CN202029997U - Tandem two-seat cockpit skeleton for helicopter - Google Patents
Tandem two-seat cockpit skeleton for helicopter Download PDFInfo
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- CN202029997U CN202029997U CN 201120002234 CN201120002234U CN202029997U CN 202029997 U CN202029997 U CN 202029997U CN 201120002234 CN201120002234 CN 201120002234 CN 201120002234 U CN201120002234 U CN 201120002234U CN 202029997 U CN202029997 U CN 202029997U
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- skeleton
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- passenger cabin
- section
- helicopter
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Abstract
The utility model belongs to structural systems of helicopter bodies and relates to a tandem two-seat cockpit skeleton for a helicopter. The cockpit skeleton takes the shape of a fiber reinforced composite polyhedron and shaped by gluing or riveting or gluing and riveting a planar right-side skeleton face (1), a planar left-side skeleton face (2) and a multi-section folded-face cockpit ceiling (3), which are one-step molded together; and all fold lines of the polyhedron are beams with hollow tubular cross sections. The cockpit skeleton has only three parts, so that the numbers of tooling and die required in part shaping can be greatly reduced and the manufacturing cost can be lowered; the individual part is easy to shape, so that the rejection rate of individual part can be effectively lowered; the connection among parts is simple and concordant, so that the working hours required in assembling can be effectively shortened and the assembling rejection rate can be effectively lowered; and the integral skeleton is light in weight, so that the bearing capacity of the structure can be effectively improved.
Description
Technical field
The invention belongs to helicopter housing construction system, relate to a kind of new configuration of tandem two-seater helicopter capsule skeleton.
Background technology
The helicopter capsule skeleton is the main stress structure of canopy.For tandem two-seater helicopter, usually the passenger cabin space is narrow and small, but be furnished with a plurality of openings (comprising daily turnover hatch door, escape hatch and polylith Transparent Parts) on the canopy usually, remove beyond these openings, passenger cabin skeleton as the main stress structure can only be designed to space rigid formula structure, and all the other zone design opaque, not opening are covering.For alleviating structural weight, improving structural bearing efficient, each of rigid frame structure section beam adopts the hollow tubular cross section usually.
Composite material has advantages such as strength-to-density ratio, specific modulus and designability, is widely used on helicopter structure.But composite material is particularly suitable for plate and shell structure, the space rigid structure that connects into for this class hollow tubular beam of passenger cabin skeleton, the application of composite material then is subjected to the restriction of multiple factors such as part shape complexity, die cost height, assembly coordination difficulty, manufacturing cycle length, fails to give full play to its advantage.
A kind of representative type passenger cabin skeleton structure configuration is, the independent moulding respectively of rigid frame structure and covering, then with covering riveting on rigid frame.Rigid frame structure is the folding face with the profile turnover then, is divided into the beam of plurality of sections tubular section, socket or be riveted together with band plate after the independent moulding of each section beam.This node configuration number of parts is many, and each forming parts difficulty, the manufacturing cycle is long, cost is high, yield rate is low, and assembly coordination difficulty, jump are difficult to control behind the forming parts, interchangeability is poor, and attaching parts is many, weight cost height, structural bearing efficient are low.
Summary of the invention
The technical problem to be solved in the present invention:
The objective of the invention is to propose the new configuration of a kind of tandem two-seater helicopter capsule skeleton that a kind of part is few, in light weight, easily manufactured, assembling is easy, interchangeability is good.
Technical scheme of the present invention:
A kind of new configuration of passenger cabin skeleton of tandem two-seater helicopter, the new configuration profile of this passenger cabin skeleton is the fiber reinforced composite polyhedron, right side skeleton face 1 by the one-time formed plane of difference, the passenger cabin ceiling 3 of the left side skeleton face 2 on plane and multistage folding face adopts to glued joint or rivet or glued joint the form that adds riveted joint and is formed by connecting, constitute the beam that polyhedral each section broken line is the hollow tubular cross section, the polyhedron part has honeycomb interlayer or the ply wood form covering with left and right sides skeleton face once-forming, described each section broken line hollow tubular cuts section bar and comprises that two are gone up polygonal beam 4 and two following polygonal beams 5, following polygonal beam is connected with fuselage mechanism by the base of several shaped sections of left and right sides skeleton face and forms, last polygonal beam is that L shaped cross section flanging and a few shaped sections top margin overlap joints of left and right sides skeleton face of passenger cabin ceiling form, right side skeleton face 1, the passenger cabin ceiling 3 of the left side skeleton face 2 on plane and multistage folding face transversely also has some crossbeams 6, crossbeam 6 and place face one-shot forming, its cross section is a rectangle or trapezoidal.
Beneficial effect of the present invention:
The present invention has provided the succinct passenger cabin skeleton structure configuration of a kind of form.This configuration has the following advantages and effect:
1) number of parts is few, has only three, can significantly reduce required frock of forming parts and number of molds, reduction manufacturing cost;
2) the single part moulding is easy, can effectively reduce the condemnation factor of single part;
3) annexation is simple between the part, harmony good, can effectively reduce and assemble required man-hour, reduction assembling condemnation factor;
4) overall weight is light, can effectively improve structural bearing efficient.
Description of drawings
Accompanying drawing 1 is a scheme drawing of the present invention, and wherein, 1 is right side skeleton face, and 2 is left side skeleton face, 3 passenger cabin ceilings for multistage folding face, and 4 is last polygonal beam, and 5 are following polygonal beam, and 6 is crossbeam.
Accompanying drawing 2 is for being A-A section of the present invention;
Accompanying drawing 3 is fitting process scheme drawing of the present invention.
The specific embodiment
The present invention makes full use of the advantage of composite material designability, covering and rigid frame structure are united two into one, vertical tubular member is divided into two, the space rigid STRUCTURE DECOMPOSITION of Fu Za band covering is three parts such as left side skeleton surface member, right side skeleton surface member and passenger cabin ceiling the most at last, three parts all adopt the composite material one-shot forming, become integral structure by splicing or glue riveting after the moulding.Concrete implementation step is as follows:
(1) according to full machine profile and load condition, the cross sectional shape and the size of selected each hollow polygonal beam;
(2) determine the folding face of right side skeleton face 1 and passenger cabin ceiling 3 and the folding face of left side skeleton face 2 and passenger cabin ceiling 3 according to polygonal beam cross sectional shape and size; Left and right sides skeleton mask has the base and the top margin of several shaped sections, and passenger cabin ceiling 3 has corresponding L shaped cross section flanging; It is rectangle or trapezoidal crossbeam 6 that the passenger cabin ceiling 3 of the left side skeleton face 2 on right side skeleton face 1, plane and multistage folding face transversely also has some cross sections.
(4) three parts such as difference moulding right side skeleton 1, left side skeleton 2 and passenger cabin ceiling 3;
(5) three parts are joined together to form whole passenger cabin skeleton, the bonded assembly form can adopt to glued joint or rivet or glued joint and add riveted joint.
Claims (1)
1. the passenger cabin skeleton of a tandem two-seater helicopter, it is characterized in that, the new configuration profile of this passenger cabin skeleton is the fiber reinforced composite polyhedron, right side skeleton face (1) by the one-time formed plane of difference, the passenger cabin ceiling (3) of the left side skeleton face (2) on plane and multistage folding face adopts to glued joint or rivet or glued joint the form that adds riveted joint and is formed by connecting, constitute the beam that polyhedral each section broken line is the hollow tubular cross section, described each section broken line hollow tubular cuts section bar and comprises that two are gone up polygonal beam (4) and two following polygonal beams (5), following polygonal beam is connected with fuselage mechanism by the base of several shaped sections of left and right sides skeleton face and forms, last polygonal beam is that L shaped cross section flanging and a few shaped sections top margin overlap joints of left and right sides skeleton face of passenger cabin ceiling form, right side skeleton face (1), the passenger cabin ceiling (3) of the left side skeleton face (2) on plane and multistage folding face transversely also has some crossbeams (6), crossbeam (6) and place face one-shot forming, its cross section is a rectangle or trapezoidal, and the polyhedron part has honeycomb interlayer or the ply wood form covering (7) with left and right sides skeleton face once-forming.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201120002234 CN202029997U (en) | 2011-01-06 | 2011-01-06 | Tandem two-seat cockpit skeleton for helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201120002234 CN202029997U (en) | 2011-01-06 | 2011-01-06 | Tandem two-seat cockpit skeleton for helicopter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202029997U true CN202029997U (en) | 2011-11-09 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201120002234 Expired - Lifetime CN202029997U (en) | 2011-01-06 | 2011-01-06 | Tandem two-seat cockpit skeleton for helicopter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202029997U (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| PL423867A1 (en) * | 2017-12-13 | 2019-06-17 | Flaris Spółka Z Ograniczoną Odpowiedzialnością | Composite performance construction of an aircraft cockpit stiffened by the spatial framework |
| CN110949656A (en) * | 2019-12-06 | 2020-04-03 | 江西洪都航空工业集团有限责任公司 | Anti-deformation combined type framework of aircraft cabin cover |
| CN112357112A (en) * | 2020-10-30 | 2021-02-12 | 哈尔滨哈飞航空工业有限责任公司 | Gluing assembly method and fixture for helicopter cabin cover |
| CN112550658A (en) * | 2020-12-08 | 2021-03-26 | 芜湖中科飞机制造有限公司 | High-performance and high-strength series-seat type composite material machine body structure |
| CN113942628A (en) * | 2021-11-19 | 2022-01-18 | 中国直升机设计研究所 | High-viability helicopter cabin |
-
2011
- 2011-01-06 CN CN 201120002234 patent/CN202029997U/en not_active Expired - Lifetime
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| PL423867A1 (en) * | 2017-12-13 | 2019-06-17 | Flaris Spółka Z Ograniczoną Odpowiedzialnością | Composite performance construction of an aircraft cockpit stiffened by the spatial framework |
| CN110949656A (en) * | 2019-12-06 | 2020-04-03 | 江西洪都航空工业集团有限责任公司 | Anti-deformation combined type framework of aircraft cabin cover |
| CN110949656B (en) * | 2019-12-06 | 2022-10-11 | 江西洪都航空工业集团有限责任公司 | Anti-deformation combined type framework of aircraft cabin cover |
| CN112357112A (en) * | 2020-10-30 | 2021-02-12 | 哈尔滨哈飞航空工业有限责任公司 | Gluing assembly method and fixture for helicopter cabin cover |
| CN112357112B (en) * | 2020-10-30 | 2023-07-21 | 哈尔滨哈飞航空工业有限责任公司 | Helicopter cabin cover gluing assembly method and clamp |
| CN112550658A (en) * | 2020-12-08 | 2021-03-26 | 芜湖中科飞机制造有限公司 | High-performance and high-strength series-seat type composite material machine body structure |
| CN113942628A (en) * | 2021-11-19 | 2022-01-18 | 中国直升机设计研究所 | High-viability helicopter cabin |
| CN113942628B (en) * | 2021-11-19 | 2023-04-11 | 中国直升机设计研究所 | High-viability helicopter cabin |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term |
Granted publication date: 20111109 |
|
| CX01 | Expiry of patent term |