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Shaw, Vikash
- Geometric Parameters Selection of a Multirole Fighter Aircraft
Abstract Views :273 |
PDF Views:7
Authors
Vikash Shaw
1,
S. K. Samal
1
Affiliations
1 Department of Aeronautical Engineering, Bhubaneswar Engineering College, Bhubaneswar, Odisha, IN
1 Department of Aeronautical Engineering, Bhubaneswar Engineering College, Bhubaneswar, Odisha, IN
Source
Technology Spectrum Review, Vol 2, No 2 (2017), Pagination: 21-24Abstract
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.References
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- The Flying Wing UAV Using Classical Control Theory
Abstract Views :460 |
PDF Views:0
Authors
Affiliations
1 Bhubaneswar Engineering College, Bhubaneswar, Odisha, IN
1 Bhubaneswar Engineering College, Bhubaneswar, Odisha, IN
Source
Technology Spectrum Review, Vol 3, No 1&2 (2018), Pagination: 1-4Abstract
This paper describes modeling design procedure of a flying wing UAV which is a tailless fixed wing aircraft and has no definite fuselage, with respect of the crew, payload and equipment being housed inside the main wing structure. In this thesis a 6 degree-of-freedom mathematical model describing the aircraft dynamics is first presented, then using these equations, the derivatives of the parameters and system identification of simplified, linear lateral and longitudinal models are estimated for the tailless aircraft. A detailed modeling procedure of flying wing UAV and stability analysis results using the linearized model at trim condition are represented. Finally, we have designed the flying wing UAV using classical control theory.Keywords
Control, Designe, Model, UAV.References
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