FIELD: rocketry.
SUBSTANCE: invention refers to the field of armaments and can be used in missile technology. Missile fired from the launch tube is proposed, which contains the stabilizing device that is installed on the rear part of the body in the form of the hull with the fin blades, each of which consists of the spring plate and of the rigid base with the tooth, which is fixed onto the inner surface of the body by the plate spring lock. Stopper is made in the form of separate, sequentially located latches, which are fixed to the tooth by the pins, each of which is provided with the threaded pin and nut at one end and with the cap on the other, the outer surface of the body is provided with the height-adjustable projections that are located under the blades in their folded position, the blade plates in the cross section are designed with the wedge thinning towards the end chord, which is made with the thickening, the front and back edges of the bases are being made with the two-sided lowering equidistant to their lateral surfaces, on which the composite material with low thermal conductivity is pressed, and the blade plates along the leading edges are covered with the layer of refractory metal. Glass fiber with a binder based on epoxy resins is used as the composite material. Chromium is used as the refractory metal.
EFFECT: ensuring the efficiency of the missile, when flying in dense layers of the atmosphere at ultra-high flight speeds and high power loads, as well as reducing the passive mass of the missile.
3 cl, 5 dwg
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Authors
Dates
2018-04-23—Published
2017-01-17—Filed