CN211592909U - Retractable wing flap auxiliary high lift device - Google Patents
Retractable wing flap auxiliary high lift device Download PDFInfo
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- CN211592909U CN211592909U CN201922139451.4U CN201922139451U CN211592909U CN 211592909 U CN211592909 U CN 211592909U CN 201922139451 U CN201922139451 U CN 201922139451U CN 211592909 U CN211592909 U CN 211592909U
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Abstract
The utility model provides a pair of supplementary high-lift device of retractable wing flap, including the main wing, the wing flap, first wing flap support arm, second wing flap support arm, hydraulic actuator drive pull rod, the supplementary high-lift device of wing flap and jack, the main wing links firmly with first wing flap support arm, first wing flap support arm is articulated with second wing flap support arm, second wing flap support arm links firmly with the wing flap, the wing flap is articulated with hydraulic actuator drive pull rod, the supplementary high-lift device of wing flap is connected with the jack, and through jack and the linkage of wing flap, realize receiving and releasing in step. The utility model discloses a but supplementary high-lift device of retractable wing flap, the supplementary high-lift device of wing flap passes through the jack and links with the wing flap, realizes the supplementary high-lift device of wing flap and the synchronous of wing flap expert receive and release, has solved the not enough problem of simple pivoting motion's wing flap high-lift effect, avoids adopting the complicated structure weight increase that big retreat volume single slit wing flap and multislice wing flap lead to simultaneously, and the reliability descends, manufacturing cost increase scheduling problem.
Description
Technical Field
The utility model belongs to the technical field of aircraft structural design, concretely relates to supplementary device that rises of retractable wing flap.
Background
In order to reduce the length of the take-off and landing runway of the airplane and improve the lift coefficient, a single-slit flap and a multi-slit flap with large backing amount are generally adopted for realizing the lift coefficient. However, due to the large retreating stroke and the complex movement mechanism, the structure is heavy, the process tool requirement is high, clamping stagnation is easy to occur, the reliability is reduced, and the manufacturing cost is increased. The flap moving mechanism which adopts simple axial movement is simple, the retreating stroke is small, the actuating system is simple, the structure weight is light, the process tool is simple, the reliability is high, but the retreating amount is small, the high lift effect is poor, and the high lift requirement is difficult to meet.
Disclosure of Invention
The utility model aims to solve the problem that the simple wing flap lift-increasing effect around the shaft motion is not enough, and adopts the complicated structure weight increase that results in with the multislice wing flap of the big volume of retreating, and the reliability descends, and the technical problem that the manufacturing cost increases provides a but the supplementary lift-increasing device of retractable wing flap, has improved the lift-increasing effect of simple wing flap around the shaft motion.
In order to solve the technical problem of the present invention, the retraction mechanism is used to realize the synchronous retraction of the flap auxiliary high lift device and the flap, the long-strip flap auxiliary high lift device is used to inhibit the upper vortex by using the retardation effect thereof, so that the wake flow is strongly washed down (the wing can generate different pressures on the upper and lower surfaces in the air flow, the upper surface pressure is smaller, the lower surface pressure is larger, and the wing generates upward lift force by virtue of the unbalanced pressure distribution. The mini-tornado "induces a small downward velocity component in the ambient airflow, which is called downwash. ) The pressure of the upper wing surface is reduced, and the pressure of the lower wing surface is increased, so that the lift force of the airplane is increased. The linkage flap auxiliary high lift device is introduced on the basis of a simple axial high lift device, the problem of insufficient flap high lift effect caused by simple axial motion is solved, and the technical problems of structural weight increase, reliability reduction, manufacturing cost increase and the like caused by the adoption of complex large-retreating-amount single-slit flaps and multi-slit flaps are avoided.
The utility model discloses a realize through following technical scheme: the utility model provides a supplementary high-lift system of retractable wing flap, includes main wing, wing flap, first wing flap support arm, second wing flap support arm, hydraulic actuator drive pull rod, the supplementary high-lift system of wing flap and jack, the main wing links firmly with first wing flap support arm, first wing flap support arm and second wing flap support arm hinged joint, second wing flap support arm with the wing flap links firmly, wing flap and hydraulic actuator drive pull rod hinged joint, the supplementary high-lift system of wing flap with jack is connected, and passes through jack with the wing flap linkage, the supplementary high-lift system of wing flap with the wing flap passes through jack realizes synchronous receiving and releasing.
In one possible implementation manner of the present disclosure, the retraction mechanism includes a first connecting rod, an L-shaped connecting rod, and a second connecting rod, where the first connecting rod is hinged to the L-shaped connecting rod; one end of the L-shaped connecting rod is hinged with the flap, and the other end of the L-shaped connecting rod is hinged with the second connecting rod; the second connecting rod is hinged with the first flap support arm.
According to one possible implementation manner of the present disclosure, the flap auxiliary high lift device is in a strip shape, and the length of the flap auxiliary high lift device is 2% of the local chord length of the whole wing when the flap is in the retracted state, so that the high lift effect is good, and the additional resistance is small. The wing flap auxiliary high lift device has the advantages that the section is an airfoil section, the integrity of the whole airfoil section can be ensured when the wing flap auxiliary high lift device is folded and unfolded, and the resistance is small.
In one possible implementation of the disclosure, the first flap arm is connected to the second flap arm by a hinge joint.
In one possible implementation of the disclosure, the flap is connected to the hydraulic actuator drive link by a hinge joint.
In one possible implementation of the disclosure, the first link is connected to the L-shaped link by a hinge joint.
In a possible implementation manner of the present disclosure, one end of the L-shaped link is connected to the flap through a hinge joint, and the other end of the L-shaped link is connected to the second link through a hinge joint.
In one possible implementation of the disclosure, the second link is connected to the first flap arm by a hinge joint.
Compared with the prior art, the utility model discloses the beneficial effect who obtains is:
the utility model discloses a but supplementary high-lift device of retractable wing flap, the supplementary high-lift device of wing flap passes through the jack and links with the wing flap, realizes the supplementary high-lift device of wing flap and the synchronous of wing flap expert receive and releases. When the wing flap is in an extending state in the taking-off and landing stage of the airplane, the wing flap auxiliary high lift device extends out simultaneously and is perpendicular to the lower surface of the wing flap, airflow at the tail edge of the lower surface of the wing flap is blocked, upward vortex is inhibited, the whole wake flow generates strong downward washing, the pressure of an upper wing surface is reduced, and the pressure of a lower wing surface is increased, so that the lift force of the airplane is increased. When the airplane cruises, the flaps are in a retracted state, and the auxiliary high lift devices are synchronously retracted into the wings through the retraction and release mechanisms, so that additional resistance generated during cruises flight is avoided. The auxiliary high lift device is hinged with the flap and the flap support arm through the hinged joint and rotates around the hinged joint through the connecting rod, so that synchronous retraction and release of the flap are realized, and the retraction and release mechanism is simple, stable in operation and small in weight.
The utility model discloses a supplementary high lift device of retractable wing flap introduces the supplementary high lift device of linkage wing flap on the basis of simple high lift device of spool, has solved the problem that the wing flap high lift effect of simple spool motion is not enough, avoids adopting the complicated structure weight increase that big retreat volume single slit wing flap and multislice wing flap lead to simultaneously, and the reliability descends, manufacturing cost increase scheduling problem.
Drawings
FIG. 1 is a flap axis view.
Fig. 2 is a side view of the flap extended state.
Fig. 3 is a side view of the flap stowed position.
Reference numerals: 1. a main wing; 2. a flap; 3. a flap auxiliary high lift device; 4. a flap auxiliary high lift device profile; 5. flap assisted high lift device length; 6. a hinge joint; 7. the hydraulic actuator drives the connecting rod; 8. 9, hinge joints; 10. an L-shaped connecting rod; 11. a hinge joint; 12. a hinge joint; 13. a second link; 14. a hinge joint; 15. a first flap support arm; 16. a hinge joint; 17. a first flap support arm; 18. a first link; 19. a hinge joint.
Detailed Description
The embodiments are described in detail below with reference to the accompanying drawings.
Referring to fig. 1 to 3, a retractable flap auxiliary high lift device comprises a main wing 1, a flap 2, a first flap support arm 15, a second flap support arm 17, a hydraulic actuator drive pull rod 7, a flap auxiliary high lift device 3 and a retraction mechanism, wherein the main wing 1 is fixedly connected with the first flap support arm 15 and is connected with the second flap support arm 17 through a hinge joint 16, and the second flap support arm 17 is fixedly connected with the flap 2; the flap 2 is connected to a hydraulic actuator drive link 7 by means of a hinge joint 8 and to the main wing 1 by means of a hinge joint 6. The retraction mechanism comprises a first connecting rod 18, an L-shaped connecting rod 10 and a second connecting rod 13, the flap auxiliary high lift device 3 is connected with the first connecting rod 18 through a hinge joint 19 and is connected with the L-shaped connecting rod 10 through a hinge joint 11, one end of the L-shaped connecting rod 10 is connected with the flap 2 through a hinge joint 9, the other end of the L-shaped connecting rod 10 is connected with the second connecting rod 13 through a hinge joint 12 and is connected with a first flap support arm 15 through a hinge joint 14, and the flap auxiliary high lift device 3 is linked with the flap 2 to realize synchronous retraction. The flap 2 is driven by the hydraulic actuator drive pull rod 7 to deflect downwards, and the flap auxiliary high lift device 3 is driven to open downwards under the action of the first connecting rod 18, the L-shaped connecting rod 10 and the second connecting rod 13.
Furthermore, the flap auxiliary high lift device 3 is a strip-shaped auxiliary high lift device, and by utilizing the retarding effect of the strip-shaped auxiliary high lift device, the upper vortex is inhibited, so that the wake flow generates strong downwash, the pressure of the upper wing surface is reduced, and the pressure of the lower wing surface is increased, so that the lift force of the airplane is increased, and the problem of insufficient flap lift effect caused by simple axial movement is solved.
When the flap 2 is in an extending state in the taking-off and landing stage of the airplane, the flap auxiliary high lift device 3 extends out simultaneously and is perpendicular to the lower surface of the flap 2, airflow at the tail edge of the lower surface of the flap 2 is retarded, upward vortex is inhibited, the whole wake flow generates strong downward washing, the pressure of an upper wing surface is reduced, and the pressure of a lower wing surface is increased, so that the lift force of the airplane is increased. The flaps 2 are in a retracted state in the cruising stage of the airplane, and the flap auxiliary high lift devices 3 are synchronously retracted into the wings through retraction mechanisms, so that additional resistance generated in cruising flight is avoided. The flap auxiliary high lift device 3 is hinged with the flap 2 and the first flap support arm 15 through a hinged joint and rotates around the hinged joint through a connecting rod, so that synchronous retraction and release of the flap 2 are realized, and the retraction and release mechanism is simple, stable in work and small in weight.
The above list is only one of the specific embodiments of the present invention. It will be clear that the invention is not limited to the above embodiments, but that many similar modifications are possible. All modifications which can be derived or suggested by a person skilled in the art from the disclosure of the invention should be considered within the scope of the invention.
Claims (8)
1. The utility model provides a supplementary high lift device of retractable wing flap, includes main wing, wing flap, first wing flap support arm, second wing flap support arm and hydraulic actuator drive pull rod, the main wing links firmly with first wing flap support arm, first wing flap support arm and second wing flap support arm hinged joint, second wing flap support arm with the wing flap links firmly, wing flap and hydraulic actuator drive pull rod hinged joint, its characterized in that: the novel high-lift wing flap device is characterized by further comprising a high-lift flap auxiliary device and a retraction mechanism, wherein the high-lift flap auxiliary device is connected with the retraction mechanism and is linked with the high-lift flap through the retraction mechanism, and the high-lift flap auxiliary device and the high-lift flap are retracted synchronously.
2. A retractable flap-assisted high lift device according to claim 1, characterized in that: the folding and unfolding mechanism comprises a first connecting rod, an L-shaped connecting rod and a second connecting rod, and the first connecting rod is hinged with the L-shaped connecting rod; one end of the L-shaped connecting rod is hinged with the flap, and the other end of the L-shaped connecting rod is hinged with the second connecting rod; the second connecting rod is hinged with the first flap support arm.
3. A retractable flap-assisted high lift device according to claim 1, characterized in that: the flap auxiliary high lift device is in a long strip shape, the length of the flap auxiliary high lift device is 2% of the local chord length of the whole wing when the flap is in a retracted state, and the section of the flap auxiliary high lift device is an airfoil section.
4. A retractable flap auxiliary high lift device according to any one of claims 1 to 3, characterized in that: the first flap support arm is connected with the second flap support arm through a hinge joint.
5. A retractable flap auxiliary high lift device according to any one of claims 1 to 3, characterized in that: the flap is connected with a hydraulic actuator driving pull rod through a hinge joint.
6. A retractable flap-assisted high lift device according to claim 2, characterized in that: the first connecting rod is connected with the L-shaped connecting rod through a hinge joint.
7. A retractable flap-assisted high lift device according to claim 2, characterized in that: one end of the L-shaped connecting rod is connected with the flap through a hinge joint, and the other end of the L-shaped connecting rod is connected with the second connecting rod through a hinge joint.
8. A retractable flap-assisted high lift device according to claim 2, characterized in that: the second connecting rod is connected with the first flap support arm through a hinge joint.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922139451.4U CN211592909U (en) | 2019-12-04 | 2019-12-04 | Retractable wing flap auxiliary high lift device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922139451.4U CN211592909U (en) | 2019-12-04 | 2019-12-04 | Retractable wing flap auxiliary high lift device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN211592909U true CN211592909U (en) | 2020-09-29 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201922139451.4U Active CN211592909U (en) | 2019-12-04 | 2019-12-04 | Retractable wing flap auxiliary high lift device |
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| CN (1) | CN211592909U (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112607054A (en) * | 2020-12-29 | 2021-04-06 | 中国航空工业集团公司西安飞机设计研究所 | Model is slowed down in wing gust |
| RU2764335C1 (en) * | 2021-10-15 | 2022-01-17 | Общество с ограниченной ответственностью «Научно Инженерная Компания» | Airplane wing flap control device |
| CN114426093A (en) * | 2022-01-19 | 2022-05-03 | 中电科芜湖通用航空产业技术研究院有限公司 | Unmanned aerial vehicle follow-up flap system, wing of unmanned aerial vehicle and unmanned aerial vehicle |
| CN114506442A (en) * | 2022-01-28 | 2022-05-17 | 中国商用飞机有限责任公司 | Wing with turbulence auxiliary device and flight device comprising same |
| CN114852301A (en) * | 2022-04-01 | 2022-08-05 | 哈尔滨工程大学 | Auxiliary propulsion device for flap of wave glider |
| CN115892448A (en) * | 2023-03-13 | 2023-04-04 | 北京启时智航科技有限公司 | Flaperon structure, wing and aircraft |
| CN118494746A (en) * | 2024-07-16 | 2024-08-16 | 壹通无人机系统有限公司 | Double-hinge flap retracting mechanism |
-
2019
- 2019-12-04 CN CN201922139451.4U patent/CN211592909U/en active Active
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112607054A (en) * | 2020-12-29 | 2021-04-06 | 中国航空工业集团公司西安飞机设计研究所 | Model is slowed down in wing gust |
| RU2764335C1 (en) * | 2021-10-15 | 2022-01-17 | Общество с ограниченной ответственностью «Научно Инженерная Компания» | Airplane wing flap control device |
| CN114426093A (en) * | 2022-01-19 | 2022-05-03 | 中电科芜湖通用航空产业技术研究院有限公司 | Unmanned aerial vehicle follow-up flap system, wing of unmanned aerial vehicle and unmanned aerial vehicle |
| CN114426093B (en) * | 2022-01-19 | 2024-03-01 | 中电科芜湖通用航空产业技术研究院有限公司 | Unmanned aerial vehicle follow-up flap system and unmanned aerial vehicle's wing and unmanned aerial vehicle |
| CN114506442A (en) * | 2022-01-28 | 2022-05-17 | 中国商用飞机有限责任公司 | Wing with turbulence auxiliary device and flight device comprising same |
| CN114506442B (en) * | 2022-01-28 | 2024-07-05 | 中国商用飞机有限责任公司 | Wing with turbulence auxiliary device and flight device comprising wing |
| CN114852301A (en) * | 2022-04-01 | 2022-08-05 | 哈尔滨工程大学 | Auxiliary propulsion device for flap of wave glider |
| CN115892448A (en) * | 2023-03-13 | 2023-04-04 | 北京启时智航科技有限公司 | Flaperon structure, wing and aircraft |
| CN118494746A (en) * | 2024-07-16 | 2024-08-16 | 壹通无人机系统有限公司 | Double-hinge flap retracting mechanism |
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP02 | Change in the address of a patent holder |
Address after: Nanchang high tech Industrial Development Zone, Jiangxi Province Patentee after: JIANGXI HONGDU AVIATION INDUSTRY GROUP Co.,Ltd. Address before: 330000 Jiangxi city in Nanchang Province, the new bridge box 460 box 5001 Patentee before: JIANGXI HONGDU AVIATION INDUSTRY GROUP Co.,Ltd. |
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| CP02 | Change in the address of a patent holder |