Rocket Propellant Burning-Rate Stand for Centrifugal Acceleration
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Solution Overview
Problem
Existing technologies lack a detailed design for a laboratory stand to study the effect of accelerations on the linear burning rate of solid rocket propellants, particularly under centrifugal forces.
Innovation Solution
A laboratory stand equipped with a DC electric motor, encoder, energy storage module, igniter power supply system, and electronic pressure measuring system, allowing for experimental tests to determine the effect of accelerations on the linear burning rate and pressure in a combustion chamber.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If a laboratory stand is designed to study the effect of accelerations on linear burning rate, then measurement precision of burning rate and pressure under centrifugal acceleration is improved, but device complexity increases due to multiple integrated systems
Solution Approach 1:
The test stand is divided into independent functional modules: a rotation mechanism module (DC motor with encoder) to generate centrifugal acceleration, a combustion chamber module with pressure sensor for pressure measurement, and a measurement system module for data acquisition. Each module can be independently designed, tested, and maintained, reducing overall system complexity while maintaining measurement precision.
Solution Approach 2:
An encoder is introduced as an intermediary device between the DC motor and the measurement system to accurately measure rotational speed and calculate centrifugal acceleration. The encoder provides precise feedback without requiring direct measurement of acceleration, simplifying the measurement process while improving accuracy.
2Measurement precision
If a DC electric motor with encoder is used to generate centrifugal acceleration, then control precision of acceleration is improved, but device complexity and energy consumption increase
Solution Approach 1:
The encoder provides real-time feedback on the rotational speed of the DC motor, allowing the control system to precisely regulate the centrifugal acceleration. This feedback mechanism enables accurate control of the acceleration applied to the solid propellant sample while maintaining a relatively simple mechanical structure.
Solution Approach 2:
The use of a DC electric motor with encoder replaces more complex mechanical acceleration generation systems. The electrical control system with feedback control is simpler and more precise than mechanical cam-driven or linkage-based acceleration mechanisms, reducing overall device complexity while improving control precision.
3Measurement precision
If pressure sensor and encoder are integrated into the combustion chamber system, then measurement accuracy of pressure and acceleration is improved, but manufacturing precision requirements increase
Solution Approach 1:
The pressure sensor and encoder are positioned in separate locations: the pressure sensor is mounted on the combustion chamber wall to measure chamber pressure, while the encoder is mounted on the motor shaft to measure rotational speed. This spatial segmentation allows each sensor to be calibrated and adjusted independently, reducing the impact of manufacturing tolerances on measurement accuracy.
Solution Approach 2:
The encoder measures rotational speed as an intermediate parameter, which is then used to calculate centrifugal acceleration through a known mathematical relationship (a = ω²r). This indirect measurement approach avoids the complexity of directly measuring acceleration, reducing manufacturing precision requirements while maintaining measurement accuracy.
4Reliability
If the test stand includes energy storage module and igniter power supply system, then reliability of experimental tests is improved, but device complexity and loss of energy increase
Solution Approach 1:
The energy storage module (batteries) and igniter power supply system are pre-configured and tested before each experiment. The igniter system is primed with the appropriate charge, and the energy storage module is charged in advance, ensuring reliable operation during the brief combustion test. This preliminary preparation improves reliability without requiring complex real-time power management systems.
Solution Approach 2:
The energy storage module and igniter system are designed as self-contained units that can be independently replaced and tested. The igniter power supply system automatically manages its own charging and discharge cycles, reducing the need for complex external power management circuitry and minimizing energy losses through simplified power conversion stages.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
Enables precise measurement of the linear burning rate and pressure changes in a combustion chamber under centrifugal acceleration, providing insights into the performance and safety limits of solid rocket motors.
Implementation Method 1
the effect of accelerations (rotary motion) on the linear burning rate of solid rocket propellants
Implementation Method 2
electronic pressure measuring system in a combustion chamber
Implementation Method 3
combustion chamber with an internal collector groove
Data Source
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AI summary
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.