CN116230057B - Missile-borne storage testing system capable of working in power failure and use method - Google Patents
Missile-borne storage testing system capable of working in power failure and use method Download PDFInfo
- Publication number
- CN116230057B CN116230057B CN202310269807.4A CN202310269807A CN116230057B CN 116230057 B CN116230057 B CN 116230057B CN 202310269807 A CN202310269807 A CN 202310269807A CN 116230057 B CN116230057 B CN 116230057B
- Authority
- CN
- China
- Prior art keywords
- module
- control processing
- missile
- data
- power
- 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
- 238000012360 testing method Methods 0.000 title claims abstract description 76
- 238000000034 method Methods 0.000 title claims abstract description 38
- 238000012545 processing Methods 0.000 claims abstract description 31
- 238000001514 detection method Methods 0.000 claims abstract description 27
- 238000004891 communication Methods 0.000 claims abstract description 25
- 230000003750 conditioning effect Effects 0.000 claims abstract description 18
- 238000013500 data storage Methods 0.000 claims abstract description 18
- 238000002955 isolation Methods 0.000 claims abstract description 15
- 230000003287 optical effect Effects 0.000 claims abstract description 14
- 230000008569 process Effects 0.000 claims description 13
- 239000003990 capacitor Substances 0.000 claims description 7
- 239000007787 solid Substances 0.000 claims description 7
- 230000005540 biological transmission Effects 0.000 claims description 5
- 230000008878 coupling Effects 0.000 claims description 4
- 238000010168 coupling process Methods 0.000 claims description 4
- 238000005859 coupling reaction Methods 0.000 claims description 4
- 238000005259 measurement Methods 0.000 claims description 4
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 4
- 230000003321 amplification Effects 0.000 claims description 3
- 238000010304 firing Methods 0.000 claims description 3
- 238000003199 nucleic acid amplification method Methods 0.000 claims description 3
- 244000137852 Petrea volubilis Species 0.000 claims description 2
- 239000003292 glue Substances 0.000 claims description 2
- 238000005070 sampling Methods 0.000 abstract description 5
- 230000001133 acceleration Effects 0.000 description 10
- 239000002184 metal Substances 0.000 description 9
- 238000010586 diagram Methods 0.000 description 6
- 238000002474 experimental method Methods 0.000 description 5
- 238000005516 engineering process Methods 0.000 description 4
- 230000007547 defect Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000004146 energy storage Methods 0.000 description 2
- 230000007613 environmental effect Effects 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 230000035939 shock Effects 0.000 description 2
- 230000008054 signal transmission Effects 0.000 description 2
- 230000001052 transient effect Effects 0.000 description 2
- 230000002411 adverse Effects 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 238000001914 filtration Methods 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 238000011084 recovery Methods 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
Classifications
-
- G—PHYSICS
- G11—INFORMATION STORAGE
- G11C—STATIC STORES
- G11C29/00—Checking stores for correct operation ; Subsequent repair; Testing stores during standby or offline operation
- G11C29/04—Detection or location of defective memory elements, e.g. cell constructio details, timing of test signals
-
- G—PHYSICS
- G11—INFORMATION STORAGE
- G11C—STATIC STORES
- G11C29/00—Checking stores for correct operation ; Subsequent repair; Testing stores during standby or offline operation
- G11C29/04—Detection or location of defective memory elements, e.g. cell constructio details, timing of test signals
- G11C2029/0401—Detection or location of defective memory elements, e.g. cell constructio details, timing of test signals in embedded memories
-
- G—PHYSICS
- G11—INFORMATION STORAGE
- G11C—STATIC STORES
- G11C29/00—Checking stores for correct operation ; Subsequent repair; Testing stores during standby or offline operation
- G11C29/04—Detection or location of defective memory elements, e.g. cell constructio details, timing of test signals
- G11C2029/0407—Detection or location of defective memory elements, e.g. cell constructio details, timing of test signals on power on
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02D—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN INFORMATION AND COMMUNICATION TECHNOLOGIES [ICT], I.E. INFORMATION AND COMMUNICATION TECHNOLOGIES AIMING AT THE REDUCTION OF THEIR OWN ENERGY USE
- Y02D10/00—Energy efficient computing, e.g. low power processors, power management or thermal management
Landscapes
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
The invention discloses a power-down operable missile-borne storage test system and a use method thereof, wherein the system comprises an upper computer data acquisition terminal and a storage test hardware circuit, wherein the storage test hardware circuit is connected with an external power supply; the storage test hardware circuit comprises a control processing module, a signal conditioning circuit, a data storage device, an attitude detection module, a positioning module, a wireless communication module and an optical coupler isolation module, wherein the signal conditioning circuit, the data storage device, the attitude detection module, the positioning module, the wireless communication module and the optical coupler isolation module are connected with the control processing module, the optical coupler isolation module is connected with the secondary ignition device, the wireless communication module is connected with the data acquisition terminal of the upper computer, and the signal conditioning circuit is connected with the external strain test device. The invention adopts the missile-borne storage testing system capable of working when power is lost and the using method, and the system can work when power is lost, can emit and recover and can change the sampling rate.
Description
Technical Field
The invention relates to the technical field of missile-borne storage testing, in particular to a missile-borne storage testing system capable of working when power is lost and a using method thereof.
Background
With the continuous development of military technologies, the strength of military fields such as weapons, aviation, missiles and the like is increasingly strong. Modern warfare has not been limited to single medium collisions only, but has evolved into multi-dimensional angular pursuits. As a weapon developed for hundreds of years, the conventional artillery has been developed into an advanced weapon such as missile and rocket projectile, and as the technology of the projectile is higher and higher, the requirement for measuring the flight parameters of the projectile is higher and higher, so that the missile-borne storage technology is generated.
The existing missile-borne storage technology integrates a sensor, data storage equipment, a control module and the like to form a miniaturized test system, the system is installed on a test object, an experiment is started, after the experiment is finished, data are imported into an upper computer for subsequent processing, and the storage test system can already meet the detection of most parameters, but is applied to the missile-borne system, and has the following problems:
1. because the projectile remains are required to be recovered after the experiment is completed and the data are uploaded to an upper computer for processing, the process firstly needs to obtain the accurate positions of the projectile remains, the flying distances of flying bodies such as missiles, rocket projectiles and the like are far away, and the existing storage test system does not have the functions of positioning guidance and the like, so that the recovery device has great difficulty after the experiment.
2. When the shell is in the exit or landing, huge acceleration can lead to loosening of a power interface, so that the system can be powered down briefly, and after the system is stabilized and powered up again, the system can record data again after the triggering condition is needed to be met again, and partial data recording is incomplete.
3. The shell can generate a huge impact after landing on the ground, and the impact can generate complex environmental noise, so that the test data is inaccurate.
4. The shell firing can go through three stages, namely, the three stages of discharging, flying and penetrating, and the time elapsed in each process is different from the acceleration born by the shell, so that the obtained data is unreliable if the data are sampled by adopting the same sampling rate.
5. Because the existing system has a multi-purpose metal housing enclosed inside the projectile, the metal has an adverse effect on the wireless transmission of signals.
Disclosure of Invention
The invention aims to provide a power-down operable missile-borne storage test system and a use method thereof.
In order to achieve the above purpose, the invention provides a power-down operable missile-borne storage test system and a use method thereof, wherein the system comprises an upper computer data acquisition terminal and a storage test hardware circuit, and the storage test hardware circuit is connected with an external power supply;
the storage test hardware circuit comprises a control processing module, a signal conditioning circuit, a data storage device, an attitude detection module, a positioning module, a wireless communication module and an optical coupler isolation module, wherein the signal conditioning circuit, the data storage device, the attitude detection module, the positioning module, the wireless communication module and the optical coupler isolation module are connected with the control processing module, the optical coupler isolation module is connected with the secondary ignition device, the wireless communication module is connected with the data acquisition terminal of the upper computer, and the signal conditioning circuit is connected with the external strain detection module.
The method for using the missile-borne storage testing system capable of working in power failure comprises the following steps of:
s1, designing a storage test hardware circuit, integrating data storage equipment, a control processing module and a gesture detection module, wherein the strain gauge detection module is electrically connected with the control processing module through a signal conditioning circuit, and the gesture detection module is electrically connected with the control processing module;
s2, debugging the storage test hardware circuit, ensuring that each function is completely realized, and confirming that the communication between the storage test hardware circuit and the upper computer data acquisition terminal is normal;
s3, installing the shell, firing the shell after ignition, and receiving positioning signal data in real time by an upper computer data acquisition terminal; after the shell is filled with water, the shell is ignited by a secondary ignition device, and after the test is finished, the position of the shell remains is accurately found according to the positioning information;
s4, recovering the shell remains, reading and storing the test data, and calculating the flight attitude parameters in the shell flight process.
Preferably, the storing of the test data in step S4 includes strain measurement data, attitude detection data, and positioning information.
Preferably, strain measurement data are acquired by adopting strain gages, the surface of a gun body is polished clean by sand paper before the strain gages are pasted, then the bottom surface of the strain gages are coated with glue, the strain gages are placed at the polished positions, internal bubbles are extruded completely, and finally two leads of the strain gages are welded to a wiring terminal.
Preferably, the terminal is directly connected to an operational amplifying part of the signal conditioning circuit, and the signal is amplified by setting a proper resistor on an external gain pin of the amplifier, and the relation between the amplification factor and the resistance is as follows:
wherein: v (V) O For the output terminal voltage, R G Is a gain resistor, V C Is the difference between the positive and negative input voltages.
Preferably, the gesture detection data are collected by a gesture detection module.
Preferably, the positioning information is generated by a positioning module, the positioning module transmits the positioning information to a control processing module, the control processing module transmits the positioning information to an upper computer data acquisition terminal in a wireless transmission mode, and the position of the shell debris can be accurately found through the positioning information after the shell lands.
Therefore, the invention adopts the missile-borne storage testing system capable of working when power is lost and the using method thereof, and has the following technical effects:
(1) The whole power consumption of the storage test system is reduced, the storage test system can still work for a period of time after power failure in the flight process, the requirement of the storage test device on the shock resistance of the battery is reduced, the data can be wirelessly transmitted to an upper computer by combining a data acquisition terminal, the data processing is convenient, and the sampling rate can be changed according to different flight stages in the flight process, so that the acquired data is more accurate and reliable.
(2) The problem that shells are difficult to recycle after landing is reasonably solved, the information of the landing places of the shells is obtained through the three-dimensional position locating module, the position information is sent to the test terminal in a wireless communication mode, and testers can recycle the shell remains and the like rapidly and effectively.
(3) The problem of the transient power failure that leads to because of the impact problem when having solved the flight is through adopting low-power consumption treater, uses solid electric capacity as energy storage element, guarantees that system still can normally work a period after the instantaneous power failure.
(4) The storage testing system overcomes the defect that when the existing storage testing system is in wireless transmission, the metal chassis shell shields signals, the chassis adopts a hole type structure, rubber is injected into the hole, signals are prevented from being shielded, and the stability of the structure is guaranteed.
The technical scheme of the invention is further described in detail through the drawings and the embodiments.
Drawings
FIG. 1 is a block diagram of a system architecture of a power down operable missile-borne storage testing system and method of use in accordance with the present invention;
FIG. 2 is a diagram of the status of a power down operable missile-borne storage testing system and a method of use of the invention;
FIG. 3 is a data communication instruction interaction flow chart of a power down operable missile-borne storage testing system and method of use of the present invention;
FIG. 4 is a schematic diagram of a power down operable missile-borne storage testing system and method of use of the present invention;
fig. 5 is a diagram of the installation location of a power down operable missile-borne storage test system and a method of use of the storage test system in a projectile in accordance with the present invention.
Reference numerals
1. Storing the test hardware circuit; 2. an external power source; 3. a strain detection module; 4. a signal conditioning circuit; 5. a data storage device; 6. a gesture detection module; 7. a control processing module; 8. a positioning module; 9. a secondary ignition device; 10. an optocoupler isolation circuit; 11. a wireless communication module; 12. the upper computer data acquisition terminal;
13. a hole; 14. a metal chassis;
15. a shell body; 16. a storage test system housing; 17. and a system power supply.
Detailed Description
The technical scheme of the invention is further described below through the attached drawings and the embodiments.
Unless defined otherwise, technical or scientific terms used herein should be given the ordinary meaning as understood by one of ordinary skill in the art to which this invention belongs.
It will be evident to those skilled in the art that the invention is not limited to the details of the foregoing illustrative embodiments, and that the present invention may be embodied in other specific forms without departing from the spirit or essential characteristics thereof. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein.
Furthermore, it should be understood that although the present disclosure describes embodiments, not every embodiment is provided with a separate embodiment, and that this description is provided for clarity only, and that the disclosure is not limited to the embodiments described in detail below, and that the embodiments described in the examples may be combined as appropriate to form other embodiments that will be apparent to those skilled in the art. Such other embodiments are also within the scope of the present invention.
It should also be understood that the above-mentioned embodiments are only for explaining the present invention, the protection scope of the present invention is not limited thereto, and any person skilled in the art should be able to cover the protection scope of the present invention by equally replacing or changing the technical scheme and the inventive concept thereof within the scope of the present invention.
Techniques, methods, and apparatus known to one of ordinary skill in the relevant art may not be discussed in detail, but are intended to be considered part of the specification where appropriate.
The disclosures of the prior art documents cited in the present specification are incorporated by reference in their entirety into the present invention and are therefore part of the present disclosure.
Example 1
As shown in the figure, the missile-borne storage test system capable of working when power failure occurs comprises an upper computer data acquisition terminal 12 and a storage test hardware circuit 1, wherein the storage test hardware circuit 1 is connected with an external power supply 2;
the storage test hardware circuit 1 comprises a control processing module 7, a signal conditioning circuit 4, a data storage device 5, an attitude detection module 6, a positioning module 8, a wireless communication module 11 and an optical coupling isolation module 10, wherein the signal conditioning circuit 4, the data storage device 5, the attitude detection module 6, the positioning module 8, the wireless communication module 11 and the optical coupling isolation module 10 are connected with a secondary ignition device 9, the wireless communication module 11 is connected with an upper computer data acquisition terminal 12, and the signal conditioning circuit 4 is connected with an external strain detection module 3.
The upper computer data acquisition terminal 12 realizes information exchange and control with the storage test hardware circuit 1 in a wireless transmission mode. The storage test hardware circuit 1 is packaged by a metal case 14, the metal case 14 is shown in fig. 4, a hole 13 embedded with rubber is formed in the metal case 14, signal transmission and installation of a circuit board are facilitated, the storage test hardware circuit 1 is powered by an external power supply 2, a control processing module 7 is connected with a strain test module 3 by a signal conditioning circuit 4, and the control processing module 7 is connected with a secondary ignition device 9 by an optical coupler isolation module 10.
The storage test hardware circuit is internally embedded with a data storage device 5, a gesture detection module 6, a positioning module 8 and a wireless communication module 11, and the modules can realize corresponding functions as follows:
the positioning module 8 is a multimode positioning module, and can send real-time positions of the shells in the flying process to the upper computer data acquisition terminal 12, so that testers can accurately find the remains of the shells according to the position information, and the remains after being launched can be conveniently recovered.
The microprocessor is arranged in the control processing module 7, the power failure working characteristic of the microprocessor is that the characteristic of low working power consumption of the microprocessor is utilized, and the microprocessor can still work for hundreds of milliseconds after power failure by combining the electric quantity stored by the solid capacitor, so that the data acquisition is not influenced, and the capacitor can be charged again after power failure is recovered.
The gesture detection module 6 consists of a nine-axis gesture sensor and a three-axis accelerometer, and can detect three-axis angle, angular velocity, acceleration and magnetic field signals through the three-axis gesture sensor and the three-axis accelerometer, wherein the three-axis angle, the angular velocity, the acceleration and the magnetic field signals are integrated on a circuit board and are directly connected with the signal conditioning circuit 4, and the signals are collected and stored by the control processing module after being amplified and filtered. The attitude detector 6 is internally provided with an automatic compensation and filtering algorithm, so that errors caused by environmental changes are reduced to the greatest extent.
The wireless communication module 11 is a module supporting remote control and remote data communication, a tester can communicate with the control end of the storage test hardware circuit in real time through the module, monitor the system state in real time, acquire experimental data in the first time, and the lower computer can transmit positioning information to the data acquisition terminal of the upper computer in real time through the module, so that the debris after the testing is convenient to find and recycle.
Fig. 2 is a state transition diagram of the system between different periods, and according to the requirement of the system when the system is in practical application, the working state of the system is divided into the following parts, namely a reactive power state, data of the data storage device 5 are read, a delay state, a standby low-power consumption state, an ignition waiting instruction, a trigger waiting state, a data acquisition state and position information are sequentially sent, and finally the acquisition is finished, the standby low-power consumption state is returned, and the acquired data is uploaded after being recovered.
After the instrument is powered on, the instrument firstly reads the value of a specific state bit of the data storage device 5, the initial value is preset and represents the initial power on, then the number is added once every time the instrument is powered on, if the value of the bit is not the initial value after the instrument is powered off, the data acquisition program is directly executed; if the power-on is the primary power-on, the instrument prompts to set delay time which is used for installing the shell; and after the fixed shell is installed, the delay time is ended, the instrument enters a low-power consumption standby mode, the system initialization is completed, and the instrument enters a waiting instruction state.
The tester can achieve different functions through different instructions, the main instructions are shown in figure 3, and the instructions are used for acquiring experimental data after the experiment is finished; the data clearing instruction is mainly used for clearing data in the data storage device 5; the system is characterized in that the system comprises an upper computer, an optical coupler isolation module 10, an optical coupler isolation module 9, a data communication module and a data communication module, wherein the upper computer sends an ignition signal, the system continuously collects acceleration signals in a state to be emitted, when the acceleration value is larger than a certain set value, the system judges the state to be emitted, when the acceleration value is larger than the certain set value, the system starts to collect and record all channel data, starts to time, when the acceleration value is smaller than the certain set value, the system judges the state to be water-in, and sends the ignition signal to the secondary ignition module 9, and in order to prevent the interference of the ignition signal on the data communication signal, the optical coupler isolation module 10 is added between the two signals to isolate the input signal from an output end at two ends. The whole transmitting process continuously collects data until the water is over, the timing is stopped, and the positioning module 6 continuously transmits three-dimensional position information (longitude, latitude and altitude) to the upper computer through the wireless communication module 11 during the flying. In the whole flight process, the acceleration values and directions of all stages are inconsistent, the stage where the flight is located is judged according to the acceleration values acquired by the attitude sensor, the proper sampling rate is selected for acquisition, after water entering is finished, the system enters a waiting instruction state, and the specific bit value in the data storage device 5 can be given an initial value again. After the tester recovers the debris, the data can be uploaded to the upper computer data acquisition terminal 12 for subsequent data processing.
The invention can solve the problem that the system temporarily fails in the flying process of the shell, as described above, the system can read the initial value preset at the specific position of the data storage device 5 after power-on, if the value is still the initial value, the initial power-on is indicated, if the value is changed, the system jumps to the data acquisition part in the figure 2 to continuously acquire signals, the power supply source in the power-off period is a solid capacitor, the working time of the system in the working state is dependent on the capacity value of the solid capacitor, and the power-off problem in the flying process is generally transient, so that the problem can be solved by the method.
Fig. 4 is a diagram of a chassis structure, in which a mounting position of the chassis in the shell is as shown in fig. 5, and a hardware circuit is mounted in a metal chassis 14 with a hole structure, so that the problem of electrostatic shielding can be reasonably solved, excessive modification on materials and appearance of the chassis is not required, the size of the chassis can be modified according to occupied space in the shell, communication and positioning antennas are not required to be modified, and the difficulty is reduced for later debugging.
Therefore, the missile-borne storage test system capable of working after power failure and the use method thereof are adopted, the overall power consumption of the storage test system is reduced, so that the storage test system can still work for a period of time after power failure in the flight process, the requirement of the storage test device on the shock resistance of a battery is reduced, the data can be wirelessly transmitted to an upper computer by combining a data acquisition terminal, the data processing is convenient, and the sampling rate can be changed according to different flight stages in the flight process, so that the acquired data is more accurate and reliable; the problem that the shells are difficult to recycle after landing is reasonably solved, the information of the landing places of the shells is obtained through the three-dimensional position locating module, the position information is sent to the test terminal in a wireless communication mode, and testers can recycle the shell remains and the like rapidly and effectively; the problem of short power failure caused by impact during flight is solved, and the system can still normally work for a period of time after instantaneous power failure by adopting a low-power-consumption processor and using a solid capacitor as an energy storage element; the storage testing system overcomes the defect that when the existing storage testing system is in wireless transmission, the metal chassis shell shields signals, the chassis adopts a hole type structure, rubber is injected into the hole, signals are prevented from being shielded, and the stability of the structure is guaranteed.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solution of the present invention and not for limiting it, and although the present invention has been described in detail with reference to the preferred embodiments, it will be understood by those skilled in the art that: the technical scheme of the invention can be modified or replaced by the same, and the modified technical scheme cannot deviate from the spirit and scope of the technical scheme of the invention.
Claims (7)
1. A power-down operable missile-borne storage test system is characterized in that: the system comprises an upper computer data acquisition terminal and a storage test hardware circuit, wherein the storage test hardware circuit is connected with an external power supply;
the storage test hardware circuit comprises a control processing module, a signal conditioning circuit, a data storage device, an attitude detection module, a positioning module, a wireless communication module and an optical coupling isolation module, wherein the signal conditioning circuit, the data storage device, the attitude detection module, the positioning module, the wireless communication module and the optical coupling isolation module are connected with the control processing module;
the control processing module is internally provided with a microprocessor, and the power-down working characteristic of the control processing module means that the microprocessor can still work for hundreds of milliseconds after power failure by utilizing the characteristic of low working power consumption of the microprocessor and combining the electric quantity stored by the solid capacitor.
2. The utility model provides a method for using power down operable missile-borne storage test system which characterized in that: the method comprises the following steps:
s1, designing a storage test hardware circuit, integrating data storage equipment, a control processing module and a gesture detection module, wherein the strain gauge detection module is electrically connected with the control processing module through a signal conditioning circuit, and the gesture detection module is electrically connected with the control processing module;
s2, debugging the storage test hardware circuit, ensuring that each function is completely realized, and confirming that the communication between the storage test hardware circuit and the upper computer data acquisition terminal is normal;
s3, installing the shell, firing the shell after ignition, and receiving positioning signal data in real time by an upper computer data acquisition terminal; after the shell is filled with water, the shell is ignited by a secondary ignition device, and after the test is finished, the position of the shell remains is accurately found according to the positioning information;
s4, recovering the shell remains, reading and storing the test data, and calculating flight attitude parameters in the process of the shell flight;
the control processing module is internally provided with a microprocessor, and the power-down working characteristic of the control processing module means that the microprocessor can still work for hundreds of milliseconds after power failure by utilizing the characteristic of low working power consumption of the microprocessor and combining the electric quantity stored by the solid capacitor.
3. A method of using a power down operable missile-borne storage testing system according to claim 2, wherein: the storing of the test data in step S4 includes strain measurement data, gesture detection data and positioning information.
4. A method of using a power down operable missile-borne storage testing system according to claim 3, wherein: the strain measurement data are acquired by adopting strain gages, the surface of a gun body is polished clean by sand paper before the strain gages are pasted, then the bottom surface of the strain gages is coated with glue, the strain gages are placed at the polished positions, internal bubbles are extruded completely, and finally two leads of the strain gages are welded to a wiring terminal.
5. A method of using a power down operable missile-borne storage testing system according to claim 4, wherein: the terminal is directly connected to the operational amplification part of the signal conditioning circuit, and the signal is amplified by setting a proper resistor on an external gain pin of the amplifier, wherein the relation between the amplification factor and the resistance value is as follows:
wherein: v (V) O For the output terminal voltage, R G Is a gain resistor, V C Is the difference between the positive and negative input voltages.
6. A method of using a power down operable missile-borne storage testing system according to claim 3, wherein: the gesture detection data are collected through a gesture detection module.
7. A method of using a power down operable missile-borne storage testing system according to claim 3, wherein: the positioning information is generated by the positioning module, the positioning module transmits the positioning information to the control processing module, the control processing module transmits the positioning information to the upper computer data acquisition terminal in a wireless transmission mode, and the positions of the cannonball remains can be accurately found through the positioning information after the cannonball lands.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310269807.4A CN116230057B (en) | 2023-03-20 | 2023-03-20 | Missile-borne storage testing system capable of working in power failure and use method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310269807.4A CN116230057B (en) | 2023-03-20 | 2023-03-20 | Missile-borne storage testing system capable of working in power failure and use method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN116230057A CN116230057A (en) | 2023-06-06 |
| CN116230057B true CN116230057B (en) | 2023-11-14 |
Family
ID=86582415
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310269807.4A Active CN116230057B (en) | 2023-03-20 | 2023-03-20 | Missile-borne storage testing system capable of working in power failure and use method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116230057B (en) |
Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101206162A (en) * | 2007-12-14 | 2008-06-25 | 哈尔滨工程大学 | System for data acquisition and signal treatment of testing flat wheel |
| CN103023590A (en) * | 2012-12-08 | 2013-04-03 | 北京工业大学 | Acquisition and processing system of global system for mobile communications for railway (GSM-R) network interference signals |
| JP2016157383A (en) * | 2015-02-26 | 2016-09-01 | 富士通株式会社 | Semiconductor integrated circuit device, wireless sensor network terminal, and memory control method of semiconductor integrated circuit device |
| CN105954574A (en) * | 2016-07-22 | 2016-09-21 | 安徽亚辉电气自动化有限公司 | Measurement and control system for switch cabinet zero-sequence current |
| US9928884B1 (en) * | 2017-05-01 | 2018-03-27 | International Business Machines Corporation | Elastic memory expansion chip architecture |
| WO2018068554A1 (en) * | 2016-10-14 | 2018-04-19 | 中兴通讯股份有限公司 | Mobile terminal and anti-theft method |
| EP3690452A1 (en) * | 2019-01-31 | 2020-08-05 | ABB Schweiz AG | On-line power measurement |
| CN111637950A (en) * | 2020-05-19 | 2020-09-08 | 哈尔滨工程大学 | Indoor leak protection water system based on infrared range finding |
| CN113835511A (en) * | 2021-09-27 | 2021-12-24 | 重庆邮电大学 | Method, system and computer equipment for power failure protection of cache data |
| WO2022048227A1 (en) * | 2020-09-07 | 2022-03-10 | 湖南国科微电子股份有限公司 | Data protection apparatus, storage device, and storage system |
| CN217718669U (en) * | 2022-03-07 | 2022-11-01 | 苏州真感微电子科技有限公司 | Sensor chip output test hardware |
| CN115755685A (en) * | 2022-11-09 | 2023-03-07 | 中国海洋大学 | Dual-processor ocean drifting buoy control system |
-
2023
- 2023-03-20 CN CN202310269807.4A patent/CN116230057B/en active Active
Patent Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101206162A (en) * | 2007-12-14 | 2008-06-25 | 哈尔滨工程大学 | System for data acquisition and signal treatment of testing flat wheel |
| CN103023590A (en) * | 2012-12-08 | 2013-04-03 | 北京工业大学 | Acquisition and processing system of global system for mobile communications for railway (GSM-R) network interference signals |
| JP2016157383A (en) * | 2015-02-26 | 2016-09-01 | 富士通株式会社 | Semiconductor integrated circuit device, wireless sensor network terminal, and memory control method of semiconductor integrated circuit device |
| CN105954574A (en) * | 2016-07-22 | 2016-09-21 | 安徽亚辉电气自动化有限公司 | Measurement and control system for switch cabinet zero-sequence current |
| WO2018068554A1 (en) * | 2016-10-14 | 2018-04-19 | 中兴通讯股份有限公司 | Mobile terminal and anti-theft method |
| US9928884B1 (en) * | 2017-05-01 | 2018-03-27 | International Business Machines Corporation | Elastic memory expansion chip architecture |
| EP3690452A1 (en) * | 2019-01-31 | 2020-08-05 | ABB Schweiz AG | On-line power measurement |
| CN111637950A (en) * | 2020-05-19 | 2020-09-08 | 哈尔滨工程大学 | Indoor leak protection water system based on infrared range finding |
| WO2022048227A1 (en) * | 2020-09-07 | 2022-03-10 | 湖南国科微电子股份有限公司 | Data protection apparatus, storage device, and storage system |
| CN113835511A (en) * | 2021-09-27 | 2021-12-24 | 重庆邮电大学 | Method, system and computer equipment for power failure protection of cache data |
| CN217718669U (en) * | 2022-03-07 | 2022-11-01 | 苏州真感微电子科技有限公司 | Sensor chip output test hardware |
| CN115755685A (en) * | 2022-11-09 | 2023-03-07 | 中国海洋大学 | Dual-processor ocean drifting buoy control system |
Non-Patent Citations (1)
| Title |
|---|
| 翟志猛.《弹载卫星导航信号存储系统研究》.2014,1-78. * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN116230057A (en) | 2023-06-06 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN111780747A (en) | Large-airspace high-dynamic navigation guidance and control integrated system and method | |
| CN207907932U (en) | A kind of bullet posture and impact acceleration test device for shedding release bullet experiment | |
| CN110906810B (en) | ARM-based triaxial high-G-value sensor testing device and testing method | |
| CN101266189A (en) | Structural low-frequency vibration wireless patrol star network construction method | |
| CN106949781B (en) | A kind of self-propelled gun gun rotated accuracy method of testing and equipment | |
| CN111780612A (en) | High-overload missile-borne comprehensive parameter testing system | |
| CN210862405U (en) | Black box record appearance system on miniature bullet | |
| CN116230057B (en) | Missile-borne storage testing system capable of working in power failure and use method | |
| CN105676303A (en) | Terrestrial magnetism data collector | |
| CN109916240B (en) | Speed measuring system for simulating projectile for impact extrusion process research of countersunk head projectile | |
| CN216558556U (en) | Triaxial angular velocity measuring device for projectile body launching test | |
| CN1971213B (en) | Remotely-controlled helicopter-carried land form detection device | |
| CN116255979A (en) | Integrated navigation system, method and aircraft | |
| CN116449803A (en) | Rocket gun multi-bullet type common-frame emission control time sequence detection system and method | |
| CN111692930B (en) | Universal radio fuse throwing test system | |
| CN114313303B (en) | Unmanned aerial vehicle flight performance detection equipment, system and detection method | |
| CN211826546U (en) | Zero-time recording device for artificial earthquake depth sounding | |
| CN203773605U (en) | Flight data recorder of medium/small-sized unmanned aerial vehicle (UAV) | |
| CN118112970A (en) | Low-power-consumption missile-borne recording device suitable for cross-medium navigation body | |
| CN212482255U (en) | High-overload missile-borne comprehensive parameter testing system | |
| CN110645849A (en) | Missile-borne storage testing device and method based on hole-seam coupling | |
| CN110595426A (en) | System and method for measuring missile-borne angle | |
| CN111623804B (en) | Laser gyro test system and test method thereof | |
| CN113739648B (en) | Reusable technology demonstration verification rocket landing detection method, system and equipment | |
| CN210892886U (en) | Missile-borne storage testing device based on hole-seam coupling |
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 |