Desing Fighter Aircraft

This paper concentrates on the design, analysis, and development of fixed-wing hand launch unmanned aerial vehicle (UAV). This flight can able to carry the payloads of 0.8. The design process involves the conceptual, preliminary, and detailed design. This paper involves the investigation of the aerodynamic characteristics over the wing to enhance the aerodynamic design of the UAV. This analysis includes estimating the best gliding ratio to increase the flight mission and attain the maximum altitude. This simulation will be performed for subsonic flow with Mach number 0.04202(14.3m/s). The manufacturing of the UAV is done using composite materials like glass fiber of both (1mm and 2 mm) thickness, carbon fiber of 2mm, and carbon rod is used for connecting the empennage to the fuselage. The detailed design has been done in CATIA V5 and the analysis of the wing has been done using XFLR, ANSYS (fluent).

This paper concentrates on the design, analysis, and development of fixed-wing hand launch unmanned aerial vehicles (UAV). This flight can able to carry payloads of 0.8. The design process involves the conceptual, preliminary, and detailed design. This paper involves the investigation of the aerodynamic characteristics over the wing to enhance the aerodynamic design of the UAV. This analysis includes estimating the best gliding ratio to increase the flight mission and attain the maximum altitude. This simulation will be performed for subsonic flow with Mach number 0.04202(14.3m/s). The manufacturing of the UAV is done using composite materials like glass fiber of both (1mm and 2 mm) thickness, carbon fiber of 2mm, and carbon rod is used for connecting the empennage to the fuselage. The detailed design has been done in CATIA V5 and the analysis of the wing has been done using XFLR, ANSYS (fluent).

The main objective of the paper is to present the main criteria for the selection of carbon fiber composite materials for fighter aircraft. Nowadays, more than ever, customers for fighter aircraft demands a highly maneuverable, agile aircraft that is reliable and easy to maintain. Composite materials are, besides metal alloys, the most important materials for aerospace application. Application of carbon fiber thermosets as airframe materials offersa significant weight and cost reductions in manufacturing process. In the last decades, such materials overcome more than 15% and 50% of the structural weight of civil and military aircraft, respectively. Weak points in the basic materials, i.e. fiber (strain, stiffness) and resin (low-viscosity) are now well known and improvements led to a new generation of carbon fiber composites. Several suppliers are offering in their chemical composition, mechanical properties and processing. This paper describes the selection criteria based on fighter aircraft components with respect to design and manufacturing requirements and presents a comparison of different carbon fiber composites.

Orang boleh bilang apa saja tentang kinerja Presiden Susilo Bambang Yudhoyono (SBY) selama hampir 10 tahun masa pemerintahannya. Tetapi, yang tak terduga dan tak banyak dibahas para pengamat politik, SBY tampaknya akan mewariskan industri pertahanan nasional yang mulai bangkit lagi. Industri pertahanan ini awalnya sudah dirintis, sebagai bagian dari industri strategis, oleh Menteri Negara Riset dan Teknologi BJ Habibie di bawah pemerintahan Presiden Soeharto.

This paper concentrates on the design, analysis, and development of fixed-wing hand launch unmanned aerial vehicle (UAV). This flight can able to carry the payloads of 0.8. The design process involves the conceptual, preliminary, and detailed design. This paper involves the investigation of the aerodynamic characteristics over the wing to enhance the aerodynamic design of the UAV. This analysis includes estimating the best gliding ratio to increase the flight mission and attain the maximum altitude. This simulation will be performed for subsonic flow with Mach number 0.04202(14.3m/s). The manufacturing of the UAV is done using composite materials like glass fiber of both (1mm and 2 mm) thickness, carbon fiber of 2mm, and carbon rod is used for connecting the empennage to the fuselage. The detailed design has been done in CATIA V5 and the analysis of the wing has been done using XFLR, ANSYS (fluent).

In this paper, multiple criteria decision making analysis technique, is presented for ranking and selection of a set of determined alternatives-fighter aircraft-which are associated with a set of decision factors. In fighter aircraft design, conflicting decision criteria, disciplines, and technologies are always involved in the design process. Multiple criteria decision making analysis techniques can be helpful to effectively deal with such situations and make wise design decisions. Multiple criteria decision making analysis theory is a systematic mathematical approach for dealing with problems which contain uncertainties in decision making. The feasibility and contributions of applying the multiple criteria decision making analysis technique in fighter aircraft selection analysis is explored. In this study, an integrated framework incorporating multiple criteria decision making analysis technique in fighter aircraft analysis is established using entropy objective weighting method. An improved integrated multiple criteria decision making analysis method is utilized to aggregate the multiple decision criteria into one composite figure of merit, which serves as an objective function in the decision process. Therefore, it is demonstrated that the suitable multiple criteria decision making analysis method with decision solution provides an effective objective function for the decision making analysis. Considering that the inherent uncertainties and the weighting factors have crucial decision impacts on the fighter aircraft evaluation, seven fighter aircraft models for the multiple design criteria in terms of the weighting factors are constructed. The proposed multiple criteria decision making analysis model is based on integrated entropy index procedure, and additive multiple criteria decision making analysis theory. Hence, the applicability of proposed technique for fighter aircraft selection problem is considered. The constructed multiple criteria decision making analysis model can provide efficient decision analysis approach for uncertainty assessment of the decision problem. Consequently, the fighter aircraft alternatives are ranked based their final evaluation scores, and sensitivity analysis is conducted.

In this paper, a neutrosophic multiple criteria decision analysis method is proposed to select stealth fighter aircraft. Neutrosophic multiple criteria decision analysis methods are used to analyze the neutrosophic environment and give results under uncertainty and incompleteness. Neutrosophic numbers are used to evaluate alternatives over a set of evaluation criteria in decision making problems. Finally, the proposed model is applied to a practical decision problem for selecting stealth fighter aircraft.

Defense and security are serious business, as they represent the integrity and dignity of a nation. It is understandable to assess military power and facilities as crucial to a nation"s defense, shown in the use of fighter airplanes. A fighter airplane serves as a window to represent nation"s values, philosophy and ideology; appeared through its design form and defense ability. The presented paper explores and compares 2 (two) types of fighter airplane, F-16 of US and SU-27 of Russia, in order to observe and characterize their design forms. Having acknowledged the characteristic of their design forms as tangible aspect of analysis, it is identified that this characteristic can be split into form design and numerical design. Comparative assessment of both fighter airplanes indicates that F-16 fighter airplane of US appears smaller than the SU-27 of Russia. The smaller size of F-16 form was meant to have superior maneuverability for air-to-air combat, while the size of SU-27 was meant to accommodate multi-tasking aspects of fighter airplane (air-to-air combat and interceptive act). As results, both airplane forms express different views and ideological perspectives. The F-16 of US shows great and superior ability to carry special task of becoming combat airplane (thrive to perfection), coming with a hefty price and catered for great quality. On the other hand, SU-27 of Russia shows a wider purpose and not necessarily has superior ability in order to carry diverse tasks of an airplane (multi-tasking), coming with a cheaper price and catered in a great quantity. Thus, it can be deduced that the American designer of fighter airplane tends to acknowledge specialization of military purpose compare to the Russian"s generalization of military purpose.

The Wind Rises (2013) is Hayao Miyazaki’s last film before he announced his retirement. The film is based on the life story of Jirō Horikoshi, who designed the Zero fighter jet during World War II. In the film, Miyazaki was influenced by Horikoshi, as well as by his father, who had a wartime factory that produced aircraft parts. Even though a fighter jet is at the center of the film, Miyazaki aims to show the design and production process of the aircraft as technological development, rather than a militarist one. After the movie was released, Miyazaki was criticized by different circles. South Korean audiences opposed the glorification of the designer of the warplane, one of the symbols of Japanese militarism, and the disregard for forced Korean workers to build these planes. On the other hand, the nationalists in Japan also accused Miyazaki of treason for emphasizing the futility of war in the film.

This paper concentrates on the design, analysis, and development of fixed-wing hand launch unmanned aerial vehicle (UAV). This flight can able to carry the payloads of 0.8. The design process involves the conceptual, preliminary, and detailed design. This paper involves the investigation of the aerodynamic characteristics over the wing to enhance the aerodynamic design of the UAV. This analysis includes estimating the best gliding ratio to increase the flight mission and attain the maximum altitude. This simulation will be performed for subsonic flow with Mach number 0.04202(14.3m/s). The manufacturing of the UAV is done using composite materials like glass fiber of both (1mm and 2 mm) thickness, carbon fiber of 2mm, and carbon rod is used for connecting the empennage to the fuselage. The detailed design has been done in CATIA V5 and the analysis of the wing has been done using XFLR, ANSYS (fluent). Keywords— Fixed-wing hand launch UAV, Design process, Aerodynamic characteristics, G...

In this paper, a neutrosophic multiple criteria decision analysis method is proposed to select stealth fighter aircraft. Neutrosophic multiple criteria decision analysis methods are used to analyze the neutrosophic environment and give results under uncertainty and incompleteness. Neutrosophic numbers are used to evaluate alternatives over a set of evaluation criteria in decision making problems. Finally, the proposed model is applied to a practical decision problem for selecting stealth fighter aircraft.

The DEFEXPO was conducted in Chennai. While the intentions of making in India are indeed timely and laudable,  there  are miles to go in terms of converting intentions in to actionable programme by involving the researchers, academia, private industry, SME/MSME and more importantly ensuring that there are no bottle necks in the processes. India has for long been driven by bureacratic hurdles and the paper addresses some of  these concerns.