一种挤压式一级火箭的推力控制方法
By employing cascaded PID control and weighted pressure distribution thrust control methods, the problems of disturbance resistance and fault tolerance in the thrust control of squeeze-type rockets were solved. This enabled precise control of the liquid nitrogen turbopump and stable output from the thrust chamber, thereby improving the rocket's thrust control accuracy and system reliability.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- SHENZHEN YULONG AEROSPACE TECH CO LTD
- Filing Date
- 2026-05-07
- Publication Date
- 2026-07-17
AI Technical Summary
Existing squeeze rockets suffer from weak anti-disturbance capabilities, low thrust tracking accuracy, and poor fault tolerance in thrust control. In particular, the speed of the liquid nitrogen turbopump lacks effective cascade coordinated control, which affects the liquid nitrogen vaporization efficiency and the distribution accuracy of the propellant mixing ratio, thus failing to meet the requirements of high-precision flight.
A thrust control method based on cascade PID control is adopted, combined with weighted pressure distribution and adaptive cooling. Key parameters are collected in real time by the flight control computer to achieve precise regulation of thrust chamber pressure and liquid nitrogen turbopump speed. A complete closed-loop control logic is established, and a fault degradation control strategy is used to ensure the stability and reliability of thrust output.
It improves thrust control precision, enhances the system's anti-disturbance capability and fault tolerance, ensures the stability and reliability of thrust output, extends the service life of the structure, and meets the requirements of high-precision flight.
Smart Images
Figure CN122190942B_ABST