CN107421710A - A kind of rocket launching combustion gas stream shock simulation experimental rig - Google Patents
A kind of rocket launching combustion gas stream shock simulation experimental rig Download PDFInfo
- Publication number
- CN107421710A CN107421710A CN201710593743.8A CN201710593743A CN107421710A CN 107421710 A CN107421710 A CN 107421710A CN 201710593743 A CN201710593743 A CN 201710593743A CN 107421710 A CN107421710 A CN 107421710A
- Authority
- CN
- China
- Prior art keywords
- combustion gas
- gas stream
- test
- conical head
- test board
- 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.)
- Granted
Links
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/08—Aerodynamic models
Landscapes
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- General Physics & Mathematics (AREA)
- Testing Of Engines (AREA)
Abstract
The invention discloses a kind of rocket launching combustion gas stream shock simulation experimental rig, the device includes experiment platen, test stand, test board, conical head guide rod, engine and fixed support, the upper surface of the experiment platen is provided with the chute of bar shaped, the bottom of the test stand is placed in the chute, the experiment platen and the test stand are bolted to connection, the test board is fixed on the test stand, the conical head guide rod has conical head front end and blunt end, the conical head front end contradicts the lateral surface of the test board, the blunt end is connected with the spout of the engine, the medial surface of the test board is fixedly connected with sensor, the engine is fixed on fixed support.Rocket launching combustion gas stream shock simulation experimental rig of the present invention has outstanding advantages of with short production cycle, the testing time is short, simple in construction, cost is relatively low.
Description
Technical field
The present invention relates to Combustion-gas dynamics technical field, and more specifically, the present invention is a kind of rocket launching combustion gas
Flow shock simulation experimental rig.
Background technology
Combustion-gas dynamics are one of professional aerodynamics subdisciplines, with aerodynamics as space technology
" commander of an advance unit or vanguard " function is the same, and property in advance is played in rocket launching technical field particularly rocket launching technical research and is checked on work
With.Combustion-gas dynamics instruct lift-off technology research and development to be mainly reflected in two aspects：First, in lift-off technology demonstration rank
Section, there is provided influence the parameters such as emission system, the impact of the combustion gas stream of rocket, ablation power, hot total environment, and clear and definite combustion gas stream is rushed
Hit, ablation power and hot specific environment distribution and intensity size；Second, in the specific development phase of lift-off technology, clearly influence
The parameter such as emission system, the specific equipment of rocket, the impact of instrument combustion gas stream, ablation power, hot specific environment, gas is instructed for supporting
Dynamic layout designs, structure heat protection design and Structural Strength Design.
Combustion-gas dynamics development is close with theory relation, is even more inseparable with experiment.Existing detection combustion gas stream
The pilot system that field influences is complicated, and the pilot system test period of Calibration Theory result is longer, is mainly shown as：It is first, conventional
The pilot system that detection combustion gas stream influences is made up of rocket engine and flat pad, and combustion gas stream impact test is to take experiment
Carrying experiment in the subscale test or emission process of system：It is according to subscale test, it is necessary to rocket engine is flat with transmitting
Platform carries out scaled down, production cycle length and system complex according to design point；Tested according to carrying, it is necessary to be closed finding
The long-time that different system is carried out under suitable launch mission is coordinated, and the experimental test cycle is longer；Second, the high temperature of combustion gas stream, high speed
It is mutually extremely complex with composition, to reduce influence of the combustion gas stream to flat pad, often flat pad is optimized repeatedly, needed
The influence under different combustion gas stream effects is compared, theoretical calculation cycle time is longer, is the correctness of proof theory result of calculation, if
The subscale test of combustion gas stream influence is carried out again or carries verification experimental verification, and it will necessarily increase considerably the lead time, add and grind
Send out input cost.The rapidity and again of rocket launching combustion gas stream shock simulation experimental study is can be seen that based on the reason for above
The property wanted is self-evident.
Therefore, based on lead time length, test period existing for existing rocket launching combustion gas stream shock simulation pilot system
How the problems such as length, calculating cycle are long, test system architecture is complicated, Innovation Input cost is high, reduce the lead time and test is all
Phase, the structure of short form test system, become those skilled in the art's technical problem urgently to be resolved hurrily and the emphasis studied all the time.
The content of the invention
To solve lead time length, test period existing for existing rocket launching combustion gas stream shock simulation pilot system
The problems such as length, calculating cycle are long, test system architecture is complicated, Innovation Input cost is high, the present invention innovatively propose a kind of fiery
Arrow launches combustion gas stream shock simulation experimental rig, effectively instead of existing subscale test scheme and carries testing program, so as to
Long test period existing for prior art, calculating cycle length, pilot system knot are efficiently solved by brief test apparatus structure
The problems such as structure is complicated, Innovation Input cost is high.
To realize above-mentioned technical purpose, the invention discloses a kind of rocket launching combustion gas stream shock simulation experimental rig,
Described device includes experiment platen, test stand, test board, conical head guide rod, engine and fixed support, the experiment platen
Upper surface be provided with the chute of bar shaped, the bottom of the test stand is placed in the chute, the experiment platen and the experiment
Frame is bolted to connection, and the test board is fixed on the test stand, before the conical head guide rod has conical head
End and blunt end, the conical head front end contradict the lateral surface of the test board, the blunt end and the engine
Spout connects, and the medial surface of the test board is fixedly connected with sensor, and the engine is fixed on the fixed support.
Based on said structure, the present invention significantly reduces research and development on the premise of combustion gas stream shock simulation function is realized
Time, calculate time and test period, and the simulation test device of the present invention also have simple structure, easily implement, cost compared with
Low outstanding advantages.
Further, described device also includes adjusting screw, the adjusting screw simultaneously with the test board, the experiment
Frame is fixedly connected.
The present invention innovatively adjusts the angle of pitch and roll angle of test board by adjusting screw, so as to realize that the present invention can be with
Quickly adjustment combustion gas stream impact attitude angle, shock point and impact distance, so that quick Calibration Theory indicates result.
Further, described device also includes height adjusting pads piece, and the height adjusting pads piece is located at the experiment platen
Between the test stand.
Present invention innovation adjusts the height of test board by height adjusting pads piece, and more rockets are impacted so as to realize
Situation is effectively simulated.
Further, described device also includes single skirt, and the sensor is connected with one end of single skirt, the list
The other end of skirt is fixedly connected with the medial surface of the test board.
Further, described device also includes being used for connecting the crossover sub of sensor and single skirt, the sensor with
One end connection of the crossover sub, the other end of the crossover sub are fixedly connected with single skirt.
By single skirt and crossover sub, sensor of the present invention can truly, reliably obtain combustion gas stream impact
Relevant information, and can, which reaches, to be avoided burn sensor and protects the technical purpose of sensor.
Further, neck is provided with the test stand, the test board is positioned in the neck, the test board
On be provided with multiple instrument connections, single skirt and the conical head guide rod are directed at same instrument connection；The test board has more
Kind specification, the test board of different size have the different instrument connection of arrangement mode；The conical head guide rod also has a variety of rule
Lattice, the conical head front end of the conical head guide rod of different size have different cone angles.
By being related to the test board of plurality of specifications and the guide rod of plurality of specifications so that the present invention is applied to more kinds of situations
Under rocket launching combustion gas stream shock simulation, and can quickly and reliably change test structure according to newest simulated conditions, so as to
Improve the application of the present invention.
Further, the center line of conical head guide rod described in the spout pair of the engine, so as to realize to combustion gas
Stream impact information more precisely obtains
Further, the sensor includes at least one of pressure sensor, temperature sensor, realizes to combustion gas stream
The collection of impulsive force and combustion gas stream temperature information.
Further, the upper surface of the experiment platen is provided with two parallel bar shaped chutes, so that test stand is more
It is stably fixed to test on platen, and can be along bar shaped slide.
Further, the engine is kerosene engine.
Beneficial effects of the present invention are：Rocket launching combustion gas stream shock simulation experimental rig of the present invention has the production cycle
Short, outstanding advantages of testing time is short, simple in construction, cost is relatively low, it can quickly detect the impact of transmitting combustion gas stream, ablation
The parameters such as power, thermal environment condition, and can rapidly obtain the theoretical indication of the transmitting combustion gas stream parameter verification such as pressure, temperature, hot-fluid
As a result, fast and effective support is provided for Modifying model optimization, algorithm improvement and result verification.
Brief description of the drawings
Fig. 1 is the structural representation of rocket launching combustion gas stream shock simulation experimental rig.
Fig. 2 is the structural representation of test board.
Fig. 3 is the attachment structure schematic diagram of sensor and single skirt.
In figure,
1st, platen is tested；2nd, test stand；3rd, test board；4th, conical head guide rod；5th, engine；6th, fixed support；7th, it is single
Skirt；8th, crossover sub；9th, sensor；10th, adjusting screw；11st, height adjusting pads piece.
Embodiment
The rocket launching combustion gas stream shock simulation experimental rig of the present invention is carried out in detail with reference to Figure of description
Explanation and illustration.
Embodiment one：The present invention is used for adjustable gas-combustion flow field quick detection and verification
As shown in Figure 1, 2, 3, the present invention is based on flat emission system, and innovation have developed a kind of rocket launching combustion gas stream
Shock simulation experimental rig, the device include experiment platen 1, test stand 2, test board 3, conical head guide rod 4, engine 5 and
Fixed support 6, the upper surface of experiment platen 1 are provided with the chute of bar shaped, and in the present embodiment, the upper surface of experiment platen 1 is provided with two
Individual parallel bar shaped chute, the bottom of test stand 2 are placed in chute, and test stand 2 includes the two L-shaped side plates and horizontal stroke to mutually claiming
Beam, crossbeam is set between two L-shaped side plates, crossbeam both ends are fixed respectively with two L-shaped side plates, two L-shaped side plate bottoms and examination
The chute matching for two bar shapeds tested on frame 2, and can be slided by the mating structure, test stand 2 on experiment platen 1, still
After the regulation of the distance of test board 3 and engine 5, test platen 1 and test stand 2 is bolted to connection, test board 3
It is fixed on test stand 2, conical head guide rod 4 has conical head front end and blunt end, and conical head front end contradicts test board 3
Lateral surface, blunt end are connected with the spout of engine 5, more specifically, neck are provided with test stand 2, test board 3 is placed
In in neck, being provided with multiple instrument connections on test board 3, single skirt 7 and conical head guide rod 4 are directed at same instrument connection；Test board 3
With plurality of specifications, according to the needs of simulated test, the test board 3 of different size has the different instrument connection of arrangement mode；Cone
Forming head guide rod 4 also has plurality of specifications, and there is different cone angles to survey for the conical head front end of the conical head guide rod 4 of different size
The medial surface of test plate (panel) 3 is fixedly connected with sensor 9, and in the present embodiment, sensor 9 is included in pressure sensor 9, temperature sensor 9
At least one, engine 5 is fixed on fixed support 6, the center line of the spout centering conical head guide rod 4 of engine 5, hair
Motivation 5 is kerosene engine.
The present embodiment is in implementation process, the first step, is fixed engine 5 with bolt using fixed support 6.Second step,
Conical head guide rod 4 straight section one end (i.e. blunt end) centering is connected at the jet pipe of engine 5.3rd step, test stand 2
It is placed on experiment platen 1, by the slant setting of test board 3 required for testing in the neck of test stand 2.4th step, then
Test stand 2 is fixed on by experiment platen 1 by connecting bolt.Test stand 2 is arranged on the experiment platen 1 with bar shaped chute
On, the movement of test stand 2 is realized using bar shaped chute, so as to quickly adjust the combustion gas stream impact of test board 3 and engine 5 away from
From；By changing the conical head angle of the setting angle of test board 3 and guide rod on test stand 2, survey can be quickly adjusted
The combustion gas stream angle of attack of test plate (panel) 3 and engine 5；, can quickly test engine 5 be by changing different test boards 3
With the test data of different zones under combustion gas stream percussion；Whole experimental rig is bolted, and energy quick obtaining is not
With the parameter under transmitting gas flow field, Calibration Theory indication result.
Although actual transmitting device structure is complicated, combustion gas stream shock environment is not quite similar, this experimental rig can be with
Using simple pilot system can quick detection transmitting combustion gas stream impact, ablation power, thermal environment condition, and energy quick obtaining is not
With the parameter under transmitting gas flow field, the parameter includes pressure, temperature, hot-fluid etc., so as to the theoretical indication result of rapid verification.
Embodiment two：The present invention is used for combustion gas stream impact posture rapid verification
As shown in Figure 1, 2, 3, on the basis of embodiment one, the device also includes adjusting screw 10, and adjusting screw 10 is same
When be fixedly connected with test board 3, test stand 2, behind the angle of inclination for determining test board transverse and longitudinal, the present invention passes through adjusting screw
10 lock onto test board 3 on test stand 2.Moreover, the device also includes height adjusting pads piece 11, height adjusting pads piece 11 is set
Between experiment platen 1 and test stand 2, the height of test stand can be adjusted by changing the number of height adjusting pads piece 11, entered
And adjust the height of test board 3.By being connected the structure of conical head guide rod 4 of centering, binding test plate 3 with the spout of engine 5
Angle adjustment on test stand 2.
In the present embodiment implementation process, the first step, puffer 5 is fixed with bolt using fixed support 6, by conical head
Straight section one end centering of guide rod 4 is connected at the jet pipe of puffer 5.Second step, test stand 2 are placed on experiment platen 1
On, then by the slant setting of test board 3 required for testing in the neck of test stand 2.3rd step, it will be tested by connecting bolt
Frame 2 is fixed on experiment platen 1.4th step, by height adjustment pad piece and adjusting screw 10 adjust test board 3 short transverse and
Lateral attitude, the conical head bus of conical head guide rod 4 is set to be contacted with test board 3, and cone and instrument connection center superposition.Will
Straight-bar one end of conical head guide rod 4 of required length and angle is connected with the nozzle pluggage centering of engine 5, utilizes test stand
2 on experiment platen 1 slip of strip hole chute, height adjusting pads piece 11 and the length adjustment of adjusting screw 10 realize test board
3 fore-and-aft directions, short transverse and horizontal regulation and the regulation for rushing in the angle of pitch and roll angle, finally make the bus of conical head
With the contact of incline plane of test board 3, and cone and instrument connection center superposition on test board 3.
In order to verify the correctness of the theoretical indication result of combustion gas stream impact effect, and improve verification efficiency, apparatus of the present invention
Combustion gas stream impact attitude angle, shock point and impact distance can be quickly adjusted, wherein, combustion gas stream impact attitude angle bag
The impact angle of pitch and roll angle are included, so that quick Calibration Theory indicates result.
Embodiment three：The present invention is used for pressure test under high-temperature fuel gas stream shock environment
As shown in Figure 1, 2, 3, on the basis of embodiment one, embodiment two, rocket launching combustion gas that the present embodiment is related to
Stream shock simulation experimental rig also includes single skirt 7, and sensor 9 is connected with one end of single skirt 7, and the other end of single skirt 7 is consolidated
Determine the medial surface of connecting test plate 3；The device also includes being used for the crossover sub 8 for connecting sensor 9 and single skirt 7, sensor 9
It is connected with one end of crossover sub 8, the other end of crossover sub 8 is fixedly connected with single skirt 7.
In the present embodiment implementation process, first the one end of crossover sub 8 is connected with single skirt 7, the other end connects with sensor 9
Connect, then exposed one end of single skirt 7 is connected with the instrument connection of test board 3, sensor 9 is realized by the tube chamber of different materials
The temperature put reduces, and while obtaining combustion gas stream test data, adds the service life of sensor 9.When engine 5 works
Between in the case that not long or combustion gas stream temperature is not too high, only with single skirt 7 or the high mode of thermal resistance material crossover sub 8
Connecting sensor 9 can equally test or and obtain combustion gas flowing pressure, or with the tube chamber formula pressure sensing with certain depth
The test of device 9 can also be tested and obtain combustion gas flowing pressure.Combustion-gas dynamics research needs to obtain test data by experiment.
Apparatus of the present invention contain such method of testing, and combustion gas flow data can be tested in the state of sensor 9 is not destroyed.
In the description of the invention, it is to be understood that " " center ", " longitudinal direction ", " transverse direction ", " length ", " width in term
Degree ", " thickness ", " on ", " under ", "front", "rear", "left", "right", " vertical ", " level ", " top ", " bottom " " interior ", " outer ", " suitable
The orientation or position relationship of the instruction such as hour hands ", " counterclockwise ", " axial direction ", " radial direction ", " circumference " are based on orientation shown in the drawings
Or position relationship, it is for only for ease of the description present invention and simplifies description, rather than instruction or the device or element that imply meaning
There must be specific orientation, with specific azimuth configuration and operation, therefore be not considered as limiting the invention.
In the present invention, unless otherwise clearly defined and limited, term " installation ", " connected ", " connection ", " fixation " etc.
Term should be interpreted broadly, for example, it may be fixedly connected or be detachably connected, or integrally；Can be that machinery connects
Connect or electrically connect；Can be joined directly together, can also be indirectly connected by intermediary, can be in two elements
The connection in portion or the interaction relationship of two elements, limited unless otherwise clear and definite.For one of ordinary skill in the art
For, the concrete meaning of above-mentioned term in the present invention can be understood as the case may be.
In the present invention, unless otherwise clearly defined and limited, fisrt feature can be with "above" or "below" second feature
It is that the first and second features directly contact, or the first and second features pass through intermediary mediate contact.Moreover, fisrt feature exists
Second feature " on ", " top " and " above " but fisrt feature are directly over second feature or oblique upper, or be merely representative of
Fisrt feature level height is higher than second feature.Fisrt feature second feature " under ", " lower section " and " below " can be
One feature is immediately below second feature or obliquely downward, or is merely representative of fisrt feature level height and is less than second feature.
In the description of this specification, reference term " the present embodiment ", " one embodiment ", " some embodiments ", " show
The description of example ", " specific example " or " some examples " etc. mean to combine the specific features of the embodiment or example description, structure,
Material or feature are contained at least one embodiment or example of the present invention.In this manual, above-mentioned term is shown
The statement of meaning property is necessarily directed to identical embodiment or example.Moreover, specific features, structure, material or the spy of description
Point can combine in an appropriate manner in any one or more embodiments or example.In addition, in the case of not conflicting,
Those skilled in the art can be by the different embodiments or example described in this specification and different embodiments or example
Feature is combined and combined.
The foregoing is merely illustrative of the preferred embodiments of the present invention, is not intended to limit the invention, all in essence of the invention
Any modification, equivalent substitution and simple modifications for being made in content etc., should be included in the scope of the protection.
Claims (10)
- A kind of 1. rocket launching combustion gas stream shock simulation experimental rig, it is characterised in that：Described device include experiment platen (1), Test stand (2), test board (3), conical head guide rod (4), engine (5) and fixed support (6), the experiment platen (1) Upper surface is provided with the chute of bar shaped, and the bottom of the test stand (2) is placed in the chute, the experiment platen (1) and described Test stand (2) is bolted to connection, and the test board (3) is fixed on the test stand (2), the conical head guide rod (4) there is conical head front end and blunt end, the conical head front end contradicts the lateral surface of the test board (3), the tack End is connected with the spout of the engine (5), and the medial surface of the test board (3) is fixedly connected with sensor (9), described to start Machine (5) is fixed on the fixed support (6).
- A kind of 2. rocket launching combustion gas stream shock simulation experimental rig according to claim 1, it is characterised in that：The dress Putting also includes adjusting screw (10), the adjusting screw (10) and meanwhile with the test board (3), the test stand (2) is fixed connects Connect.
- A kind of 3. rocket launching combustion gas stream shock simulation experimental rig according to claim 2, it is characterised in that：The dress Putting also includes lofty tone adjusting gasket (11), and the lofty tone adjusting gasket (11) is located at the experiment platen (1) and the test stand (2) between.
- 4. a kind of rocket launching combustion gas stream shock simulation experimental rig according to any claim in claims 1 to 3, It is characterized in that：Described device also includes single skirt (7), and the sensor (9) is connected with one end of single skirt (7), institute The other end for stating single skirt (7) is fixedly connected with the medial surface of the test board (3).
- A kind of 5. rocket launching combustion gas stream shock simulation experimental rig according to claim 4, it is characterised in that：The dress Putting also includes being used for the crossover sub (8) for connecting sensor (9) and single skirt (7), the sensor (9) and the crossover sub (8) one end connection, the other end of the crossover sub (8) are fixedly connected with single skirt (7).
- A kind of 6. rocket launching combustion gas stream shock simulation experimental rig according to claim 5, it is characterised in that：The examination Test on frame (2) and be provided with neck, the test board (3) is positioned in the neck, and multiple tests are provided with the test board (3) Hole, single skirt (7) and the conical head guide rod (4) are directed at same instrument connection；The test board (3) has a variety of rule Lattice, the test board (3) of different size have the different instrument connection of arrangement mode；The conical head guide rod (4) also has a variety of Specification, the conical head front end of the conical head guide rod (4) of different size have different cone angles.
- A kind of 7. rocket launching combustion gas stream shock simulation experimental rig according to claim 1,3 or 6, it is characterised in that： The center line of conical head guide rod (4) described in the spout pair of the engine (5).
- A kind of 8. rocket launching combustion gas stream shock simulation experimental rig according to claim 1,3 or 6, it is characterised in that： The sensor (9) includes at least one of pressure sensor (9), temperature sensor (9).
- A kind of 9. rocket launching combustion gas stream shock simulation experimental rig according to claim 1,3 or 6, it is characterised in that： The upper surface of the experiment platen (1) is provided with two parallel bar shaped chutes.
- A kind of 10. rocket launching combustion gas stream shock simulation experimental rig according to claim 1, it is characterised in that：It is described Engine (5) is kerosene engine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710593743.8A CN107421710B (en) | 2017-07-20 | 2017-07-20 | A kind of rocket launching combustion gas stream shock simulation experimental rig |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710593743.8A CN107421710B (en) | 2017-07-20 | 2017-07-20 | A kind of rocket launching combustion gas stream shock simulation experimental rig |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107421710A true CN107421710A (en) | 2017-12-01 |
| CN107421710B CN107421710B (en) | 2019-10-15 |
Family
ID=60429920
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710593743.8A Active CN107421710B (en) | 2017-07-20 | 2017-07-20 | A kind of rocket launching combustion gas stream shock simulation experimental rig |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107421710B (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108426694A (en) * | 2018-02-09 | 2018-08-21 | 哈尔滨工业大学 | The simulator and analogy method of space junk high-speed impact thermal protection structure |
| CN109900154A (en) * | 2019-03-13 | 2019-06-18 | 北京航天发射技术研究所 | A kind of rocket launching gas flow field quasi-steady state predicting method and device |
| CN111795828A (en) * | 2020-06-05 | 2020-10-20 | 湖北航天技术研究院总体设计所 | Horizontal simulation launch test device and method |
| CN111982957A (en) * | 2020-08-31 | 2020-11-24 | 湖北三江航天江北机械工程有限公司 | Device and method for testing ablation resistance of fluid director |
| CN112505092A (en) * | 2020-10-27 | 2021-03-16 | 中国运载火箭技术研究院 | Heat-proof skirt gas flow test device |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1401937A (en) * | 2001-08-27 | 2003-03-12 | 三菱重工业株式会社 | Pressure measuring device of burner |
| US20100146934A1 (en) * | 2008-12-15 | 2010-06-17 | Astrium Gmbh | Hot Gas Chamber |
| CN103712808A (en) * | 2012-09-29 | 2014-04-09 | 北京航天发射技术研究所 | Detection system for single-jet-pipe rocket launch water-spray cooling noise-reduction effect |
| CN106596108A (en) * | 2016-11-04 | 2017-04-26 | 上海新力动力设备研究所 | Inclined-jet-pipe solid rocket engine test rack of quick assembly type |
-
2017
- 2017-07-20 CN CN201710593743.8A patent/CN107421710B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1401937A (en) * | 2001-08-27 | 2003-03-12 | 三菱重工业株式会社 | Pressure measuring device of burner |
| US20100146934A1 (en) * | 2008-12-15 | 2010-06-17 | Astrium Gmbh | Hot Gas Chamber |
| CN103712808A (en) * | 2012-09-29 | 2014-04-09 | 北京航天发射技术研究所 | Detection system for single-jet-pipe rocket launch water-spray cooling noise-reduction effect |
| CN103712808B (en) * | 2012-09-29 | 2016-06-22 | 北京航天发射技术研究所 | A kind of single spraying pipe rocket launching spray cooling noise reduction detection system |
| CN106596108A (en) * | 2016-11-04 | 2017-04-26 | 上海新力动力设备研究所 | Inclined-jet-pipe solid rocket engine test rack of quick assembly type |
Non-Patent Citations (1)
| Title |
|---|
| 季必玉: "基于虚拟仪器的火箭燃气射流多参数测试与分析系统", 《中国优秀硕士学位论文全文数据库 工程科技Ⅱ辑》 * |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108426694A (en) * | 2018-02-09 | 2018-08-21 | 哈尔滨工业大学 | The simulator and analogy method of space junk high-speed impact thermal protection structure |
| CN109900154A (en) * | 2019-03-13 | 2019-06-18 | 北京航天发射技术研究所 | A kind of rocket launching gas flow field quasi-steady state predicting method and device |
| CN109900154B (en) * | 2019-03-13 | 2021-08-10 | 北京航天发射技术研究所 | Quasi-steady state prediction method and device for rocket launching gas flow field |
| CN111795828A (en) * | 2020-06-05 | 2020-10-20 | 湖北航天技术研究院总体设计所 | Horizontal simulation launch test device and method |
| CN111795828B (en) * | 2020-06-05 | 2022-06-03 | 湖北航天技术研究院总体设计所 | Horizontal simulation launch test device and method |
| CN111982957A (en) * | 2020-08-31 | 2020-11-24 | 湖北三江航天江北机械工程有限公司 | Device and method for testing ablation resistance of fluid director |
| CN112505092A (en) * | 2020-10-27 | 2021-03-16 | 中国运载火箭技术研究院 | Heat-proof skirt gas flow test device |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107421710B (en) | 2019-10-15 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107421710A (en) | A kind of rocket launching combustion gas stream shock simulation experimental rig | |
| CN106950128B (en) | A kind of online dynamic ablation measuring device and its measurement method for applying shock loading | |
| Edalatpour et al. | Injection of multi hydrogen jets within cavity flameholder at supersonic flow | |
| Wieting et al. | Experimental shock-wave interference heating on a cylinder at Mach 6and 8 | |
| US8131408B2 (en) | System and method for determining characteristic parameters in an aircraft | |
| CN104132811B (en) | Ramjet engine air inlet starting hesitation characteristic test apparatus | |
| CN105424495B (en) | Coal petrography sheet plane stress state experimental rig and test method under the conditions of a kind of Thermal-mechanical Coupling | |
| Gruhn et al. | Experimental investigation of a hypersonic inlet with and without sidewall compression | |
| CN101111764A (en) | Method and apparatus for determining defects in turbine parts | |
| CN111795828B (en) | Horizontal simulation launch test device and method | |
| Esfeh et al. | Evaluation of aerospike for drag reduction on a blunt nose using experimental and numerical modeling | |
| CN103439360A (en) | Solid propellant multi-thermocouple dynamic combustion performance testing system and method | |
| Juliano et al. | HIFiRE-1 boundary-layer transition: ground test results and stability analysis | |
| CN107991057A (en) | A kind of airvane surface cold wall heat flow density and device for pressure measurement | |
| Hébert et al. | Investigation of mechanisms leading to water drop breakup at Mach 4.4 and Weber numbers above 10 5 | |
| Chang et al. | Hypersonic shock impingement studies on a flat plate: flow separation of laminar boundary layers | |
| Jacobsen et al. | Flowfield near a mulitiport injector array in a supersonic flow | |
| Balakalyani et al. | An accelerometer balance for aerodynamic force measurements over Hypervelocity Ballistic models in shock tunnel | |
| Tamanini | Turbulence effects on dust explosion venting | |
| Sagerman et al. | Comparisons of measured and modeled aero-thermal distributions for complex hypersonic configurations | |
| Robinson et al. | Short duration force measurements in impulse facilities | |
| Corn et al. | Characterization of a superheated fuel jet in a crossflow | |
| CN109900154A (en) | A kind of rocket launching gas flow field quasi-steady state predicting method and device | |
| CN111681520B (en) | Simulation experiment device for external fire disaster of airplane | |
| Wang et al. | Pressure and heat flux calibration of the long-test-duration hypervelocity detonation-driven shock tunnel |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |