CN107315434B - Sample fast assembly heating system based on plane collision impact experiment - Google Patents
Sample fast assembly heating system based on plane collision impact experiment Download PDFInfo
- Publication number
- CN107315434B CN107315434B CN201710710926.3A CN201710710926A CN107315434B CN 107315434 B CN107315434 B CN 107315434B CN 201710710926 A CN201710710926 A CN 201710710926A CN 107315434 B CN107315434 B CN 107315434B
- Authority
- CN
- China
- Prior art keywords
- sample
- heating
- telescopic device
- gun barrel
- central controller
- 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
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D23/00—Control of temperature
- G05D23/19—Control of temperature characterised by the use of electric means
- G05D23/30—Automatic controllers with an auxiliary heating device affecting the sensing element, e.g. for anticipating change of temperature
- G05D23/32—Automatic controllers with an auxiliary heating device affecting the sensing element, e.g. for anticipating change of temperature with provision for adjustment of the effect of the auxiliary heating device, e.g. a function of time
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- Automation & Control Theory (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
- Devices For Use In Laboratory Experiments (AREA)
- Investigating Or Analyzing Materials Using Thermal Means (AREA)
Abstract
The invention discloses a sample rapid assembly heating system based on a plane collision impact experiment, which comprises an emission controller, a gun barrel, a central controller and a heating cavity, wherein a signal wire of the central controller is connected to the emission controller and comprises a telescopic device, the heating cavity is arranged on the side surface of a nozzle of the gun barrel, a sample is arranged on the telescopic device, the sample moves to the opposite side of the nozzle of the gun barrel from the heating cavity under the action of the telescopic device, and the signal wire of the central controller is respectively connected to the telescopic device and the sample; compared with the conventional collision test, the heat source is changed, the existing closed heat source is developed from the previous open heat source, the temperature nonuniformity in the sample heating process is reduced, the heating temperature deviation of each point on the sample is smaller, and the better test effect is achieved.
Description
Technical Field
The invention relates to the field of high-temperature tests of artillery or gas cannons, in particular to a rapid sample assembling and heating system based on a plane collision impact test.
Background
Temperature is one of the important influencing factors influencing the change of physical parameters of materials, a specific temperature field is often required to be established in a plurality of tests for researching the thermal characteristics and the heat intensity of the materials, and the research of a control method is the core problem for establishing a stable temperature field. PID control is the most widely used control method in process control, is relatively mature as a basic control algorithm, and is widely applied to industrial process control. The method has the advantages of easy realization, wide application range, simple parameter setting, strong robustness and the like, and is widely applied to temperature control. The dynamic characteristic research of the structure under high-temperature heat load attracts the attention of a plurality of researchers. Due to the experimental and testing structures, the sample is generally required to be in an open state, which makes it difficult to heat the sample, the heating rate is slow, and the heating uniformity deviation is large.
Disclosure of Invention
The invention aims to solve the problems of low heating rate and large deviation of heating uniformity in the existing heating system applied to an artillery or gas cannon, and provides a structural design method of a sample rapid assembly heating system based on a plane collision impact experiment, so that the heating rate of a heated sample is higher, the heating temperature deviation of each point on the sample is smaller, and the uniformity is better.
In order to achieve the purpose, the invention adopts the following technical scheme:
the utility model provides a sample fast assembly system of heating based on experiment is strikeed in plane collision, includes emission control ware, barrel, central controller, heating chamber, central controller's signal line is connected to the emission control ware, includes the expansion bend, the heating chamber sets up in the orificial side of barrel, be provided with the sample on the expansion bend, the sample is by the intraoral face-to-face of removing the orificial of barrel that moves in the heating chamber under the effect of expansion bend, central controller's signal line is connected to respectively on expansion bend and the sample.
In the above technical scheme, the heating cavity is a closed cavity with an opening on one side.
In the above technical solution, a door for a closed cavity is provided on the opening surface of the heating cavity.
In the above technical solution, the heating method comprises the following steps:
the method comprises the following steps: initializing various data, and fixing a sample on a telescopic device;
step two: after the test is started, the sample is sent to a heating cavity through a telescopic device to be heated;
step three: the central controller collects the temperature of the sample, controls the expansion device to reset after the temperature is stabilized at the test temperature after the sample is heated for a period of time, stops the sample right opposite to the nozzle of the gun barrel and synchronously controls the launching controller to launch the sample;
step four: the flyers in the gun barrel rapidly eject out of the gun barrel and impact on the sample under the action of the flyer bracket, and the central controller collects temperature signals on the sample while impacting.
In the technical scheme, the time from the heating cavity to the position right opposite to the nozzle of the gun barrel is in the order of hundreds of milliseconds, and the time from the emission to the impact of the flyer is in the order of milliseconds.
In the technical scheme, the time for exposing the sample to the vacuum after leaving the heat source is about hundred milliseconds, and the temperature generated by heat radiation is reduced to 1K-2K in the hundred milliseconds.
In summary, due to the adoption of the technical scheme, the invention has the beneficial effects that: compared with the conventional collision test, the heat source is changed, the existing closed heat source is developed from the previous open heat source, the temperature nonuniformity in the sample heating process is reduced, the heating temperature deviation of each point on the sample is smaller, and the better test effect is achieved.
Drawings
The invention will now be described, by way of example, with reference to the accompanying drawings, in which:
FIG. 1 is a schematic diagram of a prior art test system;
FIG. 2 is a schematic diagram of a test system of the present invention.
Detailed Description
All of the features disclosed in this specification, or all of the steps in any method or process so disclosed, may be combined in any combination, except combinations of features and/or steps that are mutually exclusive.
As shown in fig. 1, it is a schematic structural diagram of a prior testing system, which includes a launch controller, a gun barrel, a central controller, and a heating cavity, wherein the signal line of the central controller is connected to the launch controller, wherein the heating cavity is arranged right opposite to the nozzle of the gun barrel and is always in a heating state, and a sample is arranged in the heating cavity and is supported by a telescopic device, so that the sample is always in the heating cavity. But because this arrangement necessarily requires two side openings, one of which is required to face the barrel muzzle and the other of which is required to support the sample, the heating chamber, if it has two open sides, means that air can convect on both sides. This means that the heating of the whole sample becomes open heating, the air flow causes the temperature of the sample surface to rise with obvious non-uniformity, and the temperature can not be stabilized at a certain temperature because of the air flow, and the temperature causes the final test effect to have low precision and considerable error.
In order to change the situation, the invention improves the situation on the basis that the heating cavity is not arranged right opposite to the nozzle of the gun barrel, but the heating cavity is arranged on the side surface of the nozzle of the gun barrel, the telescopic device is arranged on the other side surface of the nozzle of the gun barrel, the side surface of the heating cavity facing the telescopic device is an opening surface, and the telescopic device can be used for telescopic the sample right opposite to the nozzle of the gun barrel and in the heating cavity. In order to solve the problem of non-uniformity of sample heating, the heating cavity is arranged in a sealing mode, a door is arranged on one side of the opening, when a sample is heated, six sides of the heating cavity are sealed, and therefore the whole sample can be in a stable heating environment, and the sample can be heated uniformly.
During the specific test of the scheme, the specific steps are as follows:
firstly, a central controller gives a control signal to control the expansion device to expand and contract, a sample on the expansion device is sent into a heating cavity, and after the sample is sent into the heating cavity, a door on the expansion device is controlled to conduct pipe wall, so that the heating cavity is in an internal sealing state;
secondly, the central controller controls the heating cavity to heat the sample in the heating cavity, monitors the temperature of the surface of the sample, and controls the heating cavity to open the door and reset the expansion piece after the temperature of the surface of the sample is stabilized to a certain specific temperature and is maintained for a period of time, so that the sample is sent to the opposite side of the nozzle of the gun barrel;
meanwhile, the central controller controls the launch controller to launch the flyer, the flyer is rapidly launched out of the gun barrel under the driving of the flyer bracket and impacts the surface of the sample, and the central controller collects the temperature of the surface of the sample during impact, so that the test is completed.
The time from the firing of the artillery or gas cannon to the target-striking of the flyer is about a few milliseconds during the whole process, and the time from the completion of the heating to the return of the sample to the experimental position is hundreds of milliseconds, namely the time of the sample leaving the heat source and being exposed to the vacuum during the experiment is about hundreds of milliseconds. According to the heat radiation formula of the Strand-Boltzmann heat radiation, the temperature reduction caused by the heat radiation in the hundred milliseconds is about 1K to 2K, and the influence of the temperature difference on the experimental result is small.
The heating method used in the scheme has the advantages of high heating rate; the heating temperature deviation of each point on the sample is small, the uniformity is good, the test precision is high, and the like.
The invention is not limited to the foregoing embodiments. The invention extends to any novel feature or any novel combination of features disclosed in this specification and any novel method or process steps or any novel combination of features disclosed.
Claims (4)
1. The utility model provides a sample fast assembly system of heating based on experiment is strikeed in plane collision, includes launch controller, barrel, central controller, heating chamber, central controller's signal line is connected to launch controller, its characterized in that: the device comprises a telescopic device, wherein the telescopic device is arranged on the other side face of the tube opening of the gun barrel, the side face, facing the telescopic device, of the heating cavity is an opening face, the heating cavity is arranged on the side face of the tube opening of the gun barrel, a sample is arranged on the telescopic device, the sample moves from the heating cavity to the opposite face of the tube opening of the gun barrel under the action of the telescopic device, and a signal wire of a central controller is connected to the telescopic device and the sample respectively;
the heating chamber is a closed cavity with an opening on one side, and a door for the closed cavity is arranged on the opening side of the heating chamber.
2. The heating method of the rapid sample assembly heating system based on the plane collision impact test as claimed in claim 1, characterized by comprising the following steps:
the method comprises the following steps: initializing various data, and fixing a sample on a telescopic device;
step two: after the test is started, conveying the sample into a heating cavity through a telescopic device to be heated;
step three: the central controller collects the temperature of the sample, controls the expansion device to reset after the temperature is stabilized at the test temperature after the sample is heated for a period of time, stops the sample right opposite to the nozzle of the gun barrel and synchronously controls the launching controller to launch the sample;
step four: the flyers in the gun barrel rapidly eject out of the gun barrel and impact on the sample under the action of the flyer bracket, and the central controller collects temperature signals on the sample while impacting.
3. The warming method for the sample rapid assembly warming system based on the plane collision impact experiment as claimed in claim 2, wherein the time from the heating cavity to the right opposite of the nozzle of the gun barrel of the sample is in the order of hundreds of milliseconds, and the time from the emission to the impact of the flyer is in the order of milliseconds.
4. The method for warming the sample rapid assembly warming system based on the plane collision impact test as claimed in claim 3, wherein the sample leaving the heat source is exposed to the vacuum for about hundred milliseconds, and the temperature generated by the heat radiation is reduced to 1K-2K within the hundred milliseconds.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710710926.3A CN107315434B (en) | 2017-08-18 | 2017-08-18 | Sample fast assembly heating system based on plane collision impact experiment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710710926.3A CN107315434B (en) | 2017-08-18 | 2017-08-18 | Sample fast assembly heating system based on plane collision impact experiment |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107315434A CN107315434A (en) | 2017-11-03 |
| CN107315434B true CN107315434B (en) | 2023-03-10 |
Family
ID=60176890
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710710926.3A Active CN107315434B (en) | 2017-08-18 | 2017-08-18 | Sample fast assembly heating system based on plane collision impact experiment |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107315434B (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2005328724A (en) * | 2004-05-18 | 2005-12-02 | Koga Sangyo Kk | Heating device |
| JP2016173337A (en) * | 2015-03-18 | 2016-09-29 | 日本電気株式会社 | Impact testing machine and impact testing method |
| CN106950128A (en) * | 2017-03-20 | 2017-07-14 | 清华大学 | A kind of online dynamic ablation measurement apparatus and its measuring method for applying shock loading |
| CN207051754U (en) * | 2017-08-18 | 2018-02-27 | 中国工程物理研究院流体物理研究所 | A kind of sample based on the experiment of plane collision impact quickly assembles heating system |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8311757B2 (en) * | 2007-08-14 | 2012-11-13 | American Gnc Corporation | Miniaturized smart self-calibration electronic pointing method and system |
| KR100961065B1 (en) * | 2008-09-29 | 2010-06-01 | 한국전력공사 | Simulation test system for thermal impact ageing of power transmission insulator |
-
2017
- 2017-08-18 CN CN201710710926.3A patent/CN107315434B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2005328724A (en) * | 2004-05-18 | 2005-12-02 | Koga Sangyo Kk | Heating device |
| JP2016173337A (en) * | 2015-03-18 | 2016-09-29 | 日本電気株式会社 | Impact testing machine and impact testing method |
| CN106950128A (en) * | 2017-03-20 | 2017-07-14 | 清华大学 | A kind of online dynamic ablation measurement apparatus and its measuring method for applying shock loading |
| CN207051754U (en) * | 2017-08-18 | 2018-02-27 | 中国工程物理研究院流体物理研究所 | A kind of sample based on the experiment of plane collision impact quickly assembles heating system |
Non-Patent Citations (1)
| Title |
|---|
| 平面撞击对Ti6AL4Vh合金结构的影响;温霞等;《爆炸与冲击》;20100531;全文 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107315434A (en) | 2017-11-03 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN204368446U (en) | A kind of to the omnidistance controlled test system of test article surface intensification cooling | |
| CN100561216C (en) | A kind of high temperature device for testing sound absorption performance of acoustic absorbant | |
| CN102213965B (en) | Thermostatic equipment and control method thereof | |
| CN203982907U (en) | A kind of baker of producing enamelled wire | |
| CN107315434B (en) | Sample fast assembly heating system based on plane collision impact experiment | |
| CN102362066B (en) | For the method for ignition engine ignition mixture used | |
| CN104167261A (en) | Varnished wire producing oven and temperature control method | |
| CN104596210A (en) | Degreasing furnace | |
| CN111007338B (en) | Device and method for measuring deformation of flexible electronic device in vacuum temperature-changing environment | |
| CN109655276B (en) | Test device for pollution-free rapid heating of inert gas | |
| CN105445033B (en) | A kind of CONSTANT VOLUME MODEL COMBUSTION CHAMBER for studying spray discharge pattern and its microscopic characteristics | |
| CN202711096U (en) | Tubular PECVD temperature control system | |
| CN111780616B (en) | Electromagnetic gun control method and device suitable for various projectiles | |
| CN112710567A (en) | Temperature-controllable ballistic impact experimental device | |
| CN103868945A (en) | System and method for carrying out thermal-fatigue-resisting test on integral parts | |
| CN207051754U (en) | A kind of sample based on the experiment of plane collision impact quickly assembles heating system | |
| CN202858874U (en) | Electric oven | |
| CN211856417U (en) | Multi-temperature-zone hot baking test device for energetic material product | |
| CN109115531A (en) | For accelerating the test method of heating and cooling in low pressure cabin temperature control test | |
| CN205556931U (en) | Add and play machine heating device | |
| KR20090067029A (en) | Multi-chamber for burn-in testing apparatus and test method thereof | |
| CN105972564B (en) | Quartz lamp air cooling device | |
| CN204421513U (en) | A kind of debinding furnace | |
| CN210922369U (en) | Launching device for universal large-depth submarine-launched simulated missile | |
| CN201593045U (en) | Simple gas gene gun |
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 |