【作者】 杨科；

【导师】 魏德宝；

【作者基本信息】 哈尔滨工业大学 ， 仪器仪表工程（专业学位）， 2022， 硕士

【摘要】 民用飞机的飞行静压是指飞行所在的飞行高度的大气压,静压数据是极其重要的参数之一,直接对应着飞机的飞行高度,同时还为其他设备提供静压参考源,所以在现代民机飞行试验过程中,静压的测量非常重要。常见的静压测量方法通常有前支杆和拖锥两种测量方法,前支杆测量方法是通过在飞机前部加装一根长长的支杆,将静压测量点前伸到“干净”的气流中,进而测量静压值,所谓的干净气流,就是指没有扰动的气流。拖锥测量法则是在飞机尾部加装一根长长的拉线式的锥体,将测点向后延伸到干净的气流中,进而测量静压。拖锥系统通常可以分为可收放拖锥和简易拖锥两种,顾名思义,可收放拖锥在飞行过程中是可以收放的,收放长度和速度可进行控制和调节,而简易拖锥的伸出长度是固定的。前支杆测量方法对安装强度要求较高,且安全性较低,拖锥测量法方便灵活且安全性较高,前支杆测量方法更适用于军机或通航小飞机,拖锥测量方法适用于大型飞机。可收放拖锥可大幅提升试飞效率,是现代民机静压参数测量的首选,本文主要研究的就是可收放拖锥系统。可收放拖锥系统的研制要基于飞机型号的需求,不同机型因为飞机尺寸、布局和性能的不同,对可收放拖锥的需求也不同,在方案设计上差异很大。本文首先基于某型号飞机的静压测试需求,对系统设计的总体需求进行全面分析。随后根据需求对可收放拖锥的软硬件进行了精细设计,设计内容包括客舱显示控制系统、收放控制系统、静压测量系统和驾驶舱控制系统。系统设计和制造完成后,最重要的三项工作就是确认静压测量模块的气密性能,确认拖锥的收放长度以及确认系统误差,只有这三项指标均满足要求后,系统才能投入使用。通过地面气密试验,验证了系统泄漏率≤100英尺/分钟,满足适航条款要求。通过采用飞行试验验证的方法,确认拖锥的收放长度为213.25英尺。通过拖锥塔校试验飞行和数据分析处理,确认可收放拖锥系统的高度误差在12英尺～48英尺之间,拖锥速度误差在1节以内。系统误差的测试工作是非常重要且复杂的,最终根据飞行试验的验证以及获取的试验数据,通过数据分析及结果,确认了研制的可收放拖锥系统满足设计要求。更多还原

【Abstract】 The static pressure of civil aircraft refers to the atmospheric pressure of the flight altitude where the flight is located.The static pressure data is one of the most important parameters.It directly corresponds to the flight altitude of the aircraft and also provides a static pressure reference source for other equipment.Therefore,the static pressure measurement is very important during the flight test of modern civil aircraft.Static pressure measurement methods usually have two measurement methods:front support rod and trailing cone.The front support rod measurement method is to add a long support rod to the front of the aircraft to extend the static pressure measurement point to a "clean" airflow,the static pressure value is then measured.The so-called clean airflow refers to the airflow without disturbance.The trailing cone measurement method is to pretend a long pull-line cone on the tail of the aircraft,extend the measuring point back into the clean airflow,and then measures the static pressure.The trailing cone system can usually be divided into two types:retractable trailing cone and simple trailing cone.As the name suggests,retractable trailing cone can be retracted during flight,and the retractable length and speed can be controlled and adjusted.The extension length of the cone is fixed.The front support rod measurement method has high installation strength requirements and low safety.The trailing cone measurement method is convenient and flexible and has high safety.The front support rod measurement method is more suitable for military aircraft or navigable small aircraft,while the towing cone measurement method is suitable for large aircraft.The retractable trailing cone can greatly improve the flight test efficiency.It is the first choice for the static pressure parameter measurement of modern civil aircraft.The main research in this paper is the retractable trailing cone system.The development of the retractable trailing cone system is based on the needs of the aircraft model.Different aircraft types have different requirements for the retractable trailing cone due to the difference in aircraft size,layout and performance,and the scheme design is very different.Firstly,this paper analyzes the overall requirements of the system design based on the static pressure test requirements of a certain type of aircraft.Then,the software and hardware of the retractable trailing cone were carefully designed according to the requirements,including the cabin display control system,retractable control system,static pressure measurement system and cockpit control system.After the completion of the system design and manufacturing,the three most important tasks are to confirm the airtight performance of the static pressure measurement module,confirm the retraction length of the trailing cone and confirm the system error.Only after these three indicators meet the requirements,the system can be put into use.Through the ground airtight test,it is verified that the leakage rate of the system is less than 100ft/min,which meets the requirements of the airworthiness clause.By using the method of flight test verification,it is confirmed that the retraction length of the trailing cone is 213.25 ft.Through the Tower-calibration flight test and data analysis,it is confirmed that the height error of the system is between 12ft～48ft and the speed error of the system is within 1kn.The test of system error is very important and complicated.Finally,according to the verification of flight test and obtained test data,through the data analysis and results,it is confirmed that the developed retraction trailing cone system meets the design requirements.更多还原