2-Pulse Gas Generator Combustion Surface Position Detection
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Solution Overview
Problem
Existing methods for measuring propellant consumption in missile thrusters lack precision, particularly in dynamic operational scenarios where the thruster operation pattern needs to be adjusted based on real-time target conditions, leading to inaccuracies in propellant consumption estimation.
Innovation Solution
A 2-pulse gas generator with a pressure vessel, solid propellant, igniter, barrier membrane, and position sensor device, where the propellant combustion surface position is detected and used to estimate propellant consumption, allowing for precise adjustment of thruster operation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If existing methods for measuring propellant consumption are used, then the measurement process is simple, but the precision of propellant consumption estimation is insufficient
Solution Approach 1:
The patent replaces mechanical measurement methods with ultrasonic wave-based measurement. The ultrasonic transmitter and receiver detect combustion surface position through acoustic waves, enabling precise measurement without complex mechanical contact sensors in the high-temperature combustion environment.
Solution Approach 2:
The patent introduces ultrasonic waves as an intermediary to measure combustion surface position indirectly. Instead of directly measuring propellant consumption, the system uses ultrasonic wave propagation time to detect the position of the combustion surface, which then correlates to propellant consumption amount.
2Adaptability or versatility
If thruster operation pattern is adjusted based on real-time target conditions, then the adaptability of missile operation is improved, but the accuracy of propellant consumption estimation becomes more difficult to maintain
Solution Approach 1:
The patent implements a feedback mechanism where the measured combustion surface position is continuously monitored and used to estimate propellant consumption in real-time. This allows the system to adapt to changing operational conditions while maintaining accurate consumption estimation through continuous measurement and calculation.
Solution Approach 2:
The patent enables dynamic measurement of combustion surface position during thruster operation. The ultrasonic measurement system operates in real-time, allowing the missile to adjust thruster operation patterns dynamically while accurately tracking propellant consumption regardless of changing target conditions or flight phases.
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
This approach enables higher precision in propellant consumption estimation, enabling more accurate control of thruster operations and optimizing propellant use in response to changing mission requirements.
Implementation Method 1
an ultrasonic transmitter 131 to transmit ultrasonic waves for the combustion surface of the solid propellant 3; and an ultrasonic receiver 132 to receive the ultrasonic waves reflected on the combustion surface of the solid propellant 3
Implementation Method 2
The ultrasonic wave transmitted by the ultrasonic transmitter 131 is reflected on the combustion surface F1' of the solid propellant 3, and at least a part of the reflected ultrasonic wave is received by the ultrasonic receiver 132
Data Source
AI summary
The first solid propellant is formed to have a columnar shape so as for a combustion surface to move to a first direction, and to have an end surface exposed to a combustion space. The surface of first solid propellant except for the end surface is covered with a barrier membrane. The position of combustion surface in the first direction is detected by a position sensor device in an always-on measurement or a fixed-point measurement. Based on the detected result, the consumption amount of the first solid propellant is estimated.