Approach for Understanding Range Extension of Gliding Indirect Fire Munitions

Bryson, Joshua T.; Vasile, Joseph D.; Celmins, Ilmars; Fresconi, Frank

doi:10.2514/6.2018-3158

Cited by 9 publications

(3 citation statements)

References 15 publications

Supporting

Mentioning

Contrasting

Unclassified

Order By: Relevance

“…Riyadl [9] menuliskan bahwa statik margin adalah besaran yang menunjukkan kemampuan roket untuk kembali kepada keadaan kesetimbangan jika roket mengalami gangguan pada saat terbang. Mayoritas riset yang dituangkan dalam paper jurnal menggunakan static margin (SM) sebagai parameter umum untuk memeriksa kestabilan statik dalam arah sumbu longitudinal dan menggunakan jarak longitudinal [10] sebagai parameter tolok ukur efektifitasnya. Frekuensi osilasi yang besar mudah menyebabkan roket mengalami gerakan tak terkendali [11], oleh karenanya SM telah diteliti agar dibatasi rentang gesernya [12].…”

Section: Pendahuluanunclassified

Analisa Pengaruh Aerodinamika Pada Margin Stabilitas Mortir Latih 81 Mm Dengan Sistem Kompresi Udara

Imron¹,

Widodo

Purnowidodo

2022

JRM

View full text Add to dashboard Cite

Mortar is one type of weapon used by Infantry units. One type of mortar that is widely used, especially in technical training, is the 81 mm mortar prototype produced by PT. Pindad, which has a 7.62 mm caliber munitions thruster with an average range of 110 meters. However, this mortar still has unstable aerodynamics. Therefore, this study was conducted to design a safe mortar prototype with a stability margin value, so it can determine the range and improve the troop skills. Computational fluid dynamic simulation was conducted through the ANSYS software to simulate important aerodynamic properties in this study. The angle variation of the barrel in firing used is 450,550 and 650 with compression pressure variation of 16,18, 20, 22, 24, 26, 28, 30, 32 bar. Meanwhile, the angle modification of the mortar fin is 330,440,550 and the aerodynamic simulation was carried out at 20, 30, 40 m/s speeds. The results showed that the design of an 81 mm mortar prototype which has a fin angle of 330 at a simulated speed of 20,30,40 m/s, an angle of attack of 450,550, 650 has the smallest drag force and lift force and the smallest number of postive pitch moments, but still has a standard margin of stability of about 1.57-1.81 caliber.

show abstract

Section: Pendahuluanunclassified

Analisa Pengaruh Aerodinamika Pada Margin Stabilitas Mortir Latih 81 Mm Dengan Sistem Kompresi Udara

Imron¹,

Widodo

Purnowidodo

2022

JRM

View full text Add to dashboard Cite

show abstract

“…Moreover, because the dual-pulse missile needs to be fired twice, some key variables must be determined before launch, including the ignition time of the two-stage booster engine. 1,2 These variables have a great impact on the ballistic performance of the missile, such as the range, attack speed, and attack angle. Cheng et al 3 studied the design and optimization of a discontinuous booster trajectory scheme under multiple constraints, including dynamic pressure, overload, and terminal state.…”

Section: Introductionmentioning

confidence: 99%

Multi-stage trajectory planning of dual-pulse missiles considering range safety based on sequential convex programming and artificial neural network

Liu

Zhang

Xiong

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

An algorithm based on sequential convex programming and artificial neural networks is proposed to solve the multi-stage trajectory planning problem of dual-pulse missiles considering range safety. Besides nonlinear dynamics and constraints, the dual-pulse missile introduces many discrete optimization variables (such as the ignition time of the second-stage thrust), and the algorithm needs to consider throwing the engine off to a safe location to ensure range safety, which makes trajectory planning for the dual-pulse missile more difficult to solve. In this study, the whole trajectory is first divided into four stages according to the working characteristics of the dual-pulse engine. Second, three new control variables are introduced to realize nonlinear dynamics convexification, and the relaxation technique is used to relax the constraints between the control variables to avoid non-convexity. Then, a range prediction function is designed to predict the landing location of the engine in real time. To improve the real-time prediction speed, an artificial neural network is further used to fit the range prediction function. Finally, an algorithm combining sequential convex optimization and an artificial neural network is proposed to solve the multi-stage trajectory planning problem of dual-pulse missiles accurately and rapidly. By comparing with pseudospectral method, two trajectory planning cases are solved by simulation, and the effectiveness and rapidity of the proposed method are verified.

show abstract

“…in [2]), semi-empirical codes (e.g. PRODAS [3] and Missile DATCOM [2]), or wind-tunnel experiments (e.g. in [4]).…”

Section: Introductionmentioning

confidence: 99%

Global Sensitivity Analysis for Modeling the Free-Flight Behavior of an Artillery Projectile

Machala

Collin²,

Gilson³

et al. 2020

AIAA Journal

View full text Add to dashboard Cite

A vehicle's in-flight behavior can be represented by the Newton-Euler equations of motion: usually, such a model has a nonlinear and continuous description based on ordinary differential equations. The model structure can be altered using analytic transformations-such as transformation into a quasi-LPV structure-and, when the model is supposed to reflect an existing physical system, some of its parameters might be uncertain. This paper's objective is twofold: firstly, to investigate if a quasi-LPV model does accurately replicate the physical behavior of a large-caliber spin-stabilized projectile in free flight; and secondly, to verify if the available embedded sensors data could be used to determine non-identifiability of uncertain model parameters. In order to investigate these prospects, a permutation-based global sensitivity analysis is employed. The proposed study has highlighted the non-identifiable parameters of the model, either during the whole flight or some periods of it. These results can help to enhance the preparation of free flight experiments at the open-range test site of the French-German Research Institute of Saint Louis. Nomenclature M = Mach number V = airspeed, m s −1 α, β, α t = angle of attack, angle of sideslip, total angle of attack, deg C X , C N α , C y pα = axial force, normal force slope, and Magnus force slope coefficients C lp , C mα , C mq , C npα = roll damping, pitch moment slope, pitch damping and Magnus moment slope coefficients

show abstract

Approach for Understanding Range Extension of Gliding Indirect Fire Munitions

Cited by 9 publications

References 15 publications

Analisa Pengaruh Aerodinamika Pada Margin Stabilitas Mortir Latih 81 Mm Dengan Sistem Kompresi Udara

Analisa Pengaruh Aerodinamika Pada Margin Stabilitas Mortir Latih 81 Mm Dengan Sistem Kompresi Udara

Multi-stage trajectory planning of dual-pulse missiles considering range safety based on sequential convex programming and artificial neural network

Global Sensitivity Analysis for Modeling the Free-Flight Behavior of an Artillery Projectile

Contact Info

Product

Resources

About