METHOD OF WITHDRAWING ACCELERATING ROCKET MODULE FROM SPACESHIP FLIGHT PATH Russian patent published in 2013 - IPC B64G1/64 

FIELD: transport.

SUBSTANCE: invention relates to control over separation of spacecraft and accelerating module. After separation, thrust pulse acts on accelerating module in plane crossing the module center of gravity, but crossing spacecraft outlines in jointed state, to make acute angle with accelerating module lengthwise axis. Pulse is applied with eccentricity relative to accelerating module center of gravity varying in the range of 0<δ≤R, where R is radius of accelerating module central cross-section. Thrust pulse make obtuse angle with straight line crossing pulse action direction and parallel about accelerating module lengthwise axis. Thrust pulse acting on accelerating module makes it change into precession-nutation motion whereat its accelerating module describes conical surface around direction of separation of spacecraft and accelerating module. This decreased power requirements to separation means and effects of accelerating module mid-flight engine aftereffects. Notably decreased are disturbances of spacecraft angular motion after separation. Higher safety of separation and efficiency of separated accelerating module braking in upper atmosphere. Spacecraft effective load is notable increased.

EFFECT: impact-free separation and guaranteed withdrawal in preset direction.

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