CN108100230A - A kind of helicopter horizontal tail wing box - Google Patents
A kind of helicopter horizontal tail wing box Download PDFInfo
- Publication number
- CN108100230A CN108100230A CN201711247117.XA CN201711247117A CN108100230A CN 108100230 A CN108100230 A CN 108100230A CN 201711247117 A CN201711247117 A CN 201711247117A CN 108100230 A CN108100230 A CN 108100230A
- Authority
- CN
- China
- Prior art keywords
- axle beam
- wing box
- back rest
- horizontal tail
- tail wing
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/02—Tailplanes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
Abstract
The present invention relates to helicopter rotor blade surface pressure measurement fields, are related to a kind of helicopter horizontal tail wing box, including being formed by carbon fibre fabric lamination and collectively forming the front-axle beam, the back rest, two ribs of the frame of helicopter horizontal tail wing box；It is formed by carbon fibre fabric lamination and for forming the upper covering of complete wing box body and lower covering；Top connection, the front connector formed by carbon fibre fabric lamination.The helicopter horizontal tail wing box of the present invention, it is light-weight, assembling is simple, and front connector carries out integrated design with front-axle beam, rib, top connection carries out integrated design with rib web, and load path is direct, and configuration is simple, convenient for manufacture.
Description
Technical field
The present invention relates to helicopter horizontal tail wing box field of structural design, more particularly to a kind of helicopter horizontal tail wing box.
Background technology
Helicopter horizontal tail wing box, which is located at, goes straight up to drive end unit, and weight is affected to full machine center of gravity, if the weight of afterbody
Make center of gravity that expected requirement be not achieved, it is necessary to increase counterweight or arrange airborne equipment, increase useless weight and influence aeroplane performance.
Existing helicopter horizontal tail wing box is based on metal structure, and beam, web, connector is designed respectively, so
It is attached afterwards using connector, not only affects the weight loss effect of composite material, and globality is not strong, have that weight is big, dress
With shortcomings such as cycle long, manufacture cost height.
The content of the invention
The purpose of the present invention designs a kind of helicopter horizontal tail wing box, to solve existing for existing helicopter horizontal tail wing box at least
One problem.
The technical scheme is that：
A kind of helicopter horizontal tail wing box, including：
Front-axle beam is laminated by carbon fibre fabric, before being symmetricly set on front-axle beam stage casing both ends including front-axle beam stage casing
Left section of beam and right section of front-axle beam offer connecting hole on left section of the front-axle beam and right section of front-axle beam；
The back rest is laminated by carbon fibre fabric, after being symmetricly set on back rest stage casing both ends including back rest stage casing
Left section of beam and right section of the back rest offer connecting hole on left section of the back rest and right section of the back rest, and the back rest is parallel with the front-axle beam
Arrangement；
Two ribs being at least mutually parallel, are laminated by carbon fibre fabric, vertical co-curing beam in the rear
Between the front-axle beam, the frame of the helicopter horizontal tail wing box is collectively formed；
Upper covering and lower covering, are laminated, respectively by secondary co-curing on said frame by carbon fibre fabric
Lower surface forms complete wing box body；
Top connection is laminated by carbon fibre fabric, be fixed on the median plane of the wing box body and with it is described
Ribs connects；
Front connector is laminated by carbon fibre fabric, positioned at the front-axle beam backwards to the one side of the back rest, and with institute
State front-axle beam integrated molding.
Optionally, at least two ribs are at the front-axle beam stage casing and the back rest middle section position.
Optionally, the top connection is connected with along two most intermediate ribs on front-axle beam length direction.
Optionally, sewing is used in the corner region of the wing box body.
Optionally, the front connector is two, is symmetricly set on the preceding beam sides.
Optionally, the upper and lower end face in the front-axle beam stage casing is outward extended with flange to the direction backwards to the back rest, respectively
For being connected with the upper covering and lower covering co-curing；
The upper and lower end face in the back rest stage casing is outward extended with flange to backwards to the direction of the front-axle beam, is respectively used to and institute
Covering is stated to connect with lower covering co-curing.
Invention effect：
1) it is, light-weight：Using composite material integrative design, wing box is compared with metal structure loss of weight up to 30%；
2), assembling is simple：Only need to carry out covering and beam, rib it is secondary cementing, without metal connecting piece, assembly work amount
Greatly reduce；
3), front connector and front-axle beam, rib carry out integrated design, and top connection carries out integrated design, power transmission road with rib web
Line is direct, and configuration is simple, convenient for manufacture.
Description of the drawings
Fig. 1 is the structure diagram of invention helicopter horizontal tail wing box；
Fig. 2 is the structure diagram of front-axle beam in invention helicopter horizontal tail wing box；
Fig. 3 is the structure diagram of ribs in invention helicopter horizontal tail wing box.
Specific embodiment
To make the purpose, technical scheme and advantage that the present invention is implemented clearer, below in conjunction in the embodiment of the present invention
Attached drawing, the technical solution in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label represent same or similar element or there is same or like element.Described embodiment is the present invention
Part of the embodiment, instead of all the embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to use
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiments of the present invention, ordinary skill people
Member's all other embodiments obtained without creative efforts, belong to the scope of protection of the invention.Under
Face is described in detail the embodiment of the present invention with reference to attached drawing.
In the description of the present invention, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or position relationship of the instructions such as "left", "right", " vertical ", " level ", " top ", " bottom ", " interior ", " outer " is based on attached drawing institutes
The orientation or position relationship shown is for only for ease of the description present invention and simplifies description rather than instruction or imply signified dress
It puts or element must have specific orientation, with specific azimuth configuration and operation, therefore it is not intended that the present invention is protected
The limitation of scope.
1 to Fig. 3 helicopter horizontal tail wing box of the present invention is described in further details below in conjunction with the accompanying drawings.
The present invention provides a kind of helicopter horizontal tail wing box, including front-axle beam 1, the back rest 2, ribs 5, upper covering 3, lower covering
4th, top connection 7 and front connector 6.
Front-axle beam 1 is laminated by carbon fibre fabric, and the front-axle beam that front-axle beam stage casing both ends are symmetricly set on including front-axle beam stage casing is left
Connecting hole is offered on section and right section of front-axle beam, left section of front-axle beam and right section of front-axle beam；Further, connection hole is defined as connector, connector
Shape can be semicircle or ellipse, connecting hole can be that single hole can also be diplopore.Further, front-axle beam stage casing is upper and lower
End face is outward extended with flange to the direction backwards to the back rest 2, is respectively used to and the upper covering 3 and lower 4 co-curing of covering
Connection.
The back rest 2 is arranged in parallel with front-axle beam 1.The back rest 2 is laminated by carbon fibre fabric, is symmetricly set on including back rest stage casing
Left section of the back rest at back rest stage casing both ends and right section of the back rest offer connecting hole on left section of the back rest and right section of the back rest.Equally, connecting hole
Place is defined as connector, and the shape of connector can be semicircle or ellipse, and connecting hole can be that single hole can also be diplopore.
Ribs 5 includes two be at least mutually parallel；Two ribs 5 are laminated by carbon fibre fabric, vertically
Co-curing collectively forms the frame of helicopter horizontal tail wing box between the back rest 2 and front-axle beam 1.Further, preferably ribs 5 is position
At front-axle beam stage casing and back rest middle section position.Specifically, as shown in figure 3, ribs 5 can include leading edge 8, trailing edge 9, upper limb
10th, lower edge 11, wherein leading edge 8 are connected with front-axle beam 1, and trailing edge 9 is connected with the back rest 2, upper limb 10 is connected with upper covering 3, lower edge 11 with
Lower covering 4 connects.
The mixed structure that upper covering 3 and lower covering 4 are laminate structure and sandwich structure is composed, is knitted by carbon fiber
Nitride layer is pressed, and forms complete wing box body in frame upper and lower surface by secondary co-curing respectively.In addition, upper 3 He of covering
Lower covering 4 can extend rearwardly to form enclosed construction along wing box is tangential.
Top connection 7 is laminated by carbon fibre fabric, is fixed on the median plane of wing box body and is connected with ribs 5
It connects.Further, top connection 7 is connected with along two most intermediate ribs 5 on 1 length direction of front-axle beam.
Front connector 6 is laminated by carbon fibre fabric, positioned at front-axle beam 1 backwards to the one side of the back rest 2, and with front-axle beam 1 one
Body chemical conversion type.Further, preferably front connector 6 is two, is symmetricly set on 1 side of front-axle beam.
Further, in helicopter horizontal tail wing box of the invention, the upper and lower end face in front-axle beam stage casing support or oppose to the direction of the back rest 2 to
Flange is extended with outside, is respectively used to be connected with upper covering 3 and lower 4 co-curing of covering.It supports or opposes forward the upper and lower end face in back rest stage casing
The direction of beam 1 is outward extended with flange, is respectively used to be connected with upper covering 3 and lower 4 co-curing of covering.
Further, in helicopter horizontal tail wing box of the invention, front-axle beam 1, the back rest 2, front connector 6, top connection 7 and ribs 5
Using carbon fibre fabric, and strengthened in corner region using sewing, using integrated molding.Upper covering 3 and lower covering 4 are independent
Shaping, then carries out secondary cementing, and front-axle beam 1, the back rest 2, ribs 5 and upper covering 3, lower covering 4 are linked together.
The helicopter horizontal tail wing box of the present invention is compared with other horizontal tail wing box, the helicopter horizontal tail of monoblock type carbon fiber formation
Wing box has the following advantages：
1) it is, light-weight：Using composite material integrative design, wing box is compared with metal structure loss of weight up to 30%；
2), assembling is simple：Only need to carry out covering and beam, rib it is secondary cementing, without metal connecting piece, assembly work amount
Greatly reduce；
3), front connector and front-axle beam, rib carry out integrated design, and top connection carries out integrated design, power transmission road with rib web
Line is direct, and configuration is simple, convenient for manufacture.
The above description is merely a specific embodiment, but protection scope of the present invention is not limited thereto, any
Those familiar with the art in the technical scope disclosed by the present invention, all should by the change or replacement that can be readily occurred in
It is included within the scope of the present invention.Therefore, protection scope of the present invention should using the scope of the claims as
It is accurate.
Claims (6)
1. a kind of helicopter horizontal tail wing box, which is characterized in that including：
Front-axle beam (1), is laminated by carbon fibre fabric, and the front-axle beam at front-axle beam stage casing both ends is symmetricly set on including front-axle beam stage casing
Left section and right section of front-axle beam offer connecting hole on left section of the front-axle beam and right section of front-axle beam；
The back rest (2), is laminated by carbon fibre fabric, and the back rest at back rest stage casing both ends is symmetricly set on including back rest stage casing
Left section and right section of the back rest offer connecting hole, the back rest (2) and the front-axle beam (1) on left section of the back rest and right section of the back rest
Parallel arrangement；
Two ribs (5) being at least mutually parallel, are laminated by carbon fibre fabric, vertical co-curing beam in the rear
(2) between the front-axle beam (1), the frame of the helicopter horizontal tail wing box is collectively formed；
Upper covering (3) and lower covering (4), are laminated by carbon fibre fabric, respectively by secondary co-curing in the frame
Upper and lower surface forms complete wing box body；
Top connection (7), is laminated by carbon fibre fabric, is fixed on the median plane of the wing box body and is added with described
Strong rib (5) connection；
Front connector (6), is laminated by carbon fibre fabric, positioned at the front-axle beam (1) backwards to the one side of the back rest (2),
And with the front-axle beam (1) integrated molding.
2. helicopter horizontal tail wing box according to claim 1, which is characterized in that at least two ribs (5) are positions
At the front-axle beam stage casing and the back rest middle section position.
3. helicopter horizontal tail wing box according to claim 1, which is characterized in that the top connection (7) along front-axle beam (1) with growing
Spend most intermediate two ribs (5) connection on direction.
4. helicopter horizontal tail wing box according to claim 1, which is characterized in that adopted in the corner region of the wing box body
With sewing.
5. helicopter horizontal tail wing box according to claim 1, which is characterized in that the front connector (6) is two, is symmetrically set
It puts on the front-axle beam (1) side.
6. helicopter horizontal tail wing box according to claim 1, which is characterized in that support or oppose the upper and lower end face in the front-axle beam stage casing
Flange is outward extended with to the direction of the back rest (2), is respectively used to and the upper covering (3) and lower covering (4) co-curing company
It connects；
The upper and lower end face in the back rest stage casing is outward extended with flange to backwards to the direction of the front-axle beam (1), is respectively used to and institute
Covering (3) is stated to connect with lower covering (4) co-curing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711247117.XA CN108100230A (en) | 2017-12-01 | 2017-12-01 | A kind of helicopter horizontal tail wing box |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711247117.XA CN108100230A (en) | 2017-12-01 | 2017-12-01 | A kind of helicopter horizontal tail wing box |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108100230A true CN108100230A (en) | 2018-06-01 |
Family
ID=62207990
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711247117.XA Pending CN108100230A (en) | 2017-12-01 | 2017-12-01 | A kind of helicopter horizontal tail wing box |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108100230A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110203373A (en) * | 2019-05-24 | 2019-09-06 | 成都飞机工业（集团）有限责任公司 | A kind of vertical horizontal tail detaching structure of unmanned plane |
| CN110524908A (en) * | 2019-08-27 | 2019-12-03 | 西安爱生技术集团公司 | A kind of unmanned plane composite material horizontal tail integral solidifying tooling |
| CN110815899A (en) * | 2019-10-10 | 2020-02-21 | 中国直升机设计研究所 | Helicopter blade embedded box-shaped device and forming method thereof |
| CN111907087A (en) * | 2020-07-10 | 2020-11-10 | 航天特种材料及工艺技术研究所 | Forming assembly tool and manufacturing method for composite unmanned aerial vehicle horizontal tail |
| CN112407242A (en) * | 2020-11-09 | 2021-02-26 | 北京北航天宇长鹰无人机科技有限公司 | A connect integral root rib and unmanned aerial vehicle for unmanned aerial vehicle fin |
| CN112623190A (en) * | 2020-12-29 | 2021-04-09 | 中国航空工业集团公司西安飞机设计研究所 | Aircraft stable face box section interfacing apparatus |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110203373A (en) * | 2019-05-24 | 2019-09-06 | 成都飞机工业（集团）有限责任公司 | A kind of vertical horizontal tail detaching structure of unmanned plane |
| CN110524908A (en) * | 2019-08-27 | 2019-12-03 | 西安爱生技术集团公司 | A kind of unmanned plane composite material horizontal tail integral solidifying tooling |
| CN110524908B (en) * | 2019-08-27 | 2022-05-27 | 西安爱生技术集团公司 | Unmanned aerial vehicle combined material horizontal tail integral curing forming tool |
| CN110815899A (en) * | 2019-10-10 | 2020-02-21 | 中国直升机设计研究所 | Helicopter blade embedded box-shaped device and forming method thereof |
| CN111907087A (en) * | 2020-07-10 | 2020-11-10 | 航天特种材料及工艺技术研究所 | Forming assembly tool and manufacturing method for composite unmanned aerial vehicle horizontal tail |
| CN112407242A (en) * | 2020-11-09 | 2021-02-26 | 北京北航天宇长鹰无人机科技有限公司 | A connect integral root rib and unmanned aerial vehicle for unmanned aerial vehicle fin |
| CN112623190A (en) * | 2020-12-29 | 2021-04-09 | 中国航空工业集团公司西安飞机设计研究所 | Aircraft stable face box section interfacing apparatus |
| CN112623190B (en) * | 2020-12-29 | 2023-11-21 | 中国航空工业集团公司西安飞机设计研究所 | Butt joint device for box sections of plane stabilizer |
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Legal Events
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20180601 |