# High-Reliability Wireless Pressure Measurement System Based on FEC Algorithm
###### Abstract  
As the core of an aircraft's power system, the stability and reliability of an aero-engine's performance are crucial to flight safety. Addressing the issues of complex wiring and poor flexibility in traditional wired testing systems, this paper designs and implements a wireless transmission aero-engine pressure measurement system based on FPGA. By integrating front-end memory and a back-end test bench and utilizing LoRa wireless communication technology and the Reed-Solomon (RS) forward error correction (FEC) algorithm, the system significantly enhances the reliability and anti-interference capability of data transmission. Test results demonstrate that the system can monitor and record engine pressure parameters in real time in complex environments, with a notable reduction in bit error rate and packet loss rate, especially under strong interference conditions. This system resolves wiring challenges, enhances the real-time performance of monitoring links and the stability of data storage, and is characterized by high precision, high reliability, and automation. It is suitable for complex and harsh working environments and has broad application prospects in the aviation and military sectors. F 2025 10 March 2025  
stands out. The United States, for example, has significant advantages in the precision manufacturing of aero-engine testing equipment and the innovative research into and development of testing technologies and is in a world-leading position [5]. Although China has also achieved phased achievements in related technologies, high-performance testing technologies are still in the development stage. Compared with developed countries, China started relatively late in testing equipment for aero-engine mechanical parameters, and there is also a shortage of ground-based mechanical testing equipment, resulting in insufficient fault exclusion capabilities for engines [6]. Despite the phased achievements, there are still disadvantages. For example, problems such as relatively single-function testing systems, inconvenient human-machine interaction, and low reliability still remain unsolved [7]. When an aircraft is in flight, due to the complex external environment and continuous high-load operation, the aero-engine may encounter uneven pressure distribution. This situation may cause components like fans and compressors to experience uneven stress and vibration, thus affecting their performance and structural integrity. Extensive research has confirmed that irregular pressure changes are a key factor influencing the stability of aero-engines and a common cause of their instability [8,9]. With the advancement of aerospace electronic technology and the continuous improvement of aero-engine performance, the field of engine testing is also confronted with new challenges [10]. Firstly, as the internal structure of engines is optimized and test signals become more complex, signal processing has become increasingly difficult [11,12]. Secondly, the diversity and instability of the testing environment make it challenging to collect key parameters, such as pressure, under specific conditions [13]. Existing testing systems often face severe signal interference and complex wiring problems in these environments [14]. Therefore, there is an urgent need to update engine testing technologies and equipment. The new-generation testing systems are required to have features such as real-time response, high-precision measurement, high sensitivity, high reliability, and miniaturization [15,16]. In view of the numerous problems currently faced in aero-engine testing, such as complex wiring, severe signal interference, and insufficient real-time performance, this paper innovatively proposes a system that integrates testing storage and wireless communication technologies. The development of this system has profound practical significance. It can address the drawbacks of traditional testing systems and meet the current testing requirements of aero-engines [17].