Rocket Type Research Articles

Формування вихідних даних для вирішення задач маршового розрахунку надзвукового обтікання ракет різного компонування

This paper gives a general overview of components and layouts used in supersonic rockets of different purposes. The rocket layout is specified as a structure and a set of components (a wing, a rudder, a stabilizer, a destabilizer, and a superstructure) arranged along the rocket structure. The goal of this work is to develop a unified approach to specifying the shape parameters of rocket layouts regardless of the rocket type. For complex-shape rocket layouts, the paper proposes an approach in which the shapes of the rocket structure and the additional components installed thereon are specified independently. The additional components of the rocket layout are bound to the rocket structure using operation parameters. The use of the operation parameters binds each additional component of the rocket layout to the rocket structure, thus offering a unified method for specifying the geometrical parameters of variously shaped rocket layouts. This approach is developed towards more complex shapes of rocket layout elements arbitrarily placed on rocket structures. The outside shape of each rocket component is specified in a Cartesian system of coordinates rigidly bound thereto. A unified approach to specifying the outside shape of various rocket components is presented. According to the general scheme of specifying the geometrical parameters of rocket layout components, they are specified by three methods: analytically, by plan shape, and by plan shape with board and end chord profiles. To describe the outside shape of a component, the specification method and the number and the values of its key parameters are specified. To specify rocket layout input data, one has to fix the number of additional components to be installed on the rocket structure. For each layout component, the parameters that define its shape, location on the rocket structure, and deflection angle are specified. To each layout component there corresponds an input data set of its own. The set consists of parameters that define the shape of the component and parameters of its operation as a part of the layout. A standard input data file for specifying rocket layout shapes is configured.

31-OR: ROCKET Type 1 Diabetes—Launching Diabetes Self-Management Habits in Youth with New-Onset Type 1 Diabetes

31-OR: ROCKET Type 1 Diabetes—Launching Diabetes Self-Management Habits in Youth with New-Onset Type 1 Diabetes

Adaptive control design for active Pogo suppression based on vibration-acceleration feedback

The Pogo suppression method can be divided into active suppression and passive suppression. For practical engineering, passive suppression is generally achieved through accumulators, but this method sometimes cannot meet the design requirements of liquid rockets with uncertain model parameters and time-varying parameters. As for active suppression methods, state variables are mostly used as feedback thus leading to poor practical feasibility. In this study, an adaptive Pogo active suppression controller design method is proposed where measured acceleration is used as feedback. The eigenspace transformation theory is utilized to design two types of dimensional reduced models: an observation-oriented dimensional reduced model (O-ODRM) and a control-oriented dimensional reduced model(C-ODRM). The former works for observer design, and its state variables can be reconstructed by measuring only the acceleration and can be input to the adaptive controller after matrix operations. The latter is employed for adaptive controller design, and it can effectively process the issues of model parameter uncertainty and time-varying parameters. To demonstrate the effectiveness of the proposed method, a certain type of rocket was selected as the research object for simulation analysis. The simulation results show that the proposed method, which uses measured acceleration as feedback, can achieve Pogo active suppression for liquid rockets with uncertain and time-varying parameters.

Effectiveness Evaluation of Medium-sized Carrier Rockets Based on ADC Method

Using scientific evaluation methods to evaluate the mission effectiveness and cost-efficiency of rockets is one of the important topics in the development of rocket models. Aiming at the problem that the effectiveness evaluation of carrier rockets cannot be quantitatively analyzed, this paper takes the medium-sized carrier rockets, covering both new and old generation ones in service, as the object of establishing a simplified inherent capability index system. The ADC method is utilized to quantitatively evaluate the availabilities, dependabilities, and capabilities of various types of rockets and calculates the corresponding effectiveness and cost efficiencies when performing launch missions in LEO, GTO, and SSO orbits. The results show that Model II has excellent mission effectiveness, which is particularly suitable for medium and high orbit missions; the cost-efficiency of Model III is as good as that of the former, and it can complete many tasks; but Model I is outdated.

American Girl Dolls as Professionals

American Girl Dolls as Professionals

THE ACCURACY OF NUMERICAL SIMULATION OF HUROKET EXTERNAL BALLISTICS BASED ON THE EXAMPLE OF THE M-21OF ROCKET

Using the example of the M-21OF rocket, the deviations of the results obtained by the software developed for solving the equations of external ballistics of rockets by computational methods, are investigated. The applicability of the developed software in real problems in case of the absence of tabular data and during the development of new types of rockets for evaluating their range and compiling ballistic tables is shown.

Orbital Launch Anomalies as Mechanisms of Motion of Space Rockets through MIRCE Space

The main objective of this paper is to briefly describe several orbital launches where space rockets of different types have either never made it to space or failed to deploy their payloads once they got there. The common denominator for a failure of each space rocket type, according to publicly available information provided by their management and sponsoring teams, was a launch anomaly. Based on the extremely short duration of all missions considered, the most probable mechanisms that caused orbital launch anomalies, in accordance to the MIRCE Science theory; have been induced into rockets by human actions during: design, production, assembly, transportation or launch processes. As the anomalies occurred on space rockets that are designed, produced and launched by different companies, located on different continents, it could be concluded that human errors are a generic phenomenon of the human race. The orbital launch anomalies observed in this paper are in agreement with the 5th Axiom of MIRCE Science that states, “Probability of human error in execution of any task is greater than zero”.

LARGE-SCALE REDUCTIONS IN THE ELECTRON DENSITY OF IONOSPHERIC F-REGION, OBSERVABLE ALONG ROCKET TRAJECTORIES AT LAUNCH

Purpose. The object of the study are electron density depletions (‘holes’) occurring in the ionospheric F-region under the action of rocket exhaust products. The purpose is to present and discuss the results of observations concerning the ionospheric holes that were detected in the course of a number of launches of medium-lift Kosmos vehicles from the Kapustin Yar spaceport. Nei- ther that cosmodrome, nor the rocket type had been subjects of similar analysis before. Design/methodology/approach. The observations at the Kapustin Yar cosmodrome were performed with a portable vertical Doppler sounder. The beats between a reference signal and the one reflected from the ionosphere were subjected to spectral analysis, which allowed identifying the principal mode of the Doppler frequency shift and establishing time dependences of that frequency shift. An ionosonde located nearby was used for monitoring the underlying state of the ionosphere. Findings. The measurements performed with the vertical Doppler sounder near the launch site of the medium-lift Kosmos rocket have allowed obtaining first estimates for the principal parameters of the ionospheric holes arising in the F-region along the vehicle trajectory, as well as for the accompanying quasi-periodic variations in the electron density. The spatial scale sizes of the holes have been found to be in excess of 300 km, while the electron density reductions may attain » 50 %. These results are in agreement with the data obtained by international researchers for effects from heavy- and super heavy-lift launch vehicles. Also, note that the types of propellant differed significantly. The propagation velocity of the hole’s front edge was estimated to be » 140 m/s. The hole formation was accompanied by quasi-periodic variations in the Doppler frequency shift as a result of radar signal scattering from the electron density fluctuations produced by propagating atmospheric gravity- and infrasonic waves. The atmospheric gravity waves showed periods in the range from 7 to 20 minutes, and the infrasonic waves had a period close to 2 min. The amplitudes of quasi-periodic electron density variations were estimated for the two modes to be » 0.3 ¸1.5 % and » 0.02 ¸ 0.03 %, respectively. Conclusions. Medium-lift launch vehicles (mass of a few hundred tons) are capable of forming ionospheric ‘holes’ of several hundred kilometers in size and of reducing the electron density in the F-region by a factor greater than 2.

Evaluation of a Paraffin/Nitrous Oxide Hybrid Rocket Motor with a Passive Mixing Device

Hybrid rockets offer numerous advantages over other types of rockets but tend to suffer from low combustion efficiency. Higher efficiency can be achieved by using passive devices in the combustion chamber that promote additional mixing of unreacted propellants. The current work examines a paraffin and nitrous oxide hybrid motor that uses a mixing device located downstream of the fuel grain to enhance combustion efficiency. The mixing device used in this work is a six-port baffle plate. Combustion efficiency, as measured by characteristic velocity, was found to increase by over 40% with the use of the passive mixing device. It was identified that certain high-mass-flux motor configurations resulted in unstable motor operation when the mixing device was present. Experimental results indicate that stable combustion occurs for oxidizer mass flux levels below . Exceeding this limit results in combustion oscillations in excess of 20% of the mean chamber pressure.

Theoretical Model Study on Chemical Compositions Affecting the Space Launch Vehicles

In this paper we clearly discussed about composition of chemical substances that affects the launch vehicle in ground station as well as atmospheric conditions. During the rocket-launching the large amount of inhalation of an exhaust gas released and it majorly affects the surface of the launch pad as well as the atmosphere. In rocket, the combustion produces huge number of hot gases with high temperature and pressure. This hot gas passes into the nozzle and accelerates, that time hot cloud is formed in the ground station which composed of (CO2) Carbon dioxide, (HCl) Hydrogen chloride, and carbon monoxide (CO). These hot gases not only affect the ground surface but also the atmospheric layers, will see how it’s affecting the launch vehicle as well as to protect the environment from air pollution affected by emission of gases from different types of rockets and spacecrafts

Performance Evaluation of the Launch Vehicle Using WAX-Based Altering-Intensity Swirling-Oxidizer-Flow-Type Hybrid Rocket Engine by Means of Evolutionary Algorithms

To improve the thrust by the O/F shift, which is one of the weak points of the hybrid rocket, a method with a variable oxidizer strength has been proposed. In this study, the superiority of this type of hybrid rocket over the conventional hybrid rocket without variable oxidizer supply was compared through several launch vehicle designs, such as altitude maximization by vertical launch and downrange extension problems with an optimized launch angle. A multi-objective evolutionary algorithm and the multi-disciplinary evaluation method of the launch vehicle were applied.

Enhanced Method for Analyzing Pogo Stability of Liquid Rockets with Uncertain-But-Bounded Parameters

The traditional pogo analysis method while dealing with the liquid rocket with parametric uncertainty has a large calculation workload and poor accuracy, especially for heavy rockets. To remedy the deficiency, this paper presents an enhanced method applicable for any type of liquid rocket with parametric uncertainty based on the improved Rubin’s model and interval analysis method. Firstly, the pogo analysis model is established by the improved Rubin’s method. The uncertain parameters are viewed as variables in a bounded interval, and the upper and lower bounds of the damping ratio in the pogo analysis system can be expressed as a function of the uncertain parameters with the help of the Taylor series expansion. The coefficients in the Taylor series are derived by the orthogonality of left and right eigenvectors and Nelson’s method. For the enhance method, the upper/lower bound and sensitivity of Pogo stability can be sought; in addition, an index evaluating the influence of various uncertain parameters on pogo stability is given for reducing calculation burden. The numerical simulations are provided to verify the high efficiency and accuracy of the proposed method and exhibit the effects of various parameter variations on pogo stability.

Gas Chromatography-Mass Spectrometry Quantification of 1,1-Dimethylhydrazine Transformation Products in Aqueous Solutions: Accelerated Water Sample Preparation.

The use of highly toxic rocket fuel based on 1,1-dimethylhydrazine (UDMH) in many types of carrier rockets poses a threat to environment and human health associated with an ingress of UDMH into wastewater and natural reservoirs and its transformation with the formation of numerous toxic nitrogen-containing products. Their GC-MS quantification in aqueous samples requires matrix change and is challenging due to high polarity of analytes. To overcome this problem, accelerated water sample preparation (AWASP) based on the complete removal of water with anhydrous sodium sulfate and transferring analytes into dichloromethane was used. Twenty-nine UDMH transformation products including both the acyclic and heterocyclic compounds of various classes were chosen as target analytes. AWASP ensured attaining near quantitative extraction of 23 compounds with sample preparation procedure duration of no more than 5 min. Combination of AWASP with gas chromatography–mass spectrometry and using pyridine-d5 as an internal standard allowed for developing the rapid, simple, and low-cost method for simultaneous quantification of UDMH transformation products with detection limits of 1–5 μg L−1 and linear concentration range covering 4 orders of magnitude. The method has been validated and successfully tested in the analysis of aqueous solutions of rocket fuel subjected to oxidation with atmospheric oxygen, as well as pyrolytic gasification in supercritical water modelling wastewater from carrier rockets launch sites.

The Effect of Manufacturing Quality on Rocket Precision

The effect of manufacturing quality on rocket impact point dispersion is analyzed. The approach presented here applies to any type of rocket. Here, manufacturing quality is demonstrated for the unguided rocket, and by simulating four typical manufacturing errors: erroneously manufactured warhead, misalignment between the warhead and engine chamber, asymmetrically installed propellant, and error in nozzle manufacturing. A new methodology is proposed, which combines a 3D CAD model of the asymmetrical projectile (due to manufacturing errors) and the improved Six-degrees-of-freedom (6DOF) model of its flight into a comprehensive Monte-Carlo simulation. In that way, the rocket trajectory dispersion is correlated directly to the imperfection of the manufacturing process. Three quality levels are simulated (low, standard, and high quality), and each of the analyzed manufacturing errors depends on the chosen quality. The results show how important it is to impose the highest quality on nozzle manufacturing, and if this condition is not met, reveal if strict tolerances applied to other steps of the manufacturing process can compensate for the consequential drop of precision.

Effect of some Disturbance Factors on Falling Point Distribution of Unguided Rocket

The paper investigates the individual and combined effects of disturbance factors including thrust misalignment, the offset of the centre of gravity and misalignment of the principal axes of inertia on falling point distribution of a type of unguided rocket (fin-stabilized rockets with single-stage solid-propellant rocket engines). The mathematical model used in the paper is developed from an available rocket motion model and solved for a representative rocket which is BM-21 rocket. The obtained results show dependencies of falling point deviation on disturbance parameters. These dependencies agree with the standard data given in the firing table; in addition, they are fuller and more insight ful than the previous research.

Effect of some Disturbance Factors on Falling Point Distribution of Unguided Rocket

The paper investigates the individual and combined effects of disturbance factors including thrust misalignment, the offset of the centre of gravity and misalignment of the principal axes of inertia on falling point distribution of a type of unguided rocket (fin-stabilized rockets with single-stage solid-propellant rocket engines). The mathematical model used in the paper is developed from an available rocket motion model and solved for a representative rocket which is BM-21 rocket. The obtained results show dependencies of falling point deviation on disturbance parameters. These dependencies agree with the standard data given in the firing table; in addition, they are fuller and more insight ful than the previous research.

ОПТИМІЗАЦІЯ НОСОВОЇ ЧАСТИНИ ФЮЗЕЛЯЖУ З ТОЧКИ ЗОРУ АЕРОДИНАМІКИ ЛІТАКА

The paper represents the analysis intended to optimize the fuselage nose section with regard to aircraft aerodynamics in the process of development of an unmanned transport aircraft (UTA). The article deals with provisions of high aerodynamic efficiency that cannot be achieved without proper selection of the shape and optimal fuselage parameters that determine mutual interference of aircraft components and units. When analyzing the flow improvement around the fuselage nose in flight, three fuselage versions were considered listed further: 1) a prototype for testing automatic flight control systems with participation of pilots; 2) a nose symmetrical relative to the fuselage rocket type cylinder axis; 3) a supposedly optimal variant based on the results of previous calculations. The aerodynamic characteristics of 3D fuselage models for positive integer Reynolds numbers (full-scale model) were calculated using the ANSYS software package. Three computational grids were built for these models in ANSYS ICEM CFD. The given version of the fuselage nose section intended for testing automatic flight control systems with participation of pilots initially has the greatest resistance among the considered variants. That is, first variant of the fuselage nose gives substantial braking zone as well as significant flow acceleration zone exists in place where fuselage is transformed into cylindrical part. The variant with the nose section symmetrical relative to the rocket type cylinder axis has smaller braking zone and less dispersed flow in place where fuselage is transformed into cylindrical part and, therefore, it has lower resistance in comparison with the first version. The fuselage execution developed on the basis of the results of previous calculations, despite the extensive acceleration zone at the junction of the nose to the cylindrical part, has shown the least resistance, respectively, and is the best of the considered variants. This is also confirmed by a comparison of streamlines over the nose surface. The streamlines are given for calculations at angle of attack of 8°; at this angle of attack, the difference in the coefficient Cx is clearly visible.

Влияние радиоактивных выбросов полигона «Капустин яр» на экологическую обстановку близлежащих районов

This paper discusses the environmental problems of Kazakhstan and ways to solve them on the territory of test sites in the West Kazakhstan region. The article aims to evaluate the effect of radioactive waste of the landfill on the environment Bokeiorda and Zhangala areas of West Kazakhstan region. As a result of spacecraft launches, the environment of these areas was polluted by the decay products of various types of rocket fuel, nitrogen compounds, heavy metals and other toxic substances. The article provides a theoretical analysis of statistical data on the assessment of the environmental situation in the surrounding areas relative to the Kapustin Yar landfill. Thus, in the areas of the West Kazakhstan region adjacent to the Kapustin Yar landfill, indicators were found for the analyzed period that differ from the national average or control values, which in turn indicates an adverse impact on the environment and human health of radioactive emissions from the Kapustin Yar landfill.

Lifesaving rockets in Sweden. A century of operation

The industrialization in the early 19th century gave rise to a major growth in sea-way transportations in European waters. A direct result of this was a rapid increase in sea disasters, in particular in coastal areas. The United Kingdom was the first nation to implement rescue services around its coasts, and several optional systems, in addition to traditional rescue boats, like rockets, mortars and cannons were tested. By the mid 1840's the “rocket apparatus” was implemented as a standard at many British rescue stations. The first rocket type used was the Dennett-rocket, which was of a design similar to the Congreve rockets. Rocket systems were later also designed in several other European countries with need of effective sea rescue systems.1855 the first rescue station in Sweden was taken into service equipped with a rescue boat and a rocket apparatus of Dennett fabrication. During the following century some 40 rescue stations around the Swedish coast were equipped with rocket apparatus. Over the years to come a number of different new rocket systems were tested and some implemented. Some of the Swedish rescue stations have been preserved and are today museums and it turns out that in total some 40 rockets of different types and ages have been preserved at these museum stations. The official records of all activities conducted over a century have also been saved.The today existing rockets have undergone a detailed technical investigation as for the design, performance and operation. Steps of improvements and potential influence of the general advancements of the solid rocket technology over more than a century, from the Congreve type rockets to the rockets in service at the mid of last century, have been analysed. Basically any improvements were made in small steps to advance the handling of a simple but reliable system and less to implement latest advancements in rocket technology. Like the latest rockets preserved, manufactured in 1950 and 1952, the major bulk of rockets used until the mid 20's century were of a Congreve-similar design with the stick guidance concept. The simplicity and conservative evolution to improve the range is also reflected in the use of a “compound”-type of staging for two- and three-stage rockets.

Attraction of stink bugs to rocket traps with different combinations of wing and landing board color

Abstract The stink bugs, Halyomorpha halys and Riptortus pedestris, are two of the most economically important pests of leguminous crops and fruits in Korea. Here we present the results from a field monitoring test that evaluated the effect of variation in rocket trap type and color on stink bugs captures. We tested various types of rocket traps, along with wing combinations and landing boards of various colors. The test was run in soybean fields in Miryang, Korea. We developed a modified rocket trap intended to enhance the capture efficacy of stink bugs. We evaluated traps including (1) yellow rocket trap with a solar fan and blue LED lamp, (2) a yellow trap with solar fan but no light, (3) rocket traps with black, green, yellow, white, red, brown, and blue color stimuli, (4) different color combinations of trap wings, and (5) traps with a landing board were evaluated. Our results showed that yellow winged rocket traps with solar fans and blue LED lamps attracted significantly more stink bug species than other traps, in both soybean fields. Use of these improved traps such as a yellow trap with a solar fan and blue LED lamp, and a yellow trap with a solar fan would therefore enhance the monitoring and capture of stink bugs in diversified agro-ecological landscapes. The potential use of traps with a specific hue, combination of features, and modifications to monitor stink bugs accurately is discussed. Continuing improvements to traps to meet the demands of a changing pest landscape and agricultural mechanization are needed.