US 2025/0059935 A1 · LABORATORY STAND FOR STUDYING THE EFFECT OF ACCELERATION ON THE LINEAR BURNING RATE OF SOLID ROCKET PROPELLANTS

Abstract

The subject of the invention is a laboratory stand for studying the effect of accelerations on the linear burning rate of solid rocket propellants. The laboratory stand for studying the effect of accelerations on the linear burning rate of solid rocket propellants according to the invention comprises a DC electric motor with an encoder, an energy storage module, an igniter power supply system, an electronic pressure measuring system in a combustion chamber and a rocket micromotor. The electric motor is connected to an encoder, at the same time the electric motor is connected to the main shaft by a bellows-free coupling, and an energy storage module is placed on the main shaft. On the opposite side of the rocket micromotor body located on the main shaft by a fastener there is the igniter power supply system mounted on the main shaft containing a power supply system sleeve on which conductive rings and insulating rings are placed, terminated with a closing ring and carbon brushes. The electronic pressure measuring system in the combustion chamber includes a pressure sensor located in a pressure sensor socket connected to the rocket micromotor body by means of a pressure measurement port. And, furthermore, on the threaded end of the main shaft is located a rocket micromotor body mount containing the combustion chamber with an internal collector groove and a pressure measurement port, and a safety valve port with a safety valve together with an outlet socket on the side of the rocket micromotor body.

Claims15

Dependent claims

A laboratory stand for studying the effect of accelerations on the linear burning rate of solid rocket propellants comprising a DC electric motor (1) with an encoder (2), an energy storage module (8), an igniter power supply system (B), an electronic pressure measuring system (44) in a combustion chamber (22) and a solid rocket micromotor (A), characterized in that:

the electric motor (1) is connected to the encoder (2), at the same time the electric motor is connected to a main shaft (5) by a bellows coupling (4), and an energy storage module (8) is placed on the main shaft (5),
on the opposite side of the solid rocket micromotor (A) body (21) located on the main shaft (5) by a fastener (20) there is an igniter power supply system (B) mounted on the main shaft (5) comprising a power supply system sleeve (9) on which conductive rings (10) and insulating rings (11) are placed, terminated with a closing ring (12) and carbon brushes (16),
the electronic pressure measuring system (44) in the combustion chamber includes a pressure sensor (36) located in a pressure sensor (36) socket (35) connected to the solid rocket micromotor (A) body (21) by means of a pressure measurement port (33),
and, in addition, on the threaded end of the main shaft (5) there is a solid rocket micromotor (A) body (21) mount (20) containing the combustion chamber (22) with an internal collector groove (30) and the pressure measurement port (33) and a safety valve port (24) with a safety valve (26) together with an outlet socket (27) on the side of the solid rocket micromotor (A) body (21).

1 more element

Dependencies are inferred from the claim text.

Laboratory stand for studying the effect of acceleration on the linear burning rate of solid rocket propellants

Life of this patent

Laboratory stand for studying the effect of acceleration on the linear burning rate of solid rocket propellants

Life of this patent

Abstract

Claims15