Design and Analysis of HAME UAV

After taking the Request for Proposals (RFP), initial rough weight sizing will be done. This will involve the estimation of gross take-off weight. The proposed requirements will be the baseline for the initial rough weight sizing. A layout of the UAV will be made along with the mission profile to fu

Project Title

Design and Analysis of HAME UAV

Project Area of Specialization

Mechanical Engineering

Project Summary

After taking the Request for Proposals (RFP), initial rough weight sizing will be done. This will involve the estimation of gross take-off weight. The proposed requirements will be the baseline for the initial rough weight sizing. A layout of the UAV will be made along with the mission profile to fulfil expectations. loiter airspeed predictions, wing planform geometry and power plant sizes estimates will be made. All components will be integrated to produce a rough sketch of a UAV. With a general drawing of the UAV, a more thorough estimation of the UAV’s parameters will be undertaken. This will include components weight estimation, lift and drag estimations in various operating conditions, engine estimation and aircraft aerodynamic evaluations. These estimations will allow us to validate the practicability of the initial rough layout, and our assumptions, and to make changes for design improvement. With this almost conceptual design will be done. Different optimization techniques like MDO, GA, and analytical techniques will be followed to get the same performance with the least material used and the least energy required. With the above data, we will have enough details to perform trade-off studies. Using the aerodynamics and propulsion equations, it will be possible to show the association between endurance and payload and their effect on the aircraft's maximum mass. The results of the above findings will help us to revise the UAV layout and specifications to design a better UAV matched to the proposed demands. With formally entering into the preliminary design phase a CAD model will be made.

Project Objectives

The expected deliverable of the project is as follows:

• Conceptual design of HAME UAV

• CAD model of baseline UAV

 • Design optimization using MDO

• Structural analysis of wing

Project Implementation Method

The main first goal is to make weights, aerodynamics, propulsion and performance modules. These modules can be low to high fidelity according to available resources. After getting these modules the next task is to integrate these modules like weights are being calculated in MATLAB, aerodynamics in ANSYS or TORNADO both are coupled so there should be a middleman by which MATLAB understands ANSYS and vice versa. Liaquat et al. used MS Excel as an integrator. The conceptual design selecting wing, horizontal and vertical tail and their control surfaces sizes, sweep, taper ratio and dihedral Angle is done. Fuselage length, diameter engine installation angle and thrust required are selected. Interaction between internal payload, fuel compartment and placement of landing gears and other design features are chosen. Although the level of detail in conceptual design is not very high, the interactions between all of the various components are so complex that developing a reliable conceptual design takes years of practice.  Raymer's approach being the latest and constantly updated provides a more enhanced design approach based on more data and new techniques. Unfortunately UAV data is still not compiled in the book. The parameters based on historical trends can be taken from baseline aircraft or a tailored technique can be applied. The data of UAVs for different parameters can be taken from different credible sources and the Same plots could be generated. Raymer's methods can also be used for parasitic drag, interference drag of components and induced drag estimation, detailed empirical relations for components weights, engine’s installation angle and position relations, propeller analysis using efficiency charts, ”industry-standard empirical cost equations, and physics-based equations for performance and sizing.”. These estimations and relations have been verified and tested in numerous studies over two decades, and these relations have been found quite authentic for most types of aircraft. A step by step methodology that can be followed is: Defining the objectives and constraints and deciding the design variables for a general overview. Airworthiness aspects and safety regulations such as following FAR as constraints to ensure realism. RFPs will also be the constraints. For design variables, Raymer categorises DVs into six primaries: • T/W or P/W (not variable if fixed-size engine) • W/S (wing loading) • AR (Aspect Ratio) • ?(Taper Ratio) • ? (Sweep angle) • t/c (thickness to chord ratio)

Benefits of the Project

Pakistan will have a reconnaissance UAV with medium endurance, and high altitude. With high altitudes, one can observe more ground area missions. Therefore, lesser missions or UAVs will be required. Pakistan will be capable of observing considerable hostile territory even flying in its airspace. It will allow preparing mission before hand by having the accessibility of terrain,and availability of hostile troops positions and arsenal

Technical Details of Final Deliverable

The expected deliverable of the project is as follows:

• Conceptual design of HAME UAV

• CAD model of baseline UAV 

• Design optimization using MDO

• Structural analysis of wing

Final Deliverable of the Project

HW/SW integrated system

Core Industry

Manufacturing

Other Industries

Education

Core Technology

Others

Other Technologies

Robotics

Sustainable Development Goals

Industry, Innovation and Infrastructure, Responsible Consumption and Production

Required Resources

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