Rocket Launch Research Articles

A novel strategy to enhance the cooling effectiveness in a confined porous jet impingement using non-Newtonian fluids

Jet impingement configuration is commonly employed in the thermal management of the gas turbine engines, rocket launchers, and high-density electrical equipment cooling to remove a large amount of heat. Owing to such overwhelming applications, significant research efforts have been devoted to enhance the cooling performance of jet impingement configuration. In this work, the influence of shear-thinning behaviour in overall heat transfer characteristics have been investigated as a function of pertinent dimensionless numbers as 10−6 ≤ Da ≤ 10−2 (Darcy number), 1 ≤ Pe ≤ 102 (Péclet number), 0 ≤ Ri ≤ 4 (Richardson number), 0.4 ≤ n ≤ 1 (shear-thinning index). The numerical results on local thermal non-equilibrium (LTNE) parameter, streamlines and isotherms, local and average Nusselt number are reported for a range of power-law index, Péclet number and Richardson number. All in all, shear-thinning fluids offer 50–60% enhancement in Nusselt number with reference to the Newtonian fluid at a higher Darcy number. A correlation for average Nusselt number is put forward to enable its use for process design calculations.

Simulation of non-stationary gas dynamics of solid propellant rockets launch

The article presents the results of the development of methodology for the calculation of non-stationary gas dynamics processes occurring in gas dynamic paths of rocket engines and environment at the launch of rockets. The method takes into account the change of geometry of solid fuel combustion surface during the operation of the engine and the change in the geometry of the computational domain taking into account the dynamics of rocket launch. Numerical simulation of gas-dynamic processes of the launch of model solid-fuel rocket was done. The unsteady gas-dynamic flow pattern was investigated. The pressure curve in the solid propellant rocket engine combustion chamber, the speed of movement and overload were determined.

Characteristics of thermospheric infrasound predicted using ray tracing and weakly non-linear waveform analyses.

Infrasonic signals refracted by thermal gradients in the rarefied upper atmosphere are modeled using a combination of ray tracing and weak shock theory to develop an understanding of thermospheric infrasound signals produced by energetic, transient sources. Canonical arrival structures in the form of u-wave signatures are identified for returns refracted at lower altitudes within the thermosphere, and possible multi-pathing produced by effective sound speed inflections are investigated to elucidate more complex arrival structures, which are found to be spatially localized. Variability in the source characteristics is investigated and it is found that whereas some waveform phase information is lost due to finite amplitude effects, arrival characteristics are strongly dependent on the peak overpressure near the source. Variability in the propagation path is considered using archived atmospheric specifications and implies that despite uncertainties related to the dynamic and sparsely sampled nature of the atmosphere, thermospheric signatures might be useful in estimating the yield for explosive sources. Last, thermospheric arrivals from a failed rocket launch, as well as those from several large chemical explosions, are analyzed and it is found that qualitative trends match those predicted, and analyses here provide additional insight into such signatures.

Rocket launching activities are associated with reduced insect species richness and abundance in two types of tropical plantations around the Wenchang Satellite Launch Center, southern China

Rocket launches are such rare events that their impacts on the environment or biodiversity are almost never studied. Here we report on changes in local insect diversity in the immediate aftermath of a rocket launch conducted on June 25th, 2016 from the Wenchang Satellite Launch Center, southern China. Rocket fuel emissions and disturbance associated with rocket launches may negatively influence local insect biodiversity. We compared insect community structure before and after the rocket launch in two different tropical tree plantations near the launch site. We studied insect species richness (total species numbers) and abundances (total individuals.of all species) using insect net and mercury lamp trapping in a total of six 20 × 20 m2 plots distributed three each in a mixed plantation of coconut (Cocos nucifera) with 10 native tree species, and a pure coconut plantation. Comparing insect species richness and abundances, we found that species richness and abundances were overall greater in the mixed species plantation compared to the coconut monoculture. We also found that species richness and abundance were overall lower after the launch event. However, there was no significant difference in the response of the two plantations, either in richness or abundance, to the launch disturbance. Therefore, the negative effect appeared indiscriminate with respect to plantation type, and the greater plant diversity or insect diversity in the mixed plantation did not protect against this disturbance. Therefore, the general impact of rocket launching disturbance may be similar to catastrophic disturbances (e.g., typhoons) that cause widespread mortality irrespective of species.

1001 Rocket Launches for Space Missions and Their Infrasonic Signature

AbstractInfrasound array processing is applied to monitor and characterize atmospheric explosions in the context of the Comprehensive Nuclear‐Test‐Ban Treaty. Anyhow, for many infrasound sources the exact location and time are initially unknown and sometimes difficult to precisely estimate afterward. In contrast, rocket launches are well‐defined ground‐truth events generating strong infrasonic signatures. During the last decade, the number of rocket launches for sending satellites into Earth’s orbit and for reaching space strongly increased. We collected ground‐truth information for 1001 rocket launches from 27 global spaceports between 2009 and mid‐2020 and were able to identify infrasound signatures from up to 73% of the launches on the International Monitoring System of infrasound stations. We use these unique data to estimate the global detectability of such events, to characterize rocket infrasound, to derive an amplitude‐energy relation, and to provide the results for further use as a ground‐truth reference in geophysical and atmospheric research.

Flexibility Management for Space Logistics via Decision Rules

This paper develops a flexibility management framework for space logistics mission planning under uncertainty through decision rules and multistage stochastic programming. It aims to add built-in flexibility to space architectures in the phase of early-stage mission planning. The proposed framework integrates the decision rule formulation into a network-based space logistics optimization formulation model. It can output a series of decision rules and generate a Pareto front between the expected mission cost (i.e., initial mass in low Earth orbit) and the expected mission performance (i.e., effective crew operating time), considering the uncertainty in the environment and mission demands. The generated decision rules and the Pareto front plot can help decision makers create implementable policies immediately when uncertainty events occur during space missions. An example mission case study about space station resupply under rocket launch delay uncertainty is established to demonstrate the value of the proposed framework.

A simplified dynamic model and control for a multiple launch rocket system

Multiple launch rocket system, a type of launching platform used to launch kinetic load to hit the target, is an extremely complicated mechanical system with strong vibration because of the jet force. In this study, a nonlinear dynamic model and vibration control of a multiple launch rocket system are presented to reduce vibration and improve position accuracy. A simplified dynamic model of the multiple launch rocket system is derived using the Newton–Euler method, which facilitates the controller design considering the strong complexity of the multiple launch rocket system. On this basis, the feedback linearization technique is introduced to design a nonlinear controller based on the deduced dynamic model. The simulated and experimental results show that the simplified dynamic model–based control effectively can reduce vibration level of the launching system and make the azimuth and elevation angles reach the desired values with smaller error despite of each rocket’s jet force.

Гипотеза об одной причине двух аварий ракет космического назначения

The data on two emergency launches of space rockets in 1975 and in 2015 under the manned programs of the USSR and Russia are analyzed. On the base of the data analysis concerning the external manifestation and the course of two emergencies, a hypothesis is proposed about the possibility of their single cause, which is associated with the fl ows of charged particles that overcame the Earth's protective radiation belts and could lead to accidents during the launches of Soyuz and Progress spacecraft.

Design, Analysis and Simulation of a Single Stage Rocket (Launch Vehicle) Using RockSim

This project describes the design, analysis, assembly and simulation of a single stage model rocket systems, one designed with traditional subsystems for structural, avionics, combustion chamber and recovery integrated to give a desired altitude. The analysis was based on using Rocksim 9.6 to model the different parts that made up a rocket. Aluminium was used for designing the nose cone, the fuselage and the fin set. The combustion chamber, clamps, and nozzle were designed by making use of steel. Because of the high temperature and pressure being generated from the combustion of propellant, steel was suggested. The main and drogue parachutes were designed using tubular Kevlar. And the bulk-head was designed using Basswood. For the recovering of the rocket after launch, main and drogue parachutes were incorporated into the fuselages.

Numerical Analysis and Experimental Test for the Development of a Small Shaped Charge

Currently, shaped charges are widely used in many fields of science and industry. Due to the high efficiency of piercing materials with high strength and hardness, shaped charges are commonly used in mining, military and for structural damage. The main application area of shaped charges is the military industry, where they are used in missiles with warheads (torpedoes, rocket launchers) and for piercing vehicle armor or bunker walls. When analyzing the existing solutions of shaped charges, one can find many typical solutions designed for specific applications. However, there are no universal constructions which, after appropriate regulation, will fulfil their role in a wide range of applications. The subject of this article is a new solution for a shaped charge that is characterized by compact dimensions and a short preparation time. This article presents the results of experimental research and the numerical analyses of such a charge.

On modeling and dynamics of a multiple launch rocket system

Dynamics analysis is currently a key technique to fully understand the dynamic characteristics of sophisticated mechanical systems because it is a prerequisite for dynamic design and control studies. In this study, a dynamics analysis problem for a multiple launch rocket system (MLRS) is developed. We particularly focus on the deductions of equations governing the motion of the MLRS without rockets by using a transfer matrix method for multibody systems and the motion of rockets via the Newton–Euler method. By combining the two equations, the differential equations of the MLRS are obtained. The complete process of the rockets’ ignition, movement in the barrels, airborne flight, and landing is numerically simulated via the Monte Carlo stochastic method. An experiment is implemented to validate the proposed model and the corresponding numerical results.

Delineation of burned arid landscapes using Landsat 8 OLI data: a case study of Karaganda region in Kazakhstan

In arid lands of Central Kazakhstan, fires commonly occur due to both man-made (e.g. space rocket launches) and natural factors. Remote sensing is the best method to identify burned landscapes and to assess their long-term dynamics. In this paper, we assessed total areas and seasonal features of fires using Landsat 8 OLI data of high spatial and temporal resolution, corrected for atmospheric effects. We defined data requirements, considered various spectral indices, and evaluated their suitability for automated delineation of burned areas. Spectral indices included special burn indices (NBRT, MIRBI, NBR, NBR2, BAI) and vegetation indices (MSAVI, MSAVI2, MTVI2, GEMI3) that allowed us to determine the boundaries and severity of fires indirectly based on the state of vegetation. Our study showed that burned areas were most accurately identified using indices of NBR2 (normalized burn ratio 2) and MSAVI2 (modified soil adjusted vegetation index 2). They were extracted using image segmentation and natural breaks classification methods. We have assessed MSAVI2 and NBR2 segmentation results with machine learning metrics, i.e. for Soyuz drop zone (landing area of rocket stages) precision of NBR segmentation equaled 99.5%, recall − 99.5%, accuracy − 98.5%. For Proton drop zone NBR segmentation precision equaled 99.3%, recall − 99.7%, accuracy − 99.4%. MSAVI2 results are less accurate. The accuracy of segmentation significantly depended on the vegetation state which was predetermined by the frequency and severity of previous fires within certain territory.

A completely reusable aerospace system based on subsonic carrier with the return of the first stages to the starting point

The concept of aerospace system based on air launch from subsonic twin-fuselage aircraft and the rocket launch into orbit is investigated. The scheme of aerospace system trajectory providing a return to the starting point both of the carrier and the first rocket stage with liquid-fuel motors is proposed. It was shown that the use of subsonic carrier as a launching platform of the rocket system increases the payload mass by 1.2% of the rocket segment MTOW as compared to autonomous ground take-off. The comparative analysis of three versions of carrier aircraft and three fuel options at the first rocket stage was carried out. Analysis showed that compared to kerosene variant the hydrogen hypersonic booster makes it possible to significantly increase the payload mass while the launching costs stay the same.

Performance Analysis of a Dual-Fuel Sugar Based Solid Rocket Propellant

The effects of dual-fuel on improving the ballistic efficiency of a low energy sugar-based solid rocket propellant were investigated in this paper. This was achieved by establishing a threshold proportion of sucrose to sorbitol that provided the highest ballistic efficiency, using a beam load cell (model single-point 2,000 kg linearly defined by 0-20 kN force, with ±.005 percent precision). Seven different propellant formulations were prepared, loaded into the rocket motor and tested for performance. The major performance parameters of interest were the thrust, total impulse, burn time, delivered specific impulse, delivered characteristic velocity, and the chamber pressure. The formulations tested were potassium nitrate–sucrose propellant (65% KNO3 and 35% sucrose (C12H22O11)) (KNSU); potassium nitrate-sorbitol propellant (65% KNO3 and 35% sorbitol (C6H14O6)) (KNSB); modified potassium nitrate-sucrose propellant (65% KNO3, 32% sucrose (C12H22O11)), and 3% carbon (C) (MODKNSU); potassium nitrate-sucrose-sorbitol propellant (65% KNO3, 25% sucrose (C12H22O11)), and 10% sorbitol (C6H14O6) (KNERK); potassium nitrate-sucrose-sorbitol-carbon propellant (65% KNO3, 24% sucrose (C12H22O11), 10% sorbitol (C6H14O6), and 1% carbon (C)) (MODKNERK); and finally a propellant made from KNO3, sucrose (C12H22O11), sorbitol (C6H14O6), carbon (C) and iron II oxide(Fe2O3) combinations in 65, 30, 3, 1, 1% proportion respectively. The novel result obtained from these experiments was applied to boost the performance of a KNSB rocket propellant motor during a rocket launch experiment. Both static and dynamic rocket motor internal ballistic parameters were then compared. The measured delivered motor average thrust and the effective propellant burn times were recorded as: (164.15N, 3.97s); (102.95N, 6.53s); (65.66N, 9.38s); (79.09N, 3.77s); (243.98N, 3.77s) and (92.6N, 5.89s) respectively. The MODKNERK, was established to produce a most efficient motor and with the full delivery of its ballistic energy. It was also established, that the ballistic and rocket motor efficiency of a lower energy rocket motor can be improved by starting the ignition of such motor with fast burning dual-fuel rocket propellant (MODKNERK).

Performance Analysis of a Dual-Fuel Sugar Based Solid Rocket Propellant

The effects of dual-fuel on improving the ballistic efficiency of a low energy sugar-based solid rocket propellant were investigated in this paper. This was achieved by establishing a threshold proportion of sucrose to sorbitol that provided the highest ballistic efficiency, using a beam load cell (model single-point 2,000 kg linearly defined by 0-20 kN force, with ±.005 percent precision). Seven different propellant formulations were prepared, loaded into the rocket motor and tested for performance. The major performance parameters of interest were the thrust, total impulse, burn time, delivered specific impulse, delivered characteristic velocity, and the chamber pressure. The formulations tested were potassium nitrate–sucrose propellant (65% KNO3 and 35% sucrose (C12H22O11)) (KNSU); potassium nitrate-sorbitol propellant (65% KNO3 and 35% sorbitol (C6H14O6)) (KNSB); modified potassium nitrate-sucrose propellant (65% KNO3, 32% sucrose (C12H22O11)), and 3% carbon (C) (MODKNSU); potassium nitrate-sucrose-sorbitol propellant (65% KNO3, 25% sucrose (C12H22O11)), and 10% sorbitol (C6H14O6) (KNERK); potassium nitrate-sucrose-sorbitol-carbon propellant (65% KNO3, 24% sucrose (C12H22O11), 10% sorbitol (C6H14O6), and 1% carbon (C)) (MODKNERK); and finally a propellant made from KNO3, sucrose (C12H22O11), sorbitol (C6H14O6), carbon (C) and iron II oxide(Fe2O3) combinations in 65, 30, 3, 1, 1% proportion respectively. The novel result obtained from these experiments was applied to boost the performance of a KNSB rocket propellant motor during a rocket launch experiment. Both static and dynamic rocket motor internal ballistic parameters were then compared. The measured delivered motor average thrust and the effective propellant burn times were recorded as: (164.15N, 3.97s); (102.95N, 6.53s); (65.66N, 9.38s); (79.09N, 3.77s); (243.98N, 3.77s) and (92.6N, 5.89s) respectively. The MODKNERK, was established to produce a most efficient motor and with the full delivery of its ballistic energy. It was also established, that the ballistic and rocket motor efficiency of a lower energy rocket motor can be improved by starting the ignition of such motor with fast burning dual-fuel rocket propellant (MODKNERK).

Research on Accurate Impact Point Prediction Methods of Heavy Rocket Debris

Driven by the demands of rocket launching safety and major scientific research projects, this study probes into the process of impact point prediction for heavy debris from rocket launching. By establishing the basic model of impact point prediction, an analysis of error sources of impact point prediction is conducted to define the research direction of improving the accuracy of impact point prediction. The calculation model of heavy debris impact points introduces the concept of comprehensive analysis of big data. Based on the current situation of equipment, it makes full use of valuable measured data resources of rocket launching and the data information of the measured flight and landing area in multiple samples. Using statistical methods, a back calculation of air resistance and velocity correction affecting the impact point calculation is made, thus forming an accurate calculation model of heavy debris impact points. The data validation shows that the real-time prediction accuracy of this model has been greatly improved compared with the original model, which meets the research expectations.

A Moonshot? [Turnstile

Discusses the current activities of Bell Labs. Owned currently by the Finnish company, Nokia, it recently received a US$14.1 million contract from NASA to design and develop a 4G network on the moon. According to Bell Labs, astronauts will use its wireless network for data transmission, controlling of lunar rovers, real time navigation over lunar geography (think Google Maps for the moon), and streaming of highdefinition video It is all a part of the long-term NASA plan, “which entails 37 launches of private and NASA rockets, as well as a mix of robotic and human landers with a ‘Lunar Surface Asset Deployment’ in 2028, likely the beginning of a surface outpost.

The algorithm of processing and presenting the digital trajectory data obtained when launching rocket vehicles

This research aims at finding a generalized algorithm suitable for processing and presenting the trajectory digital parameters of consumer onboard navigation equipment which is used in the process of space rocket launches. Processing and analysis of digital telemetric information coming from the onboard equipment during the flight and containing digital frames of trajectory measurements is one of the priority tasks as it is the analysis of the path deviations of the rocket that makes a significant contribution to a complete and informative assessment of the launch results. It is suggested that the generalized processing and presenting algorithm which contains the initial stages of the primary processing (extraction of digital frame structures, extraction of trajectory parameters from the frames, mathematical transformations of extracted parameters)as well as determination of primary and secondary values are necessary for solving the trajectory task and, eventually, forming a unified digital stream for representing trajectory measurements, for obtaining results of processing in graphical representation software.

Optimization of Targeting Rocket Launchers with Wheeled Robots

The quick launch weapon system is unique. This rocket launcher has a high launch rate, but the rocket launched is one stage lower than the launcher normally launched by ships of this size. For example, a (medium) cruiser would use a fast light rocket launcher to launch a light (small) rocket. Currently rocket launchers are still controlled by humans, using PCs and servo motors as control tools to determine the accuracy of the shooting angle, so complete components are needed when designing the robot so that the robot can work automatically as needed. For the input given, Automatically control the rocket launcher robot and communicate via PC, then use a USB TTL cable to forward commands to the microcontroller, then send it to the Xbee-pro transmitter circuit, then send and receive by the Xbee-pro receiver, and then send the Microcontroller for transmitter control sent to servo and rocket motors in the transmitter control system in the form of a relay. Based on the test results, the robot can guide the rocket launcher at a predetermined angle, and can launch manual rockets, multiple rockets, triple rockets and all rockets, with a success rate of up to 80%.

Система автоматичної стабілізації транспортного модуля реактивних систем залпового вогню

У статті розглядається запропонована конструктивно-компонувальна схема привода системи автоматичної стабілізації (САС) мобільного наземного транспортного модуля реактивних систем залпового вогню (РСЗВ) з гідравлічними опорами. В роботі розроблена структурна схема системи автоматичної стабілізації положення платформи РСЗВ в просторі на основі математичної моделі динаміки САC як об'єкту управління по одному каналу під дією зовнішнього збурення з урахуванням моделі реології ґрунту, як пружно-в'язко-пластичного середовища. САС на основі запропонованої моделі стабілізує положення транспортного модуля РСЗВ в просторі при підготовці до роботи і в процесі застосування при його динамічному навантаженні, а також скорочує час розгортання в бойове положення.