AMERICAN ANTI-MISSLE SHIELD, EASTERN EUROPEAN ASSET TO DISCOURAGE BALLISTIC ATTACKS

Air-missile defense is a mission of anti-aircraft missile troops known in the field as anti-missile shield. It describes an anti-ballistic area intended for research, discovery, interception and combat of surface-to-air or air-to-air missiles with ballistic trajectory. The existence of the anti-missile shield implies the creation of a security zone of allied states, institutional structures and population that can ensure their functionality and existence, deployed on an alignment (territories of several states), in order to maintain a state of normalcy and security. This defense system must include the threatened states, members of the politico-military alliance, regardless of their economic and military power. The security environment also concerns both the population of those countries and the objectives of great political, economic, strategic, critical and military infrastructure importance.

Elements of ballistic calculation for spacecraft gravity assist

The purpose of the study is an analytical description of the section of the ballistic trajectory corresponding to the normal fall of the spacecraft on the surface of an atmosphereless planet. In this case, the motion of a normally falling body is characterized by an increasing acceleration of gravity. The problem of the speed, time and acceleration of the normal fall of a body on the planet's surface in the absence of an atmosphere is reduced to solving a second-order differential equation, which is solved by the standard method. A feature of the solution is the formal use of the tabular integral at an intermediate stage. It turned out, however, that his formula is unreliable, namely, the derivative of the right-hand side is not equal to the integrand. It follows from this that the possible existing solutions to this problem, based on the use of the indicated tabular integral, are incorrect. The article presents the correction of this tabular integral, which is an incidental result of the study. In this work, the time equation of motion of a body normally falling on the surface of the planet in the absence of an atmosphere, as well as the time equations of its speed and acceleration are obtained. The results obtained can be useful in calculating passive gravity assist during interplanetary flights and calculating the sheer fall of small celestial bodies and spent structural element s of spacecraft.

A Simulation of the Effects of Badminton Serve Release Height

In this work, we develop and calibrate a model to represent the trajectory of a badminton shuttlecock and use it to investigate the influence of serve height in view of a new serve rule instated by the Badminton World Federation. The new rule means that all players must launch the shuttlecock below a height of 1.15 m, as opposed to the old rule whereby the required launch height was under the rib cage of the server. The model is based on a forward dynamics model of ballistic trajectory with drag, and it is calibrated with experimental data. The experiments also served to determine the actual influence of the new rule on the shuttlecock launch position. The model is used in a Monte Carlo simulation to determine the statistical influence of the new serve rules on the player’s ability to perform good serves; i.e., serves with little opportunity for the receiver to attack. We conclude that, for the female player in question, serving below a height of 1.15 m makes it marginally more difficult to perform excellent serves. We also conclude that there might be alternative launch positions that would be less likely to produce the best serves but could be exploited as a tactical option.

NOMINAL BALLISTIC MISSILE ASCENT OPTIMIZATION WITH THERMAL INVESTAGATION

Ballistic Missile Trajectory is one of the big issues to simulate and also to be optimized. The main objective of this paper is to find a method to obtain the Nominal trajectory for the ballistic missile through finding out the optimal parameters for each ballistic trajectory phases. To define the problem; the paper will list all governing equations and describe the parameters of input and output for each phase of the trajectory. Then, a method to reduce the number of input parameters will be discussed. We study each parameter effect to get the most optimal trajectory for the missile. At the final, optimal flight will be discussed in details. Although, we investigate the thermal effect for entry point from space into the earth atmosphere

Aerodynamic Dispersion of Respiratory Droplets and Aerosols by Turbulent Airflow

The precautionary measures recommended during the current COVID-19 pandemic do not consider the effect of turbulent airflow. We found the propagation of droplets and aerosols highly affected by this condition. The spread of respiratory droplets by the action of sneezing is characterized by the dynamics of two groups of droplets of different sizes: Larger droplets (300–900 μm) have a ballistic trajectory and can be spread up to 5 m, while a cloud of smaller droplets (100–200 μm) can be transported and dispersed at longer distances up to 18 m by the action of the turbulent airflow. In relation to the spread of exhaled aerosols during respiration, these remain in the air for long periods of time. In the presence of intense or moderate airflow, this set of particles follow airflow streamlines, and thus their propagation is directly determined by the air velocity field. Given the scientific evidence, these results should be considered in public debate about the aerodynamic dispersion characteristics of scenarios where social interactions occur and about the measures to mitigate the spread of the virus.

The position of liquid fuel residues in tank of worked-off rocket stage during ballistic descent

The results of modeling the behavior of liquid residues of the rocket fuel component in the fuel tank of the worked-off rocket stage on a ballistic trajectory are presented. The simulation is carried out for the following variants: during the controlled descent of the rocket stage and when using the technology of evaporation of liquid rocket fuel residues in the tanks of the spent stage. It is established that during the controlled descent of the spent rocket stage along the ballistic trajectory at the site of its turn and up to heights of 20 km, the liquid under the influence of overloads is distributed in the form of a film in the area of the bottom and side surface with a coverage area of up to 35 %. At the height of the maximum value of the axial overload, liquid fuel residues in the form of a film move to the area of the bottom and the adjacent side surface of the fuel tank. The total coverage area is about 22 %. The introduction of a hot coolant into the fuel tanks to vaporize the liquid remnants of rocket fuel radically changes the picture of the behavior of the liquid. Due to the high speed of the coolant in the tank, axial overload has little effect on the distribution of fuel residues in the rocket tank

Shooting Simulator «Inhibitor»: Mathematical Support for Ballistics of 7.62 Caliber Weapons

The software for support of external ballistics calculation for weapons of 7.62 mm caliber is described taking into account external factors for the optical-electronic tactical exercise machine for small arms "Inhibitor" developed at the Institute of Mechanics UdmFRC UB RAS and at Computer facilities department of Kalashnikov ISTU jointly with JSC «Kalashnikov» Concern». A tactical and technical task is given for ballistic calculation of the trajectory up to 2 km of range of weapon simulators with a laser emitter of the targeting point taking into account external factors: types of sights, especially optical, ballistic scattering of bullets, deflection of the bullet from the side wind and derivation, which have a significant impact on the ballistic trajectory. The implemented differential mathematical model of external ballistics relying on the aiming angle of the weapon simulator depending on the sight readings, the initial speed and ballistic coefficient of various types of ammunition in real time builds a ballistic trajectory with adjustments for the air temperature and pressure and dependence on lateral wind and random dispersion of bullets to further solve the "problem of meeting" with obstacles. The given results of software tests for the error in calculating the coordinates of the ballistic trajectory showed full compliance with the requirements and adequacy of mathematical models. It was concluded that further research and development of electronic shooting simulators were promising thanks to the improvement of computing tools and the development of software libraries in order to increase the accuracy of simulating external ballistics of simulators taking into account many external factors, expand functional networks and reduce cost and, therefore, increase competitiveness.

Shooting Simulator «Inhibitor»: Mathematical Support for Subsonic Weapon Ballistics

The mathematical support for calculation of external ballistics for subsonic weapons is described taking into account external factors for the tactical optical-electronic simulator for small arms "Inhibitor" developed at the Institute of mechanics UdmFRC UB RAS and at Computer facilities department of Kalashnikov ISTU jointly with JSC «Kalashnikov» Concern». The tactical and technical assignment is given for ballistic calculation of the trajectory and point of hit of subsonic simulators of PM weapon and GP-25 with the laser emitter of the targeting point taking into account external factors: position of the sighting bar of all types of sights (mechanical, optical, night) with the procedure of their preliminary sighting (transformation of coordinates of the laser spot into coordinates of the visual targeting point), features of the mounted trajectories of the GP-25 (air pressure drop with the height of the trajectory), air temperature and pressure, wind force, ballistic scattering minus the hardware error of the sighting point recorder (geometric subtraction of independent random errors). Mathematical models of external ballistics implemented in the software relying on the aiming angle of the weapon simulator, the initial speed and ballistic coefficient of various types of ammunition in real time in the simulator coordinate system make up a ballistic trajectory in order to solve the “meeting problem”. Results of software tests for the error in the calculation of ballistic trajectory characteristics are given. It was concluded that further research and development of electronic shooting simulators were promising thanks to the improvement of computing tools and the development of software libraries in order to increase the accuracy of simulating external ballistics of simulators taking into account many external factors, expand functional networks and reduce cost and, therefore, increase competitiveness.