RU168932U1 - Decoder for command and telemetry information on-board equipment command-measuring system - Google Patents

Abstract

The utility model relates to computer technology and may find application in the on-board equipment of a command-measuring system for controlling spacecraft. The proposed decoder command and telemetric information on-board equipment command-measuring system, containing a decoder of one-time commands and command-program information, a telemetry processing unit, a program-time device and a switching matrix connected to the on-board sources of receipts and telemetry information, with a digital receiver and a digital shaper response signal, made in the form of a single device. At the same time, the decoder of one-time commands, command and program information and the telemetry processing unit are implemented on one programmable logic integrated circuit. The technical result consists in reducing the dimensions, mass, energy consumption and increasing reliability during the period of active existence.

Description

The utility model relates to the field of computer technology and is intended for use in the on-board equipment of a command-measuring system (BA KIS) for controlling a spacecraft (SC).

During the period of active existence (CAC) of the spacecraft in orbit, which depending on the height of the orbit and destination may be different, and in some cases it takes at least 15 years, it is necessary to send one-time commands (RC) and command- program information (KPI), accept receipts (KB) about their execution and telemetry information (TMI). For this purpose, the KIS BA provides a decoder for command-program and telemetric information (DKTI), which includes a decoder for command-program information (DKPI) and a telemetry processing unit (BOT) that performs the functions of decoding RK and KPI, forming KB and TMI frames.

The main requirements for DKTI, in addition to the requirements of the destination: small dimensions, weight, power consumption and high reliability during the CAC.

As the closest analogue of the proposed utility model, DKTI for BA KIS can be selected, in which DKPI and BOT are separate devices (see Bulgakov NN, Alybin VG, Krivoshein AA “Features of the construction of dual-band avionics command -measurement system for controlling a spacecraft at the stage of its launch at the GSO. "Rocket and space instrument making and information technology. 2013. VI All-Russian scientific and technical conference" Actual problems of rocket and space instrument making and information . Technologies "(5-7 June 2013), pp 266-276, - M: 2014). Known DKTI, contains DKPI, BOT and switching matrix (KM). DKTI is connected to an on-board source of TMI, with a digital receiver (TsPRM) and a digital driver of a response signal (TsFOS).

A disadvantage of the known technical solution is the large size, weight and lack of reliability during the CAC, due to the following reasons:

- the mass of DKTI is increased due to the large number of connections between DKPI and BOT, including cables, transformer interface circuits and connectors;

- the reliability of the device is not high enough due to the greater number of active and passive elements than when implementing DKPI and BOT in the form of a single device;

- greater power consumption due to the need to power two devices instead of one.

In turn, the proposed utility model will eliminate these shortcomings and obtain a technical result, which consists in reducing the overall dimensions, mass, energy consumption of the DCTI while increasing reliability during the CAC.

The claimed technical result is achieved using the proposed DKTI BA KIS, which contains DKPI, BOT, program-temporary device (PVU), KM and is connected to the central control unit, CFF, source KB, source TMI, consumers RK, consumers KPI. Unlike the analogue, in the proposed DKTI BA KIS DKPI and BOT are made in the form of a single device, implemented on one programmable logic integrated circuit (FPGA). PVU is provided for parry of emergency situations in DKTI.

The proposed DKTI BA KIS is illustrated by the structural diagram, where: 1

- DKTI, 2 - a single device containing DKPI + BOT, 3 - FPGA, 4 - KM, 5 - TsPRM, 6 - TsFOS, 7 - PVU.

In DKTI 1 BA KIS DKPI and BOT 2 are made as a single device on the same board with FPGA 3. DKTI 1 BA KIS contains: inputs (RC and KPI) from TsPRM 5; inputs from the source of TMI; outputs (KB and TMI) on CFOS 6; switching matrix KM 4; software-temporary device - PVU 7. The use of FPGA 3 as a part of DKTI 1 will ensure minimum design costs, as well as maximum flexibility when upgrading equipment. DKPI and BOT 2 are functional logical blocks of FPGA 3, that is, blocks of triggers and logic elements.

Consider the work of DKTI 1 BA KIS. RCs or KPIs received from the ground station of the command and measurement system (NIS KIS) after DPCM 5 are sent to DCTI 1. RCs are decoded in FPGA 3 and after that they are sent to CM 4. Based on the results of decoding, a receipt (KB) is received, which is received at the input of DSPC 6 for further transmission to the NS KIS. Based on the results of decoding, telemetry of execution of the Republic of Kazakhstan (TM ISP) is formed. From the output of KM 4, the RCs enter the spacecraft systems for their execution. KPI is broadcast through DKTI 1 for execution in spacecraft systems. From spacecraft systems in DKTI 1, receipts (KB) are received on the performance of the RK or KPI, as well as TMI on the status of spacecraft systems. To transmit TMI to the NS KIS in the FPGA 3, a telemetric frame (TMK) is formed, which is fed to the input of the TsFOS 6, converted to the required carrier frequency, amplified and transmitted to the NS KIS. For parry of emergency situations in DKTI 1 the PVU 7 is provided, connected to KM 4.

Using DKPI and BOT, made in the form of a single device 2, implemented on one FPGA 3 allows you to:

- apply state registers inside FPGA 3 instead of the previously used three polarized relays to memorize the DKPI and BOT operating modes, exclude power commands for switching the operating modes, which significantly reduces the dimensions and weight of the device (due to miniaturization of the boards with FPGAs and elimination of connectors and cables connecting previously DKPI and BOT), and also reduces the number of cross-reservation devices;

- reduce the number of elements and connections due to the combination of two devices - DKPI and BOT in one 2, which increases the reliability of the DKTI 1 during SAS;

- use one FPGA 3 instead of the previously used two active elements in different devices, which has reduced energy consumption;

- to increase the reliability of DKTI 1 during SAS through internal redundancy in FPGA 3.

Due to the implementation in DKTI 1 DKPI and BOT in the form of a single board 2 with FPGA 3, it is possible to reduce the dimensions, weight, power consumption of DKTI 1 and increase the reliability of DKTI 1 during the CAC.

When implementing the claimed utility model in practice, the following results were obtained:

- the dimensions of the DKTI in volume terms were reduced by 50%, i.e. 7.1 dm ³ ;

- the mass of DKTI is reduced by 48%, i.e. by 4.3 kg;

- power consumption reduced by 30%;

- the calculated probability of failure-free operation for 15 years of SAS for DKTI was 0.9940 (for the analogue of DKPI and BOT - 0.9933).

Claims (1)

A decoder for command and telemetry information of the on-board equipment of the command and measurement system, comprising a decoder of one-time commands and command and program information, a telemetry processing unit, a program-time device, a switching matrix made with the possibility of connection with a digital receiver, a digital driver of a response signal, a source of receipts, source of telemetric information, consumers of one-time commands, consumers of command and program information, characterized in that the said deco p single commands and command and telemetry and program information processing unit are formed as a single unit, implemented on a programmable logic integrated circuit.

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