Path-Following Control for Thrust-Vectored Hypersonic Aircraft

Sahbon, Nezar; Jacewicz, Mariusz; Lichota, Piotr; Strzelecka, K.

doi:10.3390/en16052501

Cited by 5 publications

(6 citation statements)

References 39 publications

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“…The MATLAB/Simulink environment was used to create various simulation mathematical models; it is well known for its resilience and practicality in dealing with complicated dynamic systems. Several studies employed this environment for modelling flight simulation during research, such as developing a flight simulation model for a modified Hypersonic X-15 aircraft [22], for the Javelin projectile system [14] and research concerning the use of a vertical cold launch system with rapid pitch manoeuvres to increase range and enhance projectile coverage [23]. Moreover, the development of the six-degrees-of-freedom model was utilised to perform a parametric guidance study for a 160 mm projectile steered by lateral thrusters [24].…”

Section: Introductionmentioning

confidence: 99%

Comparison of Two Aerodynamic Models for Projectile Trajectory Simulation

Sahbon,

Welcer

2024

Aerospace

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The accuracy of aerodynamically controlled guided projectile simulations is largely determined by the aerodynamic model employed in flight simulations which impacts vehicle interaction with the surrounding air. In this work, the performance of projectile path following with two distinct aerodynamic models is examined for their possible influence on trajectory following accuracy. The study incorporates the path following guidance algorithm, which enables the object to navigate along a predefined path. The simulation mathematical model is developed in the MATLAB/Simulink environment. In addition, by integrating the path-following algorithm with the two aerodynamic models, the dynamic behaviour of the aerodynamically controlled projectile can be compared. This allows for a more comprehensive analysis of the trajectory and the effects of each model on the desired flight path. Further research can explore the differences between the two models in greater detail and quantify their impact on unmanned projectile trajectory predictions, in addition to further exploring the specific characteristics and limitations of each model. This will involve analysing their assumptions, computational methods, and inputs to identify potential sources of error or uncertainty in the simulations. Moreover, these results have important implications for the design of aerodynamically controlled projectiles as well as a deeper understanding of aerodynamic mathematical modelling in flight simulation.

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Section: Introductionmentioning

confidence: 99%

Comparison of Two Aerodynamic Models for Projectile Trajectory Simulation

Sahbon,

Welcer

2024

Aerospace

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“…The adjustable nozzle can take the form of a diaphragm [34,35]. For known thrust vector (velocity vector) control systems, the maximum flow deflection angle (at the nozzle exit) can vary in the range from +20 o to -20 o [36,37]. Adjustable nozzles can have a conical central body that can move in the axial [38] or radial directions [39].…”

Section: Introductionmentioning

confidence: 99%

Solving Innovative Problems of Thrust Vector Control Based on Euler's Scientific Legacy

Sazonov,

Mokhov,

Gryaznova

et al. 2023

Civ Eng J

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This study aims to develop an interdisciplinary approach to solving innovative thrust vector control problems. The methodology involves the development of a working hypothesis about the ejection process when using a controlled nozzle to deflect the thrust vector (velocity vector) in any direction within a complete geometric sphere. When developing the working hypothesis, a multilateral analysis of individual facts and scientific and technical information is performed using tools in the "big data" area, assessing opportunities to apply the "Foresight" methodology for predicting the development of fluidics. The authors propose new mathematical models to describe the thrust vector in the distribution of the mass flow rate of the fluid medium between flow channels. Patents for inventions support the novelty of scientific results that reveal new opportunities for more active development of fluidics as applied to simple and complex jet systems with low and extremely high energy density in flows. The proposed methodology rests on a modern computer base and is a logical continuation and development of well-known Euler’s works. The computer simulation of multiflow jet devices mainly focuses on power engineering, production, and processing of hydrocarbons. Some results of this research work, including patented design developments and calculation methods, also apply to developing robotics, unmanned vehicles, and programable jet systems. The authors attribute further development of the interdisciplinary approach for solving inventive problems to the use of different AI options. Doi: 10.28991/CEJ-2023-09-11-017 Full Text: PDF

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“…Mechanical thrust vectoring (MTV) has been employed in various military aircraft, such as McDonnell Douglas AV-8B Harrier II [1], F-35 Lightning II [2], and X-15 [3], to reduce radar cross-section by eliminating the need for traditional control surfaces. MTV is also employed to augment the effectiveness of the traditional control surfaces [4].…”

Section: Introductionmentioning

confidence: 99%