Wyniki wyszukiwania - BazTech

1

Cykl produkcyjny kompozytowego bezzałogowego statku powietrznego w technologii autoklawowej

Samoraj P., Sałaciński M., Leski A.

Prace Naukowe Politechniki Warszawskiej. Transport

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2017

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z. 116

241--250

PL

Bezzałogowe statki powietrzne (BSP) odgrywają coraz większą rolę w siłach zbrojnych, lotnictwie, rolnictwie i przemyśle. Statki te wykonywane są głównie z kompozytów. W Polsce, a nawet w krajach wysoko rozwiniętych produkująje niewielkie przedsiębiorstwa. Metody wytwarzania kompozytów opierają się głównie na metodzie kontaktowej - technologia mokra. W związku z tym parametry wykonywanych struktur często odbiegają od założeń konstrukcyjnych. Wobec powyższego przeanalizowano dostępne metody wykonywania struktur kompozytowych. Przy wyborze wzięto pod uwagę możliwe do osiągnięcia parametry wytrzymałościowe, powtarzalność technologiczną oraz wpływ czynnika ludzkiego. Wybrana metoda produkcji struktur kompozytowych opiera się na technologii prepreg z wykorzystaniem metody autoklawowej. Zaproponowano pięcio-etapowy cykl produkcyjny bezzałogowego statku powietrznego w konsorcjum Kompo-Tech złożonego z ITWL i WZL-1 S.A. w Dęblinie. Proces ten składa się z wykonania form negatywowych, makiety funkcjonalnej, form pozytywowych, form negatywowych wysokotemperaturowych oraz wytworzenia struktury bezzałogowego statku powietrznego. Artykuł zawiera charakterystykę poszczególnych procesów oraz problemy napotkane podczas ich realizacji, a także sposoby ich rozwiązania.

EN

Unmanned aerial vehicles are playing greater role nowadays in the armed forces, aircraft, agriculture and industry. These aircrafts are made mainly from composites. UAVs in Poland, and also in highly developed countries are manufactured by small companies. Processes of making composites are based on contact method - wet lay-up technology. Therefore parameters of produced structures often are different than constructional assumptions. To the above it was analyzed available methods of manufacturing of composite structures. During analyze it was considered parameters possible to achieve: strength, technological repeatability and impact of human factor. Chosen method of production of composites is based on prepreg technology with using autoclave method. It was proposed five-stage manufacturing cycle of UAV in consortium Kompo-Tech composed of ITWL and WZL-1 Inc. in Dęblin. This process consists of making of negative molds, test model, positive molds, negative molds for high temperatures and manufacturing of structure of aircraft. Article includes characteristic of each process and problems which appeared during realization and also ways of solution.

2

Use of a composite repair patches to repair the upper air intake flap for the MIG-29 aircraft engine

Sałaciński M., Stefaniuk M., Synaszko P., Lisiecki J.

Aviation Advances & Maintenance

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2017

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Vol. 40, Issue 2

101--114; 115--127

EN

The Composite Patch Bonded Repair (CPBR) is one of the most cost-efficient types of aircraft structure repair. In the CPBR, the damaged structure is reinforced by applying a composite patch. The boron-epoxy composite (BFRP) is a popular choice for these types of repair. The BFRP was utilized to repair the cracked resistance welding joints in the upper flap of the MiG-29’s RD-33 engine intake. In the present paper, the numerical results are shown, along with the comparative tests of the undamaged inlet flap, the damaged inlet flap and of the CPBR repaired inlet flap.

PL

Jednym z najbardziej ekonomicznych sposobów naprawy uszkodzonej struktury statku powietrznego jest jej wzmocnienie poprzez nałożenie na nią kompozytowego pakietu naprawczego – Composite Patch Bonded Repair (CPBR). Powszechnie stosowanym materiałem jest m.in. kompozyt epoksydowo-borowy (BFRP). Materiał ten został zastosowany do naprawy pęknięć połączenia zgrzewanego klapki górnego wlotu powietrza do silnika RD-33 samolotu MiG-29, przeprowadzonej w ITWL. Artykuł zawiera wyniki analiz numerycznych oraz badań porównawczych struktury oryginalnej nieuszkodzonej klapki, struktury uszkodzonej oraz struktury po wykonanej naprawie z zastosowaniem BFRP.

3

The Effect of Environmental Flight Conditions on Damage Propagation in Composite Sandwich Structure

Synaszko P., Sałaciński M., Kornas Ł.

Fatigue of Aircraft Structures

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2015

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Iss. 7

24--27

EN

The aim of the study was to determine the traceability of damage growth caused by inclusions of water in the composite sandwich structure. It was assumed that as a result of temperature changes during the flight and accompanying phase transformation, the zone containing water inclusions increases. The growth is caused by the destruction (mainly the tearing of walls) of the core. As part of the work, this assumption was verified experimentally. For the experiment to be successful it was necessary to simulate actual flight conditions. The simulation involved inducing phase transformations of water in the core cell as a function of time and temperature. Before and after the experiments the non-destructive tests using pulsed thermography were performed. The test results revealed an increase in the number of cells occupied by water. Adequate specimens were designed and manufactured. The study showed that cyclical changes in temperature affected the propagation of water in core sandwich structures. Further, it was found that the increase in the surface area of water-containing inclusions could be monitored using thermographic techniques.

4

Conception of New Air Target SZERSZEŃ-2

Samoraj P., Sałaciński M.

Fatigue of Aircraft Structures

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2015

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Iss. 7

47--51

EN

The project to introduce modifications to the air target SZERSZEŃ has been undertaken by the Air Force Institute of Technology. SZERSZEŃ has been used by the Polish Army for 10 years, during which time a number of modifications were introduced. Given this fact, it was decided to develop a new version of this UAV based on the experience gained during its maintenance and operation. Another aspect of this project is to focus on improving the repeatability of production by optimizing the technology processes. To achieve this aim the new instrumentation for the production of composite parts in prepreg technology was designed. The paper reviews the production possibilities for this aircraft using a new technology and presents the advantages of the modified construction and the new technology.

5

Using Sandblasting and Sol Gel Techniques for the Preparation of a Metal Surface and Their Effects on the Durability of Epoxy-Bonded Joints

Sałaciński M., Zabłocka M., Synaszko P.

Fatigue of Aircraft Structures

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2012

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Iss. 4

94--99

EN

The epoxy-bonded joints are widely employed in aerospace in the Composite Patch Bonded Repair (CPBR) method used for repair metallic and composite structures. The properties of epoxy usually meet the mechanical and environmental requirements, but the durability of bonded joints depends also on the surface preparation. The most common techniques used for the surface preparation are Forest Product Laboratory’s (FPL) technique and Phosphoric Acid Anodizing (PAA). Both methods ensure very good adhesion but they have some disadvantages. They require the application of toxic and aggressive acids, dangerous for the operator. Also, the use of acids for cleaning the surfaces can cause corrosion. The sandblasting treatment of metal surfaces ensures quite good adhesion. This technique requires neither specialist equipment nor the use of toxic substances. Recommended by the Royal Australian Air Force (RAAF) the technique is also used by the Air Force Institute of Technology. Sol Gel is a new product developed for the treatment of metal surfaces before bonding. It is not hazardous for the operator and it does not cause corrosion due to its specific chemical composition. The article describes the behavior of bonded joints between two metal surfaces prepared using sandblasting and Sol Gel. The investigations were carried out in various environment conditions according to the ASTM Standards.

6

The Effect of Cure Cycle Time on the Properties of Epoxy-Bonded Joints

Zabłocka M., Sałaciński M., Synaszko P., Kłysz S.

Fatigue of Aircraft Structures

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2012

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Iss. 4

157--161

EN

This paper presents the results of the study of the properties of epoxy-bonded joints. Depending on the parameters of cure cycles the epoxy adhesive film has got various mechanical properties. When it is possible to use cure parameters suggested in the data sheet of the adhesive film the best results are obtained. However, in aerospace applications the cure cycle depends on the thermal resistance of other aircraft elements including electrical equipment, cables, etc., and is different from the recommended in the data sheet. Composite Patch Bonded Repair (CPBR) is a special methodology, where the patch cure cycle and the bonding process must be carried out in one operation. The adhesive film cure cycle parameters depend on the prepreg cure cycle parameters. The purpose of this research is to define the influence of a prolonged cure cycle of the adhesive film on the bonded layer strength properties. The metal surface of the specimen has been prepared for bonding by sandblasting and the use of Corrosion Inhibiting Primer BR 127. The tests were performed with the use of Structural Adhesive Film AF 163-2 and two types of cure cycles: the cycle recommended by the data sheet - 121ºC/60 min and the prolonged one - 121ºC/105 min. After the cure cycle the thickness of the bonded layer was measured. Both specimens were comparatively tested during the following strength tests of the bonded layer: static breaking tests using the wedge and the shear strength investigations. The surface of the bonded layer was observed during the tests by an electronic microscope (100x, 200x), which made it possible to demonstrate the effect of the cure cycle on the porosity and observe the nature of the bonded layer damage – de-cohesive and de-adhesive.

7

Damage Detection and Size Quantification of FML with the Use of NDE

Dragan K., Kornas Ł., Kosmatka M., Leski A., Sałaciński M., Synaszko P., Bieniaś J.

Fatigue of Aircraft Structures

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2012

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Iss. 4

5--9

EN

Composite materials have been developed in recent years. A new generation of structural composite materials for advanced aircraft is Fibre Metal Laminates (FML). They are hybrid composites consisting of alternating thin layers of metal sheets and fiber-reinforced composite material. FMLs have both low weight and good mechanical properties (high damage tolerance: fatigue and impact characteristics, corrosion and fire resistance). Quality control of materials and structures in aircraft is an important issue, also for Fibre Metal Laminates. For FML parts, a 100% non-destructive inspection for internal quality during the manufacturing process is required. In the case of FML composites, the most relevant defects that should be detected by non-destructive testing are porosity and delaminations. In this paper, a number of different non-destructive methods for the inspection of Fibre Metal Laminates were studied. The possibility of quality control of manufactured FML laminates - detection of defects as well as the procedures and processes are presented and discussed.

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Inspection methods for quality control of fibre metal laminates in aerospace components

Dragan K., Bieniaś J., Sałaciński M., Synaszko P.

Kompozyty

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2011

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R. 11, nr 2

130-135

EN

Composite materials have been applied in aerospace structures in recent years. Presently, the new generation of structural composite materials for advanced aircraft are Fibre Metal Laminates (FML). They are hybrid composites consisting of alternating thin layers of metal sheets and fiber-reinforced composite material. FMLs have both low density and good mechanical properties (high damage tolerance: fatigue and impact characteristics, corrosion and fire resistance). The quality control of the materials and structures in aircraft is an important issue, also for FMLs. For FML parts, a 100% nondestructive inspection for the internal quality during the manufacturing process is required. In the case of FML composites, the most relevant defects that should be detected by non-destructive testing are porosity and delaminations. In this paper, the use of non-destructive different methods for the inspection of Fibre Metal Laminates were studied. The possibility of quality control of manufactured FML by means of defect detection procedures and processes are presented and discussed.

PL

Materiały kompozytowe, w szczególności w konstrukcjach lotniczych, odgrywają coraz większą rolę z uwagi na większe wartości wytrzymałości właściwej niż stopy aluminium, możliwość formowania dowolnych kształtów oraz odporność na przepalenia i korozję. Szczególnym typem konstrukcji kompozytowej o charakterze hybrydowym są tzw. włókniste laminaty metalowe (ang. Fibre Metal Laminates - FML). Wykonuje się je na bazie włókien szklanych, aramidowych z warstwami wytworzonymi z aluminium (np. GLARE - Glass ALuminum REinforced) lub tytanu. Laminaty FML są już stosowane m.in. w konstrukcji płatowca samolotu Airbus A-380. Pomimo szeregu zalet takich materiałów w trakcie wytwarzania lub eksploatacji mogą powstać wady produkcyjne lub uszkodzenia eksploatacyjne wpływające na trwałość konstrukcji, w której zostaną zastosowane. W artykule przedstawiono podejście do badań takich materiałów wykonanych z FML z wykorzystaniem badań nieniszczących metodami: ultradźwiękową i prądów wirowych. Ponadto pokazano wyniki badań z omówieniem konieczności wykonywania badań i zaletami/wadami poszczególnych metod.

9

Monitoring of Crack Growth in a Structure Under a Composite Patch

Sałaciński M., Synaszko P., Stefaniuk M., Dragan K.

Fatigue of Aircraft Structures

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2011

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Iss. 3

103--111

EN

In civil as well as in military aviation, boron, carbon and aramid fiber reinforced composites are employed for the repair of metal structures. After such composite bonded repairs, the monitoring of the repaired structure along with the composite patch and its bond is necessary. The paper describes the possibilities of utilizing NDT methods for periodical check-ups and examinations. Also, a novel approach to continuous monitoring of the repaired structure is presented.

10

Bonded Joint Monitoring of The Composite Aerospace Structures with The Use of Nde and Shm Approach

Dragan K., Synaszko P., Sałaciński M., Latoszek A.

Fatigue of Aircraft Structures

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2011

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Iss. 3

16--21

11

Wykrywanie korozji w strukturze statecznika pionowego samolotu MiG-29

Synaszko P., Dragan K., Bochenek D., Sałaciński M.

Logistyka

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2010

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nr 4

CD-CD

PL

Artykuł przedstawia problem wykrywania korozji w nakładkach mocowania statecznika pionowego samolotu MiG-29. W celu zapewnienia dostępu do badanych powierzchni niezbędny był demontaż stateczników pionowych. Autorzy przedstawili część wyników badań, zaprezentowali podejście do badań, oraz wysunęli propozycję usprawnienia badań w przyszłości wykluczając konieczność demontażu stateczników.

EN

The article is showing the problem of detecting the corrosion in interface of fixing an vertical stabilizer of MiG- 29. Disassembly of vertical stabilizers was necessary for providing acces to inspected surfaces. Authors described the part of results, they presented the approach of examinations, as well as they put the proposal to other technique examinations forward in the future excluding the necessity of disassembly of stabilizers.