Papers by N Shantha Kumar
Radio frequency seeker filter design for homing guidance requirements are highly demanding and ch... more Radio frequency seeker filter design for homing guidance requirements are highly demanding and challenging. Seeker data is highly noisy and is characterized by correlation, non-guassian due to target glint and modulated by radar cross section fluctuations. Over and above there will be periodic data loss due to eclipsing. For generating smooth homing guidance commands an efficient filter having minimum lag and maximum seeker noise attenuation capability is required. This paper presents an interacting multiple model seeker filter with extended Kalman filter as mode-matched filter which operates in closed homing guidance loop to generate required guidance commands to intercept maneuvering air-breathing targets. The performance of the seeker filter is evaluated using simulation of different interceptor-target engagement scenarios with different target maneuver profiles.
then determined online together with the target states. Since the target maneuvering logic is ada... more then determined online together with the target states. Since the target maneuvering logic is adaptively determined, the resulting estimation scheme can be expected to have agile response to any changes in the target behavior and there by filter time lag is expected to be well under control. This paper presents a two model based interacting multiple model seeker filter with extended Kalman filter as mode-matched filter which operates in closed homing guidance loop to generate required guidance commands to intercept maneuvering air-breathing target. The major challenge in processing the RF seeker data, especially in end game, is glint noise which is a non-Gaussian noise with heavy tail distribution. The glint noise is a function of target aspect, RCS fluctuation and range to go. Obviously, when the range to go is less, the effect of glint noise (if not accounted properly) on guidance will be more and this would in turn result in large miss distances. To overcome this problem, the glint noise and radar cross section (RCS) fluctuations present in seeker data are handled as augmented states and estimated in the filter algorithm and hence the filter algorithm is named as IMM-AEKF. The two models in IMM-AEKF consists constant acceleration (CA) and constant jerk (CJ) models as target motion models . The performance of the seeker filter is verified with six degree of freedom interceptor-target engagement simulation with seeker filter in guidance loop of the interceptor. Different sensitivity study and filter performance criteria have been used to verify the performance of the seeker filter. In target tracking applications, Kalman filters are extensively used. In general target tracking applications, the
Radio frequency seeker filter design for homing guidance requirements are highly demanding and ch... more Radio frequency seeker filter design for homing guidance requirements are highly demanding and challenging. Seeker data is highly noisy and is characterized by correlation, non-guassian due to target glint and modulated by radar cross section fluctuations. Over and above there will be periodic data loss due to eclipsing. For generating smooth homing guidance commands an efficient filter having minimum lag and maximum seeker noise attenuation capability is required. This paper presents an interacting multiple model seeker filter with extended Kalman filter as mode-matched filter which operates in closed homing guidance loop to generate required guidance commands to intercept maneuvering air-breathing targets. The performance of the seeker filter is evaluated using simulation of different interceptor-target engagement scenarios with different target maneuver profiles.
RF (radio frequency) seeker filter design for homing guidance requirements are highly demanding a... more RF (radio frequency) seeker filter design for homing guidance requirements are highly demanding and challenging [1-2,12]. Very low filter lag and high attenuation of seeker noise are some of the challenges that need to be addressed. Over and above, there will be periodic data ...
In this paper factorization filtering algorithms are described and used for processing13; data fr... more In this paper factorization filtering algorithms are described and used for processing13; data from a typical flight test range. Specifically U-D (unit upper triangular-diagonal)13; factorization based Kalman filtering algorithms are considered. The algorithms are13; validated using simulated data and implemented in MATLAB and alpha DEC machines.13; UDP protocols are used to transfer data from one DEC machine to another where the13; UD filter algorithm is activated to process the data. A very brief description of the fusion13; scheme in which the UD filtering algorithms are being used is given.
In this paper Kalman filter and Gain fusion based multi-sensor data13; fusion algorithms are inve... more In this paper Kalman filter and Gain fusion based multi-sensor data13; fusion algorithms are investigated for their performance when there is data loss. The13; results of real data are presented for situation in which two local / individual filters13; track a moving object.13; .13; . .
Feasibility study of Analysing ASLVD2 flight data estimation of Aerodynamic Derivatives
This document describes the result of feasibility study carried out for analysis of ASLVD2 flight... more This document describes the result of feasibility study carried out for analysis of ASLVD2 flight data. Based on extensive kinematic consistency checking of the data, it was found that poor information content in the data did not permit the generation of aerodynamic parameters. Hence some recommendation are made in-order to generate and acquire meaningful and consistent data sets from future flight tests of launch vehicle.
Lateral Directional Parameter Estimation of Fly-by-wire Aircraft and Validation using simulation data
This report presents the result of the investigation related to estimation of the lateral-directi... more This report presents the result of the investigation related to estimation of the lateral-directional aerodynamic derivative of the highly augmented, advanced fighter aircraft from the flight like response time. Different types of pilot input are used to generate aircraft response data in the engineer in loop flight simulator(ELS)to determine which input excitation might provide the most accurate estimate of aircraft stability and control derivatives. Also MATLAB/SIMULINK based simulation platform is used to generate aircraft response with single surface excitation to evaluate the usefulness of the method for the stability and control derivatives estimation. The maximum likelihood estimation based on output error minimization technique is used to estimate the derivatives from the aircraft response data. The result indicate that accuracy of the estimated derivatives improve the persistence excitation and single surface excitation.
Experimental study with enhanced Vision System prototype unit
2011 International Conference on Image Information Processing, 2011
Development of Algorithm for Characterization and Fusion of sensor Data for Multi Sensor Multi Target Application :Task completion cum Technical Closure Report
This report gives the summary of technical accomplishments under the DRDL sponsored project Devel... more This report gives the summary of technical accomplishments under the DRDL sponsored project Development of algorithms for characterization and fusion of sensor data for Multi Sensor Multi Target application
Defence Science Journal, 2013
A new avionics concept called integrated enhanced and synthetic vision system (IESVS) is being de... more A new avionics concept called integrated enhanced and synthetic vision system (IESVS) is being developed to enable flight operations during adverse weather/visibility conditions even in non precision airfields. This paper presents the latest trends in IESVS, design concept of the system and the work being carried out at National Aerospace Laboratories, Bangalore towards indigenous development of the same for transport aircraft.
45th AIAA Aerospace Sciences Meeting and Exhibit, 2007
Automatic detection of runway incursions using on-board sensors
A system to detect runway incursions or presence of any equipments or animals or humans on runway... more A system to detect runway incursions or presence of any equipments or animals or humans on runway prior to landing is very essential for safe landing. Such system should be capable of detecting the distant objects in order to give the pilot enough response time to take appropriate safety action. This report presents a methodology to detect the runway and obstacles on runway using images from forward looking color camera and infrared sensor onboard an aircraft while approaching an airport for landing. The detection process consists of horizon detection, reduction of runway search space in an image, runway detection/tracking, and detection/tracking of obstacles on runway. The information is then presented to the pilot in an appropriate form to improve pilot situational awareness and take necessary action. The methodology is validated using simulated data of electro-optical color camera and infrared sensor onboard an aircraft during approach for landing.
Stability and control derivatives of LCRA from flight data
This report presents the results of investigation related to the estimation of stability and cont... more This report presents the results of investigation related to the estimation of stability and control derivatives of LCRA from the flight data generated during Sept-Oct 2000 (flight no. 373 to 386) for LER-UAV project. The maximum likelihood estimation, based on output error minimization technique is used to estimate the derivatives from the aircraft response data. The preliminary exercise of model validation is carried out. The recommendations to carry out further model validation using a flight simulator before accepting the final set of derivatives are given.
Defence Science Journal, 2004
In this paper, stability and control derivatives of light canard research aircraft generated thro... more In this paper, stability and control derivatives of light canard research aircraft generated through the flight test using parameter estimation technique has been presented. The maximum likelihood estimation, based on output-error minimisation technique, is used to estimate the derivatives from the aircraft response data. The validity of the estimates has been checked by the cross validation method, wherein the estimated model response is matched with the flight-test data that are not used for estimating the derivatives.
Input Excitation Techniques for Aerodynamic Derivatives Estimation of Highly Augmented Fighter Aircraft
Defence Science Journal, 1999
This paper presents the results of an investigation related to the estimation of lateral-directio... more This paper presents the results of an investigation related to the estimation of lateral-directional aerodynamic derivatives of highly augmented and advanced fighter aircraft from the flight like response data. Different types of pilot inputs are used to generate aircraft response data in the engineer-in-loop flight simulator to determine which input excitation flight provide the most accurate estimates of aircraft stability and control derivatives. Also, MATILABI SIMULINK-based simulation platform is used to generate aircraft response with single-surface excitation to evaluate the usefulness of the method for stability and control derivatives estimation. The maximum likelihood estimation, based on output error utilisation technique is used to estimate the derivatives from the aircraft simulation response data. The results indicate that accuracy of the estimated derivatives improve with persistence excitation and single-surface excitation.
Techniques for Automatic Target Recognition
Techniques for Automatic Target Recognition. Shantha Kumar, N and Sudesh, K Kashyap andNaidu, VPS... more Techniques for Automatic Target Recognition. Shantha Kumar, N and Sudesh, K Kashyap andNaidu, VPS and Vishal, Ravindra and Girija, G (2012) Techniques for Automatic Target Recognition. ... Depositing User: Dr Sudesh Kumar Kashyap. Date Deposited: 19 Jan 2012 10:56. ...
Sensor Failure Detection and Management Scheme for Pressure Probes Kalman Filtering Technique
... Division/Department: Flight Mechanics and Control Division. Depositing User: Mrs NeetuChandra... more ... Division/Department: Flight Mechanics and Control Division. Depositing User: Mrs NeetuChandra. Date Deposited: 07 Jun 2006. Last Modified: 24 May 2010 09:41. URI: http://nal-ir.nal.res.in/id/eprint/1373. Actions (login required). View Item. ...
FIDA-Flight Data Analysis Package in PC-MATLAB
... Division/Department: Flight Mechanics and Control Division, Flight Mechanics and Control Divi... more ... Division/Department: Flight Mechanics and Control Division, Flight Mechanics and Control Division, Flight Mechanics and Control Division. Depositing User: Mrs Neetu Chandra. Date Deposited: 23 Jun 2006. Last Modified: 07 Jul 2010 11:58. ...
Masreliez filter which is a Kalman type of recursive filter is implemented and validated. The mai... more Masreliez filter which is a Kalman type of recursive filter is implemented and validated. The main computation in Masreliez filter is to evaluate the score function which directly influences the estimates of the target states. Scalar approximation for score function evaluation is extended to ...
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Papers by N Shantha Kumar