Mini Unmanned Aerial Systems (UAV) - A Review of the Parameters for Classification of a Mini UAV.

In the recent years, Mini Unmanned Aerial Vehicle (UAV) has generated a lot of interest both in military and civilian applications. Contemporary innovations have seen the entry of Mini UAV into a wide range of hitherto fore unexplored domains. Advancement in computer systems, miniaturisation of electronics, artificial intelligence and composite materials is propelling the development of Mini UAV. Mini UAV is a class of UAV within the large family of unmanned systems categorised by a set of parameters. However, there are glaring inconsistencies and lack of uniformity in specifying the parameters which define a Mini UAV. The paper explores the factors which define a Mini UAV to establish itself as a distinct class. Based on the review of the recent literature and various manufacturer’s data of Mini UAVs, both fixed-wing and rotary-wing, categorisation of Mini UAV have been analysed considering functional requirements of operating altitude, endurance, operating range, maximum take-off weight and size

Experimental and Computational Evaluation of Five Hole Five Probe Flow Analyzer for Subsonic Wind Calibration

It is very essential to predict the flow and its related parameters to understand real life fluid flow. The real-life fluid problems are studied with wind tunnels which gives very efficient results in practice. But in the case of wind tunnel studies flow angularities plays crucial role. Flow angularity determination includes measurement of static pressure, dynamic pressure and inflow angles. Flow prediction even hold a very strong hand in design process. Designing and testing being the foundation of any process industry, flow measurements and its related parameters have to be well evaluated. In such cases, wind tunnels play important role and the researchers are usually dependent on wind tunnels to carry out experiments at different Mach numbers to obtain experimental results. It is mandatory to check the flow parameters and maturity rates including turbulence, flow angularity, strain, velocity, temperature and density distribution at the test section before testing a model. The flow field and degree of maturity within the test section can be analysed with any instrument that will provide a flow field data diagram of test parts. In this paper, the performance evaluation and truthiness of five-hole five probe flow analyser is being evaluated computationally and experimentally at various Mach Numbers

Comparative study on performance accuracy of three probe and five probe flow analysers for wind tunnel testing

In the field of inviscid fluid flow studies, the theoretical concept has to be developed even more. In order to make it possible, it is very important to supplement the concepts with strong experimental results. While performing experimentation, various accepts of design can be determined with factors influencing the and also required modification can be recommended in a more systematic and economic manner. Also, the aim objective of the experiment is to extend the underlying theory and to produce new designs with improvements that can be great support to the advancement in technology. In experimental analysis, wind tunnels are used for the flow analysis over a flying object to be tested. Analyzing the flow plays a predominant role in aerodynamics study. The flow in the test section has to be uniformly streamlined and need to be parallel to the axis of the wind tunnel. The change in flow properties inside the tunnel with respect to the time should be negligible. So, before conducting a test process, calibration of wind tunnel has to be done. Normally, calibration of the subsonic wind tunnel is done by the Pitot static tube. It has the limitations of deprived accuracy and misalignment of the probe with the flow direction. Therefore, new calibrating instruments are proposed by overcoming the limitations of the Pitot static tube. In this paper, experimentation using wind tunnels has been discussed and the truth flow analysis of a low-speed open-circuit wind tunnel has been recorded using two different instruments namely three probe flow analyser and five probe flow analyser respectively. Also, the results obtained have been compared with the data obtained using a pitot static probe

Albatross and Falcon inspired Bionic UAV: An Aerodynamic Analysis

The drone industry yearns for enhanced aerodynamic performance. In order to achieve this feat, researchers and engineers are trying to mimic the natural flyers due to their aerodynamic optimality. One such flyer, the Albatross is an inspiration for many marine drones due to its planform and aerodynamic efficiency. The wing of the plan form is designed and simulated to study its properties. The Bell-Shaped Lift Distribution is incorporated for higher efficiency and elimination of the total downwash produced in case of an Elliptical Lift Distribution. A blended wing body inspired by the Falcon is used for smoother airflow interactions. Furthermore, a tilt-rotor design provides an efficient combination of hovering and cruising modes of flight. Design choices and changes are discussed and tested to obtain an efficient tilt-rotor UAV inspired by the Albatross

Hover performance analysis of coaxial Mini unmanned aerial vehicle for applications in mountain terrain

Due to its compactness, agility, good hover performance, and ease of carriage, coaxial rotor Mini UAV is apt for various military and civilian applications in mountain terrain. This paper examines various factors to arrive at viable configurations of coaxial rotor Mini UAV for applications in mountain terrain. A consideration of the coaxial rotor Mini UAV to analyse the suitability for mountain terrain is presented. Coaxial rotor design is evaluated to assess the design requirements of mountain terrain. Various design parameters are analysed to arrive at viable design configurations for coaxial rotor Mini UAVs to operate in mountain terrain. Due to mechanical complexities, more than three blades per rotor for a small coaxial rotary wing aircraft is not recommended. The compact frame of the coaxial rotor Mini UAV is a key advantage, so rotor blades with a radius bigger than 1 m are not desirable. With a radius smaller than 1 m, a range of 0.9 m to 1.2 m, and an rotor speed between 900 RPM and 1200 RPM for 3-blade and 2-blade coaxial rotors, the Mini UAV offers a variety of options for applications in mountain terrain

Flight manoeuvring and safe flight visualization with the aid of wide-ranging scrutiny and automation software

This document guides to an efficient use of FDVCAS system. FDVCAS is a reconstruction, playback, interactive visualization tool, which collects, stores, processes, analyses and present the flight data in high fidelity graphical presentation in 2D and 3D format. It synchronizes and presents in both graphical and synthetic visual form to the extends of analysing the impact of the data on the system in 3D graphic animation. The existing process involves in capturing the data from different input sources and formats, analysing the features of the data monitoring is done manually in offline in a unsynchronized fashion, This is difficult, time consuming and requires highly skilled technical expertise as it is visualized in plain data form. The above standard procedures followed shall be integrated and automated with minimum intelligence to be built, in with the system. In order to analyse the flight data in a coherent way it is required to integrate both 2D and 3D form The proposed concept is the Development of a system with a single solution by providing data display, graphical charts and replay features with a sophisticated graphical user interface, which is super imposed on the outside window imagery. FDVCAS consists of Bypass data acquisition system, Outside Window Imagery (OWI) system with graphical analyser. Bypass data acquisition system receives data from aircraft recorder and transmits the data in engineering format to FDVCAS system. The OWI system has three main modules namely, 3D Visual module, GUI based Graphical analyser and Warning display module. The warnings and the graphical plots are super imposed on the 3D Visual