Experimental equipment and method for measuring multi-angle burning rate of propellant in overload condition

Abstract

The invention discloses experimental equipment and a method for measuring multi-angle burning rate of a propellant in an overload condition, and belongs to the field of propellant testing. The experimental equipment comprises a combustor, an electric coupler, a signal collector, an intake and exhaust device, a tray device and a rotary testbed. The combustor is used for providing an experimental environment for burning of the propellant, the combustor comprises a propellant strip, a guiding wire, a heating wire and target lines. The tray device is used for bearing the combustor, and comprises atray, a fixing nut, a mandrel and a connecting rod. The intake and exhaust device comprises an adapter with at least three connectors, a pressure sensor, an air inlet valve, a filter and an exhaust valve. The rotary testbed is used for bearing the tray device and the combustor, and provides an overload environment. The invention further discloses the test method based on the experimental equipment. According to the experimental equipment and the method for measuring the multi-angle burning rate of the propellant in the overload condition, a target line method is adopted to measure the burningrate of the propellant, burning speed and pressure measurements of the propellant can be achieved in multiple angles under the overload condition, and the experimental equipment and method have the advantages that the structure is simple, and achieving is convenient.

Description

technical field [0001] The invention relates to an experimental device and method for measuring the multi-angle burning rate of propellant under overload conditions and the burning direction can be adjusted, in particular to an experimental device and method that uses the target line method to measure the burning rate of solid propellant and can cooperate with a rotating test bench to simulate overload The invention relates to a combustion experimental device capable of adjusting the combustion direction of propellant within the range of 0°-90°, and belongs to the field of propellant testing. Background technique [0002] In solid rocket motors, changes in environmental factors such as pressure, initial temperature, and airflow velocity will lead to changes in the burning rate of solid propellants, which in turn will affect the ballistic performance, flight speed, and working stability of the rocket motor. Therefore, the burning rate of propellant is one of the important pro...

AI Technical Summary

Problems solved by technology

In addition, the direction of the overload force on the rocket engine may change during the working process, resulting in a change in the angle between the propellant burning direction and the overload force direction, and this change in the angle will also have a certain impact on combustion

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