Rocket Science

Space is an emerging domain critical to humankind. Correspondingly, space cybersecurity is an emerging field with much research to be done. To help space cybersecurity practitioners better manage cyber risks, The Aerospace Corporation proposed a space cyber risk management approach dubbed Notional Risk Scores (NRS) within their Space Attack Research and Tactic Analysis (SPARTA) framework, with the intent to help quantify the cyber risks associated with space infrastructures and systems. While intended for adoption by practitioners, NRS has not been analyzed with real-world scenarios, putting its effectiveness into question. In this paper we present an algorithmic description of NRS and characterize its use and effectiveness in a case study of space-related cyber incidents and its strengths, weaknesses, and applicability via 72 real-world cyber attack scenarios against space infrastructures and systems.

We provide M.Tech in Aerospace Engineering to equip students with advanced knowledge in aerodynamics, propulsion, spacecraft design, flight mechanics, and space technology. Through rigorous research, hands-on projects, and industry exposure, we prepare our students to innovate and lead in aviation, defense, and space sectors globally.

In the vast tapestry of human civilization, the Eastern paradigm of technical thought emerges as a profound orientation toward the heavens, where the sky is not merely a backdrop but the central axis around which all innovation and inquiry revolve. This sky-centric worldview, deeply embedded in the philosophical and spiritual fabrics of ancient China and Persia (modern-day Iran), posits the celestial realm as the ultimate source of wisdom, order, and emanation. Unlike Western traditions that often prioritize earthly mastery and individual agency, Eastern sages subordinated terrestrial concerns to the non-material, the ethereal-the "nonessential" as the true essence of being. Here, the sky represents the boundless, the divine harmony that dictates the rhythm of existence, inspiring technical pursuits aimed at bridging the human with the cosmic. This paradigm manifests in the historical successes of rocket and space technologies among Eastern nations, where 60% of emphasis lies on rocketry as a direct extension of ancient skyward aspirations, and 40% on broader space exploration as a quest for celestial understanding.

Some improvement have been incorporated to the Tsiolkovsky rocket equation. The fisrt and almost obvious is that the equation is formulated in vectorial terms. The second, formulation for rotational movement is also contemplated in a new way. Finally, the relativistic form of the equation is deduced in vectorial notation showing some of the difficulties found to progress in it.

The question of the origin of Casimir Siemienowicz (d. after 1651), the artillery engineer of Poland and author of the treatise “Artis Magnae Artilleriae Pars Prima,” remains unresolved. Due to a lack of direct evidence, researchers construct their arguments on ambiguous data contained within four pages of the treatise. Unlike our predecessors, we will pose a different question and use different material. We are not interested in the place from which the engineer originated, but rather in who he considered himself to be. What was Casimir Siemienowicz’s “fatherland” (patria)? The only source for an answer remains the text of “Artis Magnae,” which has not yet been fully used by researchers: we will show how the formulations from this book can shed light on the question of identity of the 17th-century artilleryman. Finally, with the help of prosopographical analysis, we will attempt to explain his choice.

This research introduces a groundbreaking Sea-to-Air missile guidance and defense architecture named GLAUCUS-25, a fully autonomous, AI-empowered missile system tailored for the Bangladesh Armed Forces. Merging cutting-edge Deep Reinforcement Learning (DRL), Transformer-based multi-sensor fusion, Generative Adversarial Networks (GANs) for threat spoofing detection, and dynamic SLAM-guided interception logic, GLAUCUS-25 aims to set a new global standard in missile defense. This expanded paper details the complete technical blueprint of GLAUCUS-25, from embedded code examples to neural design patterns, and proposes a defense strategy that transforms Bangladesh into a sovereign AI military power.

Ukraine's Military Forces, like all contemporary militaries, rely on several Space-based capabilities providing vital support for a range of targeting, navigation, and communications services in terms of directing strikes and battlefield movement. Uniquely, much of Ukrainian Space access is dependent on a diversified patchwork of civil third-party providers 12 , which arose early in the war, and critical targeting information provided by Allies, who have their own Space Forces. Building an in-house Space Forces Capability for Ukraine, which would allow for the integration of targeting, navigation, and communications services into a comprehensive defence and offensive architecture would be the next maturing step in the transformation of Ukraine's military forces from their prewar , and current posture. Critically, Ukraine's key strategic disadvantage is its ongoing reliance on Allies for Spacebased communications coverage, and missile early warning systems. The next extension of this, will be fielding its own strategic weaponry in the form of long-range missile complexes that will require satellite support. Currently, Russia despite its evolving military problems still has a major advantage in terms of its military satellite fleet, such as its reconnaissance satellite programs: Persona satellites, which are high-resolution optical reconnaissance craft designed for detailed imaging; and, Bars-M satellites used for cartography and wide-area reconnaissance with lower resolution imagery. There is also the Liana satellite system, a Space-based intelligence program used for electronic warfare and target designation. Russia's Space-based military assets ensure accurate navigation through the GLONASS system and enhance battlefield situational awareness through Persona, significantly strengthening high-precision weaponry and operational awareness 3. Publicly enunciated in early 2022, Ukraine's Space Access Strategy, has been securing three essential Space services pillars: Pillar 1: Remote Sensing Services Pillar 2: Communications Services Pillar 3: Autonomous Capacity to bring this infrastructure into orbit Arguably, Ukraine's Space Access Strategy has reached in 2025 'Pillar 3', in terms of its armed forces' modernization and capability expansion in missile armament, missile defence, and utilizing Space-based support; where it can move away from dependency on the major Space Powers, developing its own capabilities for it to achieve Space Situational Awareness, and be able to monitor opponent Space activity that could impact on its National Security. It has been recently reported that a programme is being initiated, to seek funding for, "[a] … dual-use satellite constellation, dubbed Intermarsat … [potentially] … comprised of more than 70 small satellites in sun-synchronous orbit at an altitude of about 500 kilometres (310 miles). It would provide daily revisits across the belt between the Baltic and the Mediterranean Sea, covering countries as far north as Finland and Estonia and as far south as Bulgaria." 4 The potential size of the constellation could reduce the effectiveness of Russian Antisatellite threats having a number of redundancies, to distribute functions across several satellites in face of threats, such as: (1) Rendezvous and capture technologies; (2) Direct ascent missile attacks; (3) Nuclear space mines detonations in orbit.

As NASA, the Department of Defense and the aerospace industry in general strive to develop capabilities to explore near-Earth, Cis-lunar and deep space, the need to create more cost effective techniques of propulsion system design, manufacturing and test is imperative in the current budget constrained environment. The physics of space exploration have not changed, but the manner in which systems are developed and certified needs to change if there is going to be any hope of designing and building the high performance liquid propulsion systems necessary to deliver crew and cargo to the further reaches of space. To further the objective of developing these systems, the Marshall Space Flight Center is currently in the process of formulating a Liquid Propulsion Systems testbed, which will enable rapid integration of components to be tested and assessed for performance in integrated systems. The manifestation of this testbed is a breadboard engine configuration (BBE) with facility suppor...

The aerodynamic performance and stability of a rocket during flight are significantly influenced by the design and orientation of its control surfaces. This study investigates the effects of varying grid fin cant angles on the aerodynamic forces and stability characteristics of a rocket. Using ANSYS Fluent and Open Rocket, simulations are conducted at a constant velocity of 100 m/s, with the cant angle ranging from 0° to 15° in increments of 2.5°. The primary objective is to analyze how different grid fin configurations impact drag force, lift characteristics, and overall flight stability. The results provide valuable insights into optimizing grid fin designs for improved aerodynamic efficiency and control, contributing to the enhancement of future highperformance aerospace vehicles.

This article presents a study on the promotion of gender equality in distance learning physics, using experiments with water rockets as a pedagogical tool. A collaboration was carried out between the Technological University of Jalisco in Mexico and the Technological University of Bolívar in Colombia. Through this research, we seek to identify how the implementation of practical activities can influence the participation and interest of students of different genders in the field of physics. The results of the applied methodology are presented, as well as the implications of these findings for future educational practices.

The crisis management system is a key element of a modern, reliable, effective, and sustainable security system. In contemporary settings, management functions are implemented through the capabilities of a command-information system. Consequently, most activities are conducted within cyberspace, meaning that management functions cannot be effectively executed without adequate telecommunications and information technology support. The primary target of hostile cyber activities is precisely the command-information system. Developing an optimal methodology for the use of command-information systems, as well as for prevention and protection against cyber-attacks, is among the most critical tasks for modern defence and security systems. One approach to enhancing risk management is through the application of artificial intelligence (AI). AI should ensure superiority in cyberspace, primarily at the national level, providing the foundation for executing legitimate and lawful cyber activities in a state's defence system. This paper aims to explore the role and significance of artificial intelligence within the realm of cybersecurity by analyzing its implications for risk management in contemporary environments. Command in modern military operations, the nature of modern warfare risks, the protection of command-information systems, the autonomy of artificial intelligence in decision-making, and an understanding of cyber threats are factors through which the challenges of modern command systems can be understood.

The article, based on the structure of elementary particles in the form of spatial vortices revealed in the Theory of Space, the four-dimensional structure of space, and the essence of electromagnetic interactions, formulates Hamilton and Hamiltonian-Jacobi functions describing the free motion of an elementary particle and the system of elementary particles in a hydrogen atom, approximating elementary particles with a single spatial vortex. It is shown that the complex nutation and precession of a spatial vortex identified with an elementary particle can be identified with matter waves described by transverse de Broglie plane waves of classical quantum mechanics on the boundary hypersurface βϰβ, which also determines the limit of applicability of classical quantum mechanics, which reduces the complex trajectory of spatial vortices to the analysis of deformations on one of the boundary hypersurfaces.

The design and analysis of propellant grain configurations is a crucial step in the design of solid propellant rocket motors. This is because the performance prediction relies on accurate calculations of grain geometrical properties. Knowing the grain's burn back phases makes solid rocket motor performance prediction a breeze. This research looked into grain burn back analysis for solid rocket motors using 3-dimensional star grain geometries. Using CATIA's parametric modeling capabilities and the dynamic factors that define the intricate arrangement, the design process begins. The grain configuration is defined by the initial geometry, which is a surface. At each web increment, new surfaces are made and geometrical parameters are calculated to ensure grain burn back. To determine the interior ballistics, the equilibrium pressure approach is employed. Using this method for preliminary grain configuration design is a breeze, and it works with any complicated geometry. This paper calculates the variation of thrust with respect to time as the propellant in the igniter burns, reducing the area of the remaining propellant and causing a change in pressure in the Solid Rocket Motor with respect to time. This change in pressure causes a variation in mass flow rate.The remaining grain area in the Solid Rocket Motor is determined by utilizing MATLAB with a 0.05 mm half set. We use MATLAB to double-check the CATIA numerical findings and make sure we're looking at the right area of the remaining propellant.

Today the field of space transportation is of high interest, as a result of the growing competition world-wide. Of particular note are the new Space Companies in the US, which have increased the pressure that the global space transportation industry is under. With this is mind, DLR proposes a new ceramic rocket engine concept, with the goal of increased efficiency and reliability. Additionally, weight, cost and operational risk will be reduced, aiming to be competitive on the global scale in the future. Concerning these requirements, a specific rocket thrust chamber design, based primarily on the application of transpiration cooled porous and thermo-chemically resistant CMCs as inner combustion chamber liner material, is favored, aiming on the improvement of today's high performance standards, e.g. typical high performance main stage or upper stage propulsion systems. After more than twenty years of intensive technology development, DLR offers within its Black Engine technology program a large portfolio of fiber reinforced structure systems for functional components in rocket thrust chambers or entire rocket engines respectively, using additionally CFRP for load carrying structure components or transpiration lubricated CMC journal bearings for lifetime increase of rocket TPs. One major focus lies on the high ratio of thermal and mechanical load de-coupling capability, promising rocket engines with lifetime and maintenance standards comparable to aviation engines, which will be a significant progress for highly reusable main stages in the near future. The exclusively transpiration cooled ceramic rocket thrust chamber system, leads to several additional system improvements. First, evaluations are ongoing considering a new injection cooling method, where the porous CMC wall takes inherently both the function of cooling and injection. This new method is applied in a novel design concept, reducing significantly typical pressure loss in the combustion chamber process and promising an overall engine efficiency increase of more than 5 %. Not only is the increase in efficiency important, but also the increase in reliability by applying higher blow rates for higher inner wall safety. Technology approaches described above are a world first. Established international producers of launcher propulsion systems usually use metal designs for thrust chambers, with recent improvements coming from AM methods, increasing manufacturing efficiency. DLR's new system improvements using porous CMCs as key components in rocket thrust chambers as well as CMC journal bearings in rocket TPs predicts upcoming international competitiveness in the field of space propulsion.

Today the field of space transportation is of high interest, as a result of the growing competition world-wide. Of particular note are the new Space Companies in the US, which have increased the pressure that the global space transportation industry is under. With this is mind, DLR proposes a new ceramic rocket engine concept, with the goal of increased efficiency and reliability. Additionally, weight, cost and operational risk will be reduced, aiming to be competitive on the global scale in the future. Concerning these requirements, a specific rocket thrust chamber design, based primarily on the application of transpiration cooled porous and thermo-chemically resistant CMCs as inner combustion chamber liner material, is favored, aiming on the improvement of today's high performance standards, e.g. typical high performance main stage or upper stage propulsion systems. After more than twenty years of intensive technology development, DLR offers within its Black Engine technology program a large portfolio of fiber reinforced structure systems for functional components in rocket thrust chambers or entire rocket engines respectively, using additionally CFRP for load carrying structure components or transpiration lubricated CMC journal bearings for lifetime increase of rocket TPs. One major focus lies on the high ratio of thermal and mechanical load de-coupling capability, promising rocket engines with lifetime and maintenance standards comparable to aviation engines, which will be a significant progress for highly reusable main stages in the near future. The exclusively transpiration cooled ceramic rocket thrust chamber system, leads to several additional system improvements. First, evaluations are ongoing considering a new injection cooling method, where the porous CMC wall takes inherently both the function of cooling and injection. This new method is applied in a novel design concept, reducing significantly typical pressure loss in the combustion chamber process and promising an overall engine efficiency increase of more than 5 %. Not only is the increase in efficiency important, but also the increase in reliability by applying higher blow rates for higher inner wall safety. Technology approaches described above are a world first. Established international producers of launcher propulsion systems usually use metal designs for thrust chambers, with recent improvements coming from AM methods, increasing manufacturing efficiency. DLR's new system improvements using porous CMCs as key components in rocket thrust chambers as well as CMC journal bearings in rocket TPs predicts upcoming international competitiveness in the field of space propulsion.

This very short companion note provides a concise technical and tactical assessment of the Shahed-238 UCAV, drawing heavily from a SensusQ analysis by Rainer Pihlakas (April 2024). It highlights key features, potential vulnerabilities, and tactical deployment scenarios of this evolving Iranian drone.

In recent years plenty of research is going on to produce effective manufacturing techniques which can produce complex unique designs with reduced cost and lead time for aerospace applications. In this aspect, Additive manufacturing is getting a wide range of popularity in the aerospace manufacturing domain due to its vast applications and advantages. In terms of geometric flexibility and processing time, additive manufacturing outperforms conventional manufacturing processes. Additive manufacturing has found its place in aerospace, defence, biomedical and automotive industries. However, new application areas like space technology are opening up. This method reduces the demand for industrial infrastructure and produces decentralized products. In this study, we have reviewed the manufacturing of rocket propulsion systems through additive manufacturing techniquesWire-arc additive manufacturing and powder bed fusion are the key areas of focus for us (WAAM). These techniques help produce fewer weight components with part consolidation, reducing tooling and assembly requirements. Combustion chambers and nozzles produced using this method meet the performance requirements, they also demonstrated significant cost and schedule savings for hardware delivery. The components in rocket engines operate in extreme and harsh environments. Thus, special materials and complex geometries are required to achieve high performance. Additive manufacturing techniques can enable this, which in turn enables designer freedom from geometric constraints commonly found using traditional manufacturing techniques. Many other components such as injector systems in rocket engines can be made using additive manufacturing within less time and into a single injector head without traditional welding and joining many components A review discusses manufacturing processes, materials used and properties. It also discusses various challenges faced by additive manufacturing.

The past history of research led by INDELEC in the field of direct lightning protection has been established in a major part owing to experimental studies carried out in very high voltage laboratory, and to in-situ triggered lightning implemented facilities. Several test campaigns has been conducted these past years, particularly in Florida, France and Brazil. The accumulation of expertise outcomes during the test campaigns has been much useful to install and implement a new test facility in Indonesia. This site is located near the Jatiluhur dam on Java Island where the keraunic level is relatively high during both monsoon periods occurring each year. The first goal of this site is to give the ability to test the recently developed range of INDELEC products in its LiRi-LAB high voltage premises. In the long term, these facilities will allow us to conduct studies in order to improve our knowledge of the lightning behavior physics through the observation of the local tropical storm parameters. The installations set up at this foreign site offer the ability, when the proper storm conditions are present, to trigger natural lightning strokes owing to the firing of a rocket towing a continuous or discontinuous copper wire. This specially designed rocket, launched at the appropriate time, will trigger a cloud to ground lightning stroke. The unwound wire trailed by the rocket will guide the lightning discharge, onto our products or installation under test. This appropriate time to launch the rocket is determined by a measurement system integrating several electrical and optical sensors. The goal of this paper, in a first phase, is to describe these installations and the implemented means that must withstand the harsh environment that is lightning in real conditions. Then, in a second step, we will present some storm data and some preliminary electric field measurements.

The past history of research led by INDELEC in the field of lightning protection has been established in a major part thanks to experimental studies carried out in very high voltage laboratory, and to in-situ triggered lightning implemented facilities. Several test campaigns has been conducted these past years in several countries. The accumulation of expertise outcomes during the test campaigns has been used to install and implement a new test facility in Indonesia where the keraunic level is relatively high during both monsoon periods occurring each year. The goals of this site are to give the ability to test the recently developed range of INDELEC and to allow us to conduct pure studies in order to improve our knowledge of the lightning behavior physics. The installations being set up at this foreign site offer the ability, when the proper storm conditions are present, to trigger natural lightning strokes by means of the firing of a rocket towing a continuous or discontinuous copper wire. This specially designed rocket, launched at the appropriate time, will travel at a sufficient speed in order to trigger a cloud to ground lightning stroke. The rocket will guide the lightning discharge, because of the copper wire, onto our products or installation under test. This appropriate time is determined by a measurement system integrated several electrical and optical sensors. The topic of this paper is to describe these installations and the implemented means that must withstand the harsh environment that is lightning in real conditions. Some first measurements will be exposed.

The past history of research led by INDELEC in the field of lightning protection has been established in a major part thanks to experimental studies carried out in very high voltage laboratory, and to in-situ triggered lightning implemented facilities. Several test campaigns has been conducted these past years in several countries. The accumulated experience has been useful to install a new test facility, in Indonesia where the keraunic level is relatively high, that offers the ability, when the proper storm conditions are present, to trigger natural lightning strokes by means of the firing of a rocket towing a continuous or discontinuous copper wire. This rocket will trigger a CG stroke, guiding the lightning discharge, because of the copper wire, onto some lightning protection items or installation under test. The appropriate time for launching is determined by a measurement system integrating several sensors. This paper describes these installations and the implemented means that must withstand the harsh environment that is lightning in real conditions.

There is a pattern in which the time frame of Mars's position within 30 degrees of the lunar node correlates with the highest concentration of rocket fire from Gaza into Israel in relation to the rest of the year. This pattern is outlined and explained in Chapter 24 of Ares Le Mandat(4th ed) and substantiated going all the way back to 2007.

This report is a summary of the state of the art for additive manufacturing (AM) certification. Because the development of AM certification is ongoing across multiple domains and disciplines, and due to the limits of this report, some areas may not be covered as thoroughly as some readers would like. In addition, given the expansiveness of the AM field, this report does not present the final answer to every AM issue. It can, however, serve as a gateway to facilitate discussions among experts and policy makers to bridge technical gaps and provide a baseline from which future research can begin.

Carica papaya, a type of tree from the Caricaceae family, is renowned for its medicinal benefits due to its diverse chemical composition. The leaves of Carica papaya, in particular, are commonly used in traditional medicine for their purported anti-dengue, anti-malarial, antioxidant, and anti-inflammatory properties. However, despite their widespread use, there is limited research available on the antioxidant characteristics of Carica papaya leaves. This study aimed to examine the potential protective effects of Carica papaya leaves methanolic (CPLM) extract against oxidative stress in Artemia salina (brine shrimp). To evaluate the antioxidant potential of CPLM extract, two commonly used antioxidant activity assays, 2,2-diphenyl-1-picrylhydrazyl (DPPH) and Ferric reducing antioxidant power (FRAP) assays, were performed. Additionally, an oxidative stress protection assay was carried out by exposing ten Artemia salina nauplii to CPLM extract for one hour before exposing them to hydrogen peroxide (H2O2). The results of this study showed that the CPLM extract has antioxidant properties. Additionally, the oxidative stress protection assay revealed that the CPLM extract increased the survival rate of Artemia salina nauplii exposed to H2O2. The study suggests that the CPLM extract obtained from Carica papaya leaves possesses antioxidant properties. It can provide protection against oxidative stress caused by hydrogen peroxide in Artemia salina.

Allah, the Creator, is the only Singular Super Force. A unified theory for the major forces gravity, weak, electromagnetic and strong nuclear forces is an intractable challenge to the scientists. This article is an innovative theory for unification of all forces in the universe; S-TOE. My published theory on quantum gravity was the first step. The main parameters and equations of the starting spherical singularity bubble of the early universe; acceleration, wavelength, radius, pressure and speed, were simply derived; named Sayed`s unified forces formula (SUFF). The violation of light speed at the early beginning of universe was dramatically found; 3.93 x 1027 m/s. The wavelength (λ) was also calculated and found to be 1.321 x 10-15 m. The difference, between the calculated force (9.29x1024 N) using SUFF and the Planck force (1.2103 x 1044 N) is might be due to contribution of other predicted forces. The calculated acceleration matches with Planck acceleration. Uniquely in this theor...

In paper the issue of a rocket flight impact and overall survivability of such flight by Apis mellifera (western honeybees) specimens is raised. Author claims that it is the key for using them on Mars for pollination in future, as this species is considered as one of the best pollinators, and should be examined before sending first human missions to the Red Planet. Rocket payload ‘BeeO!Logical’ was designed in order to conduct the research, the first of its kind worldwide. Its assumptions are presented along with overall descriptions of the experiments in two sounding rockets. Analysed data included survivability, carbon dioxide concentration values (respiration levels), temperature and humidity. It has been shown that A. mellifera specimens are able to survive the rocket flight. Project development possibilities are described, including widening the scope of the research with bumblebees (Bombus) and implementation of biocybernetic model of bee colony.

This paper presents the results of the activities carried out in the framework of the Horizon 2020 project C 3 HARME aimed at characterizing a new class of Ultra-High-Temperature Ceramic Matrix Composites (UHTCMC) for application as hybrid rocket nozzle. The material is based on a ZrB2-SiC matrix reinforced with either short or long carbon fibres. An incremental approach has been adopted for the material characterization, in terms of test articles dimensions and geometrical complexity. In particular, a first screening of the most suitable materials candidates has been performed testing small button-like specimens exposed to the supersonic exhaust jet of a 200Nclass hybrid rocket nozzle. Based on the results, flat disks to be placed inside the hybrid rocket combustion chamber were manufactured and tested to assess the capability of larger components to withstand the thermo-mechanical stresses expected inside the rocket. Finally, nozzle throat inserts and complete subscale nozzles were tested, comparing their behaviour to a classical graphite nozzle tested in the same operating conditions. Results showed that long fibers materials with optimised porosity level have strong mechanical properties and outstanding erosion resistance.

The thread joints are often used to connect a rocket tube to a cap and a rocket tube to a nozzle. The connection of two components using a thread joint needs to be considered carefully. The joint is the part that most often fails because it is the location of the stress concentration. The study aims to examine the effect of load variations and thread types on the joint strength between the cap and rocket tube using the finite element method. The analysis was carried out with the help of the Ansys Workbench software. Loads of thread joint was varied 70, 80, 90, 100, and 110 kN. The rocket cap and tube material are Al 6061-T6. Static stress simulation results show that the thread joints both square thread and trapezoidal threads can withstand static loads of up to 100 kN because it has a safety factor of more than 1.25. The trapezoidal thread has a better safety factor than the square thread.

Najpierw uwaga techniczna: Zaleca się ściągnięcie tekstu w postaci pliku PDF i czytanie go w tej formie, bo na stronie Academia.edu jest mało czytelny. A teraz o treści:
Felieton ukazał się w serii publikacji, które były prezentowane pod wspólnym tytułem "wielcy znani i nieznani". W serii tej przywoływano osoby szeroko znane jako wielcy Polacy, ale których niektóre chwalebne aspekty działania były jak gdyby zepchnięte na dalszy plan, zlekceważone, zapomniane.
Jedną z takich postaci był Józef Bem. Znany o ceniony jako wybitny dowódca i wybitny artylerzysta, bohater czczony nie tylko w Polsce, ale także na Węgrzech, gdzie był przywódcą powstania, mający niezliczone pomniki - jako wojskowy.
Tymczasem mało kto pamięta, że Józef Bem ukończył studia inżynierskie, był konstruktorem tak zwanych rakiet kongrewskich, autorem sławnej w całej Europie książki na ich temat i gdy nie mógł z powodów politycznych  pracował jako inżynier w dobrach Franciszka Potockiego, wyposażając je w uzbrojenie techniczne (cukrownie, gorzelnie, młyny). Potem na emigracji w Paryżu ukończył Szkołę Dróg i Mostów i założył w 1835 roku Towarzystwo Politechniczne Polskie.

A 2024 Memorandum to the State of Israel concerning the existence and influence of Mars on regional security and militant rocket fire. Also, a warning that the most severe escalation of 2024 could occur between April 12, 2024 and June 25, 2024

For four consecutive years in 2020, 2021, 2022 and 2023, I predicted the time-frame that an increased number of rockets would be fired into Israel relative to the rest of the year, all by observing the position of the planet Mars in relation to the lunar node. The thesis is that when Mars is within 30 degrees of the lunar node, Gaza militants and the enemies of Israel fire a greater number of rockets at the state of Israel relative to the rest of the year. Since 2007 Gaza militants and Israel’s enemies are influenced by this planet Mars, the ancient god of war. The same god of war that backed the Romans when they sacked the temple in AD 70.

Here are updated stats concerning Gaza and enemy rocket fire and Mars within 30 degrees of the lunar node,

From 2007 - 2023: 24,554 Rockets were fired into Israel

Rockets fired when Mars was within 30 degrees of the lunar node: 16,597

Rockets fired any other time: 7,597

67% of rockets were fired when Mars was within 30 degrees of the lunar node

In 12/17 years between 2007 and 2023, most rockets were fired while Mars was within 30 deg of the lunar node.

Hybrid rocket engines are a green alternative to solid rocket motors and may represent a low-cost alternative to kerosene fueled rockets, while granting performance and control features similar to that of typical storable liquid rocket engines. In this work, the design of a three-stage hybrid launcher is optimized by means of a coupled procedure: an evolutionary algorithm optimizes the engine design, whereas an indirect optimization method optimizes the corresponding ascent trajectory. The trajectory integration also provides the vertical emission profiles required for the evaluation of the environmental impact of the launch. The propellants are a paraffin-based wax and liquid oxygen. The vehicle is launched from the ground and uses an electric turbo pump feed system. The initial mass is given (5000 kg) and the insertion of the payload into a 600-km circular, and polar orbit is considered as a reference mission. Clusters of similar hybrid rocket engines, with only few differences, a...

This paper deals with one of the possible methods of a qualified estimation of tactical and technical parameters of surface-to-air or air-to-air guided missiles. This method is designed to estimate missile flight parameters if they are unavailable from public sources. Although the method does not provide exact values, it is sufficient for modelling and subsequent simulation. This method is based on the use of so-called "characteristic numbers" of the missile and on the assumption of validity of the hypothesis about the similarity of characteristic missile numbers of equal or, respectively, similar technological levels. To validate the obtained parameters, a method of mathematical modelling of the missile guidance process is used. The method can also be used for a qualified estimation of missile parameters in the case of an acquisition process.

As part of the United States Advanced Manned Launch System study to determine a follow-on, or complement, to the Space Shuttle, a reusable single-stage-to-orbit concept utilizing dual-fuel rocket propulsion has been examined. Several dual-fuel propulsion concepts were investigated. These include: a separate-engine concept combining Russian RD-170 kerosene-fueled engines with space shuttle main engine-derivative engines; the keroseneand hydrogen-fueled Russian RD-701 engine; and a dual-fuel, dual-expander engine. Analysis to determine vehicle weight and size characteristics was performed using conceptual-level design techniques. A response-surface methodology for multidisciplinary design was utilized to optimize the dual-fuel vehicles with respect to several important propulsion-system and vehicle design parameters in order to achieve minimum empty weight. The tools and methods employed in the analysis process are also summarized. In comparison with a reference hydrogenfueled single-stage vehicle, results showed that the dual-fuel vehicles were from 10 to 30% lower in empty weight for the same payload capability, with the dual-expander engine types showing the greatest potential.

The present study was conducted to test for in vivo Brine Shrimp Lethality Assay (BSLA) of the ethanolic extracts of Lantana camara, Chromolaena odorata, and Euphorbia hirta and correlate cytotoxicity results with known pharmacological activities of the plants. Novel cytotoxic, antitumor, and pesticidal compounds can be isolated from potential plant sources through the assessment of cytotoxic activity against brine shrimps. Cytotoxicity was evaluated in terms of LC 50 (lethality concentration). Ten nauplii were added into three replicates of each concentration of the plant extract. After 24 hours the surviving brine shrimp larvae were counted and LC 50 was assessed. Results showed that the extracts of L. camara, C. odorata, and E. hirta were potent against the brine shrimp with LC 50 values of 55, 10, and 100 ppm (µg/mL), respectively. It indicated that bioactive components are present in these plants that could be accounted for its pharmacological effects. Thus, the results support the uses of these plant species in traditional medicine.

There is one way to explore space by using the space launch vehicles, which is known as rockets, and it can carry useful load named simply as payload of satelite from Earth into Space. In this study, performance predictions of the multi rocket motors are discussed and compared with single rocket motor with the same amount of propellant used for space travel. In this article in serial or tandem staging schemes, the boosting stage is usually the largest, the second stage and subsequent upper stages are above it, usually decreasing in size are used. In boosting stage parallel staging schemes solid or liquid rocket boosters are used to assist with launch. At low level starting to high altitude higher density fuel solid fuels, kerogen and cryogenic hydrogen(-250°C) are used as fuel. In solid propellants oxidizer is generally ammonium per chloride is used but in cryogenic liquid propellants oxygen(183.3°C) are used. In the first stage, both liquid propellant in a booster and five solid rocket propellent are used to reach about a certain altitude and velocity. In second stage, after reducing the weight by ejecting the five solid rocket propellent and only liquid propellant is used only to reach the an extra altitudes and velocities at low earth orbit (LEO). Drag and gravity effects are successfully used in all of the calculations. The added total result of velocities and altidudes found by these staged rockets are higher than the first single staged case. The advantage of multistage rockets, having same amount of propellant in staged rockets where total velocity will be increased by separating and removing waste from the system weight out of the system. Use of staged rocket system are usefull for increasing the amount of payload and decreasing the cost per unit weight as well.

Future single stage to orbit systems will utilize oxygenhydrogen propellants in their main propulsion means due to the propellant 's high energy content and environmental acceptability. Operational effectiveness studies, and life cycle cost studies have indicated that minimizing the number of different commodities on a given vehlcle, not only reduces cost, but reduces the ground span times in both the pre and post flight operations. Therefore it make sense that, oxygen and hydrogen should be utilized for the reaction controls systems, eliminating the need to deal with toxic or corrosive fluids.

Introduction: Nature has been an attractive source of new therapeutic candidate compounds. The plants produce naturally occurring secondary metabolites which are being investigated for their anticancer and antioxidant activities. Tithonia diversifolia and Gliricidia sepium are commonly growing in Bukidnon, Philippines. These plants have long list of ethno-medicinal uses. Thus, there is a need to further investigate their phytochemical constituents as well as their biological activities. Objectives: The study focuses on the phytochemicals in the ethanolic leaf extracts of T. diversifolia and G. sepium collected from Bukidnon, Philippines. Moreover, cytotoxic and antioxidant properties of the extracts were also determined through Brine Shrimp Lethality Assay (BSLA) and Total Antioxidant Capacity, respectively. Materials and Methods: Qualitative phytochemical screening and determination of Total Phenolic Content (TPC), Total Flavonoid Content (TFC), Total Antioxidant Capacity (TAC) and cytotoxicity of the ethanolic leaf extracts of T. diversifolia and G. sepium were conducted. Results and Discussion: Results of the study showed the presence of flavonoids, phenolics, tannins and terpenoids in the ethanolic leaf extracts of T. diversifolia and G. sepium. The TPC of T. diversifolia (15.20 mg GAE/g dry sample) was found higher than that of G. sepium (14.43 mg GAE/g dry sample). Similar trend was also observed in the TFC where T. diversifolia and G. sepium recorded 12.50 and 9.00 mg QE/g dry sample, respectively. T. diversifolia also gave higher TAC of 302.8 mg AAE/ g dry sample than G. sepium (200.2 mg AAE/g dry sample). For cytotoxicity test, T. diversifolia (LC 50 = 14.57 mg/L) exhibited more potent toxicity as compared to G. sepium (LC 50 = 15.85 mg/L). The results indicate that the detected phytochemicals may account for the exhibited biological activities of T. diversifolia and G. sepium. Conclusion: This study uncovers the promising antioxidative and cytotoxic property of G. sepium and T. diversifolia that warrants further investigation.

Hybrid rocket propulsion systems offer many advantages including throttling capabilities and safety. This study investigates the regression rates of non-liquefying fuels in hybrid rocket engines operating under atmospheric pressure conditions with the purpose to investigate the effects of chamber pressure and establishing a pure baseline database. Traditional polymeric fuels were the main focus of the study. The three fuels studied were high density polyethylene (HDPE), polypropylene (PP), and polymethyl methacrylate (PMMA). Regression rates were measured and the a and n experimental constants were obtained. Regression rate correction was also applied. A comparative analysis was performed, comparing the findings with existing literature data. Discrepancies were observed, highlighting the influence of external factors and chamber pressure on regression rates. The findings show discrepancy between the regression rates of fuels under different chamber pressures when compared to other studies, providing valuable insights for fuel selection and mission design. Moreover, the study emphasizes the importance of establishing pure regression rate databases to facilitate accurate comparisons and optimize the performance of hybrid rocket engines.

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The present study was conducted to test for in vivo Brine Shrimp Lethality Assay (BSLA) of the ethanolic extracts of Lantana camara, Chromolaena odorata, and Euphorbia hirta and correlate cytotoxicity results with known pharmacological activities of the plants. Novel cytotoxic, antitumor, and pesticidal compounds can be isolated from potential plant sources through the assessment of cytotoxic activity against brine shrimps. Cytotoxicity was evaluated in terms of LC 50 (lethality concentration). Ten nauplii were added into three replicates of each concentration of the plant extract. After 24 hours the surviving brine shrimp larvae were counted and LC 50 was assessed. Results showed that the extracts of L. camara, C. odorata, and E. hirta were potent against the brine shrimp with LC 50 values of 55, 10, and 100 ppm (µg/mL), respectively. It indicated that bioactive components are present in these plants that could be accounted for its pharmacological effects. Thus, the results support the uses of these plant species in traditional medicine.

Solid propellants based on potassium nitrate (KNO 3) and sucrose are widely used in rocketry, because they are inexpensive and easily obtainable compounds and also generate high specific thrust. In this study, the performance of propellants based on a mixture of 65 wt% KNO 3 and 35 wt% sucrose, named KNSu, was evaluated.Aluminum waste particles were loading at 2.5 wt%, 5 wt% and 7.5 wt%. Aluminum was used as a powder with an average particle size of 35 μm. Rocket engines were developed and the thrust versus time curves obtained for the samples studied. The results showed that the utilization of 5 wt% caused a 30% increase in both the specific impulse and the average gas ejection velocity when compared to KNSu. The incorporation of 2.5 wt% and 7.5 wt% caused a reduction in the specific impulse and other properties evaluated when compared to KNSu. Based on the results obtained, it is possible to state that the insertion of aluminum waste from the metalworking industry may contribute to the increase of the performance of rockets that use KNSu as a solid propellant.

The purpose of this work is to present the development of a static test bench for amateur rocket engines. This bench has electronic load cell assembled with four calibrated springs in order to measure the impulse and predict the rocket thrust with different dimensions of combustion chambers, nozzles and new kinds of fuel for amateur rockets. This static test bench has a vertical assembly projected in SolidWorks ® , and a computer interface using the LabView ®. The bench was tested using commercial rocket engines from C class, that must presented a total impulse of 5.01-10 N.s. The tests were done in triplicate. The results of thrust (2.41 ± 0.07 N) and total impulse (6.02 ± 0.29 N.s) are in agreement with others values from the literature. The bench demonstrated to be safe and the obtained results are satisfactory for test rocket motors with a total impulse lower than 10 N.s.