CN217403999U - Solid propellant creep test system under heat-force coupling condition - Google Patents
Solid propellant creep test system under heat-force coupling condition Download PDFInfo
- Publication number
- CN217403999U CN217403999U CN202220870275.0U CN202220870275U CN217403999U CN 217403999 U CN217403999 U CN 217403999U CN 202220870275 U CN202220870275 U CN 202220870275U CN 217403999 U CN217403999 U CN 217403999U
- Authority
- CN
- China
- Prior art keywords
- solid propellant
- creep
- test piece
- clamping unit
- lower clamping
- 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
Landscapes
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The utility model discloses a solid propellant creep test system under heat-power coupling condition, this test system include constant temperature and humidity oil bath incubator, test piece cartridge assembly, stress-determining loading device and creep test data measurement device. The mass of the oil injection weight is variable, in the experimental process, the cross section area and the required fixed stress of the measured section of the solid propellant test piece are measured, the oil injection weight can accurately provide corresponding load, and the precision of the test system is obviously improved through the synergistic effect of a creep test data measuring device. Meanwhile, the test system can provide a long-term low-stress loading for the test piece, and the cost is low. In addition, the test system is safe, reliable and easy to popularize and use.
Description
Technical Field
The utility model belongs to the technical field of solid propellant creep test technique and specifically relates to a solid propellant creep test system under heat-power coupling condition.
Background
During the long-term storage of the solid rocket engine, the deformation and stress states of the internal explosive columns of the solid rocket engine change with time under the action of self gravity load and temperature load, and creep effect is generated. Creep effects can cause changes in combustion face geometry or block gas passages, which in turn can alter the internal ballistic performance of the engine and even cause explosions. For vertical storage engines, the creep phenomenon of the cartridge is more severe. Therefore, it is of great practical interest to study creep during storage of solid propellants.
Within the solid propellant industry, creep testing under thermal-force coupling conditions is the most direct and effective method commonly used to study the creep performance of solid propellants. The conventional creep test device under the condition of thermal-force coupling consists of two parts: the high-low temperature test chamber applies temperature load and the strain fixing clamp applies strain load. This traditional test device replaces the stress load with the load of deciding to meet an emergency, replaces creep test with the relaxation test mode promptly, and there is certain error in the stress state of testpieces.
With the progress of research, the current test precision cannot meet the creep research requirement of the solid propellant, and therefore, the invention of a creep test system is urgently needed.
SUMMERY OF THE UTILITY MODEL
The utility model provides a solid propellant creep test system under heat-force coupling condition for overcome among the prior art defect such as test precision is not enough.
In order to achieve the purpose, the utility model provides a solid propellant creep test system under the condition of heat-force coupling, which comprises a constant temperature and humidity oil bath incubator, a test piece chuck component, a fixed stress loading device and a creep test data measuring device;
the test piece chuck component comprises an upper cross beam, a plurality of upper clamping units and a plurality of lower clamping units, wherein two ends of the upper cross beam are respectively fixed on two opposite wall surfaces in the constant temperature and humidity oil bath incubator, and the upper clamping units are fixed on the upper cross beam; the lower clamping unit is connected with the upper clamping unit through a solid propellant test piece; one end of the solid propellant test piece is clamped in the upper clamping unit, and the other end of the solid propellant test piece is clamped in the lower clamping unit;
the constant stress loading device comprises an oil injection weight, the oil injection weight comprises a weight shell and a transparent oil storage inner container, the weight shell is connected with the lower clamping unit through a steel silk thread, and the transparent oil storage inner container is arranged in the weight shell;
and the creep test data measuring device is used for shooting the measured part of the solid propellant test piece in a test period.
Preferably, the upper clamping unit comprises an upper clamping head and an upper protection ring, and the upper clamping head is fixed on the upper cross beam;
after the upper clamping head clamps one end of the solid propellant test piece, the upper protective ring is sleeved on the upper clamping head to limit the solid propellant test piece to horizontally slide out.
Preferably, the lower clamping unit comprises a lower clamping head and a lower guard ring, and the lower clamping head is connected with the upper clamping unit through a solid propellant test piece;
and after the lower clamping head clamps one end of the solid propellant test piece, the lower protective ring is sleeved on the lower clamping head so as to fix the other end of the solid propellant test piece.
Preferably, the test piece chuck assembly further comprises a lower cross beam, and the lower cross beam is opposite to the upper cross beam and is positioned right below the lower clamping unit;
and two ends of the lower cross beam are respectively fixed on two opposite wall surfaces in the constant-temperature and constant-humidity oil bath temperature box.
Preferably, a through hole is arranged on the lower clamping unit; a plurality of through holes are formed in the lower cross beam;
one end of the steel silk thread is provided with a circular ring buckle for fixing the stress loading direction, and the other end of the steel silk thread is provided with a circular ring for hanging an oil injection weight;
one end of the steel wire is connected with the lower clamping unit through the through hole of the lower cross beam and the through hole of the lower clamping unit and the annular buckle;
the other end of the steel silk thread is connected with the weight shell through the circular ring.
Preferably, the creep test data measuring device comprises an industrial camera, a marking paint and a crystal grid plate (precision is 50nm, and each grid side is 0.5 mm);
the marking paint is marked on the part to be observed of the solid propellant test piece;
the crystal grid plate is adhered to the marking paint.
Preferably, the transparent oil storage inner container is a transparent plastic oil storage inner container with scale marks on the inner container wall, and the precision is 1 g.
Preferably, the wall surface of the weight shell is hollowed out to expose the scale marks of the transparent oil storage inner container.
The weight housing has different weight specifications to meet different stress requirements.
Preferably, the constant stress loading device further comprises kerosene (with the density of 0.8 g/cm) 3 ) And the transparent oil storage inner container is arranged in the transparent oil storage inner container.
Preferably, the test space of the constant-temperature and constant-humidity oil bath incubator is more than or equal to 480 x 680 x 1100mm, the temperature control range is 5-80 ℃, and the heat-conducting medium is silicone oil.
Compared with the prior art, the beneficial effects of the utility model are that:
the utility model provides a solid propellant creep test system under heat-power coupling condition includes constant temperature and humidity oil bath incubator, test piece cartridge assembly, stress-determinate loading device and creep test data measurement device. The creep force can be accurately realized according to the experimental requirements, namely, corresponding load can be accurately provided through the oil injection weights; the experimental deformation can be accurately recorded, namely the position of a test point on the crystal grid plate is photographed and recorded by a creep test data measuring device and is obtained by conversion; the creep force and the deformation precision are improved, so that the precision of the whole set of test system is obviously improved. Meanwhile, the test system can provide a long-term low-stress loading for the test piece, and the cost is low. In addition, the test system is safe, reliable and easy to popularize and use.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed to be used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the structures shown in the drawings without creative efforts.
FIG. 1 is a schematic diagram of a solid propellant creep test system under thermal-force coupling conditions provided by the present invention;
fig. 2 is a schematic structural view of a test piece chuck assembly according to an embodiment of the present invention;
fig. 3 is a schematic structural view of an upper clamping unit according to an embodiment of the present invention;
fig. 4 is a cross-sectional view of a lower clamping unit according to an embodiment of the present invention;
fig. 5 is a schematic structural view of an oil filling weight according to an embodiment of the present invention;
fig. 6 is a schematic view of an embodiment of the present invention illustrating a high-precision crystal grid plate.
The reference numbers illustrate: 1: a constant temperature and humidity oil bath temperature box; 2: a test piece collet assembly; 2-1: an upper cross beam; 2-2: a lower cross beam; 2-3: an upper clamping unit; 2-3-1: an upper clamping head; 2-3-2: an upper guard ring; 2-4: a lower clamping unit; 2-4-1: a lower clamping head; 2-4-2: a lower guard ring; 2-5: a solid propellant test piece; 3: a constant stress loading device; 3-1: a steel wire; 3-2: a circular ring buckle; 3-3: a metal weight housing (including a cover); 3-4: a transparent plastic oil storage inner container; 4: creep test data measuring means; 4-1: an industrial camera; 4-2: painting the white mark; 4-3: high-precision crystal grid plate.
The objects, features and advantages of the present invention will be further described with reference to the accompanying drawings.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative efforts belong to the protection scope of the present invention.
In addition, the technical solutions of the embodiments of the present invention can be combined with each other, but it is necessary to use a person skilled in the art to realize the basis, and when the technical solutions are combined and contradictory to each other or cannot be realized, the combination of the technical solutions should not exist, and is not within the protection scope of the present invention.
As shown in FIG. 1, the embodiment provides a creep test system for a solid propellant under a heat-force coupling condition, which comprises a constant-temperature constant-humidity oil bath incubator 1, a test piece chuck assembly 2, a fixed stress loading device 3 and a creep test data measuring device 4.
In one embodiment, the constant temperature and humidity oil bath incubator 1 will provide three aging temperatures of 50 deg.C, 60 deg.C, and 70 deg.C, respectively, according to the experimental settings.
As shown in fig. 2, the test piece jaw assembly 2 includes an upper clamping unit 2-3 and a lower clamping unit 2-4. The upper clamping unit 2-3 is fixed on the upper cross beam 2-1; the lower clamping unit 2-4 is arranged opposite to the upper clamping unit 2-3.
The upper clamping unit 2-3 and the lower clamping unit 2-4 are used for clamping two ends of the solid propellant test piece 2-5 respectively.
The lower beam 2-2 can play a role in protection after the solid propellant test piece 2-5 is broken, so that the lower clamping unit 2-4 and the oil injection weight are prevented from directly falling to cause damage to the experimental device.
As shown in FIG. 3, the upper clamping unit 2-3 comprises an upper clamping head 2-3-1 and an upper protection ring 2-3-2, and after the solid propellant test piece 2-5 is fixed on the upper clamping head, the upper protection ring 2-3-2 is sleeved on the upper clamping head 2-3-1 and surrounds one end of the solid propellant test piece 2-5.
As shown in FIG. 4, the lower clamping unit 2-4 comprises a lower clamping head 2-4-1 and a lower guard ring 2-4-2, and after the solid propellant test piece 2-5 is fixed to the lower clamping head, the lower guard ring 2-4-2 is sleeved on the lower clamping head 2-4-1 and surrounds the other end of the solid propellant test piece 2-5.
The middle of the lower clamping head 2-4-1 is provided with a through hole, the axis of the through hole is vertical to the horizontal plane, the steel silk thread 3-1 penetrates through the through hole, one end of the steel silk thread 3-1 is provided with a circular ring buckle 3-2, the diameter of the buckle is slightly larger than that of the through hole and is movably connected with the lower clamping head 2-4-1, so that the stress loading direction is always vertical downwards and coincides with the central axis of the solid propellant test piece 2-5.
The constant stress loading device 3 comprises a steel wire 3-1, a circular ring buckle 3-2 and an oil injection weight.
As shown in fig. 5, the oil-filled weight comprises a metal weight housing (including a cover) 3-3 and a transparent plastic oil-storing inner container 3-4. The metal weight shell (including the cover) has five weight specifications which are respectively: 1000g, 500g, 200g, 100g, 50 g.
The required fixed stress can be calculated according to the cross section area of 2-5 of the solid propellant test piece, and the solid propellant test piece is loaded by an oil filling weight. Under the weight specification of a metal weight shell (containing a cover) 3-3, kerosene (with the density of 0.8g/cm3) can be injected to adjust the weight, the adjusting range is 0-20 g, and the adjusting precision is 1 g.
The creep test data measuring device 4 comprises an industrial camera 4-1, white mark painting 4-2 and a high-precision crystal grid plate 4-3.
As shown in fig. 6, the white marking paint 4-2 marks the portion to be measured of the solid propellant test piece 2-5, and marks the length of the portion to be measured, and the high-precision crystal lattice plate 4-3 is adhered in the middle of the portion to be measured.
And the industrial camera 4-1 shoots the measured part of the solid propellant test piece 2-5 according to a certain experimental period in the measuring process, and the elongation of the solid propellant test piece 2-5 in thermal-force coupling aging creep is obtained through image processing and punctuation conversion of professional software.
This example was subjected to a long-term 28d tensile creep test. The displacement is acquired by adopting a CCD camera and image data processing software, and the shooting time points of the camera are as follows: 0h, 12h, 1d, 3d, 7d, 10.5d, 14d, 17.5d, 21d, 24.5d, 28 d. And a high-precision crystal grid plate is used as an image reference object to ensure the sampling precision. And calculating real-time strain through the initial engineering gauge length and the displacement, and further acquiring the strain rate and the creep compliance of each time point.
The above only is the preferred embodiment of the present invention, not so limiting the patent scope of the present invention, all of which are under the concept of the present invention, the equivalent structure transformation made by the contents of the specification and the drawings is utilized, or the direct/indirect application is included in other related technical fields in the patent protection scope of the present invention.
Claims (10)
1. A solid propellant creep test system under a heat-force coupling condition is characterized by comprising a constant-temperature constant-humidity oil bath temperature box, a test piece chuck component, a fixed stress loading device and a creep test data measuring device;
the test piece chuck component comprises an upper cross beam, a plurality of upper clamping units and a plurality of lower clamping units, wherein two ends of the upper cross beam are respectively fixed on two opposite wall surfaces in the constant temperature and humidity oil bath incubator, and the upper clamping units are fixed on the upper cross beam; the lower clamping unit is connected with the upper clamping unit through a solid propellant test piece; one end of the solid propellant test piece is clamped in the upper clamping unit, and the other end of the solid propellant test piece is clamped in the lower clamping unit;
the constant stress loading device comprises an oil injection weight, the oil injection weight comprises a weight shell and a transparent oil storage inner container, the weight shell is connected with the lower clamping unit through a steel silk thread, and the transparent oil storage inner container is arranged in the weight shell;
and the creep test data measuring device is used for shooting the measured part of the solid propellant test piece in a test period.
2. The system of claim 1, wherein the upper clamping unit comprises an upper clamping head and an upper guard ring, the upper clamping head being secured to the upper beam;
and after the upper clamping head clamps one end of the solid propellant test piece, the upper protective ring is sleeved on the upper clamping head.
3. The system for solid propellant creep testing under thermally-coupled conditions of claim 1 wherein the lower clamping unit comprises a lower clamping head and a lower guard ring, the lower clamping head being connected to the upper clamping unit by a solid propellant test piece;
and after the lower clamping head clamps one end of the solid propellant test piece, the lower protective ring is sleeved on the lower clamping head.
4. The system for solid propellant creep testing under thermally-mechanically coupled conditions of claim 1 wherein said test piece cartridge assembly further comprises a lower cross member positioned opposite said upper cross member and directly below said lower clamping unit;
and two ends of the lower cross beam are respectively fixed on two opposite wall surfaces in the constant-temperature and constant-humidity oil bath temperature box.
5. The system for testing creep of a solid propellant under thermally-coupled conditions according to claim 4 wherein the lower clamping unit is provided with a through hole; a plurality of through holes are formed in the lower cross beam;
one end of the steel silk thread is provided with a circular ring buckle, and the other end of the steel silk thread is provided with a circular ring;
one end of the steel wire is connected with the lower clamping unit through the through hole of the lower cross beam and the through hole of the lower clamping unit and the circular ring buckle;
the other end of the steel wire is connected with the weight shell through the circular ring.
6. The system for creep testing of a solid propellant under thermally-coupled conditions of claim 1 wherein the creep test data measuring means comprises an industrial camera, a marking paint and a crystal grid plate;
the marking paint is marked on the part to be observed of the solid propellant test piece;
the crystal grid plate is adhered to the marking paint.
7. The creep test system for the solid propellant under the condition of heat-force coupling according to claim 1, wherein the transparent oil storage liner is a transparent plastic oil storage liner with scale marks on the wall of the liner, and the precision is 1 g.
8. The system for testing creep of a solid propellant under a heat-force coupling condition according to claim 7, wherein the wall surface of the weight housing is hollowed out to expose the scale lines of the transparent oil storage inner container.
9. The creep test system for solid propellant under the condition of thermal-force coupling as claimed in claim 1 or 8, wherein the constant stress loading device further comprises kerosene disposed in the transparent oil storage inner container.
10. The creep test system for the solid propellant under the condition of heat-force coupling according to claim 1, wherein the test space of the constant-temperature and constant-humidity oil bath incubator is not less than 480 x 680 x 1100mm, the temperature control range is 5-80 ℃, and the heat conducting medium is silicone oil.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220870275.0U CN217403999U (en) | 2022-04-15 | 2022-04-15 | Solid propellant creep test system under heat-force coupling condition |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220870275.0U CN217403999U (en) | 2022-04-15 | 2022-04-15 | Solid propellant creep test system under heat-force coupling condition |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN217403999U true CN217403999U (en) | 2022-09-09 |
Family
ID=83140856
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202220870275.0U Active CN217403999U (en) | 2022-04-15 | 2022-04-15 | Solid propellant creep test system under heat-force coupling condition |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN217403999U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117110046A (en) * | 2023-08-28 | 2023-11-24 | 中国人民解放军火箭军工程大学 | Method for testing creep property of viscoelastic material |
-
2022
- 2022-04-15 CN CN202220870275.0U patent/CN217403999U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117110046A (en) * | 2023-08-28 | 2023-11-24 | 中国人民解放军火箭军工程大学 | Method for testing creep property of viscoelastic material |
| CN117110046B (en) * | 2023-08-28 | 2024-05-03 | 中国人民解放军火箭军工程大学 | Method for testing creep property of viscoelastic material |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN217403999U (en) | Solid propellant creep test system under heat-force coupling condition | |
| Weertman | Creep of polycrystalline aluminium as determined from strain rate tests | |
| US3457777A (en) | Loading rod for a triaxial cell soil tester | |
| CN109283052A (en) | The circular elasticity modulus of tubing and the measurement method of Poisson's ratio | |
| CN112595656B (en) | Testing device and evaluation method for adaptability of explosive device long-storage environment for bomb | |
| CN112285159B (en) | Method for measuring instantaneous oxygen concentration for explosive explosion suffocation effect evaluation | |
| CN114594226B (en) | Implosion damage power evaluation device and method | |
| US3395564A (en) | Elastomeric strain module and method of calibration thereof | |
| CN112113472B (en) | Application method of small-caliber gas gun bore pressure measuring device | |
| CN111046531B (en) | Baking combustion numerical simulation calculation method for HTPE type solid engine | |
| US2472108A (en) | Thrust gauge for projectiles | |
| US3100982A (en) | Controlled shock or impact testing fixture | |
| Katulka | Micro-electromechanical systems and test results of SiC MEMS for high-g launch applications | |
| Chen | A fixture for testing material at medium strain rates | |
| Liu et al. | Tensile creep behavior and cyclic fatigue/creep interaction of hot-isostatically pressed Si 3 N 4 | |
| SU1620882A1 (en) | Method of checking the quality of running-in of i.c.engine | |
| Wagner et al. | SOME MECHANICAL PROPERTIES OF GRAPHITE IN THE TEMPERATURE RANGE 20 TO 3000 | |
| Kaufman | Performance of electrical-resistance strain gages at cryogenic temperatures | |
| SU491893A1 (en) | Material Testing Device for Stretching | |
| Flynn | Some strain-gage applications to ballistic problems: Internal ballistic pressures and other parameters were determined from external-surface strain-gage measurements on several laboratory guns | |
| Min et al. | A New Fixture for Fatigue Testing | |
| Buswell et al. | Solid Inclusion Stress Gage in Composite Propellant Charges | |
| Conway et al. | High-temperature, low-cycle fatigue of advanced copper-base alloys for rocket nozzles. Part 1: Narloy Z | |
| SU429312A1 (en) | INSTALLATION FOR MECHANICAL TESTS IN VACUUM AT HIGH TEMPERATURES | |
| Sheffield et al. | Low pressure Hugoniot cusp in polymeric materials |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |