CN101105869A - Missile-borne solid state recorder - Google Patents
Missile-borne solid state recorder Download PDFInfo
- Publication number
- CN101105869A CN101105869A CNA2007100621702A CN200710062170A CN101105869A CN 101105869 A CN101105869 A CN 101105869A CN A2007100621702 A CNA2007100621702 A CN A2007100621702A CN 200710062170 A CN200710062170 A CN 200710062170A CN 101105869 A CN101105869 A CN 101105869A
- Authority
- CN
- China
- Prior art keywords
- signal input
- circuit plate
- missile
- coder
- connector
- 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.)
- Granted
Links
Images
Landscapes
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
- Casings For Electric Apparatus (AREA)
Abstract
The invention relates to the technical field of data record instruments, or a missile-borne solid record designed to solve the current solid recorder's flaws such as big bulk, restricted design of protection structure, poor anti-overloading performance, and incapability of repeated use. The device consists of a collector and a memorizer. As a drawer structure, the collector is composed of a cover board, a signal input module, a collection control module, and a base. As an embedded structure, the memorizer is composed of a shell, a separation cushion body, and a storage circuit arranged in the separation cushion body. The collector has the advantages of multiple collection channels and adjustable high sampling rate. Through the increase of the number of module layers, the invention can lift the number of collection channels, thus being suitable for the measurement of dynamic parameters of a variety of aircrafts; the memorizer can prevent internal storage circuit board from being damaged, and the data stored are safe and reliable in the circumstance of high overload. The invention can be used repeatedly. The invention has the advantages of small volume, high universality, high sampling rate, adjustable channel number, simple operation, low cost, etc.
Description
Technical field
The present invention relates to the datalogger technical field, be specially the real-time collection of space vehicle dynamic data such as being applied to rocket, guided missile, the missile-borne solid state recorder of storage.
Background technology
Dynamic data in the missile flight process is normally obtained by radio telemetry system, and entering the dynamic data of blackout range, guided missile mainly adopt register to obtain, register is ejected before being written into body drop ground, can obtain the flying quality of guided missile blackout range after it reclaims.Early stage on-board data recording adopts magnetic recorder, and shortcoming is that volume is big, power consumption big, poor, the poor reliability of random access capability, and anti-overload ability is poor; The beginning of the eighties in last century, domesticly begin to develop solid-state recorders, adopt semiconductor memory to realize the record of data as storage medium, compare with traditional magnetic recorder, though it improves at aspects such as power consumption, dirigibility, reliability, anti-overload ability, but because of volume is bigger, the safeguard structure design is limited, is difficult for protection in removal process; In addition, because in the anti high overload design, the integrated encapsulation mode of employing is cured as one with circuit and whole housing by Embedding Material, has caused the maintainability of system poor, can not reparation property and not reproducible usability.
Summary of the invention
The present invention exists in order to solve existing solid-state recorders that volume is big, the safeguard structure design is limited; in removal process, be difficult for protection and defectives such as anti-overload ability is poor, the maintainability is poor, not reproducible use; a kind of missile-borne solid state recorder that can be partially recycled is provided, has advantages such as novel structure, volume is little, precision is high, acquisition channel is many, memory capacity is big, anti-overload ability is strong, maintenance is easy.
The present invention adopts following technical scheme to realize: missile-borne solid state recorder, comprise sampler and coder and storer, be respectively equipped with connector on sampler and coder and the storer, be connected with cable between two connectors, described sampler and coder comprises at least one signal input module, be provided with the signal input circuit plate in the signal input module, signal input module one side is provided with the connector that is connected with the signal input circuit plate, the acquisition control module of establishing the acquisition control circuit plate in the signal input module below is provided with, acquisition control module one side is provided with the connector of unite when being used to connect on the bullet signal and power supply, connector is connected with the acquisition control circuit plate by cable, the signal input circuit plate is connected by the threeway connector with the acquisition control circuit plate, the signal input module top is provided with cover plate, the acquisition control module below is provided with base, cover plate, signal input module, acquisition control module and base are the steaming utensil type structure, and four by rectangular bolt together.Sampler and coder of the present invention adopts the dismantled and assembled structure of steaming utensil type, need not to change the one-piece construction of sampler and coder, by increasing the module number of plies, just can expand the acquisition channel number, make things convenient for the upgrading of systemic-function, wherein ground floor is a signal input module, and its signal input circuit plate mainly comprises signal conditioning circuit and channel selection circuit; The second layer is an acquisition control module, and its acquisition control circuit plate mainly is responsible for finishing data acquisition, coding, but online programming can be adjusted acquisition channel number and sampling rate flexibly.The acquisition controlling of sampler and coder of the present invention realizes based on FPGA, by changing the internal logic of FPGA, can adjust the channel sample rate and the existing hardware condition down-sampling passage number of register flexibly, in addition, can also increase signal input module, come the extended channel number, make it satisfy the application demand of different occasions.Control circuit on above-mentioned signal input circuit plate, the acquisition control circuit plate and channel sample rate and the passage number of how adjusting register by the internal logic that changes FPGA are that those of ordinary skill in the art is known, are existing known technology.
Described storer comprise shell and with its fixing casing cover, be provided with in the shell with it and closely cooperate all around, and by last cushion, the isolation buffer body that intermediate buffering layer and bottom breaker constitute, the embedded interior cap that is with inner casing close-fitting and is fixed in inner casing one side of intermediate buffering layer wherein with it, interior cap inboard is fixed with the memory circuit plate that inserts inner casing, described shell, isolation buffer body in the enclosure is set and is arranged on memory circuit plate nesting formula structure in the isolation buffer body, the memory circuit plate is connected with connector on being arranged on shell by cable.Storer of the present invention adopts the nested type buffer structure, the sort buffer structure makes the storer installing/dismounting flexible, be convenient to circuit debugging and reclaim the back reading, and can guarantee that the memory circuit plate can bear bigger overload, it bears evidence overload capacity and is higher than 20000g, satisfy aircraft and land the enormous impact that moment is subjected to, guarantee that the memory circuit plate of inside was not damaged when storer reclaimed, make aircraft data reliable, complete.Described isolation buffer body can adopt the castable rubber moulding.
Be fixed with vibroshock around the base of described sampler and coder, can reduce action of environmental stresses such as vibration that sampler and coder born, impact under state of flight, improved the reliability of system works.
The base below of described sampler and coder is provided with installing plate, and installing plate is provided with pilot hole, and the size of sampler and coder installing plate and the position of pilot hole, quantity can change flexibly according to environment for use, have improved its versatility.
Described storer shell is to be made by aluminium, and inner casing is made by steel, adopts the shell of aluminium as storer, in landing process, recovery can effectively absorb impact energy, reduce the overload that inner structure is born, simultaneously, the design of the outer aluminium of interior steel has also alleviated the weight of storer greatly.
The inner casing of described storer covers and is provided with trough, and interior cap front end is fixed with the line ball lid, and line ball covers a side and has wire hole, covers on the corresponding position on the intermediate buffering layer and with line ball and has through wires hole.After the assembling of interior cap and line ball lid finishes; cap also laterally was placed in the trough in the cable that is connected with the memory circuitry plate passed; the wire hole that covers a side through line ball passes then; the cabling of cable forms " Z " font; when cable is subjected to bigger external force; this cabling mode can reduce the effect of external force effectively, avoids circuit board to be damaged, and makes circuit board obtain more reliable protection.
Compared with prior art, register of the present invention mainly is made up of disposable sampler and coder and callable storer two parts, sampler and coder is mainly nursed one's health signal on the bullet, gather and coding, and according to the working method of control signal controlling recording device, it is many to have acquisition channel, the sampling precision height, characteristics such as multiple sampling rate is adjustable, the dismantled and assembled structure of steaming utensil type is adopted in Machine Design, need not to change the one-piece construction of sampler and coder, by increasing the module number of plies, just can expand the acquisition channel number, make things convenient for the upgrading of systemic-function, have good versatility, be fit to the measurement of multiple space vehicle dynamic parameter; Storer is mainly to storing from the data of sampler and coder and protecting; its exclusive nested type buffer structure design and cable routing design; the memory circuit plate of inside is not damaged in the time of can effectively protecting it to reclaim; Circuits System institute's deposit data under the high overload situation is safe and reliable; storer is beneficial to maintenance simultaneously, can be repeatedly used.In a word, the present invention has that volume is little, versatility good, sampling rate, the recording channel number is adjustable, simple to operate, low cost and other advantages, is applicable to obtaining and testing of the multiple parameter of aircraft.
Description of drawings
Fig. 1 is a principle of work block scheme of the present invention
Fig. 2 is an external structure synoptic diagram of the present invention
Fig. 3 is the cut-open view of sampler and coder among Fig. 2
Fig. 4 is the cut-open view of storer among Fig. 2
Fig. 5 is the structure enlarged diagram of isolation buffer body among Fig. 4
Fig. 6 is the structure enlarged diagram of inner casing among Fig. 4, interior cap and line ball lid
Fig. 7 is the structure enlarged diagram of cap in inner casing reaches among Fig. 4
Among the figure: cap 17-line ball lid 18-bottom breaker 19-shell 20-sampler and coder 21-connector 22-memory 23-cable 24-memory circuit plate 25-locating hole 26-trough 27-through wires hole 28-wire hole in 1-cover plate 2-signal input module 3-signal input circuit plate 4-connector 5-acquisition control module 6-acquisition control circuit plate 7, the upper cushion 14-intermediate buffering layer 15-inner casing 16-of 8-connector 9-base 10-damper 11-installing plate 12-casing cover 13-
Embodiment
Missile-borne solid state recorder, comprise sampler and coder 20 and storer 22, be respectively equipped with connector 8 on sampler and coder 20 and the storer 22,21, be connected with cable 23 between two connectors, be used for data input store with the sampler and coder collection, described sampler and coder 20 comprises at least one signal input module 2, be provided with signal input circuit plate 3 in the signal input module 2, signal input module 2 one sides are provided with the connector 4 that is connected with signal input circuit plate 3, the aircraft signal is transferred in the sampler and coder by connector 4, in being provided with, signal input module 2 belows establish the acquisition control module 5 of acquisition control circuit plate 6, acquisition control module 5 one sides are provided with the connector 7 of unite when being used to connect on the bullet signal and power supply, connector 7 is connected with acquisition control circuit plate 6 by cable, signal input circuit plate 3 is connected by the threeway connector with acquisition control circuit plate 6, signal input module 2 tops are provided with cover plate 1, acquisition control module 5 belows are provided with base 9, cover plate 1, signal input module 2, acquisition control module 5 is in the same place by rectangular bolt with base 9, be fixed with vibroshock 10 around the base 9 of sampler and coder 20, base 9 belows are provided with installing plate 11, be convenient to the assembling of sampler and coder and carrier, installing plate 11 is provided with pilot hole 25.
Described storer 22 comprise shell 19 and with its fixing casing cover 12, be provided with in the shell 19 with it and closely cooperate all around, and by last cushion 13, the isolation buffer body that intermediate buffering layer 14 and bottom breaker 18 constitute, intermediate buffering layer 14 embedded interior cap 16 that is with inner casing 15 close-fitting and is fixed in inner casing 15 1 sides wherein with it, interior cap 16 inboards are fixed with the memory circuit plate 24 that inserts inner casing 15, described shell 19, be arranged on the isolation buffer body in the shell 19 and be arranged on the interior memory circuit plate 24 nesting formula structures of isolation buffer body, storage medium on the memory circuit plate can adopt Flash Memory, it is little to have volume, the monolithic capacity is big, cost is low, non-volatile, characteristics such as anti-overload ability is strong, and the storage mode that adopts the limit to be close to and to write, make storer record data capable of circulation, guaranteed the real-time update of data, avoid because of external disturbance causes data by accidental erasure, this is that those of ordinary skill in the art is easy to realize; Memory circuit plate 24 is connected with connector 21 on being arranged on shell 19 by cable, and storer shell 19 is to be made by aluminium, and inner casing 15 is made by steel; The interior cap 16 of storer 22 is provided with trough 26, and interior cap 16 front ends are fixed with line ball lid 17, and line ball covers 17 1 sides and has wire hole 28, covers on the 17 corresponding positions on the intermediate buffering layer 14 and with line ball and has through wires hole 27.Described memory span adopts Redundancy Design, and applicable cases at present just can write down and reaches 5000 seconds missile-flight datas, is far longer than the actual flying time of guided missile, flying quality that can omnidistance record guided missile; Jumbo design has reduced the pressure because of the storage space lifting that sampling rate improves and the acquisition channel increase brings.
Missile-borne solid state recorder volume of the present invention is little, and sampler and coder individual module height is 15mm, and storer inner casing volume is 60 * 58 * 38mm
3
The present invention is supporting a ground testing system, can long-range (300m) control missile-borne solid state recorder and the multichannel dynamic data gathered of real-time monitoring record device, and the real-time rendering waveform is finished the monitoring and the storage of data easily under the situation of not dismounting guided missile.
When register is assembled to when testing on the aircraft, the aircraft signal is input in the sampler and coder by connector 4, the system signal is input in the sampler and coder by connector 7 when power lead and aircraft, and the ground testing system of register is also by in the connector 7 input sampler and coders; After system's energized, begin to enter the store status of gathering and editing, this moment, the signal of aircraft passed through to pass through in connector 8, cable 23 and connector 21 write stories behind the sampler and coder capturing and coding, data connect 300 meters cables to ground testing system by connector 7 simultaneously, monitor the data of being gathered by host computer; Sampler and coder receive that aircraft sends the time system signal after, the frame count zero clearing, the various dynamic parameters of beginning real time record aircraft, after aircraft lands, take out storer, by ground testing system the data in the storer are read and preserved, thereby finish the record of the omnidistance flying quality of aircraft.
Claims (5)
1. a missile-borne solid state recorder comprises sampler and coder (20) and storer (22), is respectively equipped with connector (8,21) on sampler and coder (20) and the storer (22), is connected with cable (23) between two connectors, it is characterized in that:
Described sampler and coder (20) comprises at least one signal input module (2), be provided with signal input circuit plate (3) in the signal input module (2), signal input module (2) one sides are provided with the connector (4) that is connected with signal input circuit plate (3), in being provided with, signal input module (2) below establishes the acquisition control module (5) of acquisition control circuit plate (6), acquisition control module (5) one sides are provided with the connector (7) of unite when being used to connect on the bullet signal and power supply, connector (7) is connected with acquisition control circuit plate (6) by cable, signal input circuit plate (3) is connected by the threeway connector with acquisition control circuit plate (6), signal input module (2) top is provided with cover plate (1), acquisition control module (5) below is provided with base (9), cover plate (1), signal input module (2), acquisition control module (5) and base (9) are the steaming utensil type structure, and four by rectangular bolt together;
Described storer (22) comprise shell (19) and with its fixing casing cover (12), be provided with in the shell (19) with it and closely cooperate all around, and by last cushion (13), the isolation buffer body that intermediate buffering layer (14) and bottom breaker (18) constitute, the embedded interior cap (16) that is with inner casing close-fitting (15) and is fixed in inner casing (15) one sides of intermediate buffering layer (14) wherein with it, interior cap (16) inboard is fixed with the memory circuit plate (24) that inserts inner casing (15), described shell (19), be arranged on the isolation buffer body in the shell (19) and be arranged on memory circuit plate (24) nesting formula structure in the isolation buffer body, memory circuit plate (24) is connected with connector (21) on being arranged on shell (19) by cable.
2. missile-borne solid state recorder according to claim 1 is characterized in that the base (9) of described sampler and coder (20) is fixed with vibroshock (10) all around.
3. missile-borne solid state recorder according to claim 1 and 2 is characterized in that base (9) below of described sampler and coder (20) is provided with installing plate (11), and installing plate (11) is provided with pilot hole (25).
4. missile-borne solid state recorder according to claim 1 and 2 is characterized in that described storer shell (19) is to be made by aluminium, and inner casing (15) is made by steel.
5. missile-borne solid state recorder according to claim 1 and 2, the interior cap (16) that it is characterized in that described storer (22) is provided with trough (26), interior cap (16) front end is fixed with line ball lid (17), line ball lid (17) one sides have wire hole (28), cover on (17) corresponding position on the intermediate buffering layer (14) and with line ball and have through wires hole (27).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2007100621702A CN100524366C (en) | 2007-06-14 | 2007-06-14 | Missile-borne solid state recorder |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2007100621702A CN100524366C (en) | 2007-06-14 | 2007-06-14 | Missile-borne solid state recorder |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101105869A true CN101105869A (en) | 2008-01-16 |
| CN100524366C CN100524366C (en) | 2009-08-05 |
Family
ID=38999752
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNB2007100621702A Expired - Fee Related CN100524366C (en) | 2007-06-14 | 2007-06-14 | Missile-borne solid state recorder |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN100524366C (en) |
Cited By (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102322771A (en) * | 2011-08-24 | 2012-01-18 | 中北大学 | High-overload test electronic recorder with loop damping buffer protection structure |
| CN102506617A (en) * | 2011-10-26 | 2012-06-20 | 王伟 | Missile-borne data testing system |
| CN101586930B (en) * | 2009-06-20 | 2012-12-19 | 中北大学 | High-speed data acquisition processing real-time retransmission device |
| CN105303641A (en) * | 2014-06-06 | 2016-02-03 | 上海机电工程研究所 | Statistical method of high-precision missile energizing lifetime |
| CN106570950A (en) * | 2016-11-14 | 2017-04-19 | 中北大学 | Miniaturized multifunctional structure missile measurement and control instrument module, shell and black box |
| CN106933155A (en) * | 2017-04-13 | 2017-07-07 | 北京建筑大学 | A kind of railcar operation recording device |
| CN107424239A (en) * | 2017-05-17 | 2017-12-01 | 中北大学 | A kind of distance recorder for repairing anti-high-g level acceleration and hitting |
| CN108597547A (en) * | 2018-04-17 | 2018-09-28 | 中北大学 | Back Word formula encapsulation of data memory safeguard structure |
| CN108966545A (en) * | 2017-05-19 | 2018-12-07 | 无锡巨日电子科技有限公司 | Damping circuit board arrangement |
| CN109741485A (en) * | 2018-12-26 | 2019-05-10 | 西安现代控制技术研究所 | A kind of aircraft data recorder |
| CN109974762A (en) * | 2019-04-16 | 2019-07-05 | 西安建筑科技大学 | A kind of data logger of destructive test for vessels under external pressure |
| CN111157028A (en) * | 2020-01-10 | 2020-05-15 | 北京时代精衡航天科技有限公司 | Drawer-type structure-based multi-signal acquisition and coding recorder |
| CN111599035A (en) * | 2020-05-19 | 2020-08-28 | 湖北三江航天红林探控有限公司 | Missile-borne data acquisition and storage device |
| CN112212912A (en) * | 2020-09-03 | 2021-01-12 | 北京电子工程总体研究所 | Telemetering data recording device and manufacturing method |
| CN114793405A (en) * | 2021-11-26 | 2022-07-26 | 北京时代精衡航天科技有限公司 | Based on laminating formula installation measurement storage device |
| CN115393977A (en) * | 2022-07-11 | 2022-11-25 | 陕西千山航空电子有限责任公司 | Novel missile-borne recorder |
| CN115620425A (en) * | 2022-12-08 | 2023-01-17 | 湖南高至科技有限公司 | High-overload aircraft recorder |
| CN115659707A (en) * | 2022-12-28 | 2023-01-31 | 中国空气动力研究与发展中心超高速空气动力研究所 | High-overload-resistant telemetry model for ballistic target telemetry test and model design method |
-
2007
- 2007-06-14 CN CNB2007100621702A patent/CN100524366C/en not_active Expired - Fee Related
Cited By (23)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101586930B (en) * | 2009-06-20 | 2012-12-19 | 中北大学 | High-speed data acquisition processing real-time retransmission device |
| CN102322771A (en) * | 2011-08-24 | 2012-01-18 | 中北大学 | High-overload test electronic recorder with loop damping buffer protection structure |
| CN102506617A (en) * | 2011-10-26 | 2012-06-20 | 王伟 | Missile-borne data testing system |
| CN105303641B (en) * | 2014-06-06 | 2018-08-03 | 上海机电工程研究所 | A kind of statistical method in high-precision guided missile energization service life |
| CN105303641A (en) * | 2014-06-06 | 2016-02-03 | 上海机电工程研究所 | Statistical method of high-precision missile energizing lifetime |
| CN106570950A (en) * | 2016-11-14 | 2017-04-19 | 中北大学 | Miniaturized multifunctional structure missile measurement and control instrument module, shell and black box |
| CN106570950B (en) * | 2016-11-14 | 2019-01-22 | 中北大学 | A kind of micromation multifunction structure bullet measurement and control instrument module, shell and black box |
| CN106933155A (en) * | 2017-04-13 | 2017-07-07 | 北京建筑大学 | A kind of railcar operation recording device |
| CN107424239A (en) * | 2017-05-17 | 2017-12-01 | 中北大学 | A kind of distance recorder for repairing anti-high-g level acceleration and hitting |
| CN107424239B (en) * | 2017-05-17 | 2019-08-02 | 中北大学 | A kind of distance recorder for repairing anti-high-g level acceleration and hitting |
| CN108966545A (en) * | 2017-05-19 | 2018-12-07 | 无锡巨日电子科技有限公司 | Damping circuit board arrangement |
| CN108597547A (en) * | 2018-04-17 | 2018-09-28 | 中北大学 | Back Word formula encapsulation of data memory safeguard structure |
| CN109741485A (en) * | 2018-12-26 | 2019-05-10 | 西安现代控制技术研究所 | A kind of aircraft data recorder |
| CN109974762A (en) * | 2019-04-16 | 2019-07-05 | 西安建筑科技大学 | A kind of data logger of destructive test for vessels under external pressure |
| CN111157028A (en) * | 2020-01-10 | 2020-05-15 | 北京时代精衡航天科技有限公司 | Drawer-type structure-based multi-signal acquisition and coding recorder |
| CN111599035A (en) * | 2020-05-19 | 2020-08-28 | 湖北三江航天红林探控有限公司 | Missile-borne data acquisition and storage device |
| CN112212912A (en) * | 2020-09-03 | 2021-01-12 | 北京电子工程总体研究所 | Telemetering data recording device and manufacturing method |
| CN114793405A (en) * | 2021-11-26 | 2022-07-26 | 北京时代精衡航天科技有限公司 | Based on laminating formula installation measurement storage device |
| CN114793405B (en) * | 2021-11-26 | 2024-06-07 | 北京时代精衡航天科技有限公司 | Based on laminating formula installation measurement storage device |
| CN115393977A (en) * | 2022-07-11 | 2022-11-25 | 陕西千山航空电子有限责任公司 | Novel missile-borne recorder |
| CN115620425A (en) * | 2022-12-08 | 2023-01-17 | 湖南高至科技有限公司 | High-overload aircraft recorder |
| CN115659707A (en) * | 2022-12-28 | 2023-01-31 | 中国空气动力研究与发展中心超高速空气动力研究所 | High-overload-resistant telemetry model for ballistic target telemetry test and model design method |
| CN115659707B (en) * | 2022-12-28 | 2023-03-17 | 中国空气动力研究与发展中心超高速空气动力研究所 | High overload resistant telemetry model for ballistic target telemetry test and model design method |
Also Published As
| Publication number | Publication date |
|---|---|
| CN100524366C (en) | 2009-08-05 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN100524366C (en) | Missile-borne solid state recorder | |
| CN100568295C (en) | Solid recorder for posture measuring | |
| US20090082918A1 (en) | Motions Dynamics Recorder | |
| CN102288346A (en) | Miniaturized digital large-scale sensor array impact monitoring system | |
| US20120008460A1 (en) | Data acquisition system with removable | |
| CN103278846A (en) | Microseismograph, microseism signal acquiring and de-noising method, and microseism signal acquiring method | |
| CN105699798A (en) | BIT self-detection method of onboard complex alarm equipment | |
| CN111650650A (en) | Unmanned aerial vehicle-mounted semi-aviation transient electromagnetic and magnetic cooperative acquisition system and method | |
| CN102506617A (en) | Missile-borne data testing system | |
| CN111780612A (en) | High-overload missile-borne comprehensive parameter testing system | |
| CN101915727A (en) | FPGA-based particle detection statistical system and method | |
| CN105160725A (en) | Self-powered measurement memory apparatus and recovery method | |
| CN102183350A (en) | Real-time impact monitoring instrument and method of large-scale aviation structure | |
| CN105366066A (en) | Micro-miniature ultra-low-power-consumption impact monitoring system based on diode array digitization | |
| CN111599035A (en) | Missile-borne data acquisition and storage device | |
| CN109253670A (en) | A kind of more bullet kind fuse flight course parameter measuring apparatus | |
| CN107340779A (en) | Voltage compensating method and device in a kind of flight control process | |
| CN109649668A (en) | A kind of aircraft health status managing device and method | |
| CN112540548B (en) | Grounding control method, grounding control device and readable storage medium | |
| CN109916240A (en) | One kind immersing oneself in bullet impact extrusion inlet procedure research simulation projectile-velotity detecting system | |
| CN108597547A (en) | Back Word formula encapsulation of data memory safeguard structure | |
| CN202362842U (en) | Flight data and audio recorder | |
| CN107424239B (en) | A kind of distance recorder for repairing anti-high-g level acceleration and hitting | |
| CN210428150U (en) | Aircraft data acquisition and storage system | |
| CN106355677A (en) | Maintenance-free aviation recorder and method for detecting states |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20090805 Termination date: 20160614 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |