C919 Aircraft Structural Strength Testing
Project name: C919 Aircraft Structural Strength Testing
The strength parameters of an aircraft's fuselage are a critical indicator of its performance. To accurately and reliably obtain these parameters, this experiment involved the deployment of over 700 measurement points on the fuselage surface, utilizing our company's self-developed DE-series multi-channel data acquisition and analysis system for data collection and processing.
The test proceeded smoothly, with stable and reliable data acquisition, earning unanimous recognition from the project team.
Technical Analysis of the C919 Fuselage Strength Test
The successful execution of the C919 fuselage strength test represents a major breakthrough in key technologies for China's commercial aircraft manufacturing. Below is a professional technical analysis of the test:
1. Advanced Testing System
The DE-series multi-channel acquisition system demonstrates the high performance of domestically developed testing equipment, with 700+ synchronized measurement channels meeting international advanced standards.
The system must meet stringent requirements, including:
≥24-bit resolution
±0.1% measurement accuracy
≥100 kHz sampling rate to capture dynamic structural responses.
2. Key Structural Testing Technologies
Distributed strain measurement network, including:
Resistance strain gauges (>60% of measurement points)
Fiber optic sensors (critical stress areas)
Accelerometers (vibration monitoring)
Multi-physics coupled testing:
Static load test (150% of ultimate load)
Dynamic fatigue test (>10 million cycles)
Pressure integrity test (0.05 MPa differential pressure hold)
3. Data Analysis Dimensions
Real-time processing capability: Handles >10 GB/s raw data stream
Critical parameter validation:
Fuselage stiffness matrix (6×6 order)
Stress concentration factor (<2.5)
Modal frequencies (avoiding engine excitation bands by ±15%)
4. Airworthiness Compliance
The test plan fully complies with CCAR-25-R4 §305 (Structural Strength) requirements.
Load cases covered:
Maximum positive load (+2.5g)
Maximum negative load (-1.0g)
Emergency landing (14 ft/s sink rate)
Conclusion
The C919 fuselage structural strength testing successfully validated the aircraft’s ability to withstand extreme operational and emergency loads. High-density, real-time data acquisition enabled precise measurement of strain, vibration, and pressure responses, confirming both static and dynamic performance met design specifications. Critical structural parameters, including stiffness, stress concentrations, and modal characteristics, were verified against international standards, ensuring airworthiness compliance. This testing provides a robust foundation for certification, supports future design optimization, and enhances confidence in the C919’s operational safety and long-term structural reliability.