This paper analyses a rocket assisted torpedo's aerial motion, water entry motion and underwater motion It establishes equations of motion for each phase and presents the ballistic characteristics of each section It thus provides a basis for the design and calculation of rocket assisted torpedoes
Used in the visualization of exhaust plumes of a rocket engine, multiple-frame interferograms of the shock wave development processes and of the near field structure can be obtained. It provides powerful experimental means for studying the fundamental characteristics of the whole flow field.
According to the "solid particle" theory model, a theory model of the dynamic burining velocity of a rocket portfire in its igniting delay time cannulation is established, a theory model of the dynamic delay time is educed. The factors are analyzed, setting position and shape of a igniting delay time cannulation that affect its igniting delay time.
Microbiological Degradation of Asymmetric Dimethylhydrazine, a Toxic Rocket Fuel Ingredient
The possibility of microbiological cleaning of water and soil polluted with asymmetric dimethylhydrazine (ADMH), a highly toxic ingredient of rocket fuel (IRF), was studied.
Consideration was given to the controlled solid bodies such as aircraft, rocket, and so on moving in the aerodynamic medium.
Peculiarities of Estimating the Aircraft Performance Characteristics of the Rocket-and-Space Facilities under Conditions of Fuzz
The method is based on the results of measurements of the state parameters and geophysical conditions of the employment of the rocket-and-space facilities under conditions of uncertainty of the a priori data on measurement errors.
Ions with a Mass Number of Two in Mass-Spectrometric Experiments aboard Rockets and Satellites
Results of the calculation of the structure of relaxation shock waves in gas suspensions of the solid fuel of rockets are given in .
The mass-energy and specific characteristics of the propulsive jet discharges of rockets were factorized.
Variations in the electron density in the midlatitude ionospheric D region during launches and flights of different-type rockets at various distances from the launching site have been experimentally studied using partial reflections.
Coning motion stability of wrap around fin rockets
Equations of motion of ball lightning in a rocket airstream
Phenomena accompanying the injection of a dense plasma beam from the payload of a rocket into ionospheric plasma are analyzed.
It has been indicated that a change in the total electron content is caused by the propagation of an acoustic gravity wave pulse, generated during a rocket flight along the horizontal trajectory leg, in the ionosphere.
The proposed model was successfully used to analyze two emergency events: a failure of a steam turbine's cast diaphragm and a failure of a rocket engine's oxygen pump booster stage.
Regenerative cooling is an advanced method which can ensure not only the proper running but also higher performance of a rocket engine.
In this paper, the random process theory is used to study the problem of the dispersion of rockets effected by the random wind in the exterior ballistics. When the mathematical model of the dispersion was obtained, we analysed some basic laws of the dispersion, represented the physical nature of these laws according to the spectral structure of the wind field and proved that the gust intensity σ_w and the scale of turbulence L are two important physical parameters upon which the dispersion depends.
The mechanism of sub-supersonic nonliner rotational speed of inclined cutwing-body-turbine complex is analysed on the basis of profile theory. A morepractical and reliable calculating method of its rotational speed is given, thosevalues are also compared with those from experiments. This discusion may beused as reference for the design, exterior ballistics calculation and wind tunnel rotational experiment of rocket projectile.
This paper studies the factors influencing zero-wind deviation from. the tra-jectories of Rocket-Assisted Anti-Tank Projectiles. How to determine the variousparameters is invistigated and some cantions problems are also provided. Thisdiscussion gives a better set of calculating formulas for the said anti-tank projectiles.