Kamlesh Kumar

Manipal Academy of Higher Education, Aeronautical and Automobile Department, Faculty Member

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Simple & Cool...I do not like politics in career...............
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Supervisors: Prof. J Dey, Dr. SN Omkar, V Surendranath, and Prof. D Ghose
Phone: 9901249743
Address: Kamlesh Kumar
ME-Aerospace Engg IISc Bangalore(Aug 2008-July 2010)

BE-Electrical Engg (NIT Patna)(Aug 2003-June 2007)

Project Engineer @ OCWT Aerospace Engg Dept IISc

Associate Consultant @ Robert Bosch Coimbatore

Scientist @ Brigosha Tech Private Ltd

Dept. of Aeronautical and Automobile Engg,
MIT Manipal
Karnataka-576104
INDIA

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Judith L Green

University of California, Santa Barbara

Steven Pinker

Harvard University

Andreas Umland

National University of "Kyiv-Mohyla Academy"

Don Ross

University College Cork

Javier Díaz Noci

Pompeu Fabra University

Katherine Butler Schofield

King's College London

Bob Jessop

Lancaster University

David Seamon

Kansas State University

Egil Bakka

Norwegian University of Science and Technology

Armando Marques-Guedes

UNL - New University of Lisbon

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Books by Kamlesh Kumar

Aviation Visual Perceptron

Blackburn J.A. Modern Instrumentation for Scientists and Engineers (Springer, 2001)(0387950567)

Microprocessor and Microcontroller

Digital Electronics

Principle of Flight Simulation

Electric_Machinery_Fundamentals_4th_Edition

Teaching Documents by Kamlesh Kumar

Application of Digital Data Bus in Aerospace

Introduction to MATLAB & SIMULINK

Control Systems

Control Systems for Aerospace Engineer

MATLAB & SIMULINK for Aerospace Engineering

Modeling and Simulation of Micro/Mini Air Vehicle and Unmanned Air Vehicle

Navigation, Guidance & Control

Navigation Systems

Introduction to Avionics

My Presentation at MIT Manipal

B-737 Linear Autoland Simulink Model

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Aviation Visual Perceptron

Blackburn J.A. Modern Instrumentation for Scientists and Engineers (Springer, 2001)(0387950567)

Microprocessor and Microcontroller

Digital Electronics

Principle of Flight Simulation

Electric_Machinery_Fundamentals_4th_Edition

Application of Digital Data Bus in Aerospace

Introduction to MATLAB & SIMULINK

Control Systems

Control Systems for Aerospace Engineer

MATLAB & SIMULINK for Aerospace Engineering

Modeling and Simulation of Micro/Mini Air Vehicle and Unmanned Air Vehicle

Navigation, Guidance & Control

Navigation Systems

Introduction to Avionics

My Presentation at MIT Manipal

B-737 Linear Autoland Simulink Model

Download

Inertia Measurement and Dynamic Stability Analysis of a - AIR

Dynamic stability and stall during steady level turns were examined for VA-1, a joined-wing fligh... more Dynamic stability and stall during steady level turns were examined for VA-1, a joined-wing flight demonstrator aircraft. Configurations with a lower vertical tail and fairings over the main landing gear were compared with a recommendation on the combination had the best drag and dynamic stability characteristics. The dynamic stability analysis was broken into four key parts: a twist test experimentally measured mass moments of inertia, a panel method was used to find non-dimensional stability derivatives, lateral and longitudinal state space models estimated dynamic stability characteristics and handling quality levels were evaluated using a Cooper-Harper based rating system. VA-1 was found to have good longitudinal and lateral flight qualities for cruise flight. The lower vertical tail could be removed to reduce weight and drag without degrading dynamic stability. Spanwise lift coefficients for different wing sections in trimmed steady state turns at 50 and 55 degrees of bank were estimated to see which sections of the wing stalled first. The analysis revealed VA-1 can turn using bank angles less than 50 degrees without stall and that stall first occurred at the aileron, immediately outboard of the wing joint.

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EXPERIMENTAL DETERMINATION OF UNMANNED AIRCRAFT

This paper presents the methodology used in the experimental determination of the inertial proper... more This paper presents the methodology used in the experimental determination of the inertial properties of an unmanned aerial vehicle (UAV). This UAV is a prototype aircraft made of ply wood, balsa wood and aluminum, with a wingspan of 2,5m. A compound-pendulum is used to determine moments of inertia about transversal, longitudinal and vertical axes. The vertical location of the center of gravity of the aircraft is also determined. Experimental data are presented and discussed.

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Determination of Inertial Characteristics of a High Wing

A Halder, Non-member V Agarwal, Non-member R Garhwal, Non-member Dr M Sinha, Non-member To study ... more A Halder, Non-member V Agarwal, Non-member R Garhwal, Non-member Dr M Sinha, Non-member To study the dynamics of an unmanned air vehicle (UAV), prior knowledge about the vehicle's inertial characteristics is essential. An experimental study and detailed analysis has been carried out to determine the centre of gravity (CG) and inertia tensor for a high wing UAV testbed. In this paper, an improved method has been suggested for aircraft inertial characterization in general, and for high wing low cost UAV in particular. To carry out the experiment, complete experimental set-up has been designed and fabricated in-house. The method proposed here, promises to provide superior estimation of inertial characteristics of high wing UAV, compared to the methods cited in the literatures. NOTATION A,B,C : MI of the aircraft about the X body axis, Y body axis and Z body axis, respectively ρ : density of air A Halder, V Agarwal, R Garhwal and Dr M Sinha are with the

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Design, Construction and Structure Analysis of Twinrotor UAV

International Journal of Instrumentation and Control Systems, 2014

There have been many advancements in the field of aerospace and avionics. Scientists have increas... more There have been many advancements in the field of aerospace and avionics. Scientists have increasingly started to focus on VTOL (vertical takeoff and landing) aircrafts. We have built a miniature VTOL twinrotor UAV. UAVs have begun to grab a lot of attention these days due to its numerous applications such as surveillance and relief. Twinrotor is a kind of a helicopter having two main propellers instead of one and no tail fin. All three important motion of the aircraft i.e. roll, pitch, yaw are controlled by thrust vectoring using servo motors and changing the magnitude of thrust using electronics speed controllers. The paper deals with the design of a basic UAV based on application and the construction keeping in mind the different concepts that govern its motion.

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Six-DoF UAV simulation using wind tunnel test data and its cruise mode autopilot design

In this paper an autopilot system is designed for cruise mode of a fixed wing unmanned aerial veh... more In this paper an autopilot system is designed for cruise mode of a fixed wing unmanned aerial vehicle (UAV). The biggest challenge is to maneuver UAV at lower altitudes while overcoming strong coupling between longitudinal and lateral mode. The six-DoF simulation model of the UAV plant under consideration is a non-linear one, to control it for cruise mode it is trimmed at cruise conditions for decoupling of plant model. The control design is divided into two phase, in first phase PID controllers are designed for individual parameter hold related to the cruise flight envelope. In the next phase a decoupled single control with the capabilities of controlling all the parameters for cruise mode is designed. Parallel control loop structure are designed to generate the throttle and elevator control command which indeed control forward speed and altitude of the UAV during cruise. This paper will thus discuss the steps by step procedures in setting up the non-linear flight model/plant, trimming method, flight dynamics, designing control laws and plant validation using simulation software. The mathematical modelling and simulation of UAV aerodynamic wind tunnel test data are adopted from Indian Institute of Science, Bangalore.

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DESIGN AND FABRICATION OF TWINROTOR UAV Shlok Agarwal1, Apoorva Mohan2 and Kamlesh Kumar3

There have been many advancements in the field of aerospace and avionics. Scientists have increas... more There have been many advancements in the field of aerospace and avionics. Scientists have increasingly started to focus on VTOL (vertical take -off and landing) aircrafts. We have built a miniature VTOL twinrotor UAV. UAVs have begun to grab a lot of attention these days due to its numerous applications such as surveillance and relief. Twinrotor is a kind of a helicopter having two main propellers instead of one and no tail fin. All three important motion of the aircraft i.e. roll, pitch, yaw are controlled by thrust vectoring using servo motors and changing the magnitude of thrust using electronics speed controllers. The paper deals with the design of a basic UAV based on application and the construction keeping in mind the different concepts that govern its motion.

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Mathematical Modeling and Control System Design of Tiltrotor UAV

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Avionics

Kamlesh Kumar

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