Free-flight test in horizontal wind tunnel with powered aircraft
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摘要:
为了在设计初期开展气动/飞行/控制一体化研究，缩短研制周期，降低研发成本，在FL-10风洞开口试验段建立了水平风洞自由飞试验系统。该系统根据尺寸、质量及转动惯量相似准则设计缩比验证机模型，建立飞行控制系统，在此基础上对系统建模仿真，设计闭环增稳控制律，实现配平迎角稳定飞行。试验结果显示：根据相似准则设计的飞行控制律结构及参数，仿真配平迎角为5°，配平升降舵舵偏为−4.5°，风洞试验迎角控制在（5±0.2）°范围内，由于供电、信号线缆会给试验模型一个正向俯仰力矩，升降舵舵偏控制在−3.2°左右，略小于仿真配平升降舵舵偏。
Abstract:In order to carry out aerodynamic/flight/control integration research at the early stage of design, shorten the development cycle and reduce the development cost, a model free-flight test system was established in FL-10 open wind tunnel. The system was used to design the scale verification machine model according to the similarity criteria of size, mass and moment of inertia, invent the flight control system, on this basis, the system was modeled and simulated, and the closed-loop stability increasing control law was designed to realize the stable flight at the trim angle of attack. The test results showed that the structure and parameters of the flight control law were designed according to the similarity criterion, the simulated trim angle of attack was 5°, the trim elevator deviation was −4.5°, and the wind tunnel test angle of attack was controlled within (5±0.2)°. Because the power supply and signal cables gave the test model a positive pitch moment, the elevator deviation was controlled at about −3.2°, which was slightly less than the simulated trim elevator deviation.
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Key words:
- wind tunnel test /
- free-flight /
- flight control system /
- powered model /
- similarity criterion
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图 1 NASA Langley研究中心风洞自由飞试验系统
Figure 1. Wind tunnel free-flight test system of NASA Langley Research Center
图 2 航空工业气动院风洞自由飞试验系统
Figure 2. Wind tunnel free-flight test system of China Aviation Industry Aerodynamics Research Institute
图 4 某翼身融合布局模型转动惯量测量
Figure 4. Measurement of moment inertia of blended wing body model
图 5 风洞自由飞试验飞行控制计算机系统
Figure 5. Flight control computer system of wind tunnel free-flight test
图 7 五孔探针空速/迎角/侧滑角测试
Figure 7. Airspeed/angle of attack/sideslip angle test of five-hole probe
图 9 副翼脉冲信号-副翼舵面角度对应关系
Figure 9. Corresponding relationship between aileron pulse signal and aileron control surface angle
图 10 V尾脉冲信号-V尾舵面角度对应关系
Figure 10. Corresponding relationship between V-tail pulse signal and V-tail rudder surface angle
图 12 无风条件下油门开度与推力对应关系
Figure 12. Corresponding relationship between throttle and thrust under no wind condition
图 13 0 m/s及30 m/s风速条件下油门开度与推力对应关系
Figure 13. Corresponding relationship between different throttle and thrust under 0 m/s and 30 m/s wind speed
表 1 风洞自由飞试验模型参数相似关系
Table 1. Similarity relation for wind tunnel free-flight test model parameters
参数 原型机/缩比模型比例 $ m $ $ {N^3} $ ${I}_{ {x} }、{I}_{{y} }、{I}_{\textit{z} }$ $ {N^5} $ $ S $ $ {N^2} $ $ b、\overline{c} $ $ N $ 
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表 2 惯性传感器性能指标
Table 2. Performance index of inertial sensor
参数 量程 精度 俯仰、滚转角度/（°） −180～180 0.2 俯仰、滚转角速度/（（°）/s） −300～300 1
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表 3 五孔探针性能指标
Table 3. Performance index of five-hole probe
参数 量程 精度 迎角、侧滑角/（°） −30～30 0.5 俯仰、滚转角速度/（（°）/s） 5～50 0.5
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