RU2013101694A - METHOD FOR SIMULATING ROCKET LAUNCH CONDITIONS FROM LAUNCHING SUBMARINE UNDER GROUND CONDITIONS AND SYSTEM FOR ITS IMPLEMENTATION - Google Patents

Abstract

1. A method of simulating the conditions for launching a rocket from a submarine launcher in ground conditions, including starting a gas generator, creating pressure on the bottom of the rocket model and the obturation belt, ejecting the rocket model from the launch pipe, creating a force applied to the rocket model before launch, in the direction opposite to its movement, and simulating the effect of hydrostatic water pressure on the rocket at the start depth, the longitudinal resistance force and the friction force, characterized in that they are created using pneumatic piston system force simulating the effect of hydrostatic water pressure on the rocket, increasing the gas pressure in the pneumatic cylinders to a value determined by the formula: where S [m] is the total cross-sectional area of the pneumatic cylinders, S [m] is the cross-sectional area of the internal cavity of the launcher, ρ = 1020 [kg / m] is the density of sea water, g = 9.81 [m / s] is the acceleration of gravity, H [m] is the immersion depth, counted from the upper section of the launcher, and after the start of the gas generator, the start of the rocket’s prototype movement and extrusion through holes The throttle aperture of gases from pneumatic cylinders measures the current values of displacement x (t), speeds of acceleration of the rocket, pressure Rtsil (t) and gas temperature T (t) in the working cavities of the pneumatic cylinders, as well as the throttle opening area Sdr (t), determine the value of the required gas pressure in the working cavities of the pneumatic cylinders according to the formula: where S [m] is the total area of the pistons in the working cavities of the pneumatic cylinders, S [m] is the cross-sectional area of the internal cavity of the launcher, Cx (x (t)) is the calculated value of the longitudinal hydrodynamic coefficient c

Claims (3)

1. A method of simulating the conditions for launching a rocket from a submarine launcher in ground conditions, including starting a gas generator, creating pressure on the bottom of the rocket model and the obturation belt, ejecting the rocket model from the launch pipe, creating a force applied to the rocket model before launch, in the direction opposite to its movement, and simulating the effect on the rocket of hydrostatic pressure of water at the start depth, the force of longitudinal resistance and the friction force, characterized in that they create using pneumatic piston system force, simulating the effect on a rocket of hydrostatic pressure of water, increasing the gas pressure in the pneumatic cylinders to a value determined by the formula:

where S _cyl [m ² ] is the total cross-sectional area of the pneumatic cylinders, S _PU [m ² ] is the cross-sectional area of the internal cavity of the launcher, ρ = 1020 [kg / m ³ ] is the density of sea water, g = 9.81 [m / s ² ] - gravity acceleration, H ₀ [m] - immersion depth, measured from the upper section of the launcher, and after the start of the gas generator, the beginning of the movement of the rocket model and the displacement through the opening of the gas throttle from the pneumatic cylinders, the current values of displacement x (t), speed $$\dot{x}(t)$$

and acceleration $$\ddot{x}(t)$$

the layout of the rocket, the pressure Rtsil (t) and the gas temperature T (t) in the working cavities of the pneumatic cylinders, as well as the area of the orifice hole Sdr (t), determine the value of the required gas pressure in the working cavities of the pneumatic cylinders $$P_{c\mathrm{and}l}^{tReb}(t)$$

according to the formula:

where S _cyl [m ² ] is the total area of the pistons in the working cavities of the pneumatic cylinders, S _PU [m ² ] is the cross-sectional area of the internal cavity of the launcher, Cx (x (t)) is the calculated value of the longitudinal hydrodynamic drag coefficient of the rocket, depending on the measured displacement x (t), λ ₁₁ [kg] - the attached mass of the rocket in the direction of its longitudinal axis, F _Tr [N] - the friction force of the supports and the seal obturator rocket in contact with the inner walls of the launcher, compare the value of the measured pressure P _cyl (t) with the desired $$S_{c\mathrm{and}l}^{tReb}(t)$$

, change the size of the area of the orifice hole S _dr (t) to bring the pressure P _cyl (t) to the desired value $$P_{c\mathrm{and}l}^{tReb}(t)$$

. 2. A system for simulating the conditions of an underwater launch of a rocket from a launcher in ground conditions, comprising a launch tube mounted on ground power supports with a missile prototype with an obturating belt inside it, a gas generator in communication with the missile volume, a transition compartment fastened to the bow of the missile prototype, and having nodes for transmitting simulating forces to the missile model, as well as rolling bearings for moving the missile model along the guides along the axis of the launch tube, characterized in that on ground power supports Two power cylinders of the pneumatic piston system are installed, the axes of which are parallel to the longitudinal axis of the launcher, each power pneumatic cylinder is equipped with a piston and a rod, the piston working cavities of the power pneumatic cylinders are connected to each other by a manifold that is equipped with inlet and outlet pipelines, the inlet pipe is connected to a high cylinder pressure to charge the pneumatic piston system, and the outlet pipe is equipped with a throttle with an adjustable gas outlet from the working cavities of the pneumatic cylinders and equipped with a device for changing the cross-sectional area of the throttle using a controlled drive, the pneumatic cylinders are equipped with measuring pressure and gas temperature inside the working volumes of the pneumatic cylinders and a system for measuring the throttle aperture, and the missile model is equipped with sensors for displacement, speed and acceleration of the rocket model connected to control equipment. 3. The device according to p. 2, characterized in that the length of each power cylinder is greater than the length of the launch tube.