Technology Spectrum Review

Chinmayee Panigrahi ¹, S. K. Samal ¹

Affiliations
1 Bhubaneswar Engineering College, Bhubaneswar, Odisha, IN

Abstract

This paper summarizes the design, analysis and experimental evaluation of Active Aeroelastic Wing (AAW) technology and is need over conventional design process. The results provide control derivatives of control surface of an aircraft by using AAW design. Also the result indicates some different behaviour which was not expected while doing the conceptual design. It is multidisciplinary study in engineering technology. This is a new technology in the area of structural design approach. This is a intergradations of flight control, aerodynamic control, and structural performance.

Keywords

AAW, Aeroelasticiy, Conventional Approach, Wind Tunnel Model.

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S. K. Singh ¹, S. K. Samal ¹, S. Dash ¹

Affiliations
1 Aeronautical Department, Bhubaneswar Engineering College, Bhubaneswar, Odisha, IN

Abstract

In this paper the effect of spiroid winglet on aerodynamic efficiency was investigated. A sweptback and tapered wing with NACA 0015 airfoil section was considered as base geometry. Above wing is modified by providing spiroid winglet at the tip of wing. Velocity of 35 m/s was taken to simulate this. CFD code was use to carry out the computation. The simulated results were compared with experimental result to validate the CFD code. In this process tangential velocity, lift coefficient and drag coefficient were computed initially. The simulations obtained from the CFD code show a very good agreement with the experimental results. The aerodynamics parameters were calculated at different geometric angle of attack (4°, 8°, 12° and 16°). The numerical results were compared with the result of base line model to find out the effect of spiroid winglet. It was observed the drag is reduced by using spiroid winglet.

Keywords

Tip-Vortex, Spiroid Winglet, Drag, Wingtip, Induced Drag.

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S. Sahoo ¹, P. Behera ¹, S. Dash ¹, S. K. Samal ¹

Affiliations
1 Aeronautical Department, Bhubaneswar Engineering College, Bhubaneswar, Odisha, IN

Abstract

Ever since the Wright brothers have invented the piston engine airplane in 1903, tremendous amounts of time and effort were put into researching to build airplanes. With time the design had changed and the propulsion medium were developed. The desire for hypersonic flight necessitated the supersonic combustion ramjet engine potentially expanding the speed envelope to the Mach 7 range. The pulse jet work without any rotation device like compressor and turbine. Also it does not have any separate enclosed chamber for combustion. In this report we it is discussed about Ramjet Engine. This include history of Ramjet engine along with the important time stamps where the ramjet engine had grown. Also it is discussed about working principle of Ramjet along the operational mechanism. And a ramjet model was fabricated and the calculation were made for this model.

Keywords

Ramjet, Thrust, Weight to Power Ratio.

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A. Sahoo ¹, S. K. Samal ¹

Affiliations
1 Aeronautical Department, Bhubaneswar Engineering College, Bhubaneswar, Odisha, IN

Abstract

Surveying is the most essential part has to taken before taking any action on the earth-objects. It helps in recognizing the object with all its physical and chemical properties. The surveying object was to make a site map and locate the different positions of the objects on the earth surface. The map can be drawn with suitable scale to compare. This can show the natural resources and its uses of a different country like towns, villages, roads, railways, rivers, etc. Maps also include details of different engineering works, such as roads, railways, irrigation canals, etc. Starting from civil to geology all are undergoing surveying and mapping to make their effective.

Keywords

Ariel, Control, Mapping, Resolution, UAV, Un-Manned.

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Rajan Lakra ¹, Swagat Prasad Das ¹, S. K. Samal ¹

Affiliations
1 Department of Aeronautical Engineering, Bhubaneswar Engineering College, Bhubaneswar, Odisha, IN

Abstract

Composite propellants based on Ammonium Perchlorate (AP) as oxidizer are in major role in solid rocket. However, because of their high toxic exhaust, it is not suggested for global environmental pollution issue. Therefore, researchers want to replace AP based propellants with clean exhaust propellant. Ammonium Nitrate (AN) has the properties which can satisfy the present environmental need in the field of propellant. However, the disadvantage for the application of AN-as solid propellant oxidizer is its dimensional instability in different temperature ranges due to phase transformation which causes change of volume and porosity of the propellant grain. This was be resolved by the use of Phase Stabilized Ammonium Nitrate (PSAN) for propellant processing. Synthesized mixed metal oxides were used to enhance burning rate. These propellant samples were then tested for measuring burn rate in a Crawford High Pressure Strand Burner and thermal degradation studies carried out Simultaneously in Thermal Analyzer (STA). It is observed that the thermal decomposition and burn rate of the propellant is maximum by adding anyone of the mixed metal oxide catalyst among 3 different catalysts. In this research the different samples are formulated to test and get results. It has been observed that only two propellants burnt properly as compared to other propellants taken for the analysis.

Keywords

Burn Rate, Catalytic Combustion, Preparation of Catalyst, Preparation of PSAN, Solid Propellants, Thermal Decomposition.

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Vikash Shaw ¹, S. K. Samal ¹

Affiliations
1 Department of Aeronautical Engineering, Bhubaneswar Engineering College, Bhubaneswar, Odisha, IN

Abstract

Our project is to design a multirole fighter jet aircraft. A multirole fighter jet aircraft is an aircraft designed to perform different roles in warfare. The air-to-air combat role has been normally performed by fighter aircraft. In addition, a multirole fighter jet aircraft has secondary roles such as air-to-surface attack, intercepting, reconnaissance, escorting and air cover. The term multirole has been reserved for aircraft designed with the aim of using a common airframe for multiple tasks where the same basic airframe is adapted to a number of differing roles. The main motivation for developing multirole aircraft is cost reduction in using a common airframe. The project report comprises of a literature survey of about 10 fighter aircrafts. After this an appropriate aerofoil is selected and its important parameters are computed. Then, performance graphs are drawn and a 3-view diagram of the aircraft is drawn. Finally, model is made and tested.

Keywords

Fighter, Multirole, Span, Thrust to Weight.

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Jaydev Samal ¹, Kali Prasad Samantra ¹, Satyajit Pat ¹, Amit Nayak ¹, S. K. Samal ¹

Affiliations
1 Bhubaneswar Engineering College, Bhubaneswar, Odisha, IN

Abstract

An idea was carried out on an open cavity having a free stream Mach number of 0.8. The main objective of the present study is to design a passive venting that connects the high pressure region on the rear wall to a low pressure region downstream of the cavity. The baseline condition shows that the cavity flow oscillate with the total amplitude of 155 m. The vortex clipping which is responsible for the self-sustained nature of the cavity flow and the corresponding time history of the pressure on the cavity rear wall is discussed. A cross correlation analysis was carried out between the pressure history at the points on the rear wall of the cavity and the ones on the wall downstream of the cavity. Two points that defines the passive venting were identified based on the rear wall Overall Sound Pressure Level (OASPL) and the minimum time lag computed by cross correlation. The venting is shown to reduce the cavity oscillations and the rear wall pressure is shown to reach a steady state value which is desired in the perception of low cavity noise that can be used to reduce the structural loads and the acoustic loads on electronic components kept near the cavity.

Keywords

Bay, Cavity, Combat, Venting.

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S. K. Samal ¹

Affiliations
1 Bhubaneswar Engineering College, Bhubaneswar, Odisha, IN

Abstract

This paper provides the procedure to calculate the sizing of wing, flap and airfoil selection. In this a subsonic jet trainer was taken for case study, for which above sizing were done. Initially symmetric and cambered airfoil were selected to find out suitable airfoil for this type of aircraft. Lift and drag coefficient were estimated for better performance to select the wing section. NACA three different series (Five digit, 1-series and 6-series) are taken for the calculation part. All the calculation were done for the velocity of 277.78 m/s (Reynold No of 8.45 x 10⁶).

Keywords

Airfoil, NACA, Wing.

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Sushmita Nath ¹, Debajani Behura ¹, Kshirod Kumar Palai ¹, Swagat Dash ¹, S. K. Samal ¹

Affiliations
1 Bhubaneswar Engineering College, Bhubaneswar, Odisha, IN

Abstract

Winged animals cause a considerable measure of inconvenience in airplane terminals particularly amid take off and arriving of aircrafts. Rate of the fledging hitting the airship is called winged creature strike. A little feathered creature, if gets struck inside the engine can cause genuine outcomes like losing the whole aircraft, travelers and its team. It can once in a while harm the flying machine to significant degree. Thus, it is critical to distinguish any nearness of flying creature inside the range indicated. On the off chance that winged creatures are identified, they must be diverted so they would not come into the way of the flying machine. One can utilize water stream as a redirector framework since it is an innocuous approach to divert the wing creatures.

Keywords

Birds, Deflection.

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