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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. [ABSTRACT FROM AUTHOR]

The emerging arena of space exploration has created opportunities to study cancer cell biology in the environments of microgravity and hypergravity. Studying cellular behavior in altered gravity conditions has allowed researchers to make observations of cell function that would otherwise remain unnoticed. The patient-derived QNS108 brain tumor initiating cell line (BTIC), isolated from glioblastoma (GBM) tissue, was launched on a suborbital, parabolic rocket flight conducted by EXOS Aerospace Systems & Technologies. All biologicals and appropriate ground controls were secured post-launch and transported back to our research facility. Cells from the rocket-flight and ground-based controls were isolated from the culture containers and expanded on adherent flasks for two weeks. In vitro migration, proliferation, and stemness assays were performed. Following cell expansion, male nude mice were intracranially injected with either ground-control (GC) or rocket-flight (RF) exposed cells to assess tumorigenic capacity (n = 5 per group). Patient-derived QNS108 BTICs exposed to RF displayed more aggressive tumor growth than the GC cells in vitro and in vivo. RF cells showed significantly higher migration (p < 0.0000) and stemness profiles (p < 0.01) when compared to GC cells. Further, RF cells, when implanted in vivo in the brain of rodents had larger tumor-associated cystic growth areas (p = 0.00029) and decreased survival (p = 0.0172) as compared to those animals that had GC cells implanted. [ABSTRACT FROM AUTHOR]

To predict the long-term storage capability (LTSC) of composite directors for multiple launch rocket system (MLRS) in the actual environment, a creep constitutive model was established in a three-dimensional nonlinear form, which considered the moisture effect by introducing a moisture shift factor that related to moisture absorption (MA) into the nonlinear Schapery equation. The constitutive model in integral form was transformed into the incremental-iterative form to realize the numerical finite element solution. Quasi-static experiments and short-term creep-recovery tests for E-glass/6509 epoxy resin laminate were performed to obtain the moisture and stress dependent parameters. A coupled numerical model in multi-physical field of moisture diffusion-nonlinear creep was established, and the MA process and creep deformation of composite directors during storage were predicted. The influence law of creep strain on rocket launching was further investigated by establishing the coupled rocket-directors launching dynamics model. The results show that the water diffuses to the inner surface of directors after storage one year in the environment of temperature of 30°C and relative humidity of 70% RH, while a saturated MA state was reached after 8 years storage. Maximum residual strain (RS) in 20 directors locates between the 2nd and 3rd positioning mounting rings, whose distribution likes a saddle-shape. The residual strains of the middle position in the upper and lower rows are the greatest, with a value of 0.38 mm; and the middle position in the left and right columns are the smallest, with a value of 0.33 mm. The creep strain increases the angular displacement and rate in the pitch and yaw directions of the rocket axis. [ABSTRACT FROM AUTHOR]

A comprehensive investigation is undertaken to discern the structure of momentum flux, turbulent kinetic energy, and scalar fluxes like heat, CO 2 , and H 2 O in the atmospheric surface layer (ASL) at the Thumba Equatorial Rocket Launching Station—a coastal station on the west coast of southern peninsular India. The vertical transport, transfer efficiency, and dissimilarity between flux transport are studied as a function of stability using data collected over 1 year. The transfer efficiency for heat fluxes and momentum exhibits a strong dependence on stability (ζ ). However, the transfer efficiency of passive scalars CO 2 and H 2 O displays no apparent dependence on ζ . The correlation between fluxes and squared coherence estimates is evaluated to study the dissimilarity between flux transport. The correlation is strongest among momentum and heat fluxes and between CO 2 and H 2 O fluxes and shows a dependence on the prevailing stability conditions. However, the influence of stability is not evident for the various other combinations. The momentum and heat flux transport is dissimilar for unstable conditions, and it becomes similar during the transition from unstable to near-neutral conditions. The quadrant analysis is employed to study the contribution of different fluid motions to the aforementioned turbulent fluxes. Except for CO 2 and H 2 O fluxes, where all the quadrants have an equal contribution, ejections and sweeps are the dominating contributors for momentum and heat fluxes. The stability conditions greatly determine the ejection-sweep balance for heat flux, while some changes in duration and impact fraction are also detectable for momentum flux. Furthermore, contour maps of joint-probability function (JPDF) of vertical velocity fluctuations ( w ′ ) with streamwise velocity fluctuation ( u ′ ), temperature fluctuation ( T ′ ), and scalar fluctuations, respectively, are also presented. The dominance of the ejection and sweep cycles for turbulent fluxes provide evidence for the presence and importance of coherent structures in ASL. [ABSTRACT FROM AUTHOR]

Eco-friendly and low-temperature liquid hydrogen has been used as propellants for the launching of rockets. As the low-temperature two-phase gas-liquid flow differs from room-temperature flows, studying the motion of bubbles in the liquid hydrogen fluid is of great importance. By using the volume of the fluid model on the Fluent software, we perform two-dimensional numerical modeling of single Taylor bubble rising movement and double Taylor bubbles coalescence in stagnant liquid hydrogen fluids in vertical and inclined pipe. The results are as follows: for a single Taylor bubble rising in a vertical and inclined pipe, the main hydrodynamic characteristics in the nose area, the liquid film area and the wake region of bubble are determined with the pipe diameter and the inclination angle. Secondly, for double Taylor bubbles rising in a pipe of different inclination angles, the velocity, length and shape of the leading bubble change little, but the velocity and length of the trailing bubbles reduce initially, then increase and reduce again as the separation distance becomes smaller. The research results are helpful to the study of slug flow patterns in cryogenic two-phase flow, and lay a theoretical foundation for the safe transportation of liquid hydrogen propellant in cryogenic pipelines. [ABSTRACT FROM AUTHOR]

In this paper, we summarised the main field-based approaches and a large volume of data on the territories affected by the Russian space programme conducted at Plesetsk, Baikonur, and Vostochny cosmodromes. Influence of space transportation on the ozone layer depletion, as well as on environmental and human health, is negligible. The environmental consequences of rocket and space activities within launch pads and the terrestrial drop zones of jettisoned first stages of launch vehicles are allowable. Moreover, it is negligible in the second stage drop zones. Unsymmetrical dimethylhydrazine pollution is local and does not result in the formation of ecological disaster zones because ecosystems restore by themselves. Influence of rocket launches on the mesospheric cloud formation is short-time or/and insignificant. The environmental impact of space transportation by the Russian space programme on the terrestrial ecosystems is well-studied. To approve or to disprove these findings similar researches should be carried out in other terrestrial and aquatic drop zones affected due to the space programmes of other countries. [ABSTRACT FROM AUTHOR]

A Venus sample return mission is very interesting from a scientific point of view, for example, analysing the composition of the soil will help us to understand the differences between Venus and Earth. However, such a mission is extremely challenging. On Venus the ground conditions are very harsh (460 °C, 9.6 MPa), the Delta V requirement from surface to orbit is close to the Earth case, and atmospheric drag means that a rocket launch must occur above 55 km and so an Unmanned Aerial Vehicle is required to lift the samples to rocket altitude. Sample return missions have been studied in depth by NASA/JPL and ESA, and in the former case the proposed profile involves several critical points, each with a significant probability of failure: Thermal exposure during sample drilling and ascent to launch altitude. Fast balloon inflation, at 55 km altitude. Difficulties to perform a rendezvous with an orbital vehicle if the upper stage is not manoeuvrable. The purpose of this paper is to propose new methods for meeting the challenge at each critical step and reducing the risks to such a mission. In particular, we propose two innovative methods for thermal control on the lander: advanced thermal insulation and phase change materials. [ABSTRACT FROM AUTHOR]

The launch of a rocket requires an energy comparable to the energy of many natural processes. For large rockets, the energy release reaches 10–100 TJ, and the power of engines reaches 0.1–1 TW. The energy release per unit volume is much higher than the specific energy content and energy release of all natural processes. During the launch and flight of a large rocket, disturbances in the substratum, the atmosphere, the ionosphere, and even in the magnetosphere occur. Effects from rocket engine burns have been studied for more than 60 years. Research results have been published in hundreds of articles, handbooks, and monographs. It turns out that the effects produced exhibit diverse geophysical phenomena. The effects near the rocket trajectory, namely, the regions of depressed electron density (ionospheric holes), and the generation of infrasound and atmospheric gravity waves (density waves) are investigated better than other effects. Great attention has been paid to studying the geomagnetic effect. The following methods have been used in studies: the Doppler effect, the Faraday, incoherent scattering, ionosonde, magnetometric methods, etc. The effects accompanying the launches and flights of rockets are being actively studied even now. For many years, large-scale (1 to 10 Mm) disturbances that occur after rocket launches have been studied. Their study makes it possible to better understand the mechanisms of the propagation of disturbances from a rocket over global distances, the interaction of subsystems in the Earth–atmosphere–ionosphere–magnetosphere system, and the ecological consequences of rocket engine burns. Disturbances occurring in the atmosphere and geospace substantially depend on the state of the atmospheric–space weather, time of day, season, and phase of the solar cycle. Even with the launch of two identical rockets, disturbances in the mentioned system can be very different. It should be borne in mind that rockets differ in power, trajectories, fuel composition, and the location of cosmodromes. Therefore, studying the response of subsystems to rocket launches and flights remains an urgent problem. The purpose of this study is to describe the results of an analysis of the ionospheric effects of the Soyuz and Proton rockets launched during the 24th cycle of solar activity from the Baikonur Cosmodrome. To observe the effects in the ionosphere caused by the launch of the Soyuz and Proton rockets from the Baikonur Cosmodrome, a vertical sounding Doppler radar was used. As a rule, measurements are carried out at two fixed frequencies of 3.2 and 4.2 MHz. The smaller of them is effective when studying the dynamic processes in the E and F1 layers, and the larger one is effective when studying the F1 and F2 layers. The parameters of ionospheric disturbances that followed the launches of 81 Soyuz rockets and 53 Proton rockets from the Baikonur Cosmodrome in 2009–2021 are analyzed. It is confirmed that there are several groups of delay times for the possible reaction of the ionosphere to the launch and flight of the rockets. These delay times varied widely (from 10 to 300 min). The delay time groups correspond to several groups of apparent horizontal velocities of disturbance propagation (100–200, 390 ± 23 m/s, 0.97 ± 0.10, 1.28 ± 0.13, 1.68 ± 0.13, 2.07 ± 0.13 km/s, and approximately 8 km/s). Slow atmospheric gravity waves, atmospheric gravity waves of man-made origin, density shock waves, slow, and ordinary MHD waves have such velocities. As a rule, the generated perturbations (except for shock waves) are quasi-periodic in behavior with a period in the range from 5 to 20 min. The amplitude of the Doppler shift is 0.1–0.3 Hz. The relative amplitude of quasi-periodic variations in the electron density is typically 1‒10% and rarely reaches 20%. [ABSTRACT FROM AUTHOR]

Quantification of unsymmetrical dimethylhydrazine transformation products in solid samples is an important stage in monitoring of environmental pollution caused by heavy rockets launches. The new method for simultaneous quantification of unsymmetrical dimethylhydrazine transformation products in sand samples using vacuum-assisted headspace solid-phase microextraction without addition of water followed by gas chromatography-mass spectrometry is proposed. Decreasing air evacuation time from 120 to 20 s at 23 °C resulted in increased responses of analytes by 25–46% and allowed obtaining similar responses as after evacuation at −30 °C. The best combination of responses of analytes and their relative standard deviations (RSDs) was achieved after air evacuation of a sample (m = 1.00 g) for 20 s at 23 °C, incubation for 30 min at 40 °C, and 30-min extraction at 40 °C by Carboxen/polydimethylsiloxane (Car/PDMS) fiber. The method was validated in terms of linearity (R2=0.9912–0.9938), limits of detection (0.035 to 3.6 ng g−1), limits of quantification (0.12–12 ng g−1), recovery (84–97% with RSDs 1–11%), repeatability (RSDs 3–9%), and reproducibility (RSDs 7–11%). It has a number of major advantages over existing methods based on headspace solid-phase microextraction—lower detection limits, better accuracy and precision at similar or lower cost of sample preparation. The developed method was successfully applied for studying losses of analytes from open vials with model sand spiked with unsymmetrical dimethylhydrazine transformation products. It can be recommended for analysis of trace concentrations of unsymmetrical dimethylhydrazine transformation products when studying their transformation, migration and distribution in contaminated sand. [ABSTRACT FROM AUTHOR]

To recover the global economy, China in 2013 called for a new global strategy, namely, "One Belt and One Road Initiative" (BRI), which aims at reinforcing regional economic cooperation, enhancing regional collaboration of economic policy, and realizing the goal of rapid economic development of member countries. Accelerating industrialization not only has been recognized as an effective way to stimulate economic development, but also lead to the serious issue of environmental pollution, which challenges the environmental sustainability. In this study, we focus on the industrializing region as a study area to investigate the driving factors of environmental pollution. Technically, we utilized satellite observation technique to obtain NO2 columns data to denote environmental pollution and then applied dynamic spatial panel data models to evaluate what affects NO2 pollution levels. The findings are the following. (1) NO2 pollution exhibits significant and positive spatial autocorrelation, indicating spatial spillovers of NO2 pollution. (2) Lebanon, Bangladesh, Kyrgyzstan, and India experienced the largest increase of NO2 pollution while NO2 pollution in Singapore, Hungary, Greece, and Ukraine was substantially reduced. (3) The results of the dynamic spatial panel data models show that both the time dynamics effects and the spatial spillover effects are found to be significant and positive. In other words, both effects should be considered. Population is the foremost contributor to increase NO2 pollution while urbanization is an effective way to reduce pollution. An EKC relationship between NO2 pollution and per capita income was verified. Besides, industrialization, foreign direct investment, and trade openness have positive impacts on NO2 pollution. [ABSTRACT FROM AUTHOR]

With the ever rising demands for cheaper payload delivery to orbit, dual bell nozzle with a potential theoretical performance gain of up to 10% can represents one of the major ways of advance to achieve the goal. The well-known transition unsteadiness in a dual-bell rocket nozzle represents one of the major concerns for the development of such altitude compensating type nozzle (ACN). The present study proposes and investigates the possibilities of secondary radial injection for flow regime transition control. Present experimental results demonstrate potential effects of secondary injection on transition and re-transition control even with a relatively low secondary injection mass flow rates. Doing so, the transition and retransition process were significantly delayed towards the ideal transition point. In addition, side loads have been found to be greatly decreased or even eliminated. [ABSTRACT FROM AUTHOR]

The third flight of the High-Resolution Coronal Imager (Hi-C 2.1) occurred on May 29, 2018; the Sounding Rocket was launched from White Sands Missile Range in New Mexico. The instrument has been modified from its original configuration (Hi-C 1) to observe the solar corona in a passband that peaks near 172 Å, and uses a new, custom-built low-noise camera. The instrument targeted Active Region 12712, and captured 78 images at a cadence of 4.4 s (18:56:22 – 19:01:57 UT; 5 min and 35 s observing time). The image spatial resolution varies due to quasi-periodic motion blur from the rocket; sharp images contain resolved features of at least 0.47 arcsec. There are coordinated observations from multiple ground- and space-based telescopes providing an unprecedented opportunity to observe the mass and energy coupling between the chromosphere and the corona. Details of the instrument and the data set are presented in this paper. [ABSTRACT FROM AUTHOR]

In this paper, we examine a method for launching payloads from Mars, which is an alternative to a rocket launch. The idea is based on the elevator concept using a tether, one end of which is rigidly connected to the natural Martian satellite and the other end has a hook. The lifting device of the tether should capture the spacecraft on the Martian surface by the hook similar to the capturing of a ship-borne aircraft on a naval aircraft carrier. We believe that the required space elevating equipment will be developed in the coming decade. [ABSTRACT FROM AUTHOR]

A physical model is developed for math modeling of interphase interactions at the hot gas–water interface. The heat-and-mass transfer processes in two-phase flows appear at interfaces of phases. Profiles of the heat-and-mass transfer rates versus properties of phases and mode parameters are presented based on the Nusselt criterion equations. The hydrodynamic problem is solved numerically by integrating a set of equations of continuity, Navier–Stokes and energy equations using a control volume method (CVM). The conservation equations are supplemented with source terms: an equation of continuity—with a mass evaporation rate, an energy equation—with heat of interphase interactions. The computation results are compared with experimental data. [ABSTRACT FROM AUTHOR]

The results of development of the normative framework for justifying the residual resource of starting building constructions of space launch vehicles for placing spacecrafts of various purposes into the Earth orbits are presented. Created starting complexes are successfully operated in various countries around the world where space-rocket hardware is well-developed; they represent a set of functionally interconnected mobile and stationary technical objects, control equipment and constructions designed to support and conduct all types of work with start preparation and rockets launching. Their features depend on the type and power of the launch vehicles, infrastructure characteristics (the location of the complex, the nomenclature of space objects, development level in the space-rocket technology area), and tasks which are solved during launching, etc. The solution of various issues, which arise while making the normative framework for justifying the resource of starting complexes, is caused by the need to consider the problems of strength and resource of heterogeneous elements of their designs and space-rocket technology designs. The main methodological stages of resource justification are defined. The limiting resource is considered to be the critical operating time, or the number of cycles (starts) during this time, after which the specified limiting states are reached in the hazardous areas of the structure, such as: critical cracks, fracture, formation of unacceptable plastic deformations, loss of stability, growth of corrosion damages, etc. It is noted that the physical nonlinearity of the material and statistical approaches determine the basis for calculating strength and resource. The classification of loads on the starting complexes is made. The concepts of low- and high-cycle fatigue are used. In developing strength standards and the basis for calculating resource, it is reasonable to use up-to-date methods of technical diagnostics, particularly, methods of holographic interferometry and acoustic emission, and fast-converging schemes of methods for numerical operational calculations. [ABSTRACT FROM AUTHOR]

Abstract: Temporal variations in the relative number of failed rocket launches in Russia (Soviet Union) and the United States have been compared to reveal that these variations are antipersistent. The accident rates of rocket and space equipment launches have been analyzed as a function of the level and phase of solar activity cycle. The relative number of failed launches in Russia (Soviet Union) and the United States for the growth phase of solar activity has been shown to exceed the number for the phase of solar activity decline, although no clear correlation between solar activity and the number of failed launches has been detected. [ABSTRACT FROM AUTHOR]

Oil debris count is an important health monitoring parameter in aero gas turbine engine. Present paper deals with the oil debris analysis collected from the bearing houses and gear box of a military gas turbine engine. Due to relative motion between stationary parts, wearing-out has taken place in turbine bearing house. Improper assembly or dimensional inaccuracies found to be the root cause of high debris generation. For wearing-out of the drive shaft in gear box, lapses in assembly procedure and improper tolerances are found to be responsible. Though high 'g' maneuvers of the aircraft, hard landings, missile launch and bird hit or foreign object impact can lead to such high debris in the oil circuit, utmost care needs to be taken during assembly. [ABSTRACT FROM AUTHOR]

The atmospheric disturbances caused by the first rocket launch from the Vostochnyi Cosmodrome on April 28, 2016, were registered 10-24 min after the launch using the signals of the GPS/GLONASS global navigation satellite systems. The analysis of the spatial distribution of the disturbances allowed the conclusion that the launch vehicle moved northwest from the cosmodrome, which corresponds to a trajectory of the satellite movement to the orbit with an inclination of 98º. [ABSTRACT FROM AUTHOR]

The velocity of spherical gas-dust cloud expansion in the situation when the stages of solid-propellant rocket separate in the upper atmosphere have been determined. The measured velocity vary from 2.5 to 7.5 km/s. The dispersed component accelerates at the front of a shock that develops at engine-thrust shutdown. The model calculations of the gas-dust cloud luminosity intensity qualitatively coincide with the photometric profiles of object images. Such formations can vary from almost homogeneous ball-shaped clouds to rather thin spherical shells depending on the gas-dust cloud mass and the matter distribution within this cloud. [ABSTRACT FROM AUTHOR]

We studied the process of electrification of a rocket during launch and flight in the atmosphere at the active part of its trajectory. The values of charge, field strength, and rocket potential at the launch are estimated. Charging and discharging currents are determined for a rocket flying through clouds and precipitation, and solutions expressing the time variation of the rocket's charge are found. The values of charge, field strength, and rocket potential are obtained as functions of time, together with the engine plume represented as a charged plasma structure. The rocket's charge is shown to tend to an equilibrium state, and the time of reaching it is found. Mechanisms limiting the charge value are considered, and the conditions of origination of an electric breakdown (lightning) between the rocket and atmosphere are determined. [ABSTRACT FROM AUTHOR]

Results of radiophysical and magnetometric observations of dynamical processes in the ionosphere and geomagnetic field that followed launches of four rockets of different power and made from different launching sites are analyzed. It is found that the rocket launches were accompanied by an intensification of wave activity in the ionosphere and geomagnetic field. The medium reactions from various sources (various rockets) were overlapping, which made their identification more difficult. Both ionospheric and geomagnetic disturbances have, most probably, two groups of propagation velocities: about 1.2-1.7 km s and 440-760 m s. Slow MHD waves and internal gravity waves corresponded to these velocities. [ABSTRACT FROM AUTHOR]

The ignition and combustion of dust-gas suspensions are considered. It is shown that the ability of these systems to accumulate heat is determined not only by their kinetic and thermal properties but also by the relation between their reaction surface and the heat-removal surface ( f). Experimental information on flame temperatures, ignition delays, and flame propagation over gas suspensions is processed using the parameter f, and the postulate on the stimulating role of the developed reaction surface in activating these processes is validated. It is shown that during overall burning, diffusion combustion of particles occurs only for rather small values of f. The ambiguous effect of the parameter f on the ignition and combustion processes leads to the necessity of optimizing the fuel size distribution and concentration for the effective operation of the power devices. The role of the macroparameters of two-phase flames of refractory metals in the synthesis of combustion nanoproducts is analyzed. [ABSTRACT FROM AUTHOR]

The trajectories of solar missions that could be realized with conversion launchers are investigated. The insufficient energy resources of the rocket launchers is compensated by multiple gravity-assist maneuvers near terrestrial planets. A method based on the construction of a set of attainability for all the mission trajectories rather than on optimization of separate trajectories is presented, which makes it possible to analyze the problem more widely and to find global extremums using various criteria. Detailed features of the most rational trajectories are given. [ABSTRACT FROM AUTHOR]

In this article, the authors discuss the expected priorities of the U.S. National Aeronautics and Space Administration (NASA). Canadian Member of Parliament Marc Garneau cites the need for an international human mission to Mars to be led by the U.S., while physicist Ed Lu calls for the deflection of a non-threatening asteroid by employing a robotic spacecraft. Science-fiction author Neal Stephenson notes that the development of launch systems will change the relationship of humanity with space.

The article presents science-related news briefs for April of 2015. It states that the U.S. National Aeronautics and Space Administration's (NASA) Messenger spacecraft crashed on the planet Mercury on April 30 after it ran out of fuel. It mentions a NASA super-pressure balloon fell to Earth on April 27 after developing a leak 32 days into its flight circling the around the southern latitudes around Australia. It reports rocket company Blue Origin conducted its first launch test on April 29.

The article offers world news briefs as of April 13-19, 2012. North Korea's Unha-3 space rocket failed some seconds after it was launched and sunk into the Yellow Sea on April 13. U.S.-based Johnson & Johnson Healthcare Products was instructed to pay 1.2 billion dollars to Arkansas for underestimating antipsychotic drug Risperdal risks. The University of Salzburg in Austria dismissed protein crystallographer Robert Schwarzenbacher due to the alleged fabrication of a birch-pollen allergen.

The article offers world news briefs as of April 6-12, 2012. North Korea continued its plan to launch a long-range rocket in defiance of banning missile testing. Great Britain relaunched a one billion pound competition that will provide funding to companies building commercial-scale facilities to capture and store carbon dioxide emissions from power plants. Gary Gibbons was named director of the National Heart, Lung, and Blood Institute (NHLBI) by the U.S. National Institutes of Health (NIH).

The article reports on the Falcon 9 rocket which is expected to have its inaugural test flight within the end of May 2010. It says that the rocket will carry the anticipation of National Aeronautics and Space Administration (NASA) for the new generation of low-cost rockets to ship cargo and people in space. It states that the new rocket is the answer to the problem that faces the next generation of space probes due to the retirement of the Delta II rocket. It mentions that the last launch of Delta will be on 2011 for the Gravity Recovery and Interior Laboratory (GRAIL) which is a mission that will study the core of the moon. According to Alan Stern, planetary scientist and former science chief of NASA, the science mission varies on the cost of launching a vehicle.

The article reports on the investment made by an Internet tycoon who invented PayPal online payment service Elon Musk, to launch a business in rocket production in the U.S. Musk's Falcon 1 rocket is expected to become the first privately funded U.S. rocket to reach the Earth's orbit after Pegasus rocket in 1990.

The author reflects on a study led by Martin Ross which examines the impact of rocket launches on the environment. It states that the study reveals that the emissions from 1,000 rocket launches could add to the climate change as much as the emissions from aviation industry. It is also critical on the environmental threat caused by the continuous expansion of spacecraft industry worldwide.

The article provides information on an interview with Bogdan Sburlea, project manager of the non-profit Aeronautics and Cosmonautics Romanian Association (ARCA). He discusses plans to test-launch Helen, a proof-of-concept rocket of ARCA's bid for the Google Lunar X PRIZE. Sburlea also explains why the test vehicle will not actually make it into orbit.

The article presents excerpts from two articles that derive from "Nature" issues that were published 50 and 100 years prior to the date of this issue.

The article elaborates the third failure experienced by Falcon 1 rocket in the U.S. The rocket was privately funded by Space Exploration Technologies (SpaceX) but the said project failed to launch successfully after the test flight took off on August 2, 2008 from Kwajalein atoll in the Pacific Ocean, wherein the two rocket stages did not separate. The rocket carried three payloads, a U.S. Department of defense satellite called Traiblazer and two National Aeronautics and Space Administration's (NASA) satellites. Presented are the details of the issue.

The article reports on the launch of the China's first lunar orbiter Chang'e on October 24, 2007 that kicked off the country's Moon exploration program. It discusses China's exploration program that is directly aimed at sending astronauts to the Moon by 2020 and become the fifth country to launch a probe into the lunar orbit. Moreover, Joan Johnson-Freese, a China space analyst at the Naval War College in Rhode Island relates that the launch of the Chinese orbiter reflects a technological confidence-builder for the country's space scientists. Furthermore, the article infers that the space program of the country is spurring competition from other Asian countries.

The article reports on the result of the Discovery shuttle lift-off conducted on December 9, 2006 by the National Aeronautics and Space Administration (NASA) in the U.S. According to NASA's flight director Tony Ceccacci, take off was successful with small pieces of foam debris and ice falling off from the shuttle's external fuel tank. The launch was the first since the 2003 Columbia disaster.

Reports on the schedule of the launching of Mars Reconnaissance Orbiter by the U.S. National Aeronautics and Space Administration in Cape Canaveral, Florida. Progress of the agency in Mars exploration; Stability of the Mars program; Price of the orbiter.

Reports that rocket launches in Kazakhstan are causing serious illness among people who live near the take-off site. Health records of children in polluted areas.

Reports that the Space Infrared Telescope Facility (SIRTF) will go into orbit on a Delta rocket from Cape Canaveral, Florida on April 18, 2003. Description of the infrared detectors of the SIRTF; background on the work that went into making the SIRTf; Reason for the numerous delays in the launching of the SIRTF.

Reports on the successful launch of H-IIA rocket by the National Space Development Agency of Japan despite string of problems. Failure of H-II launch in February 2002; Aim to conduct data-relay and zero-gravity research; Instruments that the rocket will carry in the next scheduled launch; Operations of the instruments.

Reports that the Geosynchronous Satellite Launch Vehicle (GSLV), an Indian launch rocket, failed to take off on its attempted flight in April 2001. Impact of this setback on the Indian Space Research Organisation; Objective of the project to end India's dependence on foreign launchers for its satellites; Delays in the GSLV program.

Reports that in September, 1997 India conducted its third consecutive successful flight of the Polar Satellite Launch Vehicle, its most powerful rocket. Details of flight; Comments from prime minister Inder Kumar Gujral.

Reports on the offer by Arianespace to the European Space Agency (ESA) to use two Russian Soyuz launchers for the ESA's Cluster mission. The problems since the explosion of the Ariane-5 launcher; Other plans facing the ESA.

Discusses the importance of the successful launch by Japan's Institute of Space and Astronautical Science of the world's first space-based radio-telescope. The beginning of the Very Long Baseline Interferometry international project; The powerful launcher, the M-V rocket; The opportunities available for lunar and interplanetary missions.

Reports on the warnings from the the Altai Republic State Ecological Committee of the potential dangers of rockets launched from the neighboring Baikonur in Kazakhstan. The warning to Russia's Security Council; The threat to the ecological security due to the toxic garbage.

Reports on the concerns on the safety of the rocket launch sites in China. Concerns about the viability of China's commercial satellite launch capabilities; Allegations of disregard to human safety; Hazards of the rocket launch sites; Comments from the international satellite company Intelsat.

Reports on the successful launching of Japan's H-II rocket from the Tanegashima space center. Reaction of the Science and Technology Agency officials; Significance of the new rocket to the agency's space programs.

Reports on the failed launching of the H-II rocket developed by Japan's National Space Development Agency (NASDA). Cause of the failed launching.