RU2012153020A - METHOD FOR GASIFICATION OF LIQUID ROCKET FUEL IN A ROCKET TANK AND A DEVICE FOR ITS IMPLEMENTATION - Google Patents

Abstract

1. A method of removing a separating portion of a carrier rocket from a payload orbit, based on the receipt of an impulse by ejecting gasified liquid residues of undeveloped rocket fuel components in the oxidizer and fuel tanks, providing an impulse due to their combustion in the chamber of a gas rocket engine and high-speed outflow of combustion products into space space, characterized in that in the lower part of the fuel tank limit the volume, including the mass of undeveloped residual components of the rocket then livas (CMT) in the vicinity of the intake device by installing a separation grid, the second mass flow rate of the coolant (VT) supplied to the fuel tank is divided into 2 parts, one part of the VT is fed into the volume limited by the grid, providing a vortex flow pattern from the condition of creating maximum heat transfer and the maximum residence time of the VT in this volume, and the second part of the VT is fed into the second part of the fuel tank with the counter flows of the mixture coming from the volume limited by the separation grid, the amount of aemogo VT at the top of the fuel tank is determined from the condition of the evaporation of any remaining drops of MCT at time output from the fuel gasified product baka.2. The method according to claim 1, characterized in that the VTs in the selected areas are fed through the mains, at the end of which acoustic emitters are installed, the number and coordinates of the VT input points, the input direction, the parameters of the acoustic emitters are determined from the condition of minimum mass costs for the gasification of a given amount fuel at a given gas pressure

Claims (3)

1. A method of removing a separating portion of a carrier rocket from a payload orbit, based on the receipt of an impulse by ejecting gasified liquid residues of undeveloped rocket fuel components in the oxidizer and fuel tanks, providing an impulse due to their combustion in the chamber of a gas rocket engine and high-speed outflow of combustion products into space space, characterized in that in the lower part of the fuel tank limit the volume, including the mass of undeveloped residual components of the rocket then livas (CMT) in the vicinity of the intake device by installing a separation grid, the second mass flow rate of the coolant (VT) supplied to the fuel tank is divided into 2 parts, one part of the VT is fed into the volume limited by the grid, providing a vortex flow pattern from the condition of creating maximum heat transfer and the maximum residence time of the VT in this volume, and the second part of the VT is fed into the second part of the fuel tank with the counter flows of the mixture coming from the volume limited by the separation grid, the amount of aemogo VT at the top of the fuel tank is determined from the condition of the evaporation of any remaining drops CMT time to time the gasified product of the fuel tank. 2. The method according to claim 1, characterized in that the VTs to the selected areas are fed through the mains, at the end of which acoustic emitters are installed, the number and coordinates of the VT input points, the input direction, the parameters of the acoustic emitters are determined from the condition of minimum mass costs for gasification a given amount of fuel at a given pressure of gasified products in the tank during the entire gasification process and, upon reaching the specified pressure in the fuel tank, open the valve on the gas supply line s products, for example in a gas thruster. 3. A device for implementing the method, comprising oxidizer and fuel tanks, a tank pressurization system, a gas rocket engine with a power system and a gasification system for residual SRT, characterized in that in addition to the lower part of the fuel tank there is a separation grid with a cell size equal to : $$r=\frac{\sigma \cdot 2\pi \cdot \cos \Theta }{ph\alpha }$$

, where r is the radius of the capillary hole in the grid, σ is the force of the surface tension of the fluid, угол is the angle of wetting of the fluid, ρ is the density of the fluid, h is the height of the fluid column above the grid, α is the acceleration of the fluid when moving toward the grid, F _α is the force with which the fluid acts on the mesh element, F _H is the surface tension force, the volume bounded by the grid V _c is equal to: $$V_{\mathrm{from}}=3V_{ocm}^{\min }+6\sigma$$

, $$V_{ocm}^{\min }$$

the smallest possible volume of undeveloped residues of SRT σ is the standard deviation from the nominal value of the SRT residues.