Abstract: An important problem in studying the sloped rocket launch is to determine the oscillations and their effects on the initial conditions of the rocket path. This phenomenon influences the stability of the launching device and the firing precision. We suppose that the launching device and the moving rocket form a complex oscillating system that join together a sum of rigid bodies bound by elastic elements (the vehicle chassis, the tilting platform and the rockets in the containers). The article presents a general mathematical model that consists of a nonlinear differential equations system with variable coefficients. The system allows calculating the oscillations of the launching device during firing, evaluating the dynamic stability and also computing more accurately the rocket movement elements during launch
Abstract: Taking into consideration that during the firing, the rocket-launching device system oscillates and these oscillations may have a negative influence on the unguided rocket firing precision, it is necessary to evaluate the parameter oscillation in order to set up a precise rocket-launching device. This study intends to calculate the oscillations of a rocket-launching device system during firing, by means of numerical calculations on a nonlinear differential equation system [1]. In order to evaluate the rocket-launching device system oscillations a scheduling algorithm consisting in numerical integrating a differential equation system defining the movement of the system during launch is used
Abstract: The problem developed in this contribution is encountered in airplane aerodynamics and concerns the influence of long life longitudinal wake vortices generated by wing tips or by external obstacles such as reactors or landing gears. More generally it concerns 3D bodies of finite extension in cross flow. At the edge of such obstacles, longitudinal vortices are created by pressure differences inside the boundary layers and rotate in opposite senses. The behavior of these vortices has been studied in great detail by many authors as reported in [1]. Nevertheless the numerical simulation used for understanding the mechanisms were generally time evolution computation on a fixed space box with periodic boundary conditions using a transformation of the time evolution into a downstream evolution. The flow will be perturbed by prescribed disturbances or by a turbulent field. The main purpose of this work is to understand how we can use a real spatial simulation on a fixed domain in order to solve the problem of interaction between downstream flow and evolving vortices.
Abstract: The main task of such calculus devices is to make the gun commander activities more efficient, by performing in short time all the computation needed to open fire on the
observed (indicated) targets. In the paper, their are presented the main calculus functions and the main working features such devices should have. Finally, there are presented a
series of practical achievements in the area, belonging to the authors of this scientific paper.
Abstract: The modern integrated avionics and armament systems include a great variety of sensors, which provide the data requested for solving the air-air sighting problem. The
usually precision of air-air shooting is diminished from many hypotheses who is used in the modelling of shooting phenomena, from the movement of manoeuvrable target and from the errors generated by aircraftâs sensors. This study assays to mark out the principals sources of the trajectoryâs dispersal and suggests one method to approximate the influence of sensorâs precision in the global accurate of air-air shooting.
Abstract: In present, the conditions of the aerial combat is very difficult. The flight parameters of combat aircraft, shooter or target, reduced the possibilities of aerial shooting. This paper
presents the dynamics restrictions in the aerial combat and the possible attack area.
Abstract: The possibility of solving, with accepted accuracy, of the sighting problem in air-to-air combat using the unguided artillery weapons was a higher concern for the specialists. This problem becomes more acute when aircraftâs equipments canât provide all the necessary information for solving the sighting problem. In this case some acceptable solutions were found. This study suggests one of these solving methods, using deficient information about the firing context, this deficiency being recouped by a suiting attack procedure
Abstract: This paper treats some modalities of real time solving with sufficient exactly of the main problems which appear during preparation and execution of shooting with artillery weapons. There is presented a series of significant realizations worldwide, but also some preoccupations of Military Technical Academy specialists in this domain.
Abstract: This paper presents a determination methodology of the main factors that contribute to the viewing stability and accuracy for aircraft ordnance systems shooting. Among them, are
spacecraft bus, attitude controller, reaction wheel assembly, movement tracker unit, inertial reference unit, and gyro drift estimators. The predicted aircraft performance is analyzed for a variety of inputs are the desired attitude angles and rate set points. The stochastics inputs include random torque disturbance acting on the aircraft, random gyro bias noise, gyro
random walk, and movement tracker noise. These inputs are varied over a wide range to determine their effects on pointing accuracy and stability.
Abstract: It is presented a real time numerical calculus methodology for OTF, including FTF for image motion and vibration. We have analysed this method in case of linear, sinusoidal and
accelerated movement and consider this approach relevant for any kind of movement. Comparring to the classical methods used to establish the optical and electrono-optical
systems accuracy, this methodology uses the theoretical and experimental basis of OTF. This is an analyse manner of the image resolution, both calitative and quantitative.
