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
- Publication number
- 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
- Authority
- CN
- China
- Prior art keywords
- guide rail
- sprue
- flow passage
- inner flow
- hypersonic inlet
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Landscapes
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
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 is related to hydrodynamics technology field, more particularly to a kind of hypersonic inlet self-starting ability inspection
Survey device.
Background technology
Using supersonic combustion (super burn) punching engine as the Air-breathing hypersonic vehicle of power set, for obtain compared with
Good performance, it is desirable to capture, the hypersonic inlet of compression member has good self-starting ability, that is, work as its air-flow
Cause after the inoperative factor elimination of air intake duct, it is not necessary to which extra auxiliary starter measure, air intake duct can also revert to starting
State (is restarted).However, free stream Mach number is too low, the angle of attack is excessive, the excessively high flight of air intake duct back-pressure and Manipulative Factors, all may be used
Air intake duct can be caused inoperative, have a strong impact on flight safety.The inoperative risk of air intake duct is met with flight test in order to reduce,
The self-starting ability of hypersonic inlet is detected in the wind tunnel experiment of ground, skill is tested as an important wind tunnel experiment
Art.
In view of hypersonic wind tunnel continuous difficulty for controllably changing free stream Mach number in a blowing experiment, generally exists
Under conditions of fixed free stream Mach number, air intake duct self-starting ability test experience is carried out.During the experiment of conventional hypersonic wind tunnel
Between it is longer, up to the second to tens of second-times, by actuation mechanisms such as traditional stepper motor, magnetic valves, carry out air intake duct from
Kinetic force test experience is relatively easy.There is scholar in conventional hypersonic wind tunnel, by the lip cover of mobile air intake duct, continuously change
Become the angle of attack of air intake duct, the choke plug of mobile air intake duct downstream simulation air intake duct back-pressure to bore, in air intake duct downstream injection high pressure gas
The measures such as body segment stream, first force air intake duct inoperative, then remove the inoperative factor of corresponding air intake duct, and air intake duct is recurred
Act to assert that air intake duct has the foundation of self-starting ability under similar conditions.
Ground impulse type wing tunnel test apparatus by representative of shock tunnel, it is relatively low with its construction and operating cost,
The method of operation flexibly, can provide the advantage of high-enthalpy flow for large scale air intake duct, in hypersonic aircraft research field hair
Wave important effect.However, the experimental period of shock tunnel is of short duration, generally only millisecond is conventional superb to several ms magnitude
Air intake duct self-starting ability detection technique in velocity of sound wind-tunnel, it is impossible to which direct " transplanting " is applied to shock tunnel.Therefore, shock wave wind
Hole faces the challenge of air intake duct self-starting ability test experience method.
In the prior art, some scholars force air inlet to be said by setting quick sliding valve at inlet throat
It is existing inoperative, and detect in shock tunnel the self-starting ability of air intake duct.However, this quick sliding valve, not only its skill
Art difficulty is big, and also needs to specially be designed for specific air intake duct configuration, and its versatility is limited.Also scholar passes through
Distance piece lower wall surface in air intake duct downstream is pre-placed lightweight tamper, first forces air intake duct inoperative, thing to be occluded occur
It is blown runner after air intake duct and recovers unimpeded, then detects the self-starting ability of air intake duct.Although this detection method is easy,
It is that the geometry of lightweight tamper is irregular, and the modes of emplacement of tamper is more random, and the movement law of tamper is indefinite,
The forms of motion of tamper can not be controlled effectively, and tamper is reused after cannot also reclaiming.These factors, result in blocking
Thing action effect it is repeatable poor.In addition, some scholars close air intake port using installation polyester fiber diaphragm in advance,
First force air intake duct inoperative；Then, polyester fiber diaphragm is ruptured using pulse high-energy igniter in experimentation, opens air inlet
Road is exported, and detects the self-starting ability of air intake duct.However, experiment needs to reinstall polyester fiber diaphragm this test device every time,
And certain puzzlement is brought to control mode and security using pulse high-energy igniter.Therefore, using shock tunnel as generation
In the impulse type wind-tunnel of table, the experimental method of hypersonic inlet self-starting ability detection needs further improve.
Utility model content
The purpose of this utility model is to provide a kind of hypersonic inlet self-starting energy force checking device, and this is hypersonic
Air intake duct self-starting energy force checking device may be reused, and can force air inlet at the initial stage of the effective experimental period of shock tunnel
Road is inoperative, and in the effective experimental period of shock tunnel examine hypersonic inlet self-starting ability.
To achieve the above object, the utility model provides a kind of hypersonic inlet self-starting energy force checking device, bag
Include：
Guide rail, one end of the guide rail in the inner flow passage of hypersonic inlet model, and the guide rail with it is described
The diameter parallel of inner flow passage；
Sprue, is slidingly disposed at the guide rail；In the presence of the inner flow passage interior air-flow, in the inner flow passage
The sprue can be slid into along the guide rail outside the inner flow passage.
The hypersonic inlet self-starting energy force checking device provided relative to above-mentioned background technology, the utility model,
One end of guide rail is located in the inner flow passage of hypersonic inlet model, and sprue is slidingly disposed at guide rail；In shock tunnel
Before middle beginning hypersonic inlet self-starting ability test experience, sprue is located in inner flow passage, and sprue causes the stifled of inner flow passage
Plug, air intake duct appearance is inoperative, and multiple periodic shock wave oscillation fluidised forms occurs；Meanwhile, inner flow passage of the sprue in air intake duct
Under airflow function, moved along guide rail in quasi-one-dimensional form to the outlet of air intake duct；In effective experimental period of shock tunnel
Interior, sprue is blown the outlet of air intake duct；The inner flow passage of air intake duct recovers unimpeded, then can the shock tunnel effective reality
Test in the time, can observation air intake duct return to starting state, detect the self-starting ability of air intake duct；Shock tunnel experiment terminates
Afterwards, sprue is still located on guide rail, and the outward appearance of sprue is good, can reuse.Core of the present utility model is, utilizes
Guide rail limits the direction of motion of sprue, and then air intake duct self-starting ability can be detected；And the sprue after detecting
It may be reused, sprue is pushed into inner flow passage along guide rail；It is arranged such, can not only controls the motion shape of sprue
Formula, and sprue can be reclaimed, reuse it, it is ensured that the repeatability of sprue ponding process.
Preferably, the inner flow passage is horizontally disposed with the guide rail.
Preferably,
The hypersonic inlet model is specially two dimensional inlet, and the cross section of the inner flow passage is rectangular, institute
It is specially rectangle sprue to state sprue；Or,
The hypersonic inlet model is specially interior rotatable air intake duct, and the circular in cross-section of the inner flow passage,
The sprue is specially circular cone sprue.
Preferably, the congestion degree of the inner flow passage is between 50%~80%.
Preferably, the guide rail be specially can be to the hollow guide rail that is used as skin backing pressure probe, and the guide rail
The other end be provided with pressure sensor to detect the skin backing pressure in the inner flow passage.
Preferably, the guide rail is provided with to buffer when the sprue along the guide rail slides into when institute outside the inner flow passage
The bolster for the impulsive force having.
Preferably, in addition to the end seat to the fixed bolster and the guide rail, the end seat is in vertical direction
Column is provided with, and the end of the column is fixed by bracket base.
Preferably, the sprue is provided with the through hole passed through for the guide rail, and the inner wall smooth of the through hole.
Preferably, the end seat is adjustable relative to the position of the column.
Preferably, the number of the guide rail and the through hole is two, and the geomery of two guide rails is identical.
Brief description of the drawings
, below will be to embodiment in order to illustrate more clearly of the utility model embodiment or technical scheme of the prior art
Or the accompanying drawing used required in description of the prior art is briefly described, it should be apparent that, drawings in the following description are only
It is embodiment of the present utility model, for those of ordinary skill in the art, on the premise of not paying creative work, also
Other accompanying drawings can be obtained according to the accompanying drawing of offer.
A kind of hypersonic inlet self-starting energy force checking device that Fig. 1 is provided by the utility model embodiment shows
It is intended to；
Fig. 2 is to be not provided with the schematic diagram of two dimensional inlet in Fig. 1；
Another hypersonic inlet self-starting energy force checking device that Fig. 3 is provided by the utility model embodiment
Schematic diagram.
Wherein：
In Figure of description 1：1- two dimensional inlets, 2- solid guide rails, 3- rectangles sprue, 4- guiderail bases, 5- cushion pads
Block, 6- supports, 7- bracket bases；
In Figure of description 2：2- solid guide rails, 3- rectangles sprue, 101- through holes；
In Figure of description 3：Rotatable air intake duct, 103- hollow guide rails, 104- circular cones sprue, 105- hollow guide rails in 102-
Base, 106- buffer units, 107- vertical racks, 108- pressure sensors.
Embodiment
Below in conjunction with the accompanying drawing in the utility model embodiment, the technical scheme in the utility model embodiment is carried out
Clearly and completely describe, it is clear that described embodiment is only a part of embodiment of the utility model, rather than whole
Embodiment.Based on the embodiment in the utility model, those of ordinary skill in the art are not under the premise of creative work is made
The every other embodiment obtained, belongs to the scope of the utility model protection.
In order that those skilled in the art more fully understand the utility model scheme, below in conjunction with the accompanying drawings and specifically
The utility model is described in further detail for embodiment.
Refer to Fig. 1, Fig. 2 and Fig. 3, a kind of hypersonic inlet that Fig. 1 is provided by the utility model embodiment from
The schematic diagram of starting capability detection means；Fig. 2 is to be not provided with the schematic diagram of two dimensional inlet in Fig. 1；Fig. 3 is that the utility model is real
Apply the schematic diagram for another hypersonic inlet self-starting energy force checking device that example is provided.
A kind of hypersonic inlet self-starting energy force checking device that the utility model is provided, mainly includes guide rail and stifled
Block.One end of guide rail is in the inner flow passage of hypersonic inlet model, and the diameter parallel of guide rail and inner flow passage；And block up
Block is slidingly disposed at guide rail；In the presence of inner flow passage interior air-flow, the sprue in inner flow passage can slide into along guide rail
Outside the inner flow passage.
Hypersonic inlet model can be two dimensional inlet or Sidewall-compression inlet, it is three-dimensional in it is rotatable enter
Air flue, the inner flow passage of hypersonic inlet model includes compression section and distance piece in air intake duct.The rigidity of guide rail should be good, its
External diameter is smaller, the smooth outer surface of guide rail, preferably straight guide rail, and the cross section of guide rail can be circular or annular.Sprue
For the rigid sprue of the less geometric shape rule of quality；Sprue is shaped as square, cuboid, triangular prism, cylinder, circle
Cone or spherosome；The cross sectional dimensions of sprue, span-wise length are both less than the cross section of hypersonic inlet model inner flow passage
Size, span-wise length；, can be according to the duration of congestion and height of shock tunnel requirement of experiment for the quality and geometric shape of sprue
The inner flow passage geometric format of Supersonic Inlet model is chosen.
Start in shock tunnel before hypersonic inlet self-starting ability test experience, sprue is located in inner flow passage,
Now sprue causes the blocking of inner flow passage, and air intake duct appearance is inoperative, and multiple periodic shock wave oscillation fluidised forms occurs；Together
When, sprue is moved along guide rail under the inner flow passage airflow function of air intake duct in quasi-one-dimensional form to the outlet of air intake duct；
In effective experimental period of shock tunnel, sprue is blown the outlet of air intake duct；The inner flow passage of air intake duct recovers unimpeded, then may be used
In effective experimental period of the shock tunnel, can observation air intake duct return to starting state, detection air intake duct from
Kinetic force；After shock tunnel experiment terminates, sprue is still located on guide rail, and the outward appearance of sprue is good, can reuse.
Core of the present utility model is, the direction of motion of sprue is limited using guide rail, and then can be to air intake duct from
Kinetic force is detected；And the sprue after detecting be may be reused, and sprue is pushed into inner flow passage along guide rail；
It is arranged such, can not only controls the forms of motion of sprue, and sprue can be reclaimed, reuses it, it is ensured that
The repeatability of sprue ponding process.According to different test needs, inner flow passage can be horizontally disposed with guide rail, can also
Inner flow passage and guide rail are inclined relative to horizontal into certain angle to set.
A kind of hypersonic inlet self-starting ability that Figure of description 1 is provided by the utility model embodiment is detected
The schematic diagram of device, another hypersonic inlet self-starting ability that accompanying drawing 3 is provided by the utility model embodiment is examined
Survey the schematic diagram of device.
In Figure of description 1, the inner flow passage cross section of two dimensional inlet 1 is rectangle, and the exhibition of two dimensional inlet 1 is to width
54mm, is highly 10mm；Solid guide rail 2 is two external diameter 2mm length identical rod iron, and two solid guide rails 2 are parallel to entering
The inner flow passage axis of air flue and it is symmetrical arranged, the exhibitions of two solid guide rails 2 is to spacing 20mm；Rectangle sprue 3 is rectangular shape,
Physical dimension is 6mm (flow direction) × 6mm (transverse direction) × 50mm (open up to), and quality is 2.05g, in the windward side of rectangle sprue 3
Heart line both sides are symmetrical arranged two internal diameter 2.5mm, and spacing 20mm through hole, the via through holes of rectangle sprue 3 penetrate solid guide rail 2, and
It can be slided along solid guide rail 2, the outlet 40mm of the windward side of rectangle sprue 3 apart from air intake duct 1.Guiderail base 4 be blunt wedge-
The assembly of rectangular parallelepiped form, for fixing and supporting solid guide rail 2；Cushion pad 5 is the thick rectangle silica gel pads of 2mm, tightly
Close to guiderail base 4；Support 6 is threaded rod, for fixed and supporting guide base 4；Bracket base 7 is rectangular shape, is used
In fixed support 6.
Its operation principle is that, at the initial stage of the effective experimental period of shock tunnel, rectangle sprue 3 causes two dimensional inlet 1
Inner flow passage is blocked；Two dimensional inlet 1 occurs inoperative, and multiple periodic shock wave oscillation fluidised forms occurs；Meanwhile, rectangle sprue
3 under the inner flow passage airflow function of two dimensional inlet 1, along solid guide rail 2 in quasi-one-dimensional form going out to two dimensional inlet 1
Mouth is mobile；In effective experimental period of the shock tunnel, rectangle sprue 3 is blown the outlet of two dimensional inlet 1；Binary is entered
The inner flow passage of air flue 1 recovers unimpeded, then can observe the energy of two dimensional inlet 1 in effective experimental period of the shock tunnel
It is no to return to starting state, detect the self-starting ability of two dimensional inlet 1；After the shock tunnel experiment terminates, rectangle sprue 3
On solid guide rail 2, the outward appearance of rectangle sprue 3 is good, can reuse.The above-mentioned embodiment rectangular for inner flow passage,
Certainly, the specific size of above-mentioned all parts can be decided according to the actual requirements with position relationship, however it is not limited to described above.
Figure of description 2 gives the He of solid guide rail 2 in more detail to be not provided with the schematic diagram of two dimensional inlet in Fig. 1
The geometric position of rectangle sprue 3, the rectangle sprue 3 is provided with two through holes passed through for described two solid guide rails 2
101, and the inner wall smooth of described two through holes 101.In specific embodiment, the internal diameter of two through holes 101 is all 2.5mm, two
The exhibition of through hole 101 to spacing be 20mm.Operation principle：Rectangle sprue 3 penetrates two solid guide rails 2, square by two through holes 101
Shape sprue 3 can be slided along two solid guide rails 2.
In Figure of description 3, compared with the embodiment of accompanying drawing 1, the method used in both is similar, and the air intake duct of application is by two
First air intake duct has changed interior rotatable air intake duct into.The test device of hypersonic interior rotatable air intake duct self-starting ability detection includes：
Interior rotatable air intake duct 102, hollow guide rail 103, circular cone sprue 104, hollow guide rail base 105, buffer unit 106, vertical rack
107 and pressure sensor 108.
Wherein, the circle that the outlet of interior rotatable air intake duct 102 is internal diameter 35mm；Hollow guide rail 103 is that an external diameter is
5mm, internal diameter are 3mm steel pipe, also serve as skin backing pressure probe and use；Circular cone sprue 104 is 20 degree of semi-cone angle, base diameter 24mm's
Circular cone, its quality is 5g；Internal diameter 5.2mm through hole is set at the axis of circular cone sprue 104, and circular cone sprue 104 is through described logical
Hole penetrates hollow guide rail 103, it is possible to slided along hollow guide rail 103, rotatable air intake duct in the vertex distance of circular cone sprue 104
102 outlet 45mm；Hollow guide rail base 105 is the assembly of blunt wedge-rectangular parallelepiped form, for fixing and supporting hollow guide rail
103, and be connected with vertical rack 107；Buffer unit 106 is the thick silica gel pads of 2mm, is close to hollow guide rail base 105；It is perpendicular
Straight bracket 107 is the threaded rod of two equal lengths, for fixing and supporting hollow guide rail base 105；Pressure sensor 108 is pacified
Bottom loaded on hollow guide rail base 105, the pressure-sensing device of pressure sensor 108 is with also serving as the sky that skin backing pressure probe is used
The endoporus of heart guide rail 103 is connected, for measuring skin backing pressure.
The operation principle of the embodiment is similar to the above, and both main distinctions are, hollow guide rail 103 also serves as skin backing pressure
Probe is used, and pressure sensor 108 can be inside in the experimentation of the rotatable self-starting ability of air intake duct 102 detection, in monitoring
The change of the rotatable inner flow passage skin backing pressure of air intake duct 102.By above-mentioned as can be seen that in the first of the effective experimental period of shock tunnel
Phase, sprue is located in inner flow passage, and then forms the blocking to inner flow passage；According to actual needs, can be by the congestion degree of inner flow passage
Control is between 50%~80%, to be tested.Certainly, according to actual needs, the congestion degree of inner flow passage can also be it
His number range.
In Figure of description 3, guide rail is specially can be to the hollow guide rail 103 that is used as skin backing pressure probe, and leads
The other end of rail is provided with the pressure sensor 108 to detect the skin backing pressure in inner flow passage.And for given by Figure of description 1
Embodiment, its guide rail can also be hollow guide rail 103, and its function is identical with effect.
Hypersonic inlet self-starting energy force checking device of the present utility model, fixes bolster using end seat and leads
Rail, end seat in the vertical direction is provided with column, and the end of column is fixed by bracket base.By Figure of description 1 to attached
Fig. 3 can be seen that Figure of description 1 and in Figure of description 2, guiderail base 4 is end seat, and cushion pad 5 is bolster,
Support 6 is column；In Figure of description 3, hollow guide rail base 105 is end seat, and buffer unit is bolster, vertical branch
Frame 107 is column.Certainly, in order to realize the fixation to guide rail, other devices can also be used, however it is not limited to described herein.
In order to realize that sprue is slidingly disposed at guide rail, sprue is provided with for leading to that guide rail is passed through by the utility model
Hole, and the inner wall smooth of through hole；Such as Figure of description 2, through hole 101 of the rectangle sprue 3 provided with two inner wall smooths, two solid
Guide rail 2 is each passed through each through hole 101, realizes slip of the rectangle sprue 3 relative to solid guide rail 2；The shape of two solid guide rails 2
Shape size is identical.In order to improve the widely applicable property of the utility model hypersonic inlet self-starting energy force checking device, end
Seat is adjustable relative to the position of column, and then adjusts the height and position of guide rail.
For the embodiment given by Figure of description 1 and accompanying drawing 2, experimentation is as follows：
Before shock tunnel experiment, quality, cross sectional dimensions and the suitable rectangle sprue 3 of span-wise length should be selected first,
Through two on the windward side of rectangle sprue 3 through holes 101 run through, length identical is penetrated parallel in hypersonic inlet model
Two solid guide rails 2 that runner axisymmetrical is set.
Hypersonic inlet self-starting energy force checking device of the present utility model is installed on hypersonic inlet mould
The downstream of type, and it is relative with the outlet of hypersonic inlet model, and solid guide rail 2 and rectangle sprue 3 is in high ultrasound
In the inner flow passage of fast air intake duct model, it is ensured that the outlet of guiderail base 4 and hypersonic inlet model keeps suitable distance,
Guiderail base 4 is avoided to block the outlet of hypersonic inlet model.
Then guiderail base 4 is adjusted, makes the center line and hypersonic inlet model of solid guide rail 2 and rectangle sprue 3
Inner flow passage axis coaxle, it is ensured that rectangle sprue 3 can be slid at cushion pad 5 along solid guide rail 2；Adjust rectangle sprue
3 position on solid guide rail 2, it is ensured that the distance of rectangle sprue 3 and hypersonic inlet mold exit is suitable.
After shock tunnel experiment is started, at the initial stage of the effective experimental period of shock tunnel, rectangle sprue 3 causes high ultrasound
The inner flow passage of fast air intake duct is blocked, and hypersonic inlet occurs inoperative, and multiple periodic shock wave oscillation fluidised forms occurs,
Meanwhile, in the presence of hypersonic inlet inner flow passage air-flow, rectangle sprue 3 is along the guide rail, with quasi- motion in one dimension
Form, is moved to the outlet of hypersonic inlet model.
In the effective experimental period of shock tunnel, rectangle sprue 3 is blown the inner flow passage of hypersonic inlet, high ultrasound
After the inner flow passage of fast air intake duct recovers unimpeded, then hypersonic air inlet can be observed in effective experimental period of shock tunnel
Can road return to starting state, detect the self-starting ability of hypersonic inlet.
After shock tunnel experiment terminates, rectangle sprue 3 is rested near the cushion pad 5, and the outward appearance of rectangle sprue 3 is good
It is good, it may be reused.
Hypersonic inlet self-starting energy force checking device of the present utility model, it is simple in construction, it is reusable；When straight
When tapping into the shooting of row hypersonic inlet flow field, the characteristics of motion of sprue can be additionally obtained, for fluid structurecoupling problem
Verification.
Detailed Jie has been carried out to hypersonic inlet self-starting energy force checking device provided by the utility model above
Continue.Specific case used herein is set forth to principle of the present utility model and embodiment, and above example is said
It is bright to be only intended to help and understand method of the present utility model and its core concept.It should be pointed out that for the common of the art
For technical staff, on the premise of the utility model principle is not departed from, can also to the utility model carry out it is some improvement and
Modification, these are improved and modification is also fallen into the utility model scope of the claims.
Claims (10)
1. a kind of hypersonic inlet self-starting energy force checking device, it is characterised in that including：
Guide rail, one end of the guide rail is in the inner flow passage of hypersonic inlet model, and the guide rail and the interior stream
The diameter parallel in road；
Sprue, is slidingly disposed at the guide rail；In the presence of the inner flow passage interior air-flow, the institute in the inner flow passage
Stating sprue can slide into outside the inner flow passage along the guide rail.
2. hypersonic inlet self-starting energy force checking device according to claim 1, it is characterised in that the interior stream
Road is horizontally disposed with the guide rail.
3. hypersonic inlet self-starting energy force checking device according to claim 1, it is characterised in that
The hypersonic inlet model is specially two dimensional inlet, and the cross section of the inner flow passage is rectangular, described stifled
Block is specially rectangle sprue；Or,
The hypersonic inlet model is specially interior rotatable air intake duct, and the circular in cross-section of the inner flow passage, described
Sprue is specially circular cone sprue.
4. hypersonic inlet self-starting energy force checking device according to claim 3, it is characterised in that the interior stream
The congestion degree in road is between 50%~80%.
5. the hypersonic inlet self-starting energy force checking device according to Claims 1 to 4 any one, its feature exists
Being specially in, the guide rail can be to the hollow guide rail that is used as skin backing pressure probe, and the other end of the guide rail is provided with
Pressure sensor to detect the skin backing pressure in the inner flow passage.
6. hypersonic inlet self-starting energy force checking device according to claim 5, it is characterised in that the guide rail
Provided with the bolster to buffer the impulsive force having when the sprue is slid into outside the inner flow passage along the guide rail.
7. hypersonic inlet self-starting energy force checking device according to claim 6, it is characterised in that also including use
With the end seat of the fixed bolster and the guide rail, the end seat in the vertical direction is provided with column, and the column
End is fixed by bracket base.
8. hypersonic inlet self-starting energy force checking device according to claim 6, it is characterised in that the sprue
Provided with the through hole passed through for the guide rail, and the inner wall smooth of the through hole.
9. hypersonic inlet self-starting energy force checking device according to claim 7, it is characterised in that the end seat
Position relative to the column is adjustable.
10. hypersonic inlet self-starting energy force checking device according to claim 8, it is characterised in that described to lead
The number of rail and the through hole is two, and the geomery of two guide rails is identical.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720053829.7U CN206448877U (en) | 2017-01-17 | 2017-01-17 | A kind of hypersonic inlet self-starting energy force checking device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720053829.7U CN206448877U (en) | 2017-01-17 | 2017-01-17 | A kind of hypersonic inlet self-starting energy force checking device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206448877U true CN206448877U (en) | 2017-08-29 |
Family
ID=59671765
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720053829.7U Active CN206448877U (en) | 2017-01-17 | 2017-01-17 | A kind of hypersonic inlet self-starting energy force checking device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206448877U (en) |
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 |
-
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 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106762149B (en) | A kind of hypersonic inlet self-starting energy force checking device | |
| CN206448877U (en) | A kind of hypersonic inlet self-starting energy force checking device | |
| CN107830985B (en) | A kind of air intake duct determines congestion degree self-starting experimental rig | |
| CN103939217B (en) | Rectangular cross-section hypersonic change geometry intake duct and design method and working method | |
| Boyce et al. | The HyShot scramjet flight experiment-flight data and CFD calculations compared | |
| CN104132811B (en) | Ramjet engine air inlet starting hesitation characteristic test apparatus | |
| CN102507203B (en) | Shockwave wind tunnel-based self-starting test device for hypersonic air inlet channel | |
| CN112798214B (en) | Testing device and testing method capable of controlling icing area | |
| JP5605537B2 (en) | Supersonic wind tunnel start / stop load reduction method and supersonic wind tunnel | |
| CN113945355A (en) | Air inlet duct wind tunnel test simulation system under shock wave | |
| CN114216649B (en) | Hypersonic separation flow control test device and method | |
| CN109946298A (en) | A kind of experimental provision for high undersea hydrostatic pressures gas ice-breaking experiment | |
| Li et al. | A novel test of starting characteristics of hypersonic inlets in shock tunnel | |
| CN109900177A (en) | A kind of air gun device for high undersea hydrostatic pressures gas ice-breaking experiment | |
| Bower et al. | High-frequency excitation active flow control for high-speed weapon release (HIFEX) | |
| CN209148459U (en) | A kind of dynamic test system for testing two-dimensional structure material shock resistance | |
| Fei et al. | Aerodynamic characteristics of store during lateral jet assisted separation from cavity using free drop technique | |
| Leyva et al. | On the impact of injection schemes on transition in hypersonic boundary layers | |
| CN208026450U (en) | Gas driven generator blowing experiment device | |
| CN202141577U (en) | Radiator test device | |
| CN105717270B (en) | Gel propellant list drop second-time breakage experimental provision | |
| Ali et al. | Flowfield characteristics of oblique shocks generated using microjet arrays | |
| Vnuchkov et al. | Experimental study of a cylindrical air inlet designed on the basis of plane flows | |
| Vedrtnam et al. | Variation of drag coefficient, wall static pressure and secondary flow over passenger car | |
| Do et al. | The influence of boundary layers on supersonic inlet unstart |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |