Airworthiness certification technology about icing wind tunnel test for pneumatic de-icing aircraft
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摘要: 民用飞机为获得型号合格证，应按照有关结冰适航规章条款进行结冰适航验证，如何解读适航条款要求并制定有效的符合性验证流程，是进行适航合格审定的关键。本文以Y12F气动除冰飞机结冰风洞试验的实际工程为例，以相关结冰适航文件为基础，结合国际最新的飞机结冰研究成果，研究并总结了目标试验状态设定、设备选择、试验状态的等效转换、模型研制、风洞试验等适航审定要求和技术。构建的结冰风洞试验适航审定方法，有效地指导完成了Y12F飞机除冰系统的适航验证工作，完成中国民用航空局（CAAC）和美国联邦航空管理局（FAA）同时审查，为获得CAAC和FAA型号合格证奠定良好基础。Abstract: Civil aircraft should conduct icing airworthiness certification according to relevant icing airworthiness regulation requirements, so understanding the airworthiness regulations requirements and formulating the effective conformity certification process are the key points of airworthiness certification. Based on an engineering application of icing wind tunnel test for the Y12F aircraft, relative airworthiness documents, latest aircraft icing research results, certification requests and techniques are summarized, such as setting of target test cases, confirmation of facility, transformation of test cases, test model designing and manufacturing, icing wind tunnel testing and so on. The formed airworthiness certification method conducts the certification of Y12F airplane de-icing system effectively, which is accepted by Civil Aviation Administration of China (CAAC) and Federal Aviation Administration (FAA) synchronously, and it lays a good foundation for getting the aircraft certification of CAAC and FAA.
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图 1 除冰套模型压力曲线与除冰套原型压力曲线对比
Figure 1. The pressure curve of de-icing boot model contrasts with the pressure curve of prototype de-icing boot
图 2 冰形表面粗糙度(右)与砂纸对比照片
Figure 2. The roughness comparison between ice shape surface (right) and the sandpaper (left)
表 1 Y12F飞机典型飞行状态参数
Table 1. Classic flight profile parameter of Y12F aircraft
No. Flight profile Altitude/
feetFlap position/
(°)Air speed/
knotsAOA of wing/
(°)AOAof HT/
(°)1 Takeoff 0 0 89 6.3 -0.5 2 Climb 3000 0 139 4.3 -1.5 3 Cruise 10000 0 301 0.4 -4.5 4 Descent 20000 0 169 0.9 -3.9 5 Holding 10000 0 207 3.4 -2.5 6 Landing 0 20 69 1.6 -7.6 注：HT-Horizontal Tail，AOA-Angle of Attack 
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表 2 Y12F飞机结冰风洞试验的目标试验状态(目标试验条件矩阵)
Table 2. The target test conditions of Y12F aircraft in icing wind tunnel test (test conditions matrix)
No. Liquid water content/
(g·m-3)Mean volumetric diameter/
μmStatic air temperature/ Flight profile Air speed/knots Inflation pressure/
psigBoot cycle time/
sCCAR25 appendix C maximum conditions Objective of simulation run/remarks ℉ ℃ 1 0.53 17 14 -10.0 Takeoff 89 18 60 Continuous Intercycle 2 0.53 17 14 -10.0 Landing 69 18 60 Continuous Intercycle 3 0.51 20 21 -6.10 Landing 69 18 60 Continuous Intercycle 4 0.20 35 21 -6.10 Climb 139 18 60 Continuous Residual 5 0.68 15 21 -6.10 Descent 169 18 60 Continuous Intercycle 6 0.50 22 -4 -20.0 Cruise 301 18 60 Intermittent Residual 7 0.23 30 14 -10.0 Cruise 301 18 60 Continuous Residual 8 0.50 18 14 -10.0 Cruise 301 18 60 Continuous Residual 9 0.30 15 -4 -20.0 Cruise 301 18 60 Continuous Residual 10 0.51 20 21 -6.10 Holding 207 18 60 Continuous Intercycle 11 0.10 40 14 -10.0 Holding 207 18 60 Continuous Residual 12 0.15 25 -4 -20.0 Holding 207 18 60 Continuous Intercycle 13 0.53 17 14 -10.0 Holding 207 14 60 Continuous Low pressure-intercycle 14 0.50 22 Adjust Holding 207 18 60 Continuous Run-back 15 0.30 110 23 -5.0 Cruise 301 18 60 SLD Residual 16 0.52 40 14 -10.0 Climb 139 18 NA Intermittent Pre-activation- 2 minute 17 0.52 40 14 -10.0 Cruise 301 18 NA Intermittent Pre-activation- 2 minute 18 0.80 28 -4 -20.0 Cruise 301 18 60 Intermittent Residual 19 0.80 28 -4 -20.0 Holding 207 18 60 Intermittent Residual 20 0.60 28 -22 -30.0 Holding 207 18 60 Intermittent Residual 21 0.20 15 -22 -30.0 Cruise 301 18 60 Continuous Intercycle 22 0.50 22 -4 -20.0 Cruise 301 18 60 Intermittent Holding-45 minute duration 23 0.50 22 -4 -20.0 Cruise 301 18 NA Intermittent 22.5 minutes failure 注：NA-Not apply, no boot cycling.
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表 3 试验状态等效变换方法
Table 3. The scaled method on test conditionss
Test parameter Modified Ruff cs User selects Tst, s Φs=ΦR Vs User selects (typical) MVDs K0, s=K0, R LWCs n0, s=n0, R τs As=AR pst, s θs=θR
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表 4 试验状态等效变换结果
Table 4. The scaled result on test conditions
c/inch Tst/℉ V/knots δ/μm LWC/(g·m-3) t/s β0/% A n0 b Φ θ 参考值 44.56 21.0 301 20.0 0.51 60 0.66 0.14 0.07 0.54 5.88 2.16 等效变换值 44.56 24.5 170 25.4 1.40 40 0.66 0.15 0.1 1.07 5.88 8.96
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表 5 Y12F飞机结冰风洞试验的等效模拟试验状态(扩展试验条件矩阵)
Table 5. The scaled test conditions of Y12F aircraft in icing wind tunnel test (scaled test conditions matrix)s
No. LWC/
(g·m-3)MVD/
μmStatic air temperature/ Flight profile Air speed/
knotsInflation pressure/
psigBoot cycle time/
sCCAR25 appendix C maximum conditions Objective of simulation run/
remarks℉ ℃ 1 0.53 17 14.0 -10.0 Takeoff 89 18 60 Continuous Intercycle 2 0.53 17 14.0 -10.0 Landing 69 18 60 Continuous Intercycle 3 0.51 20 21.0 -6.1 Landing 69 18 60 Continuous Intercycle 4 0.60 35 21.0 -6.1 Climb 139 18 60 Continuous Residual 5 0.68 15 21.0 -6.1 Descent 169 18 60 Continuous Intercycle 6 0.85 30 -0.5 -18.1 Cruise 170 18 60 Intermittent Residual 7 0.88 38 17.5 -8.1 Cruise 170 18 60 Continuous Residual 8 1.80 23 17.5 -8.1 Cruise 170 18 60 Continuous Residual 9 0.30 15 -0.5 -18.1 Cruise 170 18 60 Continuous Residual 10 0.75 22 22.0 -5.6 Holding 170 18 60 Continuous Intercycle 11 0.58 43 15.0 -9.4 Holding 170 18 60 Continuous Residual 12 0.24 27 -3.0 -19.4 Holding 170 18 60 Continuous Intercycle 13 0.65 19 15.0 -9.4 Holding 170 14 60 Continuous Low pressure-intercycle 14 0.50 22 Adjust Holding 170 18 60 Continuous Run-back 15 1.27 109 10.0 -12.2 Cruise 69 18 60 SLD Residual 16 0.63 40 14.0 -10.0 Climb 139 18 Na Intermittent Pre-activation-2 minute 17 1.90 50 17.5 -8.1 Cruise 170 18 Na Intermittent Pre-activation-2 minute 18 1.50 35 -0.5 -18.1 Cruise 170 18 60 Intermittent Residual 19 0.95 30 -3.0 -19.4 Holding 170 18 60 Intermittent Residual 20 0.61 30 -21.0 -29.4 Holding 170 18 60 Intermittent Residual 21 0.34 19 -18.5 -28.1 Cruise 170 18 60 Continuous Intercycle 22 0.85 30 -0.5 -18.1 Cruise 170 18 60 Intermittent Holding-45 minute duration 23 0.85 30 -0.5 -18.1 Cruise 170 18 Na Intermittent 22.5 minute failure
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