CN115416839A - Folding wing bidirectional unfolding mechanism with skin supporting structure - Google Patents
Folding wing bidirectional unfolding mechanism with skin supporting structure Download PDFInfo
- Publication number
- CN115416839A CN115416839A CN202211086167.5A CN202211086167A CN115416839A CN 115416839 A CN115416839 A CN 115416839A CN 202211086167 A CN202211086167 A CN 202211086167A CN 115416839 A CN115416839 A CN 115416839A
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- wing
- section wing
- outer section
- supporting structure
- skin
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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
- B64C3/56—Folding or collapsing to reduce overall dimensions of aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/26—Construction, shape, or attachment of separate skins, e.g. panels
Abstract
The invention relates to a folding wing bidirectional unfolding mechanism with a skin supporting structure, belonging to the field of folding wing design; comprises an inner section wing, an outer section wing, a driving mechanism and n supporting devices; the inner section wing and the outer section wing are oppositely arranged, and a gap is reserved between the inner section wing and the outer section wing; the driving mechanism is positioned at the gap between the inner section wing and the outer section wing, and the outer section wing is driven to rotate relative to the inner section wing through the driving mechanism; the n supporting devices are horizontally arranged at the gap between the inner section wing and the outer section wing, and each supporting device takes the driving mechanism as the center and is uniformly distributed on two sides of the driving mechanism; the n supporting devices realize auxiliary support between the inner section wing and the outer section wing; the invention has larger reduction ratio, can reduce the power requirement of the driver, can provide the connecting and fixing function of the outer section structure and the supporting function of the skin at the bending part, and is suitable for the high-speed variant aircraft structure which has high dimensional requirement, limited driving torque and needs to be folded in two directions.
Description
Technical Field
The invention belongs to the field of design of folding wings, and relates to a bidirectional unfolding mechanism for a folding wing with a skin supporting structure.
Background
For an aircraft with a flight speed higher than Ma1, a low-speed takeoff and landing stage and a high-speed cruise flight stage are performed on a flight mission section of the aircraft, each stage is required to have a different aerodynamic shape in order to achieve higher flight performance, for example, the aircraft is required to have a larger aspect ratio in the low-speed takeoff and landing stage to improve the lift level, and at the moment, the wings of the aircraft are straight wings or dihedral angles with small angles to improve the lateral stability of the aircraft. Under the high-speed cruising state, the transverse stability can be enhanced by upwards folding the wings of the aircraft, and the transverse stability and the shock wave lift force can be captured by downwards folding the wings, so that the lift resistance characteristic of the whole aircraft is further enhanced. In conclusion, for a high-speed aircraft, due to the large speed span, changing the plane shape of the wing becomes a very effective means for improving the flight performance.
At the same time, the aircraft that realizes the variant by folding the wings faces the following difficulties. Firstly, a high-speed aircraft usually does not allow large gaps to appear on main lifting components such as wings and the like, and avoids the problem that the serious aerodynamic heating causes the burning loss of structures and internal equipment cables, so that the wing skins at the folding positions need to be replaced by flexible materials to realize the continuous and smooth outer surfaces of the folding wings, and an internal structure is needed to support so as to ensure that the flexible skins can overcome aerodynamic loads and cannot generate large normal deformation and damage. Secondly, in a high-speed state, the outer section of the wing which needs to be folded downwards (upwards) bears larger aerodynamic load compared with the low-speed state, the load is borne by the folding driving mechanism and is transmitted to the root of the wing, in order to reduce the requirement of type selection of the driver, the driving mechanism with a certain reduction ratio needs to be adopted, and the mechanism has the function of self-locking at any position. Finally, the existing folding wing structure can only be folded towards a single direction, and the upward or downward bidirectional folding function of the same mechanism can be realized more difficultly on the premise of meeting the requirements of the two points. In conclusion, the folding wing structure of the high-speed aircraft is difficult to design.
Disclosure of Invention
The technical problem solved by the invention is as follows: the folding wing bidirectional unfolding mechanism with the skin supporting structure has a large reduction ratio, can reduce the power requirement of a driver, can provide the connection and fixation effect of an outer section structure, has the supporting effect of the skin at the bent part, is suitable for a high-speed variant aircraft structure which has high dimensional requirement, is limited in matching driving moment and needs bidirectional folding.
The technical scheme of the invention is as follows:
a folding wing bidirectional unfolding mechanism with a skin supporting structure comprises an inner section wing, an outer section wing, a driving mechanism and n supporting devices; the inner section wing and the outer section wing are oppositely arranged, and a gap is reserved between the inner section wing and the outer section wing; the driving mechanism is positioned at the gap between the inner section wing and the outer section wing, and the outer section wing is driven to rotate relative to the inner section wing through the driving mechanism; the n supporting devices are horizontally arranged at the gap between the inner section wing and the outer section wing, and each supporting device takes the driving mechanism as the center and is uniformly distributed on two sides of the driving mechanism; the n supporting devices realize auxiliary support between the inner section wing and the outer section wing.
In the above folding wing bidirectional unfolding mechanism with the skin supporting structure, n is a positive integer and is not less than 2; the gap between the inner section wing and the outer section wing is coated with the skin, and the skin is supported through the supporting device.
In the above bidirectional unfolding mechanism for a folding wing with a skin support structure, the support device comprises a rotary support structure and a skin support structure; two ends of the rotary supporting structure are respectively connected with the butt joint surfaces of the inner section wing and the outer section wing; the skin supporting structure is respectively connected with the butt joint surfaces of the inner section wing and the outer section wing; the rotary supporting structure and the skin supporting structure are horizontally arranged in parallel; and during installation, the rotary supporting structure of each supporting device points to the driving mechanism, and the skin supporting structure is arranged far away from the driving mechanism.
In the above bidirectional unfolding mechanism for the folding wing with the skin support structure, the driving mechanism comprises a worm fixing seat, a turbine transmission seat, m worms and m turbines; the worm fixing seat is fixedly arranged on the side wall of the inner section wing pointing to the outer section wing; the turbine transmission seat is fixedly arranged on the side wall of the outer section wing, which points to the inner section wing; the worm fixing seat corresponds to the turbine transmission seat in position; m worms are arranged in a row and are uniformly arranged on the worm fixing seat; the m turbines are arranged in a row and are uniformly arranged on the turbine transmission seat; and the worms are meshed with the turbines in a one-to-one correspondence manner.
In the above bidirectional unfolding mechanism for the folding wing with the skin supporting structure, m is a positive integer and is not less than 4; when the turbine transmission seat is driven by m worms to rotate through m turbines, the outer section wings are linked to rotate.
In the bidirectional unfolding mechanism for the folding wing with the skin supporting structure, the reduction ratio of each group of worm and worm wheel is 16-40; the m sets of worms and turbines achieve an amplification of the input torque by a factor of 16m to 40 m.
In the above bidirectional unfolding mechanism for a folding wing with a skin support structure, the rotary support structure includes 2 inner wing tabs, 1 outer wing tab and a rotary shaft; wherein, 2 inner wing lugs are parallelly arranged on the side wall of the inner section wing pointing to the outer section wing; the outer wing lug is arranged on the side wall of the outer section wing pointing to the inner section wing; outer wing auricle head end stretches into between 2 interior wing auricle head ends, and outer wing auricle head end and 2 interior wing auricle head ends pass through the rotation axis and connect, realize that outer wing auricle uses the rotation axis to rotate for 2 interior wing auricles as the axle.
In the above bidirectional unfolding mechanism for a folding wing with a skin support structure, the skin support structure comprises 4 lug supports and q fork rod assemblies; the 4 lug plate supports are grouped in pairs, wherein 1 group is fixedly arranged on the side wall of the outer section wing pointing to the inner section wing; the other 1 group is arranged on the side wall of the inner section wing pointing to the outer section wing; the q fork rod assemblies are connected into 1 row through pin shafts in sequence; the fork rod assembly positioned on the side 2 is respectively connected with the corresponding ear piece supports 2 through the pin shafts 2; q is a positive integer, and q is 2 or more.
In the above bidirectional unfolding mechanism for a folding wing with a skin supporting structure, the fork lever assembly comprises 2 connecting rods; 2 connecting rods are crossed to form an X shape; the cross parts of the 2 connecting rods are connected through 1 pin shaft; 2 connecting rods of each fork rod assembly rotate relatively; the connecting rod head ends extending out of the adjacent 2 fork rod assemblies are connected with each other through a mounting pin shaft.
In the above folding wing bidirectional unfolding mechanism with the skin supporting structure, the angle between the inner section wing and the outer section wing is set to be 0 degree when the inner section wing and the outer section wing are positioned on the same horizontal plane; the clockwise rotation direction of the outer section wing is set as positive, and the anticlockwise rotation direction of the outer section wing is set as negative; the rotation range of the outer section of the wing is-45 degrees to 60 degrees.
Compared with the prior art, the invention has the beneficial effects that:
(1) The invention is provided with a skin supporting structure, and q fork rod assemblies are connected into 1 row through pin shafts in sequence; the fork rod assembly positioned on the side 2 is connected with the corresponding lug plate supports 2 through the pin shafts 2 respectively, and the flexible skin can overcome aerodynamic load and cannot generate large normal deformation and damage through the skin supporting structure;
(2) The reduction ratio of each group of worm and worm wheel is 16-40; the m groups of worms and turbines amplify the input torque by 16m-40m times, and can bear larger aerodynamic load in a high-speed state;
(3) The invention can realize the upward or downward bidirectional turnover function in the same mechanism.
Drawings
FIG. 1 is a general schematic view of a bi-directional deployment mechanism of the present invention;
FIG. 2 is a schematic view of the driving mechanism of the present invention;
FIG. 3 is a schematic view of a rotary support structure according to the present invention;
FIG. 4 is a schematic view of the skin support structure of the present invention;
FIG. 5 is a schematic view of the outer wing segment of the present invention rotated 60;
FIG. 6 is a schematic view of the-45 position of the outer wing section of the present invention.
Detailed Description
The invention is further illustrated by the following examples.
The invention provides a folding wing bidirectional unfolding mechanism with a skin supporting structure, which has a larger reduction ratio when an aircraft needs to turn the outer side of a wing upwards and downwards to change the pneumatic performance, can reduce the power requirement of a driver, can provide the connection fixing function of an outer section structure and the supporting function of a skin at a bent part, and is suitable for the structural design of a high-speed variant aircraft which has high dimensional requirement, limited matching driving moment and needs bidirectional turning.
The folding wing bidirectional unfolding mechanism comprises an inner section wing 1, an outer section wing 2, a driving mechanism 3 and n supporting devices as shown in fig. 1; the inner section wing 1 and the outer section wing 2 are oppositely arranged, and a gap is reserved between the inner section wing 1 and the outer section wing 2; the driving mechanism 3 is positioned at a gap between the inner section wing 1 and the outer section wing 2, and the outer section wing 2 is driven to rotate relative to the inner section wing 1 through the driving mechanism 3; the n supporting devices are horizontally arranged at the gap between the inner section wing 1 and the outer section wing 2, and each supporting device takes the driving mechanism 3 as the center and is uniformly distributed at two sides of the driving mechanism 3; the n supporting devices realize auxiliary support between the inner section wing 1 and the outer section wing 2. n is a positive integer and n is not less than 2; the gap between the inner section wing 1 and the outer section wing 2 is coated with a skin, and the skin is supported by the supporting device.
The supporting device is designed into 2 parts, and particularly comprises a rotating supporting structure 4 and a skin supporting structure 5; two ends of the rotary supporting structure 4 are respectively connected with the butt joint surfaces of the inner section wing 1 and the outer section wing 2; the skin supporting structure 5 is respectively connected with the butt joint surfaces of the inner section wing 1 and the outer section wing 2; the rotary supporting structure 4 and the skin supporting structure 5 are horizontally arranged in parallel; and when installed, the rotating support structure 4 of each support device is directed towards the drive mechanism 3, and the skin support structure 5 is located away from the drive mechanism 3.
As shown in fig. 2, the driving mechanism 3 includes a worm fixing seat 31, a worm wheel transmission seat 32, m worm wheels 33 and m worm wheels 34; wherein, the worm fixing seat 31 is fixedly arranged on the side wall of the inner section wing 1 which points to the outer section wing 2; the turbine transmission seat 32 is fixedly arranged on the side wall of the outer section wing 2 pointing to the inner section wing 1; the worm fixing seat 31 corresponds to the turbine transmission seat 32 in position; the m worms 33 are uniformly arranged on the worm fixing seat 31 in a row; the m turbines 34 are uniformly arranged on the turbine transmission seat 32 in a row; and the worm 33 is engaged with the worm wheel 34 in a one-to-one correspondence. m is a positive integer, and m is not less than 4; when the turbine transmission seat 32 is driven by the m worms 33 to rotate through the m turbines 34, the linkage outer section wing 2 rotates.
In order to realize a larger reduction ratio and provide larger expansion torque, the reduction ratio of each set of worm 33 and worm wheel 34 is 16-40; the m sets of worms 33 and turbines 34 achieve an amplification of the input torque by a factor of 16m to 40 m.
As shown in fig. 3, the rotary support structure 4 includes 2 inner wing tabs 41, 1 outer wing tab 42, and a rotary shaft 43; wherein, 2 inner wing lugs 41 are parallelly arranged on the side wall of the inner wing section 1 pointing to the outer wing section 2; the outer wing lug 42 is arranged on the side wall of the outer section wing 2 pointing to the inner section wing 1; the head end of the outer wing ear 42 extends into the space between the head ends of the 2 inner wing ears 41, and the head end of the outer wing ear 42 is connected with the head ends of the 2 inner wing ears 41 through the rotating shaft 43, so that the outer wing ear 42 rotates relative to the 2 inner wing ears 41 by taking the rotating shaft 43 as a shaft.
As shown in fig. 4, the skin support structure 5 includes 4 tab mounts 51 and q clevis assemblies; the 4 lug supports 51 are grouped in pairs, wherein 1 group is fixedly arranged on the side wall of the outer section wing 2 pointing to the inner section wing 1; the other 1 group is arranged on the side wall of the inner section wing 1 which points to the outer section wing 2; the q fork rod assemblies are connected into 1 row through the pin shaft 52 in sequence; and the fork lever component at the side 2 is respectively connected with the corresponding 2 lug supports 51 through 2 pin shafts 52; q is a positive integer, and q is 2 or more.
The fork lever assembly comprises 2 links 53;2 connecting rods 53 are crossed into an X shape; and the intersections of the 2 connecting rods 53 are connected by 1 pin 52; 2 links 53 of each fork lever assembly are relatively rotated; the ends of the connecting rods 53 extending from adjacent 2 fork rod assemblies are interconnected by a mounting pin 52.
The inner section wing 1 and the outer section wing 2 are set to be 0 degree when positioned on the same horizontal plane; the clockwise rotation direction of the outer section wing 2 is set as positive, and the anticlockwise rotation direction of the outer section wing 2 is set as negative; the rotation range of the outer segment wing 2 is-45 to 60 degrees as shown in fig. 5 and 6.
In the present invention, the skin support structure 5 provides support for the entire skin structure. The structure is composed of multiple links 53; and fixing tab mounts 51 connected to both wings, as shown in fig. 4. The links 53 are connected to each other by a pin 52 to constitute a linkage mechanism. The remaining pins 52, except for the pin 52 located in the middle, will be connected to the skin covering it in a strapping manner, wherein the corresponding skin location needs to be provided with a strap. When the wings on the two sides rotate relatively, the lug support 51 drives the link mechanism to move, so that the pin shaft 52 still keeps a smooth molded surface position, and dimensional support is provided for the outer skin.
The driving mechanism 3 is used for driving the outer section wing 2 to rotate, and simultaneously plays a role in supporting and fixing the outer section wing 2. The mechanism comprises: the worm fixing seat 31, the worm wheel transmission seat 32, the m worm wheels 33 and the m worm wheels 34 are shown in FIG. 2. The worm 33 is connected with a driving motor positioned in the fixed wing and is arranged on the inner section wing surface through the worm fixing seat 31. The worm wheel rotating seat 32 is fixedly connected with the outer section wing 2, and when the worm wheel rotating seat 32 is driven by the worm 34 to rotate, the outer section wing 2 is directly linked to rotate. The rotating seat is only provided with a half worm gear structure because the angle of the outer section of the wing 2 turning upwards or downwards is limited and a complete worm gear structure is not needed. The whole driving mechanism 3 consists of a plurality of groups of worm and worm transmission mechanisms and is used for bearing hinge moment caused by aerodynamic force of the outer section airfoil surface. The worm and gear transmission mechanism has a self-locking function besides providing a large reduction ratio, and after the drive motor does not drive the worm to rotate any more, the outer section airfoil is locked at the current position, and an additional mechanical locking mechanism is not needed to keep the current position.
The rotary supporting structure 4 is used for hinged connection between the inner section wing 1 and the outer section wing 2. Comprises an inner wing lug 41, an outer wing lug 42 and a rotating shaft 43. The inner wing lug 41 is fixedly connected with the inner section wing 1, the outer wing lug 42 is fixedly connected with the outer section wing 2, and the rotating shaft 43 is used as a rotating shaft for connecting and rotationally positioning the two sections of wing surfaces.
The invention realizes that when the outer side of the wing of the aircraft needs to be turned upwards and downwards to change the pneumatic performance, the structure mechanism has larger speed reduction ratio, can reduce the power requirement of a driver, can provide the connection and fixation function of an outer section structure and the supporting function of a skin at a bent part, and is suitable for the structural design of a high-speed variant aircraft which has high dimensional requirement, is limited in matching driving moment and needs to be turned over in two directions.
Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention, and those skilled in the art can make variations and modifications of the present invention without departing from the spirit and scope of the present invention by using the methods and technical contents disclosed above.
Claims (10)
1. The utility model provides a take two-way expansion mechanism of folding wing of covering bearing structure which characterized in that: comprises an inner section wing (1), an outer section wing (2), a driving mechanism (3) and n supporting devices; the inner section wing (1) and the outer section wing (2) are oppositely arranged, and a gap is reserved between the inner section wing (1) and the outer section wing (2); the driving mechanism (3) is positioned at a gap between the inner section wing (1) and the outer section wing (2), and the outer section wing (2) is driven to rotate relative to the inner section wing (1) through the driving mechanism (3); the n supporting devices are horizontally arranged at the gap between the inner section wing (1) and the outer section wing (2), and each supporting device takes the driving mechanism (3) as the center and is uniformly distributed on two sides of the driving mechanism (3); the n supporting devices realize auxiliary support between the inner section wing (1) and the outer section wing (2).
2. The folding wing bidirectional unfolding mechanism with the skin supporting structure of claim 1, is characterized in that: n is a positive integer and n is not less than 2; the gap between the inner section wing (1) and the outer section wing (2) is coated with a skin, and the skin is supported by the supporting device.
3. The folding wing bidirectional unfolding mechanism with the skin supporting structure of claim 1, is characterized in that: the supporting device comprises a rotary supporting structure (4) and a skin supporting structure (5); two ends of the rotary supporting structure (4) are respectively connected with the butt joint surfaces of the inner section wing (1) and the outer section wing (2); the skin supporting structure (5) is respectively connected with the butt joint surfaces of the inner section wing (1) and the outer section wing (2); the rotary supporting structure (4) and the skin supporting structure (5) are horizontally arranged in parallel; and during installation, the rotary supporting structure (4) of each supporting device points to the driving mechanism (3), and the skin supporting structure (5) is arranged far away from the driving mechanism (3).
4. The bidirectional unfolding mechanism with the skin supporting structure for the folding wing of claim 1, wherein: the driving mechanism (3) comprises a worm fixing seat (31), a turbine transmission seat (32), m worms (33) and m turbines (34); wherein, the worm fixing seat (31) is fixedly arranged on the side wall of the inner section wing (1) pointing to the outer section wing (2); the turbine transmission seat (32) is fixedly arranged on the side wall of the outer section wing (2) pointing to the inner section wing (1); the worm fixing seat (31) corresponds to the turbine transmission seat (32); the m worms (33) are arranged in a row and are uniformly arranged on the worm fixing seat (31); the m turbines (34) are arranged in a row and are uniformly arranged on the turbine transmission seat (32); and the worm (33) is meshed with the worm wheel (34) in a one-to-one corresponding way.
5. The folding wing bidirectional unfolding mechanism with the skin supporting structure as claimed in claim 4, wherein: m is a positive integer and is not less than 4; when the turbine transmission seat (32) is driven to rotate by the m worms (33) through the m turbines (34), the outer section wing (2) is linked to rotate.
6. The folding wing bidirectional unfolding mechanism with the skin supporting structure of claim 5, is characterized in that: the reduction ratio of each group of worm (33) and worm wheel (34) is 16-40; the m groups of worms (33) and the turbines (34) realize the amplification of the input torque by 16m-40m times.
7. The bidirectional unfolding mechanism for a folding wing with a skin supporting structure, according to claim 3, is characterized in that: the rotary support structure (4) comprises 2 inner wing lugs (41), 1 outer wing lug (42) and a rotary shaft (43); wherein, 2 inner wing lugs (41) are parallelly arranged on the side wall of the inner section wing (1) which points to the outer section wing (2); the outer wing lug (42) is arranged on the side wall of the outer section wing (2) pointing to the inner section wing (1); the head end of the outer wing ear (42) extends into the space between the head ends of the 2 inner wing ears (41), and the head end of the outer wing ear (42) is connected with the head ends of the 2 inner wing ears (41) through a rotating shaft (43), so that the outer wing ear (42) rotates relative to the 2 inner wing ears (41) by taking the rotating shaft (43) as a shaft.
8. The folding wing bidirectional unfolding mechanism with the skin supporting structure of claim 3, is characterized in that: the skin support structure (5) comprises 4 lug supports (51) and q fork rod assemblies; the 4 lug plate supports (51) are arranged in pairs in a group, wherein 1 group is fixedly arranged on the side wall of the outer section wing (2) pointing to the inner section wing (1); the other 1 group is arranged on the side wall of the inner section wing (1) which points to the outer section wing (2); the q fork rod assemblies are connected into 1 row through pin shafts (52) in sequence; and the fork rod components at the 2 sides are respectively connected with 2 corresponding lug plate supports (51) through 2 pin shafts (52); q is a positive integer and q is 2 or more.
9. The folding wing bidirectional unfolding mechanism with the skin supporting structure of claim 8, is characterized in that: the fork lever assembly comprises 2 connecting rods (53); 2 connecting rods (53) are crossed into an X shape; and the intersections of the 2 connecting rods (53) are connected through the 1 pin shaft (52); 2 connecting rods (53) of each fork rod assembly are relatively rotated; the head ends of the connecting rods (53) extending out of the adjacent 2 fork rod assemblies are connected with each other through a mounting pin shaft (52).
10. The folding wing bidirectional unfolding mechanism with the skin supporting structure of claim 1, is characterized in that: the inner section wing (1) and the outer section wing (2) are set to be 0 degree when being positioned on the same horizontal plane; the clockwise rotation direction of the outer section wing (2) is set as positive, and the anticlockwise rotation direction of the outer section wing (2) is set as negative; the rotation range of the outer section wing (2) is-45 degrees to 60 degrees.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211086167.5A CN115416839A (en) | 2022-09-06 | 2022-09-06 | Folding wing bidirectional unfolding mechanism with skin supporting structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211086167.5A CN115416839A (en) | 2022-09-06 | 2022-09-06 | Folding wing bidirectional unfolding mechanism with skin supporting structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115416839A true CN115416839A (en) | 2022-12-02 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211086167.5A Pending CN115416839A (en) | 2022-09-06 | 2022-09-06 | Folding wing bidirectional unfolding mechanism with skin supporting structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115416839A (en) |
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2022
- 2022-09-06 CN CN202211086167.5A patent/CN115416839A/en active Pending
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