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All Journal International Journal of Applied Mathematics, Sciences, and Technology for National Defense
Oktaviana, Aditya Tri
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Biochemistry, Genetics & Molecular Biology Chemistry Computer Science & IT Mathematics Physics

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Infinite spherical well as model of quantum carnot engine Fahmi, Khazali; Oktaviana, Aditya Tri; Palupi, Endah Kinarya
International Journal of Applied Mathematics, Sciences, and Technology for National Defense Vol. 1 No. 1 (2023): International Journal of Applied Mathematics, Sciences, and Technology for Nati
Publisher : FoundAE

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.58524/app.sci.def.v1i1.175

Abstract

The potential well is a simple example that generally used to present an understanding of quantum mechanics. In this article, we used infinite spherical well model to evaluate the thermodynamic processes in a quantum Carnot engine. The energy of the particles depended on the value of n and l lead to complex calculations. For simplicity we used the φ100 and φ200 quantum states to determine work and efficiency of a quantum Carnot machine. The results obtained show that efficiency depends on the value of  which is the ratio of RC and RB.
Approximation of BPS Skyrme model using modified Lagrangian Skyrmion Oktaviana, Aditya Tri; Rahman Alfarasyi, Abdul; Gia Huy, Truong; Fahmi, Khazali
International Journal of Applied Mathematics, Sciences, and Technology for National Defense Vol. 1 No. 3 (2023): International Journal of Applied Mathematics, Sciences, and Technology for Nati
Publisher : FoundAE

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.58524/app.sci.def.v1i3.302

Abstract

One of the nuclear atomic models represented by Skyrmion was the Skyrme model. This model was a modified nonlinear sigma model with a Skyrme field where the classical solution use generalized sixth order terms and potential terms. The binding energy that will be studied in the Skyrme SU(2) model is to generalize the second order nonlinear sigma model terms with sixth order derivative terms. The Lagrangian will be obtained for these two terms to find the BPS (Bogomolny Prasad Sommerfield) solution for the profile function numerically. The result of numerical calculation will be used to calculate static energy and rotational energy, where the characteristic of the nucleus can be observed from these two energies. Furthermore, the value of the coupling constant in the Lagrangian Skyrmion will be calculated from the static energy and rotational energy obtained previously. These values are expected to help in the application of Skyrme model for many research physics field.
Preliminary study of dynamic modeling based on quaternion analysis for tricopter drone Alam, Agya Sewara; Kusumadjati, Adhi; Oktaviana, Aditya Tri
International Journal of Applied Mathematics, Sciences, and Technology for National Defense Vol. 2 No. 3 (2024): International Journal of Applied Mathematics, Sciences, and Technology for Nati
Publisher : FoundAE

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.58524/app.sci.def..v2i3.530

Abstract

Recently drone was used in many aspects, especially on military operation. Drone type three rotor, namely tricopter, was used for surveillance with stability motion needed too well operating. This study examines the dynamical aspects of a tricopter. A quaternion-based transformation method is developed to transition between reference coordinate systems. It forms a mathematical foundation for modeling tricopter dynamics. The quaternion formulation used as a mathematical tool to obtain equation of motion in translational and rotational. The result show that the derived equations provide a quaternion-based framework for modeling the tricopter's motion, enabling singularity-free transformations and accurate translational and rotational dynamics for real-time flight control and stability. These models form the basis for advanced navigation systems, offering precise trajectory planning and attitude control. Further research should focus on advanced control strategies, aerodynamic effects, and experimental validation to optimize tricopter’s performance.
Shielding innovation for health security: A PHITS-based optimization of Portland material for proton therapy Suyanto, Damar Adhiwidya; Oktaviana, Aditya Tri; Syväjärvi, Mikael; Sardjono, Yohannes; Wijaya, Gede Sustresna; Triatmoko, Isman Mulyadi
International Journal of Applied Mathematics, Sciences, and Technology for National Defense Vol. 3 No. 2 (2025): International Journal of Applied Mathematics, Sciences, and Technology for Nati
Publisher : FoundAE

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.58524/app.sci.def.v3i2.841

Abstract

Proton therapy is an advanced treatment method for cancer that uses protons to irradiate tumors with high precision. However, the high energy of protons requires effective shielding to protect the surrounding environment and personnel from radiation exposure. In this research, the radiation shielding performance of Portland material was evaluated using the PHITS version 3.351 simulation software. The study focuses on assessing the attenuation of radiation within the cyclotron room under various operational conditions. The effectiveness of radiation shielding made from Portland material in a 230 MeV, 300 NA cyclotron room for a proton therapy facility was investigated. The results from PHITS simulations provide insights into the potential of Portland material in reducing radiation levels in proton therapy rooms, contributing to the safety and efficiency of such facilities. This analysis is essential for optimizing shielding design and ensuring compliance with safety regulations in proton therapy facilities.
Model-prototype based flight test: Bringing flight control engineering to life for a reusable rocket with flightgear Oktaviana, Aditya Tri; Alwan, Mochammad Ibnu; Kusumadjati, Adhi; Syväjärvi, Mikael
International Journal of Applied Mathematics, Sciences, and Technology for National Defense Vol. 4 No. 1 (2026): International Journal of Applied Mathematics, Sciences, and Technology for Nati
Publisher : FoundAE

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.58524/app.sci.def.v4i1.1128

Abstract

ackground: Reusable rocket technology has gained significant attention due to its potential to reduce launch costs, development time, and environmental impact. However, conventional development and flight testing of reusable rockets require substantial financial resources and carry high risks of material loss, particularly during early-stage experimentation and in resource-constrained research or defense education environments. Aims: This study proposes a low-cost and accessible approach for reusable rocket development through a Model–Prototype Based Flight Test (MPBFT) method. The aim is to integrate mathematical flight control modeling, prototype-level implementation, and real-time three-dimensional visualization into a single co-simulation framework that enables virtual flight testing without physical launch, specifically for reusable rocket descent and landing maneuvers. Method: The MPBFT framework integrates a dynamic model of the reusable rocket developed in MATLAB/Simulink based on rigid-body flight dynamics, with explicit mathematical formulations including governing differential equations, state-space representation, and closed-loop transfer function. A derivative-based proportional–integral–derivative (PID) controller was designed to regulate the rocket's pitch attitude. Real-time 3D visualization was achieved through co-simulation with FlightGear via UDP communication at 50 Hz. Controller gains were tuned iteratively (Kp=12.5, Ki=0.08, Kd=5.2), and robustness was assessed under parameter perturbations (+20% moment of inertia, +15% damping, step disturbance). Results: Simulation results demonstrated stable closed-loop attitude control with the following quantitative metrics: 8.2% maximum overshoot, 3.87 s settling time (±2%), 0.014° steady-state error, damping ratio of 0.62, integral absolute error of 8.42°·s, and control effort (RMS) of 3.21 N·m. Robustness analysis confirmed that all perturbed configurations remained stable and within acceptable thresholds (overshoot <15%, settling time <6 s, steady-state error <0.1°). The co-simulation successfully provided synchronized real-time 3D visualization of rocket pitch motion during descent. Conclusion: The MPBFT framework is an effective and economical alternative for reusable rocket flight control testing, particularly suitable for research, defense aerospace education, and resource-constrained environments. Future work will extend the framework to multi-axis 6-degree-of-freedom dynamics, hardware-in-the-loop simulation, actuator and sensor modeling, and physical subscale flight validation to further enhance fidelity and applicability for advanced reusable rocket control system development.
Co-Authors Alam, Agya Sewara Alwan, Mochammad Ibnu Gia Huy, Truong Isman Mulyadi Triatmoko, Isman Mulyadi Khazali Fahmi Kusumadjati, Adhi Palupi, Endah Kinarya Rahman Alfarasyi, Abdul Suyanto, Damar Adhiwidya Syväjärvi, Mikael Wijaya, Gede Sustresna Yohannes Sardjono