Rocket Engine Control Circuit Using Segmented Loops
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Solution Overview
Problem
Current rocket engine thrust regulation methods are complex and require significant calculation effort, making them vulnerable to failures and inefficient, especially in limited onboard computing power environments.
Innovation Solution
A method involving open-loop control for supply valves and closed-loop control for turbines, using a tracking filter and disturbance corrector to regulate the flow of liquid propellants, allowing for precise thrust control with reduced computational resources and fewer regulation devices.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If complex regulation methods with multiple valves and devices are used to regulate thrust over a wide range, then thrust regulation precision is improved, but device complexity and calculation effort increase significantly
Solution Approach 1:
The regulation system is segmented into two distinct control loops: an outer loop that calculates the setpoint for the first supply valve based on thrust demand, and an inner loop that calculates the setpoint for the first turbine based on the valve setpoint and feedback from actual thrust. This segmentation allows each loop to handle specific aspects of control, reducing the overall complexity while maintaining precision.
Solution Approach 2:
The inner control loop incorporates feedback from the actual thrust value to calculate the setpoint for the first turbine. This feedback mechanism enables the system to automatically adjust the turbine operation based on actual performance, improving thrust regulation precision without requiring complex mechanical regulation devices.
2Adaptability or versatility
If multiple regulation devices and valves are used for thrust control, then thrust regulation capability is improved, but reliability decreases due to more potential failure points
Solution Approach 1:
The invention extracts the essential regulation function from complex mechanical valve systems and implements it through a simplified electronic control system that directly actuates the first supply valve and first turbine. By removing unnecessary intermediate regulation devices while retaining the core control capability, the system achieves both thrust regulation versatility and improved reliability.
Solution Approach 2:
The control system achieves multiple functions (thrust regulation, adaptability to different operating conditions) through a universal electronic control architecture that can handle various thrust demands and operating scenarios through software algorithms rather than requiring separate mechanical regulation devices for each function.
3Measurement precision
If complex calculation methods are used for regulation, then thrust control precision is improved, but the burden on onboard computing resources increases
Solution Approach 1:
The outer control loop pre-calculates the setpoint for the first supply valve based on the desired thrust value before the inner loop executes the fine adjustment. This preliminary action allows the system to establish a good initial operating point, reducing the computational complexity required for the feedback correction in the inner loop and thereby reducing overall computing power consumption.
Data Source
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AI summary
The invention relates to a method and circuit for controlling a rocket engine (1) comprising at least one combustion chamber (3) and a liquid propellant supply circuit (10) with a pump (12) and a turbine (14) for actuation of the pump (12), a supply valve (15), and a turbine control device (14). An opening setpoint (DVCH) for the valve (15) is calculated from an external setpoint (Cext), according to an open-loop control law; a setpoint for the turbine control device (14) is calculated from said external setpoint (Cext) and at least one feedback value, according to a closed-loop control law; and the valve (15) and the turbine control device (14) are controlled according to the respective setpoints.