CN110539874B - Wing mounting structure of tilt rotor aircraft - Google Patents
Wing mounting structure of tilt rotor aircraft Download PDFInfo
- Publication number
- CN110539874B CN110539874B CN201910889177.4A CN201910889177A CN110539874B CN 110539874 B CN110539874 B CN 110539874B CN 201910889177 A CN201910889177 A CN 201910889177A CN 110539874 B CN110539874 B CN 110539874B
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- support plate
- ribs
- hole
- edge
- wing
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/26—Attaching the wing or tail units or stabilising surfaces
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D1/00—Dropping, ejecting, releasing, or receiving articles, liquids, or the like, in flight
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Abstract
This application belongs to tiltrotor aircraft's wing carry structural design field, concretely relates to tiltrotor aircraft's wing carry structure, include: the front support plate is connected to a rear beam of the wing and is provided with a front mounting hole; the first middle support plate is connected to the rear beam and provided with a first middle hole; one end of the hollow mounting shaft sequentially penetrates through the front mounting hole and the first middle hole, and the other end of the hollow mounting shaft is used for being connected with the nacelle; the transmission shaft extending out of the nacelle penetrates through the hollow mounting shaft.
Description
Technical Field
This application belongs to tiltrotor aircraft's wing carry structural design field, concretely relates to tiltrotor aircraft's wing carry structure.
Background
Tilt rotor aircraft's wingtip carry nacelle makes the wingtip atress concentrate, bears great load, influences tilt rotor aircraft's flight performance, has restricted tilt rotor aircraft flight performance's improvement, in addition, the transmission shaft that stretches out in the nacelle appears the card easily at rotatory in-process and dies the scheduling problem.
The present application is made in view of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
It is an object of the present application to provide a wing mounting structure for a tiltrotor aircraft that overcomes or alleviates at least one of the disadvantages of the prior art.
The technical scheme of the application is as follows:
a wing mounting structure for a tiltrotor aircraft, comprising:
the front support plate is connected to a rear beam of the wing and is provided with a front mounting hole;
the first middle support plate is connected to the rear beam and provided with a first middle hole;
one end of the hollow mounting shaft sequentially penetrates through the front mounting hole and the first middle hole, and the other end of the hollow mounting shaft is used for being connected with the nacelle; the transmission shaft extending out of the nacelle penetrates through the hollow mounting shaft.
According to at least one embodiment of the present application, further comprising:
the front edge strip is arranged around the edge of the front support plate and is used for being connected to the rear beam;
a first bead disposed around an edge of the first intermediate support plate for connection to the back beam.
According to at least one embodiment of the present application, both sides of the front support plate are provided with a plurality of front ribs, wherein,
a plurality of front ribs are arranged on one side of the front support plate, wherein part of the front ribs is annularly arranged around the front mounting hole, one end of the rest part extends to the front edge strip, and the other end of the rest part extends to the front ribs arranged around the front mounting hole on the side of the front support plate;
and the other end of the front support plate extends to the front rib arranged around the front mounting hole at the side of the front support plate.
According to at least one embodiment of the application, one side of the first middle support plate is provided with a plurality of first ribs, parts of the first ribs are annularly arranged around the first middle hole, one end of the rest parts extends to the first flange, and the other end of the rest parts extends to the first ribs arranged around the first middle hole.
According to at least one embodiment of the present application, a first suspension arm is connected at one end to the first intermediate support plate and at the other end to the moving airfoil;
a plurality of second intermediate support plates for connection to the back beam, each second intermediate support plate having a second intermediate aperture therein; the transmission shaft penetrating through the hollow mounting shaft sequentially penetrates through the second middle holes of the second middle support plates;
and one end of each second hanging arm is correspondingly connected with one second middle support plate, and the other end of each second hanging arm is used for being connected with the moving wing surface.
According to at least one embodiment of the present application, the rear frame further comprises a plurality of second flanges, each second flange being disposed around an edge of a corresponding second intermediate support plate for connection to the rear frame.
According to at least one embodiment of the application, one side of each second middle support plate is provided with a plurality of second ribs, a part of the plurality of second ribs is annularly arranged around a second middle hole of the second middle support plate, one end of the rest part extends to a second edge strip arranged around the edge of the second middle support plate, and the other end of the rest part extends to a second rib arranged around a second mounting hole on the second middle support plate.
According to at least one embodiment of the present application, further comprising:
the rear support plate is connected to the rear beam and provided with a rear mounting hole; the transmission shafts sequentially penetrating through the second middle holes of the second middle support plates penetrate through the rear mounting holes;
the skin is provided with a first end, a second end opposite to the first end, a first edge extending between the first end and the second end, a second edge opposite to the first edge, a first through hole and a plurality of second through holes; the first edge and the second edge are used for being connected with the rear beam, the inner wall of the first end is connected with the edge of the front supporting plate, and the inner wall of the second end is connected with the edge of the rear supporting plate, so that a closed chamber is formed; the first mounting arm extends out of the first via hole; each second hanging arm correspondingly extends out of one second through hole.
According to at least one embodiment of the present application, the rear support plate further comprises a rear edge strip disposed around an edge of the rear support plate for connecting to the rear beam;
one side of the rear support plate is provided with a plurality of rear ribs, the parts of the rear ribs are annularly arranged around the rear mounting hole, one end of the rest parts extends to the rear edge strip, and the other end of the rest parts extends to the rear ribs arranged around the rear mounting hole.
According to at least one embodiment of the application, the drive shaft is clearance fitted with the first intermediate bore and each of the second intermediate bores.
Drawings
Fig. 1 is a schematic structural diagram of a wing mounting structure of a tiltrotor aircraft according to an embodiment of the present disclosure;
fig. 2 is an external view of a wing mounting structure of a tiltrotor aircraft according to an embodiment of the present application;
FIG. 3 is a schematic view of an angle of a front plate according to an embodiment of the present disclosure;
FIG. 4 is a schematic structural view of another angle of the front panel provided by the embodiment of the present application;
FIG. 5 is a schematic structural view of a first intermediate support plate provided by an embodiment of the present application;
FIG. 6 is a schematic structural diagram of a hollow mounting shaft provided in an embodiment of the present application;
FIG. 7 is a schematic view of an angle configuration of a rear support plate according to an embodiment of the present disclosure;
FIG. 8 is a schematic view of another angle configuration of a rear support plate according to an embodiment of the present disclosure;
wherein:
1-a front support plate; 2-a rear beam; 3-a first intermediate support plate; 4-hollow hanging shaft; 5-a nacelle; 6-a transmission shaft; 7-leading edge strip; 8-a first bead; 9-front ribs; 10-a first rib; 11-a first loading arm; 12-a second intermediate support plate; 13-a second loading arm; 14-a rear support plate; 15-covering; 16-a trailing edge strip; 17-rear ribs; 18-moving airfoil.
Detailed Description
The present application will be described in further detail with reference to the drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the relevant application and are not limiting of the application. It should be noted that, for convenience of description, only the portions related to the present application are shown in the drawings.
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present application will be described in detail below with reference to the embodiments with reference to the attached drawings.
It should be noted that in the description of the present application, the terms of direction or positional relationship indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. are based on the directions or positional relationships shown in the drawings, which are only for convenience of description, and do not indicate or imply that the device or element must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present application. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
Furthermore, it should be noted that, in the description of the present application, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as being fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present application can be understood by those skilled in the art as the case may be.
The present application is described in further detail below with reference to fig. 1 to 8.
A wing mounting structure for a tiltrotor aircraft, comprising:
the front support plate 1 is connected to a rear beam 2 of the wing and is provided with a front mounting hole;
a first intermediate support 3, for connection to the back beam 2, having a first intermediate hole thereon;
one end of the hollow mounting shaft 4 sequentially penetrates through the front mounting hole and the first middle hole, and the other end of the hollow mounting shaft is connected with the nacelle 5; a transmission shaft 6 extending from the nacelle 5 is provided through the inside of the hollow mounting shaft 4.
As will be readily understood by those skilled in the art of the wing mounting structure of the tilt rotor aircraft disclosed in the above embodiments, the hollow mounting shaft 4 supported by the front support plate 1 and the first middle support plate 3 connected to the wing back spar 2 is connected to the nacelle 5, so as to disperse the weight of the nacelle 5 to the wing back spar 2, and bear a corresponding load by the wing back edge, thereby avoiding the problem of concentrated stress on the wing tip, and the transmission shaft 6 extending from the nacelle 5 penetrates through the hollow mounting shaft 4, and the transmission shaft 6 is in clearance fit with the inside of the hollow mounting shaft 4, so that the transmission shaft 6 passes through the transmission shaft 6, no friction is generated between the transmission shaft 6 and the hollow mounting shaft 4, and the transmission shaft 6 is prevented from being jammed and being deformed.
In some optional embodiments, further comprising:
a front edge strip 7 disposed around an edge of the front support plate 1 for connection to the rear beam 2;
a first flange 8 is provided around the edge of the first intermediate support 3 for connection to the back rest 2.
In alternative embodiments, both sides of the front panel 1 are provided with a plurality of front ribs 9, wherein,
a plurality of front ribs 9 are arranged on one side of the front support plate 1, wherein part of the front ribs is annularly arranged around the front mounting hole, the rest parts are longitudinally and transversely arranged, one end of each front rib extends to the front edge strip 7, and the other end of each front rib 9 extends to the side of the front support plate 1 and is arranged around the front mounting hole; the front ribs 9 on the side of the front support plate 1 are integrally in a hollow cross shape, so that the load of the front support plate 1 is effectively transmitted and dispersed, and effective support is provided for the front support plate 1;
a plurality of front ribs 9 are arranged on the other side of the front support plate 1, wherein part of the front ribs are arranged in a semi-annular shape and surround the front mounting hole, the rest parts are arranged in a longitudinal and transverse mode, one end of each front rib extends to the front edge strip 7, and the other end of each front rib extends to the front rib 9 arranged on the side, surrounding the front mounting hole, of the front support plate 1; the front ribs 9 on the side of the front support plate 1 are in a half-hollow cross shape integrally, so that the load of the front support plate 1 is effectively transmitted and dispersed, and the support is provided for the front support plate 1.
As will be readily understood by those skilled in the art regarding the wing mounting structure of the tilt rotor aircraft disclosed in the above embodiments, the front support plate 1 is stiffened on both sides, the front rib 9 on one side of the front support plate is overall in a shape of "hollow cross", and the front rib 9 on the other side of the front support plate is overall in a shape of half "hollow cross", so that the support effect on the front support plate 1 and the overall mass are comprehensively balanced.
In some alternative embodiments, a plurality of first ribs 10 are provided on one side of the first middle support plate 3, a part of the plurality of first ribs 10 is annularly arranged around the first middle hole, and the other part of the plurality of first ribs 10 extends to the first rim 8 at one end and extends to the first ribs 10 arranged around the first middle hole at the other end.
In some alternative embodiments, the first suspension arm 11 is connected at one end to the first intermediate plate 3 and at the other end to the moving airfoil 18;
a plurality of second intermediate brackets 12 for connecting to the back beam 2, each second intermediate bracket 12 having a second intermediate hole therein; the transmission shaft 6 penetrating through the hollow mounting shaft 4 sequentially penetrates through the second middle holes of the second middle support plates 12;
and a plurality of second hanging arms 13, wherein one end of each second hanging arm 13 is correspondingly connected with one second middle support plate 12, and the other end of each second hanging arm 13 is used for being connected with the movable wing surface 18.
In some optional embodiments, a plurality of second flanges are further included, each second flange being disposed around an edge of a corresponding one of the second intermediate brackets 12 for attachment to the back beam 2.
In some alternative embodiments, a plurality of second ribs are disposed on one side of each second intermediate support plate 12, and a portion of the plurality of second ribs is disposed annularly around the second intermediate hole of the second intermediate support plate 12, and the remaining portion extends at one end to a second rim disposed around an edge of the second intermediate support plate 12 and at the other end to a second rib disposed around a second mounting hole in the second intermediate support plate 12.
In some optional embodiments, further comprising:
a rear stay 14 for connecting to the rear beam 2, having a rear mounting hole thereon; the transmission shafts 6 sequentially penetrating through the second middle holes of the second middle support plates 12 penetrate through the rear mounting holes;
a skin 15 having a first end, a second end opposite the first end, a first side extending between the first end and the second end, a second side opposite the first side, and having a first via, a plurality of second vias thereon; the first edge and the second edge are used for being connected with the back beam 2, the inner wall of the first end is connected with the edge of the front supporting plate 1, and the inner wall of the second end is connected with the edge of the back supporting plate 14, so that a closed chamber is formed; the first hanging arm 11 extends out of the first via hole; each second suspension arm 13 extends from a corresponding one of the second vias.
In some alternative embodiments, a rear edge strip 16 is included, disposed around an edge of the rear brace 14, for connecting to the rear beam 2;
one side of the rear support plate 14 is provided with a plurality of rear ribs 17, the parts of the plurality of rear ribs 17 are annularly arranged around the rear mounting hole, one end of the rest parts extends to the rear edge strip 16, and the other end of the rest parts extends to the rear ribs 17 arranged around the rear mounting hole.
In some alternative embodiments, the transmission shaft 6 is in clearance fit with the first middle hole and each second middle hole to prevent the first middle hole and the second middle hole from clamping the transmission shaft 6, and prevent the first middle hole and the second middle hole from generating uneven force on the transmission shaft 6, so that the transmission shaft 6 is deformed.
So far, the technical solutions of the present application have been described in connection with the preferred embodiments shown in the drawings, but it is easily understood by those skilled in the art that the scope of protection of the present application is obviously not limited to these specific embodiments. Equivalent changes or substitutions of related technical features can be made by those skilled in the art without departing from the principle of the present application, and the technical scheme after the changes or substitutions will fall into the protection scope of the present application.
Claims (9)
1. The utility model provides a tilt rotor aircraft's wing carries structure which characterized in that includes:
the aircraft wing mounting structure comprises a front support plate (1) which is connected to a rear beam (2) of the wing and is provided with a front mounting hole;
a first intermediate support plate (3) for connection to the rear beam (2) and having a first intermediate hole therein;
one end of the hollow mounting shaft (4) sequentially penetrates through the front mounting hole and the first middle hole, and the other end of the hollow mounting shaft is used for being connected with the nacelle (5); a transmission shaft (6) extending out of the nacelle (5) penetrates through the hollow mounting shaft (4);
a first loading arm (11) having one end connected to the first intermediate support plate (3) and the other end connected to a moving airfoil (18);
a plurality of second intermediate brackets (12) for connecting to the rear beam (2), each of the second intermediate brackets (12) having a second intermediate hole therein; a transmission shaft (6) penetrating through the hollow mounting shaft (4) sequentially penetrates through second middle holes of the second middle support plates (12) to be arranged;
and a plurality of second hanging arms (13), wherein one end of each second hanging arm (13) is correspondingly connected with one second middle support plate (12), and the other end of each second hanging arm is used for being connected with the moving wing surface (18).
2. Wing mounting structure according to claim 1,
further comprising:
a front edge strip (7) arranged around an edge of the front support plate (1) for connection to the rear beam (2);
a first bead (8) disposed around an edge of the first intermediate support plate (3) for connection to the rear beam (2).
3. The wing mounting mechanism of claim 2,
a plurality of front ribs (9) are arranged on both sides of the front support plate (1), wherein,
a plurality of front ribs (9) are arranged on one side of the front support plate (1), wherein part of the front ribs are annularly arranged around the front mounting hole, one end of the rest part of the front ribs extends to the front edge strip (7), and the other end of the front ribs extends to the front ribs (9) arranged around the front mounting hole on the side of the front support plate (1);
and a plurality of front ribs (9) are arranged on the other side of the front support plate (1), wherein part of the front ribs is arranged around the front mounting hole in a semi-annular manner, one end of the rest part of the front ribs extends to the front edge strip (7), and the other end of the front rib extends to the front ribs (9) arranged around the front mounting hole on the side of the front support plate (1).
4. The wing mounting mechanism of claim 3,
one side of the first middle support plate (3) is provided with a plurality of first ribs (10), the part of each first rib (10) is annularly arranged around the first middle hole, one end of the rest part extends to the first edge strip (8), and the other end extends to the first rib (10) arranged around the first middle hole.
5. The wing mounting mechanism of claim 1,
the rear support plate structure further comprises a plurality of second edge strips, wherein each second edge strip correspondingly surrounds the edge of one second middle support plate (12) and is connected to the rear beam (2).
6. The wing mounting mechanism of claim 5,
one side of each second middle support plate (12) is provided with a plurality of second ribs, the second ribs are arranged in a mode that parts of the second ribs are annularly arranged around a second middle hole of the second middle support plate (12), one end of the rest parts extends to a second edge strip arranged around the edge of the second middle support plate (12), and the other end of the rest parts extends to a second rib arranged around a second hanging hole on the second middle support plate (12).
7. The wing mounting mechanism of claim 1,
further comprising:
a rear support plate (14) for connecting to the rear beam (2) and having a rear mounting hole thereon; the transmission shafts (6) sequentially penetrating through the second middle holes of the second middle support plates (12) penetrate through the rear mounting holes;
a skin (15) having a first end, a second end opposite the first end, a first side extending between the first end and the second end, a second side opposite the first side, and having a first via, a plurality of second vias thereon; the first edge and the second edge are used for being connected with the rear beam (2), the inner wall of the first end is connected with the edge of the front support plate (1), and the inner wall of the second end is connected with the edge of the rear support plate (14), so that a closed chamber is formed; the first hanging arm (11) extends out of the first through hole; each second hanging arm (13) correspondingly extends out of one second through hole.
8. The wing mounting mechanism of claim 7,
further comprising a rear edge strip (16) disposed around an edge of the rear brace (14) for connection to the rear beam (2);
one side of the rear support plate (14) is provided with a plurality of rear ribs (17), the parts of the rear ribs (17) are annularly arranged around the rear mounting hole, one end of the rest parts extends to the rear edge strip (16), and the other end of the rest parts extends to the rear ribs (17) arranged around the rear mounting hole.
9. The wing mounting mechanism of claim 7,
the transmission shaft (6) is in clearance fit with the first middle hole and each second middle hole.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910889177.4A CN110539874B (en) | 2019-09-19 | 2019-09-19 | Wing mounting structure of tilt rotor aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910889177.4A CN110539874B (en) | 2019-09-19 | 2019-09-19 | Wing mounting structure of tilt rotor aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110539874A CN110539874A (en) | 2019-12-06 |
| CN110539874B true CN110539874B (en) | 2023-04-07 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201910889177.4A Active CN110539874B (en) | 2019-09-19 | 2019-09-19 | Wing mounting structure of tilt rotor aircraft |
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Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105620717A (en) * | 2014-10-31 | 2016-06-01 | 中国航空工业集团公司西安飞机设计研究所 | Wingtip load diffusion structure of tilt rotor aircraft |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP4238311B2 (en) * | 2002-12-19 | 2009-03-18 | 防衛省技術研究本部長 | 3D composite joint |
| CN101423117A (en) * | 2008-12-05 | 2009-05-06 | 北京航空航天大学 | Tilt-rotor plane operated and propelled by thrust scull and slipstream rudder |
| CN101984331B (en) * | 2010-09-30 | 2012-11-28 | 南京航空航天大学 | Dynamics comprehensive test bed for half-unfolding gas bomb with long tilting rotor wing |
| US10023294B2 (en) * | 2014-08-07 | 2018-07-17 | Bell Helicopter Textron Inc. | Tail spar spring |
| CN104986354B (en) * | 2015-06-23 | 2017-04-19 | 中国航空工业集团公司西安飞机设计研究所 | Reusable tilting rotorcraft test stand |
| CN206939066U (en) * | 2017-03-23 | 2018-01-30 | 沈阳无距科技有限公司 | Multiaxis unmanned plane |
| CN207523932U (en) * | 2017-11-17 | 2018-06-22 | 沈阳无距科技有限公司 | Tandem wing tilting rotor wing unmanned aerial vehicle |
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2019
- 2019-09-19 CN CN201910889177.4A patent/CN110539874B/en active Active
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105620717A (en) * | 2014-10-31 | 2016-06-01 | 中国航空工业集团公司西安飞机设计研究所 | Wingtip load diffusion structure of tilt rotor aircraft |
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| CN110539874A (en) | 2019-12-06 |
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