CN213083484U - Folding wing with folding trailing edge flap - Google Patents
Folding wing with folding trailing edge flap Download PDFInfo
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- CN213083484U CN213083484U CN202021502508.9U CN202021502508U CN213083484U CN 213083484 U CN213083484 U CN 213083484U CN 202021502508 U CN202021502508 U CN 202021502508U CN 213083484 U CN213083484 U CN 213083484U
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- wing
- flap
- trailing edge
- folding
- skin
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Abstract
The utility model belongs to the technical field of the aviation, concretely relates to foldable wing of folding trailing edge flap in area, it includes main wing and folding trailing edge flap, and wherein many crank shape flaps support the rib, support the articulated connection of rib lower surface through connecting axle and the covering that corresponds, constitute and rely on the folding trailing edge flap support skeleton of covering support rib, reset spring makes crank shape flaps support the long limit upper surface of rib and hug closely covering support rib lower surface, and flexible flaps covering adheres to the connection and supports the skeleton upper surface at folding trailing edge flap. On the basis of current foldable wing, the utility model relates to a wing is folding, expand at random, and adjustable wing trailing edge flap constitutes the foldable wing of taking folding trailing edge flap, can solve current foldable wing well and do not have wing trailing edge flap, the limited problem of wing controllability, cooperates foldable wing aileron for foldable wing has the primary function of modern fixed wing.
Description
Technical Field
The utility model belongs to the technical field of the aviation, concretely relates to foldable wing of folding trailing edge flap in area.
Background
In the prior art, the patent numbers: 201620324195.X, 201621063844.1, 201910263631.5, 201921875322.5, and US10696376 disclose a folding wing with its full folding and unfolding fixed wing capability that can be widely used in various types of small and light manned and unmanned aircraft.
The existing folding wing mainly comprises a folding multiple triangular supporting framework, a slide rail, a skin supporting rib, an air bag inflatable skin, a straight folding extending wing, an aileron thereof and a wing action device, so as to form a folding and unfolding fixed wing.
The technical defects of the prior art are as follows: the wings are provided with adjustable ailerons, but without adjustable trailing edge flaps, so that the aerodynamic adjustment capability of the wings is limited.
SUMMERY OF THE UTILITY MODEL
The utility model aims at: on the basis of the existing folding wing, the wing trailing edge flap which can be folded and unfolded randomly and can be adjusted is designed to form the folding wing with the folding trailing edge flap, so that the defects of the prior art can be well overcome.
The utility model discloses a folding trailing edge flap is installed in the design of current folding wing trailing edge position, and folding trailing edge flap can be along with folding wing synchronous deformation, and folding wing expandes the back, when the aircraft need increase the wing lift, by the flexible linkage cable of flap drive arrangement pulling, drives each crank shape flap support rib and rotates around the connecting axle in step to make trailing edge flap downwardly regulated, increase wing camber and area, change the aerodynamic form of wing, increase the wing lift.
An embodiment of the utility model provides a foldable wing of folding trailing edge flap in area, including the main wing, the main wing includes: wing supporting framework, slide rail, skin supporting rib, air bag inflatable skin on upper surface of wing, skin on lower surface of wing, aileron, and
a folded trailing edge flap, the folded trailing edge flap comprising: a plurality of crank-shaped flap support ribs; a flexible flap skin; a connecting shaft; a flexible linkage main cable; a flexible linkage supporting cable; a linkage cable support; a return spring; and a flap drive device, which is provided with a flap drive,
the plurality of crank-shaped flap support ribs are hinged and connected with the lower surfaces of the corresponding skin support ribs through connecting shafts to form a folding trailing edge flap support framework depending on the skin support ribs, the upper surfaces of the long sides of the crank-shaped flap support ribs are tightly attached to the lower surfaces of the skin support ribs through reset springs, and the flexible flap skin is attached to the upper surfaces of the folding trailing edge flap support framework.
Furthermore, the linkage cable support is arranged on the lower surface of the skin support rib, and forms a space triangle with the short side of the crank-shaped flap support rib and the connecting shaft; the flexible linkage main cable is connected with each flexible linkage branch cable in parallel, one end of each flexible linkage branch cable is connected with the end head of the short side of the crank-shaped flap support rib, the other end of each flexible linkage branch cable is connected with the flexible linkage main cable, the flexible linkage main cables are connected in series and penetrate through cable holes in the support seats of the linkage cables, and the terminal of each flexible linkage branch cable is connected with the flap driving device.
After the folding wing is unfolded, the skin supporting ribs are pulled by the wing skin and are in a position fixing state, and at the moment, the skin supporting ribs are supported by the wing supporting framework and can bear the aerodynamic load of the wing; the plurality of crank-shaped flap support ribs are hinged with the lower surfaces of the corresponding skin support ribs through connecting shafts to form a folding trailing edge flap support framework depending on the skin support ribs, and the upper surfaces of the long edges of the crank-shaped flap support ribs are tightly attached to the lower surfaces of the skin support ribs through the reset springs.
Furthermore, after the folding wing is unfolded, when the aircraft needs to increase the wing lift force, the flap driving device provides power, the flexible linkage main rope moves along the cable hole on the linkage rope support by pulling, so that each flexible linkage branch rope connected with the flexible linkage main rope in parallel is driven to synchronously move along the cable hole on the linkage rope support, and each crank-shaped flap support rib connected with the flexible linkage main rope is further pulled to synchronously rotate around the connecting shaft, the whole folding trailing edge flap is formed, the rotation and downward adjustment of the whole folding trailing edge flap are realized, the wing camber and the area are increased, the wing aerodynamic form is changed, and the purpose of increasing the wing lift force is achieved.
The flexible flap skin is attached to the upper surface of the folding trailing edge flap supporting framework to form a stress surface for bearing airflow by the folding trailing edge flap.
Further, when the aircraft resumes normal flight, the flap driving device releases the flexible linkage main cable, and each flexible linkage branch cable connected in parallel with the flexible linkage main cable loses the pulling force on the crank-shaped flap supporting rib and is subjected to the airflow on the lower surface of the wing and the acting force of the return spring to fold the trailing edge flap to return.
Furthermore, when the folding wing is folded, the wing supporting framework drives the skin supporting ribs and the wing skin to be folded towards the direction of the machine body, the skin supporting ribs drive the crank-shaped flap supporting ribs, the flexible flap skin and the flexible linkage cables to be synchronously folded towards the direction of the machine body, and the folding process of the folding wing with the folding trailing edge flap is completed.
Furthermore, the flexible flap skin is provided with flexible flap skin holes, when the folding trailing edge flap is adjusted downwards, part of airflow on the lower surface of the wing can extend to the trailing edge of the wing through the flexible flap skin holes, and therefore the speed of the airflow on the trailing edge of the wing can be increased, the laminar flow damage of the airflow on the upper surface of the wing can be delayed, and the reverse eddy influence of the folding trailing edge flap can be weakened.
Furthermore, one end of the flexible associated skin is connected with the front end of the flexible flap skin, the other end of the flexible associated skin is connected with the wing lower surface skin, the disturbance of the wing lower surface airflow to the flexible flap skin can be weakened in the non-adjusting state of the folding trailing edge flap, and the flexible associated skin can be made of flexible materials or elastic materials.
Furthermore, the folding trailing edge flap is provided with a flap slot, after the folding trailing edge flap is adjusted downwards, a flap slot is formed between the lower area of the step of the crank-shaped flap support rib and the skin on the lower surface of the wing, and partial airflow on the lower surface of the wing can extend to the trailing edge through the flap slot, so that the airflow speed of the trailing edge of the wing can be accelerated, the laminar flow damage of the airflow on the upper surface of the wing can be delayed, and the reverse eddy influence of the folding trailing edge flap can be weakened.
Further, the flap drive provides power to the flexible linkage cable.
The technical proposal of the utility model ensures that the folding wing has the function of adjusting the wing flap and the wing flap, and is matched with the aileron, so that the folding wing has the main function of the prior fixed wing; the folding trailing edge flap is completely attached to the main wing structure, so that the structure is simple, and the function is complete; the utility model discloses be applied to the aircraft that needs improve wing lift through the wing flap is adjusted, enlarged the application range of foldable wing.
Drawings
The invention will be further discussed with reference to the accompanying drawings:
FIG. 1 is a fully folded plan view of a folding wing (left half structure, right half plane) with a folding trailing edge flap;
FIG. 2 is a half-deployed plan view of a folding wing (left half structure, right half plane) with a folded trailing edge flap;
FIG. 3 is a fully deployed plan view of a folding wing (left half structure, right half plane) with a folded trailing edge flap;
FIG. 4 is a fully deployed plan view of a folding wing with a folded trailing edge flap;
FIG. 5 is a cross-sectional view A-A (1) of the folding wing of FIG. 4;
FIG. 6 is a partial enlarged view of a in FIG. 5;
FIG. 7 is a cross-sectional view A-A (2) of the folding wing of FIG. 4;
FIG. 8 is a partial enlarged view of b in FIG. 7;
FIG. 9 is a fully deployed plan view of a folding wing (with a slot) with a folded trailing edge flap;
FIG. 10 is a cross-sectional view B-B (1) of the folding wing of FIG. 9;
FIG. 11 is a partial enlarged view of c in FIG. 10;
FIG. 12 is a cross-sectional view B-B (2) of the folding wing of FIG. 9;
fig. 13 is a partial enlarged view of d in fig. 12.
In the drawings: (1) a wing support skeleton; (2) a slide rail; (3) a skin support rib; (4) the air bag inflatable covering is arranged on the upper surface of the wing; (5) covering the lower surface of the wing; (6) an aileron; (7) a crank-shaped flap support rib; (8) a flexible flap skin; (9) a connecting shaft; (10) a flexible linkage main cable; (11) a flexible linkage supporting cable; (12) a linkage cable support; (13) a return spring; (14) a flexible associated skin, (15) a flexible flap skin hole; (16) a flap slot; (17) flap drive.
Detailed Description
In order to make the technical problem, technical solution and advantageous effects to be solved by the present invention more clearly understood, the following description is given in conjunction with the accompanying drawings and embodiments to further explain the present invention in detail. Two types of folding wings with folding trailing edge flaps are shown in the drawings, and those skilled in the art can understand that other types of folding wings with folding trailing edge flaps can be developed by using the same principle, and they all belong to the scope of the present invention.
In the following discussion, the various numbers in the drawings are denoted as: 1: wing supporting framework, 2: slide rail, 3: skin support rib, 4: wing upper surface gasbag inflatable covering, 5: wing lower surface skin, 6: the folding wing formed by the aileron and the like in the prior art is called as a main wing for short.
Fig. 1, 2, 3 show a folding wing with a folding trailing edge flap (left half structure, right half plane): a process plan view of fully folded, half unfolded, fully unfolded.
Fig. 1 shows a fully folded state of a folding wing with a folded trailing edge flap when the wing is folded.
Fig. 2 shows a folding wing unfolding process with folding trailing edge flaps, wherein the wing support framework drives the skin support ribs 3 and the wing skin to unfold outwards, and the skin support ribs 3 drive the crank-shaped flap support ribs 7 and the flexible flap skin 8 and the flexible linkage cable to unfold outwards synchronously.
Fig. 3 shows that after the wing with the folded trailing edge flap is completely unfolded, the skin support rib 3 drives the crank-shaped flap support rib 7 to unfold and tighten the flexible flap skin 8, so as to form the folded wing with the folded trailing edge flap.
FIG. 4 is a fully deployed plan view of a folding wing with a folded trailing edge flap; FIG. 5 is a sectional view A-A (1) of FIG. 4 showing the cross-sectional interrelationship between the folded trailing edge flap and the main wing.
Fig. 6 is an enlarged view of a portion a of fig. 5, showing: at a proper position of the lower surface of the trailing edge of the main wing skin support rib 3, the crank-shaped flap support rib 7 is hinged with the skin support rib 3 through a connecting shaft 9, the upper surface of the long edge of the crank-shaped flap support rib 7 is tightly attached to the lower surface of the skin support rib 3 through a return spring 13, and the flexible flap skin 8 is attached to the upper surface of the crank-shaped flap support rib 7 and is tightly attached to the skin 5 on the lower surface of the main wing.
Furthermore, a linkage cable support 12 is arranged on the lower surface of the skin support rib 3, and forms a space triangle with the short side of the crank-shaped flap support rib 7 and the connecting shaft 9.
Furthermore, the flexible linkage main cable 10 and each flexible linkage branch cable 11 connected in parallel therewith jointly form a flexible linkage cable, one end of the flexible linkage branch cable 11 is connected with the end of the short side of the crank-shaped flap support rib 7, the other end is connected with the flexible linkage main cable 10, and the flexible linkage main cable 10 passes through a cable hole on the linkage cable support 12.
As shown in fig. 3, a plurality of crank-shaped flap support ribs 7 are hinged to the corresponding skin support ribs 3 in the same manner as described above, so as to form a folding trailing edge flap support framework depending on the skin support ribs 3.
Furthermore, a flexible flap skin 8 is connected to the upper surface of the folding trailing edge flap supporting framework to form a stress surface of the folding trailing edge flap for bearing airflow.
Further, the flexible linkage main cable 10 is connected in parallel with the flexible linkage branch cables 11 connected with the crank-shaped flap support ribs 7, the flexible linkage main cable 10 is connected in series and penetrates through cable holes in the linkage cable supports 12, and the terminal end of the flexible linkage main cable is connected with a flap driving device 17.
Further, when the aircraft needs to increase the wing lift force, the flap driving device 17 provides power to pull the flexible linkage main rope 10 to move along the cable hole on the linkage rope support 12, so as to drive each flexible linkage branch rope 11 connected in parallel with the flexible linkage main rope 10 to synchronously move along the cable hole on the linkage rope support 12, further pull each crank-shaped flap support rib 7 connected with the flexible linkage branch rope and the flexible flap skin 8 connected with the upper surface of the crank-shaped flap support rib to synchronously rotate around the connecting shaft 9, form integral folding trailing edge flap to rotate and adjust downwards, and achieve the purposes of increasing the wing camber and area, changing the wing aerodynamic form and increasing the wing lift force.
FIG. 7 is a section A-A (2) of FIG. 4, showing the cross-sectional configuration of the airfoil after the folded trailing edge flap has been adjusted downwardly. Fig. 8 is a partial enlarged view of b of fig. 7, showing the downwardly adjusted configuration of the crank-shaped flap support rib 7 rotated about the connecting shaft 9 by the pulling of the flexible link stay 11.
In fig. 6 and 8, the flexible associated skin 14 is connected to the front end of the flexible flap skin 8 at one end and to the wing lower surface skin 5 at the other end, so that disturbance of the wing lower surface airflow to the flexible flap skin 8 can be reduced in the non-adjustment state of the folded trailing edge flap, and the flexible associated skin 14 may be made of a flexible material or an elastic material.
In the figure, 15 is a flexible flap skin hole, which functions to: when the folding trailing edge flap is adjusted downwards, part of airflow on the lower surface of the wing can extend to the trailing edge of the wing through the flexible flap skin holes 15, so that the airflow speed of the trailing edge of the wing can be accelerated, the laminar flow damage of the airflow on the upper surface of the wing can be delayed, and the reverse eddy influence of the folding trailing edge flap can be weakened.
Fig. 9 shows another version of a folding wing with a folded trailing edge flap, which is primarily characterized by a flap slot 16.
FIG. 10 is a sectional view B-B (1) of FIG. 9, showing the sectional relationship between the main wing and the folded trailing edge flap.
Fig. 11 is a partial enlarged view of c of fig. 10, in which: the skin support rib 3 is designed to have step deformation at the rear edge part, and the skin 5 on the lower surface of the wing connected with the skin support rib is correspondingly connected in a step shape.
Furthermore, the crank-shaped flap support rib 7 is also designed to be deformed in a step manner, a flexible flap skin 8 is connected to the upper surface of the step of the crank-shaped flap support rib 7, the lower surface of the step of the crank-shaped flap support rib 7 is free of the skin, and the area is the area of the flap slot 16.
Furthermore, the crank-shaped flap support rib 7 is connected with the lower surface of the skin support rib 3 through the connecting shaft 9, in a normal state, under the action of the return spring 13, the stepped upper surface of the crank-shaped flap support rib 7 is matched and close to the stepped lower surface of the skin support rib 3, and the front end of the flexible flap skin 8 is hidden behind the step formed by the skin 5 on the lower surface of the wing, so that the impact of the airflow on the front end of the folded trailing edge flap on the lower surface of the wing is weakened.
FIG. 12 is a sectional view B-B (2) of FIG. 9, showing the cutaway relationship between the folded trailing edge flap down-adjusted and the main wing.
Fig. 13 is an enlarged view of part d of fig. 12, in which: after the folding trailing edge flap is adjusted downwards, a flap strip slit 16 is formed between the lower area of the step of the crank-shaped flap support rib 7 and the wing lower surface skin 5, and partial airflow on the wing lower surface can be continued to the wing trailing edge through the flap strip slit 16, so that the airflow speed of the wing trailing edge can be accelerated, the laminar flow damage of the airflow on the wing upper surface can be delayed, and the reverse eddy influence of the folding trailing edge flap can be weakened.
Those skilled in the art will appreciate that flap drive 17 can power the flexible linkage cable in a number of ways, such as: the swing arm, or the speed changing gear, or the chain, etc. are adopted, and will not be described in detail herein.
The utility model has the main advantages that:
1. the folding wing has the functions of adjusting the flap and the flap, and is matched with the aileron, so that the folding wing has the main functions of the existing fixed wing;
2. the folding trailing edge flap is completely attached to the main wing structure, so that the structure is simple, and the function is complete;
3. the utility model discloses be applied to the aircraft that needs improve wing lift through the wing flap is adjusted, enlarged the application range of foldable wing.
Example (b):
the utility model discloses be applied to a hovercar, this hovercar all need increase the wing lift through the wing flap is adjusted in taking off and descending stage, realizes that hovercar takes off smoothly and descends safely.
The above description is only exemplary of the present invention and should not be taken as limiting the scope of the present invention, as any modifications, equivalents, improvements and the like made within the spirit and principles of the present invention are intended to be included within the scope of the present invention.
Claims (9)
1. A folding wing with a folding trailing edge flap is characterized by comprising a main wing,
the main wing includes: a wing supporting framework (1), a slide rail (2), a skin supporting rib (3), a wing upper surface air bag inflatable skin (4), a wing lower surface skin (5) and an aileron (6), an
A folded trailing edge flap, the folded trailing edge flap comprising: a plurality of crank-shaped flap support ribs (7); a flexible flap skin (8); a connecting shaft (9); a flexible linkage main cable (10); a flexible linkage guy cable (11); a link cable support (12); a return spring (13); and a flap drive (17),
a plurality of crank-shaped flap supporting ribs (7) are hinged to the lower surfaces of corresponding skin supporting ribs (3) through connecting shafts (9) to form a folding trailing edge flap supporting framework depending on the skin supporting ribs (3), the upper surfaces of the long edges of the crank-shaped flap supporting ribs (7) are tightly attached to the lower surfaces of the skin supporting ribs (3) through reset springs (13), and flexible flap skins (8) are attached to the upper surfaces of the folding trailing edge flap supporting frameworks.
2. The folding wing with a folded trailing edge flap of claim 1, characterized in that: the linkage cable support (12) is arranged on the lower surface of the skin support rib (3), and forms a space triangle with the short side of the crank-shaped flap support rib (7) and the connecting shaft (9); the flexible linkage main cable (10) is connected with each flexible linkage branch cable (11) in parallel, one end of each flexible linkage branch cable (11) is connected with the short-edge end of the crank-shaped flap support rib (7), the other end of each flexible linkage branch cable is connected with the flexible linkage main cable (10), the flexible linkage main cables (10) are connected in series and penetrate through cable holes in each linkage cable support (12), and the terminals of the flexible linkage main cables are connected with a flap driving device (17).
3. The folding wing with a folded trailing edge flap of claim 1, characterized in that: after the folding wing is unfolded, when the aircraft needs to increase the wing lift force, the flap driving device (17) provides power, the flexible linkage main cable (10) moves along cable holes on the linkage cable support (12) by pulling, so that each flexible linkage branch cable (11) connected with the flexible linkage main cable (10) in parallel is driven to synchronously move along the cable holes on the linkage cable support (12), and each crank-shaped flap support rib (7) connected with the flexible linkage main cable is further pulled to synchronously rotate around the connecting shaft (9), and the whole folding flap trailing edge is rotated and adjusted downwards.
4. The folding wing with a folded trailing edge flap of claim 1, characterized in that: when the aircraft resumes normal flight, the flap driving device (17) releases the flexible linkage main cable (10), and each flexible linkage branch cable (11) connected in parallel with the flexible linkage main cable (10) loses the pulling force on the crank-shaped flap supporting rib (7) and is reset by the airflow on the lower surface of the wing and the acting force of the reset spring (13).
5. The folding wing with a folded trailing edge flap of claim 1, characterized in that: when the folding wing is folded, the wing supporting framework (1) drives the skin supporting rib (3) and the wing skin to be folded towards the direction of the machine body, the skin supporting rib (3) drives the crank-shaped flap supporting rib (7), the flexible flap skin (8) and the flexible linkage cable to be synchronously folded towards the direction of the machine body, and the folding process of the folding wing with the folding trailing edge flap is completed.
6. The folding wing with a folded trailing edge flap of claim 1, characterized in that: the flexible flap skin (8) is provided with flexible flap skin holes (15), when the flap of the folding trailing edge is adjusted downwards, part of airflow on the lower surface of the wing can extend to the trailing edge of the wing through the flexible flap skin holes (15), so that the airflow speed of the trailing edge of the wing can be accelerated, the laminar flow damage of the airflow on the upper surface of the wing can be delayed, and the reverse eddy influence of the flap of the folding trailing edge can be weakened.
7. The folding wing with a folded trailing edge flap of claim 1, characterized in that: one end of the flexible associated skin (14) is connected with the front end of the flexible flap skin (8), the other end of the flexible associated skin is connected with the wing lower surface skin (5), the disturbance of the wing lower surface airflow to the flexible flap skin (8) can be weakened in the non-adjusting state of the folding trailing edge flap, and the flexible associated skin (14) can be made of flexible materials or elastic materials.
8. The folding wing with a folded trailing edge flap of claim 1, characterized in that: the folding trailing edge flap is provided with a flap slot (16), after the folding trailing edge flap is adjusted downwards, a flap slot (16) is formed between the lower area of the step of the crank-shaped flap support rib (7) and the wing lower surface skin (5), partial airflow on the lower surface of the wing can extend to the trailing edge of the wing through the flap slot (16), and therefore the airflow speed of the trailing edge of the wing can be accelerated, the laminar flow damage of the airflow on the upper surface of the wing can be delayed, and the reverse vortex influence of the folding trailing edge flap can be weakened.
9. Folding wing with folded trailing edge flap according to one of claims 1 to 8, characterized in that: the flap drive (17) powers the flexible linkage cable.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021502508.9U CN213083484U (en) | 2020-07-27 | 2020-07-27 | Folding wing with folding trailing edge flap |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021502508.9U CN213083484U (en) | 2020-07-27 | 2020-07-27 | Folding wing with folding trailing edge flap |
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| Publication Number | Publication Date |
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| CN213083484U true CN213083484U (en) | 2021-04-30 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202021502508.9U Withdrawn - After Issue CN213083484U (en) | 2020-07-27 | 2020-07-27 | Folding wing with folding trailing edge flap |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111824394A (en) * | 2020-07-27 | 2020-10-27 | 及兰平 | Folding wing with folding trailing edge flap |
-
2020
- 2020-07-27 CN CN202021502508.9U patent/CN213083484U/en not_active Withdrawn - After Issue
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111824394A (en) * | 2020-07-27 | 2020-10-27 | 及兰平 | Folding wing with folding trailing edge flap |
| CN111824394B (en) * | 2020-07-27 | 2023-09-05 | 及兰平 | Folding wing with folding trailing edge flap |
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