A hypersonic aerodynamic optical effect wind tunnel experiment timing coordination system

Abstract

The application discloses a hypersonic aerodynamic optical effect wind tunnel experiment timing coordination system, which comprises a wind tunnel, an experiment section of the wind tunnel is used for forming a hypersonic flow field; an imaging system is installed in an experiment model of the wind tunnel and is used for shooting an imaging target after receiving a trigger signal; a sensor assembly is used for detecting a state of establishment of the hypersonic flow field in the experiment section and is fused when the hypersonic flow field in the experiment section is established; and a trigger circuit is electrically connected with the sensor assembly and the imaging system. The sensor circuit is fused, the sensor assembly is arranged in the flow field in the experiment section of the wind tunnel, the sensor assembly is electrically connected with the imaging system through the trigger circuit, the fuse wire in the sensor assembly is fused by high-temperature and high-pressure gas when the hypersonic flow field is formed in the experiment section, the trigger circuit directly outputs a trigger signal to the imaging system, the imaging system immediately collects an image, and the response speed and the accuracy of the timing system control are improved.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of hypersonic technology, and in particular to a hypersonic aerodynamic-optical effect wind tunnel experiment timing coordination system. BACKGROUND

[0002] The aerodynamic-optical effect will cause the image of the imaging target to shift, jitter and blur, and is a key factor affecting the hypersonic dynamic imaging. It is a factor that must be considered in the design of imaging systems such as hypersonic kinetic energy interception, starlight navigation and reconnaissance. Under hypersonic flight conditions, the flow field is accompanied by dissociation, ionization and complex thermo-chemical reactions, making it difficult to accurately numerically predict the aerodynamic-optical effect. Wind tunnel experiments are still the main means for studying the hypersonic aerodynamic-optical effect.

[0003] Achieving hypersonic flight conditions in a wind tunnel requires extremely high driving energy for the wind tunnel, so the wind tunnel is a pulse type wind tunnel, and the effective experiment time is short. The effective time of a domestic and foreign hypersonic wind tunnel at Mach 9 or above is not more than forty milliseconds. The imaging frame frequency of a hypersonic weapon is low, and only one frame of image can be collected within the effective experiment time for examining the performance of the imaging system in the wind tunnel, which puts extremely high requirements on the timing coordination between the wind tunnel operation and the imaging system. In order to realize timing coordination, a trigger signal needs to be output to the imaging system when the hypersonic flow field is established. However, in order to avoid the direct impact of the hypersonic airflow on the pressure sensor, the wind tunnel adopts a flow-around structure to protect the sensor, resulting in a long response time of the pressure sensor and low accuracy in capturing the time when the flow field is established. When a thermocouple sensor is used, its sensitivity is low, the signal amplitude is small, and it is easily affected by electromagnetic interference signals, which can easily cause false triggering.

[0004] Therefore, the timing coordination precision is low when the existing pressure and heat flow sensors are used for timing coordination, and it is difficult to carry out hypersonic aerodynamic-optical effect wind tunnel experiments, which seriously restricts the design of imaging systems such as hypersonic kinetic energy interception, starlight navigation and reconnaissance. SUMMARY

[0005] The purpose of the present application is to provide a hypersonic aerodynamic-optical effect wind tunnel experiment timing coordination system to solve the problem that the existing pressure sensor and thermocouple sensor are difficult to respond quickly, resulting in low precision of timing coordination control and difficulty in carrying out hypersonic aerodynamic-optical effect wind tunnel experiments.

[0006] To solve the above technical problems, the present application specifically provides the following technical solutions:

[0007] A hypersonic aerodynamic-optical effect wind tunnel experiment timing coordination system, comprising:

[0008] A wind tunnel, comprising an experiment section, the experiment section being used to form a hypersonic flow field;

[0009] An imaging system, which is an imaging load in the aerodynamic optical effect wind tunnel experiment, is installed in the inside of the wind tunnel experiment model, and after receiving a trigger signal, photographs the imaging target, and determines the influence of the aerodynamic optical effect through the analysis of the photographed image;

[0010] A sensor assembly is arranged in the experiment section, and is used for detecting the establishment state of the hypersonic flow field of the experiment section, and when the hypersonic flow field of the experiment section is established, the internal fuse wire of the sensor assembly is fused;

[0011] A trigger circuit is arranged in the inside of the sensor assembly;

[0012] The trigger circuit is electrically connected with the sensor assembly and the imaging system, so as to establish the timing cooperative control of the wind tunnel operation and the imaging system;

[0013] When the fuse wire in the inside of the sensor assembly is fused at the moment, the trigger circuit outputs a trigger signal to the imaging system, and at the same time, the imaging system receives the trigger signal to start photographing the image.

[0014] As a preferred scheme of the present application, the sensor assembly comprises a sensing head, a supporting horizontal rod and a supporting vertical rod, the sensing head is installed at the front end of the supporting horizontal rod and faces the flow field direction, and the supporting horizontal rod is vertically installed on the supporting vertical rod;

[0015] The front end of the sensing head has a through hole, the through hole penetrates to the inside of the sensing head, a fuse wire is arranged in the inside of the sensing head, the fuse wire is arranged close to the inner port of the through hole, and the trigger circuit is electrically connected with both ends of the fuse wire;

[0016] The flow field forms a stagnation point area at the sensing head to generate high-temperature and high-pressure airflow, and the fuse wire is washed through the through hole, so that the fuse wire is fused when the hypersonic flow field is established.

[0017] As a preferred scheme of the present application, the sensing head comprises a protective cap, the protective cap is a spherical top cylindrical shape, and the through hole is located at the spherical top of the protective cap;

[0018] The cylindrical segment of the protective cap is a hollow structure, the cylindrical segment of the protective cap has a threaded hole at the end, and a connecting screw rod is installed through the threaded hole, and the connecting screw rod is threadedly installed at the front end of the supporting horizontal rod;

[0019] The connecting screw rod has two screw holes, two connecting electrodes are respectively threadedly installed through the screw holes, one end of the two connecting electrodes is located in the protective cap and respectively contacts both ends of the fuse wire, and the other end of the two connecting electrodes is located outside the protective cap, so that after the connecting screw rod is installed on the supporting horizontal rod, the other end of the connecting electrode is arranged in the supporting horizontal rod.

[0020] The support crossbar has a hole for arranging a wire to electrically connect the connecting electrode and the trigger circuit.

[0021] As a preferred scheme of the present application, the end of the connecting electrode in the protective cap is provided with a threaded hole, and a locking screw is arranged in the threaded hole to press the two ends of the fuse wire against the connecting electrode.

[0022] As a preferred scheme of the present application, the support vertical rod has a horizontal section in the shape of a right triangle, and the edge between the two vertical surfaces of the support vertical rod is opposite to the flow direction.

[0023] As a preferred scheme of the present application, the trigger circuit comprises a resistor R1 and a resistor R2, and the resistor R1 and the resistor R2 are connected in series.

[0024] The two ends of the fuse wire are connected in parallel to the two ends of the resistor R2, the two ends of the fuse wire are electrically connected to the output end of the imaging system, and the non-series ends of the resistor R1 and the resistor R2 are connected to the positive and negative poles of a power supply to form an input end.

[0025] When the fuse wire is not fused, the fuse wire is short-circuited, and the voltage of the output end is 0V, or when the fuse wire is fused, the fuse wire is open-circuited, and the voltage of the output end is the voltage output by the resistor R2, so as to trigger the imaging system to work.

[0026] Compared with the prior art, the present application has the following beneficial effects:

[0027] The present application adopts the fuse wire breaking mode of the sensor circuit, and the sensor assembly is arranged in the flow field of the experimental section of the wind tunnel, and the sensor assembly is electrically connected to the imaging system through the trigger circuit, so that when the high-speed flow field is formed in the experimental section, the fuse wire in the sensor assembly is broken by the high-temperature and high-pressure airflow, the trigger circuit directly outputs a trigger signal to the imaging system, the imaging system immediately collects an image, and the response speed and accuracy of the time sequence system control are improved. BRIEF DESCRIPTION OF DRAWINGS

[0028] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings needed in the following embodiment or prior art description will be briefly introduced. Obviously, the drawings in the following description are only exemplary, and other drawings can be obtained by the provided drawings without creative labor for those skilled in the art.

[0029] Figure 1This is a schematic diagram of the composition of the timing coordination system for hypersonic aero-optical effects wind tunnel experiments provided in an embodiment of the present invention;

[0030] Figure 2 A schematic diagram of the sensor component structure of the hypersonic aero-optical effect wind tunnel experimental timing coordination system provided in an embodiment of the present invention;

[0031] Figure 3 A schematic diagram of the sensor head portion of the timing coordination system for hypersonic aero-optical effects wind tunnel experiments provided in an embodiment of the present invention;

[0032] Figure 4 A schematic diagram of the supporting column structure of the wind tunnel experimental timing coordination system for hypersonic aero-optical effects provided in an embodiment of the present invention;

[0033] Figure 5 A circuit diagram of the triggering circuit of the timing coordination system for the hypersonic aero-optical effect wind tunnel experiment provided in an embodiment of the present invention.

[0034] The labels in the diagram represent the following:

[0035] 1-Sensor head; 2-Support crossbar; 3-Support upright;

[0036] 11-Protective cap; 12-Connecting screw; 13-Connecting electrode; 14-Locking screw; 15-Fuse; 16-Through hole. Detailed Implementation

[0037] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0038] like Figure 1 As shown, this invention provides a timing coordination system for hypersonic aero-optical effects wind tunnel experiments, comprising:

[0039] A wind tunnel, which includes an experimental section, is used to create hypersonic flow fields;

[0040] The imaging system is an imaging payload in the wind tunnel experiment of aero-optical effects. It is installed inside the wind tunnel experimental model, receives a trigger signal, and then captures images of the target. The influence of aero-optical effects is determined by analyzing the captured images.

[0041] The sensor assembly, located in the experimental section, is used to detect the establishment status of the hypersonic flow field in the experimental section, and its internal fuse melts when the hypersonic flow field is established in the experimental section.

[0042] A trigger circuit is arranged inside the sensor assembly;

[0043] The trigger circuit is electrically connected to the sensor assembly and the imaging system to establish timing coordination control of the wind tunnel operation and the imaging system;

[0044] When the fuse inside the sensor assembly is blown, the trigger circuit outputs a trigger signal to the imaging system, and at the same time, the imaging system receives the trigger signal to start shooting images.

[0045] The timing coordination system of the wind tunnel experiment mainly arranges the sensor assembly in the experimental section of the wind tunnel, so that it is in the flow field, and establishes the connection between the imaging system and the sensor assembly through the trigger circuit, so that when the experimental section of the wind tunnel forms a hypersonic flow field, the fuse inside the sensor assembly is blown to form an open circuit, and then the trigger circuit outputs a trigger signal to the imaging system, and the imaging system receives the trigger signal to start shooting images, so as to achieve timing coordination control.

[0046] Since the trigger signal is triggered by the open circuit of the trigger circuit, after the sensor assembly is opened, the trigger circuit changes in voltage, and the imaging system can directly collect images according to the voltage mutation, without the need for complex data processing, so that the response speed is faster and the timing coordination control accuracy is higher.

[0047] Compared with the timing coordination control composed of a pressure sensor, the present application adopts the way of sensor circuit blowing, arranges the sensor assembly in the flow field of the experimental section of the wind tunnel, and electrically connects the sensor assembly to the imaging system through the trigger circuit, so that when the experimental section forms a hypersonic flow field, the fuse inside the sensor assembly is blown by the high-temperature and high-pressure airflow, and then the trigger circuit directly outputs a trigger signal to the imaging system, so that the imaging system immediately collects images, thereby improving the response speed and accuracy of the timing system control.

[0048] Based on the above embodiment, a preferred embodiment of the sensor assembly is provided.

[0049] As shown in Figure 2 , Figure 3 The sensor assembly includes a sensing head 1, a supporting horizontal rod 2 and a supporting vertical rod 3, the sensing head 1 is installed at the front end of the supporting horizontal rod 2 and faces the flow field direction, and the supporting horizontal rod 2 is vertically installed on the supporting vertical rod 3;

[0050] The front end of the sensing head 1 has a through hole 16, the through hole 16 penetrates to the inside of the sensing head 1, a fuse 15 is arranged in the inside of the sensing head 1, the fuse 15 is arranged close to the inner port of the through hole 16, and the trigger circuit is electrically connected to both ends of the fuse 15;

[0051] The flow field forms a stagnation point region at the sensing head 1 to generate high-temperature and high-pressure airflow, and the airflow flushes the fuse wire 15 through the through hole 16, so that the fuse wire 15 is melted when the hypersonic flow field is established.

[0052] In the embodiment, the fuse wire 15 is arranged in the sensing head 1 and abuts against the through hole 16 by arranging the through hole 16 at the front end of the sensing head 1 to communicate the inside and outside of the sensing head 1, the flow field forms a stagnation point region at the sensing head 1 to generate high-temperature and high-pressure airflow, and the high-temperature and high-pressure airflow melts the fuse wire 15 when the hypersonic flow field is formed, so that the trigger circuit outputs a trigger signal (the high-temperature and high-pressure airflow formed at the front end of the sensing head 1 enters the inside of the sensing head 1 along the through hole 16 to flush the fuse wire 15, and the fuse wire 15 is quickly melted at a temperature of several thousand K under the hypersonic condition).

[0053] In order to improve the melting speed and shorten the melting time to improve the response speed and accuracy of the timing coordination control, the following preferred embodiments are provided.

[0054] As shown in Figure 3 , the sensing head 1 comprises a protective cap 11, the protective cap 11 is a spherical top cylindrical shape, and the through hole 16 is formed at the spherical top of the protective cap 11;

[0055] The cylindrical segment of the protective cap 11 is a hollow structure, has a threaded hole at the end of the cylindrical segment of the protective cap 11, and a connecting screw 12 is installed through the threaded hole, and the connecting screw 12 is threadedly installed at the front end of the support cross bar 2;

[0056] The connecting screw 12 has two screw holes, two connecting electrodes 13 are respectively threadedly installed through the screw holes of the connecting screw 12, one end of the two connecting electrodes 13 is located in the protective cap 11 and respectively abuts against two ends of the fuse wire 15, and the other end of the two connecting electrodes 13 is located outside the protective cap 11, so that the end of the connecting electrode 13 is arranged in the support cross bar 2 after the connecting screw 12 is installed on the support cross bar 2;

[0057] The support cross bar 2 has a channel for arranging a line to electrically connect the connecting electrode and the trigger circuit through a lead wire.

[0058] In the embodiment, the protective cap 11 of the sensing head 1 is a spherical top cylindrical shape made of stainless steel, the spherical top is directly opposite to the flow field direction, and the through hole 16 is located at the spherical top of the protective cap 11, so that the airflow can form a stagnation point region at the spherical top. The smaller the radius of the spherical top is, the higher the heat flow density of the stagnation point region is, and the shorter the breaking time of the fuse wire is. However, the radius of the spherical top is too small, which will result in small installation space in the protective cap 11 and is not conducive to installation. After comprehensive consideration, the diameter of the spherical top is 15 mm.

[0059] The connecting screw 12 is made of nylon, which has the functions of insulation and support connection, and is used to connect the protective cap 11 and the support horizontal rod 2. The connecting electrode 13 is made of copper, which has the function of a wire, and can be regarded as a wire in series after being connected with the fuse 15.

[0060] The fuse 15 is melted under the action of airflow and cooperates with the trigger circuit to output a trigger signal. The fuse 15 is made of a soldering tin wire with a diameter of 0.5 mm, which has a low melting point and a soft texture and is easy to melt.

[0061] Of course, in order to firmly connect the connecting electrode 13 with the fuse 15, as shown in the figure, the end of the connecting electrode 13 located in the protective cap 11 is provided with a screw hole, and the connecting electrode 13 is provided with a locking screw 14 through the screw hole, which is used to press the two ends of the fuse 15 on the connecting electrode 13. Figure 3

[0062] In the embodiment, the fuse 15 is pressed on the end of the connecting electrode 13 by the locking screw 14, which effectively avoids displacement caused by airflow scouring and ensures that the fuse 15 is melted in time.

[0063] Of course, in order to reduce the influence of the sensor assembly on the flow field, as shown in the figures, the horizontal section of the support vertical rod 3 is a right triangle, and the edge between the two vertical surfaces of the support vertical rod 3 is opposite to the flow field direction. Figure 2 Figure 4 The support vertical rod 3 is made of stainless steel, and its section is a right triangle, and the two right angles are located on the windward surface to reduce the influence on the flow field.

[0064] Based on the above embodiment, the following provides a preferred embodiment of a trigger circuit.

[0065] As shown in the figure, the trigger circuit includes a resistor R1 and a resistor R2, and the resistor R1 and the resistor R2 are connected in series.

[0066] The two ends of the resistor R2 are connected in parallel with the two ends of the fuse 15, and the two ends of the fuse 15 are electrically connected to form an output end of the imaging system, and the non-series ends of the resistor R1 and the resistor R2 are connected to form an input end of the power supply positive and negative poles. Figure 5

[0067] When the fuse 15 is not melted, the fuse 15 is short-circuited, and the voltage of the output end is 0V, or when the fuse 15 is melted, the fuse 15 is open-circuited, and the voltage of the output end is the voltage output by the resistor R2, so as to trigger the imaging system to work.

[0068]

[0069] ​​​​In the embodiment, the resistors R1 and R2 are connected in series, wherein R1=1kΩ and R2=4kΩ, and a 5V DC power supply is used. Before the experiment, the fuse 15 is connected to the connecting electrode 13, and the connecting electrode 13 is connected to the power supply through a wire arranged in the support crossbar 2 Figure 4 The middle potential points 1 and 2 are connected, and R3 represents the fuse 15, wherein V+ and V- constitute a trigger signal output end. Since the fuse 15 has a very small resistance value, when the fuse 15 is not broken, it functions as a short circuit, and the potential difference of the trigger signal output end is 0V. When the hypersonic flow field is formed, the fuse 15 will be broken under the action of the airflow, and the potential difference between the trigger signal output ends is output as 4V after being divided by the resistors R1 and R2, so as to trigger the imaging system, and realize the time sequence cooperation between the imaging system and the wind tunnel flow field.

[0070] The above embodiments are only exemplary embodiments of the present application, and are not used to limit the present application, and the protection scope of the present application is defined by the claims. Those skilled in the art can make various modifications or equivalent replacements to the present application within the spirit and protection scope of the present application, and such modifications or equivalent replacements are also regarded as falling within the protection scope of the present application.

Claims

1. A hypersonic aerodynamic optical effect wind tunnel experiment timing coordination system, characterized in that, The application relates to a time sequence coordination system for a hypersonic aerodynamic optical effect wind tunnel experiment. The system comprises: a wind tunnel including an experiment section for forming a hypersonic flow field; an imaging system for an imaging load in the aerodynamic optical effect wind tunnel experiment, which is installed in the interior of an experiment model of the wind tunnel, takes images of an imaging target after receiving a trigger signal, and determines the influence of the aerodynamic optical effect through analysis of the taken images; a sensor assembly arranged in the experiment section for detecting the establishment state of the hypersonic flow field in the experiment section, and melting a fuse wire in the interior of the sensor assembly when the hypersonic flow field in the experiment section is established; and a trigger circuit arranged in the interior of the sensor assembly. The trigger circuit is electrically connected with the sensor assembly and the imaging system to establish time sequence coordination control of the wind tunnel operation and the imaging system. When the fuse wire in the interior of the sensor assembly is melted, the trigger circuit outputs a trigger signal to the imaging system, and at the same time, the imaging system receives the trigger signal to start taking images.

2. The time sequence coordination system for the hypersonic aerodynamic optical effect wind tunnel experiment according to claim 1, wherein the sensor assembly comprises a sensing head, a supporting horizontal rod and a supporting vertical rod, the sensing head is installed at the front end of the supporting horizontal rod and faces the flow field direction, and the supporting horizontal rod is vertically installed on the supporting vertical rod. The front end of the sensing head has a through hole penetrating into the interior of the sensing head, a fuse wire is arranged in the interior of the sensing head, the fuse wire is arranged close to the inner port of the through hole, and the trigger circuit is electrically connected with both ends of the fuse wire. The flow field forms a stagnation point region at the sensing head to generate high-temperature and high-pressure airflow, and the fuse wire is washed through the through hole to melt the fuse wire when the hypersonic flow field is established.

3. The time sequence coordination system for the hypersonic aerodynamic optical effect wind tunnel experiment according to claim 2, wherein the sensing head comprises a protective cap, the protective cap is a spherical top cylindrical structure, and the through hole is located at the spherical top of the protective cap. The cylindrical section of the protective cap is a hollow structure, has a threaded hole at the end of the cylindrical section of the protective cap, and is provided with a connecting screw rod installed through the threaded hole, the connecting screw rod is threadedly installed at the front end of the supporting horizontal rod, the connecting screw rod has two screw holes, the connecting screw rod is threadedly provided with two connecting electrodes through the screw holes, one end of the two connecting electrodes is located in the protective cap and contacts the two ends of the fuse wire, and the other end of the two connecting electrodes is located outside the protective cap. The supporting horizontal rod has a channel for arranging a circuit to electrically connect the connecting electrodes and the trigger circuit through a lead wire.

4. The time sequence coordination system for the hypersonic aerodynamic optical effect wind tunnel experiment according to claim 3, wherein the end of the connecting electrode located in the protective cap is provided with a screw hole, the connecting electrode is provided with a locking screw rod installed through the screw hole, and the locking screw rod is used for pressing the two ends of the fuse wire on the connecting electrode. ​ ​ ​ ​ ​ ​ ​ 5. The timing coordination system for hypersonic aero-optical effects wind tunnel experiments according to claim 2, characterized in that, The horizontal cross-section of the support pole is a right-angled triangle, and the edge between the two vertical planes of the support pole faces the direction of the flow field.

6. The timing coordination system for hypersonic aero-optical effects wind tunnel experiments according to claim 1, characterized in that, The trigger circuit includes resistors R1 and R2, and resistors R1 and R2 are connected in series. The two ends of the resistor R2 are connected in parallel to the two ends of the fuse, and the two ends of the fuse are electrically connected to the imaging system to form the output terminal. The non-series ends of the resistors R1 and R2 are connected to the positive and negative terminals of the power supply to form the input terminal. When the fuse does not blow, the fuse is short-circuited and the voltage at the output terminal is 0V; or when the fuse blows, the fuse is open-circuited and the voltage at the output terminal is the voltage divided by the resistor R2, thereby triggering the imaging system to work.

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