FIELD: rocketry. SUBSTANCE: installed in the installation combustion chamber are a specimen of solid propellant, asbestos filler and a transceiving transducer of microwave radiation with a cone and radiator joined to it. Attached to the radiator outlet is a support with a specimen of solid propellant armored with liquid-viscous noncombustible material on the side of the support. The specimen is made in the form of a parallelepiped with movable and fixed holders attached on the two sides. The fixed holder is attached on the support. The movable holder is coupled to the deforming piston through a rod. Specimen tension in the installation occurs at actuation of the primer, when pressure rises in the installation that acts on the deforming piston. EFFECT: provided determination of the law of solid propellant burning rate within a wide range of pressures according to the results of combustion of one specimen. 1 dwg
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