RU2498399C1 - System for controlling, collecting and processing data with onboard spacecraft recording equipment - Google Patents

Abstract

FIELD: radio engineering, communication.

SUBSTANCE: disclosed system for controlling, collecting and processing data with onboard spacecraft recording equipment includes at least one onboard recording equipment unit connected by at least two communication channels to a data control and processing unit, which is connected onboard spacecraft equipment through at least one communication channel for subsequent collection of information on Earth. The data control and processing unit includes: an interfacing device, a self-contained timer, a single-board computer, a forced cooling system, a heat sensor system, a storage unit, a synchronous data transmission unit, a secondary power unit and a command transmission and power distribution system.

EFFECT: easier and reliable simultaneous connection to different onboard recording equipment.

7 cl, 2 dwg

Description

The invention relates to the field of remote control of onboard recording equipment (ARB) of spacecraft (SC). The proposed system allows you to process and transmit recorded data to Earth from a space station.

A known method of controlling onboard equipment of a spacecraft is see RF patent invention No. 2440677 dated 01/20/2012, which consists in reading the telemetry information (TMI) necessary for controlling specific onboard equipment, transmitting it to the flight control center (MCC) for analysis, forming radio commands ( RK) by the operator of the MCC, transferring the RK through the onboard transceiver to the onboard control complex (BKU), converting the RK and translating them from the BKU KA into the control unit (BU) onboard equipment of the KA. In this case, the TMI values are removed by means of the control panel in the interests of the entire set of on-board equipment with a given update period, normalized and stored in the memory of the control panel with the subsequent transfer of the TMI to the MCC, command packages for turning on / off the on-board equipment with the specified time intervals for issuing commands are generated and transmitted to the control panel in advance, and subsequently launch one RK.

The disadvantage of this invention is the inability to simultaneously control various on-board equipment. Another disadvantage of this method is the complexity, and in real conditions, the impossibility of simultaneously obtaining a large array of data on r of various on-board recording equipment.

The closest technical solution is French patent FR 2697375A1 from 1994-04-29, in which each module of the onboard recording equipment of the spacecraft is connected by cable to the spacecraft, from where the signal arrives on Earth.

The disadvantage of this system is the impossibility of using it to transmit various scientific information in combination with the simultaneous control of equipment receiving this scientific information.

The proposed system is aimed at eliminating the above disadvantages.

Tasks solved using the proposed system:

- cheaper design of scientific equipment (HA) due to the cheaper elemental base (corresponding to less critical operating conditions in the conditions of thermal volume) used in the control unit and data processing (BUOD);

- standardization and unification of the element base of the BUOD;

- reduction of heat dissipation of ARBs due to the distribution of the control system, data collection and processing;

- creating a flexible system of operational management, collection and processing of information through the simultaneous combination of management functions, organization of reception, accumulation and preliminary processing of information from various unrelated ARBs;

- saving financial resources and increasing the reliability of the NA system (BRA + BUOD) due to the maintainability of the BUOD during normal operation (the possibility of maintenance of the BUOD by the astronaut crew);

- technical result - the possibility of easy, convenient, reliable simultaneous connection to the device of various on-board recording equipment installed outside the spacecraft’s thermal volume, and, in the future, controlling it.

The technical result is achieved by the fact that the control system for collecting and processing data from on-board recording equipment (BRA) of the spacecraft (CL) includes at least one BRA unit connected by at least two communication channels to the control and data processing unit (BOD) ), which is connected with the onboard equipment (BA) of the spacecraft through at least one communication channel for subsequent dumping of information to the Earth, while the BUOD includes:

- a pairing device (CSS), connected by at least two communication channels with the ARB;

- an autonomous timer device (ATU) connected by a local highway with a USB;

- a single-board computer (OPK) connected by a local highway to the DC;

- related to the defense industry, forced cooling system (STR), a system of temperature sensors (STD), a storage unit (BZU) and a synchronous data transfer unit (BSPD);

- a secondary power supply unit (BP), which provides constant power to the defense industry complex, STR, STD, BZU, BSPD;

- a command translation and power distribution system (STKRP) supplying and controlling a power supply;

BA BA includes:

- Onboard equipment control system (SMSA);

- containing an information management system (IMS);

- On-board measurement system (SBI).

In addition, STKRP receives telemetric information from each ARB and transmits it to the SCA of the spacecraft, as well as receives control commands from the SCA of the spacecraft and transmits them to the DC for subsequent transmission to the ballast via communication channels.

The BSPD receives information from the defense industry complex, buffers it in its own memory (memory) for subsequent transmission to the SCA of the spacecraft for operational dumping to Earth and analysis.

In addition, the command translation and power distribution system (STKRP) includes telemetric sensors: relay contact (KP), thermal sensor (TD), electronic key (EC), analog sensor (HELL) and docking control (KS) the information from which STKRP gives to the system onboard measurements of the spacecraft (SBI KA).

The communication channels through which the DC is connected with the ICS are SpaceWire and / or MIL1553 and / or LVDS and / or CAN.

The OPK high-speed data transmission interfaces for communication with the IMS are RS422 / 485 and / or USB and / or Ethernet.

Communication channels linking the ARB to the control and data processing unit (BOD) include a service control drop and an information transmission channel.

In the control system, data collection and processing of data from the onboard recording equipment (ARB) of the spacecraft, removable storage media are used as a BDU, and the USB has its own memory for buffering NI received in the USB from the BRA.

The general scheme of the proposed system is shown in FIG. 1, which shows:

- BA KA-on-board equipment of the spacecraft (for a space station there is an additional opportunity to use, if necessary - in the case when the BA is invalid and cannot receive NI and provide control actions to the BUOD, to control the operation of the BUOD and to receive the NI from the BUU BUOD - on-board laptop);

- SUBA - on-board equipment control system from which the BUOD receives power and receives relay control commands (RCUs);

- IMS - information management system;

- SBI - on-board measurement system;

- BRA 1 ... BRA N-board recording equipment, in the number of N-pieces (N-integer), installed on the outer side of the space station or spacecraft (outside the GO) and each having at least two communication channels: service control channel SKU and KPI information transmission channel (depending on the conditions of the experiment and the size of the transmitted NI flux, it is possible to use one bi-directional interface, such as, for example, RS422 with a transmission speed of up to 1 Mbps, for the simultaneous implementation of the above communication channels - SKU and KPI);

- SKU - service control channel;

- KPI - information transfer channel;

- BUOD - control and data processing unit, this unit is installed inside a space station or spacecraft, i.e. in the pressurized volume (GO) of the station or spacecraft.

BUOD contains the following systems:

- ATU - stand-alone timer device;

- LM - a local highway through which ATU and CSS, CSS and defense industry are connected;

- US - interface device that connects the ARB 1 ... ARB N to the OPK and has communication channels: SpaceWire, MIL1553, LVDS, CAN;

- TsM - digital arrays;

- OPK - a single-board computer with high-speed data transfer interfaces (RS422 / 485, USB and Ethernet) designed for communication with the IMS BA KA;

- STR - forced cooling system associated with the defense industry;

- STD - a system of temperature sensors associated with the defense industry;

- BZU - block storage device associated with the defense industry;

- BSPD - a block of synchronous data transmission in SBI (on-board measurements system of a spacecraft) of scientific information, also associated with the defense industry complex;

- BP - a secondary power supply unit that provides constant power to the defense industry complex, STR, STD, BZU, BSPD;

- STKRP - a command translation and power distribution system that controls the power supply, as well as the transmission of official telemetry information from the ARB to the SBI. The structure of the STKRP includes telemetry sensors KR - relay contact, TD - thermal sensor, EC - electronic key, AD - analog sensor, KS - docking control;

- US, ATU and BP are connected to the internal bus of the defense industry complex (local highways (LM) such as PCI, ISA, etc.) through standard mezzanine connectors.

In the inventive system BUOD is intended for:

- organization of control of various BRA but for service control channels (SKU) through the MIL1553, SpaceWirc, USD, RS422 / 485 or CAN interfaces or other necessary interfaces;

- receiving arrays of digital information from various BRA through information transmission channels (KPI), through high-speed interfaces MIL1553, RS422 / 485 or CAN (with speeds of the order of 1 Mbit / s) or high-speed (more than 10 Mbit / s) - LVDS, LAN, SpaceWire (for one ARB, there may be several KPI performed on different high-speed interfaces);

- receiving arrays of digital information from various ARBs using SpaceWirc high-speed interfaces (with speeds from 2 to 400 Mbit / s), LVDS, Ethernet;

- collection of auxiliary service information (interrogation of additional temperature sensors installed on the BUOD fuel elements included in the temperature sensor system (STD)) for its subsequent inclusion in the format of scientific information;

- collection of auxiliary service information received from telemetric sensors installed in the ARB for its subsequent transmission to the SBI;

- accumulation, temporary storage of information arrays received from various ARBs and their transmission to the spacecraft information management system (IMS) via the LAN (Ethernet) channel for subsequent discharge to Earth;

- receiving the on-board time code (KBV) (at least 1 time per day) and four-byte command words from the spacecraft information control system (IMS) via RS422 or CAN control channels;

- receiving ballistic and navigation data via RS422 / 485, Ethernet or CAN control channels for their subsequent inclusion in the NI format for subsequent positioning in the space of the ARB at any time during the registration of NI;

- development of an independent time stamp (with the help of ATU) with the aim of further linking it to the KBV mark;

- processing and compression of the received arrays of information or various BRAs and their transmission through the BSPD to the SBI for operational dumping to the Earth and analysis.

The defense industry complex is the central element of the BUOD and is a commercially available powerful processor module of the industry standard (it is possible to use a specialized defense industry complex, created separately for the specific development of the BUOD and having all the necessary interfaces for interfacing with the spacecraft and spacecraft, but the creation of such a defense industry is extremely expensive, in addition he must additionally pass certification to determine the possibility of its use in space technology), having an internal mud (a local highway such as PCI, ISA, etc.).

The DPC manages the BRA, programmatically collects service and scientific information from the BRA according to the measurement program encoded in the 0101 programmable read-only memory (DEP) of the DPC, writes data to the DPC RAM, as well as preprocesses the information and outputs it to either the BEC through Serial-type interfaces ATA, either in the BA KA through its own high-speed interfaces (Ethernet, USB, etc.), or first transferring the above information through the LM to the USB (if the OPK does not have the necessary high-speed interfaces for transmitting information tion in AD CA), and then in AD spacecraft through CSS speed interfaces (LVDS, SpaceWire et al.).

The military-industrial complex, as a rule, includes the following basic elements: processor, RAM, Ethernet network controllers, video controller, RS422 / 485/232 serial ports, USB ports, a soldered flash drive, standard parallel port (LPT), Serial ATA interface, watchdog timers, etc.

To fulfill the requirements of the purpose, the BUOD uses the QNX type real-time operating system (RTOS) installed in the defense industry complex, which is highly reliable when working in network applications and allows full compatibility with, for example, the RTOS IMS of the Russian segment (PC) of the International Space Station (ISS) ), which allows you to effectively interact (exchange data on request) at the server level of the ICS PC ISS and BUOD (for example, using the well-known system “server” - “client”).

CSS expands the capabilities of the BUOD by providing interfaces for exchanging with ARBs, which are absent in the defense industry complex.

The DC receives scientific information (NI) from the ARB in the form of digital arrays via the KPI channels and transmits it to the defense industry complex via LM.

The DC has its own memory for buffering NI coming into the DC from the ARB if necessary (buffering occurs when the ARB is operating in high load mode and the LM cannot cope with a large data stream).

The CA carries out data exchange between the BRA and the BODA via the BMS channels: the BCH and the CBA arrive in the BRA, and the responses (receipts) to the BRA of the BCH come to the BRA.

The UE carries out data exchange between the BUOD and the BMS (IMS) via the KPI channels implemented on high-speed interfaces, such as LVDS, SpaceWire (transmitting NI CM) and on the SKU service channels implemented on RS422 or CAN interfaces. Through CCU channels from the ICS to the CC, KU and KBV are received, and from the CC to the ICS, there are responses (receipts) to received by the CC KU, as well as service information that displays the state of the telemetry parameters of the BUOD.

The need to use an independent (from the OPK system processor) autonomous timer device (ATU), which controls the periodic procedures of software devices, is dictated firstly by the possibility of the occurrence of microprocessors "freezing" (looping) due to single failures, which, as is known, have a non-zero probability. At the same time, the ATU can supply the relative information system code with an accuracy of 0.1 μs to the information collection system. Thus, secondly, the ATU is designed to link the time of registration of events to the time stamp issued by the information management system (IMS) of the spacecraft.

STKRP receives an onboard supply voltage of 28 V from a SUBA SC on a separate feeder, has inside protection against improper connection of power poles and from a short-time pulse inrush current of 10 A, and also filters (blocks) the input power from electrical noise from both the load side, connected to the power feeder, and vice versa, from the BUOD.

STKRP receives discrete (relay) control commands (RKU) from the SCMS and transmits them to the US and to the ARB. In the command chain, ± 28.5 V power is used, supplied to the control unit and, accordingly, to the ARB according to the independent power types. The commands I receive are in the BUOD / BRA on the control windings of the relay with duplicated "dry" relay contacts. In parallel with the commands, the on-board supply voltage of the relay is supplied with a voltage of 28.5 V, which, when these relays are activated, is supplied to the load and creates a constant load current (electronic components of the BUOD / BRA). The passage of all the control switches is confirmed by receipts (response of the controllers OD / BRA to the passage of the control switches) issued by the BUOD / BRA through the discrete channels of the SBI telemetry through the contacts of the relay “dry contact”. At the same time, the load current to the external circuit is limited to a value of 10 mA (when normally closed contacts are closed). Additionally, receipts are duplicated and submitted to the US as a format for register status teams (STK). The structure of STKRP for monitoring the supply voltage of 5 V includes one EC-type sensor (electronic key). In addition, STKRP provides information from the telemetry sensors (TM sensors) BUOD (KR - relay contact, TD - thermal sensor, EC - electronic key) and ARB (KR - relay contact, TD - thermal sensor, EC - electronic key, AD - analog sensor, KS - docking control).

The main function of the BSPD is to receive data in the form of digital arrays (DTMs) of information from the OPK but to the synchronous data transmission channel (after their preliminary processing of the OPK and compression), buffering them in its own memory for subsequent transmission to the SCA of the spacecraft for operational reset to Earth and analysis.

BP is intended for:

- the generation of primary on-board power supplied to STKRP by a power feeder by supplying to STKRP the appropriate control switchgear, secondary power supply voltages for powering the US, OPK, ATU, BSPD, as well as the internal bus of the OPK (local PCI, ISA, etc.);

- stabilization of power ratings and their primary filtering from electrical noise and interference.

The LES is necessary if it is required to store information the volume of which exceeds the volume of drives (buffering) that are regularly located in the defense industry complex. The structure of the CCD can include removable storage media such as, for example, a set of removable solid-state IDE storage media up to 256 GB each, which allows you to record useful events continuously and very quickly (two orders of magnitude faster than writing to the internal flash memory) (digital arrays of scientific information) when the ARB operates in the high-load detector mode (at response frequencies from 1 MHz and above).

With increased consumption of BUOD electronic systems (for example, if the OPK consumes more than 12 W) and its operation in the spacecraft instrument compartments at an ambient temperature of 30 ° C or higher, in order to achieve the necessary temperature regime on the surface of the fuel elements in the BUOD along with heat sinks for conductive heat removal to the body, a forced cooling system (STR) is used based on fans operating in the "hot" reserve, which provides air circulation by blowing and increasing cooling efficiency.

The proposed structure of a distributed system for collecting and processing data from airborne recording equipment has a star topology, in the center of which there is a BUOD, and at the ends of the beams there are various tins of the airborne recording apparatus, each of which is connected to the BUOD with its own separate information transmission channels (based on interfaces RS422 / 485, CAN, LVDS, etc.), through which scientific information is transmitted relating only to this BRA, which allows for the flow of information and bending necessary for each BRA th system of operational management of the ARB.

A typical algorithm for the operation of ARBs with a BUOD is as follows.

ARB detectors are a source of experimental data (a set of signals) coming through the interface (a set of registers) but to the logical and amplitude measurement channels (the number of these channels for each ARB can be different) into electronic modules of the ARB, where they are converted into digital data arrays, which are received to the ARB output interfaces, which include controllers that control the collection and transmission of generated arrays of scientific and service data but KPI and SRS. In this case, the BRA includes: the information recorder itself (a detecting device) and a system for collecting and pre-processing information (SSOD), intended for receiving digital data from the BRA information recorder, filtering useful information, packing it into digital arrays of digital information, intermediate buffering CM and their transmission via communication channels in the BUOD.

The controllers of the N channels also have sufficient buffer (stack) drives in order not to stop the collection of arrays formed for transmission to the UC BUOD during the operation inhibit signal, for example, on the Ni channel, caused, for example, by the fact that the current array arrays of the Ni channel in the BZU, the BUOD is overfilled and re-mounted to a new (free) drive, or a system failure caused by the fact. The ban signal is issued on the SKI from the OPK BUOD, which accumulates information in the BZU with periodic remounting (switching) of drives (“disks”). In the absence of a signal to prohibit transmission, the free data channel KPI_N discharges information from the BRA_N to the BUOD, where it is temporarily stored on the available “diskette” of the BZU until the time when the DIC resource allocated for the preliminary processing of “disk_N” is available, as a result of which an array of compressed scientific information is formed, which is to be output in real time through the BSPD in the SBI (telemetry drip). Simultaneously with the layout of arrays intended for output to the SBU, as well as uncompressed arrays in the ICS, the defense industry complex collects information from service systems and generates arrays of service information, which can be transmitted separately from scientific information arrays by commands from the SMSA (for example, to evaluate performance parameters and BUOD and BRA). All data formats in the information arrays are tied to the on-board time tags generated by the ATU. In addition, the ATU, in the event of a failure (“freezing”) in the DIC program, restarts it (“soft restart”), while maintaining the restart status in the service register, which allows identifying possible errors in the information that occurred when the system was restarted, despite the fact that all N-channels for transmitting arrays are automatically set to prohibit signals.

Thus, with a standard (trouble-free) slave of a remote system, there is always a certain correlation between the BUOD performance (input, processing, storage, data output) and the density of the input information stream, which is currently in the ARB buffers to be transferred to the BUOD. This ratio is selected deliberately, based on specific tasks, and determines the specific structure and execution of the nodes BUOD and ARB. However, the overall structure of the system (Figure 1) does not change, it is obviously somewhat redundant (as, for example, for the case when the increased performance of the defense complex is required, which can have an energy consumption of more than 10 W, which requires the use of STR).

An example implementation of the inventive system on the ISS is shown in Figure 2.

On consists of two ARBs (multi-angle camera and a block of photodetectors) located outside the civil defense and incorporating separate SSOD. The AT is connected with the control and data acquisition unit (LUOD) located in the GO, and the data exchange between the SSOD of each BRA and LUOD takes place through the SKU and KPI channels, implemented on the basis of the RS422 and LVDS interfaces, according to the algorithm described above for the operation of the BRA with LUOD.

Such a circuit implementation makes it possible to significantly simplify the interaction of ISS service systems with each individual BRA, assigning the functions of accumulation and preliminary processing of information - compression and rejection of images received from the BRA to the ACU.

Above, the main features of the control system for collecting and processing data from the on-board recording equipment of the spacecraft were disclosed, but it is obvious to any person skilled in the art that based on the disclosed data, many variants of a similar system can be created, the circuit of which is disclosed in this application, and which other electronic components, but performing similar functions disclosed.

Claims (7)

1. A control system for collecting and processing data from on-board recording equipment (BRA) of a spacecraft (SC), comprising at least one BRA unit connected by at least two communication channels to a control and data processing unit (BOD) , which is associated with the onboard equipment (BA) of the spacecraft through at least one communication channel for subsequent dumping of information to the Earth, while the BUOD includes:
- a pairing device (CSS) connected by at least two communication channels with the ARB;
- Autonomous timer device (ATU), connected by a local highway with the US;
- a single-board computer (OPK) connected by a local highway to the DC;
- a forced cooling system (STO), a temperature sensor system (STD), a storage unit (BZU), and a synchronous data transfer unit (BSPD) associated with the defense industry complex;
- a secondary power supply unit (PSU), which provides constant power to the defense industry complex, STR, STD, BZU and BSPD;
- a command translation and power distribution system (STKRP), which supplies the PSU with a primary (on-board) voltage of +28 V and controls the PSU using commands; in addition, STKRP receives telemetry information from each ARB and transmits it to the SCS of the spacecraft, and also receives commands control from the SUBA KA and translates them into the CA for subsequent transmission to the ARB via communication channels, the BA KA includes:
- Onboard equipment control system (SMSA);
- information management system (IMS);
- on-board measurement system (SBI),
BSPD receives information from the defense industry complex, buffers it in its own memory for the subsequent synchronous transmission of digital arrays (digital arrays) to the spacecraft SBI in the on-line reset mode of the digital earth to Earth. 2. The control system for collecting and processing data from the onboard recording equipment (ARB) of the spacecraft according to claim 1, characterized in that the command translation and power distribution system (STKRP) includes telemetry sensors: relay contact (KR), thermal sensor (TD) , an electronic key (EC), an analog sensor (HELL) and docking control (CS), the information from which STKRP issues to the spacecraft on-board measurement system (SCI KA). 3. The control system for collecting and processing data from on-board recording equipment (BRA) of the spacecraft according to claim 1, characterized in that the communication channels through which the communication unit is connected with the ICS are SpaceWire, and / or MIL 1553, and / or LVDS, and / or CAN. 4. The control system, data collection and processing from on-board recording equipment (BRA) of the spacecraft according to claim 1, characterized in that the high-speed data transmission interfaces of the defense industry complex for communication with the ICS are RS 422/485, and / or USB, and / or Ethernet. 5. The control system for collecting and processing data from the on-board recording equipment (BRA) of the spacecraft according to claim 1, characterized in that the communication channels connecting the BRA unit to the control and data processing unit (BOD) include a service control channel and a transmission channel information. 6. The control system for collecting and processing data from on-board recording equipment (BRA) of the spacecraft according to claim 1, characterized in that removable storage media are used as the BZU. 7. The control system for collecting and processing data from the onboard recording equipment (ARB) of the spacecraft according to claim 1, characterized in that the DC has its own memory for buffering NI received in the USB from the ARB.

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