FIELD: physics.
SUBSTANCE: device has longitudinal units for dividing shells of the nose fairing, made from two parts, between which there is a detonating cord, and units for attaching the nose fairing half to the carrier rocket. The detonating cord is placed along the perimetre of the fairing in a closed volume, which is encircled by an adapter, made from two parts which overlap each other and are joined by fastening elements, fitted diametrically and oppositely in the plane of division of the nose fairing halves. Cavities formed in the closed volume, as well as between the inner surface of the adapter and outer surface of the closed volume are filled with porous material. At places where the adapter is attached to units for dividing the shells of the nose fairing, there are gaps fitted with sock absorbers.
EFFECT: reduced vibroimpact load on the structure of the rocket and spacecraft upon explosion of the detonating cord and increased reliability of the device and easier assembling of the nose fairing.
3 dwg
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