Table of contents for issue 1, volume 3200, Journal of Physics: Conference Series

1. Introduction

Welcome to the publication of the Proceedings of the International Conference on Aerospace Science and Technology (ICASST) 2025, which was hosted at the facilities of Biblioteca Nacional de Ciencia y Tecnología (BNTC), Instituto Politécnico Nacional (IPN), in Gustavo A. Madero, Mexico City, Mexico, from November 17th to November 21st, 2025. ICASST 2025 was a scientific forum for the dissemination of basic research and/or technological development projects, which allows interaction between professionals, scholars and industrialists, promoting scientific-technological collaborations in the aerospace field and related areas. The program included presentations, round tables, courses/workshops, talk sessions, as well as keynote lectures given by widely recognized national and international experts in their area. The Conference was held in a hybrid way, face-to-face/virtual.

For the review and acceptance of research papers, a high-level Academic Committee was consolidated, consisting of institutional, national and international researchers. Research centres and schools of the Instituto Politécnico Nacional participated in the Scientific Committee, such as Centro de Desarrollo Aeroespacial (CDA), Unidad Profesional Interdisciplinaria en Ingeniería y Tecnologías Avanzadas (UPIITA), Escuela Superior de Ingeniería Mecánica y Eléctrica Unidad Zacatenco (ESIME Zacatenco), Centro de Innovación y Desarrollo Tecnológico en Cómputo (CIDETEC), as well as Centro de Investigación en Computación (CIC). In the national face, we had the participation in the Scientific Committee of Instituto Mexicano del Petróleo (IMP), Centro de Investigación en Matemáticas, A.C. (CIMAT), Unidad de Alta Tecnología, Facultad de Ingeniería, Instituto de Geofísica, Instituto de Física and Facultad de Ciencias of Universidad Nacional Autónoma de México (UNAM), Laboratorio de Instrumentación Espacial of Universidad Nacional Autónoma de México (UNAM), as well as Centro de Investigación y de Estudios Avanzados (CINVESTAV). Finally, the international presence came hand in hand with University Space Engineering Consortium (UNISEC-Global), Tikohnov Moscow Institute of Electronics and Mathematics, HSE University in Russia, University of Bristol in the United Kingdom, Adamson University in Philippines and Kyushu Institute of Technology in Japan. In this way, a rigorous double-blind peer-review process was carried out, which adhered to the best international scientific review practices. Of the total of papers received, there was a 57.1% rejection rate for manuscripts that did not meet the high standards of the peer-review process carried out. Accepted papers were presented orally and subsequently published in the Journal of Physics: Conference Series of the Institute of Physics (IOP) of Great Britain, in an Open Access base, for their worldwide dissemination. Finally, we would like to give a special mention to Secretaría de Investigación y Posgrado (SIP) of Instituto Politécnico Nacional (IPN), México, for the partial financial support received to organise the International Conference on AeroSpace Science and Technology 2025.

List of Conference Committee is available in this PDF.

All papers published in this volume have been reviewed through processes administered by the Editors. Reviews were conducted by expert referees to the professional and scientific standards expected of a proceedings journal published by IOP Publishing.

• Type of peer review: Double Anonymous

• Conference submission management system: Morressier

• Number of submissions received: 14

• Number of submissions sent for review: 13

• Number of submissions accepted: 8

• Acceptance Rate (Submissions Accepted / Submissions Received × 100): 57.1

• Average number of reviews per paper: 3.25

• Total number of reviewers involved: 20

• Contact person for queries:

Name: Abraham de Jesús Pablo Sotelo

Email: abraham@icasst.mx

Affiliation: Instituto Politécnico Nacional

This work presents the optimization of a rectenna as an auxiliary mean for the electrical power subsystem (EPS) of a CubeSat by implementing a microstrip antenna operating in C band. The technical basic requirements of CubeSats have been considered, with emphasis on the limitations of weight, size, misused radiofrequency spectrum and vulnerability caused by failures in the energy supply; searching for solutions or alternatives to increase the CubeSat lifetime and energy efficiency. The rectenna elements were simulated and analyzed with help of the CST STUDIO SUITE for the analysis of the obtained dimensions in the calculation of the parameters for the main antenna. The software ADVANCED DESIGN SYSTEM (ADS) was used for the filter and the voltage multiplier tests. The rectenna analysis and construction delivered the expected results and new considerations for future work in the area.

This article presents the design, integration, and experimental validation of the UHF-band communications subsystem of the K’OTO nanosatellite (1U CubeSat), developed at the High Technology Unit (UAT) of the UNAM Faculty of Engineering as a low-cost educational platform. The system integrates a radio-frequency printed circuit board (PCB), a monopole antenna integrated into the solar panel structure, and an automated ground station, operating under the AX.25 communications protocol and FSK (Frequency Shift Keying) modulation in the UHF band.

The architecture was proposed to support telemetry and command transmission, employing a validation methodology that combines theoretical link modeling, digital simulation, and experimental verification. This approach enables the implementation of a reliable, flexible communication link optimized for the power, mass, and volume constraints typical of CubeSat missions.

The K’OTO mission, planned for deployment from the International Space Station (ISS) in collaboration with the Japan Aerospace Exploration Agency (JAXA), represents a technological advancement in the design of educational nanosatellites in Latin America.

Its development exemplifies collaboration among academia, government, and industry, demonstrating that it is possible to establish a replicable, low-cost satellite communication system that fosters technological advancement and capacity-building in emerging space programs.

The Channel Encoding is crucial in transmission systems. The ideal case must be to encode with the minimum of extra data while maximising protection for the information. Since there exist lots ways for encoding, we must know how to build every type of encoder. In this article, we develop restrictions for Hamming Encoders in order to pose a systematic way to find distinct hamming codes. By knowing the restrictions, we discuss the properties for correcting codes and how much extra information is required for protecting large amount of data giving a way for discern which is an optimal Hamming encoder for the required system, furthermore giving a way for developing it as a programmable Hamming code. The importance in the limitations of the systematization on linear codes are shown, highlighting its importance according to the channel characterisation, being the most important, the Bit Error Rate (BER) parameter.We finally discuss the advantages for choosing one of the catalogue of Linear Codes by modelling it according to probabilistic analysis.

The development of nanosatellites is marked by a high failure rate, where system faults lead to partial or total loss of the satellite. The harsh conditions during rocket launch are a recurring cause of mission failure. The most widely used mitigation strategy is testing and verification: develop the satellite systems and then test them to confirm structural integrity under conditions similar to those expected during launch and start-up. At the National Polytechnic Institute (Instituto Politécnico Nacional IPN-Mexico), the development of satellite systems is a priority. However, in Mexico there is a notable lack of infrastructure to carry out such tests, especially in controlled environments. This project seeks to address this gap by enabling mechanical tests, specifically vibration tests. The work focuses on the design and simulation of a mechanism that generates linear, oscillatory, and controlled motion. Mechanical requirements are derived from relevant international standards, and an iterative design process yields a design that meets the proposed requirements and operating ranges. The design is feasible for mechanical tests with sine and random vibration at adjustable frequencies, applicable to nanosatellite-type test objects.

This paper proposes a comprehensive methodology for optimal maintenance scheduling in gas turbines, based on the analysis of operating parameters and reliability, the maintenance procedures typically exhibit minor variations depending on the turbomachinery application. The procedures applied to power-generation, or onshore systems differ in concept from those employed on offshore platforms.

For example, the following cases may occur: The approach combines the principles of Reliability-Centered Maintenance (RCM), the Maintenance Management System (MMS), and the OREDA-type database, along with professional experience in generating plants, with the aim of reducing unscheduled failures and optimizing the availability of generating units.

Through three real-life case studies, failures resulting from poor programming are analyzed, including fouling, mechanical disengagement, and, above all, speed-related failures. The results demonstrate that predictive management based on temperature, vibration, pressure, and angular velocity data can anticipate the deterioration of critical components, improve operational efficiency, and minimize costs associated with downtime, considering that these systems are currently regulated by the electricity market through the National Energy Control Center (CENACE) for onshore applications, both within this country and internationally. The proposed methodology constitutes a tool adaptable to different industrial environments to strengthen the reliability and operational continuity of turbo machinery.

Overall, this methodology contributes to increased operational availability, reliability, and energy efficiency of generating units, as well as a trend toward energy savings that translates into economic benefits for the plant, representing a replicable model for the modern management of critical industrial assets.

Gas turbines are extensively used for electric power generation, in the aviation field, and for mechanical drive applications such as pumps and compressors in the petroleum industry. Their inherent advantages, such as compactness, lightweight design, and compatibility with multiple fuel sources, make them particularly suitable for offshore platform installations. This study presents the field-testing conditions of the system and the corresponding certification process for the intended real-world application, replacing the existing gas turbine, gearbox, and pump units with this new technological solution to assess the performance characteristics of the Solar Centaur 50s Gas Turbine, a key component of the Pump Train: gas turbine, gearbox, torque converter, and screw pump under diverse operating conditions.

The results obtained from the Turbogas C50s program were compared with experimental data obtained from tests conducted in San Diego, California. The calculated thermal efficiency exhibited a maximum deviation of less than 4% at a 50% load condition, with a minimum deviation of 0.725% observed at full load. Moreover, the calculated power output demonstrated a maximum deviation of 2.9% at 50% load, while maintaining an error of less than 0.01% at full load.

The simulated operating cases using the Turbogas C50s thermodynamic simulator were evaluated based on the API-616 to determine the key parameters at the outlet of the gas turbine, through the analysis performed using the Thermoflow program.

In this analysis, the ideal performance map of the Solar Centaur 50s gas turbine was determined by considering the compression ratio and gas turbine inlet temperature as variables. These variables were selected due to their substantial impact on the overall performance of the turbine, as a technological novelty within the national oil industry, considering that four units replaced the ten units previously in operation.

The proliferation of space debris in low orbits constitutes an undeniable problem for current and future space missions, as well as for the astronomical community. Space debris mitigation measures require constant and precise monitoring of these objects; however, this information cannot always be provided by ground-based telescopes. In this work, the use of a digital twin representing an inverse synthetic aperture radar (ISAR) is employed to study centimeter-scale objects such as space debris and meteoroids in low Earth orbit. The evaluation of the concept and feasibility of a system to detect “lethal non-trackable” (LNT) objects in the 1 – 10 cm range using a 35 GHz ISAR with a 6 % bandwidth, a 30 KHz pulse repetition frequency, and a 40 dB gain antenna is made. The feasibility assessment confirms that this configuration provides sufficient spatial resolution and sensitivity to detect LNT debris ranging from 1 to 10 cm in diameter.

In remote volcanic regions, continuous monitoring of glacier retreat and ice-melt dynamics remains a major challenge due to limited accessibility and extreme environmental conditions. To address this, small satellite platforms like CubeSats offer a compact and cost-effective alternative for autonomous Earth observation. This work presents a distributed on-board image processing framework integrated into a satellite data bus architecture, enabling preliminary image discernment directly within the space segment. The system implements brightness and opacity-based selection algorithms to pre-filter images prior to storage or transmission, operating within the constrained computational resources of embedded microcontrollers. By autonomously prioritizing scientifically relevant imagery, the approach optimizes data utilization during the limited ground-station visibility time, thus maximizing the value of each communication period. The proposed architecture distributes processing tasks across interconnected embedded nodes, improving throughput and scalability while maintaining compatibility with distributed satellite systems. This framework demonstrates a feasible pathway toward intelligent, resource-aware payloads for environmental monitoring in inaccessible volcanic regions.