CN110937119A - Integrated full-composite material connecting rod structure - Google Patents
Integrated full-composite material connecting rod structure Download PDFInfo
- Publication number
- CN110937119A CN110937119A CN201911349608.4A CN201911349608A CN110937119A CN 110937119 A CN110937119 A CN 110937119A CN 201911349608 A CN201911349608 A CN 201911349608A CN 110937119 A CN110937119 A CN 110937119A
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- Prior art keywords
- composite material
- composite
- connecting rod
- joints
- combined material
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- 239000002131 composite material Substances 0.000 title claims abstract description 92
- 239000002184 metal Substances 0.000 claims description 10
- 239000000463 material Substances 0.000 claims description 9
- 238000013461 design Methods 0.000 abstract description 7
- 238000012360 testing method Methods 0.000 abstract description 6
- 238000000034 method Methods 0.000 abstract description 5
- 239000013585 weight reducing agent Substances 0.000 abstract description 5
- 238000010276 construction Methods 0.000 description 4
- 238000004804 winding Methods 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 230000008901 benefit Effects 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 2
- 238000011161 development Methods 0.000 description 2
- 239000007769 metal material Substances 0.000 description 2
- 230000008439 repair process Effects 0.000 description 2
- 238000004088 simulation Methods 0.000 description 2
- 241001631030 Explorator Species 0.000 description 1
- 229910000831 Steel Inorganic materials 0.000 description 1
- 238000004364 calculation method Methods 0.000 description 1
- 238000012669 compression test Methods 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 238000007711 solidification Methods 0.000 description 1
- 230000008023 solidification Effects 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
- 238000009864 tensile test Methods 0.000 description 1
- 230000000007 visual effect Effects 0.000 description 1
Images
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/40—Arrangements for mounting power plants in aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/40—Arrangements for mounting power plants in aircraft
- B64D27/402—Arrangements for mounting power plants in aircraft comprising box like supporting frames, e.g. pylons or arrangements for embracing the power plant
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/40—Arrangements for mounting power plants in aircraft
- B64D27/404—Suspension arrangements specially adapted for supporting vertical loads
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mutual Connection Of Rods And Tubes (AREA)
Abstract
An integrated all-composite connecting rod structure for helping an airplane to reduce weight belongs to the technical field of airplane weight reduction. The invention provides a method for testing the wettability of a composite material of a connecting rod, and belongs to the field of design of airplane structures. The composite material barrel comprises two composite material joints and a composite material barrel body, wherein the two composite material joints are respectively connected with two ends of the composite material barrel body, and the two composite material joints and the composite material barrel body are of an integrated structure. Each composite material joint comprises two composite material lugs and a composite material connecting structure, the two composite material lugs are arranged at the head end of the composite material connecting structure, the tail ends of the composite material connecting structures of the two composite material joints are respectively and integrally connected with the two end parts of the composite material barrel body, and the size of each composite material lug needs to meet the rigidity requirement when bearing load.
Description
Technical Field
The invention relates to an airplane hanging force transmission structure, in particular to a composite material connecting rod, and belongs to the technical field of airplane weight reduction.
Background
The development of the airplane mainly aims at low cost and high carrying capacity, and the problem of weight reduction of the structure is firstly solved to achieve the aim, and the lower connecting rod of the hanging box section is an important force transmission part of the hanging box section and is used for connecting the bottom of the hanging box section and the lower wing surface of the wing to transmit the thrust of an engine. The traditional airplanes, including B737, B777 and C919 airplanes, are made of metal materials, but with the progress of composite material technology, compared with the traditional steel lower connecting rod structure, if the hanging lower connecting rod is made of metal and composite materials, the weight can be reduced by 50% -60%, and potential economic benefits are huge. Therefore, the development of the composite material lower pull rod is one of the key technologies for achieving the weight reduction purpose of the airplane.
The airplane hanging team always hopes to adopt a composite material connecting rod technology to help the airplane to reduce weight, and the material performance plays an important role in hanging the lower connecting rod, so that effective exploration is not carried out at present.
Disclosure of Invention
Aiming at the problem of helping the weight reduction of the airplane, the invention provides an integrated all-composite material connecting rod structure.
The invention discloses an integrated all-composite material connecting rod structure which comprises two composite material joints 1 and a composite material barrel body 2, wherein the two composite material joints 1 are respectively connected with two ends of the composite material barrel body 2, and the two composite material joints and the composite material barrel body 2 are of an integrated structure.
Preferably, each composite material joint 1 comprises two composite material lugs 1-1 and a composite material connecting structure 1-2, the two composite material lugs 1-1 are arranged at the head end of the composite material connecting structure 1-2, the tail ends of the composite material connecting structures 1-2 of the two composite material joints 1 are respectively and integrally connected with the two end parts of the composite material barrel body 2, and the size of each composite material lug 1-1 needs to meet the requirement on rigidity when bearing load.
Preferably, the opposite surfaces of the two metal connecting structures 1-2 of one composite material joint 1 in the two composite material joints 1 are convex cambered surfaces;
the opposite surfaces of the two metal connecting structures 1-2 of the other composite material joint 1 in the two composite material joints 1 are inclined planes, and the bottom ends of the two metal connecting structures 1-2 form an included angle.
Preferably, the ply angle of the composite material barrel is +/-10 degrees.
The invention has the advantages that the structure of the full composite material is adopted, the weight of the structure body is greatly reduced, the structure efficiency is improved, the structure is integrally formed, and the connection between the cylinder body and the joint is avoided, so that the phenomenon of local stress concentration is not easy to generate in loading.
Drawings
FIG. 1 is a schematic structural diagram of an integrated all-composite connecting rod structure;
FIG. 2 is a schematic cross-sectional view of the joint of the present invention;
FIG. 3 is a schematic view of a composite joint construction;
FIG. 4 is a schematic view of another composite tab construction.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It should be noted that the embodiments and features of the embodiments may be combined with each other without conflict.
The invention is further described with reference to the following drawings and specific examples, which are not intended to be limiting.
The invention discloses an integrated all-composite material connecting rod structure which comprises two composite material joints 1 and a composite material barrel body 2, wherein the two composite material joints 1 are respectively connected with two ends of the composite material barrel body 2, and the two composite material joints and the composite material barrel body 2 are of an integrated structure.
Preferably, as shown in fig. 2, each composite material joint 1 comprises two composite material lugs 1-1 and a composite material connecting structure 1-2, the two composite material lugs 1-1 are arranged at the head end of the composite material connecting structure 1-2, the tail ends of the composite material connecting structures 1-2 of the two composite material joints 1 are respectively and integrally connected with the two end parts of the composite material barrel 2, and the size of the composite material lug 1-1 needs to meet the requirement of rigidity when bearing load.
Preferably, the opposite surfaces of the two metal connecting structures 1-2 of one of the two composite material joints 1 are convex cambered surfaces, as shown in fig. 3;
the opposite surfaces of the two metal connecting structures 1-2 of the other composite material joint 1 in the two composite material joints 1 are inclined planes, and the bottom ends of the two metal connecting structures 1-2 form an included angle, as shown in fig. 4.
Preferably, the ply angle of the composite material barrel is +/-10 degrees.
Under the condition of meeting the realizability of design and process, the barrel body and the joint of the embodiment are both made of composite materials, namely the composite material integrated structure is shown in figure 1. The scheme of the embodiment has no reference to engineering application structures, so that the design scheme has general feasibility. The composite material connecting rod structure is modeled by applying CATIA software, and the strength of the model can be analyzed by adopting Abaqus software. The two kinds of software are widely applied to finite element simulation design, and the error between the two kinds of software and a test result is small. The structural design becomes visual by adopting a simulation method, and the obtained calculation result is more consistent with the real situation, so that the manufacturing cost is reduced to the maximum extent, and the precision of the designed product is improved. The CATIA and Abaqus software functions completely meet the design requirements of the connecting rod structure, and the maturity is high.
The structure of the embodiment is integrally formed, and the connection between the cylinder body and the joint is avoided, so that the phenomenon of local stress concentration is not easy to generate in loading. However, since the tabs of the joint are of composite material construction, the structural stiffness at the tabs is weaker when subjected to loads compared to metal constructions, requiring increased tab size to meet the stiffness requirements.
The structure of this embodiment can be in MTS2500KN electro-hydraulic servo test go up tensile and compression test, but when the testpieces were installed, need design anchor clamps and connect combined material connecting rod tip and testing machine to guarantee the stability of structure.
Since the structure of the present embodiment is formed by integrally molding the composite material, when a test piece is damaged in a small area during use, the test piece can be repaired by referring to the aircraft structure repair manual SRM, the aircraft maintenance manual AMM, the component repair manual CMM, and the like. Because the structure has no joint, the damage area is small in the loading process, and the maintainability is good.
The technical scheme is feasible, but a large number of dies and tools are needed for ensuring the quality, and the related auxiliary cost is high. Meanwhile, multiple sets of guarantee dies and tools such as multi-axial discontinuous winding, female and male die pressurization curing, high-precision positioning tools and the like are needed, the processing is complex, the cost is high, the product performance is fully exerted, and the performance is highest.
The scheme of the embodiment needs multi-axial winding and high-pressure pressurization curing, so that a large multi-axial winding laying device and a large press are needed, the number of processes is increased by two compared with other schemes in the single-piece manufacturing operation cost, and the manufacturing cost is expected to be increased by 50%. The precision is guaranteed to main explorator during the assembly, and the degree of difficulty is lower. When this structure of multiaxial winding, need two location centre gripping frocks, inserts, whole solidification and interior support piece are processed respectively to three sets of negative and positive whole mould, still need interior inserts location high-precision frock in addition.
Although the invention herein has been described with reference to particular embodiments, it is to be understood that these embodiments are merely illustrative of the principles and applications of the present invention. It is therefore to be understood that numerous modifications may be made to the illustrative embodiments and that other arrangements may be devised without departing from the spirit and scope of the present invention as defined by the appended claims. It should be understood that features described in different dependent claims and herein may be combined in ways different from those described in the original claims. It is also to be understood that features described in connection with individual embodiments may be used in other described embodiments.
Claims (4)
1. The utility model provides a full combined material connecting rod structure of integral type, its characterized in that includes two combined material and connects (1) and combined material stack shell (2), and two combined material connect (1) and are connected with the both ends of combined material stack shell (2) respectively, and two combined material connect and combined material stack shell (2) structure as an organic whole.
2. The integrated full-composite connecting rod structure according to claim 1, wherein each composite joint (1) comprises two composite lugs (1-1) and one composite connecting structure (1-2), the two composite lugs (1-1) are arranged at the head end of the composite connecting structure (1-2), the tail ends of the composite connecting structures (1-2) of the two composite joints (1) are respectively and integrally connected with the two ends of the composite barrel body (2), and the size of the composite lugs (1-1) is required to meet the rigidity requirement when bearing load.
3. The integrated all-composite connecting rod structure according to claim 2, wherein the two metal connecting structures (1-2) of one (1) of the two composite joints (1) have convex cambered surfaces opposite to each other;
the opposite surfaces of two metal connecting structures (1-2) of the other composite material joint (1) in the two composite material joints (1) are inclined planes, and the bottom ends of the two metal connecting structures (1-2) form an included angle.
4. The integrated, fully composite connecting rod structure of claim 3, wherein the lay-up angle of the composite barrel is ± 10 °.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911349608.4A CN110937119A (en) | 2019-12-24 | 2019-12-24 | Integrated full-composite material connecting rod structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911349608.4A CN110937119A (en) | 2019-12-24 | 2019-12-24 | Integrated full-composite material connecting rod structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110937119A true CN110937119A (en) | 2020-03-31 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911349608.4A Pending CN110937119A (en) | 2019-12-24 | 2019-12-24 | Integrated full-composite material connecting rod structure |
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| CN (1) | CN110937119A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112498654A (en) * | 2020-10-12 | 2021-03-16 | 深圳烯创先进材料研究院有限公司 | Composite material hanging rod piece structure |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1932315A (en) * | 2005-06-24 | 2007-03-21 | 斯奈克玛 | Mechanical part and process to manufacture such a part |
| US20080042007A1 (en) * | 2005-11-17 | 2008-02-21 | Stephane Machado | Device for securing an insert in a structure |
| CN102781650A (en) * | 2009-12-08 | 2012-11-14 | 梅西耶-布加蒂-道提公司 | Process for manufacturing a connecting rod made of a composite having a localized overthickness |
| CN203612215U (en) * | 2013-12-12 | 2014-05-28 | 中航商用航空发动机有限责任公司 | Thrust pulling rod arranged between aero-engine and engine mounting structure |
| CN104023954A (en) * | 2011-12-14 | 2014-09-03 | 波音公司 | Composite Columnar Structure Having Co-Bonded Reinforcement and Fabrication Method |
| CN104736326A (en) * | 2012-10-11 | 2015-06-24 | Bd发明股份有限公司 | One-piece connecting rod and production method thereof |
| US20150239553A1 (en) * | 2014-02-25 | 2015-08-27 | Snecma | Fiber reinforcement for making an elongate mechanical part out of composite material |
| CN204756407U (en) * | 2015-05-08 | 2015-11-11 | 上海云逸民用航空科技有限公司 | Combined material member |
| CN205298241U (en) * | 2016-01-05 | 2016-06-08 | 江苏沪宁钢机股份有限公司 | Two power lever member that tape spool held |
| EP3395591A1 (en) * | 2017-04-06 | 2018-10-31 | THK Rhythm Automotive GmbH | Landing gear component and method for its production |
| CN109163006A (en) * | 2018-11-09 | 2019-01-08 | 哈尔滨工业大学 | A kind of link mechanism of composite material and metal bonding |
-
2019
- 2019-12-24 CN CN201911349608.4A patent/CN110937119A/en active Pending
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1932315A (en) * | 2005-06-24 | 2007-03-21 | 斯奈克玛 | Mechanical part and process to manufacture such a part |
| US20080042007A1 (en) * | 2005-11-17 | 2008-02-21 | Stephane Machado | Device for securing an insert in a structure |
| CN102781650A (en) * | 2009-12-08 | 2012-11-14 | 梅西耶-布加蒂-道提公司 | Process for manufacturing a connecting rod made of a composite having a localized overthickness |
| CN104023954A (en) * | 2011-12-14 | 2014-09-03 | 波音公司 | Composite Columnar Structure Having Co-Bonded Reinforcement and Fabrication Method |
| CN104736326A (en) * | 2012-10-11 | 2015-06-24 | Bd发明股份有限公司 | One-piece connecting rod and production method thereof |
| CN203612215U (en) * | 2013-12-12 | 2014-05-28 | 中航商用航空发动机有限责任公司 | Thrust pulling rod arranged between aero-engine and engine mounting structure |
| US20150239553A1 (en) * | 2014-02-25 | 2015-08-27 | Snecma | Fiber reinforcement for making an elongate mechanical part out of composite material |
| CN204756407U (en) * | 2015-05-08 | 2015-11-11 | 上海云逸民用航空科技有限公司 | Combined material member |
| CN205298241U (en) * | 2016-01-05 | 2016-06-08 | 江苏沪宁钢机股份有限公司 | Two power lever member that tape spool held |
| EP3395591A1 (en) * | 2017-04-06 | 2018-10-31 | THK Rhythm Automotive GmbH | Landing gear component and method for its production |
| CN109163006A (en) * | 2018-11-09 | 2019-01-08 | 哈尔滨工业大学 | A kind of link mechanism of composite material and metal bonding |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112498654A (en) * | 2020-10-12 | 2021-03-16 | 深圳烯创先进材料研究院有限公司 | Composite material hanging rod piece structure |
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Application publication date: 20200331 |
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