525 heat dissipation Effects 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/44—Varying camber
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/18—Spars; Ribs; Stringers
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/18—Spars; Ribs; Stringers
- B64C3/182—Stringers, longerons
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/18—Spars; Ribs; Stringers
- B64C3/185—Spars
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/18—Spars; Ribs; Stringers
- B64C3/187—Ribs
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/44—Varying camber
- B64C3/48—Varying camber by relatively-movable parts of wing structures
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Body Structure For Vehicles (AREA)
Abstract
The invention provides a camber-changing wing structure with deformation feedback, which is divided into four structural sections, including a wing leading edge structural section, a wing middle and rear structural section and a wing trailing edge structural section. All the structural sections are connected front and back through the rotating shaft, and the change of the structural camber of the wing is realized through a steering engine connected with the rotating shaft. The angle sensors are respectively arranged in each wing structural section, and can form a complete wing deformation feedback control system together with a steering engine control system on the aircraft. The structure can change the shape and the structural layout of the structure according to different flight conditions, so that the aerodynamic characteristics and the flight performance of the aircraft are improved, the deformation condition of the structure can be observed in real time, and the camber of the wing can be correspondingly regulated according to the actual flight state.
Description
Technical Field
The invention relates to a camber-changing wing structure with deformation feedback, and belongs to the technical field of aviation products.
Background
The aircraft wing camber technology can adjust the wing camber in real time to improve the flight efficiency so as to adapt to complex and changeable task environments, and is considered to be one of the future aviation technology research directions. The existing bending design at home and abroad mainly adopts novel functional materials such as a compliant mechanism, piezoelectric ceramics, memory alloy and the like and a driving mechanism to realize the function of changing the bending of the wing. However, the above-mentioned technology still has many problems in practical application, such as insufficient maturing technology of compliant mechanism, small driving force provided by piezoelectric ceramics, low deformation efficiency of memory alloy due to structural heat dissipation problem, etc. Rigid mechanisms are currently the first choice to achieve a wing camber design from a technical maturity and reliability perspective.
The existing camber-changing wing generally lacks of real-time shape deformation detection and feedback, only a camber-changing driving structure is designed, and the system is an open-loop control system. The design considers that the deformation effect of the wing steering engine is unchanged after the wing steering engine is subjected to pneumatic load, and the actual situation is quite different, so that the wing steering engine cannot accurately adjust the wing camber according to the flight state and the flight condition. Therefore, in order to ensure higher precision and reduce the influence of external disturbance and system parameter variation on the system, it is necessary to configure corresponding angle sensors in the camber wing to form a complete deformation feedback control system.
Disclosure of Invention
In order to overcome the defects in the prior art, the invention provides a wing structure with variable camber and a feedback adjusting device, which can adjust the camber of the wing according to different flight conditions so as to improve the lift-drag ratio and the maneuvering performance of an airplane and feed back and correspondingly adjust the camber of the wing in real time.
The invention provides a technical scheme of a camber-changing wing structure with deformation feedback adjustment, which mainly adopts the following technical measures: the wing structure is divided into four structural sections from the front edge to the rear edge along the chord direction, wherein the four structural sections comprise a wing front edge structural section, a wing middle and rear structural section and a wing rear edge structural section. Each wing structural section is a wing box structure consisting of longitudinal walls, ribs, masks and the like, and the main beams are arranged in the wing leading edge structural sections.
The wing structural sections are connected through the connecting piece through the ribs at the part of the connection part, and compared with the ordinary ribs at the non-connection part, the lug connected with the rotating shaft is added and is simultaneously used for being connected with the rotating shaft through the connecting piece. And at the rotating shaft, the outer sides of the two connecting pieces are respectively and tightly connected with two common ribs. The front middle part, the rear middle part and the rear edge structural section of the wing are controlled in a rotating mode through a rotating mechanism, the angle sensor is connected with a rotating shaft on the wing rotating device through a driving wheel, and the actual rotating angle of the steering engine is calculated by utilizing data of the sensor and the transmission proportion of the driving wheel, so that feedback and adjustment of wing camber are achieved.
The bending feedback control process of the scheme is as follows: the wing bending degree is expected, the flight control device outputs corresponding signals, the steering engine receives the signals from the flight control device, and the rotating shaft drives the reinforcing ribs connected with the steering engine to rotate under the driving of the steering engine, so that the wing structural section connected with the steering engine realizes the rotation function. Meanwhile, the steering engine drives an angle sensor connected with the steering engine to rotate, and the angle sensor reads the rotation angle of the steering engine and converts the rotation angle into corresponding electric signals to be transmitted to the flight control device, so that a complete angle feedback system is formed. The three steering engines can work independently, and form a feedback device independent of each other with the corresponding three angle sensors, so that the change of the bending degree of the whole wing structure and the feedback control of the bending degree are finally realized.
The variable camber wing structure with deformation feedback mainly comprises: common ribs, connection ribs, steering engine ribs, main beams, longitudinal walls, connecting pieces, steering engines, rotating shafts, angle sensors, transmission devices, masks and the like.
The lug connected with the rotating shaft is added, and the thickness of the lug serving as a connecting piece is correspondingly increased so as to meet the strength of the connecting part.
The steering engine wing rib is arranged between longitudinal walls in the structural section, the position of the steering engine wing rib is determined according to the position relation among the angle sensor, the driving wheel and the rotating shaft and is used for fixing the steering engine in the wing structural section,
the main beam is an internal structure of the wing, is arranged in a front edge structure section of the wing, and the wing spar penetrates through the whole wing structure and is connected with the fuselage, so that the wing and the fuselage are fixedly connected into a whole.
The longitudinal wall is an internal structure of the wing and is connected with each wing rib section along the wingspan direction. At the rotating shaft, the longitudinal wall is split, so that a sufficient rotating space is reserved for the rotating shaft.
The connecting piece connects the rib and the rotating shaft at the joint of the rib and the rotating shaft through the consolidation of the rib, and the connection mode of the connecting piece and the rib is determined according to the mode of selecting materials.
The steering engine and the rotating shaft form a rotating system to realize the camber change of the wing, and meanwhile, the rotating shaft bears a certain load, and the connecting mode between the steering engine and the rotating shaft is determined according to the structure of the steering engine and the material of the rotating shaft.
The angle sensor is fixed on the longitudinal wall in a fixed mode according to the specific structure of the wing.
The transmission device connects the angle sensor with the rotating shaft on the wing rotating device, and calculates the actual rotating angle of the steering engine by using the data of the sensor and the transmission proportion of the transmission wheel, thereby realizing the feedback and adjustment of the wing camber. The form of the driving wheel is selected according to the structure of the wing, and is a gear, a rubber wheel or other forms.
The cover plates are paved on the inner bearing structure of the wing, and form a closed wing box together with structures such as longitudinal walls, main beams, wing ribs and the like, and the connection mode of the cover plates is determined according to specific materials.
The skin is arranged at the joint of each wing structural section and is used for maintaining the aerodynamic shape of the wing structure, and the connection mode is determined according to specific materials.
According to one aspect of the present invention there is provided a camber airfoil structure with deformation feedback, comprising:
wing structural sections including a wing leading edge structural section, a wing middle and rear structural section, a wing trailing edge structural section from a leading edge to a trailing edge of the wing in a chord wise direction,
the rotating mechanism is arranged on the longitudinal walls of the middle structural section of the wing, the middle and rear structural sections of the wing and the rear edge structural section of the wing and is used for connecting the adjacent wing structural sections,
wherein: the wing leading edge structure section, the wing middle and rear structure sections, the wing trailing edge structure section each comprise a wing box structure,
the wing box structure comprises a longitudinal wall, wing ribs and a mask,
the rotating mechanism comprises a driving rotating shaft, a steering engine and an angle sensor,
the rotating shaft is connected with the reinforcing ribs on the adjacent wing structure to realize the connection between the rotating mechanism and the adjacent wing structure section,
the angle sensor is coupled with the rotating shaft through the driving wheel, so that the actual rotating angle of the steering engine is determined according to the data of the sensor and the driving proportion of the driving wheel, the feedback and the adjustment of the camber of the wing are realized,
the camber wing structure further comprises:
the steering engine wing ribs are arranged between longitudinal walls in the structural section, the positions of the steering engine wing ribs are determined according to the position relation among the angle sensor, the driving wheel and the rotating shaft, so that the steering engine is fixed in the wing structural section,
a steering engine which is arranged on the rib of the steering engine,
and the skin is arranged at the gap between the wing structural sections and is used for keeping good aerodynamic appearance.
According to another aspect of the present invention, there is provided a camber feedback control method for a wing structure based on the above-mentioned camber wing structure with deformation feedback, characterized by comprising:
the steering engine receives the electric signals of the expected bending degree of the given wing,
the steering engine drives the rotating shaft to drive the reinforcing rib to rotate, so that the wing structural section connected with the reinforcing rib realizes the rotation function,
the steering engine drives the angle sensor to rotate, the angle sensor reads the rotation angle of the steering engine, converts the rotation angle into corresponding electric signals and transmits the corresponding electric signals to the flight control device, and therefore a complete angle feedback system is formed.
The beneficial effects and advantages of the invention include:
a wing structure with variable camber and a feedback regulating device is provided, which can regulate the camber of the wing according to different flight conditions so as to improve the lift-drag ratio and the maneuvering performance of an airplane. The invention provides a set of camber measuring device which can realize real-time feedback and corresponding adjustment of the camber of the wing by combining with a rotating device.
Drawings
FIG. 1 is an overall isometric view of a camber airfoil structure with deformation feedback according to an embodiment of the present invention.
FIG. 2 is a structural partial schematic view of a camber airfoil structure with deformation feedback according to one embodiment of the invention.
FIG. 3 is a schematic view of a stiffening rib structure of a camber airfoil structure with deformation feedback according to an embodiment of the invention.
Reference numerals:
Detailed Description
The invention will now be further described with reference to examples and figures.
The invention provides a camber-changing wing structure with deformation feedback, which is divided into four structural sections from a front edge to a rear edge along the chord direction. Each wing structural section is a wing box structure consisting of longitudinal walls, ribs, masks and the like, and the main beams are arranged in the wing leading edge structural sections. The wing structural sections are connected with the rotating shaft through part of wing ribs. The rotating mechanism of the wing structure consists of a driving rotating shaft, a steering engine and a coupler. The steering engine realizes the change of wing camber by driving the rotating shaft connected with the structural section to rotate. Meanwhile, the variable camber wing structure realizes a deformation feedback function through the angle measuring device, the angle sensor is connected with the steering engine through the driving wheel, and the rotation angle of the steering engine is indirectly calculated according to the rotation angle of the sensor and the transmission ratio. The outer surface of the whole structure of the wing is wrapped by a flexible skin.
The main design comprises the following structures: (1) the deformed wing structural section comprises a wing leading edge structural section, a wing middle and rear structural section and a wing trailing edge structural section; (2) the rotating mechanism comprises a steering engine, a rotating shaft, a coupling and the like; (3) the angle feedback mechanism comprises an angle sensor, a detachable bracket and a rotating wheel;
as shown in fig. 1 and 2:
a camber airfoil structure with deformation feedback according to an embodiment of the invention is divided in chord direction from the leading edge to the trailing edge into an airfoil leading edge structure section (1), an airfoil mid-structure section (2), an airfoil mid-rear structure section (3) and an airfoil trailing edge structure section (4). Each wing structure section is a wing box structure comprising a longitudinal wall (5), ribs (6), a skin (7) and the like (fig. 1). The rotating mechanism of the camber-changing wing structure comprises a driving rotating shaft (8) and a steering engine (9). The rotating shaft (8) is connected with a reinforcing rib (14) on the adjacent wing structure, so that the connection between the rotating mechanism and the adjacent wing structure section is realized. The steering engine (9) is arranged at the root of the wing and is fixed on a steering engine wing rib (15) (figure 2). The angle sensor (10) is connected with a rotating shaft (8) in the wing rotating mechanism through a driving wheel (12) (figure 2), and the actual rotating angle of the steering engine is determined by utilizing the data of the sensor (10) and the transmission proportion of the driving wheel (12), so that the feedback and adjustment of the wing camber are realized.
A skin (16) is mounted at the gap between the wing structural sections for maintaining a good aerodynamic profile.
As shown in fig. 2, the bending feedback control process of the implementation mechanism is as follows: the steering engine (9) receives an electric signal with expected bending degree from the outside, and the rotating shaft (8) drives the reinforcing ribs (14) connected with the steering engine to rotate under the driving of the steering engine (9), so that the wing structural section connected with the steering engine realizes the rotation function. Meanwhile, the steering engine (9) drives an angle sensor (10) connected with the steering engine to rotate, and the angle sensor (10) reads the rotation angle of the steering engine (9) and converts the rotation angle into corresponding electric signals to be transmitted to the flight control device, so that a complete angle feedback system is formed.
The rotating mechanisms connected with the wing structural sections can work independently, and form feedback devices independent of each other with the corresponding three angle sensors, so that the change of the bending degree of the whole wing structure and the feedback control of the bending degree are finally realized.
Claims (3)
1. A camber wing structure with deformation feedback, comprising:
a wing structural section comprising a wing leading edge structural section (1), a wing middle structural section (2), a wing middle and rear structural section (3) and a wing trailing edge structural section (4) from the leading edge to the trailing edge of the wing along the chord direction,
the rotating mechanism is arranged on a longitudinal wall (5) of the middle structural section (2), the middle and rear structural sections (3) and the rear edge structural section (4) of the wing and is used for connecting the adjacent wing structural sections,
wherein: the wing leading edge structural section (1), the wing middle structural section (2), the wing middle and rear structural section (3) and the wing trailing edge structural section (4) each comprise a wing box structure,
the wing box structure comprises a longitudinal wall (5), a wing rib (6) and a mask (7),
the rotating mechanism comprises a driving rotating shaft (8) and a steering engine (9),
the rotating shaft (8) is connected with a reinforcing rib (14) on the adjacent wing structure to realize the connection between the rotating mechanism and the adjacent wing structure section,
the camber-changing wing structure also comprises an angle sensor (10) and a driving wheel (12) arranged on the rotating shaft (8), wherein the angle sensor is fixed on the longitudinal wall, the angle sensor (10) is coupled with the rotating shaft (8) through the driving wheel (12), so that the actual rotation angle of the wing structure section driven by the steering engine is determined according to the data of the sensor (10) and the driving proportion of the driving wheel (12),
the camber wing structure further comprises:
steering engine wing ribs (15) which are arranged between longitudinal walls (5) in the structural section so as to fix the steering engine (9) in the wing structural section,
a steering engine (9) which is arranged on a steering engine wing rib (15),
a skin (16) mounted at the gap between the wing structural sections for maintaining a good aerodynamic profile.
2. A wing structure camber feedback control method based on a variable camber wing structure with deformation feedback according to claim 1, characterized by comprising:
the steering engine (9) receives an electric signal of the expected bending degree of the given wing,
the steering engine (9) is used for driving the rotating shaft (8) to drive the reinforcing rib (14) to rotate, so that the wing structural section connected with the reinforcing rib realizes the rotation function,
the rotating shaft (8) drives the angle sensor (10) to rotate through the driving wheel (12), so that the angle sensor (10) reads the rotating angle of the rotating shaft (8) and converts the rotating angle into corresponding electric signals and transmits the corresponding electric signals to the flight control device, thereby forming a complete angle feedback system.
3. The wing structure camber feedback control method of claim 2, comprising:
three rotating mechanisms connecting the wing leading edge structure section (1) with the wing middle structure section (2), the wing middle structure section (2) with the wing middle rear structure section (3), the wing middle rear structure section (3) and the wing trailing edge structure section (4) can work independently, and angle sensors (10) in the rotating mechanisms form independent feedback devices, so that the change of the bending degree of the whole wing structure and the feedback control of the bending degree of the whole wing structure are finally realized.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311450340.XA CN117227965A (en) | 2019-11-01 | 2019-11-01 | Variable camber airfoil structure with deformation feedback |
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911061124.XA CN110654530A (en) | 2019-11-01 | 2019-11-01 | Variable camber wing structure with deformation feedback |
| CN202311450340.XA CN117227965A (en) | 2019-11-01 | 2019-11-01 | Variable camber airfoil structure with deformation feedback |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911061124.XA Division CN110654530A (en) | 2019-11-01 | 2019-11-01 | Variable camber wing structure with deformation feedback |
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| CN117227965A true CN117227965A (en) | 2023-12-15 |
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| CN201911061124.XA Pending CN110654530A (en) | 2019-11-01 | 2019-11-01 | Variable camber wing structure with deformation feedback |
| CN202311450340.XA Pending CN117227965A (en) | 2019-11-01 | 2019-11-01 | Variable camber airfoil structure with deformation feedback |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201911061124.XA Pending CN110654530A (en) | 2019-11-01 | 2019-11-01 | Variable camber wing structure with deformation feedback |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN111439368B (en) * | 2020-03-16 | 2021-08-27 | 北京航空航天大学 | Variable camber wing based on flexible skin of composite material corrugated plate |
| CN111439367A (en) * | 2020-05-12 | 2020-07-24 | 丁力 | Flexibly deformable trailing edge variable camber wing |
| CN112357058B (en) * | 2020-11-19 | 2022-09-20 | 航天彩虹无人机股份有限公司 | Steering engine mounting structure of unmanned aerial vehicle, unmanned aerial vehicle and mounting method of steering engine |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| GB163853A (en) * | 1920-03-18 | 1921-06-02 | Samuel Edgar Saunders | Improvements in means for varying the camber of the wings or control surfaces of aircraft |
| CN206537487U (en) * | 2017-01-23 | 2017-10-03 | 中国民航大学 | A kind of aircraft of the variable wing of aerofoil profile and the application wing |
| CN107444617A (en) * | 2017-07-13 | 2017-12-08 | 北京航空航天大学 | A kind of variable adaptive wing structure of camber |
| CN109050878A (en) * | 2018-08-01 | 2018-12-21 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of continuous variable camber structure of aircraft and its distributing drive control method |
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- 2019-11-01 CN CN201911061124.XA patent/CN110654530A/en active Pending
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