RU2012129626A - METHOD FOR DOWN THE SEPARATE PART OF THE STAGE OF THE SPACE MISSILE ROCKET AND DEVICE FOR ITS IMPLEMENTATION - Google Patents

Abstract

1. The method of launching the separating part of the stage of a space rocket, based on the orientation, stabilization and controlled movement of the separating part due to the energy contained in the undeveloped residues of the components of the liquid fuel in the tanks of the separating part based on their gasification and supply to the gas rocket propulsion launch vehicle, this control the movement of the center of mass and around the center of mass of the separating part is carried out by the deviations of the rotary chambers of a gas jet propulsion system using of a velocity pulse, characterized in that after the application of the velocity pulse, the design of the separating part is carried out at the junction of the propulsion system with the remaining compartments of the separating part using a directional explosion. 2. The method according to claim 1, characterized in that the velocity impulse applied to the center of mass of the separating part of the stage of the space rocket is calculated from the condition that the compartment of the propulsion system is lowered to a given aiming point on the Earth’s surface, according to the formula:, where µ is the Earth’s gravitational constant, r, r-, respectively, the radii of the apogee and perigee of the descent orbit of the marching propulsion system of the separating part. 3. The detachable part of the stage of a space rocket on the liquid components of rocket fuel, which includes a fuel compartment, a power compartment, on the upper bottom of which there are mounted rotary chambers of a gas rocket engine, and a marching propulsion system installed on the lower bottom, characterized in that on the lower bottom of the power compartment placed elongated cumulus

Claims (3)

1. The method of launching the separating part of the stage of a space rocket, based on the orientation, stabilization and controlled movement of the separating part due to the energy contained in the undeveloped residues of the components of the liquid fuel in the tanks of the separating part based on their gasification and supply to the gas rocket propulsion launch vehicle, this control the movement of the center of mass and around the center of mass of the separating part is carried out by the deviations of the rotary chambers of a gas jet propulsion system using of the velocity pulse, characterized in that after applying the speed pulse, the design of the separating part is carried out at the junction of the propulsion system with the remaining compartments of the separating part using a directed explosion. 2. The method according to claim 1, characterized in that the velocity impulse applied to the center of mass of the separating part of the stage of the space rocket is calculated from the condition that the compartment of the propulsion system is lowered to a predetermined aiming point on the surface of the Earth, according to the formula: $$\Delta V=\sqrt{\frac{\mu }{r_{\alpha }}}\left(\mathrm{one}-\sqrt{\frac{2r_{\pi }}{r_{\alpha }+r_{\pi }}}\right)$$

where µ - Earth's gravitational constant $$\mathrm{3,986}\cdot {10}^5\frac{\mathrm{to}{m}^3}{{\mathrm{from}}^2}$$

, r _α , r _π - respectively, the radii of apogee and perigee of the orbit of the descent of the marching propulsion system of the separating part. 3. The detachable part of the stage of a space rocket on the liquid components of rocket fuel, including a fuel compartment, a power compartment, on the upper bottom of which there are mounted rotary chambers of a gas rocket engine, and on the lower bottom there is a marching propulsion system, characterized in that on the lower the bottom of the power compartment has an elongated cumulative charge connected by electrical communication through a switching device to a power source.