CN104044728A - Spring type flap sealing mechanism - Google Patents
Spring type flap sealing mechanism Download PDFInfo
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- CN104044728A CN104044728A CN201410279901.9A CN201410279901A CN104044728A CN 104044728 A CN104044728 A CN 104044728A CN 201410279901 A CN201410279901 A CN 201410279901A CN 104044728 A CN104044728 A CN 104044728A
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Abstract
The invention relates to a spring type flap sealing mechanism which comprises an upper sealing mechanism and a lower sealing mechanism, wherein the upper sealing mechanism and the lower sealing mechanism are respectively riveted with wings and flaps; the upper sealing mechanism comprises an upper rear sealing plate, an upper middle sealing plate, an upper front sealing plate, an upper hinge rear joint, an upper hinge front joint, a spring and a lower spring hook; the lower sealing mechanism comprises a lower rear sealing plate, a lower middle sealing plate, a lower front sealing plate, a lower hinge rear joint, a lower hinge front joint and an upper spring hook. The spring type flap sealing mechanism disclosed by the invention has the advantage of simple structure and function principle, and complex members such as sliding tracks are not needed; under the action of spring tension, the tail ends of the middle sealing plates are attached on the outer surfaces of the rear sealing plates all the time, so that gaps between the wings and the flaps can be effectively sealed, and a sealing effect can be kept all the time in the process of flap deflection.
Description
Technical field
The present invention relates to aeroplane structure design field, relate in particular to a kind of spring loaded wing flap sealing mechanism.
Background technology
The maneuver flap of aircraft wing leading edge is generally driven by rotary actuator, and rotary actuator is connected with wing flap with wing by auricle respectively.When dirty deflection, between the front part of a Chinese robe or jacket and main plane, can produce very large gap, this gap all has adverse effect to aircraft Stealth Fighter and aeroperformance.
At present part aircraft adopts one to be fixed to closing plate on wing flap to the sealing gap between wing and wing flap, and sealing plate is the sheet metal of a flexibility, by methods such as predeformation, its end and wing outside face is fitted.Under wing flap, opportunity, thriving face can force lower seal plate to deform partially.The problem existing is at present: because actuator auricle is larger, near top airfoil closing plate auricle can upwarp and cause closing plate poorly sealed when inclined to one side under wing flap.In addition, under wing flap, the distortion of lower aerofoil closing plate is larger partially time, and in aircraft flight process its maneuver flap position with state of flight real-time change, make closing plate within the shorter flight time, bear the bending repeatedly of more number of times, thus, closing plate can crack and destroy very soon, and the life-span is shorter.
No. 3974978 patent of the U.S. adopts mechanism type sealing arrangement to above-mentioned sealing gap at lower aerofoil.In this scheme, closing plate is connected with wing by hinge, and its end is fitted in wing flap outside face, so seals the gap between wing and wing flap.A spring is installed between closing plate and wing makes closing plate end and wing flap keep laminating; On closing plate, have a spring support arm, a spring hanger is equipped with in wing lower aerofoil inner side; Spring end is connected on the spring hanger of wing lower aerofoil inner side and the spring support arm of closing plate.
China ZL201210031514.4 patent has proposed a set of sliding track mechanism formula sealing arrangement, and it comprises upper and lower two cover sealing mechanisms.In this scheme, slide rail is installed in wing inner side, and closing plate is arranged on wing flap by built-in hinge and is overlapped on wing outside face, and roller support arm is equipped with in closing plate inner side, utilizes pulley-sliding track mechanism that closing plate end is fitted with wing outside face all the time.
For No. 3974978 patent of the U.S., due in engineering reality between wing and wing flap space comparatively nervous, make that larger spring is installed herein more difficult.When flap deflection angle is larger, the length that spring need to stretch is larger, the spring free length that this just need to be longer, and this has brought difficulty also to the application of spring.In addition, the hinge form in this scheme between closing plate and wing is simple, causes still having larger gap between closing plate and wing, and this can also have larger adverse effect to the stealthy new of aircraft.
There is following shortcoming in China ZL201210031514.4 patent: 26S Proteasome Structure and Function principle is complicated, and member is more; For guaranteeing that closing plate end can fit tightly with wing, needs higher sliding track mechanism working accuracy; Because aircraft wing thickness is successively decreased to wing tip direction by wing root, and generally there is torsion in wing, and making the closing plate characteristics of motion is complicated space motion, caused difficulty to design and the processing of sliding track mechanism; Because the plate of obturaging is space motion, in the plate motion process of obturaging, need to produce a small amount of torsion, for guaranteeing sealing effectiveness, in spanwise, need to arrange a plurality of sliding track mechanisms, cause sleeve mechanism weight larger.
In view of above-mentioned defect, creator of the present invention has obtained this creation finally through long research and practice.
Summary of the invention
The object of the present invention is to provide a kind of spring loaded wing flap sealing mechanism, in order to overcome above-mentioned technological deficiency.
For achieving the above object, the invention provides a kind of spring loaded wing flap sealing mechanism, it comprises upper and lower two cover sealing mechanisms, and upper and lower sealing mechanism is assembled together by the modes such as riveted joint and wing and wing flap respectively;
Wherein, upper sealing mechanism comprises joint after closing plate before closing plate in rear flank closing plate, upside, upside, upside hinge, the front connector of upside hinge, spring, downside spring hanger;
Lower seal machine comprises joint after closing plate before closing plate in lower rear flank closing plate, downside, downside, downside hinge, the front connector of downside hinge, upside spring hanger.
Further, described wing all has step-like depression at upper and lower aerofoil, and installs rear flank closing plate and lower rear flank closing plate at recess;
Described wing flap all has step-like depression at upper and lower aerofoil, and before recess is installed upside closing plate before closing plate and downside;
Described rotary actuator is connected with wing flap with wing respectively by auricle.
Further, described spring arranged crosswise, the both ends of the spring of described upper sealing mechanism is hung in after upside hinge on joint and downside spring hanger, and the both ends of the spring of described lower seal mechanism is hung in after downside hinge on joint and upside spring hanger.
Further, described upper rear flank closing plate has step-like depression in surface thereon, the outer surface profile of step upper part is consistent with aerofoil profile, part below step is bent downwardly, its crooked radian will guarantee that wing flap puts down in process, in upside, closing plate can not interfered with upper rear flank closing plate, and its length will guarantee that wing flap puts down closing plate in rear upside completely and still can be overlapped on the closing plate of rear flank, and be unlikely to both, departs from.
Further, described lower rear flank closing plate is segment distance place bending to the inside after closing plate end in downside, curved shape guarantees that in downside, closing plate end lap is when the closing plate outside face of lower rear flank, and in downside, closing plate outer surface profile is consistent with aerofoil profile curve.
Further, in described upside, in closing plate and downside, closing plate is Varying Thickness Plates, state on wing flap is received, and its outer surface profile is consistent with aerofoil profile curve.
Further, after upside hinge, after joint and downside hinge, joint is secured to respectively in upside closing plate inner side in closing plate and downside, after upside hinge after joint and downside hinge the pinhole of joint have respectively spring hanging hole below.
Further, after in described upside, closing plate guarantees that wing flap puts down completely, its end is still overlapped on rear flank closing plate outside face; In downside, the length of closing plate guarantees after wing flap puts down completely, and its end can not slide on wing lower surface; Lower rear flank closing plate guarantees that it does not produce and interfere with other parts in wing flap down state.
Further, before described upside, the front closing plate of closing plate and downside is arranged on respectively the recess of the upper and lower outside face of wing flap, and its outer surface profile is consistent with aerofoil profile curve.
Further, the front connector of described upside hinge and the front connector of downside hinge are connected to before upside the inner side of closing plate before closing plate and downside by modes such as riveted joints respectively.
Beneficial effect of the present invention is compared with prior art: the 26S Proteasome Structure and Function principle of spring loaded wing flap sealing mechanism of the present invention is simple, does not need the complex components such as slide rail; Under the effect of spring tension, middle closing plate end is fitted in rear closing plate outside face all the time, can effectively seal the gap between wing and wing flap, and also can remain sealing effectiveness in flap deflection process; Each parts do not need to produce large deformation, and the life-span is longer; After hinge between middle closing plate and front closing plate, joint plays the effect of spring hanger simultaneously; Its size is less, and weight is lighter, and it is easier to process.
Accompanying drawing explanation
Fig. 1 is the three-dimensional exploded view of spring loaded wing flap sealing mechanism of the present invention;
Fig. 2 is the three-dimensional assembly drowing of spring loaded wing flap sealing mechanism of the present invention;
Fig. 3 A is the planar view of the present invention's state on wing flap is received;
Fig. 3 B is that the present invention is at the planar view of wing flap down state.
The specific embodiment
Below in conjunction with accompanying drawing, to the present invention is above-mentioned, be described in more detail with other technical characterictic and advantage.
Refer to shown in Fig. 1, it is the three-dimensional exploded view of spring loaded wing flap sealing mechanism of the present invention; Sealing mechanism of the present invention is divided into upper and lower two cover sealing mechanisms; Upper and lower sealing mechanism is assembled together by the modes such as riveted joint and wing 1 and wing flap 11 respectively.
Wherein, upper sealing mechanism comprises joint 9 after closing plate 13 before closing plate 12 in rear flank closing plate 15, upside, upside, upside hinge, upside hinge front connector 14, downside spring hanger 10 and corresponding attaching parts;
Lower seal machine comprises joint 7 after closing plate 4 before closing plate 6 in lower rear flank closing plate 3, downside, downside, downside hinge, downside hinge front connector 5, upside spring hanger 16 and corresponding attaching parts.
Wing 1 all has step-like depression at upper and lower aerofoil, and installs rear flank closing plate 15 and lower rear flank closing plate 3 at recess.
Wing flap 11 all has step-like depression at upper and lower aerofoil, and before recess is installed upside closing plate 4 before closing plate 13 and downside.
Rotary actuator 2 is connected with wing flap 11 with wing 1 respectively by auricle.
Refer to shown in Fig. 2 spring 8 arranged crosswise, the effect that after upside hinge, after joint 9 and downside hinge, joint 7 serves as spring hanger simultaneously.Spring 8 two ends of upper sealing mechanism are hung in after upside hinge on joint 9 and downside spring hanger 10, and the both ends of the spring of lower seal mechanism is hung in after downside hinge on joint 7 and upside spring hanger 16.On wing flap is received and down state, all springs all remain on tensioning state, and spring tension makes in upside the end of closing plate 6 in closing plate 12 and downside be fitted in all the time rear flank closing plate 15 and lower rear flank closing plate 3 outside faces.
Refer to shown in Fig. 3 A, it is the planar view of the present invention's state on wing flap is received; Upper rear flank closing plate 15 thereon surface has step-like depression.The outer surface profile of step upper part is consistent with aerofoil profile, part below step is bent downwardly, its crooked radian will guarantee that wing flap 11 puts down in process, in upside, closing plate 12 can not interfered with upper rear flank closing plate 15, its length will guarantee that wing flap 11 puts down closing plate 12 in rear upside completely and still can be overlapped on rear flank closing plate 15, and be unlikely to both, departs from.
Lower rear flank closing plate 3 is segment distance place bending to the inside after closing plate 6 ends in downside, and curved shape guarantees that in downside, closing plate 6 end laps are when closing plate 3 outside face of lower rear flank, and in downside, closing plate 6 outer surface profiles are consistent with aerofoil profile curve.The length of lower rear flank closing plate 3 guarantee its not with downside hinge after joint 7 parts such as grade interfere.
In Fig. 3 A, in upside, in closing plate 12 and downside, closing plate 6 is Varying Thickness Plates, at wing flap 11, receives state, and its outer surface profile is consistent with aerofoil profile curve.After upside hinge, after joint 9 and downside hinge, joint 7 is secured in upside closing plate 6 inner sides in closing plate 12 and downside by modes such as riveted joints respectively, after upside hinge after joint 9 and downside hinge the pinhole of joint 7 have respectively spring hanging hole below.After upside hinge joint 9 to guarantee on wing flap is received state its not with upside in closing plate 12 interfere, after downside hinge joint 7 to guarantee wing flap down state its not with downside in closing plate 6 interfere.Spring hanger 10 and 16 is connected to wing flap 11 inner sides by modes such as riveted joints respectively.
Refer to shown in Fig. 3 B, it is the lateral plan of the present invention in wing flap 11 down states; In upside, the length of closing plate 12 can not be too short, and after guaranteeing that wing flap 11 puts down completely, its end is still overlapped on rear flank closing plate 15 outside faces.In downside, the length of closing plate 6 can not be oversize, guarantee after wing flap 11 puts down completely, and its end can not slide on wing 1 lower surface.Lower rear flank closing plate 3 will guarantee to put 11 times states at wing flap, and it does not produce and interferes with other parts.
In Fig. 3 A, before upside, the front closing plate 4 of closing plate 13 and downside is arranged on respectively the recess of wing flap 11 upper and lower outside faces, and its outer surface profile is consistent with aerofoil profile curve.Upside hinge front connector 14 and downside hinge front connector 5 are connected to before upside the inner side of closing plate 4 before closing plate 13 and downside by modes such as riveted joints respectively.
The upper and lower sealing mechanism of the present invention comprises that respectively rear side closing plate, middle side seal plate, front seal plate, built-in hinge, spring and corresponding attaching parts etc. partly form, simple in structure.Middle closing plate is connected with front closing plate by built-in hinge, and its end lap is at rear closing plate outside face, and spring is equipped with in inner side.Under the effect of spring tension, middle closing plate end and the laminating of rear closing plate intimate can guarantee all the time sealing effectiveness in wing flap motion process.State on wing flap is received, sealing mechanism does not destroy wing aerodynamic configuration; In wing flap down state, between wing flap and wing be connected and transition comparatively level and smooth, greatly alleviated the burbling in At High Angle of Attack situation, less to the adverse effect of aircraft aerodynamic performance.Meanwhile, the present invention can be used for the sealing of the motion aerofoils such as aircraft aileron, yaw rudder.
The foregoing is only preferred embodiment of the present invention, is only illustrative for invention, and nonrestrictive.Those skilled in the art is understood, and in the spirit and scope that limit, can carry out many changes to it in invention claim, revise, and even equivalence, but all will fall within the scope of protection of the present invention.
Claims (10)
1. a spring loaded wing flap sealing mechanism, is characterized in that, it comprises upper and lower two cover sealing mechanisms, and upper and lower sealing mechanism is assembled together by the modes such as riveted joint and wing and wing flap respectively;
Wherein, upper sealing mechanism comprises joint after closing plate before closing plate in rear flank closing plate, upside, upside, upside hinge, the front connector of upside hinge, spring, downside spring hanger;
Lower seal machine comprises joint after closing plate before closing plate in lower rear flank closing plate, downside, downside, downside hinge, the front connector of downside hinge, upside spring hanger.
2. spring loaded wing flap sealing mechanism according to claim 1, is characterized in that, described wing all has step-like depression at upper and lower aerofoil, and installs rear flank closing plate and lower rear flank closing plate at recess;
Described wing flap all has step-like depression at upper and lower aerofoil, and before recess is installed upside closing plate before closing plate and downside;
Described rotary actuator is connected with wing flap with wing respectively by auricle.
3. spring loaded wing flap sealing mechanism according to claim 1 and 2, it is characterized in that, described spring arranged crosswise, the both ends of the spring of described upper sealing mechanism is hung in after upside hinge on joint and downside spring hanger, and the both ends of the spring of described lower seal mechanism is hung in after downside hinge on joint and upside spring hanger.
4. spring loaded wing flap sealing mechanism according to claim 1 and 2, it is characterized in that, described upper rear flank closing plate has step-like depression in surface thereon, the outer surface profile of step upper part is consistent with aerofoil profile, part below step is bent downwardly, its crooked radian will guarantee that wing flap puts down in process, in upside, closing plate can not interfered with upper rear flank closing plate, its length will guarantee that wing flap puts down closing plate in rear upside completely and still can be overlapped on the closing plate of rear flank, and be unlikely to both, departs from.
5. spring loaded wing flap sealing mechanism according to claim 4, it is characterized in that, described lower rear flank closing plate is segment distance place bending to the inside after closing plate end in downside, curved shape guarantees that in downside, closing plate end lap is when the closing plate outside face of lower rear flank, and in downside, closing plate outer surface profile is consistent with aerofoil profile curve.
6. spring loaded wing flap sealing mechanism according to claim 1 and 2, is characterized in that, in described upside, in closing plate and downside, closing plate is Varying Thickness Plates, state on wing flap is received, and its outer surface profile is consistent with aerofoil profile curve.
7. spring loaded wing flap sealing mechanism according to claim 6, it is characterized in that, after upside hinge, after joint and downside hinge, joint is secured to respectively in upside closing plate inner side in closing plate and downside, after upside hinge after joint and downside hinge the pinhole of joint have respectively spring hanging hole below.
8. spring loaded wing flap sealing mechanism according to claim 1 and 2, is characterized in that, after in described upside, closing plate guarantees that wing flap puts down completely, its end is still overlapped on rear flank closing plate outside face; In downside, the length of closing plate guarantees after wing flap puts down completely, and its end can not slide on wing lower surface; Lower rear flank closing plate guarantees that it does not produce and interfere with other parts in wing flap down state.
9. spring loaded wing flap sealing mechanism according to claim 1 and 2, is characterized in that, before described upside, the front closing plate of closing plate and downside is arranged on respectively the recess of the upper and lower outside face of wing flap, and its outer surface profile is consistent with aerofoil profile curve.
10. spring loaded wing flap sealing mechanism according to claim 9, is characterized in that, the front connector of described upside hinge and the front connector of downside hinge are connected to before upside the inner side of closing plate before closing plate and downside by modes such as riveted joints respectively.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410279901.9A CN104044728A (en) | 2014-06-23 | 2014-06-23 | Spring type flap sealing mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410279901.9A CN104044728A (en) | 2014-06-23 | 2014-06-23 | Spring type flap sealing mechanism |
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| CN104044728A true CN104044728A (en) | 2014-09-17 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201410279901.9A Pending CN104044728A (en) | 2014-06-23 | 2014-06-23 | Spring type flap sealing mechanism |
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| CN (1) | CN104044728A (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106081065A (en) * | 2016-08-11 | 2016-11-09 | 中国航空工业集团公司西安飞机设计研究所 | A kind of aileron cabin seals structure |
| CN108725753A (en) * | 2018-05-11 | 2018-11-02 | 西北工业大学 | Curved face type Varying-thickness sealing plate and its design method for aircraft movable wing |
| CN109606641A (en) * | 2018-11-07 | 2019-04-12 | 中国航空工业集团公司西安飞机设计研究所 | A kind of aircraft flexible trailing edge bottom wing surface seal structure |
| KR102005937B1 (en) * | 2019-02-13 | 2019-08-01 | 국방과학연구소 | Structure of flight wing |
| CN110775251A (en) * | 2019-12-12 | 2020-02-11 | 贵州贵航飞机设计研究所 | Method for maintaining moving gap between movable wing surface and fixed wing surface of wing |
| US10619740B2 (en) | 2015-12-21 | 2020-04-14 | Airbus Operations Limited | Seal assembly |
| CN111159943A (en) * | 2019-12-25 | 2020-05-15 | 中国航空工业集团公司西安飞机设计研究所 | Buckling treatment method for movable wing surface sealing structure |
| CN113998094A (en) * | 2021-12-17 | 2022-02-01 | 江西洪都航空工业股份有限公司 | Aircraft pneumatic component clearance block structure |
| CN116480513A (en) * | 2023-05-17 | 2023-07-25 | 中国长江三峡集团有限公司 | Blade and tidal current energy generator |
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| US6247670B1 (en) * | 1999-09-07 | 2001-06-19 | Ramot University Authority For Applied Research And Industrial Development Ltd | Active flaperon assembly |
| CN102209662A (en) * | 2008-11-10 | 2011-10-05 | 空中客车营运有限公司 | Vane having a regulating flap and a gap covering device and an adjusting mechanism for a gap covering device |
| CN102582825A (en) * | 2012-02-14 | 2012-07-18 | 西北工业大学 | Sealing mechanism for plane wing surfaces |
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Patent Citations (3)
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| US6247670B1 (en) * | 1999-09-07 | 2001-06-19 | Ramot University Authority For Applied Research And Industrial Development Ltd | Active flaperon assembly |
| CN102209662A (en) * | 2008-11-10 | 2011-10-05 | 空中客车营运有限公司 | Vane having a regulating flap and a gap covering device and an adjusting mechanism for a gap covering device |
| CN102582825A (en) * | 2012-02-14 | 2012-07-18 | 西北工业大学 | Sealing mechanism for plane wing surfaces |
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10619740B2 (en) | 2015-12-21 | 2020-04-14 | Airbus Operations Limited | Seal assembly |
| CN106081065B (en) * | 2016-08-11 | 2019-02-12 | 中国航空工业集团公司西安飞机设计研究所 | A kind of aileron cabin sealing structure |
| CN106081065A (en) * | 2016-08-11 | 2016-11-09 | 中国航空工业集团公司西安飞机设计研究所 | A kind of aileron cabin seals structure |
| CN108725753A (en) * | 2018-05-11 | 2018-11-02 | 西北工业大学 | Curved face type Varying-thickness sealing plate and its design method for aircraft movable wing |
| CN108725753B (en) * | 2018-05-11 | 2021-06-04 | 西北工业大学 | Design method of curved surface type variable-thickness sealing plate for movable airfoil surface of airplane |
| CN109606641A (en) * | 2018-11-07 | 2019-04-12 | 中国航空工业集团公司西安飞机设计研究所 | A kind of aircraft flexible trailing edge bottom wing surface seal structure |
| KR102005937B1 (en) * | 2019-02-13 | 2019-08-01 | 국방과학연구소 | Structure of flight wing |
| CN110775251A (en) * | 2019-12-12 | 2020-02-11 | 贵州贵航飞机设计研究所 | Method for maintaining moving gap between movable wing surface and fixed wing surface of wing |
| CN110775251B (en) * | 2019-12-12 | 2023-12-08 | 中航贵州飞机有限责任公司 | Method for maintaining movement gap between movable airfoil surface and fixed airfoil surface of wing |
| CN111159943A (en) * | 2019-12-25 | 2020-05-15 | 中国航空工业集团公司西安飞机设计研究所 | Buckling treatment method for movable wing surface sealing structure |
| CN113998094A (en) * | 2021-12-17 | 2022-02-01 | 江西洪都航空工业股份有限公司 | Aircraft pneumatic component clearance block structure |
| CN113998094B (en) * | 2021-12-17 | 2023-07-04 | 江西洪都航空工业股份有限公司 | Gap plugging structure for pneumatic part of airplane |
| CN116480513A (en) * | 2023-05-17 | 2023-07-25 | 中国长江三峡集团有限公司 | Blade and tidal current energy generator |
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Application publication date: 20140917 |