A high-speed wind tunnel multi-physics field pulsation parameter decoupling measurement device

Abstract

The present invention discloses a high-speed wind tunnel multi-physics field pulsation parameter decoupling measurement device frame, which solves the problems of complex installation and debugging of multiple measurement units and easy interference between measurement units during measurement. It includes an upper flat plate section, a vertical flat plate section and a strut section. The upper flat plate section is detachably connected to the top of the vertical flat plate section, and the tail of the vertical flat plate section is integrally connected with the strut section; the upper surface of the upper flat plate section is provided with an embedded dynamic pressure sensor installation hole, and the head of the vertical flat plate section is provided with a hot wire probe fixing place, a first pitot pressure probe fixing place and a second pitot pressure probe fixing place from top to bottom, and a wiring compartment is provided inside the vertical flat plate section. This measurement device frame has the advantages of convenient disassembly and assembly and convenient and quick adjustment.

Description

Technical Field

[0001] The invention belongs to the technical field of wind tunnel testing and measurement, and in particular relates to a high-speed wind tunnel multi-physical field pulsation parameter decoupling measurement device frame. Background Art

[0002] Wind tunnel testing is one of the important means of aerodynamic research. With the development of aerospace technology, the requirements for wind tunnel testing capabilities have become higher and higher. In particular, in-depth research on key engineering issues such as super / hypersonic boundary layer transition has found that the difference between the wind tunnel test environment and the flight environment makes it extremely difficult to accurately predict the boundary layer transition. It is necessary to deepen the understanding and recognition of the test flow field environment of ground test equipment and improve the flow field quality and data correction capability of ground test equipment. After a wind tunnel is built, the static and dynamic qualities of the flow field must be identified. Among them, the dynamic flow field quality, that is, the modal characteristics of the free flow disturbance, is an important indicator to measure the success of the wind tunnel design. For conventional low-speed wind tunnels, the parameter to measure its dynamic quality is turbulence, that is, the root mean square of the velocity deviation. Relatively speaking, the flow field structure of supersonic / hypersonic wind tunnels is complex, and the definition of the dynamic quality of its flow field is more difficult. In the flow field of a transient hypersonic wind tunnel, there are disturbances such as vortex waves, entropy waves and sound waves due to the mutual coupling caused by the rectifier, boundary layer and heating. These disturbances have a serious impact on the measurement results of wind tunnel tests, such as the transition of laminar / turbulent boundary layers, shock wave / boundary layer interference mode, drag coefficient measurement, etc. However, the mechanism of action is still unclear and needs further exploration. In particular, the boundary layer transition problem under supersonic / hypersonic flow, different types of incoming flow disturbance sub-modes directly determine the transition point position and the type of transition wave, such as vortex wave mode usually causes the first mode (Tollmien-Schlichting wave) transition, while the acoustic wave mode will cause the second mode (Mack wave) transition. Therefore, it is crucial to accurately measure the free flow disturbance submodes in supersonic / hypersonic wind tunnels, analyze the source and magnitude of the disturbance, give a quantitative evaluation of the wind tunnel disturbance level, and develop technical methods to control the wind tunnel disturbance level on this basis, identify the influence of different disturbance quantities on typical physical processes such as boundary layer transition, form relevant criteria for wind tunnel test data correction, and improve the simulation capability of ground test equipment for the research of related basic scientific issues in supersonic / hypersonic wind tunnels. Generally speaking, the measurement of high-speed flow disturbance in wind tunnels often requires the separate arrangement of measurement units such as hot wires, pitot probes, and dynamic pressure sensors. The existing decoupled measurement device frame has the disadvantages of complicated installation and debugging process and mutual interference between multiple measurement units. Summary of the invention

[0003] Based on the above shortcomings, the purpose of the present invention is to provide a high-speed wind tunnel multi-physical field pulsation parameter decoupling measurement device frame, which can reasonably arrange the probe positions of each measurement unit, and is suitable for the decoupling measurement of multi-physical field pulsation parameters such as supersonic / hypersonic wind tunnel inflow temperature field, velocity field and pressure field, and solves the problem of complex installation and debugging of multiple measurement units and easy mutual interference between measurement units when measuring the pulsation parameters of high-speed inflow in the wind tunnel.

[0004] The technical solution adopted by the present invention is: a high-speed wind tunnel multi-physical field pulsation parameter decoupling measurement device frame, including an upper flat plate section, a vertical flat plate section and a strut section, the upper flat plate section is detachably connected to the top of the vertical flat plate section, and the tail of the vertical flat plate section is integrally connected with the strut section; an embedded dynamic pressure sensor mounting hole is opened on the upper surface of the upper flat plate section, and a hot wire probe fixing place, a first pitot pressure probe fixing place and a second pitot pressure probe fixing place are arranged on the head of the vertical flat plate section from top to bottom, and a wiring compartment is arranged inside the vertical flat plate section.

[0005] The present invention also has the above technical features:

[0006] 1. The head of the upper flat plate section is a single-sided wedge shape.

[0007] 2. The head of the vertical flat plate section is in a double-sided wedge shape.

[0008] 3. The measuring device frame also includes a strut adapter section. According to different wind tunnel strut mechanisms, the strut section and the strut adapter section are selected for connection.

[0009] 4. The measuring device frame also includes an upper plate heightening component. According to different incoming flow Mach number requirements, the upper plate section is selected to be connected to the vertical plate section through the upper plate heightening component.

[0010] The advantages and beneficial effects of the present invention are as follows: through reasonable layout, mutual interference between the measuring units is avoided; the measuring device frame adopts a wedge-shaped special head shape design to achieve the non-reflection condition of the decoupling measuring device to the measured flow field; the support rod section and the vertical flat plate section are an integrated structure, which plays a role of stable support. It has the advantages of convenient disassembly and assembly and convenient and quick adjustment. BRIEF DESCRIPTION OF THE DRAWINGS

[0011] Figure 1 It is a stereoscopic diagram of a high-speed wind tunnel multi-physics field pulsation parameter decoupling measurement device frame;

[0012] Figure 2 It is a main view of a high-speed wind tunnel multi-physics field pulsation parameter decoupling measurement device frame;

[0013] Figure 3 It is a left view of the frame of a high-speed wind tunnel multi-physics field pulsation parameter decoupling measurement device;

[0014] In the figure, 1-upper flat plate section, 2-vertical flat plate section, 3-strut section, 4-wiring compartment, 5-embedded dynamic pressure sensor mounting hole, 6-strut adapter section, 7-hot wire probe fixing place, 8-first fixing place of Pitot pressure probe, 9-second fixing place of Pitot pressure probe, 10-upper flat plate heightening component. DETAILED DESCRIPTION

[0015] Combined with Figure 1 , the following implementation modes are given to further illustrate the technical solution of the present invention.

[0016] Example 1

[0017] like Figure 1-3 As shown, a high-speed wind tunnel multi-physics field pulsation parameter decoupling measurement device frame includes an upper flat plate section, a vertical flat plate section and a strut section. The upper flat plate section is detachably connected to the top of the vertical flat plate section, and the tail of the vertical flat plate section is integrally connected with the strut section to play a role of stable support; the upper surface of the upper flat plate section is provided with an embedded dynamic pressure sensor mounting hole, and the head of the vertical flat plate section is provided with a hot wire probe fixing place, a first pitot pressure probe fixing place and a second pitot pressure probe fixing place from top to bottom, and a wiring compartment is provided inside the vertical flat plate section. The head of the upper flat plate section is a single-sided wedge shape. The head of the vertical flat plate section is a double-sided wedge shape. In addition, the device frame also includes a strut adapter section. According to different wind tunnel strut mechanisms, the strut section is selected to be connected with the strut adapter section. By replacing the strut adapter section, universal wind tunnel measurement can be achieved. The device frame also includes an upper plate heightening component. According to different incoming flow Mach number requirements, the upper plate section is selected to be connected with the vertical plate section through the upper plate heightening component. The heightening component and the second fixing point of the Pitot pressure probe are suitable for lower Mach numbers.

[0018] Example 2

[0019] The present embodiment is applied to the multi-parameter pulsation measurement of the supersonic / hypersonic incoming flow field in a wind tunnel. The measuring units installed on the measuring device frame include an embedded dynamic pressure sensor, a hot wire probe and a pitot pressure probe. The three measuring units are reasonably installed on the measuring device frame at the same time, and have the ability to simultaneously measure the incoming flow velocity pulsation, total temperature pulsation, total pressure and static pressure pulsation, wherein the measurement of the incoming flow velocity pulsation and the total temperature pulsation is realized by the high-speed hot wire measurement unit; the measurement of the total pressure pulsation and the static pressure pulsation is realized by the pitot pressure probe and the pulsation pressure sensor respectively. When measuring, the decoupling measuring device frame is installed at the front section of the angle of attack mechanism of the wind tunnel, and the angle of attack mechanism is adjusted to 0 degrees. When the high-speed airflow flows through the hot wire probe and the pitot pressure probe, the velocity pulsation, total temperature pulsation, and total pressure pulsation of the incoming flow are measured; when the airflow flows through the upper plate pulsation pressure measurement hole, the static pressure pulsation is measured; for relatively high-speed incoming flow, the first fixing point of the pitot pressure probe is selected when the Mach number is greater than 3, and it is not necessary to install a vertical plate heightening device. For relatively low-speed incoming flow, the first fixing point of the pitot pressure probe is selected when the Mach number is less than 3, and a plate heightening component is added. During the measurement process, under the condition that the measured flow field space is approximately the same, no shock wave interference is achieved between the three measurement units. For the measurement of different wind tunnel incoming flow fields, the corresponding strut adapter section can be connected after the strut section.

Claims

1. A high-speed wind tunnel multi-physics field pulsation parameter decoupling measurement device frame, comprising an upper plate section, a vertical plate section and a strut section, an upper plate heightening component and a strut transition section, characterized in that: The upper flat plate section is detachably connected to the top of the vertical flat plate section, and the tail of the vertical flat plate section is integrally connected with the strut section; an embedded dynamic pressure sensor mounting hole is opened on the upper surface of the upper flat plate section, and a hot wire probe fixing place, a first pitot pressure probe fixing place and a second pitot pressure probe fixing place are sequentially arranged at the head of the vertical flat plate section from top to bottom, and a wiring compartment is arranged inside the vertical flat plate section; the head of the upper flat plate section is a single-sided wedge shape; the head of the vertical flat plate section is a double-sided wedge shape; according to different wind tunnel strut mechanisms, the strut section is selected to be connected with the strut transition section; according to different incoming flow Mach number requirements, the upper flat plate section is selected to be connected with the vertical flat plate section through the upper flat plate raising component.

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