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Rocket Engine Thrust Force Measurement

Axial Force Testing for Propulsion Systems

A facility developing liquid-propellant rocket engines needed a reliable way to measure thrust during static fire tests. These tests involve extreme conditions, including intense exhaust heat and strong vibrations, that complicate force measurement. Accurate force measurement under changing conditions is critical for engine validation, combustion stability analysis, and mission modelling.

Challenge

  1. Thermal Drift Across Extreme Temperatures: Exposure to intense exhaust heat makes stable measurements difficult.
  2. High-Frequency Dynamic Loading: Thrust changes rapidly during engine start‑up and shutdown. Capturing these rapid changes accurately is difficult, especially in a high‑vibration environment.
  3. Bidirectional Force Requirements: This application requires the measurement system to handle high compression forces from engine thrust. It must also handle tension forces during pre-test calibration. Designing for accurate performance in both directions adds complexity to the setup.

Solution

  1. Temperature Performance Validation: Known deadweight loads were applied at rated temperature extremes in a controlled lab environment. This testing validated load cell performance under real conditions. TC Span and TC Zero were then adjusted using the collected data to improve measurement accuracy and reliability across all operating conditions.
  2. High-Frequency Data Acquisition: The AN310 indicator was configured for high-speed sampling to capture thrust during the critical ignition and shutdown phases. This allows accurate measurement while filtering out noise from the high-vibration environment.
  3. Bidirectional Structural Integrity: The 363YS is designed to handle both the high compression forces generated by engine thrust and the tension forces required during pre-test calibration. This ensures stable and accurate performance in both loading conditions.
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Conclusion

The ANYLOAD 363YS and AN310 system delivered measurable improvements across all critical performance areas. The facility achieved a thrust measurement accuracy of ±0.05%, which enabled more precise fuel-to-oxidizer ratio tuning. Reduced thermal drift ensured stable output in high-heat conditions, improving repeatability and reducing the need for frequent recalibration. High-resolution data captured during critical test phases provided deeper insight into engine performance and streamlined the validation process. Overall, higher fidelity ground test data reduced uncertainty in projected flight conditions and helped lower launch risk.

Rocket-Engine-Main-v2
363YS-Grid

Keywords:
Static Fire Testing, Rocket Engine Thrust,  Peak Force Capture, High Temperature.

Featured Products

CUSTOM 363YS
Compression & Tension Load Cell
See standard version.

  • Temperature compensation under load for superior data fidelity
  • Physically tested to survive in extreme temperature environments
  • Customized for vibration, water/steam, and flame resistance
  • Standard Rated Capacities: 1t, 2t, 3t, 5t, 10t, 20t, 30t, 50t, 100t, 150t, 200t, 300t

AN310
Panel Mount Indicator
See Product.

  • Internal resolution of 16 million counts ensures exceptional precision and stability in measurement
  • Ultra-high-speed 5 kHz ADC enables fast, accurate weight capture, ideal for dynamic weighing scenarios.
  • Simultaneous multi-output support allows seamless integration with multiple systems and protocols.
  • 4 digital inputs (photocoupler) and 4 digital outputs (PhotoMOS relay) provide flexible external control and system interaction.
  • 10-point calibration capability provides precise linearity across the full measuring range.
  • Password-protected calibration
  • Dual calibration modes support both real-load and digital methods for flexible installation and maintenance.
  • Stores up to 3 calibration backups with easy restore and automatic/manual save options

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