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Recent Projects : 
    Glider based Payload (Torpedo) delivery System

Sponsoring Agency : NSTL
Period : 2011-2012

Description : The goal of this project is to develop a design of a glider configuration which when mounted on the torpedo can assist it to glide. The specified objective is to achieve a minimum range of 25 Km in a maximum duration of 250 sec when the whole assembly is launched from an altitude of 6 Km with a circular error......
 
  Parachute Assisted Unmanned Aerial Vehicle

Sponsoring Agency : ADRDE
Period : 2010-2011

Description : The deliverables of this project are to design, develop and manufacture a full scaled unmanned aerial vehicle which can be used for surveillance. The vehicle should also be designed in a way such that it can be recovered with the help of a parafoil mounted in it. The wing span is aimed to be kept high to facilitate .......
 
    Design of 5 DOF Dynamic Test Rig for Aerodynamic Characterization of Flight Vehicle

Description : The design of a 5 DOF (pitch, roll, yaw, heave and sway) dynamic test rig serves the purpose of estimating the aerodynamic derivatives of flight vehicles of any configuration. A mathematical model was developed which incorporates the 5 DOF in flight ......
 
  Research Work on Stratospheric Airships

Sponsoring Agency : ADRDE
Period : 2010-2011

Description : Stratospheric Airships are lighter than air high altitude long endurance (LTA-HALE) systems operating at altitudes typically in the range of 18-22 Km. These systems are completely unmanned and the operating altitude is chosen on the basis of minimum atmospheric disturbances in that ......
 
  Micro Air Vehicle

Description : A miniature air vehicle is proposed to be developed which can operate in an unmanned state so that it can be useful for shot endurance surveillance purposes. The prime objective of this project is to design and manufacture a light weight (<50gms) and ......
 
  Supercavitation

Description : Supercavitation is a cutting edge technology under research currently for improving the performance underwater vehicle. Supercavitation phenomenon helps underwater vehicles to achieve high speeds by reducing the amount of drag .....
 
  Parafoil

Description : Parafoil is non-rigid wing usually made up of porous fabric. The estimation of aerodynamic parameter is carried out using analytical and experimental data available to check its response against extreme conditions. This knowledge is also used for controlling the system. A 9DOF mathematical model was developed to simulate .....
 
  Non-Linear Dynamic Inversion Technique

Description : Development of Control Laws for different unmanned aerospace vehicles using Nonlinear Dynamic Inversion (NDI) technique is being carried out at Flight Lab, IIT Kanpur. NDI is a control design technique which is highly emerging in the field of controls of nonlinear systems. The key reason for preferring this techni .....
 
 
Previous Projects : 
     
 

Sl. No.

Period

Sponsoring Agency

Title of Project

Co-Investigators

(if any)

1.       

2011-2012

NSTL

Development and Implementation of control algorithm for air launched torpedo

 

2.       

Dec’ 10 to Dec’ 12

DRDO

Aerodynamic characterization and performance estimations through flight test

 

3.       

2010-2011

ADRDE

Development of artificial neural network based control low for parachute assisted uav

 

4.       

2010-2011

ADRDE

Acquisition of flight data for ram air parachute

 

5.       

2010-2011

ADRDE

Estimation of flight characteristics of ram air parachute

 

6.       

2009-2010

ADRDE

Dynamics stability analysis of aerostat 2000 cum size

 

7.       

2009-2010

ADRDE

Trajectory and stability analysis of conventional parachute payload combination for fae

 

8.       

2009-2010

ARDE

Separation and stability studies of 250kg pre- fragmented bomb

 

9.       

2009-2010

ARDE

Aerodynamic studies and characterisation of 120mm...bomb(rab)

 

10.    

Nov’ 08 to               Nov’ 10

ARMREB

Design and evaluation different control strategies for upgrading existing aircraft bomb to guided bombs

-

11.    

May’ 08 to May’ 10

ARDB

Aerodynamic Parameters Estimation of HANSA-III Aircraft with unsteady aerodynamic Modelling Conventional and Neural method

 

12.    

2008-2009

ARDE

The oretical studies on the configuration design of fsapds stabilizer unit stability analysis and sabot separation dynamics

 

 

13.    

March ’07 to March ‘ 10

ARDB

High Alpha Aero Dynamic Testing

Dr. T. G. Pai

14.    

June’ 07 to June’ 09

ARDB

High Alpha Aerodynamic testing and Modeling

Dr. T.G. Pai (PI)

15.    

June ’07 to June ‘09

ARDB

Identification of a parafoil longitudinal Aerodynamic characteristics using ground based-Flight test

-

 

16.    

2007-2008

ZEUS

6DOF simulation of missiles

 

 

17.    

March ’06 to March 07

DRDO

Design Fabrication and characterization of Atomizers

 

Dr. A. Kushari

18.    

2006-2007

HEMRL

Generation of longitudinal and lateral directional aerodynamic force coefficients of FAE Bomb with ring tail configuration by wind tunnel testing at subsonic and supersonic speeds

 

19.    

March’ 05 to               March’ 07

ARMREB

Study on Trajectory Correction System using Impulse Jet to Reduce the Impact Point Dispersion

-

20.    

March’ 05 to      March’ 07

ARMREB

Aerodynamic Study of Lattice Fins using Wind Tunnel Testing for High Angle of Maneuver of Strategic Aircraft Bomb

-

21.    

March 05 to           March 06

ARDB

Design Studies on Motor Glider

-

22.    

2005-2006

HEMRL

Prediction of Aerodynamics Parameters Aerodynamic Load, Lug Loads and Stability Characteristics of FAE Bombs

Sri A. Misra

23.    

2005-2006

HEMRL

Safe Separation Study on FAE Bomb

Sri A. Misra

24.    

2005-2006

ARDE

Aerodynamic Characterization of Lattice Fin for Aircraft Bombs

 

25.    

2004-2005

ARDE

Design Evaluation and Finalization of Arming Mechanism for Fuze DA/SD for Non-Spinning Submunition

 

26.    

April’03 to               Dec’ 04

ARMREB

CFD Solution to Sabot Separation

Dr. T. K. Sengupta  (PI)

27.    

April’ 03 to       May’ 05

ARMREB

Aerodynamic Parameter Estimation of Artillery Projectiles from Radar-Tracked Flight Data

-

28.    

2002-2003

ARDE

Modelling of Separation Phenomena and Aerodynamic of Cargo Ammunition..

 

29.    

2002-2003

ARDE

Missile Dynamics, Sizing of Control Fins and Wind Tunnel Testing of Cannon Launched Guided Missile.

 

30.    

July’ 2000 to       July’ 2002

ARMREB

Neural Network Modelling of Range performance of Armament Stores

Dr. S. C. R

31.    

Dec’ 2000 to 2001

ARDE

Aerodynamic Studies/125 KG Bomb with Ballistic Unit, by ARDE, Pune

Dr. S. C. R.

32.    

April’99 to     March’01

ADA

Parameter Estimation from flight data using neural network

Dr. S. C. R

 
 
     
 
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