民用大飞机试飞测试中存在一些特殊测试需求的科目，其特点是任务周期短、测量点分布广、测量点位多，如客舱\货舱温度测试、机翼振动和大气压力测试等。这类试飞科目，采用现有基于有线以太网的机载数据采集系统，存在测量设备安装困难、测试线缆敷设与穿舱工作复杂、相关改装工作周期长等问题。针对民机试飞过程中机翼结构关键状态参数的测量对采集系统提出柔性化（能与机翼共形）、微型化（不影响气动效应）、狭小空间内可实现的要求，通过开发包含柔性天线模块和柔性多传感参数采集模块的一体化集成微系统，并将微系统集成于民机机翼，验证了系统的功能可靠性和采集信号传输稳定性。因此设计了民用大飞机机翼状态监测的无线柔性测量系统，描述了系统的设计方法、数据传输策略和第三方记录器集成方法，最终通过机上地面试验实现数据的采集记录，试验结果表明该机载柔性采集系统可以实现温度、三轴振动、压力的测量。

Unique test requirements in civil large aircraft flight testing, characterized by short task durations, wide measurement point distribution, and numerous measurement locations, are addressed. Challenges in the existing wired Ethernet-based onboard data acquisition systems, including difficult measurement equipment installation, complex test cable layout, and prolonged retrofitting periods, are identified. A flexible, miniaturized, and compact space-compatible measurement system for critical wing structural state parameter measurements during civil aircraft flight testing was proposed. An integrated microsystem, including a flexible antenna module and a multi-sensor parameter collection module, was developed and integrated into the civil aircraft wing. The system's reliability and stable signal transmission were demonstrated. The design and application of a wireless flexible measurement system for wing state monitoring on civil aircraft were detailed. The system design approach, data transmission strategy, and integration with third-party loggers were described. Ground and flight tests were conducted to collect data. The onboard flexible system's capability to measure temperature, three-axis vibration, and pressure is verified.