Hypersonic aerodynamic optical effect wind tunnel experiment time sequence cooperation system

Abstract

The invention discloses a hypersonic aerodynamic optical effect wind tunnel experiment time sequence cooperation system, which comprises a wind tunnel, an experimental section of which is used for forming a hypersonic flow field; the imaging system is installed in the wind tunnel experiment model and used for shooting an imaging target after receiving the trigger signal; the sensor assembly is used for detecting the establishment state of the hypersonic flow field in the experimental section and fusing when the hypersonic flow field is established in the experimental section; and the trigger circuit is electrically connected with the sensor assembly and the imaging system. A sensor circuit fusing mode is adopted, the sensor assembly is arranged in the experimental section flow field of the wind tunnel, and the sensor assembly is electrically connected with the imaging system through the trigger circuit, so that after the hypersonic flow field is formed in the experimental section, the fuse wire in the sensor assembly is fused by the high-temperature and high-pressure gas, and the hypersonic flow field is formed. If yes, the trigger circuit directly outputs a trigger signal to the imaging system, so that the imaging system acquires images immediately, and the response speed and accuracy of time sequence system control are improved.

Description

Technical Field

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

[0002] Aero-optical effects can cause target image shift, jitter, and blur, making them a key factor affecting hypersonic dynamic imaging and an essential consideration in the design of imaging systems for hypersonic kinetic interception, starlight navigation, and reconnaissance. Under hypersonic flight conditions, the flow field is accompanied by dissociation, ionization, and complex thermochemical reactions, making accurate numerical prediction of aero-optical effects difficult. Wind tunnel experiments remain the primary method for studying hypersonic aero-optical effects.

[0003] Achieving hypersonic flight conditions in a wind tunnel requires extremely high drive energy requirements. Consequently, all wind tunnels are pulsed, resulting in short effective test times. Hypersonic wind tunnels at home and abroad operate at Mach 9 and above for no more than 40 milliseconds. Hypersonic weapons have low imaging frame rates, and only one frame can be captured during the effective test time for evaluating the performance of the imaging system in a wind tunnel. This places extremely high demands on the timing coordination between wind tunnel operation and the imaging system. To achieve this timing coordination, a trigger signal must be output to the imaging system when the hypersonic flow field is established. However, hypersonic wind tunnels employ flow-around structures to protect pressure sensors from direct impact by the hypersonic airflow. This results in long response times for the pressure sensors and low accuracy in capturing the flow field establishment moment. Furthermore, thermocouple sensors, due to their low sensitivity and small signal amplitude, are susceptible to electromagnetic interference signals, which can easily lead to false triggering.

[0004] Therefore, when pressure and heat flow sensors are currently used for timing coordination, the timing coordination accuracy is low, making it difficult to carry out wind tunnel experiments on hypersonic aerodynamic-optical effects, which seriously restricts the design of imaging systems such as hypersonic kinetic interception, starlight navigation and reconnaissance. Summary of the Invention

[0005] The purpose of the present invention is to provide a timing coordination system for hypersonic aero-optical effect wind tunnel experiments to solve the problem in the prior art that the pressure sensors and thermocouple sensors are difficult to respond quickly, resulting in low accuracy of timing coordination control and difficulty in conducting hypersonic aero-optical effect wind tunnel experiments.

[0006] In order to solve the above technical problems, the present invention specifically provides the following technical solutions:

[0007] A time-series coordination system for hypersonic aero-optical effect wind tunnel experiments, comprising:

[0008] A wind tunnel comprising an experimental section for forming a hypersonic flow field;

[0009] The imaging system is an imaging payload in the pneumo-optical effect wind tunnel experiment. It is installed inside the wind tunnel experiment model. After receiving the trigger signal, it captures the imaging target and determines the influence of the pneumo-optical effect by analyzing the captured images.

[0010] The sensor assembly is arranged in the test section and is used to detect the establishment state of the hypersonic flow field in the test section. When the hypersonic flow field is established in the test section, the fuse inside it melts.

[0011] The trigger circuit is arranged inside the sensor assembly.

[0012] Wherein, the trigger circuit is electrically connected to the sensor assembly and the imaging system to establish the timing coordinated control between the wind tunnel operation and the imaging system.

[0013] When the fuse inside the sensor assembly melts instantaneously, the trigger circuit outputs a trigger signal to the imaging system. At the same time, the imaging system receives the trigger signal and starts to capture images.

[0014] As a preferred embodiment of the present invention, the sensor assembly includes a sensing head, a support cross bar and a support vertical rod. The sensing head is installed at the front end of the support cross bar and faces the flow field direction directly. The support cross bar is vertically installed on the support vertical rod.

[0015] Wherein, the front end of the sensing head has a through hole that penetrates to the inside of the sensing head. A fuse is arranged inside the sensing head. The fuse is arranged close to the inner port of the through hole, and the trigger circuit is electrically connected to both ends of the fuse.

[0016] The flow field forms a stagnation region at the sensing head to generate high-temperature and high-pressure airflow, and flushes the fuse through the through hole to melt the fuse when the hypersonic flow field is established.

[0017] As a preferred embodiment of the present invention, the sensing head includes a protective cap. The protective cap is spherical dome cylindrical, and the through hole is located at the spherical dome of the protective cap.

[0018] The cylindrical section of the protective cap is a hollow structure. There is a threaded hole at the end of the cylindrical section of the protective cap, and a connecting screw is installed through this threaded hole. The connecting screw is threadedly installed at the front end of the support cross bar.

[0019] There are two threaded holes on the connecting screw. Two connecting electrodes are respectively threadedly installed through these threaded holes on the connecting screw. One end of each of the two connecting electrodes is located inside the protective cap and contacts both ends of the fuse respectively, and the other end is located outside the protective cap. After the connecting screw is installed on the support cross bar, this end of the connecting electrode is placed inside the support cross bar.

[0020] Among them, the support cross bar has a duct inside for arranging circuits to electrically connect the connection electrode and the trigger circuit through wires.

[0021] As a preferred solution of the present invention, the end of the connection electrode located inside the protective cap is provided with a threaded hole, and a locking screw is installed through this threaded hole of the connection electrode. The locking screw is used to press both ends of the fuse on the connection electrode.

[0022] As a preferred solution of the present invention, the horizontal cross-section of the support vertical pole is a right triangle, and the edge between the two vertical planes of the support vertical pole is directly facing the flow field direction.

[0023] As a preferred solution of the present invention, the trigger circuit includes a resistor R1 and a resistor R2, and the resistor R1 and the resistor R2 are connected in series;

[0024] Both ends of the resistor R2 are connected in parallel with both ends of the fuse, and both ends of the fuse are electrically connected to the imaging system to form an output end, and the non-series ends of the resistor R1 and the resistor R2 are connected to the positive and negative poles of the power supply to form an input end;

[0025] Among them, when the fuse is not blown, the fuse is short-circuited and the voltage of the output end is 0V. Or when the fuse is blown, the fuse is open-circuited and the output end voltage is the voltage divided by the resistor R2 to trigger the imaging system to work.

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

[0027] The present invention adopts the method of fusing the sensor circuit, sets a sensor assembly in the flow field of the test section of the wind tunnel, and the sensor assembly is electrically connected to the imaging system through the trigger circuit. After a hypersonic flow field is formed in the test section, the fuse inside the sensor assembly is washed and blown by the high-temperature and high-pressure airflow, then the trigger circuit directly outputs a trigger signal to the imaging system, enabling the imaging system to immediately collect images, and improving the response speed and accuracy of the timing system control. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following will briefly introduce the drawings required for the description of the embodiments or the prior art. Obviously, the drawings in the following description are only exemplary, and for those of ordinary skill in the art, other implementation drawings can be obtained according to the provided drawings without creative efforts.

[0029] Figure 1Schematic diagram of the composition of the hypersonic aerodynamic-optical effect wind tunnel experiment timing coordination system provided by the embodiment of the present invention;

[0030] Figure 2 Schematic diagram of the structure of the sensor assembly of the hypersonic aerodynamic-optical effect wind tunnel experiment timing coordination system provided by the embodiment of the present invention;

[0031] Figure 3 Schematic diagram of the structure of the sensing head part of the hypersonic aerodynamic-optical effect wind tunnel experiment timing coordination system provided by the embodiment of the present invention;

[0032] Figure 4 Schematic diagram of the structure of the support vertical rod part of the hypersonic aerodynamic-optical effect wind tunnel experiment timing coordination system provided by the embodiment of the present invention;

[0033] Figure 5 Schematic circuit diagram of the trigger circuit of the hypersonic aerodynamic-optical effect wind tunnel experiment timing coordination system provided by the embodiment of the present invention.

[0034] The reference numerals in the figure are respectively represented as follows:

[0035] 1 - Sensing head; 2 - Support cross bar; 3 - Support vertical rod;

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

[0037] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings 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 embodiments. 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.

[0038] As Figure 1 shown, the present invention provides a hypersonic aerodynamic-optical effect wind tunnel experiment timing coordination system, including:

[0039] A wind tunnel, which includes an experimental section for forming a hypersonic flow field;

[0040] An imaging system, which is an imaging load in the hypersonic aerodynamic-optical effect wind tunnel experiment, is installed inside the wind tunnel experiment model, takes pictures of the imaging target after receiving a trigger signal, and determines the influence of the aerodynamic-optical effect through the analysis of the taken pictures;

[0041] A sensor assembly, which is arranged in the experimental section, is used to detect the establishment state of the hypersonic flow field in the experimental section, and the fuse inside it melts when the hypersonic flow field is established in the experimental section;

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

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

[0044] When the fuse inside the sensor assembly melts instantaneously, the trigger circuit outputs a trigger signal to the imaging system. At the same time, the imaging system receives the trigger signal and starts to capture images.

[0045] The timing coordination system for the wind tunnel experiment of the present invention mainly arranges the sensor assembly in the experimental section of the wind tunnel to make it in the flow field, and establishes the connection between the imaging system and the sensor assembly through the trigger circuit. When a hypersonic flow field is formed in the experimental section of the wind tunnel, if the fuse inside the sensor assembly melts and an open circuit occurs, the trigger circuit outputs a trigger signal to the imaging system, and the imaging system starts to capture images at the moment of receiving the trigger signal, so as to achieve the timing coordination control.

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

[0047] Compared with the timing coordination control composed of pressure sensors, the present invention adopts the method of fusing the sensor circuit. 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. After a hypersonic flow field is formed in the experimental section, the fuse inside the sensor assembly is melted 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, improving the response speed and accuracy of the timing system control.

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

[0049] As Figure 2 、 Figure 3 shown, the sensor assembly includes a sensing head 1, a support cross bar 2 and a support vertical bar 3. The sensing head 1 is installed at the front end of the support cross bar 2 and faces the flow field direction. The support cross bar 2 is vertically installed on the support vertical bar 3;

[0050] Wherein, 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 inside 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 region at the sensor head 1, generating a high-temperature and high-pressure air flow, which flushes the fuse 15 through the through-hole 16 to fuse the fuse 15 when the hypersonic flow field is established.

[0052] In this embodiment, by providing a through-hole 16 at the front end of the sensor head 1 to connect the inside and outside of the sensor head 1, and arranging the fuse 15 inside the sensor head 1 and against the through-hole 16, the flow field forms a stagnation region at the sensor head 1, generating a high-temperature and high-pressure air flow. When a hypersonic flow field is formed, the high-temperature and high-pressure air flow fuses the fuse 15, and then the trigger circuit outputs a trigger signal (the high-temperature and high-pressure air flow formed at the front end of the sensor head 1 will enter the inside of the sensor head 1 along the through-hole 16 and flush the fuse 15. Under hypersonic conditions, the temperature is as high as several thousand K at this time, and the fuse 15 will quickly fuse).

[0053] And in order to improve the fusing speed, shorten the fusing time to improve the response speed and accuracy of the timing cooperative control, the following preferred embodiments are provided.

[0054] As Figure 3 shown, the sensor head 1 includes a protective cap 11, the protective cap 11 is spherical-dome cylindrical, and the through-hole 16 is formed at the spherical dome of the protective cap 11;

[0055] The cylindrical section of the protective cap 11 is a hollow structure, and there is a threaded hole at the end of the cylindrical section of the protective cap 11, and a connecting screw 12 is installed through this threaded hole. The connecting screw 12 is threadedly installed at the front end of the support crossbar 2;

[0056] There are two threaded holes on the connecting screw 12. The connecting screw 12 threadedly installs two connecting electrodes 13 through these threaded holes respectively. One end of each of the two connecting electrodes 13 is located inside the protective cap 11 and abuts against both ends of the fuse 15 respectively, and the other end is located outside the protective cap 11, so that after the connecting screw 12 is installed on the support crossbar 2, this end of the connecting electrode 13 is placed inside the support crossbar 2;

[0057] Among them, there is a duct inside the support crossbar 2 for arranging circuits to electrically connect the connecting electrodes and the trigger circuit through wires.

[0058] In this embodiment, the protective cap 11 of the sensor head 1 is spherical-dome cylindrical made of stainless steel, and the spherical dome is facing the flow field direction, and the through-hole 16 is located at the spherical dome of the protective cap 11, so that the air flow can form a stagnation region at the spherical dome. And the smaller the radius of the spherical dome, the higher the heat flux density in the stagnation region and the shorter the fuse breaking time. However, if the radius of the spherical dome is too small, the installation space inside the protective cap 11 will be small, which is not conducive to installation. After comprehensive consideration, the diameter of the spherical dome is 15 mm.

[0059] Moreover, the connecting screw 12 is made of nylon, which plays an insulating and supporting connection role and is used to connect the protective cap 11 and the supporting cross bar 2. The connecting electrode 13 is made of copper and acts as a wire. That is, after connecting the fuse 15, it can be regarded as a series-connected wire.

[0060] The fuse 15 melts under the action of air flow and cooperates with the trigger circuit to output a trigger signal. The fuse 15 uses a solder wire with a diameter of 0.5 mm, which has a low melting point, soft texture, and is easy to melt.

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

[0062] In this embodiment, the fuse 15 is pressed against the end of the connecting electrode 13 by the locking screw 14, effectively avoiding displacement due to air flow scouring and ensuring that the fuse 15 is scoured and melted in time.

[0063] Of course, in order to reduce the influence of the sensor component on the flow field, as Figure 2 、 Figure 4 shown, the horizontal cross-section of the supporting vertical rod 3 is a right triangle, and the edge between the two vertical planes of the supporting vertical rod 3 is exactly in the flow field direction.

[0064] Among them, the supporting vertical rod 3 is made of stainless steel, its cross-section is a right triangle, and its two right-angled sides are located on the windward side to weaken the influence on the flow field.

[0065] Based on the above embodiments, the following provides a preferred embodiment of the trigger circuit.

[0066] As Figure 5 shown, the trigger circuit includes a resistor R1 and a resistor R2, and the resistor R1 and the resistor R2 are connected in series;

[0067] Both ends of the resistor R2 are connected in parallel with both ends of the fuse 15, and both ends of the fuse 15 are electrically connected to the imaging system to form an output end, and the non-series-connected ends of the resistor R1 and the resistor R2 are connected to the positive and negative power supplies to form an input end;

[0068] Among them, when the fuse 15 is not melted, the fuse 15 is short-circuited and the voltage at the output end is 0V. Or when the fuse 15 is melted, the fuse 15 is open-circuited and the output end voltage is the voltage divided by the resistor R2 to trigger the imaging system to work.

[0069] In this embodiment, resistors R1 and R2 are connected in series, where R1 = 1 kΩ and R2 = 4 kΩ, and they are powered by a 5V DC power supply. Before the experiment, fuse 15 is connected to connection electrode 13, and connection electrode 13 is connected to Figure 4 mid-potential points 1 and 2 through a wire arranged in support crossbar 2. R3 represents fuse 15, and V+ and V- constitute the trigger signal output terminal. Since the resistance value of fuse 15 is very small, it acts as a short circuit when fuse 15 is not broken, and the potential difference at the trigger signal output terminal is 0V. When the hypersonic flow field is formed, fuse 15 will break under the scouring effect of the airflow, and the potential difference between the trigger signal output terminals is output as 4V after being divided by resistors R1 and R2, thereby triggering the imaging system and realizing the timing coordination 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. 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 essence and protection scope of the present application, and such modifications or equivalent replacements should also be 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 Comprising: A wind tunnel, which includes a test section for forming a hypersonic flow field; An imaging system, which is an imaging payload in the wind tunnel experiment of the aerodynamic optical effect, is installed inside the wind tunnel experiment model, takes pictures of the imaging target after receiving a trigger signal, and determines the influence of the aerodynamic optical effect by analyzing the taken pictures; A sensor assembly, which is arranged in the test section, is used to detect the establishment state of the hypersonic flow field in the test section, and when the hypersonic flow field is established in the test section, the fuse inside it melts; A trigger circuit, which is arranged inside the sensor assembly; Wherein, the trigger circuit is electrically connected to the sensor assembly and the imaging system to establish the timing collaborative control of the wind tunnel operation and the imaging system; When the fuse inside the sensor assembly melts instantaneously, the trigger circuit outputs a trigger signal to the imaging system, and at the same time, the imaging system receives the trigger signal and starts taking pictures.

2. The timing collaborative system for the hypersonic aerodynamic optical effect wind tunnel experiment according to claim 1, characterized in that The sensor assembly includes a sensing head, a support cross bar and a support vertical rod. The sensing head is installed at the front end of the support cross bar and faces the flow field direction directly, and the support cross bar is vertically installed on the support vertical rod; Wherein, the front end of the sensing head has a through hole, the through hole penetrates into the inside of the sensing head, a fuse is arranged inside the sensing head, the fuse is arranged close to the inner port of the through hole, and the trigger circuit is electrically connected to both ends of the fuse; The flow field forms a stagnation area at the sensing head to generate high-temperature and high-pressure air flow, and flushes the fuse through the through hole to melt the fuse when the hypersonic flow field is established.

3. The timing collaborative system for the hypersonic aerodynamic optical effect wind tunnel experiment according to claim 2, characterized in that The sensing head includes a protective cap, the protective cap is spherical dome cylindrical, and the through hole is located at the spherical dome of the protective cap; The cylindrical section of the protective cap is a hollow structure, there is a threaded hole at the end of the cylindrical section of the protective cap, and a connecting screw is installed through this threaded hole, and the connecting screw is threadedly installed at the front end of the support cross bar; There are two threaded holes on the connecting screw, and two connecting electrodes are respectively threadedly installed through these threaded holes on the connecting screw. One end of each of the two connecting electrodes is located inside the protective cap and respectively contacts both ends of the fuse, and the other end is located outside the protective cap, so that after the connecting screw is installed on the support cross bar, this end of the connecting electrode is placed inside the support cross bar; Wherein, there is a duct inside the support cross bar for arranging circuits to electrically connect the connecting electrode and the trigger circuit through a wire.

4. The timing collaborative system for the hypersonic aerodynamic optical effect wind tunnel experiment according to claim 3, characterized in that The end of the connecting electrode located inside the protective cap is provided with a threaded hole, and a locking screw is installed through this threaded hole on the connecting electrode, and the locking screw is used to press both ends of the fuse against the connecting electrode.

5. A hypersonic aerodynamic-optical effect wind tunnel experiment timing coordination system according to claim 1, characterized in that the horizontal cross-section of the support vertical rod is a right triangle, and the edge between the two vertical planes of the support vertical rod is directly opposite to the flow field direction.

6. A hypersonic aerodynamic-optical effect wind tunnel experiment timing coordination system according to claim 1, characterized in that the trigger circuit includes a resistor R1 and a resistor R2, and the resistor R1 and the resistor R2 are connected in series; both ends of the resistor R2 are connected in parallel with both ends of the fuse, and both ends of the fuse are electrically connected to the imaging system to form an output end, and the non-series ends of the resistor R1 and the resistor R2 are connected to the positive and negative poles of the power supply to form an input end; wherein, when the fuse is not blown, the fuse is short-circuited, and the voltage of the output end is 0V, or when the fuse is blown, the fuse is open-circuited, and the output end voltage is the voltage divided by the resistor R2 to trigger the imaging system to work.

Images