CN209852565U - Aircraft tail, wing panel and aircraft - Google Patents
Aircraft tail, wing panel and aircraft Download PDFInfo
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- CN209852565U CN209852565U CN201920361141.4U CN201920361141U CN209852565U CN 209852565 U CN209852565 U CN 209852565U CN 201920361141 U CN201920361141 U CN 201920361141U CN 209852565 U CN209852565 U CN 209852565U
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Abstract
The utility model provides an aircraft fin, pterygoid lamina and aircraft, this aircraft fin include the vaulting pole of arranging in pairs and the pterygoid lamina of arranging in pairs, wherein: the struts arranged in pairs are connected to the fuselage of the aircraft; the roots of the wings arranged in pairs are respectively hinged with the corresponding support rods, so that the wings arranged in pairs can be switched to realize end butt joint above or below the support plane formed by the support rods arranged in pairs under the action of external force.
Description
Technical Field
The utility model relates to an aircraft technical field, in particular to fin, pterygoid lamina and aircraft of aircraft.
Background
The V-shaped empennage of the existing nose three-point landing gear airplane adopts a fixed design, integrates the functions of a horizontal empennage and a vertical empennage, and achieves the functions of weight reduction, invisibility and the like, but the nose landing gear of the airplane bears larger load when the airplane takes off and lands, and the empennages can not share the load. The existing rear three-point undercarriage airplane has the advantages that the empennage is located above the empennage supporting rod, the undercarriage is located below the airplane body, the weight of the tail part is large due to the existence of the undercarriage and the empennage at the tail part of the airplane body, the structure is complex, the airplane body energy consumption of airplane flying is increased, and the maintenance is carried out respectively, so that the process is complicated.
SUMMERY OF THE UTILITY MODEL
In order to solve the above technical problems, the present invention provides an airplane tail fin, which includes struts arranged in pairs and wing plates arranged in pairs;
wherein: the struts arranged in pairs are connected parallel to one another to the fuselage of the aircraft;
the roots of the wing plates arranged in pairs are respectively hinged with the corresponding stay bars, so that the wing plates arranged in pairs can be switched to realize end butt joint above or below the supporting plane formed by the stay bars arranged in pairs under the action of external force.
Optionally, a landing gear is also included;
the landing gear is hinged to one of the wings, and the landing gear is switchably erected in an upper abutment position of the wing and a lower abutment position of the wing.
Optionally, the tips of the wings arranged in pairs have upper and lower butting position fitting slopes symmetrically arranged in the thickness direction, and the tips of the wings arranged in pairs further have butting grooves having openings at both the upper and lower butting position fitting slopes;
the base of the landing gear is hinged within the docking slot at the end of one of the wings such that the landing gear is switchably extendable from the openings of the upper and lower docking position mating ramps.
Optionally, a rotating shaft arranged along a boundary edge of the upper butt joint position matching inclined plane and the lower butt joint position matching inclined plane is arranged in the butt joint groove of one of the wing plates;
the base of the landing gear is mounted to the shaft.
Optionally, both of the docking slots have side wall surfaces that form a wrap stop for the base of the landing gear when the docking positions are mated to each other.
Optionally, the upper docking position fitting slope and the lower docking position fitting slope of each of the wings are perpendicular to each other, and the two side wall surfaces of each of the docking slots are perpendicular to each other.
Optionally, a locking mechanism is further included;
the locking mechanism is arranged at the tail end of the wing plate and fixes the wing plate oppositely arranged at the butt joint position of the tail end of the wing plate.
Optionally, the locking mechanism comprises:
the locking groove comprises a first locking groove and a second locking groove which are perpendicular to each other and communicated with each other, and the first locking groove and the second locking groove are respectively arranged on the upper butt joint position matching inclined plane and the lower butt joint position matching inclined plane of one of the wing plates;
the locking block comprises a first locking block and a second locking block which are perpendicular to each other and are integrally arranged, and the first locking block and the second locking block are respectively arranged in a sliding chute of the upper butt joint position matching inclined plane and a sliding chute of the lower butt joint position matching inclined plane of the other wing plate;
the first locking block and the second locking block are respectively provided with a bent elbow, and the first locking groove and the second locking groove are respectively provided with an inner bent groove matched with the elbow;
the first locking block and the second locking block both have the freedom degrees of driving the elbow to be arranged in the inner bending groove under the action of external force and driving the elbow to move out of the inner bending groove under the action of external force in the opposite direction.
Optionally, the locking mechanism further comprises:
the unlocking pull rod extends to the sliding groove from the outer side of the wing plate and is fixedly connected with the locking block;
the elastic element is sleeved on the unlocking pull rod, one end of the elastic element abuts against the wall surface of the sliding groove, and the other end of the elastic element abuts against the outer wall surface of the locking block.
Optionally, an elevator is further included; the elevator is hinged to the wing plate.
The embodiment of the utility model provides a pterygoid lamina is still provided, the end of pterygoid lamina has last butt joint position cooperation inclined plane and lower butt joint position cooperation inclined plane that the symmetry set up on the thickness direction, and, the end of pterygoid lamina still has the butt joint groove, the butt joint groove is in go up butt joint position cooperation inclined plane and lower butt joint position cooperation inclined plane and all have the opening.
Optionally, the upper docking position mating slope and the lower docking position mating slope are perpendicular to each other, and two side wall surfaces of the docking slot are perpendicular to each other.
Optionally, the upper docking position matching inclined plane is provided with a first locking groove, and the lower docking position matching inclined plane is provided with a second locking groove; the first locking groove and the second locking groove are perpendicular to each other and communicated with each other.
Optionally, the upper docking position matching inclined plane and the lower docking position matching inclined plane are provided with sliding grooves.
The utility model provides an embodiment still provides an aircraft, and this aircraft includes foretell aircraft fin.
According to the above technical scheme, the utility model discloses an aircraft fin pterygoid lamina can rotate around the vaulting pole, and can realize realizing terminal butt joint in support plane's top or below, at aircraft flight in-process, the terminal butt joint of pterygoid lamina is at last butt joint position, the undercarriage is erect in the terminal top of pterygoid lamina, can not hinder the pterygoid lamina and realize the fin function, when the aircraft slides, the terminal butt joint of pterygoid lamina is butt joint position under, the undercarriage is erect in the terminal below of pterygoid lamina, the undercarriage normally works, share the weight of nose landing gear, the balance and the safety when the nose landing gear of cooperation aircraft guarantees that the aircraft slides, and this fin light in weight, can alleviate the load of aircraft, and simple structure, easily installation and maintenance.
Drawings
The following drawings are only schematic illustrations and explanations of the present invention, and do not limit the scope of the present invention.
Fig. 1 is a schematic view of the docking position on the empennage of the aircraft according to the embodiment of the present invention.
Fig. 2 is a schematic view of the docking position under the tail wing of the aircraft according to the embodiment of the present invention.
Fig. 3 is a schematic view of a wing panel of an airplane tail wing according to an embodiment of the present invention.
Fig. 4 is a schematic view of a portion of the structure of fig. 3.
Fig. 5 is a side view of an aircraft tail according to an embodiment of the invention.
Fig. 6 is a partial schematic view of a wing panel of an aircraft tail according to an embodiment of the present invention.
Fig. 7 is a schematic view of a locking mechanism according to an embodiment of the present invention.
Fig. 8 is a cross-sectional view of a locking mechanism according to an embodiment of the present invention.
Wherein: 1, a support rod;
2 wing plates;
21, matching an inclined plane at the butt joint position;
22 lower butt joint position matching inclined plane;
23 butt groove, 231 side wall surface;
24 a sleeve;
3, a landing gear;
31 a base;
4, a rotating shaft;
6, a locking mechanism;
61 locking grooves;
61a first locking groove, 61b second locking groove;
611, an inward-bending groove;
62a locking block;
62a first latch block, 62b a second latch block;
621 an elbow;
63, a chute;
unlocking the pull rod 64;
65 an elastic element;
5 elevator.
Detailed Description
In order to clearly understand the technical features, objects, and effects of the present invention, embodiments of the present invention will be described with reference to the accompanying drawings, in which like reference numerals refer to like parts in the drawings.
"exemplary" means "serving as an example, instance, or illustration" herein, and any illustration, embodiment, or steps described as "exemplary" herein should not be construed as a preferred or advantageous alternative.
For the sake of simplicity, the drawings only schematically show the parts relevant to the present invention, and do not represent the actual structure as a product. In addition, in order to make the drawings concise and understandable, components having the same structure or function in some of the drawings are only schematically illustrated or only labeled.
In this document, "upper", "lower", "front", "rear", "left", "right", and the like are used only to indicate relative positional relationships between relevant portions, and do not limit absolute positions of the relevant portions.
In this document, "first", "second", and the like are used only for distinguishing one from another, and do not indicate the degree and order of importance, the premise that each other exists, and the like.
In this context, "equal", "same", etc. are not strictly mathematical and/or geometric limitations, but also include tolerances as would be understood by a person skilled in the art and allowed for manufacturing or use, etc. Unless otherwise indicated, numerical ranges herein include not only the entire range within its two endpoints, but also several sub-ranges subsumed therein.
In order to solve the technical problems of heavy weight, complex structure and incapability of sharing the load of the nose landing gear in the prior art, as shown in fig. 1-5, an embodiment of the present invention provides an aircraft tail wing, which comprises support rods 1 arranged in pairs, wing plates 2 arranged in pairs and a frame 3 which falls together.
The struts 1 arranged in pairs are connected parallel to one another to the fuselage of the aircraft, in particular the struts 1 may be fixed to the fuselage.
The roots of the pair of wing plates 2 are hinged with the corresponding stay bars 1 respectively, so that the pair of wing plates 2 can be switched to realize end butt joint above or below a supporting plane formed by the pair of stay bars 1 under the action of external force, specifically, the root of each wing plate 2 is hinged with one stay bar 1, the wing plates 2 can rotate around the stay bars 1, the rotating direction of the wing plates 2 can be a direction far away from the other stay bar 1 arranged in pair, namely the outer side direction of the stay bars 1, and the angle which the wing plates 2 can rotate can be 270 degrees, the ends of the two wing plates 2 are butted above the supporting plane, namely an upper butt joint position, and the ends of the two wing plates 2 are butted below the supporting plane, namely a lower butt joint position.
The tail ends of the wing plates 2 arranged in pairs are provided with an upper butt joint position matching inclined surface 21 and a lower butt joint position matching inclined surface 22 which are symmetrically arranged in the thickness direction, the upper butt joint position matching inclined surface 21 and the lower butt joint position matching inclined surface 22 are perpendicular to each other, and an included angle between the upper butt joint position matching inclined surface 21 and the lower butt joint position matching inclined surface 22 and the surface of the wing plate 2 is 45 degrees, so that the included angle is 90 degrees after the two wing plates 2 are butted at the upper butt joint position and the lower butt joint position, meanwhile, the two upper butt joint position matching inclined surfaces 21 are butted at the upper butt joint position, and the two lower butt joint position matching inclined surfaces 22 are butted at the; the ends of the wing plates 2 arranged in pairs are also provided with butt joint grooves 23, the butt joint grooves 23 are provided with openings at the upper butt joint position matching inclined surfaces 21 and the lower butt joint position matching inclined surfaces 22, specifically, the butt joint grooves 23 are arranged at the junctions of the upper butt joint position matching inclined surfaces 21 and the lower butt joint position matching inclined surfaces 22, and the butt joint grooves 23 are provided with openings at the upper butt joint position matching inclined surfaces 21 and the lower butt joint position matching inclined surfaces 22; the base 31 of the landing gear 3 is hinged in a docking slot 23 in the end of one of the wings 2, in which docking slot 23 the base 31 of the landing gear 3 can rotate, and the landing gear 3 can be switchably extended from the opening of the upper docking position mating ramp 21 and the lower docking position mating ramp 22, i.e. the docking slot 23 enables the mounting of the landing gear 3, in the upper docking position the landing gear 3 is extended from the opening of the lower docking position mating ramp 22, in the lower docking position the landing gear 3 is extended from the opening of the upper docking position mating ramp 21, i.e. in the upper docking position the landing gear 3 is erected above the end of the wing 2, and in the lower docking position the landing gear 3 is erected below the end of the wing 2.
During the use, pterygoid lamina 2 can rotate around vaulting pole 1, and undercarriage 3 is installed in the end of pterygoid lamina 2 to two pterygoid lamina 2 ends can be stabilized at last butt joint position and butt joint position down, at last butt joint position, and undercarriage 3 is located 2 terminal tops of pterygoid lamina, and undercarriage 3 does not influence pterygoid lamina 2 and realizes the fin function, and at butt joint position down, undercarriage 3 is located 2 terminal belows of pterygoid lamina, and undercarriage 3 shares the load of nose landing gear, guarantees the gliding balance of aircraft.
In an alternative example, a sleeve 24 is fixed at the root of the wing plate 2, the sleeve 24 is sleeved on the stay bar 1, the sleeve 24 can rotate around the stay bar 1, and under the action of an external force, the wing plate 2 and the sleeve 24 rotate around the stay bar 1 at the same time, it can be understood that limiting elements can be arranged at two ends of the sleeve 24, the limiting elements limit the position of the sleeve 24 on the stay bar 1 and prevent the sleeve 24 from sliding back and forth on the stay bar 1, and the limiting elements can be positioning pins or other existing limiting elements as long as the position of the limiting sleeve 24 can be achieved.
The utility model discloses an aircraft fin pterygoid lamina 2 can rotate around vaulting pole 1, and can realize realizing terminal butt joint in support plane's top or below, in aircraft flight in-process, pterygoid lamina 2's terminal butt joint is at last butt joint position, undercarriage 3 erects in pterygoid lamina 2's terminal top, can not hinder pterygoid lamina 2 and realize the fin function, when the aircraft slides, pterygoid lamina 2's terminal butt joint is in butt joint position down, undercarriage 3 erects in pterygoid lamina 2's terminal below, undercarriage 3 normally works, share the weight of nose landing gear, balance and safety when the nose landing gear of cooperation aircraft guaranteed that the aircraft slides, and this fin light in weight, can alleviate the load of aircraft, and simple structure, easily installation and maintenance.
In one example, the abutment groove 23 of one of the wings 2 has a pivot 4 provided along the boundary edge of the upper abutment position engagement ramp 21 and the lower abutment position engagement ramp 22, the base 31 of the undercarriage 3 is mounted on the pivot 4, the pivot 4 extends along the hinge edge, the base 31 of the undercarriage 3 is hinged to the pivot 4, and the base 31 is rotatable about the pivot 4 to achieve an upper abutment position in which the undercarriage 3 protrudes from the opening of the lower abutment position engagement ramp 22, and a lower abutment position in which the undercarriage 3 protrudes from the opening of the upper abutment position engagement ramp 21.
Further, both of the abutment slots 23 have side wall surfaces 231 which, when mutually engaged in the abutment position, form a wrapping limit for the base 31 of the landing gear 3, it being understood that, the upper mating inclined surface 21 and the lower mating inclined surface 22 are both provided with side wall surfaces 231 of the mating groove 23, when the upper abutment position fitting inclined surface 21 of one wing plate 2 is abutted with the upper abutment position fitting inclined surface 21 of the other wing plate 2, the two docking slots 23 are engaged with each other, the side wall surfaces 231 of the two docking slots 23 wrap the base 31 to limit the rotation angle of the landing gear 3, namely, the landing gear 3 is fixed in the upper butt joint position, and similarly, in the lower butt joint position, the lower butt joint position matching inclined surface 22 of one wing plate 2 is butted with the lower butt joint position matching inclined surface 22 of the other wing plate 2, and the two butt joint grooves 23 are spliced with each other to limit the rotation of the landing gear 3.
It will be appreciated that the upper and lower abutment position mating ramps 21, 22 of each wing 2 are perpendicular to each other to enable abutment of the wings 2 in the upper and lower abutment positions, and the two side wall surfaces 231 of each abutment slot 23 are perpendicular to each other, the abutment slots 23 limit rotation of the landing gear 3 when engaged, and the landing gear 3 rotates 90 ° when switched between the upper and lower abutment positions, so that the side wall surfaces 231 are perpendicular to each other to provide space for rotation of the landing gear 3, while limiting rotation of the landing gear 3 in both the upper and lower abutment positions.
In one example, as shown in fig. 6-8, the aircraft tail further includes a locking mechanism 6; this locking mechanical system 6 sets up in pterygoid lamina 2's the end and at pterygoid lamina 2 of the fixed relative pterygoid lamina 2 that sets up in the butt joint position of pterygoid lamina 2, and after two pterygoid lamina 2 docks, the position of two pterygoid lamina 2 is not firm in the aircraft driving process, meets the condition of jolting two pterygoid lamina 2 and probably takes place the dislocation even butt joint form and is destroyed, and locking mechanical system 6 locks two pterygoid lamina 2 at this time, and the form of butt joint is kept to fixed pterygoid lamina 2 position in the assurance use.
Specifically, the locking mechanism 6 includes a locking groove 61 provided at a distal end of one of the wings 2 and a locking block 62 provided at a distal end of the other wing 2.
The locking groove 61 comprises a first locking groove 61a and a second locking groove 61b which are perpendicular to each other and communicated with each other, wherein the first locking groove 61a and the second locking groove 61b are respectively arranged on the upper butt joint position matching inclined surface 21 and the lower butt joint position matching inclined surface 22 of one of the wing plates 2;
the locking block 62 includes a first locking block 62a and a second locking block 62b which are perpendicular to each other and are integrally provided, the first locking block 62a and the second locking block 62b are respectively installed on a sliding groove 63 of the upper butt position matching inclined surface 21 and a sliding groove 63 of the lower butt position matching inclined surface 22 of the other wing panel 2, and the sliding groove 63 is provided with a sliding space for allowing the locking block 62 to slide back and forth;
two locking blocks 62 are mounted on the same wing plate 2, two locking grooves 61 are opened on the other wing plate 2, wherein, the first locking block 62a and the second locking block 62b both have a bent elbow 621, the first locking groove 61a and the second locking groove 61b both have an inner bending groove 611 adapted to the elbow 621, and the first locking block 62a and the second locking block 62b both have a freedom degree of driving the elbow 621 to be mounted in the inner bending groove 611 under the action of an external force and driving the elbow 621 to move out from the inner bending groove 611 under the action of an external force in opposite directions, namely, when the locking block 62 receives the external force, the locking block 62 drives the elbow 621 to be extruded in the inner bending groove 611, when the elbow 621 is located in the inner bending groove 611, the elbow 621 cannot move freely, the two wing plates 2 are fixed with each other, when the locking block 62 receives the external force in opposite directions, the locking block 62 drives the elbow 621 to move in opposite directions, the elbow 621 comes out of the inward curved groove 611, and the locking between the two flanges 2 is released.
Further, the locking mechanism 6 further includes an unlocking lever 64 and an elastic member 65.
The unlocking pull rod 64 extends from the outer side of the wing plate 2 to the sliding groove 63 and is fixedly connected with the locking block 62, the unlocking pull rod 64 can drive the locking block 62 to move, and the locking state and the unlocking state of the locking block 62 in the structure 6 are switched through the unlocking pull rod 62; the elastic element 65 is sleeved on the unlocking pull rod 64, one end of the elastic element 65 abuts against the wall surface of the sliding groove 63, the other end of the elastic element 65 abuts against the outer wall surface of the locking block 62, the elastic element 65 has elastic force, in a normal state, the elastic element 65 is compressed, the elbow 621 of the locking block 62 is locked in the inner curved groove 611, the unlocking pull rod 64 is pulled, the elastic element 65 is further compressed, at the moment, the elbow 621 is separated from the inner curved groove 611, the locking state of the two wing plates 2 is released, and the wing plates 2 can rotate under the action of external force.
Alternatively, the end of the unlocking lever 64 may be provided with a handle or a pull ring for easy operation, where the elastic member 65 may be a spring in a compressed state.
The aircraft tail further comprises an elevator 5, which elevator 5 is hinged to the wing plate 2 and which elevator 5 is swingable relative to the wing plate 2.
The embodiment of the utility model provides an aircraft is still provided, and this aircraft includes foretell aircraft fin, and when using, the pterygoid lamina 2 flexible realization fin of aircraft fin and the 3 two functions of installation undercarriage save installation space to can alleviate the weight of whole aircraft.
It should be understood that although the present description has been described in terms of various embodiments, not every embodiment includes only a single embodiment, and such description is for clarity purposes only, and those skilled in the art will recognize that the embodiments described herein can be combined as a whole to form other embodiments as would be understood by those skilled in the art.
The above list of details is only for the feasible embodiments of the present invention and is not intended to limit the scope of the present invention, and all equivalent embodiments or modifications, such as combinations, divisions or repetitions of the features, which do not depart from the technical spirit of the present invention, should be included in the scope of the present invention.
Claims (15)
1. An aircraft tail, characterized in that it comprises struts (1) arranged in pairs and wings (2) arranged in pairs;
wherein: the struts (1) arranged in pairs are connected to the fuselage of an aircraft;
the roots of the wing plates (2) arranged in pairs are respectively hinged with the corresponding stay bars (1), so that the wing plates (2) arranged in pairs can be switched to realize end butt joint above or below a supporting plane formed by the stay bars (1) arranged in pairs under the action of external force.
2. The aircraft tail according to claim 1, characterized in that it further comprises a landing gear (3);
the landing gear (3) is hinged to one of the wings (2), and the landing gear (3) is switchably erected in an upper docking position of the wings (2) and a lower docking position of the wings (2).
3. The aircraft tail according to claim 2 characterized in that the tips of the wings (2) arranged in pairs have upper and lower docking position engagement slopes (21, 22) symmetrically arranged in the thickness direction, and the tips of the wings (2) arranged in pairs further have docking slots (23), the docking slots (23) having openings at both the upper and lower docking position engagement slopes (21, 22);
the base (31) of the landing gear (3) is hinged in the docking slot (23) at the end of one of the wings (2) so that the landing gear (3) can be switchably extended from the openings of the upper docking position mating ramp (21) and the lower docking position mating ramp (22).
4. The aircraft tail according to claim 3 characterized in that the butt-joint groove (23) of one of the wings (2) has a pivot (4) provided therein along the boundary edge of the upper butt-joint position mating slope (21) and the lower butt-joint position mating slope (22);
the base (31) of the undercarriage (3) is mounted to the shaft (4).
5. The aircraft tail according to claim 4 characterized in that both of the docking slots (23) have a side wall surface (231) which forms a wrap limit for the base (31) of the landing gear (3) when they are spliced to each other in the docked position.
6. The aircraft tail according to claim 5 characterized in that the upper docking position mating ramp (21) and the lower docking position mating ramp (22) of each wing (2) are perpendicular to each other and the two side wall surfaces (231) of each docking slot (23) are perpendicular to each other.
7. An aircraft tail according to claim 3 further comprising a locking mechanism (6);
the locking mechanism (6) is arranged at the tail end of the wing plate (2) and fixes the wing plate (2) which is oppositely arranged at the butt joint position of the tail end of the wing plate (2).
8. The aircraft tail according to claim 7 characterized in that the locking mechanism (6) comprises:
the locking groove (61) comprises a first locking groove (61a) and a second locking groove (61b) which are perpendicular to each other and communicated with each other, and the first locking groove (61a) and the second locking groove (61b) are respectively arranged on the upper butt joint position matching inclined surface (21) and the lower butt joint position matching inclined surface (22) of one of the wing plates (2);
the locking block (62) comprises a first locking block (62a) and a second locking block (62b) which are perpendicular to each other and are integrally arranged, and the first locking block (62a) and the second locking block (62b) are respectively arranged on a sliding groove (63) of the upper butt joint position matching inclined surface (21) and a sliding groove (63) of the lower butt joint position matching inclined surface (22) of the other wing plate (2);
the first locking block (62a) and the second locking block (62b) are respectively provided with a bent elbow (621), and the first locking groove (61a) and the second locking groove (61b) are respectively provided with an inward-bent groove (611) matched with the elbow (621);
the first locking block (62a) and the second locking block (62b) have the freedom degree of driving the elbow (621) to be arranged in the inner bending groove (611) under the action of external force and driving the elbow (621) to move out of the inner bending groove (611) under the action of external force in the opposite direction.
9. The aircraft tail according to claim 8 characterized in that the locking mechanism (6) further comprises:
the unlocking pull rod (64) extends from the outer side of the wing plate (2) to the sliding groove (63) and is fixedly connected with the locking block (62);
the elastic element (65) is sleeved on the unlocking pull rod (64), one end of the elastic element (65) abuts against the wall surface of the sliding groove (63), and the other end of the elastic element (65) abuts against the outer wall surface of the locking block (62).
10. The aircraft tail according to claim 1 further comprising an elevator (5); the elevator (5) is hinged to the wing plate (2).
11. A wing plate (2), characterized in that a tip of the wing plate (2) has an upper butt position fitting slope (21) and a lower butt position fitting slope (22) which are symmetrically provided in a thickness direction, and the tip of the wing plate (2) further has a butt groove (23), the butt groove (23) having an opening in both the upper butt position fitting slope (21) and the lower butt position fitting slope (22).
12. The wing (2) according to claim 11, characterized in that the upper abutment position mating ramp (21) and the lower abutment position mating ramp (22) are perpendicular to each other and the two side wall surfaces (231) of the abutment groove (23) are perpendicular to each other.
13. The wing (2) according to claim 11, characterized in that said upper abutment position cooperating ramp (21) presents a first locking groove (61a) and said lower abutment position cooperating ramp (22) presents a second locking groove (61 b); the first locking groove (61a) and the second locking groove (61b) are perpendicular to each other and communicate with each other.
14. The strake (2) according to claim 11, characterized in that the upper docking position mating ramp (21) and the lower docking position mating ramp (22) are slotted with sliding slots (63).
15. An aircraft comprising an aircraft tail as claimed in any one of claims 1 to 10.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920361141.4U CN209852565U (en) | 2019-03-20 | 2019-03-20 | Aircraft tail, wing panel and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920361141.4U CN209852565U (en) | 2019-03-20 | 2019-03-20 | Aircraft tail, wing panel and aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209852565U true CN209852565U (en) | 2019-12-27 |
Family
ID=68934366
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920361141.4U Active CN209852565U (en) | 2019-03-20 | 2019-03-20 | Aircraft tail, wing panel and aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN209852565U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115817791A (en) * | 2023-01-09 | 2023-03-21 | 北京启时智航科技有限公司 | Horizontal tail actuating mechanism and wing structure |
-
2019
- 2019-03-20 CN CN201920361141.4U patent/CN209852565U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115817791A (en) * | 2023-01-09 | 2023-03-21 | 北京启时智航科技有限公司 | Horizontal tail actuating mechanism and wing structure |
| CN115817791B (en) * | 2023-01-09 | 2023-04-14 | 北京启时智航科技有限公司 | Horizontal tail actuating mechanism and wing structure |
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