CN114563153B - Ultrahigh-speed pneumatic test device for accelerating gas test through track - Google Patents
Ultrahigh-speed pneumatic test device for accelerating gas test through track Download PDFInfo
- Publication number
- CN114563153B CN114563153B CN202210454845.2A CN202210454845A CN114563153B CN 114563153 B CN114563153 B CN 114563153B CN 202210454845 A CN202210454845 A CN 202210454845A CN 114563153 B CN114563153 B CN 114563153B
- Authority
- CN
- China
- Prior art keywords
- cylinder
- vacuum pipeline
- sealing cover
- pipeline
- test
- 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
Images
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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
-
- 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
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Abstract
The invention belongs to the technical field of ultrahigh speed wind tunnel tests and discloses an ultrahigh speed pneumatic test device for testing gas through a track accelerating cylinder. The front end and the rear end of a vacuum pipeline of the ultrahigh-speed pneumatic test device are both closed, and a vacuum pipeline guide rail is arranged on the inner wall of the vacuum pipeline; the front section of the vacuum pipeline is clamped with an air cylinder, the front end and the rear end of the air cylinder are sealed, and a power device is arranged on a sealing cover at the front end of the air cylinder; the middle section is provided with a model supporting rod, the test model is fixed on the model supporting rod, and the head of the test model faces forwards; a micro-frying device is arranged in front of the head of the test model; the rear section is provided with a deceleration pipeline which is coaxial with the vacuum pipeline. The ultra-high speed pneumatic test device is used for subsonic, supersonic and hypersonic airflow ground simulation; the total pressure simulation capability of the air flow can be improved through the pre-charging pressure, and the ground simulation of the air flow with higher total temperature, total pressure and Mach number can be realized through energy storage; realizing ultrahigh-speed pure air flow simulation; and the ultrahigh-speed flow simulation of gases with any components is realized.
Description
Technical Field
The invention belongs to the technical field of ultrahigh speed wind tunnel tests, and particularly relates to an ultrahigh speed pneumatic test device for testing gas through a track accelerating cylinder.
Background
In the aerospace field, in order to reproduce the real flight environment of an aircraft under ground test conditions, two methods are generally adopted: one is to directly accelerate the test model to the flying speed, such as model flying test, ballistic target equipment, rocket sled equipment and the like; the other method is to fix the test model, accelerate the gas to the flying speed by adopting certain measures, and realize that the relative speed between the test model and the gas is consistent with the real flying environment, such as a subsonic wind tunnel, a supersonic wind tunnel, a hypersonic wind tunnel and the like. For subsonic wind tunnels (Mach number is less than 1), the flight speed required to be simulated is low, and ground reproduction of real flight environments is easy to realize. For supersonic wind tunnel (Mach number 1 < Mach number 5), although total temperature, total pressure and speed of the required simulation airflow are high, under the current technical level, economic ground simulation can still be realized. For a hypersonic wind tunnel (Mach number is more than 5), along with the increase of the Mach number, the total temperature, the total pressure and the speed which are required to be simulated by the ground reproduction flight environment gradually exceed the supportable limit of the technology, in the research, generally aiming at the concerned solved content, part of parameters are selectively simulated, for example, when aerodynamic force and aerodynamic heat problems need to be researched, a method for reducing the simulated total temperature is generally selected to realize the simultaneous simulation of the Mach number and the Reynolds number, and the representative wind tunnel is a conventional hypersonic wind tunnel; when the temperature effect needs to be considered at the same time, instantaneous high-temperature and high-pressure gas supply is generally realized by a method of sacrificing effective test time, and typical equipment is a shock tunnel and an expansion tunnel; when long-time thermal assessment at a real incoming flow temperature needs to be realized, an arc wind tunnel test mode is generally adopted, but the total pressure cannot be simulated; when the ultra-high speed flight environment needs to be completely reproduced in a long test time, a ballistic target mode can be adopted, and the cost of effective mass is replaced by sufficient test time. However, with the deep research of the pneumatic problem of the ultra-high speed aircraft, the demand of people for simultaneously reproducing the physical and chemical parameters of the ultra-high speed flight environment is more urgent, and the requirements of people on the simulation of high total temperature, high total pressure and long-time ultra-high speed airflow of ground wind tunnel equipment at present and in the future cannot be met due to the self limitation of the ultra-high speed wind tunnels in spite of various types.
At present, the ultrahigh speed wind tunnel test technology needs to be expanded, and an ultrahigh speed pneumatic test device for accelerating gas test through a track is developed.
Disclosure of Invention
The invention aims to solve the technical problem of providing an ultrahigh-speed pneumatic test device for testing gas by using a track accelerating cylinder.
The invention relates to an ultrahigh-speed pneumatic test device for testing gas through a rail accelerating cylinder, which is characterized by comprising a long and straight vacuum pipeline; the front end and the rear end of the vacuum pipeline are both closed, and the inner wall of the vacuum pipeline is provided with a vacuum pipeline guide rail which is communicated from front to back, coaxial with the vacuum pipeline and symmetrically distributed in the center;
in the inner cavity of the vacuum pipeline, a cylinder is clamped on a vacuum pipeline guide rail at the front section, the cylinder is a circular closed pipeline formed by combining two semicircular pipelines which are symmetrical up and down, a gap is formed in the contact end surface of each semicircular pipeline, the gap is closed through a cylinder side end sealing element, and the front end and the rear end of the cylinder are respectively sealed through a cylinder front end sealing cover and a cylinder rear end sealing cover; the sealing cover at the front end of the cylinder is provided with power devices which are symmetrically distributed along the circumferential direction;
a model supporting rod corresponding to a sealing piece at the side end of the cylinder is arranged in the middle section of an inner cavity of the vacuum pipeline, the test model is fixed on the model supporting rod, and the head of the test model faces the front end of the vacuum pipeline;
a linear micro-frying device corresponding to the sealing element at the side end of the cylinder is arranged in front of the head of the test model and on the inner wall of the vacuum pipeline;
a deceleration pipeline which is coaxial with the vacuum pipeline is arranged at the rear section of the inner cavity of the vacuum pipeline;
in the process that the cylinder moves along the vacuum pipeline guide rail from front to back, the micro-explosion device is firstly embedded into the sealing piece at the side end of the cylinder, the micro-explosion device is exploded for the first time before the sealing cover at the front end of the cylinder reaches the head of the test model, the sealing cover at the front end of the cylinder and the sealing piece at the side end of the cylinder are damaged, and the head of the test model penetrates through the sealing cover at the front end of the cylinder; then the model supporting rod is embedded into the gap, the micro-explosion device is subjected to secondary explosion before the sealing cover at the rear end of the air cylinder reaches the head of the test model, the sealing cover at the rear end of the air cylinder is damaged, and the head of the test model penetrates through the sealing cover at the rear end of the air cylinder; the cylinder continues to move forwards, and continues to decelerate after entering the deceleration pipeline until the cylinder stops at the rear end of the vacuum pipeline.
Further, the power device is a solid rocket.
Furthermore, the deceleration pipeline is a plurality of deceleration strips distributed along the moving direction of the cylinder at the rear section of the vacuum pipeline.
Further, the cylinder front end sealing cover and the cylinder rear end sealing cover are both resin membranes.
Further, the cylinder side end sealing element is a rigid plastic sealing strip.
The ultrahigh-speed pneumatic test device for testing gas through the rail acceleration cylinder disclosed by the invention is used for pre-filling the test gas into the cylinder for sealing, and accelerating the cylinder and the test gas in a vacuum environment to achieve the required test conditions. The two ends of the vacuum pipeline are sealed, and the inner wall of the vacuum pipeline is provided with a vacuum pipeline guide rail arranged along the axis direction and used for limiting the cylinder in the moving process.
The vacuum pipeline in the ultrahigh-speed pneumatic test device for testing gas through the rail acceleration cylinder provides an environment with low vacuum degree; the cylinder is used for storing test gas and wrapping the test gas for acceleration; the power device is fixedly connected with the air cylinder and is used for accelerating the air cylinder and the test gas to the required speed; the test model and the model supporting rod are connected and fixed in the vacuum pipeline, so that the air cylinder and test gas can smoothly pass through the test model; the speed reduction pipeline is used for reducing the speed of the air cylinder and stopping the air cylinder after the test is finished, and the micro-explosion device is triggered by an electric signal and used for opening the windward end face, the rear end face and the side end sealing piece of the air cylinder when the air cylinder penetrates through the model.
The working principle of the ultrahigh-speed pneumatic test device for testing gas through the rail acceleration cylinder is as follows: the test gas is filled into the cylinder in advance for sealing, and the power device accelerates the gas in the cylinder and the cylinder in a vacuum environment, so that the cylinder is accelerated to the speed required by the test before reaching the test model. The test model is connected with the model support rod and is fixed in the vacuum pipeline, and the cylinder adopts the mode of slightly exploding the device electric explosion to open the sealed lid of cylinder front end, side end sealing member in the twinkling of an eye before arriving the test model, and inside the test model got into the cylinder, because the gap of cylinder side end face was very little for the cylinder inner area, and the cylinder functioning speed was extremely fast moreover, and consequently the pressure of revealing can be ignored. Set up the electric explosion time delay through the fried device a little, open the sealed lid of cylinder rear end in the twinkling of an eye before test model reachs the sealed lid of cylinder rear end, test model passes through from inside the cylinder, and whole process is the test process. Then the cylinder is decelerated and stopped under the action of a deceleration pipeline.
The working process of the ultrahigh-speed pneumatic test device for testing gas through the rail acceleration cylinder comprises the following steps: before the test, the cylinder is arranged at the starting end of the vacuum pipeline, test gas with certain temperature and pressure is filled into the cylinder and sealed for storage, and meanwhile, the vacuum pipeline is vacuumized. When the test is started, the power device accelerates the air cylinder and the test gas in the air cylinder in a vacuum environment, and the thrust of the power device is controlled to enable the air cylinder to reach the speed required by the test before reaching the test model; at the moment that the air cylinder reaches the test model, the front end sealing cover and the side end sealing piece of the air cylinder are rapidly opened, the test model passes through the inside of the air cylinder, when the test model reaches the rear end of the air cylinder, the rear end sealing cover of the air cylinder is rapidly opened, and the test model passes through the air cylinder; the test process is the process of passing the test model through the cylinder. After the test model passes through the air cylinder, the air cylinder decelerates and stops under the action of the deceleration pipeline, and the test is finished. And after the test is finished, the air cylinder is pulled to the outgoing end.
The ultrahigh-speed pneumatic test device for testing gas by the rail acceleration cylinder can be used for ground simulation of subsonic, supersonic and hypersonic airflow; the total pressure simulation capability of the air flow can be improved in a pre-charging pressure mode; the ground simulation of the air flow with higher total temperature, total pressure and Mach number can be realized in an energy storage mode; the ultrahigh-speed pure air flow simulation can be realized; the ultrahigh-speed flow simulation of gases with any components can be realized.
Drawings
FIG. 1 is a schematic structural diagram (initial position) of a super high speed pneumatic test device for testing gas through an orbital acceleration cylinder according to the present invention;
FIG. 2 is a cross-sectional view taken along line A-A of FIG. 1;
FIG. 3 is a schematic diagram of the structure of a cylinder in the ultra-high speed pneumatic test device for testing gas by an orbital acceleration cylinder according to the present invention;
FIG. 4 is a cross-sectional view taken along line B-B of FIG. 3;
FIG. 5 is an enlarged view of portion C of FIG. 4;
FIG. 6 is a schematic diagram of the ultra high speed pneumatic test apparatus for testing gas by rail acceleration cylinder according to the present invention (test position);
FIG. 7 is an enlarged view of a portion D of FIG. 6;
fig. 8 is a schematic structural view (deceleration position) of the ultra-high-speed pneumatic test device for testing gas by the orbital acceleration cylinder according to the present invention.
1. A vacuum line; 2. a cylinder; 3. a power plant; 4. a test model; 5. a deceleration duct; 6. a model strut; 7. a micro-frying device;
101. the front end of the vacuum pipeline; 102. the rear end of the vacuum pipeline; 103. a vacuum duct guide;
201. a sealing cover at the front end of the cylinder; 202. a cylinder rear end sealing cover; 203. a cylinder side end seal.
Detailed Description
The present invention will be described in detail below with reference to the accompanying drawings and examples.
As shown in fig. 1 to 8, the ultra-high speed pneumatic testing device for testing gas by using the rail acceleration cylinder of the invention comprises a long and straight vacuum pipeline 1; the front end 101 and the rear end 102 of the vacuum pipeline 1 are both closed, and the inner wall of the vacuum pipeline 1 is provided with a vacuum pipeline guide rail 103 which is communicated from front to back, coaxial with the vacuum pipeline 1 and symmetrically distributed in the center;
in the inner cavity of the vacuum pipeline 1, a cylinder 2 is clamped on a front section of a vacuum pipeline guide rail 103, the cylinder 2 is a circular closed pipeline formed by combining two semicircular pipelines which are symmetrical up and down, a gap is formed in the contact end surface of each semicircular pipeline, the gap is closed through a cylinder side end sealing piece 203, and the front end and the rear end of the cylinder 2 are respectively sealed through a cylinder front end sealing cover 201 and a cylinder rear end sealing cover 202; the power devices 3 which are symmetrically distributed along the circumferential direction are arranged on the sealing cover 201 at the front end of the cylinder;
a model supporting rod 6 corresponding to the cylinder side end sealing piece 203 is arranged in the middle section of the inner cavity of the vacuum pipeline 1, the test model 4 is fixed on the model supporting rod 6, and the head of the test model 4 faces the front end of the vacuum pipeline 1;
a linear micro-frying device 7 corresponding to the cylinder side end sealing piece 203 is arranged in front of the head of the test model 4 and on the inner wall of the vacuum pipeline 1;
a deceleration pipeline 5 which is coaxial with the vacuum pipeline 1 is arranged at the rear section of the inner cavity of the vacuum pipeline 1;
in the process that the cylinder 2 moves along the vacuum pipeline guide rail 103 from front to back, the micro-frying device 7 is firstly embedded into the cylinder side end sealing piece 203, before the cylinder front end sealing cover 201 reaches the head of the test model 4, the micro-frying device 7 is exploded for the first time to damage the cylinder front end sealing cover 201 and the cylinder side end sealing piece 203, and the head of the test model 4 penetrates through the cylinder front end sealing cover 201; then the model supporting rod 6 is embedded into the gap, before the sealing cover 202 at the rear end of the cylinder reaches the head of the test model 4, the micro-explosion device 7 is exploded for the second time to destroy the sealing cover 202 at the rear end of the cylinder, and the head of the test model 4 penetrates through the sealing cover 202 at the rear end of the cylinder; the cylinder 2 continues to move forward, continues to decelerate after entering the deceleration duct 5, until it stops at the vacuum duct rear end 102.
Further, the power device 3 is a solid rocket.
Further, the cylinder front end sealing cover 201 and the cylinder rear end sealing cover 202 are both resin films.
Furthermore, the deceleration pipeline 5 is a plurality of deceleration strips distributed along the moving direction of the cylinder 2 at the rear section of the vacuum pipeline 1.
Further, the cylinder side end sealing piece 203 is a hard plastic sealing strip.
Example 1
The present embodiment simulates a real airflow environment with a flying height of 30km and a flying speed of mach number of 10. According to calculation, under the flight condition, the static temperature of the atmospheric environment is 227K, the static pressure is 1200Pa, the relative speed of the airflow and the aircraft is 3km/s, the length of the cylinder 2 required for realizing 10ms effective test time simulation on the ground is 30m, and the total mass of the cylinder 2 and the built-in air is controlled within 300 kg.
The length of the vacuum pipeline 1 is 20km, the initial vacuum pressure of the vacuum pipeline 1 is set to be 0.1Pa, the pneumatic resistance of the air cylinder 2 in the high-speed running process can be ignored, and the air cylinder front end sealing cover 201 and the air cylinder rear end sealing cover 202 are made of resin membranes with lower strength, so that the air cylinder front end sealing cover 201 and the air cylinder rear end sealing cover 202 can be rapidly opened under the action of the micro-frying device 7.
The initial position is shown in figure 1, the cylinder 2 is positioned at the outgoing end, the test model 4 is fixed on the model support rod 6, the model support rod 6 is fixed at the center of the vacuum pipeline 1, and the distance from the front edge of the test model 4 to the front end 101 of the vacuum pipeline is 10 km. The solid rocket is adopted as a power device 3, the thrust of the solid rocket is 13.5 tons, and the acceleration of the forward running of the test gas driven by the cylinder 2 under the action of the thrust is 450m/s2After the power device 3 starts, the time is 6.7s, and the speed of the cylinder 2 after the cylinder 2 slides for 10km reaches 3000 m/s. At this time, the power unit 3 is closed, and the cylinder front end sealing cover 201 is rapidly opened; the test position is as shown in fig. 6, the test model 4 passes through the test gas in the cylinder 2 at a relative speed of 3000m/s, the rear end sealing cover 202 of the cylinder is quickly opened at the moment before the test model 4 touches the rear end sealing cover 202 of the cylinder, and the cylinder 2 continues to move forwards and enters the deceleration pipeline 5; the deceleration position is shown in fig. 8, and the cylinder 2 enters the deceleration operation stage until the cylinder 2 is stagnant in the deceleration duct 5, and the test is ended. After the test is finished, the air cylinder 2 is pulled to the outgoing end.
Although the embodiments of the present invention have been disclosed, the embodiments are not limited to the applications listed in the description and the embodiments, and can be fully applied to various fields of hypersonic boundary layer transition mode methods suitable for the present invention. Additional modifications and refinements will readily occur to those skilled in the art without departing from the principles of the present invention, and the present invention is not limited to the specific details and illustrations shown and described herein.
Claims (5)
1. A super-high speed pneumatic test device for testing gas through a rail acceleration cylinder is characterized by comprising a long and straight vacuum pipeline (1); the front end (101) and the rear end (102) of the vacuum pipeline (1) are both closed, and the inner wall of the vacuum pipeline (1) is provided with a vacuum pipeline guide rail (103) which is communicated from front to back, coaxial with the vacuum pipeline (1) and symmetrically distributed in the center;
in the inner cavity of the vacuum pipeline (1), a cylinder (2) is clamped on a front section of vacuum pipeline guide rail (103), the cylinder (2) is a circular closed pipeline formed by combining two semicircular pipelines which are symmetrical up and down, a gap is formed in the contact end surface of each semicircular pipeline, the gap is closed through a cylinder side end sealing element (203), and the front end and the rear end of the cylinder (2) are respectively sealed through a cylinder front end sealing cover (201) and a cylinder rear end sealing cover (202); the front end sealing cover (201) of the cylinder is provided with power devices (3) which are symmetrically distributed along the circumferential direction;
a model supporting rod (6) corresponding to the cylinder side end sealing piece (203) is installed in the middle section of the inner cavity of the vacuum pipeline (1), the test model (4) is fixed on the model supporting rod (6), and the head of the test model (4) faces to the front end of the vacuum pipeline (1);
a linear micro-frying device (7) corresponding to the cylinder side end sealing piece (203) is arranged in front of the head of the test model (4) and on the inner wall of the vacuum pipeline (1);
a deceleration pipeline (5) which is coaxial with the vacuum pipeline (1) is arranged at the rear section of the inner cavity of the vacuum pipeline (1);
in the process that the air cylinder (2) moves along the vacuum pipeline guide rail (103) from front to back, the micro-frying device (7) is firstly embedded into the air cylinder side end sealing piece (203), before the air cylinder front end sealing cover (201) reaches the head of the test model (4), the micro-frying device (7) is exploded for the first time to damage the air cylinder front end sealing cover (201) and the air cylinder side end sealing piece (203), and the head of the test model (4) penetrates through the air cylinder front end sealing cover (201); then the model supporting rod (6) is embedded into the gap, the micro-explosion device (7) is exploded for the second time before the sealing cover (202) at the rear end of the air cylinder reaches the head of the test model (4), the sealing cover (202) at the rear end of the air cylinder is damaged, and the head of the test model (4) penetrates through the sealing cover (202) at the rear end of the air cylinder; the cylinder (2) continues to move forwards, enters the speed reduction pipeline (5) and then continues to reduce the speed until the cylinder stops at the rear end (102) of the vacuum pipeline.
2. The ultra high speed pneumatic test device for testing gas through an orbital acceleration cylinder according to claim 1, characterized in that the power device (3) is a solid rocket.
3. The ultra-high speed pneumatic test device for testing gas through an orbital acceleration cylinder according to claim 1, characterized in that the deceleration pipeline (5) is a plurality of deceleration strips distributed along the moving direction of the cylinder (2) at the rear section of the vacuum pipeline (1).
4. The ultra high speed pneumatic test device for testing gas through an orbital acceleration cylinder according to claim 1, wherein the front end sealing cover (201) and the rear end sealing cover (202) of the cylinder are both resin films.
5. The ultra high speed pneumatic test device for testing gas through an orbital acceleration cylinder according to claim 1, wherein the cylinder side end seal (203) is a rigid plastic seal.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210454845.2A CN114563153B (en) | 2022-04-28 | 2022-04-28 | Ultrahigh-speed pneumatic test device for accelerating gas test through track |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210454845.2A CN114563153B (en) | 2022-04-28 | 2022-04-28 | Ultrahigh-speed pneumatic test device for accelerating gas test through track |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114563153A CN114563153A (en) | 2022-05-31 |
| CN114563153B true CN114563153B (en) | 2022-07-01 |
Family
ID=81720902
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210454845.2A Active CN114563153B (en) | 2022-04-28 | 2022-04-28 | Ultrahigh-speed pneumatic test device for accelerating gas test through track |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114563153B (en) |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO1989002071A1 (en) * | 1987-08-26 | 1989-03-09 | University Of Queensland | Hypervelocity wind tunnel with ballistic piston |
| JP2002071508A (en) * | 2000-08-28 | 2002-03-08 | Mitsubishi Heavy Ind Ltd | Inpact type wind tunnel equipment |
| CN104236846A (en) * | 2014-08-29 | 2014-12-24 | 北京卫星环境工程研究所 | Built-in vacuum re-pressing air diffuser |
| CN112146902A (en) * | 2020-10-10 | 2020-12-29 | 中铁西南科学研究院有限公司 | Dynamic model test system and method for tunnel pneumatic effect in alpine and high-altitude environment |
| CN112444368A (en) * | 2020-10-26 | 2021-03-05 | 中国航天空气动力技术研究院 | Ground simulation test device for ultrahigh-speed reentry test airflow |
| CN112504615A (en) * | 2020-10-27 | 2021-03-16 | 中国运载火箭技术研究院 | Rotary acceleration type magnetic suspension electromagnetic propulsion test system and method |
| CN112747890A (en) * | 2020-12-29 | 2021-05-04 | 中国航天空气动力技术研究院 | Pneumatic and thermal combined test system and test method |
| CN112945516A (en) * | 2021-03-19 | 2021-06-11 | 北京空天技术研究所 | Pneumatic thermal test device for pipeline high-speed train and design method thereof |
| WO2022033608A1 (en) * | 2020-08-11 | 2022-02-17 | 日照坤仑智能科技有限公司 | Drive system and performance measurement method for aircraft model in wind tunnel |
-
2022
- 2022-04-28 CN CN202210454845.2A patent/CN114563153B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO1989002071A1 (en) * | 1987-08-26 | 1989-03-09 | University Of Queensland | Hypervelocity wind tunnel with ballistic piston |
| JP2002071508A (en) * | 2000-08-28 | 2002-03-08 | Mitsubishi Heavy Ind Ltd | Inpact type wind tunnel equipment |
| CN104236846A (en) * | 2014-08-29 | 2014-12-24 | 北京卫星环境工程研究所 | Built-in vacuum re-pressing air diffuser |
| WO2022033608A1 (en) * | 2020-08-11 | 2022-02-17 | 日照坤仑智能科技有限公司 | Drive system and performance measurement method for aircraft model in wind tunnel |
| CN112146902A (en) * | 2020-10-10 | 2020-12-29 | 中铁西南科学研究院有限公司 | Dynamic model test system and method for tunnel pneumatic effect in alpine and high-altitude environment |
| CN112444368A (en) * | 2020-10-26 | 2021-03-05 | 中国航天空气动力技术研究院 | Ground simulation test device for ultrahigh-speed reentry test airflow |
| CN112504615A (en) * | 2020-10-27 | 2021-03-16 | 中国运载火箭技术研究院 | Rotary acceleration type magnetic suspension electromagnetic propulsion test system and method |
| CN112747890A (en) * | 2020-12-29 | 2021-05-04 | 中国航天空气动力技术研究院 | Pneumatic and thermal combined test system and test method |
| CN112945516A (en) * | 2021-03-19 | 2021-06-11 | 北京空天技术研究所 | Pneumatic thermal test device for pipeline high-speed train and design method thereof |
Non-Patent Citations (4)
| Title |
|---|
| experiences of living with a malignant fungating wound:a qualitative study;Lo,shu-fen;《journal of clinical nursing》;20081001;第17卷(第20期);第2699-2708页 * |
| 一种两自由度全机模型阵风试验支撑装置研制;唐建平;《实验流体力学》;20210615;第35卷(第3期);第94-99页 * |
| 磁浮飞行风洞试验技术及其应用研究;倪章松;《空气动力学学报》;20211015;第39卷(第5期);第95-110页 * |
| 超高声速风洞扩压器试验研究与分析;童华;《实验流体力学》;20140615;第28卷(第3期);第78-81、103页 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114563153A (en) | 2022-05-31 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| Trimpi | A preliminary theoretical study of the expansion tube: a new device for producing high-enthalpy short-duration hypersonic gas flows | |
| CN112504615B (en) | Rotary acceleration type magnetic suspension electromagnetic propulsion test system and method | |
| CN102705081B (en) | Binary hypersonic variable geometrical inlet channel, design method and work mode | |
| CN206847890U (en) | Black box high impact shock test bullet support | |
| CN103512423B (en) | A kind of supersonic air big gun emitter | |
| CN104632411A (en) | Internal waverider-derived turbine base combined dynamic gas inlet adopting binary variable-geometry manner | |
| CN108036918A (en) | The FREE-PISTON SHOCK TUNNEL of one kind of multiple mode operations | |
| CN115165289B (en) | Ultrasonic explosion phenomenon wind tunnel test simulation system and method | |
| CN114563153B (en) | Ultrahigh-speed pneumatic test device for accelerating gas test through track | |
| CN207703439U (en) | A kind of high enthalpy shock tunnel of 2m magnitudes free-piston driving | |
| CN103017996A (en) | High-magnitude strong-impact test method | |
| US20220090560A1 (en) | Helicon yield plasma electromagnetic ram-scramjet drive rocket ion vector engine | |
| Shrewsbury | Effect of boattail juncture shape on pressure drag coefficients of isolated afterbodies | |
| WO2022090212A1 (en) | A tube transport system for very high vehicle speeds and a method of operating a tube transport system | |
| CN114544134A (en) | Gas type wind tunnel based on rail acceleration | |
| CA2012228A1 (en) | Means and method for reducing differential pressure loading in an augmented gas turbine engine | |
| CN110362123B (en) | Hypersonic velocity temporary impulse type wind tunnel start-stop control system and method | |
| CN102680255B (en) | Springback-preventing high-speed train model accelerating device based on momentum transferring | |
| CN103454062B (en) | For the accelerating system of bullet train collision experiment | |
| CN102494904B (en) | High-speed train model accelerating device driven based on compressed gas | |
| CN114754966A (en) | Superspeed vacuum test device with rail car | |
| Li et al. | Reliability improvement of the piston compressor in FD-21 free-piston shock tunnel | |
| Martin | A review of shock tubes and shock tunnels | |
| CN109178335B (en) | Fan air guide type boosting aircraft catapult | |
| CN212254530U (en) | Free molecular flow generation device for rarefied gas dynamic test |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |