CN111337220A - High-speed flight test flow field measurement system - Google Patents

High-speed flight test flow field measurement system Download PDF

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CN111337220A
CN111337220A CN202010291303.9A CN202010291303A CN111337220A CN 111337220 A CN111337220 A CN 111337220A CN 202010291303 A CN202010291303 A CN 202010291303A CN 111337220 A CN111337220 A CN 111337220A
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camera
cabin
glass
recorder
flow field
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CN111337220B (en
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高阳
任昆
罗太超
潘宏椂
王长峰
邹凯
周月荣
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China Academy of Aerospace Aerodynamics CAAA
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    • GPHYSICS
    • G01MEASURING; TESTING
    • G01MTESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M9/00Aerodynamic testing; Arrangements in or on wind tunnels
    • G01M9/06Measuring arrangements specially adapted for aerodynamic testing

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Abstract

本发明涉及一种高速飞行试验流场测量系统,包括头舱、丝线、后舱、记录仪组件、相机盒组件、视频采集器;所述头舱为高速飞行试验的研究性舱段,丝线采用种植法或粘接法一端固定在头舱所关心区域,后舱用于安置固定单机设备并与前舱通过轴向螺钉连接,相机盒组件穿壁固定于后舱壁面上,用于拍摄丝线区域流场分布,视频采集器与记录仪组件固定在后舱内部,分别用于对拍摄的丝线区域流场影像进行数据采集及存储。

Figure 202010291303

The invention relates to a flow field measurement system for a high-speed flight test, comprising a head cabin, a wire, a rear cabin, a recorder assembly, a camera box assembly and a video collector; the head cabin is a research cabin for a high-speed flight test, and the wire adopts One end of the planting method or bonding method is fixed on the area of interest in the head cabin, the rear cabin is used to place and fix stand-alone equipment and is connected with the front cabin through axial screws, and the camera box assembly is fixed through the wall on the rear bulkhead surface for photographing the silk thread area. Flow field distribution, video collector and recorder components are fixed inside the rear cabin, respectively used for data collection and storage of the flow field images in the silk thread area.

Figure 202010291303

Description

一种高速飞行试验流场测量系统A high-speed flight test flow field measurement system

技术领域technical field

本发明涉及一种高速飞行试验流场测量系统,属于空气动力学研究领域。The invention relates to a high-speed flight test flow field measurement system, which belongs to the field of aerodynamics research.

背景技术Background technique

数值计算、风洞试验、飞行试验是进行空气动力研究的三种手段。其中,飞行试验可以通过较低试验成本得到大量实际飞行数据,用以确定相关理论的可用性、精确度,并促使理论进一步发展。在开展飞行试验过程中,飞行器表面的流场变化规律是一项十分重要的研究内容。Numerical calculation, wind tunnel test and flight test are three methods of aerodynamic research. Among them, the flight test can obtain a large amount of actual flight data at a lower test cost to determine the availability and accuracy of the relevant theory, and to promote the further development of the theory. In the process of flight test, the change law of the flow field on the surface of the aircraft is a very important research content.

本文所述高速飞行特指飞行速度不低于5倍声速的飞行,已有的高速飞行试验流场测量方法,大多是在飞行器结构壁面布置大量的测温或测压传感器,通过对飞行过程中的传感器数据进行记录及分析,得到流场的变化规律。在这种情况下,飞行器结构壳体需对应加工大量传感器接口,生产难度大;由于传感器数量众多,产品装配难度大;受限于传感器的布置情况,流场显示往往不够直观,数据分析难度较大;无法得到小尺寸模型和弯曲薄翼面表面的流场分布。The high-speed flight mentioned in this paper specifically refers to the flight whose flight speed is not less than 5 times the speed of sound. Most of the existing high-speed flight test flow field measurement methods are to arrange a large number of temperature or pressure sensors on the wall of the aircraft structure. The sensor data is recorded and analyzed to obtain the change rule of the flow field. In this case, a large number of sensor interfaces need to be processed for the structural shell of the aircraft, and the production is difficult; due to the large number of sensors, the product assembly is difficult; limited by the arrangement of the sensors, the flow field display is often not intuitive, and the data analysis is more difficult. Large; the flow field distribution cannot be obtained for small size models and curved thin airfoil surfaces.

发明内容SUMMARY OF THE INVENTION

本发明解决的技术问题是:提出一种高速飞行试验流场测量系统,可同时满足生产及装配简单、测量结果直观、模型尺寸适应性强、测量方案简洁可靠等要求。The technical problem solved by the present invention is to propose a high-speed flight test flow field measurement system, which can simultaneously meet the requirements of simple production and assembly, intuitive measurement results, strong model size adaptability, and simple and reliable measurement scheme.

本发明解决技术的方案是:一种高速飞行试验流场测量系统,包括头舱、丝线、后舱、记录仪组件、相机盒组件、视频采集器;所述头舱为高速飞行试验的研究性舱段,丝线采用种植法或粘接法一端固定在头舱所关心区域,后舱用于安置固定单机设备并与前舱通过轴向螺钉连接,相机盒组件穿壁固定于后舱壁面上,用于拍摄丝线区域流场分布,视频采集器与记录仪固定在后舱内部,分别用于对拍摄的丝线区域流场影像进行数据采集及存储。The technical solution of the present invention is: a high-speed flight test flow field measurement system, including a head cabin, a wire, a rear cabin, a recorder assembly, a camera box assembly, and a video collector; the head cabin is for research purposes in high-speed flight tests In the cabin section, one end of the silk thread is fixed to the concerned area of the head cabin by planting method or bonding method. The rear cabin is used to place and fix stand-alone equipment and is connected with the front cabin through axial screws. The camera box assembly is fixed on the rear cabin wall through the wall. It is used to photograph the flow field distribution in the silk thread area. The video collector and the recorder are fixed inside the rear cabin, and are respectively used for data collection and storage of the captured silk thread area flow field images.

优选的,所述相机盒组件包括玻璃、相机盒主体、相机盒盖、相机保护壳、相机、线缆密封盖、耐高温缓冲垫A、耐高温缓冲垫B、限位片;耐高温缓冲垫A及耐高温缓冲垫B分布于玻璃两侧,通过限位片对三者进行限位并固定在相机盒主体上,相机与相机保护壳固定到位后作为整体安装到相机盒盖上,相机盒盖与相机盒主体连接,相机线缆连接到位后,将线缆密封盖安装在相机盒主体尾部,通过在缝隙处涂胶实现线缆的固定及密封。Preferably, the camera case assembly includes glass, a camera case body, a camera case cover, a camera protective case, a camera, a cable sealing cover, a high temperature resistant buffer pad A, a high temperature resistant buffer pad B, a limit piece; a high temperature resistant buffer pad A and high temperature resistant buffer pads B are distributed on both sides of the glass. The three are limited by the limit piece and fixed on the main body of the camera case. After the camera and the protective case of the camera are fixed in place, they are installed on the cover of the camera case as a whole. The cover is connected to the main body of the camera box. After the camera cable is connected in place, the cable sealing cover is installed on the tail of the main body of the camera box, and the cable is fixed and sealed by applying glue at the gap.

优选的,所述的相机盒主体上开设方孔,所述的玻璃截面为凸形,耐高温缓冲垫A为封闭方形框架结构,套装在所述凸形上,所述凸形结构上部与所述方孔匹配;耐高温缓冲垫B为U形框架,放置在所述凸形的下表面,限位片为U形结构,紧靠耐高温缓冲垫B安装在相机盒主体上。Preferably, a square hole is formed on the main body of the camera box, the cross section of the glass is convex, the high temperature resistant buffer pad A is a closed square frame structure, and is sleeved on the convex shape, and the upper part of the convex structure is connected to the The square holes are matched; the high temperature resistant buffer pad B is a U-shaped frame, placed on the lower surface of the convex shape, and the limiting piece is a U-shaped structure, which is installed on the camera box body close to the high temperature resistant buffer pad B.

优选的,玻璃四周与相机盒主体内壁面预留0.5mm间隙,间隙内涂满高温密封胶。Preferably, a gap of 0.5 mm is reserved around the glass and the inner wall of the main body of the camera box, and the gap is filled with high-temperature sealant.

优选的,相机盒组件与后舱外表面共形且二者外表面齐平,相机盒子组件四周无逆气流台阶,顺气流台阶不大于0.5mm。Preferably, the camera box assembly is conformal to the outer surface of the rear cabin and the outer surfaces of the two are flush, there is no reverse airflow step around the camera box assembly, and the downstream airflow step is not greater than 0.5mm.

优选的,所述的丝线区域光线入射方向与玻璃平面不垂直。Preferably, the incident direction of the light in the wire area is not perpendicular to the glass plane.

优选的,同一相机搭配多种规格镜头,根据公式

Figure BDA0002450486750000021
确定满足使用要求的焦距范围,进而确定相机镜头规格。Preferably, the same camera is matched with lenses of various specifications, according to the formula
Figure BDA0002450486750000021
Determine the focal length range that meets the usage requirements, and then determine the camera lens specifications.

优选的,所述的玻璃选用石英玻璃,耐温不低于1000℃,玻璃上下两面镀有憎水膜,玻璃的长度及宽度均不超过150mm,厚度不少于10mm。Preferably, the glass is made of quartz glass, the temperature resistance is not lower than 1000°C, the upper and lower sides of the glass are coated with a hydrophobic film, the length and width of the glass are not more than 150mm, and the thickness is not less than 10mm.

优选的,所述的丝线的直径0.1~1mm,丝线露出模型表面的长度为10~80mm,丝线孔间距10~80mm。Preferably, the diameter of the wire is 0.1-1 mm, the length of the wire exposed on the surface of the model is 10-80 mm, and the distance between the wire holes is 10-80 mm.

优选的,后舱半锥角不低于25°,后舱半锥角应大于头舱半锥角且两者之差不少于20°。Preferably, the half cone angle of the rear cabin is not less than 25°, and the half cone angle of the rear cabin should be greater than the half cone angle of the head cabin and the difference between the two is not less than 20°.

优选的,所述记录仪组件,包括共形卡箍、记录仪、连接板;连接板固定于后舱内壁面,记录仪放置在连接板上,共形卡箍与连接板连接到位后将记录仪可靠固定于两者之间。Preferably, the recorder assembly includes a conformal clamp, a recorder, and a connecting plate; the connecting plate is fixed on the inner wall of the rear cabin, the recorder is placed on the connecting plate, and the conformal clamp and the connecting plate are connected in place to record the The instrument is securely fixed between the two.

优选的,所述记录仪具有数据双冗余备份功能,单机外形包括球面及柱面,有效避免应力集中,通过共形卡箍固定在连接板上,可适应落地冲击等工作环境。Preferably, the recorder has a dual redundant data backup function, and the single-unit shape includes a spherical surface and a cylindrical surface, which can effectively avoid stress concentration, and is fixed on the connecting plate by a conformal clamp, which can adapt to the working environment such as landing impact.

本发明与现有技术相比的有益效果是:The beneficial effects of the present invention compared with the prior art are:

提出一种高速飞行试验流场测量系统,可同时满足生产及装配简单、测量结果直观、模型尺寸适应性强、测量方案简洁可靠等要求。A flow field measurement system for high-speed flight test is proposed, which can meet the requirements of simple production and assembly, intuitive measurement results, strong model size adaptability, and simple and reliable measurement scheme.

该高速飞行试验流场测量系统可得到小尺寸模型以及弯曲薄翼面流场分布 The high-speed flight test flow field measurement system can obtain a small size model and the flow field distribution of a curved thin airfoil .

该高速飞行试验流场测量系统组成简单,引入本系统后飞行器整体外形不受破坏,避免给其它系统带来新的问题。该系统具有多重热密封能力,安全性高。The high-speed flight test flow field measurement system is simple in composition, and the overall shape of the aircraft will not be damaged after the introduction of the system, so as to avoid bringing new problems to other systems. The system has multiple heat sealing capabilities for high safety.

该高速飞行试验流场测量系统适应能力强,工作范围广。该高速飞行试验流场测量系统在常温及不超过500℃高温工况下,均可稳定、可靠工作。该高速飞行试验流场测量系统在火箭各典型工况振动、冲击、过载环境下,均可稳定、可靠工作。The high-speed flight test flow field measurement system has strong adaptability and wide working range. The high-speed flight test flow field measurement system can work stably and reliably under normal temperature and high temperature conditions not exceeding 500 °C. The high-speed flight test flow field measurement system can work stably and reliably under the vibration, shock and overload environments of various typical rocket operating conditions.

该高速飞行试验流场测量的相机、玻璃、缓冲垫等均集成到相机盒组件中,装配简单,可靠。The camera, glass, buffer pad, etc. for the flow field measurement of the high-speed flight test are all integrated into the camera box assembly, and the assembly is simple and reliable.

附图说明Description of drawings

图1为本发明一种高速飞行试验流场测量系统组成示意图。FIG. 1 is a schematic diagram of the composition of a flow field measurement system for a high-speed flight test of the present invention.

图2为记录仪组件组成示意图。Figure 2 is a schematic diagram of the components of the recorder.

图3为本发明相机盒组件组成示意图。FIG. 3 is a schematic diagram of the composition of the camera box assembly of the present invention.

图4为本发明相机盒组件零件组成爆炸图。FIG. 4 is an exploded view of the components of the camera box assembly of the present invention.

图5为光线通过透光玻璃后折射情况示意图。FIG. 5 is a schematic diagram of the refraction of light after passing through the transparent glass.

图1中:1头舱、2丝线、3后舱、4记录仪组件、5相机盒组件、6视频采集器。In Figure 1: 1 head cabin, 2 silk cables, 3 rear cabins, 4 recorder components, 5 camera box components, 6 video collectors.

图2中:41共形卡箍、42记录仪、43连接板。In Figure 2: 41 conformal clamp, 42 recorder, 43 connecting plate.

图3及图4中:51玻璃、52相机盒主体、53相机盒盖、54相机保护壳、55相机、56线缆密封盖、57耐高温缓冲垫A、58耐高温缓冲垫B、59限位片。In Figure 3 and Figure 4: 51 glass, 52 camera case body, 53 camera case cover, 54 camera protective case, 55 camera, 56 cable sealing cover, 57 high temperature buffer pad A, 58 high temperature buffer pad B, 59 limit bit slice.

具体实施方式Detailed ways

下面结合实施例对本发明作进一步阐述。The present invention will be further elaborated below in conjunction with the examples.

下面将结合本发明实施例中的附图1-5,对本发明实施例中的技术方案进行清楚、完整地表述,显然,所描述的实施例仅仅是本发明一部分实施例,而不是全部的实施例。基于本发明中的实施例,本领域普通技术人员在没有做出创造性劳动前提下所获得的所有其他实施例,都属于本发明保护的范围。The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings 1-5 in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the implementations. example. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

请参阅图1,本发明提供一种技术方案:一种高速飞行试验流场测量系统,包括头舱1、丝线2、后舱3、记录仪组件4、相机盒组件5、视频采集器6,所述头舱为高速飞行试验的研究性舱段,丝线采用粘接法固定在头舱所关心区域,后舱用于安置固定单机设备并与前舱通过轴向螺钉连接,记录仪组件与视频采集器固定在后舱内部,相机盒组件穿壁固定于后舱壁面上。1, the present invention provides a technical solution: a high-speed flight test flow field measurement system, comprising a head cabin 1, a wire 2, a rear cabin 3, a recorder assembly 4, a camera box assembly 5, and a video collector 6, The head cabin is a research cabin for high-speed flight tests. The wire is fixed to the area of interest in the head cabin by bonding. The rear cabin is used to place and fix stand-alone equipment and is connected with the front cabin through axial screws. The recorder components and video The collector is fixed inside the rear cabin, and the camera box assembly is fixed on the wall surface of the rear cabin through the wall.

在飞行过程中,粘接在头舱上的丝线可实时显示所在区域的流场分布情况,相机对丝线区域流场显示情况进行拍摄,视频采集器将相机拍摄到的影像进行数据采集并存储至记录仪中,待飞行试验完成后,通过对记录仪进行回收得到所需的影像数据,进而得到飞行过程中丝线区域流场的变化规律。During the flight, the silk thread bonded to the head cabin can display the flow field distribution in the area in real time. The camera shoots the flow field display in the silk thread area, and the video collector collects and stores the data of the image captured by the camera in the In the recorder, after the flight test is completed, the required image data is obtained by recovering the recorder, and then the variation law of the flow field in the silk thread area during the flight is obtained.

如图2所示,本发明所包含的记录仪组件,包括共形卡箍41、记录仪42、连接板43,连接板固定于后舱内壁面,记录仪放置在连接板上,共形卡箍与连接板连接到位后可将记录仪可靠固定于两者之间。记录仪具有数据双冗余备份设计功能,单机外形主要为球面及柱面,有效避免应力集中,通过共形卡箍固定在连接板上,可适应落地冲击等工作环境。As shown in FIG. 2, the recorder assembly included in the present invention includes a conformal clamp 41, a recorder 42, and a connecting plate 43. The connecting plate is fixed on the inner wall of the rear cabin, the recorder is placed on the connecting plate, and the conformal clamp After the hoop and the connecting plate are connected in place, the recorder can be securely fixed between the two. The recorder has the function of dual redundant data backup design. The shape of the single machine is mainly spherical and cylindrical, which can effectively avoid stress concentration. It is fixed on the connecting plate by the conformal clamp, which can adapt to the working environment such as landing impact.

如图3所示,本发明所包含的相机盒组件,包括玻璃51、相机盒主体52、相机盒盖53、相机保护壳54、相机55、线缆密封盖56、耐高温缓冲垫A57、耐高温缓冲垫B58、限位片59,耐高温缓冲垫A及耐高温缓冲垫B分布于玻璃两侧,通过限位片对三者进行限位并固定在相机盒主体上,相机与相机保护壳固定到位后作为整体安装到相机盒盖上,相机盒盖与相机盒主体通过螺栓进行连接,相机线缆连接到位后,将线缆密封盖安装在相机盒主体尾部,通过在缝隙处涂胶实现线缆的固定及密封。As shown in FIG. 3 , the camera case assembly included in the present invention includes a glass 51 , a camera case body 52 , a camera case cover 53 , a camera protective case 54 , a camera 55 , a cable sealing cover 56 , a high temperature resistant buffer pad A57 , The high temperature buffer pad B58, the limit sheet 59, the high temperature resistant buffer pad A and the high temperature resistant buffer pad B are distributed on both sides of the glass, and the three are limited by the limit sheet and fixed on the main body of the camera case, the camera and the camera protective shell After being fixed in place, it is installed on the camera case cover as a whole. The camera case cover and the camera case body are connected by bolts. After the camera cable is connected in place, the cable sealing cover is installed at the end of the camera case body by applying glue at the gap. Cable fixing and sealing.

相机盒子组件需穿壁安装,基于热防护考虑,应保证其与后舱外表面保持齐平,相机盒子组件四周无逆气流台阶,顺气流台阶不大于0.5mm。The camera box assembly needs to be installed through the wall. Based on thermal protection considerations, it should be kept flush with the outer surface of the rear cabin. There is no reverse airflow step around the camera box assembly, and the downstream airflow step is not greater than 0.5mm.

丝线区域光线入射方向与玻璃平面不垂直,在布置相机位置时,需对光路折射情况计算,得到光线经过玻璃折射后偏移距离。图5中i为入射角,r为出射角,n为折射率,玻璃厚度为a,n=sin i/sinr,r=arcsin(sin i/n),可以求得光线经过玻璃折射后的偏移距离

Figure BDA0002450486750000051
将玻璃折射率及具体工况的入射角代入,可求得光线偏移距离。The incident direction of the light in the silk line area is not perpendicular to the glass plane. When arranging the camera position, it is necessary to calculate the refraction of the optical path to obtain the offset distance of the light after refraction by the glass. In Figure 5, i is the incident angle, r is the exit angle, n is the refractive index, and the glass thickness is a, n=sin i/sinr, r=arcsin(sin i/n), the polarization of the light after being refracted by the glass can be obtained. move distance
Figure BDA0002450486750000051
By substituting the refractive index of the glass and the incident angle of the specific working conditions, the light offset distance can be obtained.

同一相机可搭配多种规格镜头,根据公式

Figure BDA0002450486750000052
可确定满足使用要求的焦距范围,进而确定相机镜头规格。The same camera can be matched with lenses of various specifications, according to the formula
Figure BDA0002450486750000052
The focal length range that meets the usage requirements can be determined, and then the camera lens specifications can be determined.

流场测量系统工作时,应保证试飞器丝线区域光线充裕。When the flow field measurement system is working, it should be ensured that the wire area of the test vehicle is well lit.

玻璃两侧布置有耐高温缓冲垫,玻璃四周与相机盒子内壁面预留与0.5mm间隙,该间隙涂满高温密封胶,以上措施可提高玻璃振动及冲击环境的适应能力。所用耐高温缓冲垫A及耐高温缓冲垫B可以耐受500℃以上温度而不变质、不分解。High temperature resistant buffers are arranged on both sides of the glass, and a 0.5mm gap is reserved around the glass and the inner wall of the camera box. The gap is filled with high temperature sealant. The above measures can improve the adaptability of the glass to vibration and shock environments. The high temperature resistant buffer pad A and the high temperature resistant buffer pad B used can withstand temperatures above 500°C without deterioration or decomposition.

相机盒本体机械接口与后舱连接处布置有减振垫,相机盒本体侧壁与后舱开孔之间设计有0.5mm间隙,该间隙涂满高温密封胶,可防止热气流直接窜入,并提高产品振动及冲击环境的适应能力。A vibration damping pad is arranged at the connection between the mechanical interface of the camera box body and the rear compartment, and a 0.5mm gap is designed between the side wall of the camera box body and the opening of the rear compartment. And improve the adaptability of products to vibration and shock environments.

相机盒本体尾部的线缆密封盖主要用于实现相机线缆处的密封,线缆与密封盖开孔之间存在间隙,该间隙涂满高温密封胶,通过这项措施,在玻璃损坏导致外部热气流进入盒子内部时,不会进一步进入到后舱内部,提高了相机盒组件热密封的可靠性。The cable sealing cover at the rear of the camera box body is mainly used to seal the camera cable. There is a gap between the cable and the opening of the sealing cover. The gap is filled with high-temperature sealant. When the hot air enters the inside of the box, it will not further enter the inside of the rear compartment, which improves the reliability of the thermal sealing of the camera box assembly.

透光玻璃选用石英玻璃,耐温不低于1000℃,具有极低的热膨胀系数,高的耐热形,极好的化学稳定性,优良的电绝缘性,低而稳定的超声延迟性能,最佳的透紫外光谱性能以及透可见光及近红外光谱性能,并有着高于普通玻璃的机械性能,玻璃上下两面镀有憎水膜。玻璃的长度及宽度均不超过150mm,厚度不少于10mm。The light-transmitting glass is made of quartz glass, the temperature resistance is not lower than 1000 ° C, it has a very low thermal expansion coefficient, high heat resistance, excellent chemical stability, excellent electrical insulation, low and stable ultrasonic delay performance, the most It has excellent UV-transmitting spectral performance, visible light and near-infrared spectral performance, and has mechanical properties higher than ordinary glass. The upper and lower sides of the glass are coated with a hydrophobic film. The length and width of the glass shall not exceed 150mm, and the thickness shall not be less than 10mm.

丝线可使用种植法或粘接法固定,根据实际使用工况情况确定。所选丝线柔软轻质,可以耐受500K以上温度而不变质。丝线的直径0.1~1mm,丝线露出模型表面的长度为10~80mm,丝线孔间距10~80mm。The silk thread can be fixed by the planting method or the bonding method, which is determined according to the actual working conditions. The selected silk thread is soft and lightweight, and can withstand temperatures above 500K without deterioration. The diameter of the silk thread is 0.1-1 mm, the length of the silk thread exposing the surface of the model is 10-80 mm, and the distance between the thread holes is 10-80 mm.

后舱半锥角不低于25°,后舱半锥角应大于头舱半锥角且两者之差不少于20°,以避免视野不足导致图像无法识别。The half cone angle of the rear cabin should not be less than 25°, and the half cone angle of the rear cabin should be greater than the half cone angle of the head cabin, and the difference between the two should not be less than 20°, so as to avoid the lack of vision and the unrecognizable image.

综上所述,给出一优选实施例中,丝线为石英纤维线,柔软轻质,可以耐受1000℃温度而不变质。丝线的直径0.8mm,丝线露出模型表面的长度为40mm,丝线孔间距40mm。相机盒组件与后舱外表面打磨共形,四周均无台阶。后舱半锥角25°,头舱半锥角5°。所选耐高温缓冲垫A及耐高温缓冲垫B采用Dq441J-108高温胶定制,相机组件各间隙处所涂高温密封胶均选用Dq441J-108高温胶,可以耐受500℃温度而不变质。透光玻璃选用石英玻璃,牌号为JGS1,耐温1200℃,玻璃长、宽均为130mm,厚度为15mm。测量系统入射光线入射角约70°,玻璃折射率1.7,光线偏移约10.7mm,相机位置对应调整。To sum up, in a preferred embodiment, the silk thread is a quartz fiber thread, which is soft and lightweight, and can withstand a temperature of 1000°C without deterioration. The diameter of the wire is 0.8mm, the length of the wire exposed on the surface of the model is 40mm, and the distance between the wire holes is 40mm. The camera box assembly is conformal to the outer surface of the rear cabin, and there are no steps around it. The half cone angle of the rear cabin is 25°, and the half cone angle of the head cabin is 5°. The selected high temperature buffer pad A and high temperature buffer pad B are customized with Dq441J-108 high temperature glue, and the high temperature sealant applied to each gap of the camera components is Dq441J-108 high temperature glue, which can withstand the temperature of 500 ℃ without deterioration. The light-transmitting glass is made of quartz glass, the grade is JGS1, the temperature resistance is 1200°C, the length and width of the glass are 130mm, and the thickness is 15mm. The incident angle of the incident light of the measuring system is about 70°, the refractive index of the glass is 1.7, the light deviation is about 10.7mm, and the camera position is adjusted accordingly.

尽管已经示出和描述了本发明的实施例,对于本领域的普通技术人员而言,可以理解在不脱离本发明的原理和精神的情况下可以对这些实施例进行多种变化、修改、替换和变型,本发明的范围由所附权利要求及等同物限定。Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, and substitutions can be made in these embodiments without departing from the principle and spirit of the invention and modifications, the scope of the invention is defined by the appended claims and their equivalents.

Claims (12)

1.一种高速飞行试验流场测量系统,其特征在于:包括头舱、丝线、后舱、记录仪组件、相机盒组件、视频采集器;所述头舱为高速飞行试验的研究性舱段,丝线采用种植法或粘接法一端固定在头舱所关心区域,后舱用于安置固定单机设备并与前舱通过轴向螺钉连接,相机盒组件穿壁固定于后舱壁面上,用于拍摄丝线区域流场分布,视频采集器与记录仪固定在后舱内部,分别用于对拍摄的丝线区域流场影像进行数据采集及存储。1. a high-speed flight test flow field measurement system, is characterized in that: comprise head cabin, silk thread, rear cabin, recorder assembly, camera box assembly, video collector; Described head cabin is the research cabin section of high-speed flight test , One end of the silk thread is fixed to the area of interest in the head cabin by planting method or bonding method. The rear cabin is used to place and fix stand-alone equipment and is connected with the front cabin by axial screws. The camera box assembly is fixed on the rear cabin wall through the wall. To shoot the flow field distribution in the silk thread area, the video collector and the recorder are fixed inside the rear cabin, and are used for data collection and storage of the captured silk thread area flow field images respectively. 2.根据权利要求1所述的系统,其特征在于:所述相机盒组件包括玻璃、相机盒主体、相机盒盖、相机保护壳、相机、线缆密封盖、耐高温缓冲垫A、耐高温缓冲垫B、限位片;耐高温缓冲垫A及耐高温缓冲垫B分布于玻璃两侧,通过限位片对三者进行限位并固定在相机盒主体上,相机与相机保护壳固定到位后作为整体安装到相机盒盖上,相机盒盖与相机盒主体连接,相机线缆连接到位后,将线缆密封盖安装在相机盒主体尾部,通过在缝隙处涂胶实现线缆的固定及密封。2. The system according to claim 1, wherein the camera case assembly comprises glass, a camera case body, a camera case cover, a camera protective case, a camera, a cable sealing cover, a high temperature resistant cushion A, a high temperature resistant cushion Buffer pad B, limit sheet; high temperature resistant buffer pad A and high temperature resistant buffer pad B are distributed on both sides of the glass, the three are limited by the limit sheet and fixed on the main body of the camera box, the camera and the camera protective shell are fixed in place Then, it is installed on the camera case cover as a whole. The camera case cover is connected to the camera case body. After the camera cable is connected in place, the cable sealing cover is installed at the end of the camera case body. seal. 3.根据权利要求2所述的系统,其特征在于:所述的相机盒主体上开设方孔,所述的玻璃截面为凸形,耐高温缓冲垫A为封闭方形框架结构,套装在所述凸形上,所述凸形结构上部与所述方孔匹配;耐高温缓冲垫B为U形框架,放置在所述凸形的下表面,限位片为U形结构,紧靠耐高温缓冲垫B安装在相机盒主体上。3. The system according to claim 2, wherein a square hole is formed on the main body of the camera box, the cross section of the glass is convex, and the high temperature resistant buffer pad A is a closed square frame structure, which is sleeved on the On the convex shape, the upper part of the convex structure matches the square hole; the high temperature resistant buffer pad B is a U-shaped frame, which is placed on the lower surface of the convex shape, and the limit piece is a U-shaped structure, which is close to the high temperature resistant buffer Pad B is attached to the camera case body. 4.根据权利要求3所述的系统,其特征在于:玻璃四周与相机盒主体内壁面预留0.5mm间隙,间隙内涂满高温密封胶。4 . The system according to claim 3 , wherein a gap of 0.5 mm is reserved around the glass and the inner wall of the camera box body, and the gap is filled with high-temperature sealant. 5 . 5.根据权利要求1所述的系统,其特征在于:相机盒组件与后舱外表面共形且二者外表面齐平,相机盒子组件四周无逆气流台阶,顺气流台阶不大于0.5mm。5 . The system according to claim 1 , wherein the camera box assembly is conformal to the outer surface of the rear cabin and the outer surfaces of the two are flush, there is no reverse airflow step around the camera box assembly, and the downstream airflow step is not greater than 0.5mm. 6.根据权利要求2所述的系统,其特征在于:所述的丝线区域光线入射方向与玻璃平面不垂直。6. The system according to claim 2, wherein the incident direction of the light in the wire area is not perpendicular to the glass plane. 7.根据权利要求2所述的系统,其特征在于:同一相机搭配多种规格镜头,根据公式
Figure FDA0002450486740000021
确定满足使用要求的焦距范围,进而确定相机镜头规格。
7. The system according to claim 2, wherein: the same camera is matched with lenses of various specifications, according to the formula
Figure FDA0002450486740000021
Determine the focal length range that meets the usage requirements, and then determine the camera lens specifications.
8.根据权利要求2所述的系统,其特征在于:所述的玻璃选用石英玻璃,耐温不低于1000℃,玻璃上下两面镀有憎水膜,玻璃的长度及宽度均不超过150mm,厚度不少于10mm。8. The system according to claim 2, characterized in that: the glass is selected from quartz glass, the temperature resistance is not lower than 1000 ℃, the upper and lower sides of the glass are coated with a hydrophobic film, and the length and width of the glass are not more than 150mm, The thickness is not less than 10mm. 9.根据权利要求1所述的系统,其特征在于:所述的丝线的直径0.1~1mm,丝线露出模型表面的长度为10~80mm,丝线孔间距10~80mm。9 . The system according to claim 1 , wherein the diameter of the wire is 0.1-1 mm, the length of the wire exposed on the surface of the model is 10-80 mm, and the distance between the wire holes is 10-80 mm. 10 . 10.根据权利要求1所述的系统,其特征在于:后舱半锥角不低于25°,后舱半锥角应大于头舱半锥角且两者之差不少于20°。10. The system according to claim 1, wherein the half cone angle of the rear cabin is not less than 25°, the half cone angle of the rear cabin should be greater than the half cone angle of the head cabin and the difference between the two is not less than 20°. 11.根据权利要求1所述的系统,其特征在于:所述记录仪组件,包括共形卡箍、记录仪、连接板;连接板固定于后舱内壁面,记录仪放置在连接板上,共形卡箍与连接板连接到位后将记录仪可靠固定于两者之间。11. The system according to claim 1, wherein: the recorder assembly comprises a conformal clamp, a recorder, and a connecting plate; the connecting plate is fixed on the inner wall of the rear cabin, and the recorder is placed on the connecting plate, After the conformal clamp and the connecting plate are connected in place, the recorder is reliably fixed between them. 12.根据权利要求11所述的系统,其特征在于:所述记录仪具有数据双冗余备份功能,单机外形包括球面及柱面。12 . The system according to claim 11 , wherein the recorder has a dual redundant data backup function, and the single-machine shape includes a spherical surface and a cylindrical surface. 13 .
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Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104408703A (en) * 2014-11-28 2015-03-11 中国航空工业空气动力研究院 Wind tunnel dynamic test piece optical flow visualization system and image phase averaging method thereof
CN106017847A (en) * 2016-05-11 2016-10-12 上海工程技术大学 Observation system and method for aerodynamic force test and flapping wing flow field of flapping-wing micro air vehicle
CN107676776A (en) * 2017-11-14 2018-02-09 山东耀华特耐科技有限公司 A kind of high temperature resistant fault detection system of boiler hearth of circulating fluidized bed
CN108398229A (en) * 2017-12-27 2018-08-14 中国航天空气动力技术研究院 A kind of aircraft three-dimensional surface flow distribution wind-tunnel measurements method
CN208273081U (en) * 2018-01-16 2018-12-21 深圳市百康兴电子科技有限公司 A kind of complete full HD camera module of glass high temperature resistant Anti- tarnishing of 4G

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104408703A (en) * 2014-11-28 2015-03-11 中国航空工业空气动力研究院 Wind tunnel dynamic test piece optical flow visualization system and image phase averaging method thereof
CN106017847A (en) * 2016-05-11 2016-10-12 上海工程技术大学 Observation system and method for aerodynamic force test and flapping wing flow field of flapping-wing micro air vehicle
CN107676776A (en) * 2017-11-14 2018-02-09 山东耀华特耐科技有限公司 A kind of high temperature resistant fault detection system of boiler hearth of circulating fluidized bed
CN108398229A (en) * 2017-12-27 2018-08-14 中国航天空气动力技术研究院 A kind of aircraft three-dimensional surface flow distribution wind-tunnel measurements method
CN208273081U (en) * 2018-01-16 2018-12-21 深圳市百康兴电子科技有限公司 A kind of complete full HD camera module of glass high temperature resistant Anti- tarnishing of 4G

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
张甲奇等: "等离子体流动控制模型自由飞试验技术", 《飞行力学》 *

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