RU2014106469A - METHOD OF CONFIRMING THE INTERNAL BALLISTIC AND ENERGY CHARACTERISTICS OF THE SOLID-FUEL CHARGE OF THE SPECIAL PURPOSED ROCKET ENGINE AND THE STAND DEVICE - Google Patents

Abstract

1. A method for confirming the ballistic and energy characteristics of a solid-propellant charge of a special-purpose rocket engine, which consists in burning a series of charges with different burning speeds in a simulator chamber with a round critical discharge aperture with measuring pressure in a simulator chamber, characterized in that the charge is thermostated before burning to a temperature that ensures the rate of combustion of the charge and pressure in the engine with minimal deviations from their nominal values and determined by the formula:, where t is the temperature of the temperature control of the charge before the fire bench test (AIS); t is the maximum temperature in the range of operation; t is the minimum temperature in the range of operation; is the rate of burning of a charge in a particular batch, determined in a constant pressure device (PPD); u is the maximum rate of charge burning at a maximum temperature in the operating range; u is the minimum rate of burning of a charge at a minimum temperature in the operating range. 2. A bench device for confirming the ballistic and energy characteristics of the solid propellant charge of a special-purpose rocket engine, containing a metal slipway with a horizontal rotary plate for mounting a simulator chamber with a round critical hole, a pressure measuring sensor in the simulator chamber, a power meter between the rotary plate and the slipway the fact that the slipway has a vertical thrust wall to which a bracket with a bearing assembly for verticals is attached swinging plate shaft ceiling elements, fastened siloizmeritelej n

Claims (4)

1. A method for confirming the ballistic and energy characteristics of a solid-propellant charge of a special-purpose rocket engine, which consists in burning a series of charges with different burning speeds in a simulator chamber with a round critical discharge aperture with measuring pressure in a simulator chamber, characterized in that the charge is thermostated before burning to a temperature that ensures the rate of combustion of the charge and pressure in the engine with minimal deviations from their nominal values and determined by formula:

, where t _term is the temperature of temperature control of the charge before the fire bench test (AIS); t _max - maximum temperature in the operating range; t _min - the minimum temperature in the range of operation; $$u_{PPD}^i$$

- the rate of combustion of a charge in a particular batch, determined in a constant pressure device (PPD); u _max - the maximum burning rate of the charge at the maximum temperature in the operating range; u _min - the minimum burning rate of the charge at the minimum temperature in the operating range. 2. A bench device for confirming the ballistic and energy characteristics of the solid propellant charge of a special-purpose rocket engine, containing a metal slipway with a horizontal rotary plate for mounting a simulator chamber with a round round critical hole, a pressure measuring sensor in the simulator chamber, a force meter between the rotary plate and the slipway characterized in that the slipway has a vertical thrust wall to which a bracket is mounted with a bearing assembly for verti of the rotary plate shaft, the load meter is mounted on the vertical contact wall of the slip and is in contact with the side surface of the rotation plate, the rotation plate and the vertical contact wall of the slip are connected in a horizontal plane by a coiled spring for the initial compression of the rotation plate of the slip to the force meter, the rotary plate under the simulator camera has vertical racks (a pair of racks) in contact with the floor of the stand through end bearings, the axes of which are perpendicular to the axis of the load cell, the imitation chamber is enclosed in a heat-insulating casing made, for example, of foam plastic, the simulator chamber has a pipeline with a nozzle whose axis is parallel to the axis of the load cell and whose axes are perpendicular to the vertical contact wall of the slipway, the distance from the axis of the vertical shaft of the turntable to the axis of the load meter "l" and to the axis nozzles of the pipeline "L" are connected by the ratio:

, where F _forces - load meter readings, R _sop - reactive thrust of the nozzle of the camera simulator. 3. The device according to claim 2, characterized in that the axis of the load meter and the nozzle of the pipeline are in a common horizontal plane. 4. The device according to claim 2, characterized in that the simulator chamber is equipped with a thermally insulated tank that simulates the initial free volume of the combustion chamber of a standard engine.