KR20030080456A - Aircraft propeller manufacturing method - Google Patents

Aircraft propeller manufacturing method Download PDF

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Publication number
KR20030080456A
KR20030080456A KR1020020019073A KR20020019073A KR20030080456A KR 20030080456 A KR20030080456 A KR 20030080456A KR 1020020019073 A KR1020020019073 A KR 1020020019073A KR 20020019073 A KR20020019073 A KR 20020019073A KR 20030080456 A KR20030080456 A KR 20030080456A
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KR
South Korea
Prior art keywords
propeller
epoxy resin
resin
metal plate
make
Prior art date
Application number
KR1020020019073A
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Korean (ko)
Inventor
송호엽
Original Assignee
송호엽
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Publication date
Application filed by 송호엽 filed Critical 송호엽
Priority to KR1020020019073A priority Critical patent/KR20030080456A/en
Publication of KR20030080456A publication Critical patent/KR20030080456A/en

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C39/00—Shaping by casting, i.e. introducing the moulding material into a mould or between confining surfaces without significant moulding pressure; Apparatus therefor
    • B29C39/02—Shaping by casting, i.e. introducing the moulding material into a mould or between confining surfaces without significant moulding pressure; Apparatus therefor for making articles of definite length, i.e. discrete articles
    • B29C39/10—Shaping by casting, i.e. introducing the moulding material into a mould or between confining surfaces without significant moulding pressure; Apparatus therefor for making articles of definite length, i.e. discrete articles incorporating preformed parts or layers, e.g. casting around inserts or for coating articles
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C39/00—Shaping by casting, i.e. introducing the moulding material into a mould or between confining surfaces without significant moulding pressure; Apparatus therefor
    • B29C39/003—Shaping by casting, i.e. introducing the moulding material into a mould or between confining surfaces without significant moulding pressure; Apparatus therefor characterised by the choice of material
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
    • B29K2027/00—Use of polyvinylhalogenides or derivatives thereof as moulding material
    • B29K2027/06—PVC, i.e. polyvinylchloride
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
    • B29K2063/00—Use of EP, i.e. epoxy resins or derivatives thereof, as moulding material
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
    • B29L2031/00—Other particular articles
    • B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
    • B29L2031/3076—Aircrafts
    • B29L2031/3085—Wings

Landscapes

  • Laminated Bodies (AREA)

Abstract

PURPOSE: A method for manufacturing a propeller for an airplane is provided to minimize the contraction of the propeller and to improve hardness and strength by using a mixture of epoxy resin, polyvinyl chloride powder, and alumina powder. CONSTITUTION: A method for manufacturing a propeller for an airplane comprises the steps of: mixing epoxy resin, polyvinyl chloride powder, and alumina powder into synthetic epoxy resin(1); inserting a steel plate(2) into the center of the propeller; molding epoxy resin into the propeller.

Description

비행기 프로펠라 제작공법{omitted}Airplane propeller manufacturing method {omitted}

본 발명은 비행기에 사용되는 프로펠라 제작 방법에 관한 것이다.The present invention relates to a method for manufacturing a propeller used in an airplane.

에폭시 배합 수지를 이용하여 형틀에 주형을 하는 방법으로 에폭시 수지에 여러 가지 고분자를 배합하여 경화시켜 프로펠라를 제작하는 방법으로 지금까지의 프로펠라 제작 방법은 여러 가지 방법이 있으나 현재까지는 경비행기 프로펠라에있어서는 나무로 가공하여 코팅시키는 방법과 불포화 폴리에스텔 수지로 적층하여 만드는 제작 방법이 있으나 이 방법들은 여러 가지 결점이 있다. 나무로 가공하여 만드는 방법은 우기나 일기가 습하고 건조함에 따라 변형이 생기고, 재질이 너무 약하고 불포화 폴리에스텔 수지로 적층시키는 방법은 불포화 폴리에스텔 수지의 수축율이 심하여 두껍게 제작시 변형이 생기고 재질이 너무 약하고 얇게 제작시 프로펠라의 고속 회전시 프로펠라의 떨림과 잡음으로 인하여 양력을 제대로 얻을수 없다. 또한 비철 금속주조 방법은 주조시 금속의 수축율 때문에 프로펠라 날개의 얻고자 하는 곡면을 얻지 못하는 결점이 있다.It is a method of casting mold on mold using epoxy compounding resin. It is a method of making propellers by mixing various polymers in epoxy resin and curing. Until now, there are many methods of making propellers. There is a method of processing and coating and a method of manufacturing by laminating with an unsaturated polyester resin, but these methods have various drawbacks. The method of processing with wood makes deformation as the rainy season or weather is wet and dry, and the material is too weak, and the method of laminating with unsaturated polyester resin shows that the shrinkage of unsaturated polyester resin is so severe that the deformation is too thick and the material is too weak. In case of thin production, the propeller may not be properly lifted due to vibration and noise of the propeller during high speed rotation of the propeller. In addition, the non-ferrous metal casting method has a drawback in that it is impossible to obtain a curved surface of the propeller blade due to shrinkage of the metal during casting.

그러나 본 고안은 에폭시 수지와 PVC가루와 산화알루미나 가루를 배합하여 그 수축율을 최소화 하였고 경도와 강도가 우수하고 가볍다.However, the present invention minimizes the shrinkage rate by combining epoxy resin, PVC powder and alumina powder, and its hardness and strength are excellent and light.

프로펠라의 날개 중심부(2)에 금속판을 넣어 수지와 금속의 상호 보완 작용을 극대화 시키고 프로펠라의 중심부에 들어가는 금속판(3)에 구멍을 만들어 수지와 금속판의 완전 접착 성질의 불합리한 점을 고려 금속판의 구멍을 만듬으로서 프로펠라에 수지와 프로펠라의 내부의 금속판과의 접합성을 한층 더 극대화 시킴으로서 프로펠라의 강도를 높일 뿐만 아니라 무게도 줄일 수 있다.Put the metal plate in the center of the propeller wing (2) to maximize the complementary action of the resin and metal, and make a hole in the metal plate (3) entering the center of the propeller to make the hole of the metal plate in consideration of the irrationality of the perfect adhesive property of the resin and the metal plate. In addition, the propeller can be further strengthened and the weight can be reduced by further maximizing the bond between the resin and the metal plate inside the propeller.

또한 프로펠라 외형(5)에 도금을 하여 프로펠라의 경도와 강도를 극대화 시킨 발명품이다.In addition, it is an invention that maximized the hardness and strength of the propeller by plating on the propeller outer shape (5).

본 발명은 비행기 프로펠라를 만드는 공법으로서 경비행기 프로펠라는 지금까지 나무나 불포화 폴리에스텔 수지로 만들어 나무로 만든 프로펠라는 일기의 변동에 따라 변형이 있고 또한 불포화 폴리에스텔 수지로 적층시키는 방법이 있으나 나무와 같은 두께로 만들면 불포화 폴리에스텔 수지의 수축 변형 때문에 얻고자 하는 모형을 얻을 수 없어 어려움이 있다. 폴리에스텔 수지로 얇게 만들면 프로펠라의 떨림으로 인하여 좋은 양력을 얻을 수 없었다. 본 발명은 이와 같은 문제점을 완전히 해결하는 기술적인 과제를 해결하였다. 또한 경비행기의 가벼운 조건을 고루 해결 하였다.According to the present invention, a propeller made of airplane propeller is made of wood or unsaturated polyester resin, and the propeller made of wood has been modified according to the change of diary and also laminated with unsaturated polyester resin. If it is made of resin, it is difficult to obtain the model to be obtained because of shrinkage deformation of unsaturated polyester resin. When thinned with polyester resin, good lift could not be obtained due to the vibration of the propeller. The present invention solves the technical problem of completely solving this problem. It also solved the light condition of light aircraft.

제 1 도는 본 고안의 프로펠라의 정면도1 is a front view of the propeller of the present invention

제 2 도는 본 고안의 A-A 단면도2 is a cross-sectional view of the present invention A-A

제 3 도는 본 고안의 프로펠라 제품 중앙에 위치한 금속판의 모형3 is a model of the metal plate located in the center of the propeller product of the present invention

제 4 도는 본 고안의 B-B 단면도의 상세도4 is a detailed view of the B-B cross-sectional view of the present invention

제 5 도는 제 3 도의 A-A 단면도의 상세도5 is a detailed view of the A-A cross-sectional view of FIG.

＜도면의 주요 부분에 대한 부호설명＞<Code Description of Main Parts of Drawing>

1.프러펠라의 외형 합성수지 부분 2.프로펠라 안에 내장된 금속판1. Outer synthetic resin part of propeller 2. Metal plate embedded in propeller

3.프로펠라 안에 내장된 금속판 구멍 4.프로펠라 장작구 금속 봉구3. Metal plate hole inside propeller 4. Propeller wood tool metal fittings

5.프로펠라의 외형 도금층5.Exterior plating layer of propeller

본 발명은 에폭시 수지와 PVC가루 산화알루미나를 배합하여 가볍고 고강도인 수지를 만들어 비행기 프로펠라 중심부(2)에 철판을 넣어 형틀에 주형하여 비행기 프로펠라를 만드는 구성이다.The present invention is a configuration to make a plane propeller by mixing the epoxy resin and PVC powdered alumina to make a light and high-strength resin to put a steel plate in the center of the plane propeller (2) to mold.

프로펠라 중심부의 철판 날개(3)에 구멍을 뚫어 에폭시수지와 철판의 접합을 최대로 살린 비행기 프로펠라를 만드는 기술적인 공법이다.It is a technical method to make a plane propeller that makes the most of the bonding between the epoxy resin and the iron plate by making a hole in the iron plate wing (3) in the center of the propeller.

이상에서와 같이 본 발명에 의하면 비행기 프로펠라의 중요부분(1)날개의 곡선면을 수축이 없는 고강도의 수지로 형틀에 주형하여 프로펠라 중심부에 들어가는 금속판(2)을 넣어 수지에서 얻을 수 없는 인장강도를 보강하고 금속에서 얻을 수 없는 프로펠라 날개의 곡선면을 쉽게 얻을 수 없는 것을 본 발명에서는 얻는 효과가 있다.As described above, according to the present invention, a critical portion (1) of the airplane propeller is molded into a mold with a high-strength resin having no shrinkage, and a metal plate (2) entering the center of the propeller is put in the mold to obtain a tensile strength that cannot be obtained from the resin. In the present invention, it is possible to easily obtain curved surfaces of propeller blades that cannot be reinforced and obtained from metal.

Claims (2)

에폭시수지55％ PVC가루30％ 산화알루미나 15％ 배합하여 고강도의 에폭시수지를 만들어 비행기 프로펠라를 제작하는 재료로 쓰인다.Epoxy resin 55% PVC powder 30% Alumina oxide 15% It is used as a material to make airplane propeller by making high strength epoxy resin. 비행기 날개 중심부에 날개 모형의 금속판을 만들어 넣고 그 금속판에 일정한 부분 여러곳에 구멍을 만들어 무게도 줄이고 에폭시 수지와 금속판의 접합을 최대로 증대시키고 비행기 프로펠라 외부에 도금을 하여 경도와 인장 강도를 최대로 높이는 방법In the center of the aircraft wings, make a metal model of the wing model and make holes in several parts of the metal plate to reduce the weight, maximize the bond between the epoxy resin and the metal plate, and plate the outside of the airplane propeller to maximize the hardness and tensile strength. Way
KR1020020019073A 2002-04-08 2002-04-08 Aircraft propeller manufacturing method KR20030080456A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
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KR1020020019073A KR20030080456A (en) 2002-04-08 2002-04-08 Aircraft propeller manufacturing method

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Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5341382A (en) * 1976-09-29 1978-04-14 Oki Electric Ind Co Ltd Manufacture of base material having metal cores
JPS56171099U (en) * 1980-05-20 1981-12-17
US4608404A (en) * 1983-06-30 1986-08-26 Union Carbide Corporation Epoxy compositions containing oligomeric diamine hardeners and high strength composites therefrom
JPH036241A (en) * 1989-05-31 1991-01-11 Tonen Corp High-strength high-modulus hybrid prepreg
JPH05245997A (en) * 1992-03-03 1993-09-24 Koei Chem Co Ltd High strength damping composite laminate

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5341382A (en) * 1976-09-29 1978-04-14 Oki Electric Ind Co Ltd Manufacture of base material having metal cores
JPS56171099U (en) * 1980-05-20 1981-12-17
US4608404A (en) * 1983-06-30 1986-08-26 Union Carbide Corporation Epoxy compositions containing oligomeric diamine hardeners and high strength composites therefrom
JPH036241A (en) * 1989-05-31 1991-01-11 Tonen Corp High-strength high-modulus hybrid prepreg
JPH05245997A (en) * 1992-03-03 1993-09-24 Koei Chem Co Ltd High strength damping composite laminate

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