CN111380427A - Missile full-missile double-station parallel excitation reliability test method and system based on comprehensive stress - Google Patents
Missile full-missile double-station parallel excitation reliability test method and system based on comprehensive stress Download PDFInfo
- Publication number
- CN111380427A CN111380427A CN202010112485.9A CN202010112485A CN111380427A CN 111380427 A CN111380427 A CN 111380427A CN 202010112485 A CN202010112485 A CN 202010112485A CN 111380427 A CN111380427 A CN 111380427A
- Authority
- CN
- China
- Prior art keywords
- missile
- vibration
- double
- full
- comprehensive
- 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.)
- Pending
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B35/00—Testing or checking of ammunition
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The invention provides a missile full-missile double-platform parallel excitation reliability test method and system based on comprehensive stress, which are characterized in that a comprehensive stress environment section of a test is analyzed and determined according to a task section of a missile in the using process, a random vibration scheme of a double vibration platform is determined according to the environment section, the vibration input magnitude is ensured to be uniformly distributed, a reliability test is carried out on a full-missile-grade product by selecting a scheme 20-1 in a short-time high-risk scheme in GJB 899A, the comprehensive stress is used as the full-missile-grade acceleration test stress, and the reliability of the full missile is inspected through double-platform parallel excitation control. The method simultaneously selects a double-platform parallel excitation scheme under the comprehensive stress, selects a full-elasticity-grade product for testing, and solves the problems that the full-elasticity-grade product is difficult to truly simulate the environment and check the reliability.
Description
Technical Field
The invention relates to the technical field of reliability tests, in particular to a method and a system for testing reliability of full-elastic-level double-platform parallel excitation flight based on comprehensive stress.
Background
At present, a flight reliability test is carried out on a missile full-missile level, temperature, humidity, vibration or electric stress is generally selected as single acceleration stress, the failure mechanism of a whole machine excited by the test is single, the test efficiency is low, and the traditional single-vibration-table test method can cause unreasonable energy distribution of a product, incapability of meeting the requirements of multi-spectral shapes, too complex test tooling and unreal boundary characteristic simulation.
Patent document CN104034498A discloses a quick-clamping vibration test bed for missile vibration test, which is provided with: the vibration machine comprises a lower base, a vibration table, vibration springs, more than two vibration motors and three clamping structures, wherein the lower base and the vibration table are arranged in parallel, the vibration springs are used for connecting the lower base and the vibration table, the vibration motors are uniformly arranged at the lower part of the vibration table, and the three clamping structures are arranged on the vibration table in parallel at equal intervals; the vibration test bed can clamp the missile to enable the missile to vibrate along with the vibration test bed, the clamping is stable and reliable, and the vibration of the vibration test bed is transmitted to the missile without distortion as far as possible. However, according to the requirements of actual work, the industry needs to simulate the full-bomb flight reliability test more truly in the reliability test, and apply the vibration stress, the temperature, the humidity and the electric stress on the full bomb simultaneously.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a missile full-missile double-station parallel excitation reliability test method and system based on comprehensive stress.
The invention provides a missile full-missile double-station parallel excitation reliability test method based on comprehensive stress, which comprises the following steps of:
step S1: drawing a test profile according to a task profile of the missile in the using process, wherein the test profile can simulate the environmental conditions and the using state of a product for completing a task under the ground climate condition;
step S2: establishing double-station parallel excitation vibration in a comprehensive environment, determining the control direction of the double-station parallel excitation vibration, and simultaneously performing double-station parallel excitation control under the stress of the comprehensive environment;
step S3: and (3) carrying out reliability test on the full-elasticity-grade product by adopting a scheme 20-1 in a short-time high-risk scheme in GJB 899A.
Preferably, in step S2, the full projectile is simultaneously subjected to double-station parallel vibration in a comprehensive stress environment.
Preferably, the test section is provided with 4 simulated climatic environments in one cycle, wherein the simulated climatic environments are formed by temperature, humidity, vibration stress and electric stress in one 16h cycle.
Preferably, the temperature simulates the climate environment of spring, summer, autumn and winter encountered by the missile in real time according to the on-duty state of the missile in the battlefield, and the upper and lower temperature limits are high and low temperatures specified by technical specifications.
Preferably, each climate environment simulates and transmits flight vibration for 2 times per cycle, the vibration time is determined according to the flight time, the vibration direction is the direction vertical to the elastic axis, namely the Y direction, and the vibration condition is selected according to the flight environment section.
Preferably, during the power-on process, the nominal voltage accounts for 50% of the test power-on time, the upper and lower bias voltages account for 25% of each, and the general upper and lower bias voltages range to ± 10% of the nominal voltage.
The invention provides a missile full-missile double-platform parallel excitation reliability test system based on comprehensive stress, which comprises a comprehensive environment test box, a vibration platform unit, a suspension unit and a vibration control unit;
the comprehensive environment test box is an accommodating space with a window, and a tested product can be accommodated in the accommodating space;
the vibration table unit is used for placing two vibration tables below the comprehensive environment test box, and the two vibration tables are used for clamping and supporting two ends of a tested product through clamps respectively;
the hanging unit penetrates into the accommodating space from the top of the comprehensive environment test box to lift the clamp, so that the height of the clamp can be freely adjusted, and the vibration of the clamp is isolated;
the vibration control unit is provided with a control sensor on the clamp and a measurement sensor on the tested product so as to realize vibration control.
Preferably, the suspension unit comprises a rubber rope, a hoist and a steel wire rope;
the rubber rope and the hoist are respectively fixed on the bearing beam, the clamp is hoisted by penetrating a steel wire rope into the comprehensive environment test box, and the rubber rope can isolate the vibration of the clamp to generate restoring force so that a tested product returns to the original balance position in the vibration process;
the height of the clamp is adjusted by the hoist, and vertical movement and horizontal movement of the tested product are achieved.
Preferably, the vibration control unit includes a multi-dimensional control instrument, a sensor and a charge amplifier;
in the double-platform parallel excitation vibration test, a multidimensional controller sends out a driving signal, a power amplifier pushes a vibration platform, a signal of a control point on the table surface of the vibration platform is collected, the driving signal sent out by the multidimensional controller is corrected according to a control spectrum to obtain a response magnitude specified by the control point, and when the control is stable, a response point signal of a sensor on a tested product is collected to obtain a spectrogram of the response point.
Preferably, in the position selection of the control point on the table top, the two control points moving transversely are selected at the outer ends of the excitation points of the clamp in the same axial direction, and square control or rectangular control is adopted in the test.
Compared with the prior art, the invention has the following beneficial effects:
1. the temperature-vibration comprehensive stress is selected to replace single stress, so that the failure mechanism of the full bomb can be comprehensively excited.
2. The method simultaneously selects a double-platform parallel excitation scheme under the comprehensive stress, selects a full-elasticity-grade product for testing, and solves the problems that the full-elasticity-grade product is difficult to truly simulate the environment and check the reliability.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
FIG. 1 is a schematic view of a test installation of a dual parallel excitation control under a comprehensive stress of the present invention;
FIG. 2 is a schematic flow chart of the dual stage parallel excitation control according to the present invention;
fig. 3 is a schematic diagram of vibration control of a double-stage parallel vibration test according to the present invention.
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
The invention provides a full missile reliability test method for simulating the missile flight process in a comprehensive environment by adopting double-vibration-table excitation in a missile for the first time, solves the problem of boundary simulation in the missile reliability test of an elongated body, more truly verifies the reliability level of the full missile, and performs the reliability test by taking the full missile as a test object and through comprehensive stress and double-table parallel excitation.
In the implementation, a test profile is drawn according to a mission profile of the missile in the using process, and the test profile can simulate various environmental conditions and using states of a product for completing missions under various ground climate conditions. Secondly, a double-platform parallel excitation vibration system under the comprehensive environment is constructed, and the parallel excitation vibration control direction is determined. Again, reliability tests were performed using protocol 20-1 of the short-term high-risk protocols in GJB 899A.
Taking a ship-based air-borne missile as an example, a test section is drawn according to a mission section of the missile in the using process, and a cycle is 16h according to test requirements, wherein the test section is formed by temperature, humidity, vibration and electric stress.
The temperature stress simulates meteorological environments of spring, summer, autumn and winter which the missile may encounter in real time according to the on-duty state of the missile system in the position, the upper and lower temperature limits are high and low temperatures specified by technical specifications, and the specific stress level and the duration are shown in figure 1.
And humidifying and keeping for a certain time in each cycle at a high-temperature stage, carrying out dehumidification treatment for 27min (including cooling time) after the second energization of the product, and keeping the dehumidification state for 2h before the next energization of the cycle. The product simulates and transmits flight vibration for 2 times in each cycle and each climate environment, the vibration time is determined according to the flight time, the vibration direction is the vertical direction of the elastic axis, namely the Y direction, and the vibration condition is selected according to the flight environment section.
During the entire test, the product was subjected to a tensile bias electrical stress. In the power-on process, the nominal voltage accounts for 50% of the test power-on time, the upper and lower pull-down bias voltages respectively account for 25%, and the range of the common upper and lower pull-down bias voltages is +/-10% of the nominal voltage.
According to the actual combat requirement that the missile is in a standby launching state in the battle launching stage, each climate section is electrified for 2 times in the test according to the test section, the specific power on-off time is that the power starts to be electrified (simulating the battle launching) 1 minute before each vibration starting, the vibration time is covered by the continuous power on time, and the performance detection is carried out before launching, during launching flight and after flight. And the two vibration tables are simultaneously excited in parallel while the environmental stress is integrated, and the two vibration tables are synchronously controlled.
As shown in fig. 2, the test system includes a comprehensive environment test chamber, a vibration table unit (including a vibration table, a decoupling hydraulic bulb, and a special fixture), a suspension unit, a vibration control unit (a MIMO multidimensional controller, an acceleration sensor), and the like.
The vibration table system unit comprises a vibration table, decoupling hydraulic bulbs and special fixtures, the two vibration tables are placed below the test box, the decoupling hydraulic bulbs are connected to the moving coil, the bulbs and the special fixtures are connected through screws, meanwhile, heat preservation and insulation materials are additionally arranged between the bulbs and the special fixtures, and products are installed on the special fixtures. The vibration table and the ball head are arranged under the test box, the product and the clamp are arranged in the test box, and the product is electrified to test the cable to be led out through the lead hole to be connected with an external power supply and test equipment.
The hanging unit consists of two sets of rubber ropes, a hoist and a steel wire rope. At the top of the test box, each set of rubber rope and the hoist are respectively fixed on the bearing beam, and the special clamp is hoisted by penetrating the steel wire rope into the test box. The rubber rope can effectively isolate the vibration on the special fixture, so that the vibration of the special fixture can not be transmitted to the cross beam, the rubber rope can generate certain restoring force, and the product can return to the original balance position by itself in the vibration process. The rubber rope is arranged outside the test box, so that the change of the length of the rubber rope caused by expansion with heat and contraction with cold in high and low temperature environments is effectively avoided. The steel wire rope is less affected by high and low temperatures, so the steel wire rope is placed in a test box for force transmission. After the whole suspension system is completed, the height of the special fixture can be freely adjusted through the hoist, so that the missile is vertically moved and horizontally leveled, the mass of the missile is not borne by the ball head and the moving coil, and finally the free boundary condition in flight is simulated.
The vibration control unit comprises a multidimensional controller, a sensor, a charge amplifier and the like, the control sensor is fixed on the clamp, and the measurement sensor is installed on a product to realize vibration control.
As shown in fig. 3, in the double-bench parallel excitation vibration test, the vibration control system sends a driving signal from the controller according to a required random vibration control spectrum, the vibration bench is pushed by a power amplifier, a signal of a control point on the table surface of the vibration bench is collected, the driving signal sent by the controller is corrected according to the control spectrum to obtain a response magnitude specified by the control point, and when the control is stable, a response point signal of a sensor on the test piece is collected to obtain a spectrogram of the response point.
In the position selection of the control points, two control points moving transversely are selected at the outer ends of the excitation points of the special fixture in the same axial direction. During the test, square control (controlling the sensors to be equal to the number of the vibration tables) or rectangular control (controlling the sensors to be larger than the number of the vibration tables) can be adopted, and response limitation can be performed at key points of the product.
The statistical test scheme adopts the scheme 20-1 in the short-term high-risk scheme in GJB 899A, and the parameters of the scheme are shown in the following table.
Table reliability identification test protocol parameters
In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present application.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (10)
1. A missile full-missile double-station shunt excitation reliability test method based on comprehensive stress is characterized by comprising the following steps:
step S1: drawing a test profile according to a task profile of the missile in the using process, wherein the test profile can simulate the environmental conditions and the using state of a product for completing a task under the ground climate condition;
step S2: establishing double-station parallel excitation vibration in a comprehensive environment, determining the control direction of the double-station parallel excitation vibration, and simultaneously performing double-station parallel excitation control under the stress of the comprehensive environment;
step S3: and (3) carrying out reliability test on the full-elasticity-grade product by adopting a scheme 20-1 in a short-time high-risk scheme in GJB 899A.
2. The missile full-missile double-station shunt-excitation reliability test method based on the comprehensive stress as claimed in claim 1, wherein in the step S2, the full missile is subjected to double-station shunt-excitation vibration simultaneously under the comprehensive stress environment.
3. The missile full-missile double-station parallel excitation reliability test method based on the comprehensive stress as claimed in claim 1, wherein the test section is that 4 simulated climatic environments are set in one cycle of 16h, and each cycle is composed of temperature, humidity, vibration stress and electric stress.
4. The missile full-missile double-station parallel excitation reliability test method based on the comprehensive stress as claimed in claim 3, wherein the temperature simulates the climate environments of spring, summer, autumn and winter encountered by the missile in real time according to the on-duty state of the missile in a formation, and the upper and lower limits of the temperature are high and low temperatures specified by technical specifications.
5. The missile full-missile double-station parallel excitation reliability test method based on the comprehensive stress as claimed in claim 3, wherein each climate environment simulates and launches flight vibration for 2 times per cycle, the vibration time is determined according to the flight time, the vibration direction is the vertical direction of a missile axis, namely the Y direction, and the vibration condition is selected according to the flight environment section.
6. The missile full-missile double-station parallel excitation reliability test method based on the comprehensive stress as claimed in claim 3, wherein in the electrifying process, the nominal voltage accounts for 50% of the electrifying time of the test, the upper and lower pull bias voltages respectively account for 25%, and the general upper and lower pull bias voltages range from +/-10% of the nominal voltage.
7. A missile full-missile double-platform parallel excitation reliability test system based on comprehensive stress is characterized by comprising a comprehensive environment test box, a vibration platform unit, a suspension unit and a vibration control unit;
the comprehensive environment test box is an accommodating space with a window, and a tested product can be accommodated in the accommodating space;
the vibration table unit is used for placing two vibration tables below the comprehensive environment test box, and the two vibration tables are used for clamping and supporting two ends of a tested product through clamps respectively;
the hanging unit penetrates into the accommodating space from the top of the comprehensive environment test box to lift the clamp, so that the height of the clamp can be freely adjusted, and the vibration of the clamp is isolated;
the vibration control unit is provided with a control sensor on the clamp and a measurement sensor on the tested product so as to realize vibration control.
8. The missile full-missile double-station shunt excitation reliability test system based on the comprehensive stress as claimed in claim 7, wherein the suspension unit comprises a rubber rope, a hoist and a steel wire rope;
the rubber rope and the hoist are respectively fixed on the bearing beam, the clamp is hoisted by penetrating a steel wire rope into the comprehensive environment test box, and the rubber rope can isolate the vibration of the clamp to generate restoring force so that a tested product returns to the original balance position in the vibration process;
the height of the clamp is adjusted by the hoist, and vertical movement and horizontal movement of the tested product are achieved.
9. The missile full-missile double-station shunt excitation reliability test system based on the comprehensive stress as claimed in claim 7, wherein the vibration control unit comprises a multi-dimensional control instrument, a sensor and a charge amplifier;
in the double-platform parallel excitation vibration test, a multidimensional controller sends out a driving signal, a power amplifier pushes a vibration platform, a signal of a control point on the table surface of the vibration platform is collected, the driving signal sent out by the multidimensional controller is corrected according to a control spectrum to obtain a response magnitude specified by the control point, and when the control is stable, a response point signal of a sensor on a tested product is collected to obtain a spectrogram of the response point.
10. The missile full-missile double-station parallel excitation reliability test system based on the comprehensive stress as claimed in claim 9, wherein two transversely moving control points are selected at the outer ends of the excitation points of the clamps in the axial direction on the selection of the positions of the control points on the table top, and square control or rectangular control is adopted during the test.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010112485.9A CN111380427A (en) | 2020-02-24 | 2020-02-24 | Missile full-missile double-station parallel excitation reliability test method and system based on comprehensive stress |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010112485.9A CN111380427A (en) | 2020-02-24 | 2020-02-24 | Missile full-missile double-station parallel excitation reliability test method and system based on comprehensive stress |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111380427A true CN111380427A (en) | 2020-07-07 |
Family
ID=71218605
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010112485.9A Pending CN111380427A (en) | 2020-02-24 | 2020-02-24 | Missile full-missile double-station parallel excitation reliability test method and system based on comprehensive stress |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111380427A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112284667A (en) * | 2020-10-23 | 2021-01-29 | 中国兵器工业第五九研究所 | Ammunition equipment damage/fault excitation test method based on storage period environmental factors |
| CN112525460A (en) * | 2020-10-29 | 2021-03-19 | 中国人民解放军92942部队 | Test method based on multi-axis swinging and vibration composite test platform |
| CN113418670A (en) * | 2021-06-29 | 2021-09-21 | 上海机电工程研究所 | Vibration ejection separation test system |
| CN114112274A (en) * | 2021-11-05 | 2022-03-01 | 上海机电工程研究所 | Separation test device under random vibration ejection condition and installation test method thereof |
| CN114441201A (en) * | 2021-12-08 | 2022-05-06 | 中国人民解放军96901部队22分队 | Cruise missile whole missile reliability test method |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20050120797A1 (en) * | 2003-12-04 | 2005-06-09 | Butts Gary C. | Shakers and methods of testing |
| CN102735413A (en) * | 2012-06-15 | 2012-10-17 | 北京机电工程研究所 | Four-vibration table two-direction joint vibration device |
| CN103913283A (en) * | 2013-01-05 | 2014-07-09 | 广州苏试众博环境实验室有限公司 | Flexible moving type temperature and humidity testing system |
| CN104034498A (en) * | 2014-05-20 | 2014-09-10 | 于涛 | Quick clamping vibration test bench for missile vibration tests |
| CN104236836A (en) * | 2013-06-08 | 2014-12-24 | 北京强度环境研究所 | Pressure balancing system and method for rocket conveying pipeline system vibration test |
| CN105241625A (en) * | 2015-11-18 | 2016-01-13 | 苏州苏试试验仪器股份有限公司 | Connector structure used for dual-table synchronous vibration |
| CN106248327A (en) * | 2016-07-11 | 2016-12-21 | 北京强度环境研究所 | A kind of firing box Transport Vibration assay device and method |
| CN107192567A (en) * | 2016-03-15 | 2017-09-22 | 北京强度环境研究所 | Large-scale full-scale system generalization combined environment test device |
| CN107782995A (en) * | 2017-10-23 | 2018-03-09 | 中国北方车辆研究所 | A kind of electronic product combined stress is known the real situation test method |
| CN110646770A (en) * | 2019-08-21 | 2020-01-03 | 中国航天标准化研究所 | Reliability test verification system for radar microwave product |
-
2020
- 2020-02-24 CN CN202010112485.9A patent/CN111380427A/en active Pending
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20050120797A1 (en) * | 2003-12-04 | 2005-06-09 | Butts Gary C. | Shakers and methods of testing |
| CN102735413A (en) * | 2012-06-15 | 2012-10-17 | 北京机电工程研究所 | Four-vibration table two-direction joint vibration device |
| CN103913283A (en) * | 2013-01-05 | 2014-07-09 | 广州苏试众博环境实验室有限公司 | Flexible moving type temperature and humidity testing system |
| CN104236836A (en) * | 2013-06-08 | 2014-12-24 | 北京强度环境研究所 | Pressure balancing system and method for rocket conveying pipeline system vibration test |
| CN104034498A (en) * | 2014-05-20 | 2014-09-10 | 于涛 | Quick clamping vibration test bench for missile vibration tests |
| CN105241625A (en) * | 2015-11-18 | 2016-01-13 | 苏州苏试试验仪器股份有限公司 | Connector structure used for dual-table synchronous vibration |
| CN107192567A (en) * | 2016-03-15 | 2017-09-22 | 北京强度环境研究所 | Large-scale full-scale system generalization combined environment test device |
| CN106248327A (en) * | 2016-07-11 | 2016-12-21 | 北京强度环境研究所 | A kind of firing box Transport Vibration assay device and method |
| CN107782995A (en) * | 2017-10-23 | 2018-03-09 | 中国北方车辆研究所 | A kind of electronic product combined stress is known the real situation test method |
| CN110646770A (en) * | 2019-08-21 | 2020-01-03 | 中国航天标准化研究所 | Reliability test verification system for radar microwave product |
Non-Patent Citations (1)
| Title |
|---|
| 谭汉清等: "海军战术导弹可靠性试验工程实践", 《强度与环境》 * |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112284667A (en) * | 2020-10-23 | 2021-01-29 | 中国兵器工业第五九研究所 | Ammunition equipment damage/fault excitation test method based on storage period environmental factors |
| CN112525460A (en) * | 2020-10-29 | 2021-03-19 | 中国人民解放军92942部队 | Test method based on multi-axis swinging and vibration composite test platform |
| CN113418670A (en) * | 2021-06-29 | 2021-09-21 | 上海机电工程研究所 | Vibration ejection separation test system |
| CN114112274A (en) * | 2021-11-05 | 2022-03-01 | 上海机电工程研究所 | Separation test device under random vibration ejection condition and installation test method thereof |
| CN114441201A (en) * | 2021-12-08 | 2022-05-06 | 中国人民解放军96901部队22分队 | Cruise missile whole missile reliability test method |
| CN114441201B (en) * | 2021-12-08 | 2024-08-20 | 中国人民解放军96901部队22分队 | Method for testing reliability of whole missile of cruise missile |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN111380427A (en) | Missile full-missile double-station parallel excitation reliability test method and system based on comprehensive stress | |
| CN107121254B (en) | A kind of large size guided missile on-hook vibration rig and method | |
| CN104316872B (en) | Pressure relay storage life prediction method based on step-down degradation acceleration test | |
| CN203965169U (en) | A kind of vibration, centrifugal and climatic environment complex experiment equipment | |
| CN109596801A (en) | A kind of store experiment device and method for simulating solid rocket motor grain stress | |
| CN110702533A (en) | High-low temperature circulation and loading test device for long-term mechanical property of geosynthetic material | |
| CN107607247B (en) | Explosive explosion impulse and wind pressure combined test method | |
| CN105973799B (en) | Multispecimen humid heat cycling and alternating load coupling dynamic testing device | |
| CN105223078B (en) | A kind of protection type vibration isolator 5-linked creep testing machine | |
| CN110672159A (en) | Reliability identification test method suitable for combination of internal field and external field of electromechanical product | |
| CN110108551A (en) | Mechanical properties of rock test device and method based on acoustic emission detection technology | |
| CN106500981B (en) | A kind of rubber laminated spring is comprehensive performance test bed and its test method | |
| CN110542525A (en) | Method for testing vibration fatigue performance of metal in axial resonance state | |
| CN110160894B (en) | Impact load test system | |
| CN104075905B (en) | One is centrifuged and climatic environment complex experiment equipment | |
| CN111060411B (en) | Intelligent rock mass creep shear testing machine and testing method | |
| CN209513501U (en) | A kind of test device of geosynthetics long-term mechanical property | |
| CN104132792B (en) | One kind utilizes laser displacement signal testing bridge floor compliance device and its method | |
| CN210464190U (en) | Be used for penetration weapon electronic system mechanics equivalent test device | |
| CN210571360U (en) | Fatigue test device for rubber lifting lugs of exhaust system | |
| CN205898553U (en) | Use concrete temperature stress testing machine system that gos into formula environmental laboratory | |
| CN208688766U (en) | A kind of electric vibration testing device | |
| CN106248327A (en) | A kind of firing box Transport Vibration assay device and method | |
| CN114814664A (en) | Fretting wear experiment device and method for wire system of connecting wire clamp | |
| CN210323239U (en) | Test system suitable for multi-gear transmission conductor deicing fault research |
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 | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20200707 |