METHOD OF SEPARATING AIRCRAFT ELEMENTS Russian patent published in 2022 - IPC B64G1/64 F42B15/36 

FIELD: aviation; rocket engineering.

SUBSTANCE: invention relates to methods of separating structural elements, mainly rocket stages, and can be used in aircraft and rocket engineering. Method of separating elements of aircraft involves making power flanges of mating elements, rod installed in sleeve of retaining inserts, and housing, in which pyrocartridge is installed. At that, the inner cavity of the housing is made in the form of a two-stage cylinder, on one of the stages of which a transition cylinder is rigidly fixed, in which a sleeve is installed with the possibility of movement along the longitudinal axis of the housing, which is a 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 a transition cylinder and a housing. Adapter cylinder thrust against the sleeve piston enveloped by it is provided through a spring, and the cavity between the transition cylinder and the sleeve piston enveloping it is interconnected with the pyrocartridge. At that, the sleeve piston stroke along the transition cylinder has a smaller value than the sleeve piston stroke along the two-stage cylinder of the housing, gas cavities between sleeve pistons communicate via throttling holes made in adapter cylinder. Rod enveloped by the sleeve is made in the form of a tightening bolt with a thrust on the body through a 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, which are partially immersed into the groove of the body of the tightening bolt. Retaining inserts are shaped to the submerged part 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, which is made in the form of a stepped cylindrical bushing, with provision of support at the end of its movement against the protrusion, which is made in the sleeve, and further squeezing by retaining inserts during return movement of the sleeve.

EFFECT: proposed invention — aircraft elements separation method — provides separation pusher functions, which allows improving reliability of aircraft and reducing its weight, and availability of pyro-gas damping of moving elements reduces characteristics of vibration impact.

1 cl, 3 dwg