CN206132718U - Automatically controlled solid propellant burning rate testing arrangement - Google Patents
Automatically controlled solid propellant burning rate testing arrangement Download PDFInfo
- Publication number
- CN206132718U CN206132718U CN201621187299.7U CN201621187299U CN206132718U CN 206132718 U CN206132718 U CN 206132718U CN 201621187299 U CN201621187299 U CN 201621187299U CN 206132718 U CN206132718 U CN 206132718U
- Authority
- CN
- China
- Prior art keywords
- automatically controlled
- electrode
- solid propellant
- controlled solid
- bottom electrode
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Landscapes
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The utility model provides an automatically controlled solid propellant burning rate testing arrangement, last electrode that includes the bottom electrode that contacts with the need checking sample lower surface, contacts with the need checking sample upper surface, going up the electrode and being connected through insulation connecting rod and displacement sensor, displacement sensor is connected with the analog signal capture card, analog signal capture card and computer link, upward electrode, bottom electrode are connected with the power. The utility model discloses simple structure through the change that displacement sensor recorded powder column burning thickness in real time, can measure the instantaneous burning rate of automatically controlled solid propellant under different voltage conditions.
Description
Technical field
This utility model is related to automatically controlled solid propellant burning velocity testing field, and in particular to the automatically controlled solid propellant propulsion of one kind measurement
The device of agent Burning rate testing.
Background technology
The burn rate of propellant is the key index of Design of Solid Propellant Rocket Engine, and the method for testing of Conventional solid propellant is
Jing has a lot, for example target collimation method, acoustic-emission, image method and standard testing motor method.Automatically controlled solid propellant is solid with conventional
Body propellant is different, and automatically controlled solid propellant is a kind of stopped working solid propellant that is special, being capable of conduction, and automatically controlled solid is pushed away
Enter agent under power on condition, load certain voltage, igniting can be realized；Advanced by control voltage size adjustment in combustion process
The burn rate of agent, propellant extinguishes when cutting off the electricity supply, and is capable of achieving repeatedly igniting and stops working.When electrode is necessary with powder column in combustion process
Contact is carved, to ensure that propellant is conductive, the burning of automatically controlled solid propellant could be controlled by being carried in the voltage at electrode two ends
State.Prior art cannot be used directly for measuring the burn rate of automatically controlled solid propellant.
The content of the invention
Goal of the invention of the present utility model is, in order to overcome the above-mentioned deficiency of prior art, and to provide a kind of automatically controlled solid
Propellant burning velocity testing device, can measure instantaneous burn rate of the automatically controlled solid propellant under different voltage conditions.
The technical solution of the utility model is：Including the bottom electrode and testing sample that contact with testing sample lower surface
The Top electrode that upper surface contacts, the Top electrode Jing insulated connecting rod is connected with displacement transducer, and displacement transducer is believed with simulation
Number capture card connection, collection of simulant signal card is connected with computer, and the Top electrode, bottom electrode and power supply connect.
The Top electrode, bottom electrode Jing voltage regulating devices are connected with power supply.
Institute's displacement sensors are loaded on support.
The support includes insulating base, the support bar stood on insulating base, the fix bar loaded on support boom end, dress
Guide post in the middle part of support bar.
The bottom electrode is loaded on insulating base middle part.
The Top electrode is porous electrode, and bottom electrode is plectane plane electrode, and bottom electrode lower lobes portion inserts insulation base
In installing hole in the middle part of seat.
The beneficial effects of the utility model：Test device is simple, and by displacement transducer powder column combustion thickness δ is measured in real time
Change, propellant burn rate at any time can be obtained, you can survey instantaneous burn rate.
Description of the drawings
Fig. 1 is structural representation of the present utility model.
Wherein：The automatically controlled solid propellant grain of 1- bottom electrodes, 2-, 3- Top electrodes, 4- insulated connecting rods, 5- displacement transducers,
6- insulating bases, 7- support bars, 8- fix bars, 9- guide posts.
Specific embodiment
Below in conjunction with the accompanying drawings embodiment is described further to this utility model.
In Fig. 1, this utility model includes bottom electrode 1, automatically controlled solid propellant testing sample 2, Top electrode 3, insulated connecting rod
4th, displacement transducer 5, insulating base 6, support bar 7, fix bar 8 and guide post 9.Bottom electrode 1 is plectane plane electrode, is fixed on
On insulating base 6, for ensureing conductive and control propellant the fired state of propellant testing sample 2, electricity is connect by binding post
Source one end.Automatically controlled solid propellant testing sample 2 is cylindric, is coaxially mounted between bottom electrode 1 and Top electrode 3, propellant
Start burning from the end of Top electrode 3, burning direction is axially propagated gradually downward along powder column, ensure propellant with electricity by connecting rod deadweight
Moment contact is conductive between pole.Top electrode 3 is porous electrode, is connected with insulated connecting rod 4, for ensureing that propellant is conductive and controls
The fired state of propellant, by binding post the power supply other end is connect.Insulated connecting rod 4 is used to connect Top electrode 3 and displacement transducer
5.Displacement transducer 5 is used to gather propellant charge thickness dynamic variable signal vertically, and displacement transducer is by propellant sample
Product thickness dynamic variable signal is converted to voltage change signal, and by data collecting card computer is transferred to, using computer number
Propellant thickness of sample dynamic variable signal and the relation curve between the time are obtained according to software processes are processed.Insulating base 6
Fixed supporting role, and the short circuit of anti-locking apparatus.Support bar 7 is used for fixed support fix bar 8 and guide post 9.Fix bar 8 is used for solid
Positioning displacement sensor 5.Guide post 9 is used to ensure insulated connecting rod 4 axially movable, prevents to offset.
Method of testing of the present utility model is：Automatically controlled solid propellant testing sample is installed between upper/lower electrode, is installed
Displacement transducer, displacement transducer connects computer by collection of simulant signal card, and computer starting exclusive data processes software；
Magnitude of voltage is set, and electrode two ends loading certain voltage, propellant starts burning from Top electrode end, and burning direction is for vertically gradually
Propagate downwards；The variable signal of propellant combustion thickness is measured in real time by displacement transducer, at computer exclusive data
Reason software processes obtain the relation curve between propellant combustion web δ and time tδ-t, the instantaneous combustion of automatically controlled solid propellant
Speed isr(t)=dδ/dt。
Above example is only a specific embodiment of the present utility model, is not intended to limit of the present utility model
Protection domain.It is all it is of the present utility model spirit and principle within, any modification, equivalent substitution and improvements done etc. all should be wrapped
It is contained within protection domain of the present utility model.
Claims (6)
1. a kind of automatically controlled solid propellant burning velocity testing device, it is characterised in that：Including what is contacted with testing sample lower surface
Bottom electrode（1）The Top electrode contacted with testing sample upper surface（3）, the Top electrode（3）Jing insulated connecting rods（4）With displacement
Sensor（5）Connection, displacement transducer（5）It is connected with collection of simulant signal card, collection of simulant signal card is connected with computer, institute
State Top electrode（3）, bottom electrode（1）It is connected with power supply.
2. automatically controlled solid propellant burning velocity testing device according to claim 1, it is characterised in that：The Top electrode（3）、
Bottom electrode（1）Jing voltage regulating devices are connected with power supply.
3. automatically controlled solid propellant burning velocity testing device according to claim 1, it is characterised in that：Institute's displacement sensors
（5）Loaded on support.
4. automatically controlled solid propellant burning velocity testing device according to claim 3, it is characterised in that：The support includes exhausted
Edge pedestal（6）, stand on insulating base（6）On support bar（7）, loaded on support bar（7）The fix bar of end（8）, loaded on support
Bar（7）The guide post at middle part（9）.
5. automatically controlled solid propellant burning velocity testing device according to claim 3, it is characterised in that：The bottom electrode（1）
Loaded on insulating base（6）Middle part.
6. automatically controlled solid propellant burning velocity testing device according to claim 3, it is characterised in that：The Top electrode（3）
For porous electrode, bottom electrode（1）For plectane plane electrode, bottom electrode（1）Insert insulating base in lower lobes portion（6）The peace at middle part
In dress hole.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621187299.7U CN206132718U (en) | 2016-10-28 | 2016-10-28 | Automatically controlled solid propellant burning rate testing arrangement |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621187299.7U CN206132718U (en) | 2016-10-28 | 2016-10-28 | Automatically controlled solid propellant burning rate testing arrangement |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206132718U true CN206132718U (en) | 2017-04-26 |
Family
ID=58577885
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621187299.7U Active CN206132718U (en) | 2016-10-28 | 2016-10-28 | Automatically controlled solid propellant burning rate testing arrangement |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206132718U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110779398A (en) * | 2019-10-30 | 2020-02-11 | 湖南宏大日晟航天动力技术有限公司 | Firework launching device and method |
| CN111208255A (en) * | 2020-02-24 | 2020-05-29 | 北京理工大学 | Visual high-pressure burning rate instrument and method for multiple solid propellant drug strips |
| CN112147268A (en) * | 2020-09-03 | 2020-12-29 | 西安近代化学研究所 | Device and method for nondestructively preparing flameout surface of solid propellant |
-
2016
- 2016-10-28 CN CN201621187299.7U patent/CN206132718U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110779398A (en) * | 2019-10-30 | 2020-02-11 | 湖南宏大日晟航天动力技术有限公司 | Firework launching device and method |
| CN111208255A (en) * | 2020-02-24 | 2020-05-29 | 北京理工大学 | Visual high-pressure burning rate instrument and method for multiple solid propellant drug strips |
| CN111208255B (en) * | 2020-02-24 | 2021-01-05 | 北京理工大学 | Visual high-pressure burning rate instrument and method for multiple solid propellant drug strips |
| CN112147268A (en) * | 2020-09-03 | 2020-12-29 | 西安近代化学研究所 | Device and method for nondestructively preparing flameout surface of solid propellant |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN206132718U (en) | Automatically controlled solid propellant burning rate testing arrangement | |
| CN105021492A (en) | Apparatus for testing cable heating and combustion characteristics under effect of simulating fault arc | |
| CN104155341B (en) | A kind of boron powder combustion heat value test device | |
| CN102590284A (en) | Device for measuring water saturation distribution of rock core at high temperature and high pressure | |
| CN103018094A (en) | Device for rapid-heating quasi-static high-temperature Hopkinson pressure bar experiment | |
| CN105203245B (en) | Pressure test device installation method at a kind of lower different depth of explosive wastewater impact | |
| CN103400019A (en) | Matlab/Simulink-based alternating current (AC) fault arc simulation method | |
| CN103439360A (en) | Solid propellant multi-thermocouple dynamic combustion performance testing system and method | |
| CN105547584B (en) | One kind is portable to pull to force value system for field calibrating installation | |
| CN107290399B (en) | Transformer water content measuring device based on PDC/FDS medium response method | |
| CN107807057A (en) | A kind of experimental provision suitable for the loading of coal and rock axial vibrations | |
| CN106230383A (en) | A kind of MWT solar cell test device and method of testing | |
| CN202994702U (en) | Novel friction sensitivity instrument | |
| CN105526037B (en) | A kind of gas engine Iganition control system | |
| CN214895520U (en) | Intermittent type formula cable buffer layer material ablation resistance detection device | |
| CN110607811A (en) | Pile group loading test device and method for simulating high-speed rail bridge operation load | |
| CN200941109Y (en) | Resistance tester for leakage of work terrace/platform | |
| CN106017885B (en) | A kind of electric power pylon can jack column foot load-carrying properties experimental rig | |
| CN113406392A (en) | Resistance measuring device and resistance measuring method in cable buffer layer ablation process | |
| CN206056838U (en) | A kind of test device of electric connector contact pin contact engaging and separating force | |
| CN112362989B (en) | Spark discharge simulation device and test method for high-voltage electrostatic dust collector | |
| CN203838275U (en) | Acoustoelectric integration post insulator vibration acoustic detection device | |
| ATE315883T1 (en) | DETERMINING CABLE LENGTH FOR AN ELECTRIC ARC FURNACE | |
| CN207727529U (en) | A kind of lower shaft multi-angle locking device of steel dam anchor gate | |
| CN205120908U (en) | Circuit board withstand voltage test tool |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |