Missile Mathematical Model and System Design

István, Papp

doi:10.32565/aarms.2017.1.3

Cited by 3 publications

(1 citation statement)

References 3 publications

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“…Papp [14] of the National University of Public Service at Budapest developed a mathematical model and system design for missiles and defined the flight conditions of airto-air missiles. Papp designed mathematical models and controllers that matched specific flight conditions using fundamental aerodynamic coefficients such as lift and drag coefficients and trigonometric functions to create nonlinear systems for controller design.…”

Section: A Modelingmentioning

confidence: 99%

Linearized State-Space Model-Based Attitude Control for Rocket With Four Controllable Fins—Part 1-1: Basic Modeling and Identification

Kim,

Tullu,

Jung

2023

IEEE Access

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In this study, we present, analyze, and validate a linear state-space model for a simplified rocket with four fins. The model is validated experimentally using a wind tunnel. The proposed model consists of two main elements: a rocket body and fins. The body is represented as a cylinder integrated from infinitesimal sections along the longitudinal direction (x-axis), and each fin is interpreted as an individual rigid body. Applying a linear state space facilitates the use of linear analysis tools, leading to expedient system stability assessment and controller design. Stability analysis of the specific model is performed for validation. The results of the analysis showed that the phase margins of pitching and yawing were 16.9°, and that of rolling was 2.21°. However, the linearized state space carries the risk of discrepancies with the actual dynamics. The model is experimentally validated in a wind tunnel to reduce risk. The rocket model is affixed to a stationary jig in a wind tunnel and has four degrees of freedom. This arrangement allows for the verification of a coupled three-axis rotational model. The results show convergence within an average similarity of 77% in the linear range, confirming the reliability of the model. The validated model can be used for comprehensive analyses including control system design, performance optimization, and robustness analysis of a rocket with four fins in the future.

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Section: A Modelingmentioning

confidence: 99%

Linearized State-Space Model-Based Attitude Control for Rocket With Four Controllable Fins—Part 1-1: Basic Modeling and Identification

Kim,

Tullu,

Jung

2023

IEEE Access

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Modeling and simulation of a canard-based sounding rocket dynamics at climb and descent phases

Hanif,

Putro,

Duhri

et al. 2023

Machine Learning and Information Processing: Proceedings of Icmlip 2023

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State-Space Modeling of a Rocket for Optimal Control System Design

Kisabo¹,

Adebimpe²

2019

Ballistics

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This chapter is the first of two others that will follow (a three-chapter series). Here we present the derivation of the mathematical model for a rocket's autopilots in state space. The basic equations defining the airframe dynamics of a typical six degrees of freedom (6DoFs) are nonlinear and coupled. Separation of these nonlinear coupled dynamics is presented in this chapter to isolate the lateral dynamics from the longitudinal dynamics. Also, the need to determine aerodynamic coefficients and their derivative components is brought to light here. This is the crux of the equation. Methods of obtaining such coefficients and their derivatives in a sequential form are also put forward. After the aerodynamic coefficients and their derivatives are obtained, the next step is to trim and linearize the decoupled nonlinear 6DoFs. In a novel way, we presented the linearization of the decoupled 6DoF equations in a generalized form. This should provide a lucid and easy way to implement trim and linearization in a computer program. The longitudinal model of a rocket presented in this chapter will serve as the main mathematical model in two other chapters that follow in this book.

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Missile Mathematical Model and System Design

Cited by 3 publications

References 3 publications

Linearized State-Space Model-Based Attitude Control for Rocket With Four Controllable Fins—Part 1-1: Basic Modeling and Identification

Linearized State-Space Model-Based Attitude Control for Rocket With Four Controllable Fins—Part 1-1: Basic Modeling and Identification

Modeling and simulation of a canard-based sounding rocket dynamics at climb and descent phases

State-Space Modeling of a Rocket for Optimal Control System Design

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