Estimation of Circular Error Probability of Strapped Down Inertial Navigation System by Propagation of Error Covariance Matrix

This paper provides an error model of the strapped down inertial navigation system in the state space format. A method to estimate the circular error probability is presented using time propagation of error covariance matrix. Numerical results have been obtained for a typical flight trajectory. Sensitivity studies have also been conducted for variation of sensor noise covariances and initial state uncertainty. This methodology seems to work in all the practical cases considered so far. Software has been tested for both the local vertical frame and the inertial frame. The covariance propagation technique provides accurate estimation of dispersions of position at impact. This in turn enables to estimate the circular error probability (CEP) very accurately

Current Trends in Tactical Missile Guidance

The problem of tactical missile guidance is very challenging and has been treated using several basic metlfodologies in the past four decades. Major techniques can be grouped underclassical guidance laws, modern guidance laws, l'aws for manoeuvring targets, predictive guidance for endgame scenario, and guidance laws based on intelligent control methods. Each technique has some advantages and disadvantages while implementing in a practical system. Guidance law selection is dictated by nature of flight profile like boost, midcourse, terminal homing, etc, and also miss-distance and a single-shot kill probability. This paper presents a brief survey of the existing techniques and current trends in tactical missile guidance

Target Acceleration Estimation from Radar Position Data using Neural Network

This work is a preliminary investigation on target manoeuvre estimation in real-time from the available measurements of noisy position data from tracking radar using an artificial neural network (ANN). Recently, simulation study of target manoeuvre estimation in real-time from the same position alone measurement using extended Kalman filter has been carried out in a simulated environment using measurements at 100 ms interval. The results reveal that the estimated acceleration consists of substantial error and lag, which is a stumbling block for guidance accuracy in real-time. So, the target acceleration has been estimated using the ANN with less error and lag than the same using Kalman estimator

Target Acceleration Estimation from Radar Position Data using Neural Network

This work is a preliminary investigation on target manoeuvre estimation in real-time from the available measurements of noisy position data from tracking radar using an artificial neural network (ANN). Recently, simulation study of target manoeuvre estimation in real-time from the same position alone measurement using extended Kalman filter has been carried out in a simulated environment using measurements at 100 ms interval. The results reveal that the estimated acceleration consists of substantial error and lag, which is a stumbling block for guidance accuracy in real-time. So, the target acceleration has been estimated using the ANN with less error and lag than the same using Kalman estimator

Ultra High MULTI CLOCK FREQUENCY BAUD RATE 128 Bit Multichannel PRBS CODEC ASIC I.P Core Design for High speed wireless internet Wi-Fi Routers, MODEM's, NIC's

The main aim is for HDL Design and Implementation of 128 Bit Multichannel PRBS CODEC for High Speed wireless internet computing products like Wi-Fi Routers, MODEM’s. this is very suit for very high speed internet computing products / applications of Big Parallel Network Data MODEM Interface based Computing Servers/Stations. This design consists of PRBS Encoder and Decoder Design of Different Channel Frequencies in terms of different PRBS Patterns Sequences – 2e7-1,2e10-1, 2e15-1, 2e23-1, 2e31-1, 2e48-1, 2e52-1, 2e64-1,2e128-1 by tapping through different feedback elements. Tapping of PRBS Done as per C.C.I.T.T – I.T.U O.150,O.151,O.152,O.153 Standards . these pattern sequences are encoded and decoded through different PRBS channel type selector/de-selector and outputs are generated through serial and parallel form of different PRBS Patterns. Programming design description done by Verilog HDL/VHDL and Design Synthesis & Implementation done through Xilinx ISE Software and Debugging done by Advanced FPGA Development Boards/Kits. Design Verification done through highly proficient Test Bench/Stimulus Design Module Codes

Computer simulation methods for launch vehicle mission and control problems

The flight control system of a launch vehicle is the result of the right trade-off between different objectives, such as the interaction between the control, guidance and performance aspects of a mission with specified end conditions and the analysis of the mission trajectories and vehicle systems under a variety of normal and failure modes. Hence an evaluation of the design and performance of such a system is not feasible through purely analytical means even with simplified models. This, together with the necessity for step-by-step refinement of the models used for the vehicle and its environment, calls for the computer simulation approach. The various considerations involved in developing and selecting the simulation model and implementing it on a computer are discussed. To illustrate the approach, a hybrid simulation evaluation of the performance of the first stage control system of a satellite launch vehicle and that of the controlled vehicle under different operational modes is presented

HDL Design for Peta Hertz Clock based 2e31-1 Peta Bits Per Second (Pbps) PRBS Design for Ultra High Speed Applications/Products

The Design is mainly Intended for High Speed Random Frequency Carrier Wave Generator of Peta Bits Per Second P.b.p.s (Peta Bits Per Second) Data Rate 2e31-1 Tapped PRBS Pattern Sequence. The P.R.B.S is Designed by using L.F.S.R Linear Feed Back Shift Register & XOR Gate with Specific Tapping Points as per C.C.I.T.T I.T.U Standards. R.T.L Design Architecture Implemented by using V.H.D.L &/ Verilog H.D.L, Programming & Debugging Done by using Spartan III F.P.G.A Kit. Transmission done through this carrier frequency. Propagation Carrier Done either Serially / Parallel lines I/O. DOI: 10.17762/ijritcc2321-8169.15083

On the orthogonality of suboptimum estimate in the combined estimation and control problem

By deriving the equations for an error analysis of modeling inaccuracies for the combined estimation and control problem, it is shown that the optimum estimation error is orthogonal to the actual suboptimum estimate