Simulation of Guidance Subsystem of Launch Vehicle Based on Matlab/Simulink

Lin, Lan; Li, Hui; Ding, Wei P.

doi:10.1109/icie.2009.234

Cited by 3 publications

(1 citation statement)

References 2 publications

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“…In order to linearize the non-linear system about the steady states trim points, simulink model was developed in matlab environment [16], in which the 6 DOF non-linear model along with all dependencies were incorporated. Matlab linearization tool linmod was used for model linearization, as a result of which, linearized state space representation of the model about the trim point was obtained for the optimized trajectory.…”

Section: Model Linearization and Eigen Value Analysismentioning

confidence: 99%

Dynamic Modeling & Stability Analysis of a Generic UAV in Glide Phase

2017

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Abstract. In this paper, we present dynamic modelling and stability analysis of a generic UAV in the glide phase under engine failure condition. When such extreme phenomena occurs, the most desirable requirement is to survive that stage by keeping the vehicle controllable by maintaining its orientation and to glide the vehicle towards the intended direction with maximum extended range. This study investigates the stability aspects of one such aerial vehicle under engine failure condition. In the proposed architecture, a six degree of freedom vehicle dynamic simulation model is implemented through a set of coupled non-linear differential equations. The aerodynamic forces and moments encountered by the UAV during various phases of the flight are ascertained through empirical / non-empirical techniques. Nonlinear constrained optimization technique is employed to evaluate the steady state values of the optimized trajectory for the complete flight regime. Results from dynamical systems theory are applied to investigate local stability characteristics of UAV around the steady state. Complete set of dynamic modes of UAV throughout the glide phase are evaluated and mode content in each of the motion variable is determined using modal decomposition technique. The dynamic characteristics of the open-loop configuration are assessed to generate adequate benchmark performance for closed-loop controller design

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Section: Model Linearization and Eigen Value Analysismentioning

confidence: 99%

Dynamic Modeling & Stability Analysis of a Generic UAV in Glide Phase

2017

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Synthesis of a unified simulation and modeling complex for calculating the motion of an aircraft using the MATLAB Simulink software package

Klishin,

Kolesnikova,

Iljukhin

2023

The International Conference on Battery for Renewable Energy and Electric Vehicles (Icb-Rev) 2022

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Simulation and Design of Strapdown Inertial Navigation System Based on RT-Lab/Simulink

Song

Yong-yuan

Yang

2009

2009 Second International Conference on Information and Computing Science

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According to engineering characteristics which are huge construction quantities, long design period and high real time requirement of Strapdown Inertial Navigation System (SINS), this paper introduces simulation of SINS based on Simulink and structure design of SINS based on RT-Lab. And implemented real-time simulation for RT-Lab after double sample of rotation vector on quaternion is used to attitude updating algorithm and double sample of compensated sculling error is used to velocity updating algorithm. Simulation results show that simulation method which based on RTLab/Simulink easy to realize of SINS, and overcome bad real time capability when simulation only use Matlab and large amounts of computation,long period and big error when simulation use C code which based on hardware.

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Simulation of Guidance Subsystem of Launch Vehicle Based on Matlab/Simulink

Cited by 3 publications

References 2 publications

Dynamic Modeling & Stability Analysis of a Generic UAV in Glide Phase

Dynamic Modeling & Stability Analysis of a Generic UAV in Glide Phase

Synthesis of a unified simulation and modeling complex for calculating the motion of an aircraft using the MATLAB Simulink software package

Simulation and Design of Strapdown Inertial Navigation System Based on RT-Lab/Simulink

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