CN206448877U - A kind of hypersonic inlet self-starting energy force checking device - Google Patents
A kind of hypersonic inlet self-starting energy force checking device Download PDFInfo
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- CN206448877U CN206448877U CN201720053829.7U CN201720053829U CN206448877U CN 206448877 U CN206448877 U CN 206448877U CN 201720053829 U CN201720053829 U CN 201720053829U CN 206448877 U CN206448877 U CN 206448877U
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Abstract
The utility model discloses a kind of hypersonic inlet self-starting energy force checking device, including：Guide rail, one end of the guide rail is in the inner flow passage of hypersonic inlet model, and the diameter parallel of the guide rail and the inner flow passage；Sprue, is slidingly disposed at the guide rail；In the presence of the inner flow passage interior air-flow, the sprue in the inner flow passage can be slid into outside the inner flow passage along the guide rail.Above-mentioned hypersonic inlet self-starting energy force checking device, can not only control the forms of motion of sprue, and can reclaim sprue, reuse it, it is ensured that the repeatability of sprue ponding process.
Description
Technical Field
The utility model relates to a hydrodynamics technical field, in particular to hypersonic intake duct is from starting ability detection device.
Background
In order to obtain better performance, a hypersonic air inlet channel serving as an air flow capturing and compressing part of the hypersonic air inlet channel is required to have good self-starting capability, namely after a factor causing the air inlet channel to be not started is eliminated, the air inlet channel can be recovered to a starting state (restarting) without extra auxiliary starting measures. However, the air inlet channel may not start due to the fact that the flying and control factors such as low incoming flow mach number, large attack angle, and high back pressure of the air inlet channel seriously affect the flying safety. In order to reduce the risk of the air inlet channel not starting in a flight test, the self-starting capability of the hypersonic air inlet channel is detected in a ground wind tunnel test, and the method becomes an important wind tunnel test technology.
In view of the difficulty that the hypersonic wind tunnel continuously and controllably changes the incoming flow Mach number in a primary blowing experiment, the self-starting capability detection experiment of the air inlet channel is usually carried out under the condition of fixing the incoming flow Mach number. The conventional hypersonic wind tunnel has long experimental time which can reach the magnitude of seconds to tens of seconds, and the self-starting capability detection experiment of the air inlet channel is relatively easy to carry out by means of the traditional actuating mechanisms such as a stepping motor and an electromagnetic valve. In a conventional hypersonic wind tunnel, a scholart forces an air inlet to be not started firstly by moving a lip cover of the air inlet, continuously changing an attack angle of the air inlet, moving a throttling and blocking cone simulating back pressure of the air inlet at the downstream of the air inlet, injecting high-pressure gas to be throttled at the downstream of the air inlet and the like, then removing corresponding factors of the non-starting of the air inlet, and restarting the air inlet as a basis for determining that the air inlet has self-starting capability under similar conditions.
The ground pulse type wind tunnel experimental equipment represented by the shock tunnel has the advantages of relatively low construction and operation cost and flexible operation mode, can provide high enthalpy airflow for a large-scale air inlet channel, and plays an important role in the research field of hypersonic aircrafts. However, the experimental time of the shock tunnel is short, usually only milliseconds to tens of milliseconds, and the self-starting capability detection technology of the air inlet channel in the conventional hypersonic wind tunnel cannot be directly applied to the shock tunnel in a 'transplanting' manner. Therefore, the shock tunnel faces the challenge of the experimental method for detecting the self-starting capability of the air inlet.
In the prior art, some scholars force the air inlet to be not started by arranging a quick sliding valve at the throat of the air inlet, and detect the self-starting capability of the air inlet in a shock tunnel. However, such a quick slide valve is not only technically difficult, but also requires a special design for a specific inlet channel configuration, and is limited in versatility. The learner also forces the air inlet to be not started by placing a light blockage on the lower wall surface of the isolation section at the downstream of the air inlet in advance, and the flow channel is recovered to be smooth after the blockage is blown out of the air inlet, so that the self-starting capability of the air inlet is detected. Although the detection method is simple and convenient, the light blockage has irregular geometric shape, random blockage placing mode, unclear movement rule of the blockage, ineffective control of the movement form of the blockage and no reuse of the blockage after recovery. These factors all result in less reproducible effects of the plug. In addition, some scholars adopt a polyester membrane which is pre-installed to seal the outlet of the air inlet channel, and force the air inlet channel not to start firstly; then, in the experimental process, a pulse high-energy igniter is used for breaking the polyester membrane, an outlet of the air inlet channel is opened, and the self-starting capacity of the air inlet channel is detected. However, the testing device needs to be reinstalled with the terylene film in each experiment, and the use of the pulse high-energy igniter brings certain troubles to the control mode and the safety. Therefore, in an impulse type wind tunnel represented by a shock tunnel, an experimental method for detecting the self-starting capability of a hypersonic inlet needs to be further improved.
SUMMERY OF THE UTILITY MODEL
The utility model aims at providing a hypersonic intake duct is from starting ability detection device, this hypersonic intake duct is from starting ability detection device can used repeatedly, can force the intake duct not start at the initial stage of the effective experimental time of shock tunnel to examine the self-starting ability of hypersonic intake duct in the effective experimental time of shock tunnel.
In order to achieve the above object, the utility model provides a hypersonic intake duct is from starting ability detection device, include:
one end of the guide rail is arranged in an inner flow channel of the hypersonic inlet channel model, and the guide rail is parallel to the axis of the inner flow channel;
the blocking block is slidably arranged on the guide rail; under the action of the airflow in the inner flow passage, the blocking block positioned in the inner flow passage can slide to the outside of the inner flow passage along the guide rail.
Compared with the prior art, the utility model provides a hypersonic inlet duct self-starting ability detection device, one end of guide rail is located the interior runner of hypersonic inlet duct model, and the sprue locates the guide rail slidably; before a hypersonic inlet channel self-starting capability detection experiment is started in a shock tunnel, a blocking block is positioned in an inner runner, the blocking block blocks the inner runner, the inlet channel is not started, and a plurality of periodic shock oscillation flow states appear; meanwhile, the blocking block moves to the outlet of the air inlet channel in a quasi-one-dimensional mode along the guide rail under the action of the air flow of the inner channel of the air inlet channel; in the effective experimental time of the shock tunnel, the blocking block is blown out of the outlet of the air inlet channel; the inner flow channel of the air inlet channel is recovered smoothly, and then whether the air inlet channel can be recovered to a starting state or not can be observed within the effective experimental time of the shock tunnel, and the self-starting capability of the air inlet channel is detected; after the shock tunnel experiment is finished, the blocking block is still positioned on the guide rail, the appearance of the blocking block is good, and the blocking block can be used again. The core of the utility model is that the guide rail is used to limit the movement direction of the block, thereby detecting the self-starting capability of the air inlet channel; the detected blocking block can be reused, and the blocking block is pushed into the inner flow channel along the guide rail; so set up, not only can control the motion form of sprue, can retrieve the sprue moreover, make it can reuse, guaranteed the repeatability of sprue jam effect process.
Preferably, the inner runner and the guide rail are both horizontally arranged.
Preferably, the first and second electrodes are formed of a metal,
the hypersonic-speed air inlet channel model is a binary air inlet channel, the cross section of the inner flow channel is rectangular, and the block is a rectangular block; or,
the hypersonic inlet duct model is specifically an inward turning type inlet duct, just the cross section of the inner flow passage is circular, and the block is specifically a conical block.
Preferably, the degree of blockage of the inner flow channel is between 50% and 80%.
Preferably, the guide rail is a hollow guide rail capable of being used as a skin pressure probe, and a pressure sensor for detecting skin pressure in the inner flow passage is arranged at the other end of the guide rail.
Preferably, the guide rail is provided with a buffer member for buffering impact force when the block slides out of the inner flow channel along the guide rail.
Preferably, still include and be used for fixing the bolster and the end seat of guide rail, the end seat is equipped with the stand in vertical direction, just the end of stand is fixed through the support base.
Preferably, the blocking block is provided with a through hole for the guide rail to pass through, and the inner wall of the through hole is smooth.
Preferably, the position of the end mount relative to the upright is adjustable.
Preferably, the number of the guide rails and the number of the through holes are two, and the two guide rails have the same shape and size.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required to be used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the provided drawings without creative efforts.
Fig. 1 is a schematic diagram of a self-starting capability detection device for a hypersonic air inlet according to an embodiment of the present invention;
FIG. 2 is a schematic view of FIG. 1 without a binary inlet;
fig. 3 is a schematic diagram of another hypersonic air inlet self-starting capability detection apparatus provided by the embodiment of the present invention.
Wherein:
in the attached figure 1 of the specification: 1-a binary air inlet channel, 2-a solid guide rail, 3-a rectangular block, 4-a guide rail base, 5-a buffer cushion block, 6-a bracket and 7-a bracket base;
in the description, in the attached figure 2: 2-solid guide rail, 3-rectangular block, 101-through hole;
in the attached figure 3 of the specification: 102-an internal rotation type air inlet channel, 103-a hollow guide rail, 104-a conical block, 105-a hollow guide rail base, 106-a buffer component, 107-a vertical bracket and 108-a pressure sensor.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
In order to make the technical field of the present invention better understand, the present invention will be described in detail with reference to the accompanying drawings and the detailed description.
Referring to fig. 1, fig. 2 and fig. 3, fig. 1 is a schematic diagram of a hypersonic air inlet channel self-starting capability detection device according to an embodiment of the present invention; FIG. 2 is a schematic view of FIG. 1 without a binary inlet; fig. 3 is a schematic diagram of another hypersonic air inlet self-starting capability detection apparatus provided by the embodiment of the present invention.
The utility model provides a pair of hypersonic intake duct is from starting ability detection device mainly includes guide rail and sprue. One end of the guide rail is arranged in an inner flow channel of the hypersonic air inlet channel model, and the guide rail is parallel to the axis of the inner flow channel; the blocking block is slidably arranged on the guide rail; under the action of the airflow in the inner flow passage, the blocking block positioned in the inner flow passage can slide to the outside of the inner flow passage along the guide rail.
The hypersonic inlet model can be a binary inlet, a lateral pressure type inlet and a three-dimensional inward rotation type inlet, and an inner flow passage of the hypersonic inlet model comprises an inlet inner compression section and an isolation section. The guide rail has good rigidity and small outer diameter, the outer surface of the guide rail is smooth, the guide rail is preferably a flat guide rail, and the cross section of the guide rail can be circular or annular. The block is a rigid block with smaller mass and regular geometric shape; the shape of the block is a cube, a cuboid, a triangular prism, a cylinder, a cone or a sphere; the cross section size and the spanwise length of the blocking block are smaller than those of a flow passage in the hypersonic-speed air inlet channel model; aiming at the mass and the geometric shape of the block, the block can be selected according to the blocking time required by a shock tunnel experiment and the geometric form of an inner runner of the hypersonic inlet channel model.
Before a hypersonic speed air inlet channel self-starting capability detection experiment is started in a shock tunnel, a blocking block is positioned in an inner flow channel, the blocking block blocks the inner flow channel at the moment, the air inlet channel is not started, and a plurality of periodic shock wave oscillation flow states appear; meanwhile, the blocking block moves to the outlet of the air inlet channel in a quasi-one-dimensional mode along the guide rail under the action of the air flow of the inner channel of the air inlet channel; in the effective experimental time of the shock tunnel, the blocking block is blown out of the outlet of the air inlet channel; the inner flow channel of the air inlet channel is recovered smoothly, and then whether the air inlet channel can be recovered to a starting state or not can be observed within the effective experimental time of the shock tunnel, and the self-starting capability of the air inlet channel is detected; after the shock tunnel experiment is finished, the blocking block is still positioned on the guide rail, the appearance of the blocking block is good, and the blocking block can be used again.
The core of the utility model is that the guide rail is used to limit the movement direction of the block, thereby detecting the self-starting capability of the air inlet channel; the detected blocking block can be reused, and the blocking block is pushed into the inner flow channel along the guide rail; so set up, not only can control the motion form of sprue, can retrieve the sprue moreover, make it can reuse, guaranteed the repeatability of sprue jam effect process. According to different test requirements, the inner runner and the guide rail can be horizontally arranged, and the inner runner and the guide rail can also be inclined at a certain angle relative to the horizontal plane.
Description attached drawing 1 is the utility model provides a hypersonic intake duct self-starting ability detection device's schematic diagram, and figure 3 is the utility model provides another kind of hypersonic intake duct self-starting ability detection device's schematic diagram.
In the attached figure 1 of the specification, the cross section of an inner flow passage of a binary air inlet channel 1 is rectangular, the spanwise width of the binary air inlet channel 1 is 54mm, and the height of the binary air inlet channel 1 is 10 mm; the solid guide rails 2 are two steel bars with the same length and the outer diameter of 2mm, the two solid guide rails 2 are parallel to the axis of the inner flow channel of the air inlet channel and are symmetrically arranged, and the span-wise distance between the two solid guide rails 2 is 20 mm; rectangular sprue 3 is the cuboid shape, and the geometric dimension is 6mm (flow direction) x 6mm (horizontal) x 50mm (exhibition direction), and the quality is 2.05g, sets up two internal diameters 2.5mm at the windward side central line bilateral symmetry of rectangular sprue 3, interval 20 mm's through-hole, and rectangular sprue 3 penetrates solid guide 2 through the through-hole to can slide along solid guide 2, rectangular sprue 3's windward side is 40mm apart from the export of intake duct 1. The guide rail base 4 is a combination body in a form of a blunt wedge-cuboid and is used for fixing and supporting the solid guide rail 2; the buffer cushion block 5 is a rectangular silica gel gasket with the thickness of 2mm and is tightly attached to the guide rail base 4; the bracket 6 is a threaded rod and is used for fixing and supporting the guide rail base 4; the bracket base 7 is in a rectangular parallelepiped shape and is used for fixing the bracket 6.
The working principle is that at the initial stage of the effective experimental time of the shock tunnel, the rectangular blocking block 3 causes the blocking of the inner flow channel of the binary air inlet channel 1; the binary air inlet 1 is not started and has a plurality of periodic shock wave oscillation flow states; meanwhile, the rectangular block 3 moves to the outlet of the binary air inlet channel 1 in a quasi-one-dimensional mode along the solid guide rail 2 under the action of the air flow of the inner flow channel of the binary air inlet channel 1; in the effective experimental time of the shock tunnel, the rectangular blocking block 3 is blown out of the outlet of the binary air inlet channel 1; the inner flow channel of the binary air inlet channel 1 is recovered smoothly, and then whether the binary air inlet channel 1 can be recovered to a starting state or not can be observed in the effective experimental time of the shock tunnel, and the self-starting capability of the binary air inlet channel 1 is detected; after the shock tunnel experiment is finished, the rectangular plugging block 3 is positioned on the solid guide rail 2, and the rectangular plugging block 3 is good in appearance and can be reused. In the above embodiment, the inner flow passage is rectangular, and of course, the specific size and position relationship of the above components may be determined according to actual needs, and are not limited to the above.
Description figure 2 is a schematic diagram of fig. 1 without a binary air inlet channel, and shows the geometric positions of the solid guide rails 2 and the rectangular blocks 3 in more detail, wherein the rectangular blocks 3 are provided with two through holes 101 for the two solid guide rails 2 to pass through, and the inner walls of the two through holes 101 are smooth. In a specific embodiment, the inner diameters of the two through holes 101 are both 2.5mm, and the span-wise distance between the two through holes 101 is 20 mm. The working principle is as follows: the rectangular blocks 3 penetrate into the two solid guide rails 2 through the two through holes 101, and the rectangular blocks 3 can slide along the two solid guide rails 2.
In the description of fig. 3, compared with the embodiment of fig. 1, the method used by the two is similar, and the inlet used is changed from the binary inlet to the internal-rotation inlet. The test device that hypersonic speed internal rotation formula intake duct self-starting ability detected includes: the device comprises an internal rotation type air inlet 102, a hollow guide rail 103, a conical block 104, a hollow guide rail base 105, a buffer part 106, a vertical bracket 107 and a pressure sensor 108.
Wherein, the outlet of the inner rotary type air inlet channel 102 is circular with the inner diameter of 35 mm; the hollow guide rail 103 is a steel pipe with the outer diameter of 5mm and the inner diameter of 3mm, and is also used as a pitot pressure probe; the conical block 104 is a cone with a half cone angle of 20 degrees and a bottom diameter of 24mm, and the mass of the conical block is 5 g; a through hole with the inner diameter of 5.2mm is arranged at the axis of the conical block 104, the conical block 104 penetrates into the hollow guide rail 103 through the through hole and can slide along the hollow guide rail 103, and the distance between the vertex of the conical block 104 and the outlet of the inward-turning air inlet channel 102 is 45 mm; the hollow guide rail base 105 is a combination of a blunt wedge and a cuboid, is used for fixing and supporting the hollow guide rail 103, and is connected with the vertical bracket 107; the buffer component 106 is a silica gel gasket with the thickness of 2mm and is tightly attached to the hollow guide rail base 105; the vertical support 107 is two threaded rods with the same length and is used for fixing and supporting the hollow guide rail base 105; the pressure sensor 108 is arranged at the bottom of the hollow guide rail base 105, and a pressure sensitive element of the pressure sensor 108 is communicated with an inner hole of the hollow guide rail 103 which is also used as a pitot pressure probe and used for measuring pitot pressure.
The working principle of the embodiment is similar to that described above, and the main difference between the two is that the hollow guide rail 103 is also used as a pitot pressure probe, and the pressure sensor 108 can monitor the change of the pitot pressure of the flow passage in the internal rotation type air inlet 102 in the experimental process of detecting the self-starting capability of the internal rotation type air inlet 102. According to the method, at the initial stage of the effective experiment time of the shock tunnel, the blocking block is positioned in the inner flow passage, so that the blocking of the inner flow passage is formed; according to actual needs, the degree of blockage of the inner flow passage can be controlled between 50% and 80% so as to carry out experiments. Of course, the degree of blockage of the inner flow passage can also be in other numerical ranges according to actual needs.
In the description of fig. 3, the guide rail is specifically a hollow guide rail 103 which can be used as a skin pressure probe, and the other end of the guide rail is provided with a pressure sensor 108 for detecting the skin pressure in the inner flow passage. For the embodiment shown in fig. 1, the guide rail may be a hollow guide rail 103, and the function and function are the same.
The utility model discloses a hypersonic intake duct is from starting ability detection device utilizes fixed bolster of end socket and guide rail, and the end socket is equipped with the stand in vertical direction, and the end of stand passes through the support base fixedly. As can be seen from the attached drawings 1 to 3 in the specification, in the attached drawings 1 and 2 in the specification, the guide rail base 4 is an end seat, the buffer cushion block 5 is a buffer piece, and the bracket 6 is an upright post; in the attached figure 3 of the specification, the hollow guide rail base 105 is an end seat, the buffer component is a buffer component, and the vertical support 107 is an upright post. Of course, other means for securing the guide rail may be used and are not limited to those described herein.
In order to realize that the blocking block can be arranged on the guide rail in a sliding way, the blocking block is provided with a through hole for the guide rail to pass through, and the inner wall of the through hole is smooth; as shown in the attached figure 2 of the specification, the rectangular block 3 is provided with two through holes 101 with smooth inner walls, and two solid guide rails 2 respectively penetrate through each through hole 101, so that the rectangular block 3 slides relative to the solid guide rails 2; the two solid guide rails 2 have the same shape and size. In order to improve the utility model discloses hypersonic intake duct is from starting ability detection device's suitability extensive, and the end seat is adjustable for the position of stand, and then adjusts the high position of guide rail.
For the embodiments shown in the attached fig. 1 and 2, the experimental process is as follows:
before a shock tunnel experiment, a rectangular block 3 with proper mass, cross section size and spanwise length is selected, and two solid guide rails 2 which are the same in length and are symmetrically arranged in parallel to the axis of a flow channel in a hypersonic air inlet channel model penetrate through two through holes 101 which penetrate through the windward side of the rectangular block 3.
Will the utility model discloses a hypersonic intake duct is from starting ability detection device installs in the low reaches of hypersonic intake duct model, and is relative with the export of hypersonic intake duct model to make solid guide rail 2 and rectangle sprue 3 be in the interior runner of hypersonic intake duct model, ensure that guide rail base 4 keeps suitable distance with the export of hypersonic intake duct model, avoid guide rail base 4 to block up the export of hypersonic intake duct model.
Then, adjusting a guide rail base 4 to enable the central lines of the solid guide rail 2 and the rectangular block 3 to be coaxial with the axis of the inner flow channel of the hypersonic-speed air inlet channel model, and ensuring that the rectangular block 3 can slide to the buffer cushion block 5 along the solid guide rail 2; the position of the rectangular block 3 on the solid guide rail 2 is adjusted, and the distance between the rectangular block 3 and the hypersonic inlet channel model outlet is ensured to be appropriate.
After a shock tunnel experiment is started, at the initial stage of the effective experiment time of the shock tunnel, the rectangular blocking block 3 causes the blocking of an inner runner of the hypersonic air inlet channel, the hypersonic air inlet channel is not started, a plurality of periodic shock wave oscillation flow states appear, and meanwhile, under the action of the air flow of the inner runner of the hypersonic air inlet channel, the rectangular blocking block 3 moves towards the outlet of the hypersonic air inlet channel model along the guide rail in a quasi-one-dimensional motion mode.
In the effective experimental time of the shock tunnel, the rectangular blocking block 3 is blown out of an inner flow channel of the hypersonic air inlet channel, and after the inner flow channel of the hypersonic air inlet channel is recovered to be smooth, whether the hypersonic air inlet channel can be recovered to a starting state or not can be observed in the effective experimental time of the shock tunnel, and the self-starting capability of the hypersonic air inlet channel is detected.
After the shock tunnel experiment is finished, the rectangular blocking block 3 stays near the buffer cushion block 5, and the rectangular blocking block 3 is good in appearance and can be used repeatedly.
The hypersonic inlet channel self-starting capability detection device has simple structure and can be repeatedly used; when the flow field in the hypersonic inlet channel is shot directly, the motion rule of the blocking block can be obtained additionally and used for verifying the fluid-solid coupling problem.
It is right above that the utility model provides a hypersonic intake duct is from starting ability detection device has carried out detailed introduction. The principles and embodiments of the present invention have been explained herein using specific examples, and the above descriptions of the embodiments are only used to help understand the method and its core ideas of the present invention. It should be noted that, for those skilled in the art, without departing from the principle of the present invention, the present invention can be further modified and modified, and such modifications and modifications also fall within the protection scope of the appended claims.
Claims (10)
1. A hypersonic air inlet passage self-starting capability detection device is characterized by comprising:
one end of the guide rail is arranged in an inner flow channel of the hypersonic inlet channel model, and the guide rail is parallel to the axis of the inner flow channel;
the blocking block is slidably arranged on the guide rail; under the action of the airflow in the inner flow passage, the blocking block positioned in the inner flow passage can slide to the outside of the inner flow passage along the guide rail.
2. The hypersonic air inlet channel self-starting capability detection device of claim 1, wherein the inner flow channel and the guide rail are both horizontally arranged.
3. The hypersonic air intake duct self-startability detection device according to claim 1,
the hypersonic-speed air inlet channel model is a binary air inlet channel, the cross section of the inner flow channel is rectangular, and the block is a rectangular block; or,
the hypersonic inlet duct model is specifically an inward turning type inlet duct, just the cross section of the inner flow passage is circular, and the block is specifically a conical block.
4. The hypersonic air inlet channel self-starting capability detection device of claim 3, characterized in that the degree of blockage of the inner flow channel is between 50% and 80%.
5. The device for detecting the self-starting capability of the hypersonic air inlet passage according to any one of claims 1 to 4, wherein the guide rail is a hollow guide rail which can be used as a skin pressure probe, and a pressure sensor for detecting skin pressure in the inner flow passage is arranged at the other end of the guide rail.
6. The hypersonic air inlet channel self-starting capability detection device of claim 5, wherein the guide rail is provided with a buffer member for buffering the impact force when the block slides along the guide rail to the outside of the inner flow channel.
7. The hypersonic air inlet channel self-starting capability detection device of claim 6, further comprising an end seat for fixing the buffer member and the guide rail, wherein the end seat is provided with a stand column in the vertical direction, and the tail end of the stand column is fixed through a support base.
8. The hypersonic air inlet channel self-starting capability detection device as claimed in claim 6, wherein the block is provided with a through hole for the guide rail to pass through, and the inner wall of the through hole is smooth.
9. The hypersonic air inlet channel self-starting capability detection device of claim 7, wherein the position of the end mount relative to the upright is adjustable.
10. The hypersonic air inlet channel self-starting capability detection device of claim 8, characterized in that the number of the guide rails and the through holes is two, and the two guide rails have the same shape and size.
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106762149A (en) * | 2017-01-17 | 2017-05-31 | 中国科学技术大学 | A kind of hypersonic inlet self-starting energy force checking device |
| CN107830985A (en) * | 2017-10-11 | 2018-03-23 | 中国科学院力学研究所 | A kind of air intake duct determines congestion degree self-starting experimental rig |
| CN109443784A (en) * | 2018-11-30 | 2019-03-08 | 南京航空航天大学 | A kind of experimental rig that can adjust Sidewall-compression inlet contract ratio in real time |
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2017
- 2017-01-17 CN CN201720053829.7U patent/CN206448877U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106762149A (en) * | 2017-01-17 | 2017-05-31 | 中国科学技术大学 | A kind of hypersonic inlet self-starting energy force checking device |
| CN107830985A (en) * | 2017-10-11 | 2018-03-23 | 中国科学院力学研究所 | A kind of air intake duct determines congestion degree self-starting experimental rig |
| CN107830985B (en) * | 2017-10-11 | 2019-06-28 | 中国科学院力学研究所 | A kind of air intake duct determines congestion degree self-starting experimental rig |
| CN109443784A (en) * | 2018-11-30 | 2019-03-08 | 南京航空航天大学 | A kind of experimental rig that can adjust Sidewall-compression inlet contract ratio in real time |
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