Discrete Time Transfer Matrix Method for Projectile Trajectory Prediction

Khalil, Mostafa; Rui, Xiaoting; Hendy, Hossam

doi:10.1061/(asce)as.1943-5525.0000381

Cited by 7 publications

(8 citation statements)

References 8 publications

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“…However, in case of star grain, the pressure and thrust profiles are obtained using reliable internal ballistics prediction equations. 42 ‐ Finally, the missile maximum range is computed using a proper point-mass trajectory model 43 based on the zero-lift drag coefficient CD=f(M) computed before. Based on the error between the computed and desired maximum ground range, another I T value is generated and the next iteration of the inner loop commences.…”

Section: Design Parameters Calculationmentioning

confidence: 99%

A preliminary multidisciplinary design procedure for tactical missiles

Khalil

Hashish

Abdalla

2018

Proceedings of the Institution of Mechanical Engineers, Part G:

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During missile system development, multidisciplinary design procedure is iteratively implemented based on the missile objective and target nature including internal ballistic, warhead function, and airframe configuration. By applying missile preliminary design, a good estimation for different design parameters can be obtained which will be useful through further detail design process. The aim of this paper is to build a preliminary design procedure for an unguided tactical missile that uses single-stage solid propellant motor to deliver a defined payload mass to a desired ground range. Based on data of available similar mature missile systems, two empirical formulas are developed to serve in the initial sizing of the missile with consideration of slenderness ratio, warhead mass, and desired ground range. Two different design concepts are implemented for tubular and star grains with different propellant compositions and chamber filling coefficients while the body-alone airframe configuration is adopted. The results demonstrate the capability of the proposed design procedure in defining the detailed design parameters. The impact of changing the propellant compositions and chamber filling coefficients on the obtained ground range is also explored.

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Section: Design Parameters Calculationmentioning

confidence: 99%

A preliminary multidisciplinary design procedure for tactical missiles

Khalil

Hashish

Abdalla

2018

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…The computational firing tables are developed based on a flight trajectory model. Different flight trajectory models can be implemented to compute artillery FT, such as the point-mass (PM) model [2][3][4], the modified-point-mass (MPM) model [9][10][11], and the six-degree-of-freedom (6-DOF) model [12][13][14]. The issues of relative complexity and accuracy of these models were investigated in [13][14][15].…”

Section: Introductionmentioning

confidence: 99%

Archive of Mechanical Engineering

Khalil

2021

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Production and assessment of artillery firing tables (FT) are the key tasks in solving ballistic problems through both standard and non-standard firing conditions. According to the literature, two different standard firing table formats were developed by the former-Soviet and the United States armies. This study proposes the main difference between these FT formats, as the standard meteorological conditions. An accuracy assessment has been proposed to justify different sources of errors through modeling and production of such tables, including applied meteorological message, aiming angles round-off, linear superposition principle, and Earth approximation. A case study has been proposed for the 155M107 projectile to demonstrate the impact of the Coriolis effect as well as other ballistic and atmospheric non-standard conditions. As a part of the construction of artillery FT, a fitting process has to be made between available firing data and simulations. Therefore, a parametric study is implemented to study the number of test elevations per charge needed through the fitting process and its corresponding production error. Hence, based on the number of test elevations available, the genetic algorithm (GA) has been utilized to obtain the test elevations order needed with minimum FT production error. The results show a good agreement with the data stated in the literature.

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“…12 A model reference adaptive control approach is adopted to design an ACLS control law under the condition of external uncertainties, and the air wake disturbance can be obviously reduced and the robustness of the control system is especially ensured. 13,14 Some representative methods in tracking the approach trajectory are researched, such as discrete-time transfer matrix 15 and linear envelope method. 16 Wang and colleagues 17,18 design a track controller of hypersonic vehicle based on fuzzy method and sliding mode control.…”

Section: Introductionmentioning

confidence: 99%

Automatic flight control design considering objective and subjective risks during carrier landing

Wang

Zhang

Zhu

2019

Proceedings of the Institution of Mechanical Engineers, Part I:

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In this article, a design scheme of automatic carrier landing system control law based on combination of the objective risk and the subjective risk is proposed, in order to improve the safety and flying quality of the landing. The nonlinear longitudinal mathematical model is constructed in the air wake turbulence condition during carrier landing, which is transformed into a linear perturbed model by the state-space equations with deviation state variables. The concepts of the objective risk and the subjective risk in the recovery of an aircraft aboard a carrier are addressed. A principle of predicting the future states based on the current ones is put forward so that a mathematic model for the objective risk is established, synthetically considering the current and future landing state deviations. For the other risk, the corresponding model is obtained by the subjective experiences of the pilots in the flight simulation tests. Furthermore, a novel model predictive control algorithm, which contains the additional subjective risk and the time-varying weights of the state terms, is proposed. Automatic carrier landing control law is built by introducing the objective risk, the subjective risk, and the effect of carrier air wake disturbance. In the rolling optimization progress, these time-varying weights are dynamically tuned according to the constantly changing objective risk to control the state deviations and suppress this risk, while the subjective risk is handled by the additional risk terms. Besides, the action of carrier air wake disturbance is considered and compensated in the derivation of the linear matrix inequalities. Test results based on a semi-physical simulation platform indicate that the new automatic carrier landing system control algorithm proposed by this article brings about an excellent carrier landing performance as well as an improved flying quality.

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Discrete Time Transfer Matrix Method for Projectile Trajectory Prediction

Cited by 7 publications

References 8 publications

A preliminary multidisciplinary design procedure for tactical missiles

A preliminary multidisciplinary design procedure for tactical missiles

Archive of Mechanical Engineering

Automatic flight control design considering objective and subjective risks during carrier landing

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