RU186199U1 - Program-temporary and routing device of on-board equipment of 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 claimed utility model makes it possible to use, with minimal modifications, the existing on-board equipment of the command-measuring system in advanced spacecraft using interfaces and protocols of high-speed inter-instrument information exchange and integration of on-board systems of SpaceWire spacecraft. The proposed interface can be used to receive technological commands and control commands for the program-time and routing device. A program-time and routing device containing a programmable logic integrated circuit using the complex SpaceWire functional unit, a SpaceWire router and a time-stamping unit are connected to a command-program and telemetry information decoder, an on-board synchronization device, an on-board control complex, and on-board tele-signaling equipment.

Description

The utility model relates to the field of computer technology and is intended for use in the on-board equipment (BA) of a command-measuring system (CIS) for controlling a spacecraft (SC). BA KIS is designed to receive one-time commands (RK) and command and program information (KPI) from earth stations (AP) KIS, to decode and relay them to airborne systems, as well as to generate receipts (HF) and telemetry frames (TMK) and transmit them at the ZIS KIS.

The closest analogue of the proposed utility model is the program-temporary device (PVU) BA KIS, known from the patent for utility model RU 168 932, published in 2017. RU 168 932 PVU is used as part of the command and telemetry information decoder (DKTI) BA KIS. The proposed decoder of command and telemetric information on-board equipment of the 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 on-board sources of receipts and telemetric 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.

However, this technical solution has its drawbacks, such as: an increase in the number of technological control commands is impossible without increasing the input cascades of reception, there is no possibility of receiving control commands during normal operation, and there are restrictions on the use of BA KIS in promising spacecraft using SpaceWire.

 Practical application of the proposed utility model will make it possible to use the currently existing BA KIS in promising spacecraft with minimal modifications to the equipment, ensuring the receipt of technological and full-time PVU commands via the interface of high-speed inter-instrument information exchange and integration of onboard spacecraft systems - SpaceWire, as well as expand the functionality of the BA KIS while maintaining weight and size characteristics, which leads to increased reliability of the reception of technological control commands.

The proposed FPGA, in contrast to the analogue, includes a programmable logic integrated circuit (FPGA) using the complex SpaceWire functional block (SFB) and connects to the DCTI through the SpaceWire router.

The proposed utility model is illustrated by a structural diagram, where:

1 - three sets of DKTI-1, DKTI-2, DKTI-3,

2 - two sets of PVMU-1 and PVMU-2,

3 - FPGA

4 - SpaceWire router,

5 - block issuing time stamps (BVM),

6 - switching distribution device (switchgear),

7 - duplicated onboard synchronization device (BSU),

8 - duplicated onboard control complex (BKU),

9 - duplicated on-board signaling equipment (BATS).

PVMU 2 is two independent sets: PVMU-1 and PVMU-2. Each set of FDAU 2 consists of three independent BVM 5. BVM 5 of each set gives out time stamps, which are used to switch the DKTI 1 sets and the transmitter-receiver unit (PPU) in case of their failure and to control the operating modes of the PPU and
DCTI 1.

Each set produces a sequence of four time stamps: M24, M1, M2 and M3. PVMU-1 issues M24 tags with a period of 24 h ± 5 min after 24 h ± 5 min after power is supplied. PVMU-2 issues M24 tags with a period of 24 h ± 5 min after 26 h ± 5 min after power supply. Label M1 is issued 15 minutes ± 5 s after the issuance of label M24. Label M2 is issued after 30 min ± 5 s after issuing the label M24. The M3 mark is issued 45 minutes ± 5 s after the M24 mark is issued. The duration of the issuance of all tags is (40 - 100) ms.

The control of the FDAU 2 is carried out according to PK040 and PK045 coming from the SpaceWire 4 router to FPGA 3. Both RCs restart the FDA. After processing PK045, PVMU-1 issues the M24 mark after 24 h ± 5 min, PVMU-2 - after 26 h ± 5 min. The period of issue of marks M24 and the time of issue of marks M1, M2 and M3 are saved. After processing PK040, PVMU-1 issues the M24 mark after 12 h ± 5 min, PVMU2 - after 14 h ± 5 min. The period of issuing labels M24 becomes equal to 12 h ± 5 min, the time of issuing labels M1, M2 and M3 does not change. The duration of all issued tags is saved.

Instead of the optoelectronic cascades previously allocated for each technological team separately, the SpaceWire 4 router is also used to transmit 2 technological commands to the PFMU, which allows not to increase the weight and size parameters of the FFMU2.

To verify the operation of the FDAU 2, technological teams are provided: “Acceleration”, “Block 1”, “Block 2”, “Block 3”.

The Acceleration command allows you to accelerate the issuance of all timestamps by 30 times. In this case, PVMU-1 will give out the M24 mark with a period of (48 ± 5) minutes after (48 ± 5) min after restarting, PVMU-2 will give out the M24 mark with a period of (48 ± 5) minutes after (52 ± 5) min after restart. Label M1 will be issued after (30 ± 5) s, M2 - after 1 min ± 5 s, M3 - after 1.5 min ± 5 s after issuing the mark M24.

The commands "Block 1", "Block 2" and "Block 3" allow you to block the issuance of time stamps from the first, second and third computers of both sets of FDA2.

PVMU 2 is also used as a routing device between DKTI 1, BKU 8, BATS 9 and BSU 7, allowing you to exchange the following types of information: RK and KPI from DKTI 1 in BKU 8, receipts on the RK and KPI from BKU 8 in DKTI 1, telemetry information (TMI) from BATS 9 in DKTI 1, a request for TMI from DKTI 1 in BATS 9, the code for the on-board time scale (BSW) from BSU 7 in DKTI 1.

In practical use of the proposed utility model, the existing BA KIS can be used with minimal modifications in advanced spacecraft using interfaces and protocols of high-speed inter-instrument information exchange and integration of SpaceWire spacecraft onboard systems.

Claims (4)

The program-temporary and routing device of the on-board equipment of the command-measuring system associated with the decoder of the command-program and telemetric information, characterized in that it includes interconnected through a switchgear the first programmable logic integrated circuit using the complex SpaceWire functional unit connected to the decoder of command-program and telemetry information via the SpaceWire router and a second programmable logic integrated circuit using the complex SpaceWire function block, connected to the decoder of command-program and telemetry information via the SpaceWire router.

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