Rocket Launch Research Articles

Analysis and Design of a Recyclable Inductive Power Transfer System for Sustainable Multi-Stage Rocket Microgrid with Multi-Constant Voltage Output Characteristics—Theoretical Considerations

After a traditional one-time rocket is launched, most of its parts will fall into the atmosphere and burn or fall into the ocean. The parts cannot be recycled, so the cost is relatively high. Multi-stage rockets can be recovered after launch, which greatly reduces the cost of space launches. Moreover, recycling rockets can reduce the generation of waste and reduce pollution and damage to the environment. With the reduction in rocket launch costs and technological advances, space exploration and development can be carried out more frequently and economically. It provides technical support for the sustainable use of space resources. It not only promotes the sustainable development of the aerospace field but also has a positive impact on global environmental protection, resource utilization, and economic development. In order to adapt to the stage-by-stage separation structure of the rocket, this paper proposes a new multi-stage rocket inductive power transfer (IPT) system to power the rocket microgrid. The planar coil structure is used to form wireless power transfer between each stage of the rocket, reducing the volume of the magnetic coupling structure. The volume of the circuit topology structure is reduced by introducing an auxiliary coil. An equivalent three-stage S/T topology is proposed, and the constant voltage output characteristics of multiple loads are analyzed. A multi-stage coil structure is proposed to supply power to multiple loads simultaneously. In order to eliminate undesired magnetic coupling between coils, ferrite cores are added between coils for effective electromagnetic shielding. The parameters of the magnetic coupling structure are optimized based on the finite element method (FEM). A prototype of the proposed IPT system is built to simulate a multi-stage rocket. A series of experiments are conducted to verify the advantages of the proposed IPT system, and the three-stage rocket system efficiency reached 88.5%. This project is theoretical. Its verification was performed only in the laboratory conditions.

Global 3D rocket launch and re-entry air pollutant and CO2 emissions at the onset of the megaconstellation era

Satellite megaconstellation (SMC) missions are spurring rapid growth in rocket launches and anthropogenic re-entries. These events inject pollutants and carbon dioxide (CO2) in all atmospheric layers, affecting climate and stratospheric ozone. Quantification of these and other environmental impacts requires reliable inventories of emissions. We present a global, hourly, 3D, multi-year inventory of air pollutant emissions and CO2 from rocket launches and object re-entries spanning the inception and growth of SMCs (2020–2022). We use multiple reliable sources to compile information needed to build the inventory and conduct rigorous and innovative cross-checks and validations against launch livestreams and past studies. Our inventory accounts for rocket plume afterburning effects, applies object-specific ablation profiles to re-entering objects, and quantifies unablated mass of objects returning to Earth. We also identify all launches and objects associated with SMC missions, accounting for 37–41% of emissions of black carbon particles, carbon monoxide, and CO2 by 2022. The data are provided in formats for ease-of-use in atmospheric chemistry and climate models to inform regulation and space sustainability policies.

Worldwide Rocket Launch Emissions 2019: An Inventory for Use in Global Models

AbstractThe rate of rocket launches is accelerating, driven by the rapid global development of the space industry. Rocket launches emit gases and particulates into the stratosphere, where they impact the ozone layer via radiative and chemical processes. We create a three‐dimensional per‐vehicle inventory of stratospheric emissions, accounting for flight profiles and all major fuel types in active use (solid, kerosene, cryogenic and hypergolic). In 2019, stratospheric (15–50 km) rocket launch emissions were 5.82 Gg , 6.38 Gg O, 0.28 Gg black carbon, 0.22 Gg nitrogen oxides, 0.50 Gg reactive chlorine and 0.91 Gg particulate alumina. The geographic locations of launch sites are preserved in the inventory, which covers all active launch sites in 2019. We also report the emissions data from contemporary vehicles that were not launched in 2019, so that users have freedom to construct their own launch activity scenarios. A subset of the inventory—stratospheric emissions for successful launches in 2019—is freely available and formatted for direct use in global chemistry‐climate or Earth system models.

PneumoPlanet: An Inflatable Moonbase Concept for the European Space Agency 1. Design and Location

One of the greatest objectives of space exploration today is to establish a permanent outpost on the Moon that would allow exploration of the lunar polar regions and the exploitation of local water resources. We envision this lunar outpost as a structure made up of inflatable elements, which would utilize solar energy to produce biomass, and thus, both oxygen and food for the astronauts. Due to the extremely low weight of the inflatable elements, we could build a very large infrastructure on the Moon with the help of only a few rocket launches. The low cost and the sustainable nature of such infrastructure can lay the foundation for a permanent human presence on the Moon. Keywords: Inflatable, Lunar Habitat, Moonbase, Illumination, Sustainability, Greenhouse, Cultivation

Influence of ideas of Russian cosmism on formation and development of scientific and technical elite of rocket engineering and cosmonautics

The article is devoted to the influence of philosophical and theoretical ideas of the scientific direction of Russian cosmism on their transformation into a scientific and practical plane – the creation of the rocket and space industry, the launch of satellites, rockets, and humans into space. The relevance of the problem considered in the article lies in the fact that space, while remaining the sphere of interests of the leading world powers competing with each other in political, economic, cultural, and military terms, remains a platform for international cooperation, on which factors of national and global security largely depend. In this work, space exploration is considered in the development from philosophical and scientific research of the late 19th – early 20th century to projects of private corporations investing in the exploration of the Moon, colonization of Mars, development of a fleet of interstellar ships for travel to the Alpha Centauri system in our days. Scientific novelty is determined by a comprehensive consideration of the dialectics of the intellectual, creative and pragmatic in matters of space exploration. In a short period of time, under the influence of the philosophical ideas of the scientific direction of cosmism, and their logical continuation in the form of the development of the theory of cosmonautics and rocket science, there was the emergence of a new stratum of society – scientific and technical elite, which brought the country to a new level of technical development, which allows it to remain the world's leading space power to this day.

Dual-mode Antenna Tracking System for Rocket Launch Applications

Rocket launches are complex events that require tracking antennas to maintain a communication link. This study introduces a hybrid tracking strategy that combines manual and program modes by utilizing a predetermined trajectory of the rocket. Automatic switching between tracking modes ensures ongoing monitoring, even during unexpected trajectory changes with the monopulse approach. The dual parabolic antenna arrangement enables this switching. The system estimates the monopulse ratio from the signal strength of each antenna, allowing automatic program tracking to shift to manual mode when reception concerns arise. Performance evaluations included manual, programmable, and dual-mode tests. The system responded to human input and automatically aligned the antenna with slight elevation errors during the initial phase. Adjusting the initial elevation reduced the error. The mode transition was examined by measuring the antenna radiation patterns and monopulse ratio. The system’s performance was evaluated in rocket launches, with the rocket trajectory input into the graphical user interface. The antenna exhibited an azimuthal movement of up to 10 °, and the ratio fluctuation values remained within the antenna’s field of view. After 8.8 seconds, the mode switched from program to manual, indicating that the functioning of the system’s functioning was stable.

Polymeric Reactors for Catalytic Reactions beyond Earth

AbstractCurrent space missions to Luna and Mars are considering to use the resources, which can be found on‐site at the destination. This strategy named in‐situ resource utilization (ISRU) saves valuable pay‐load capacities during the rocket launch from the earth surface. Specifically, in mars missions it is intended to produce the necessary rocket fuel CH4 for the back‐transit to earth via water electrolysis and subsequent CO2 methanation. The present study elaborates this concept and examines the question if polymeric reactors are feasible for heterogeneously catalyzed reactions in applications beyond earth. The study aims at providing a theoretical backbone for a proof‐of‐concept. The evaluation is conducted theoretically by design considerations and adds experimental results to show the general feasibility of polymeric reactors for applicable reaction conditions.

Ppb-level unsymmetrical dimethylhydrazine detection based on In2O3 hollow microspheres with Nd doping

As one of main high-energy fuels for rocket launching, unsymmetrical dimethylhydrazine (UDMH) and its decomposition products do harm to environment and human health. It is significant to develop a device to monitor its leakage. In this work, a UDMH gas sensor based on In2O3 hollow microspheres with Nd dopant was fabricated. The pure, 1.0 mol%, 3.0 mol% and 5.0 mol% Nd doped In2O3 were synthesized via one-step solvothermal method. Among them, 3.0% Nd-In2O3 based sensor exhibits the highest response toward UDMH vapor. Its response value to 100 ppm UDMH is 183.3 at optimal working temperature of 250 °C, 6.8 times higher than that of pure In2O3 (26.8). Besides high response to UDMH, the 3% Nd-In2O3 based sensor represents excellent selectivity, rapid response speed (2 s) and ultra-low theoretical LOD to UDMH (0.28 ppb). The improved gas sensing performance via Nd doping could be attributed to the enhanced specific surface area, increased concentration of adsorbed oxygen and improved adsorption capacity for UDMH molecular on the surface. The excellent sensing performance of Nd doped In2O3 hollow microspheres makes it a promising candidate for real-time UDMH detection.

Evolution of Company Strategies in Response to Dynamic Changes in the Global Rocket Market

Purpose: Explore the genesis of the global rocket launcher market, focusing on its history, current trends, and influencing factors. The research delves into the strategies of aerospace companies and their adaptation to changing market conditions, identifying key elements that shape and modify these strategies. Design / Method / Approach: Multifaceted analytical methodology was utilized, including logical, statistical, and graphical techniques to investigate the rocket launcher market thoroughly. A systemic approach facilitated the examination of the interrelationships among technological innovations, economic implications, and political factors. Structural-functional analysis delineated the operational mechanisms of various market segments, and comparative analysis was used to discern global tendencies and regional specificities. Findings: Reveal an analysis of the strategic approaches of entities engaged in the production of rocket launchers, emphasizing their state of development and evolution over time. This analysis also identifies the factors impacting the rocket launcher market, which are critical for the strategic formulation and adaptation processes. Strategies demonstrating significant efficacy amidst rapid market changes were distinctly highlighted. Theoretical Implications: Contribute to expanding the knowledge base regarding the strategic perspectives of companies in the field of space economics, offering new data and interpretations. This integration of economics, technology, politics, and international relations showcases the benefits of an interdisciplinary approach in understanding complex industry processes in a changing market environment, specifically regarding strategic management in a changing market environment. Practical Implications: As a decision - making guide for industry leaders and professionals, offering data and analytics for strategic planning and informed decision - making. Therefore, the practical value of the research lies in providing useful resources for a wide range of stakeholders, including industry representatives, policymakers, investors, and the academic community. The findings of the study can serve as educational material for courses and programs related to the study of high-tech markets and the formation of a system of strategic management in companies. Originality / Value: Comprehensive perspective on the rapidly evolving rocket launcher industry, with a particular focus on the last twenty years and significant attention to the last five years. This period has seen considerable technological innovations and shifts in the global economy and political landscape, providing insights into the key factors shaping the industry and predictions about future changes and trends. Research Limitations / Future Research: The primary challenge for analyzing the market and company strategies is the limited availability of verified and reliable information, as the rocket launcher market is closely intertwined with state defense programs, which significantly restrict information access. Future research could delve deeper into the impact of technological innovations, government regulations, and the interaction between the rocket launcher market and other aerospace sectors on the strategies of companies from different countries. Given the dynamic nature of the market, regular data updates, at least biennially, are essential for keeping the analysis current. Paper type: Empirical JEL Classification: F23, L1, O3

SpaceX's Network Effects and Innovation Strategy Analysis

The core competitiveness of an enterprise refers to the unique capabilities and resources of an enterprise that stand out in the market and surpass its competitors. This competitiveness is a key factor for the long-term survival and development of enterprises. Business leaders need to carefully analyze and develop the company's core competencies to ensure that the company has a lasting competitive advantage in the market. This paper deeply discusses the core competitiveness of Space X, including product innovation, competitors and differentiated competition, business space, innovation strategy, network effect, and positive feedback loop. The SWOT analysis of SpaceX reveals its strengths in brand reach and technological innovation but also highlights some challenges, such as the lack of products for everyday users. The company's innovative strategies, including reusable rocket launches and Starlink satellite networks, make it a leader in the private space industry. SpaceX The vision for the future transcends commercial space activities to explore and colonize multiple planets, demonstrating its commitment to a sustainable space civilization.

Anthropogenic Impacts in the Lower Stratosphere: Scale Invariant Analysis

Aircraft and rockets entered the lower stratosphere on a regular basis during World War II and have done so in increasing numbers to the present. Atmospheric testing of nuclear weapons saw radioactive isotopes in the stratosphere. Rocket launches of orbiters are projected to increase substantially in the near future. The burnup of orbiters has left signatures in the aerosol. There are proposals to attenuate incoming solar radiation by deliberate injection of artificial aerosols into the stratosphere to “geoengineer” cooling trends in surface temperature, with the aim of countering the heating effects of infrared active gases. These gases are mainly carbon dioxide from fossil burning, with additional contributions from methane, chlorofluorocarbons, nitrous oxide and the accompanying positive feedback from increasing water vapor. Residence times as a function of altitude above the tropopause are critical. The analysis of in situ data is performed using statistical multifractal techniques and combined with remotely sensed and modeled results to examine the classical radiation–photochemistry–fluid mechanics interaction that determines the composition and dynamics of the lower stratosphere. It is critical in assessing anthropogenic effects. It is argued that progress in predictive ability is driven by the continued generation of new and quantitative observations in the laboratory and the atmosphere.

Orthopedics in Space Travel: Developing Procedures to Evaluate the Safety of Implants Amidst the Rise of Commercial Space Tourism

With the rise of commercial space tourism, the barrier of entry into space lowers. Therefore, passengers with more complex medical conditions are predicted to enter space. This report aims to initiate the development of procedures assessing the safety of space travel for individuals with orthopedic implants. In preparation for the 2023 sounding rocket launch by McGill Rocket Team, the Payload subteam developed a bone model, a human model, a finite element analysis model, and a testing model for determining the safety of orthopedic implants under the harsh conditions of spaceflight. Measuring the dynamic forces of the MRT's Portho's rocket in flight yielded vibrations in the 300-2750 Hz range, which is valuable for creating better models of the loading conditions on orthopedic implants in silico. Three point bending testing revealed high precision but low accuracy in measuring the mechanical strength of the models. Ultimately, the study recommends adjusting the human, bone, and testing models to prevent oversimplification. Further, future work should analyze bone screw interfaces on a microscopic level to detect small changes in implant stresses. By implementing these changes, procedures can accurately describe the safety of spaceflight for those with orthopedic implants.

MILITARY ECOCIDE IN UKRAINE AS A DESTRUCTIVE CONSEQUENCE OF THE USE OF RUSSIAN MISSILES AND PROJECTILES

Effectively, russia’s aggression against Ukraine can be considered the first case of intentional ecocide during wartime in this century. Through its actions, russia has caused massive destruction of the animal and plant world, pollution of the atmosphere, Ukrainian fertile lands, and water resources. According to calculations by the working group at the State Environmental Inspection, as of January 2023, the ecological damage to Ukraine during the 11 months of russian military aggression amounts to over 1 trillion 743 billion hryvnias, or over 47.6 billion dollars. This sum includes hundreds of thousands of square kilometers of ruined soil and devastated lands, forest fires, emissions of poisonous substances into the atmosphere, destruction of animals, alterations to the migratory paths of birds, and more. The top five regions most affected by ecocide in Ukraine are Dnipropetrovsk, Kharkiv, Mykolaiv, Donetsk, and Zaporizhzhia regions.
 The study of war ecocide crimes allows to systematise them by the following features: air pollution, soil pollution, destruction of green spaces, destruction of wildlife, water pollution, unauthorized use of subsoil, and disruption of ecosystems Since the beginning of the full-scale armed aggression by russian occupation forces on objects within the 71 territory of Ukraine, almost 6,500 missile strikes and nearly 3,500 aerial strikes have been carried out, resulting in environmental damage.
 Missiles launched onto Ukrainian territory carry hundreds and thousands of kilograms of chemical substances. In case of complete combustion and dispersion of remnants into the surrounding environment, they pose significant pollution and are toxic to all living beings.
 The destruction of the upper fertile layer of soil, which has been forming over centuries, occurs as a result of missile explosions, artillery shells of various types, cluster bombs, drones, mines, and various types of multiple rocket launchers.
 A significant problem is the contamination of soil with chemical substances, leading to a reduction in fertility and causing harm to both humans and animals living in polluted areas. In substantial areas of Ukraine, there is considerable damage to the surface layer of the soil due to the burning of munitions. The detonation of missiles, artillery shells, cluster bombs results in the release of carbon monoxide, carbon dioxide, water vapor, nitrogen oxides, formaldehyde, hydrogen cyanide, nitrogen, as well as a large amount of toxic organic compounds, which then enter the soil.
 According to assessments from the Kyiv School of Economics and Zoï Environment Network, a total of 186,000 km2 of land, nearly 31% of Ukraine's territory, is at risk of damage and pollution. Among them, over 20,000 km2 are damaged by more than 75% In addition to missiles, the aggressor country employs projectiles of various calibers and cluster bombs, the detonation of which causes environmental destruction, including damage to buildings, structures, industrial facilities, soil, wildlife, and ecosystems. Ukrainian land has transformed into a horrifying testing ground for various types of weaponry, including long-range artillery, salvo fire systems, phosphorus bombs, and guided missiles.
 A threatening issue is the replacement of territories, particularly agricultural lands. A mined area loses its intended purpose and cannot be utilized for a long period. Additionally, the demining of such territory requires substantial expenses.
 Therefore, russian missiles and projectiles pose a deadly threat to humans, animals, plants, harm the environment, devastate soil, water bodies, forests, destroy infrastructure, alter landscapes, and dismantle ecosystems.
 Thus, the investigation of war ecocide crimes involving russian missiles and projectiles allows the conclusion that these are extremely harmful actions resulting from military aggression. Those who perpetrate them are well aware of the serious and irreversible long-term damage inflicted on the environment.

Single drop cytometry onboard the International Space Station

Real-time lab analysis is needed to support clinical decision making and research on human missions to the Moon and Mars. Powerful laboratory instruments, such as flow cytometers, are generally too cumbersome for spaceflight. Here, we show that scant test samples can be measured in microgravity, by a trained astronaut, using a miniature cytometry-based analyzer, the rHEALTH ONE, modified specifically for spaceflight. The base device addresses critical spaceflight requirements including minimal resource utilization and alignment-free optics for surviving rocket launch. To fully enable reduced gravity operation onboard the space station, we incorporated bubble-free fluidics, electromagnetic shielding, and gravity-independent sample introduction. We show microvolume flow cytometry from 10 μL sample drops, with data from five simultaneous channels using 10 μs bin intervals during each sample run, yielding an average of 72 million raw data points in approximately 2 min. We demonstrate the device measures each test sample repeatably, including correct identification of a sample that degraded in transit to the International Space Station. This approach can be utilized to further our understanding of spaceflight biology and provide immediate, actionable diagnostic information for management of astronaut health without the need for Earth-dependent analysis.

Risk analysis of offshore rocket launch propellant filling system under data and knowledge scarcities

To improve the reliability of offshore launch propellant filling systems and mitigate potential hazards in the case of data and knowledge scarcity, a weighted Failure Mode and Effect Analysis (weighted-FMEA) methodology is proposed. A detailed hazard identification framework is proposed to identify potential failure modes of the systems. The Best Worst Method and a comparative matrix is then combined to unify the differences between systems and components. Subsequently, the grey theory is used to mitigate the subjectivity/uncertainty of experts’ judgment. Critical failures and corresponding preventive actions are recommended based on the analysis results. The superiority of the proposed model is confirmed by a comparison analysis with existing methods. Overall, the proposed weighted-FMEA model helps to prevent accidents and ensures the safe operation of offshore propellant-filling systems.

Nonequilibrium Flow Simulations Using Unified Gas-Kinetic Wave-Particle Method

Nonequilibrium flows are commonly encountered in aerospace engineering applications such as spacecraft reentry, rocket launch, and satellite attitude control. Numerical simulations help greatly in the understanding of nonequilibrium flow, multiscale effects, and the dynamics in these applications. Coupling particle transport and collision within the gas evolution process, the unified gas-kinetic wave-particle (UGKWP) method has been developed for multiscale flow simulation, offering a strategy that strikes a balance between accuracy and efficiency. In the present study, the UGKWP method simulates challenging flow problems with large Knudsen number variations, including supersonic flow around a sphere, hypersonic flow around a space vehicle, nozzle plume into vacuum, and side-jet impingement on the hypersonic flow. The UGKWP accurately captures complex flow structures and has been verified through experimental data or direct simulation Monte Carlo results. Regarding computational cost, the UGKWP method requires only 60 GiB of memory to simulate the three-dimensional space vehicle with 560,593 cells under various flow conditions, which is manageable even on personal workstations. Given its excellent efficiency and accuracy, the UGKWP method shows its substantial benefits in simulating multiscale flow for aerospace engineering applications.

Multiphysics and multi-scale design and analysis of nuclear thermal propulsion pellet bed reactor based on spherical cermet fuel element

Due to the advantages of high thrust and high specific impulse, nuclear thermal propulsion (NTP) is a preferred near-term rocket engine technology for future Mars missions. This article introduces the reactor design based on spherical cermet fuel element, with the aim of studying the feasibility of applying this new fuel in NTP system. First, design requirements are determined based on the unique features of NTP. In terms of neutronics, the effect of rocket launch accidents and fuel loss caused by high-temperature hydrogen are considered. Thermal hydraulics refer to the requirements of NASA's Mars Design Reference Architecture 5.0 (DRA 5.0) for impulse, thrust, and thrust to weight ratio. Second, based on the requirements above, the optimal reactor configuration parameters are obtained with the goal of maximizing the thrust to weight ratio: reactor radius 51.1 cm, height 106 cm, aspect ratio 1.04, reflector 13 cm, and reactor mass 3940 kg. Finally, the performances of the optimal reactor design are analyzed. The neutron spectrum shows a characteristic of fast neutron spectrum, and fuel loss analysis shows that the core can withstand a fuel mass loss of about 4 wt%. In addition, the core axial and radial power distribution are calculated, with an overall power peak factor of 1.26. The thermal hydraulic calculation provides a range of core operating conditions that satisfy the design requirements of DRA 5.0 and temperature, with power of 620 ∼ 950 MW and flow rate of 16 ∼ 24 kg/s. Compared with the ANL200/2000 reactor using prismatic cermet, it has the advantage of higher specific impulse. The main disadvantage is the large pressure drop, which prevents it from being applied to the scenarios of high power and high thrust. Therefore, for NTP reactor using spherical cermet elements, it should be applied to low to medium power scenarios.

Research on vibration characteristics of rocket engine flow pipeline

PurposeAbnormal vibrations often occur in the liquid oxygen kerosene transmission pipelines of rocket engines, which seriously threaten their safety. Improper handling can result in failed rocket launches and significant economic losses. Therefore, this paper aims to examine vibrations in transmission pipelines.Design/methodology/approachIn this study, a three-dimensional high-pressure pipeline model composed of corrugated pipes, multi-section bent pipes, and other auxiliary structures was established. The fluid–solid coupling method was used to analyse vibration characteristics of the pipeline under various external excitations. The simulation results were visualised using MATLAB, and their validity was verified via a thermal test.FindingsIn this study, the vibration mechanism of a complex high-pressure pipeline was examined via a visualisation method. The results showed that the low-frequency vibration of the pipe was caused by fluid self-excited pressure pulsation, whereas the vibration of the engine system caused a high-frequency vibration of the pipeline. The excitation of external pressure pulses did not significantly affect the vibrations of the pipelines. The visualisation results indicated that the severe vibration position of the pipeline thermal test is mainly concentrated between the inlet and outlet and between the two bellows.Practical implicationsThe results of this study aid in understanding the causes of abnormal vibrations in rocket engine pipelines.Originality/valueThe causes of different vibration frequencies in the complex pipelines of rocket engines and the propagation characteristics of external vibration excitation were obtained.

Oxygen vacancy based WO3/SnO2-x promote electrochemical H2O2 accumulation by two-electron water oxidation reaction and toxic uniform dimethylhydrazine degradation

The key to constructing an anodic electro-Fenton system hinges on two pivotal criteria: enhancing the catalyst activity and selectivity in water oxidation reaction (WOR), while simultaneously inhibiting the decomposition of hydrogen peroxide (H2O2) which is on-site electrosynthesized at the anode. To address the issues, we synthesized novel WO3/SnO2-x electrocatalysts, enriched with oxygen vacancies, capitalize on the combined activity and selectivity advantages of both WO3 and SnO2-x for the two-electron pathway electrocatalytic production of H2O2. Moreover, the introduction of oxygen vacancies plays a critical role in impeding the decomposition of H2O2. This innovative design ensures that the Faraday efficiency and yield of H2O2 are maintained at over 80 %, with a noteworthy production rate of 0.2 mmol h−1 cm−2. We constructed a novel electro-Fenton system that operates using only H2O as its feedstock and applied it to treat highly toxic uniform dimethylhydrazine (UDMH) from rocket launch effluent. Our experiments revealed a substantial total organic carbon (TOC) removal, achieving approximately 90 % after 120 mins of treatment. Additionally, the toxicity of N-nitrosodimethylamine (NDMA), a byproduct of great concern, was shown to be effectively mitigated, as evidenced by acute toxicity evaluations using zebrafish embryos. The degradation mechanism of UDMH is predominantly characterized by the advanced oxidative action of H2O2 and hydroxyl radicals, as well as by complex electron transfer processes that warrant further investigation.

Unique Carbon Fibers for High-Temperature Applications

Carbon-carbon composites have been used for many decades in applications, such as rocket nozzles, brakes, and thermal protection systems (TPS). The material consists of carbon fiber in a matrix of carbon/graphite. Carbon-carbon provides structural performance while withstanding extremely high temperatures. The material has a low coefficient of thermal expansion and performs well under thermal shock. Interest in carbon-carbon has grown recently with the focus on hypersonic weapon systems that undergo high thermal shock. The challenge with hypersonics is to develop a thermal protection systems that does not ablate or erode so the control surfaces of a hypersonic weapon remain intact to allow for manuevering of the weapon in flight. Most carbon-carbon composites produced to date do ablate at elevated temperatures and there continues to be many applications for this material. Rocket nozzles and throats are a primary example and with the increases in launches of rockets, ablative carbon-carbon will still be key component in launch systems.