吸气式空空导弹FADS系统标定研究

陈广强; 豆修鑫; 杨云军; 周伟江; 豆国辉

doi:10.11729/syltlx20170133

吸气式空空导弹FADS系统标定研究

doi: 10.11729/syltlx20170133

中国航天空气动力技术研究院空气动力理论与应用研究所, 北京 100074

基金项目:

国家自然科学基金项目 11472258

国家自然科学基金项目 11372040

详细信息

作者简介:
陈广强(1982-), 男, 广西合浦人, 硕士, 高级工程师。研究方向:嵌入式大气传感技术, 飞行器气动布局设计与计算技术。通信地址:北京7201信箱16分箱(100074)。E-mail:guangqiangchen@sina.com

通讯作者:
豆修鑫, E-mail: xiuxindou@sina.com

中图分类号: V211.74
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- 被引次数: 0
出版历程
- 收稿日期: 2017-10-20
- 修回日期: 2018-01-04
- 刊出日期: 2018-10-25

Study on calibration of FADS system for air-breathing air-to-air missile

Institute of Theoretical and Applied Aerodynamics, China Academy of Aerospace Aerodynamics, Beijing 100074, China

摘要

摘要: 针对自主研发的吸气式空空导弹FADS系统，利用FD-12风洞对其进行了标定研究。分析了风洞标定试验的技术特点，提出一种采用变支杆长度方法避开风洞试验台阶波的标定方案，包括支杆设计、模型加工、安装以及测压管路气密性检测等，在风洞中完成标定试验。试验结果表明：在Ma2.0~3.5范围内，FADS系统的测量误差精度全部达到设计目标，其中静压误差≤490Pa（≤3%）、马赫数误差≤0.1、迎角和侧滑角误差≤0.5°；与首次标定相比，各来流参数测量误差均减小，特别是Ma2状态下，静压最大相对误差由11.5%降低到3.0 %，马赫数最大误差由0.15下降到0.10，迎角最大误差由2.5°降低到0.5°，侧滑角最大误差由1.2°降低到0.5°。研究结果可为FADS系统设计提供技术参考。
- 吸气式空空导弹 /
- 嵌入式大气数据传感系统 /
- 风洞试验标定 /
- 台阶波
Abstract: Aiming at the independently developed FADS system of the air-breathing air-to-air missile, the calibration is carried out by FD-12 wind tunnel. The technical characteristics of the wind tunnel calibration test are analyzed. The wind tunnel calibration scheme is proposed to avoid the step shock wave by using the variable length pole, mainly including the pole design, machining and installation of the model and the air tightness detection of the pressure pipe. The second calibration is done in FD-12 wind tunnel.The experimental results show that:in the range of Mach number from 2.0~3.5, the measurement error of FADS system achieves the design goal:the error of the static pressure is less than 490Pa (less than 3%), the error of Ma is less than 0.1, and both errors of the angle of attack and the angle of side slip are less than 0.5°. Compared with the calibration at first time, the errors of the flow parameter measurements are all reduced, especially for the Ma2 status where the maximum relative error of the static pressure decreases from 11.5% to 3.0%, the maximum error of Ma decreases from 0.15 to 0.10, the maximum error of angle of attack decreases from 2.5° to 0.5°, and the maximum error of angle of side slip decreases from 1.2° to 0.5°. The research results can provide technical reference for the design of FADS system.
- air-breathing air-to-air missile /
- FADS system /
- wind tunnel calibration /
- step shock wave

HTML全文

图 1 欧洲"流星"远程吸气式空空导弹

Figure 1. European "Meteor" long range air-to-air missile

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图 2 FADS系统原理样机

Figure 2. Prototype of FADS system

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图 3 测压点布局

Figure 3. Layout of pressure measurement points

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图 4 风洞标定示意图

Figure 4. Sketch of wind tunnel calibration

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图 5 风洞试验模型

Figure 5. Wind tunnel test model

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图 6 Ma=2, β=0°测量结果对比

Figure 6. Comparison of measurement results of β=0°, Ma=2 case

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图 7 FADS系统风洞试验标定设计流程

Figure 7. Flowchart of design in calibration of FADS system

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图 8 Ma=2.0, 3.0, 4.0的台阶波结构

Figure 8. Step shock wave structure of Ma=2.0, 3.0, 4.0 cases

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图 9 风洞标定模型位置和各参数定义

Figure 9. Position of the wind tunnel calibration model and the definition of each parameter

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图 10 Ma=2模型位置

Figure 10. Model location of Ma=2 case

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图 11 Ma=2.5~3.5模型位置

Figure 11. Model location of Ma=2.5~3.5 case

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图 12 Ma=2, β=-5°测量结果对比(短支杆)

Figure 12. Comparison of measurement results of Ma=2, β=-5°(short pole)

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图 13 Ma=2, β=-5°测量结果对比(长支杆)

Figure 13. Comparison of measurement results of Ma=2, β=-5°(long pole)

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图 14 Ma=3, β=5°测量结果对比

Figure 14. Comparison of measurement results of Ma=3, β=5°

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表 1 首次标定试验状态

Table 1. Test status for the first calibration

序号	来流参数	参数范围
1	Ma	2.0, 2.5, 3.0, 3.5, 4.0
2	迎角α/(°)	-2, 0, 2, 4, 6, 10, 12
3	侧滑角β/(°)	0, -3, -5
4	静压p_∞/kPa	参考风洞实际静压

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表 2 首次标定误差统计表

Table 2. The error statistics of the first calibration

实验状态	静压误差 /Pa	静压相对误差	马赫数误差	迎角误差 /(°)	侧滑角误差/(°)
Ma=2.0	≤3000	≤11.5%	< 0.15	≤2.5	≤1.2
Ma=2.5	≤970	≤6.0%	< 0.10	< 1.0	< 1.0
Ma=3.0	< 400	≤4.4%	< 0.10	< 1.0	< 1.0
Ma=3.5	< 300	≤3.3%	< 0.10	< 1.0	< 1.0
Ma=4.0	< 300	≤6.9%	< 0.10	< 1.0	< 1.0

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表 3 两次标定结果对比(不含迎角±12°状态)

Table 3. Comparison of two calibration results without the angle of attack ±12°

试验马赫数	模型	静压误差 /Pa	静压相对误差	马赫数误差	迎角误差 /(°)	侧滑角误差/(°)
2.0	首次	≤3000	≤11.5%	≤0.15	≤2.5	≤1.2
2.0	二次	≤490	≤1.9%	≤0.05	≤0.5	≤0.5
2.5	首次	≤970	≤6.0%	≤0.10	≤1.0	≤1.0
2.5	二次	≤400	≤2.4%	≤0.05	≤0.5	≤0.5
3.0	首次	≤400	≤4.4%	≤0.10	≤1.0	< 1.0
3.0	二次	≤200	≤2.4%	≤0.05	≤0.5	≤0.5
3.5	首次	≤300	≤3.3%	≤0.10	≤1.0	≤1.0
3.5	二次	≤200	≤3.0%	≤0.10	≤0.5	≤0.5
4.0	首次	≤300	≤6.9%	≤0.10	≤1.0	≤1.0

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