GB1561328A - Construction of composite structural members such as propeller blades - Google Patents
Construction of composite structural members such as propeller blades Download PDFInfo
- Publication number
- GB1561328A GB1561328A GB27064/75A GB2706475A GB1561328A GB 1561328 A GB1561328 A GB 1561328A GB 27064/75 A GB27064/75 A GB 27064/75A GB 2706475 A GB2706475 A GB 2706475A GB 1561328 A GB1561328 A GB 1561328A
- Authority
- GB
- United Kingdom
- Prior art keywords
- spar
- shell
- interfacing
- load
- bond
- 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.)
- Expired
Links
- 239000002131 composite material Substances 0.000 title claims description 10
- 238000010276 construction Methods 0.000 title claims description 7
- 239000000463 material Substances 0.000 claims description 21
- 229910052751 metal Inorganic materials 0.000 claims description 8
- 239000002184 metal Substances 0.000 claims description 8
- 229920005989 resin Polymers 0.000 claims description 6
- 239000011347 resin Substances 0.000 claims description 6
- 239000004033 plastic Substances 0.000 claims description 4
- 229920003023 plastic Polymers 0.000 claims description 4
- 239000004411 aluminium Substances 0.000 claims description 2
- 229910052782 aluminium Inorganic materials 0.000 claims description 2
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 2
- 239000003822 epoxy resin Substances 0.000 claims description 2
- 229920000647 polyepoxide Polymers 0.000 claims description 2
- 239000007787 solid Substances 0.000 claims description 2
- 239000011257 shell material Substances 0.000 description 17
- 230000004048 modification Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 229920003002 synthetic resin Polymers 0.000 description 2
- 239000000057 synthetic resin Substances 0.000 description 2
- 101100055224 Anemone leveillei AL10 gene Proteins 0.000 description 1
- XUKUURHRXDUEBC-KAYWLYCHSA-N Atorvastatin Chemical compound C=1C=CC=CC=1C1=C(C=2C=CC(F)=CC=2)N(CC[C@@H](O)C[C@@H](O)CC(O)=O)C(C(C)C)=C1C(=O)NC1=CC=CC=C1 XUKUURHRXDUEBC-KAYWLYCHSA-N 0.000 description 1
- 239000000853 adhesive Substances 0.000 description 1
- 230000001070 adhesive effect Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000007935 neutral effect Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 229920002994 synthetic fiber Polymers 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B15/00—Layered products comprising a layer of metal
- B32B15/04—Layered products comprising a layer of metal comprising metal as the main or only constituent of a layer, which is next to another layer of the same or of a different material
- B32B15/08—Layered products comprising a layer of metal comprising metal as the main or only constituent of a layer, which is next to another layer of the same or of a different material of synthetic resin
- B32B15/092—Layered products comprising a layer of metal comprising metal as the main or only constituent of a layer, which is next to another layer of the same or of a different material of synthetic resin comprising epoxy resins
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/16—Blades
- B64C11/20—Constructional features
- B64C11/26—Fabricated blades
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B27/00—Layered products comprising a layer of synthetic resin
- B32B27/38—Layered products comprising a layer of synthetic resin comprising epoxy resins
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form
- B32B3/26—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layer; characterised by a layer with cavities or internal voids ; characterised by an apertured layer
- B32B3/266—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layer; characterised by a layer with cavities or internal voids ; characterised by an apertured layer characterised by an apertured layer, the apertures going through the whole thickness of the layer, e.g. expanded metal, perforated layer, slit layer regular cells B32B3/12
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B7/00—Layered products characterised by the relation between layers; Layered products characterised by the relative orientation of features between layers, or by the relative values of a measurable parameter between layers, i.e. products comprising layers having different physical, chemical or physicochemical properties; Layered products characterised by the interconnection of layers
- B32B7/04—Interconnection of layers
- B32B7/12—Interconnection of layers using interposed adhesives or interposed materials with bonding properties
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
- B64C27/46—Blades
- B64C27/473—Constructional features
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2305/00—Condition, form or state of the layers or laminate
- B32B2305/08—Reinforcements
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2311/00—Metals, their alloys or their compounds
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2363/00—Epoxy resins
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2603/00—Vanes, blades, propellers, rotors with blades
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
- B64C27/46—Blades
- B64C27/473—Constructional features
- B64C2027/4733—Rotor blades substantially made from particular materials
- B64C2027/4736—Rotor blades substantially made from particular materials from composite materials
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Laminated Bodies (AREA)
Description
(54) IMPROVEMENTS IN OR RELATING TO THE
CONSTRUCTION OF COMPOSITE STRUCTURAL
MEMBERS SUCH AS PROPELLER BLADES
(71) We, HAWKER SIDDELEY DYNAMICS LXTBD, a British Company of Manor
Road, Hatfield, Hertfordshire AL10 9LL,
England, do hereby declare the invention for which we pray that a Patent may be granted to us, and the method by which it is to be performed to be particularly described in and by the following statement:- This invention relates to improvements in
the construction and manufacture of composite structural members and is particu
larly, though not exclusively, directed to
improvements in propeller and other blades made of elongated fibre-reinforced synthetic plastics materal.In the application of the
invention to such blades it is especially
concerned with the provision of means
which ensure that repair or modification of
of the blade may be achieved while main
taining the integrity of the load-carrying
member of the blade.
In our previously granted Patent No.
1,291,562, there is disclosed the concept of a fabricated composite member, such as a
propeller, wherein the blade is a shell formed
of a fibre-reinforced synthetic material at
tached to and supported by a load-carrying
spar of an expensive high grade material.
In the repair or modification of the shells
of such blades it is important that the oper
ator carrying out such repair or modification,
either with the use of hand or machine tools,
shall be able to do so without the risk of
resulting damage to the load-carrying spar
within, and it is an object of the invention
to provide a form of construction which pre
serves the integrity of the load-carrying spar
during such operations, while allowing the removal and replacement of or local repair
to a damaged blade shell.
In accordance with the invention, a com
posite structural member comprises a lightlyloaded shell formed of a fibre-reinforced synthetic plastics material attached to and
supported by an internal load-carrying spar made of higher grade material chosen to give the required load-carrying capability, and wherein an interfacing member is provided between the shell and the load-carrying spar.
Preferably, the interfacing member is of a material which is distinctively perceptively different from the material of the shell, whereby an operator effecting removal of shell material for replacement or repair is readily enabled to determine the desirable safe limit of shell material removal. The distinction may be provided by use of a material for the interface which is different in physical nature to that of the shell, e.g. hardness, colour or type. In a preferred arrangement, the interface material is a metal and a bond is achieved between the interface and the spar by an adhesive such as an expoxy resin.
Advantageously, the bond between the spar and the interface material may be of a first resin and the bond between the interface and the shell of a second resin, the second resin having a lower shear strength than the first, so that the physical separation of the shell from the interface is preferential to that of the interface from the spar.
According to a further feature, the interface material may be perforated so that the bond between the metal and the spar is improved.
To give a better understanding of the invention, two examples of embodiments thereof will now be described with reference to the accompanying drawings, in which: Figures 1 and 2 are diagrammatic partial cross sections through parts of two forms of propeller blade of composite construction.
In Fig. 1, which is a diagrammatic representation of a section through a blade on a plane normal to the neutral axis, a spar member 1 made of a high modulus loadbearing fibre-reinforced synthetic resin material carries a blade shell 2, also of fibre-reinforced synthetic resin material but which is less strong and less expensive than the material of .the spar since it does not have to be load-bearing. Between the spar 1 and the shell 2 is an interfacing member 3 which is made of metal, such as aluminium, and assembly is achieved by the interface member 3 being firstly strongly bonded to the spar 1 by means of an epoxy resin layer 4; the shell 2 is then less strongly bonded to the interfacing member 3 by means of a further expoxy resin layer 5.
Fig. 2 shows in diagrammatic fashion a similar form of construction wherein the only difference from Fig. 1 is that interface member 3a is, unlike member 3 in Fig. 1, no longer a solid metal strip but is perforated by holes 6 whereby the bond between the member 3a and adjacent members 1, 2 may be enhanced.
WHAT WE CLAIM IS:
1. A composite structural member comprising a lightly-loaded shell formed of a fibre-reinforced synthetic plastics material attached to and supported by an internal load-carrying spar made of higher grade material chosen t6 give the required load-carrying capability, and wherein an interfacing member is provided between the shell and the load-carrying spar.
2. A structural member according to claim 1, wherein the interfacing member is of a material which is distinctively perceptibly different from the material of the shell.
3. A structural member according to claim 1 or claim 2, wherein the interfacing member is of metal.
4. A structural member according to claim 1 or claim 2 or claim 3, wherein the interfacing member is bonded to the spar with a bond of greater shear strength than the bond between the interfacing member and the shell.
5. A structural member according to any one of the preceding claims, wherein the interfacing member has holes in it.
6. A composite propeller substantially as described with reference to Figure 1 or Figure 2 of the accompanying drawings.
**WARNING** end of DESC field may overlap start of CLMS **.
Claims (6)
1. A composite structural member comprising a lightly-loaded shell formed of a fibre-reinforced synthetic plastics material attached to and supported by an internal load-carrying spar made of higher grade material chosen t6 give the required load-carrying capability, and wherein an interfacing member is provided between the shell and the load-carrying spar.
2. A structural member according to claim 1, wherein the interfacing member is of a material which is distinctively perceptibly different from the material of the shell.
3. A structural member according to claim 1 or claim 2, wherein the interfacing member is of metal.
4. A structural member according to claim 1 or claim 2 or claim 3, wherein the interfacing member is bonded to the spar with a bond of greater shear strength than the bond between the interfacing member and the shell.
5. A structural member according to any one of the preceding claims, wherein the interfacing member has holes in it.
6. A composite propeller substantially as described with reference to Figure 1 or Figure 2 of the accompanying drawings.
Priority Applications (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB27064/75A GB1561328A (en) | 1975-08-26 | 1975-08-26 | Construction of composite structural members such as propeller blades |
| DE2638689A DE2638689C3 (en) | 1975-08-26 | 1976-08-26 | Composite component, especially propeller blade |
| FR7625817A FR2322006A1 (en) | 1975-08-26 | 1976-08-26 | PERFECTIONS RELATED TO THE CONSTRUCTION OF REINFORCED ELEMENTS SUCH AS PROPELLER BLADES |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB27064/75A GB1561328A (en) | 1975-08-26 | 1975-08-26 | Construction of composite structural members such as propeller blades |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB1561328A true GB1561328A (en) | 1980-02-20 |
Family
ID=10253581
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB27064/75A Expired GB1561328A (en) | 1975-08-26 | 1975-08-26 | Construction of composite structural members such as propeller blades |
Country Status (3)
| Country | Link |
|---|---|
| DE (1) | DE2638689C3 (en) |
| FR (1) | FR2322006A1 (en) |
| GB (1) | GB1561328A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0169191A2 (en) * | 1984-07-16 | 1986-01-22 | KUNEX Türenwerk Gesellschaft m.b.H. | Sound-deadening flat construction element |
| EP1832691A1 (en) * | 2006-03-11 | 2007-09-12 | W. Döllken & Co GmbH | Support strip for a composite panel |
-
1975
- 1975-08-26 GB GB27064/75A patent/GB1561328A/en not_active Expired
-
1976
- 1976-08-26 FR FR7625817A patent/FR2322006A1/en active Granted
- 1976-08-26 DE DE2638689A patent/DE2638689C3/en not_active Expired
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0169191A2 (en) * | 1984-07-16 | 1986-01-22 | KUNEX Türenwerk Gesellschaft m.b.H. | Sound-deadening flat construction element |
| EP0169191A3 (en) * | 1984-07-16 | 1987-06-03 | Kunex Turenwerk Gesellschaft M.B.H. | Sound-deadening flat construction element |
| EP1832691A1 (en) * | 2006-03-11 | 2007-09-12 | W. Döllken & Co GmbH | Support strip for a composite panel |
| WO2007104510A1 (en) * | 2006-03-11 | 2007-09-20 | W. Döllken & Co. GmbH | Support strip for a composite panel |
Also Published As
| Publication number | Publication date |
|---|---|
| FR2322006A1 (en) | 1977-03-25 |
| FR2322006B3 (en) | 1979-05-25 |
| DE2638689B2 (en) | 1978-08-03 |
| DE2638689A1 (en) | 1977-03-10 |
| DE2638689C3 (en) | 1979-03-29 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PS | Patent sealed [section 19, patents act 1949] | ||
| 732 | Registration of transactions, instruments or events in the register (sect. 32/1977) | ||
| 732 | Registration of transactions, instruments or events in the register (sect. 32/1977) | ||
| PCNP | Patent ceased through non-payment of renewal fee |