AIRCRAFT ELEMENT SEPARATION SYSTEM Russian patent published in 2022 - IPC B64G1/64 F42B15/36 

FIELD: aviation; rocket engineering.

SUBSTANCE: invention relates to systems for separating structural elements, mainly of rocket stages, and can be used in aircraft and rocket engineering. Aircraft elements separation system includes power flanges of coupled elements, a rod, retaining inserts installed in the sleeve and a housing with a pyro cartridge installed in it. At that, the internal cavity of the housing is made in the form of a two-stage cylinder with a transition cylinder rigidly fixed in one of the stages and installed with possibility of movement along longitudinal axis of housing by sleeve presented in form of hollow rod, one end of which is made in the form of a piston with a cover, enclosing the transition cylinder and enclosed by the housing, and the other end is made in the form of a piston enveloped by the transition cylinder and the housing, with the transition cylinder thrust through the spring into the enveloped sleeve piston. Cavity between transition cylinder and enveloping it sleeve piston is interconnected with pyrocartridge, note here that sleeve piston stroke in transition cylinder is smaller than that in case two-stage cylinder, and gas cavities between the sleeve pistons communicate through the throttle holes made in the transition cylinder. Rod enveloped by the sleeve is made in the form of a tightening bolt resting on the body through the conical bushing. In the body of the tightening bolt there is an annular groove with a conical side wall located on the side opposite to the direction of bolt tightening. Thrust part of the head of the tightening bolt is made in the form of separate retaining inserts partially immersed into the groove of the body of the tightening bolt, having the shape of the submerged part, which is identical to the shape of the groove of the body of the tightening bolt. At the same time surfaces of interaction of retaining inserts with the sleeve are made conical along the entire length of the sleeve stroke, with a taper angle not exceeding the friction angle. Also, the tail part of the tightening bolt body is equipped with a crimping locking gate made in the form of a stepped cylindrical bushing, with the possibility of resting at the end of its movement against the protrusion made in the sleeve, and further squeezing by the retaining inserts, during the return movement of the sleeve.

EFFECT: proposed invention — aircraft elements separation system performs function of separation pusher, which allows improving reliability of aircraft and reducing its weight, and availability of pyro-gas damping of movable elements of the system reduces characteristics of vibration impact.

1 cl, 3 dwg