尖前缘驻点热流精细化测量研究

张杨; 贾广森; 沙心国; 陈星

doi:10.11729/syltlx20180112

尖前缘驻点热流精细化测量研究

doi: 10.11729/syltlx20180112

张杨^1,,
贾广森²,
沙心国^2, ,,
陈星²

1.
北京航天长征飞行器研究所, 北京 100076
2.
中国航天空气动力技术研究院, 北京 100074

基金项目:

国家自然科学基金面上项目 11872349，91752111

详细信息

作者简介:
张杨(1978-), 女, 湖南醴陵人, 高级工程师, 硕士研究生。研究方向:气动热环境研究。通信地址:北京9200信箱76分箱9号。E-mail:zhangy1zy@sina.com

通讯作者:
沙心国, E-mail: shaxg@163.com

中图分类号: V211.71
计量
- 文章访问数: 178
- HTML全文浏览量: 92
- PDF下载量: 14
- 被引次数: 0
出版历程
- 收稿日期: 2018-08-25
- 修回日期: 2018-12-25
- 刊出日期: 2019-12-25

Precise stagnation point heat flux measurement technique of sharp leading edges

1.
Beijing Institute of Space Long March Vehicle, Beijing 100076, China
2.
China Academy of Aerospace Aerodynamics, Beijing 100074, China

摘要

摘要: 为提高升阻比特性，现代高超声速飞行器常采用尖前缘结构，这对热防护系统提出了很大挑战。尖前缘结构由于表面曲率较大，常规的点测量和面测量试验技术均难以对驻点热流进行准确测量。针对尖前缘驻点热流测量难题，制作了专用的整体式薄膜电阻温度计，建立了驻点热流参数辨识方法，并以不同前缘半径（R=1.0、2.0和5.0 mm）的斜劈模型为研究对象，在FD-20高超声速脉冲风洞中开展了试验验证，来流马赫数分别为4、5、6和8，试验结果表明：整体式传感器稳定性好、灵敏度高、耐冲刷性强，其参数辨识方法精度高，试验获得的前缘驻点热流与理论值误差小于15%。
- 尖前缘 /
- 驻点热流 /
- 风洞试验 /
- 参数辨识
Abstract: In order to improve the aerodynamic performance, a sharp leading edge is widely used in the hypersonic flight vehicles, which exerts a huge challenge on thermal protection systems. The sharpness of the leading edge makes it hard to measure the stagnation point heat flux precisely. In this paper, an integral sensor with high spatial resolution is developed to measure the stagnation point heat flux, and the corresponding estimation method is adopted as well. A wedge model with an interchangeable nose(R=1.0, 2.0 and 5.0 mm) is employed to validate the effectiveness of the sensor, and a series of experiments are conducted at the FD-20 impulse wind tunnel under the condition of Mach number of 4, 5, 6 and 8. The results indicate that the difference of the stagnation point heat flux values is less than 15% between experimental measurement and theoretical prediction.
- sharp leading edges /
- stagnation point heat flux /
- wind tunnel testing /
- parameter identification

HTML全文

图 1 尖前缘驻点热流测量传感器示意图

Figure 1. Schematic of the integral heat flux sensors

下载: 全尺寸图片幻灯片

图 2 尖前缘驻点热流测量传感器实物图

Figure 2. Photograph of the integral heat flux sensors

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图 3 热物性随温度的变化规律

Figure 3. Substrate thermal property variation with temperature

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图 4 热物性参数对热流测量的影响

Figure 4. Heat flux deviation with temperature rise

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图 5 不同来流条件下表面温升(前缘半径R=1 mm)

Figure 5. Computed temperature rise under various flow conditions

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图 6 前缘半径对多维导热的影响

Figure 6. Computed temperature versus time for different sharp leading edge radiuses

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图 7 斜劈模型

Figure 7. Wedge model

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图 8 FD-20脉冲风洞

Figure 8. FD-20 impulse wind tunnel

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表 1 不同来流条件测量误差随计算时间变化情况

Table 1. Measured heat flux error deviation with time under various flow conditions

Q/(kW·m^-2)	Time/ms	Q_1D/Q_3D^*
100	5	0.976
	10	0.942
	20	0.876
	30	0.825
500	5	0.976
	10	0.942
	20	0.876
	30	0.825
1000	5	0.976
	10	0.942
	20	0.876
	30	0.825
^*: Q_1D采用一维热传导计算值, Q_3D采用三维热传导计算值。

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表 2 试验来流参数

Table 2. Test conditions

Flow condition	Ma	p_o/MPa	T_o/K	Re/m^-1	Piston
(1)	4.02	2.00	624.7	2.92×10⁷	NO
(2)	4.92	3.08	631.6	2.81×10⁷	NO
(3)	5.92	6.56	909.7	2.21×10⁷	YES
(4)	7.97	19.36	960.0	2.83×10⁷	YES

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表 3 不同来流条件下尖前缘驻点热流测量结果及误差

Table 3. Measured heat flux and errors

Flowcondition		R=1 mm	R=2 mm	R=5 mm
(1)	Q_t/(kW·m^-2)	1154.5	816.3	516.3
	Q_exp/(kW·m^-2)	983.7	794.9	553.8
	Error	-14.79%	-2.63%	+7.26%
(2)	Q_t/(kW·m^-2)		721.0
	Q_exp/(kW·m^-2)		676.4
	Error		-6.19%
(3)	Q_t/(kW m^-2)	1921.2	1358.5	859.2
	Q_exp/(kW·m^-2)	1097.0	956.4	676.2
	Error	-42.9%	-29.6%	-21.3%
(4)	Q_t/(kW·m^-2)		1331.8
	Q_exp/(kW·m^-2)		952.4
	Error		-28.49%
Error=(Q_exp-Q_t)/Q_t×100%, Q_t为理论值, Q_exp为试验测量值, Q_exp.m为修正后的试验测量值

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表 4 修正前后测量结果对比

Table 4. Comparison of measured and modified heat flux

Flow condition		R=1 mm	R=2 mm	R=5 mm
(3)	Q_t/(kW·m^-2)	1921.2	1358.5	859.2
	Q_exp/(kW·m^-2)	1097.0(-42.9%)	956.4(-29.6%)	676.2(-21.3%)
	Q_exp.m/(kW·m^-2)	1808.7(-5.86%)	1339.2(-1.42%)	817.6(-4.84%)
(4)	Q_t/(kW·m^-2)		1331.8
	Q_exp/(kW·m^-2)		952.4(-28.49%)
	Q_exp.m/(kW·m^-2)		1322.93(-0.67%)

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