CN207976930U - A kind of spacecraft flight data analysis recording equipment - Google Patents

Abstract

The utility model provides a kind of spacecraft flight data analysis recording equipment, which is installed on inside spacecraft, including：Data acquisition module, data storage quickly analyze reading module and telemetering and localizing emission module with protection module, data；Data acquisition module obtains multichannel spacecraft data, will wait for that deposit data is sent to data storage with protection module, performance monitoring data is sent to data and is quickly analyzed in reading module；Data store and protection module, will wait for deposit data compression storage；Data quickly analyze reading module, and to performance monitoring data quick interpretation online, fault data is exported into telemetering and localizing emission module；Telemetering and localizing emission module pass down fault data, while for after spacecraft contacts to earth, emitting urgent positioning signal.The utility model can be monitored the in-orbit state of spacecraft carries out diagnosis and by data down transmission ground to failure, can be analyzed spacecraft state in the spacecraft terrestrial time that falls.

Description

A kind of spacecraft flight data analysis recording equipment

Technical field

The utility model is related to data interpretation analysis technical fields more particularly to a kind of spacecraft flight data analysis to record Equipment is passed for being acquired under storage, security protection, status monitoring, real-time diagnosis and data selectivity to spacecraft data.

Background technology

Spacecraft, e.g., the in-orbit condition monitoring and fault diagnosis of the spacecrafts such as rocket and satellite are Space Vehicle Health management Crucial and basis.For a long time, China's spacecraft mainly to spacecraft tightly track and measure by ground observing and controlling system, The data passed down by manual analysis spacecraft telemetry link, to realize the condition monitoring and fault diagnosis to spacecraft.But It is that, as the in-orbit spacecraft quantity in China is on the increase, Spacecraft malfunction rate increases therewith, and data analysis workload also increases rapidly It is long, it since the spacecraft data down transmission period is long, only relies on and passes spacecraft data under limited telemetering channel, by ground into line number According to interpretation, the needs of spacecraft in-orbit fast state monitoring and fault diagnosis are can no longer meet, Ground analysis overlong time is held On the opportunity for easily losing timely rescue spacecraft, there is an urgent need to spacecrafts to have in-orbit monitoring and self diagnostic capability certainly, event occurring It will sentence certainly when barrier and be passed under information and part significant data, and improve the analyzing processing efficiency that ground faces Spacecraft malfunction.

The service life of satellite operation on orbit in spacecraft is all very limited, is largely 1-2, no longer than 10 years.It defends After star exceeds service life, generally can gradually it pass away the earth from track under the action of atmospheric drag.But satellite remains are big There is no after-flame in gas-bearing formation and ground of falling is not rare.In September, 2011, U.S.'s Upper Atmosphere Research Satellite disintegration South Pacific of falling are flat Ocean, maximum fragment weight 150kg.These satellite fragmentations are not utterly useless, in fact, our times various countries are to the broken of the satellite that falls Piece is quite paid attention to and has carried out a large amount of searches, it is desirable to hereby it is possible to analyze satellite capacity and in-orbit situation.If fallen The in-orbit significant data information in-flight of satellite can be preserved in the satellite fragmentation on ground, then subsequent satellitosis is analyzed and had There are important value and meaning.

Currently, data are mainly by Integrated Electronic System management and control on satellite.Integrated Electronic System includes Star Service management Module (i.e. CIMA, CIMB), primary power source module (PCM), secondary power supply module (PAM), is matched at large capacity management module (SMM) Electric management module (PDM), navigation management module (GNSS), communication module (TCM) and expanding function module (FEM) etc..Wherein, Star Service management module (i.e. CIMA, CIMB) be satellite platform higher management module, complete Integrated Electronic System in each module it Between monitoring and management, be responsible for whole star track operation, gesture stability, thermal control, load management, telemetry and telecommand data processing； Large capacity management module (SMM) realize to the massive store of payload data and under passed management；Primary power source module (PCM) it is responsible for converting the solar into the available primary power source of satellite and realizes the management of charging and discharging to accumulator group, primary electricity Source voltage is 12V；The primary power source that primary power source module generates is converted to Integrated Electronic System by secondary power supply module (PAM) Secondary power supply needed for interior each module and payload, the secondary power supply voltage provided have -12V, 5V, 28V；Distribution management module (PDM) the power supply and distribution management to satellite inner platform and load power supply is realized；Navigation management module (GNSS) realizes the navigation of satellite Positioning provides accurate time, position and speed letter for attitude control system, communication system and related application load on star Breath；Communication module (TCM) realizes the communication of satellite uplink and downlink data；Expanding function module (FEM) regards feelings and expands correlation function.

But the large capacity management module (SMM) at present on satellite is integrated board, only has data storage capacities, no Have data protection ability, data safety can not be preserved when satellite crashes.Star Service management module (i.e. CIMA, CIMB) is also collection At board, it is responsible for track operation, gesture stability, thermal control, load management, the telemetry and telecommand data processing of whole star, can has Simple data monitoring capabilities do not have fault detection and diagnosis ability, and it is even more impossible to realize what inference machine was detached with inference rule Reasoning interpretation mode can not be adapted to the data interpretation demand of the spacecrafts such as multiple types, Multiple Type satellite.Therefore, it is necessary to set A kind of spacecraft flight data analysis recording equipment is counted, spacecraft data acquisition storage, security protection, status monitoring, reality are met When diagnosis and data selectivity down pass etc. functional requirements, can be described as " spacecraft black box ".

It is well known that in aviation field, black box is the machine upper-part of focussing search after aviation accident occurs, profession Entitled " flight data recorders ", the equipment are able to record the flying quality of a large amount of keys and indicate aircraft and engine performance Variation tendency.After aviation accident occurs, although aircraft itself may be damaged centainly, flight data recorders are anti-with it The special type protections energy such as thump, penetration, high temperature resistance baked wheaten cake, the immersion of anti-deep sea pressure, sea water resistance, the immersion of corrosion resistance liquid Power can preserve the information of its storage inside in various aircraft accidents.In the normal flight operations of aircraft, flight data recording Instrument is only responsible for record and stores various data informations, is passed under these data are not real-time, is mainly used for ex-post analysis.

The design philosophy for using for reference aircraft black box is absorbed, if installing a spacecraft flight data point on spacecraft New record equipment, record and the storage in-orbit flying quality of spacecraft：On the one hand, can by on-board processing device to these data into Row analysis in real time, assessment heath state of spacecraft will be sentenced and be passed under information and significant data, be carried when noting abnormalities or failure certainly The analyzing processing speed of high Spacecraft malfunction, catches spacecraft rescue opportunity in time；On the other hand, it can fall ground in spacecraft After ball, data information important on star is utmostly preserved, is carried for ex-post analysis spacecraft state, Correction and Control or Curve guide impeller For foundation.

The flight data recorders of aviation field can not be used directly on spacecraft, and main cause is as follows：

The working environment of aircraft and spacecraft, drop event, data-interface, data scale and communication mode etc. is deposited over the ground In larger difference, the flight data recorders of aviation field is caused not used on spacecraft directly.

By taking the satellite in spacecraft as an example：(1) aircraft flight is in 30km dense atmospheres below, and satellite flight in The outer space of 120km or more, temperature, air pressure, the atmospheric density difference of the two working environment are big, punching caused by crash ground Hit intensity is different, and aircraft black box anti-crash index is generally not less than 5100g, but satellite black box anti-crash index is higher than 5100g.In addition, the heat generated with air friction during airplane falling is smaller, ablation occurs mainly in aircraft explosive combustion When, generally require flight data recorders resistance in more than 1000 degrees Celsius of flame can to burn 30 minutes.And satellite fell High temperature ablation is generated with atmospheric friction in journey, temperature reaches as high as 3000 degrees Celsius or more, and the duration is relatively short.Fly The above difference of machine flying height relative satellite causes aircraft and satellite structure design and protective materials to flight data recorders Requirement it is different.

(2) data bus interface that aircraft uses is mainly ARINC629, ARINC429 (HB 6096), ARINC825 (CAN), MIL-STD-1773, MIL-STD-1553B (GJB 289A), AS 5643 (IEEE 1394) etc..And what satellite used Data bus interface is mainly ISA/PCA buses, CAMAC buses, vxi bus, IEEE488 buses, RS-232 buses, RS- 485 buses, RS-422 buses, LAN buses, usb bus, CAN bus etc..The difference of data-interface is to flight data recorders Data acquisition interface design proposes different requirements.

(3) aircraft, which generally requires, preserves no less than 25 hours flying qualities, no less than 2 hours video datas, not small In 2 hours audio datas.And satellite need not preserve audio data, need to store be load video or image data, Performance data and flying quality information of the component of satellite platform etc., storage data quantity are needed according to the revisiting period of satellite and right Underground pass the time determine, short then several hours, it is long then several days, based on data safety consideration, data storage should by it is long when progress Row design, thus, aircraft and satellite are designed with the data storage of flight data recorders different requirements.

(4) communication mode mainly uses ACARS systems (Aircraft Communications to aircraft over the ground Addressing and Reporting System, aircraft communication addressing and reporting system), realize aircraft and earth station it Between short message (message) transmitted by radio or satellite, volume of transmitted data is small.Flight data recorders on aircraft are general only Records store data, without using ACARS system real-time transmission datas, the automatically activated signal emitter only after born. And communication mode uses telemetering channel to satellite over the ground, and data biography is only carried out when satellite enters telemetry ground station coverage area It is defeated, meanwhile, the flight data recorders on satellite need to have telemetry selection and transmittability.The difference of communication mode over the ground The different signal emission module design to flight data recorders proposes different requirements.

Utility model content

In order to solve the above-mentioned technical problem, the main purpose of the utility model is to provide a kind of spacecraft flight data point New record equipment, for the unique working environment of spacecraft, drop event, data-interface, data scale and communication mode over the ground Etc. having carried out innovative design, which can be monitored the in-orbit state of spacecraft carries out diagnosis and by data to failure Under pass ground, spacecraft state can be analyzed in the spacecraft terrestrial time that falls, for example, the crash of rocket and satellite all may be used With with the Technical Analysis failure judgement situation.

In order to achieve the above object, the utility model provides a kind of spacecraft flight data analysis recording equipment, described Equipment accesses spacecraft bus equipment by bus interface, is installed on inside spacecraft, the equipment includes：Data acquisition module Block, data storage quickly analyze reading module and telemetering and localizing emission module with protection module, data；

The data acquisition module, for obtaining multichannel spacecraft data by bus interface, by spacecraft described in multichannel Data are continuous data stream all the way by built-in multichannel data multiplexor unit multiple connection, will wait for that deposit data is sent in data flow To data storage with protection module, performance monitoring data is sent to data and is quickly analyzed in reading module；

The data storage and protection module, for waiting for that deposit data compression is stored in depositing for stacked inside Memory slice by described It stores up in protector；

The data quickly analyze reading module, for carrying out online quick interpretation to the performance monitoring data, will sentence The fault data of reading is exported into telemetering and localizing emission module；

The telemetering and localizing emission module pass through spacecraft telemetering for generating telemetered signal based on the fault data Channel passes down in real time, while for after spacecraft contacts to earth, emitting urgent positioning signal by transmitter.

Further, the data acquisition module, including be linked in sequence bus interface, data channel administrative unit, Cell fifo, multichannel data multiplexor unit, ram cell and FTL units；

It includes load data, spacecraft performance data and telemetering that the bus interface of data acquisition module is obtained from spacecraft One or more spacecraft data in data, the space flight by data channel administrative unit corresponding with bus interface to acquisition The data source of device data is selected, and by cell fifo corresponding with data channel administrative unit to every road spacecraft number By the multichannel spacecraft data multiplexing after buffering it is continuous data all the way via multichannel data multiplexor unit according into row buffering Stream, is connected by the ram cell being connect with multichannel data multiplexor unit and the FTL units being connect with RAM units to described all the way Continuous data flow is cached.

Preferably, the bus interface includes CAN interface, ISA/PCA bus interface, CAMAC bus interface, VXI Bus interface, IEEE488 bus interface, RS-232 bus interface, RS-485 bus interface, RS-422 bus interface, LAN buses It is one or more in interface and usb bus interface.

Further, the guard shield of the storage protector of the stacked inside Memory slice is using aluminium, aeroge and stainless One or more layers material in steel carries out security protection；

Built-in stacking Memory slice in the shell waits for deposit data for compressing storage, it is preferred that stacks the storage of Memory slice The storehouse number of plies is no less than 32 layers (128Gb), and memory rate is not less than 256Mbit/s, and output speed is not less than 12Mbit/s.

Preferably, the stacking Memory slice uses 3D Plus NAND FLASH memories.

Further, the data quickly analyze reading module and are based on independent inference machine and are plugged on plug type storage Plug type storage card in card slot carries out online quick interpretation to performance monitoring data, and the data quickly analyze reading module The reasoning interpretation chip that built-in independent inference machine is detached with inference rule, read-write reasoning built in the plug type storage card The storage chip of rule.

Further, the reasoning interpretation chip in the inference machine is the centre developed based on embedded computer technology Manage device；The storage chip includes storing based on one or more in BIT information, threshold range information and logic criterion information The storage chip of information；

Wherein, BIT information is the information that detection and isolated fault are directly provided inside spacecraft；Threshold range is to pass through Include the upper limit or/and the range of normal value of lower limit to measured parameter setting；Logic criterion is patrolled using comprising "AND", "or", " non-" Collect the logical formula of symbol.

Further, the telemetering includes with localizing emission module：Order and data processor, transmitter, power amplifier, radio frequency Switch, antenna and the memory being connect with spacecraft telemetry command system；

The order and data processor is connect with memory, and needs are chosen after the fault data processing for that will receive Telemetry or important fault data pass ground down in real time by the telemetering channel of spacecraft telemetry command system；

The order and data processor is sequentially connected with transmitter, power amplifier, RF switch and antenna, in spacecraft It falls after contacting to earth, urgent positioning emission function is automatically turned on by transmitter, to all the winds launches specific frequency, regular Radio signal, report the orientation residing for itself.

Compared with prior art, the utility model provides a kind of spacecraft flight data analysis recording equipment, has following Advantageous effect：

(1) the in-orbit condition monitoring and fault diagnosis of spacecraft：

Record and the storage in-orbit flying quality of spacecraft, have the quick analysis interpretation ability to spacecraft data, can Monitoring spacecraft state, assessment Space Vehicle Health situation can judge the failure being likely to occur when there is exception or failure, And information and significant data will be sentenced certainly by the telemetering channel ground Xia Chuan, improve analyzing processing speed of the ground in face of Spacecraft malfunction Degree, catches spacecraft rescue opportunity in time.

(2) subsequent spacecraft state analysis：

Reach service life in spacecraft or terminated task fall terrestrial time due to other failures, by its resisting strong impact, The special type protections designs such as penetration, high temperature resistance baked wheaten cake, the immersion of anti-deep sea pressure, sea water resistance, the immersion of corrosion resistance liquid, maximum journey Degree preserves the important data information of spacecraft, and foundation is provided for ex-post analysis spacecraft state, Correction and Control or Curve guide impeller.

Description of the drawings

Fig. 1 is to be shown according to a kind of structure of the embodiment one of spacecraft flight data analysis recording equipment of the utility model It is intended to；

Fig. 2 is to be illustrated according to a kind of signal transmission relationship of spacecraft flight data analysis recording equipment of the utility model Figure；

Fig. 3 is the data acquisition module principle according to a kind of spacecraft flight data analysis recording equipment of the utility model Block diagram；

Fig. 4 is the telemetering and localizing emission mould according to a kind of spacecraft flight data analysis recording equipment of the utility model Block functional block diagram.

Specific implementation mode

In order to make those skilled in the art more fully understand the utility model, below in conjunction with the utility model reality The attached drawing in example is applied, the technical scheme in the utility model embodiment is clearly and completely described, it is clear that described Embodiment is only the embodiment of the utility model part, instead of all the embodiments.Based on the reality in the utility model Example is applied, every other embodiment obtained by those of ordinary skill in the art without making creative efforts is all answered When the range for belonging to the utility model protection.

Embodiment one

Referring to Fig.1-2, Fig. 1-2 shows a kind of spacecraft flight data analysis recording equipment provided by the utility model Schematic diagram, the equipment access spacecraft bus equipment by bus interface, are installed on inside spacecraft, the equipment includes： Data acquisition module 11, data storage quickly analyze reading module 13 and telemetering and localizing emission mould with protection module 12, data Block 14；

The data acquisition module 11 mainly acquires space flight for obtaining multichannel spacecraft data by bus interface 111 The spacecraft data of device platform and payload are realized to analog quantity, digital quantity, switching value, bus, video, figure as needed Spacecraft data described in multichannel are passed through built-in multichannel data multiplexer list by the signal of the diversiform datas such as picture or format conversion First multiple connection is continuous data stream all the way, will wait for that deposit data is sent in data storage and protection module in data flow, by performance Monitoring data are sent to data and quickly analyze in reading module；

The data storage and protection module 12, for waiting for that deposit data compression is stored in stacked inside Memory slice by described In 121 storage protector；

The data quickly analyze reading module 13, will for carrying out online quick interpretation to the performance monitoring data The fault data that interpretation goes out is exported into telemetering and localizing emission module；

The telemetering and localizing emission module 14, it is distant by spacecraft for generating telemetered signal based on the fault data It surveys under channel and passes, while for after spacecraft contacts to earth, emitting urgent positioning signal by transmitter.

Wherein, a kind of shell shape of spacecraft flight data analysis recording equipment is preferably cylindrical or cuboid, To enhance its data protection ability, the equipment is preferably installed on to the centre of spacecraft, is fallen ablation in spacecraft In the process, using the ablation of equipment outer layer as the protection to the equipment, its high temperature resistance ablation ability is improved.

As shown in figure 3, the data acquisition module, including satellite data or rocket data are obtained by bus interface；Packet Include the bus interface being linked in sequence, data channel administrative unit, FIFO units (First Input First Output, it is advanced First dequeue memory), multichannel data multiplexor unit, ram cell (Random Access Memory, random access memory Device) and FTL units (Flash Translation Layer, flash translation layer (FTL))；

LVDS receiving channels, CAN interface and RS-422 bus interface in the bus interface of data acquisition module from One or more spacecraft numbers in corresponding load data, spacecraft performance data and/or telemetry are obtained on spacecraft According to, realize signal to diversiform datas such as analog quantity, digital quantity, switching value, bus, images or format conversion, by with it is total The corresponding data channel administrative unit of line interface selects the data source of the spacecraft data of acquisition, and by with data The corresponding cell fifo of channel management unit into row buffering, will delay every road spacecraft data via multichannel data multiplexor unit Multichannel spacecraft data multiplexing after punching is continuous data stream all the way, mono- by the RAM being connect with multichannel data multiplexor unit Member and the FTL units being connect with RAM units cache the continuous data stream all the way, before realizing data massive store Safe Cache, will finally wait for deposit data export storage to data with protection module realize store.

Preferably, the bus interface includes CAN interface, ISA/PCA bus interface, CAMAC bus interface, VXI Bus interface, IEEE488 bus interface, RS-232 bus interface, RS-485 bus interface, RS-422 bus interface, LAN buses It is one or more in interface and usb bus interface.

The guard shield of the storage protector of the stacked inside Memory slice is using one layer in aluminium, aeroge and stainless steel Or multilayer material carry out security protection, can high temperature resistance ablation, resisting strong impact, penetration, anti-deep sea pressure, sea water resistance impregnate, it is resistance to Corrosive liquids immersion etc..Data are stored crashes existence mnemon with protection module overall structure, falls ground in spacecraft Data safety is protected in the process.

Built-in stacking Memory slice in the shell waits for deposit data for compressing storage, stacks the store storehouse number of plies of Memory slice No less than 32 layers (128Gb), memory rate are not less than 256Mbit/s, and output speed is not less than 12Mbit/s.

Preferably, the stacking Memory slice uses 3D Plus NAND FLASH memories, 3D Plus NAND FLASH The store storehouse number of plies is increased to 32 layers (128Gb) or more, memory rate is not small by memory by the method for the three-dimensional silicon layer of increase In 256Mbit/s, output speed is not less than 12Mbit/s, supports initialization bad block scan and programming, and erasing failure bad block Data are carried out compression storage, have many advantages, such as that storage density is high, low in energy consumption, non-volatile by detection.Data are substantially single with cluster Position, is loaded into respective storage region in the way of level Four flowing water.All data are deposited after carrying out real-time RS (256,252) coding Storage carries out decoding error correction in real time when data readback, to eliminate space environment number caused by the Single event upset effecf of spacecraft According to mistake.

The data quickly analyze the reasoning interpretation core that independent inference machine built in reading module 13 is detached with inference rule Piece.The data are quickly analyzed reading module 13 based on independent inference machine and are plugged in plug type memory card slot 131 Plug type storage card 132 carries out online quick interpretation, read-write reasoning built in plug type storage card to performance monitoring data The storage chip of rule.Plug type storage card can in the plug type memory card slot that data quickly analyze reading module into Row plug facilitates user setting and modification inference rule.The reasoning interpretation mode that this inference machine is detached with inference rule designs So that data quickly analyze reading module and have adaptation ability to multiple types, Multiple Type spacecraft, can also be applicable The field that other need to carry out data interpretation with space flight, aviation, car and boat, industry, machinery, medical treatment etc..

Reasoning interpretation chip in the inference machine includes the central processing unit developed based on embedded computer technology；Institute The storage chip for stating inference rule includes storage based on BIT (Build-In Test, built-in test) information, threshold range information With the storage chip of one or more information in logic criterion information；Reasoning interpretation process realizes boat using logic judgement mode The judgement of its device state integrity；

Wherein, BIT information is the letter that system or module inside spacecraft can directly provide detection and isolated fault Breath, including coding mode or switching value form are used, it can be directly realized by sentencing for spacecraft state integrity according to these information It is disconnected；Threshold range is by including the upper limit or/and the range of normal value of lower limit to measured parameter setting, when parameter is beyond normal When being worth range, judgement measured parameter is abnormal；Logic criterion, using the logical formula for including the logical symbols such as "AND", "or", " non-", Such as, measured parameter is brought into logical formula, shows certain failure occur if logical formula is "true".

As shown in figure 4, the telemetering includes with localizing emission module：Order and data processor, power amplifier, is penetrated transmitter Frequency switch, antenna and the memory being connect with spacecraft telemetry command system；

The order and data processor is connect with memory, and needs are chosen after the fault data processing for that will receive The telemetering channel ground Xia Chuan that telemetry or important fault data pass through spacecraft telemetry command system；

The order and data processor is sequentially connected with transmitter, power amplifier, RF switch and antenna, in spacecraft It falls after contacting to earth, urgent positioning emission function is automatically turned on by transmitter, to all the winds launches specific frequency, regular Radio signal, report the orientation residing for itself.

Telemetering can either be completed to pass task under spacecraft telemetry with localizing emission module, and can realize that spacecraft touches Urgent positioning signal transmitting behind ground.When spacecraft operation on orbit, telemetering is needed with localizing emission module according to ground telemetering data Summed data quickly analyzes the sentence read result of reading module, from data storage with protection module in choose needs telemetry or Important fault data passes through the telemetering channel ground Xia Chuan.Spacecraft falls contact to earth after, telemetering is opened automatically with localizing emission module Urgent positioning emission function is opened, to all the winds launches specific frequency, regular radio signal, reports residing for itself Orientation, so that searcher finds.

The technical solution that the utility model embodiment one provides, has the advantages that：

(1) the in-orbit condition monitoring and fault diagnosis of spacecraft：

Record and the storage in-orbit flying quality of spacecraft, have the quick analysis interpretation ability to spacecraft data, can Monitoring spacecraft state, assessment Space Vehicle Health situation can judge the failure being likely to occur when there is exception or failure, And information and significant data will be sentenced certainly by the telemetering channel ground Xia Chuan, improve analyzing processing speed of the ground in face of Spacecraft malfunction Degree, catches spacecraft rescue opportunity in time.

(2) subsequent spacecraft state analysis：

Reach service life in spacecraft or terminated task fall terrestrial time due to other failures, by its resisting strong impact, The special type protections designs such as penetration, high temperature resistance baked wheaten cake, the immersion of anti-deep sea pressure, sea water resistance, the immersion of corrosion resistance liquid, maximum journey Degree preserves the important data information of spacecraft, and foundation is provided for ex-post analysis spacecraft state, Correction and Control or Curve guide impeller.

Above description is only a specific implementation of the present invention, but the scope of protection of the utility model is not limited to In this, any one skilled in the art within the technical scope disclosed by the utility model, can readily occur in variation Or replace, it should be covered within the scope of the utility model.Therefore, the scope of protection of the utility model should be with the power Subject to the protection domain that profit requires.

Claims (8)

1. a kind of spacecraft flight data analysis recording equipment, the equipment accesses spacecraft bus equipment by bus interface, It is installed on inside spacecraft, which is characterized in that the equipment includes：Data acquisition module, data storage and protection module, data Quickly analysis reading module and telemetering and localizing emission module；

The data acquisition module, for obtaining multichannel spacecraft data by bus interface, by spacecraft data described in multichannel It is continuous data stream all the way by built-in multichannel data multiplexor unit multiple connection, will waits for that deposit data is sent to number in data flow According to storage with protection module, performance monitoring data is sent to data and is quickly analyzed in reading module；

Data storage and protection module, for waiting for that deposit data compression is stored in the storage of stacked inside Memory slice and prevents by described It protects in device；

The data quickly analyze reading module, and for carrying out online quick interpretation to the performance monitoring data, interpretation is gone out Fault data export into telemetering and localizing emission module；

The telemetering and localizing emission module pass through spacecraft telemetering channel for generating telemetered signal based on the fault data It is passed under in real time, while for after spacecraft contacts to earth, emitting urgent positioning signal by transmitter.

2. equipment as described in claim 1, which is characterized in that the data acquisition module, including the bus being linked in sequence connect Mouth, data channel administrative unit, cell fifo, multichannel data multiplexor unit, ram cell and FTL units；

The bus interface of data acquisition module is obtained from spacecraft in load data, spacecraft performance data and telemetry One or more spacecraft data, by data channel administrative unit corresponding with bus interface to the spacecraft data of acquisition Data source is selected, and is delayed to every road spacecraft data by cell fifo corresponding with data channel administrative unit Multichannel spacecraft data multiplexing after buffering is continuous data stream all the way via multichannel data multiplexor unit by punching, by with The ram cell of multichannel data multiplexor unit connection and the FTL units being connect with ram cell flow into the continuous data all the way Row caching.

3. equipment as claimed in claim 1 or 2, which is characterized in that the bus interface includes CAN interface, ISA/PCA Bus interface, CAMAC bus interface, vxi bus interface, IEEE488 bus interface, RS-232 bus interface, RS-485 buses It is one or more in interface, RS-422 bus interface, LAN bus interface and usb bus interface.

4. equipment as described in claim 1, which is characterized in that outside the protection of the storage protector of the stacked inside Memory slice Shell uses one or more materials in aluminium, aeroge and stainless steel to carry out security protection；

Built-in stacking Memory slice in the shell waits for deposit data for compressing storage, and the store storehouse number of plies for stacking Memory slice is many In 32 layers, memory rate is not less than 256Mbit/s, and output speed is not less than 12Mbit/s.

5. equipment as described in claim 1 or 4, which is characterized in that the stacking Memory slice uses 3D Plus NAND FLASH memory.

6. equipment as described in claim 1, which is characterized in that the data quickly analyze reading module and are based on independent reasoning Machine and the plug type storage card being plugged in plug type memory card slot carry out online quick interpretation, institute to performance monitoring data State the storage chip of read-write inference rule built in plug type storage card.

7. equipment as claimed in claim 6, which is characterized in that the reasoning interpretation chip in the inference machine is based on embedded The central processing unit of computer technology exploitation；The storage chip includes that storage is based on BIT information, threshold range information and logic The storage chip of one or more information in criterion information；

Wherein, BIT information is the information that detection and isolated fault are directly provided inside spacecraft；Threshold range is by quilt It includes the upper limit or/and the range of normal value of lower limit to survey parameter setting；Logic criterion is accorded with using comprising "AND", "or", " non-" logic Number logical formula.

8. equipment as described in claim 1, which is characterized in that the telemetering includes with localizing emission module：Order and data Processor, transmitter, power amplifier, RF switch, antenna and the memory being connect with spacecraft telemetry command system；

The order and data processor is connect with memory, the telemetering for choosing needs after handling the fault data of reception Data or important fault data pass ground down in real time by the telemetering channel of spacecraft telemetry command system；

The order and data processor is sequentially connected with transmitter, power amplifier, RF switch and antenna, for falling in spacecraft After contacting to earth, urgent positioning emission function is automatically turned on by transmitter, to all the winds launches specific frequency, regular nothing Line electric signal reports the orientation residing for itself.